Abstract

The present invention concerns an optical metrology system (1) comprising an active unit (AU, 2, 6), a first passive unit (PU1, 3, 51) that includes a first mirror (11) and a first polarizer (19), and a second passive unit (PU2, 4, 52) that includes a second mirror (12) and a second polarizer (19), wherein the first (PU1, 3, 51) and the second passive units (PU2, 4, 52) are coupled: with a first object/target and a second object/target, respectively; or one with a given object/target and the other with a reference frame/system. The active unit (AU, 2, 6) includes: a light source (13, 60) designed to emit a light signal that includes a first light component at a first wavelength (λ1) and a second light component at a second wavelength (λ2); optical means designed to direct the light signal emitted by the light source (13, 60) toward the first passive unit (PU1, 3, 51) along a first optical path; a dichroic optical element (14, 66) that is arranged on the first optical path between the optical means and the first passive unit (PU1, 3, 51) and is designed to cause the first light component to continue propagating along the first optical path up to the first passive unit (PU1, 3, 51), whereby said first light component is reflected by the first mirror (11) while the first polarizer (19) applies a linear polarization to said first light component, the second light component to propagate from the dichroic optical element (14, 66) along a second optical path up to the second passive unit (PU2, 4, 52), whereby said second light component is reflected by the second mirror (12) while the second polarizer (19) applies a linear polarization to said second light component, and the reflected first and second light components coming from the first (PU1, 3, 51) and the second passive units (PU2, 4, 52) to propagate from said dichroic optical element (14, 66) along the first optical path toward the optical means; a detector (15, 611) for measuring relative pitch and yaw angles between the first and the second objects/targets, or absolute pitch and yaw angles of the given target with respect to the reference frame/system; and a polarimeter-based detector (18, 612) for measuring relative roll angle between the first and the second objects/targets, or absolute roll angle of the given target with respect to the reference frame/system. The optical means are further designed to direct the reflected first and second light components coming from the dichroic optical element (14, 66) toward the detector (15, 611) and the polarimeter-based detector (18, 612).

IPC Classes  ?

• G01S 17/88 - Lidar systems, specially adapted for specific applications
• G01S 7/481 - Constructional features, e.g. arrangements of optical elements
• G01S 17/66 - Tracking systems using electromagnetic waves other than radio waves
• G01S 17/46 - Indirect determination of position data
• G01S 7/499 - Details of systems according to groups , , of systems according to group using polarisation effects
• G01B 11/26 - Measuring arrangements characterised by the use of optical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of optical techniques for testing the alignment of axes

Abstract

A fully-reconfigurable coaxial filter is provided that includes coaxial resonators mounted such that both opposite ends are coupleable to corresponding tuners, first tuners made of dielectric material, each first tuner being slidably mounted at a first end of a corresponding coaxial resonator to be movable relative to the first end to form a dielectric of a capacitive load, and second tuners made of dielectric material, each second tuner being slidably mounted at a second end of a corresponding coaxial resonator to be movable relative to the second end to form a dielectric of a capacitive load associated with the second end of the corresponding coaxial resonator. The first and second tuners are movable relative to the corresponding coaxial resonator so as to tune the capacitive loads associated with the opposite ends of the coaxial resonator and, resultingly, a resonant frequency and mutual coupling coefficient of the coaxial resonator.

IPC Classes  ?

• H01P 1/20 - Frequency-selective devices, e.g. filters
• H01P 7/04 - Coaxial resonators

Abstract

A connection unit comprising two female connectors configured to be connected to respective circuit branches of a fluidic line and a coupling element for coupling the connectors together and establish a fluidic connection between the circuit branches, wherein the connectors are provided with first, normally closed sealing elements to define a sealing termination of the circuit branches when the connectors are disconnected from each other; the coupling element includes a double-male connector separable from the female connectors and provided with a pair of shanks that can be coupled to the respective female connectors and a control element movable between a first position where the coupling element can be coupled to the connectors in a mechanical pre-coupling condition without fluidic connection between the female connectors and a second position where the shanks of the double-male connector engage the respective female connectors and establish a fluidic connection therebetween.

IPC Classes  ?

• F16L 37/36 - Couplings of the quick-acting type with fluid cut-off means with fluid cut-off means in each of two pipe-end fittings with two lift valves being actuated to initiate the flow through the coupling after the two coupling parts are locked against withdrawal
• F16L 37/096 - Couplings of the quick-acting type in which the connection between abutting or axially-overlapping ends is maintained by locking members combined with automatic locking by means of hooks hinged about an axis
• F16L 37/107 - Bayonet-type couplings
• F16L 37/113 - Couplings of the quick-acting type in which the connection between abutting or axially-overlapping ends is maintained by locking members using a rotary external sleeve or ring on one part the male part having lugs on its periphery penetrating into the corresponding slots provided in the female part
• F16L 37/32 - Couplings of the quick-acting type with fluid cut-off means with fluid cut-off means in each of two pipe-end fittings at least one of two lift valves being opened automatically when the coupling is applied
• F16L 37/35 - Couplings of the quick-acting type with fluid cut-off means with fluid cut-off means in each of two pipe-end fittings at least one of two lift valves being opened automatically when the coupling is applied at least one of the valves having an axial bore communicating with lateral apertures

Abstract

Optical unit for a projective optical metrological system, which receives a light signal coming from a light constellation comprising a number of light sources; the optical unit includes: an optoelectronic image acquisition system and a first and a second optical circuit, which receive the light signal and are traversed by a first and a second optical beam, respectively. The first and the second optical circuits direct, respectively, at least a first part of the first optical beam and at least a first part of the second optical beam on the optoelectronic image acquisition system, so as to cause the simultaneous formation of two different images of the constellation in the optoelectronic image acquisition system. The optical unit further includes an electronic processing unit coupled to the optoelectronic image acquisition system, which determines a number of quantities indicative of the position and/or attitude of the light constellation with respect to the optical unit, based on the two images. The optical unit further includes an optical receiver and a derivation optical circuit configured to optically couple the optical receiver and at least one of the first and the second optical circuit, so that the optical receiver receives an optical information signal, which is a function of at least one of the first and the second optical beams. The optical receiver demodulates digital data from the optical information signal.

IPC Classes  ?

• G01C 21/16 - NavigationNavigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigatedDead reckoning by integrating acceleration or speed, i.e. inertial navigation
• G01C 21/02 - NavigationNavigational instruments not provided for in groups by astronomical means
• H04B 7/185 - Space-based or airborne stations

Abstract

A capacitive feedthrough hermetically sealable to a hybrid module for space applications is provided that includes a multilayer ceramic structure including, on the top face, a metallized top central region designed to receive an input electrical signal to be filtered, a dielectric top region extending around the metallized top central region, and a metallized top peripheral region extending around the dielectric top region up to joining the metallized external closed side walls to act therewith as electrical ground; and, on the bottom face, a metallized bottom central region designed to provide an output filtered electrical signal, a dielectric bottom region extending around the metallized bottom central region, and a metallized bottom peripheral region extending around the dielectric bottom region up to joining the metallized external closed side walls to act therewith as electrical ground. The multilayer ceramic structure further includes ceramic layers, first metallized layers and one or more second metallized layers stacked on one another such that: each first metallized layer is interposed between two respective ceramic layers arranged immediately on and below said first metallized layer; each/the second metallized layer is interposed between two respective ceramic layers arranged immediately on and below said second metallized layer; the first and second metallized layers are vertically alternated such that each/the second metallized layer has a respective upper first metallized layer arranged above said second metallized layer, and a respective lower first metallized layer arranged below said second metallized layer; and two ceramic layers are respectively arranged immediately below the top face and immediately above the bottom face.

IPC Classes  ?

• H02G 3/22 - Installations of cables or lines through walls, floors or ceilings, e.g. into buildings
• H01G 4/30 - Stacked capacitors
• B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles

Abstract

The invention concerns a method of providing a space extended reality service on earth, comprising: acquiring, by means of one or more acquisition systems/devices (1) installed on a space platform (2), real-time data related to a surrounding space environment and/or to one or more astronauts (3) in said space environment; generating, by means of a computer graphics processing device/system (4), based on the acquired real-time data and on synthetic data, a three-dimensional extended reality environment reproducing the space environment and one or more three-dimensional avatar(s) of the astronaut(s) (3) reproducing movements and/or actions and/or facial expressions and/or voice of said astronaut(s) (3), wherein the synthetic data digitally represent the space environment and/or the astronaut(s) (3); and providing one or more users (5) on earth with a space extended reality service based on the generated three-dimensional extended reality environment and avatar(s).

IPC Classes  ?

• G06F 3/01 - Input arrangements or combined input and output arrangements for interaction between user and computer
• G06T 19/00 - Manipulating 3D models or images for computer graphics

Abstract

An evaporator assembly (2) including at. least one compensation chamber (10) and at least one capillary pump (11) comprising a primary wick (15), the evaporator assembly (2) including a secondary wick (16) extending through the at least one compensation chamber (10) and the at least one capillary pump (11) and contacting the primary wick (15) thereof; the least one compensation chamber (10) and the at least one capillary pump (11) are arranged parallel to one another along respective distinct axes (A, B).

IPC Classes  ?

• F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
• F28D 15/04 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes with tubes having a capillary structure

Abstract

A release system for the release of satellites from a launch vehicle is provided that includes: (i) a torsion bar, having a first end which is fixed by means of support means to a launch vehicle and is locked in rotation around a longitudinal axis of the torsion bar, and a second end which is connected by means of hinge means to the launch vehicle and is free to rotate around the longitudinal axis; (ii) at least one launch arm extending perpendicularly from the torsion bar and comprising (a) a torsion lever having a first end which is fixed to the torsion bar in an integral manner, and (b) a guide having a first end connected to a second end of the torsion lever, and a second free end; (iii) at least one slider which is fixed in an integral manner to a satellite to be launched and arranged to engage the guide in a sliding manner; and (iv) and a limit stop element designed to act upon the torsion lever to stop the rotation of the launch arm around the longitudinal axis.

IPC Classes  ?

• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

Abstract

A passive cyclone separator to treat a fluid in a microgravity environment to separate a liquid phase of the fluid from a gas phase of the fluid, comprising a tubular body having a longitudinal axis and internally defining a separation chamber within which the gas phase of the fluid is separable, in use, from the liquid phase of the fluid; an inlet opening through which the fluid is injectable, in use, into the separation chamber along an injection axis; a liquid phase outlet opening, through which the liquid phase separated from the gas phase exits, in use, the separation chamber; and a gas phase outlet opening, through which the gas phase separated from the liquid phase exits, in use, the separation chamber; the injection axis is inclined towards the liquid phase outlet opening so as to define a non-zero fluid injection angle with a direction orthogonal to the longitudinal axis.

IPC Classes  ?

• B04C 5/04 - Tangential inlets
• B04C 5/20 - Apparatus in which the axial direction of the vortex is reversed with heating or cooling, e.g. quenching, means
• B04C 9/00 - Combinations with other devices, e.g. fans
• B01D 19/00 - Degasification of liquids
• C02F 1/38 - Treatment of water, waste water, or sewage by centrifugal separation
• C02F 1/20 - Treatment of water, waste water, or sewage by degassing, i.e. liberation of dissolved gases

Abstract

A fully-reconfigurable coaxial filter (20) comprising: - a number of coaxial resonators (21) each mounted such that both opposite ends (21A, 21B) are coupleable to corresponding tuners (22, 23); - a number of first tuners (22) made of dielectric material, each first tuner (22) is slidably mounted at a first end (21A) of a corresponding coaxial resonator (21) to be movable relative to the first end (21A) to form a dielectric of a capacitive load associated with the first end (21A) of the corresponding coaxial resonator (21); and - a number of second tuners (23) made of dielectric material, each second tuner (23) is slidably mounted at a second end (21B), opposite to the first open end (21A), of a corresponding coaxial resonator (21) to be movable relative to the second end (21B) to form a dielectric of a capacitive load associated with the second end (21B) of the corresponding coaxial resonator (21); whereby the first and second tuners (22, 23) are movable relative to the corresponding coaxial resonator (21) so as to tune the capacitive loads associated with the opposite ends (21A, 21B) of the coaxial resonator (21) and, resultingly, a resonant frequency and a mutual coupling coefficient of the coaxial resonator (21).

IPC Classes  ?

• H01P 1/205 - Comb or interdigital filtersCascaded coaxial cavities

Abstract

An on-orbit servicing spacecraft includes an engagement system to engage a space vehicle or object to be serviced or tugged, so as to form a space system, and an electronic reaction control system to cause the spacecraft to rotate about roll, yaw, and pitch axes to control attitude and displacement along given trajectories to cause the spacecraft to carry out given maneuvers. The electronic reaction control system includes (i) a sensory system to directly sense physical quantities or allow physical quantities to be indirectly computed based on sensed physical quantities, including one or more of position, attitude, angular rates, available fuel, geometrical features, and on-board systems state, (ii) attitude control thrusters mounted so as to allow their positions and orientations to be adjustable, and (iii) an attitude control computer in communication with the sensory system and the attitude control thrusters and programmed to receive data from the sensory system and to control, based on the received data, positions, orientations, and operating states of the attitude control thrusters so as to control attitude and position of the spacecraft. The attitude control computer is programmed to cause the spacecraft to carry out a given mission including an engagement step, in which the engagement system and the attitude control thrusters are controlled by the attitude control computer to engage a space vehicle or object to be serviced or tugged, and one or more operating steps, in each of which the attitude control thrusters are controlled by the attitude control computer to meet one or more requirements established for the operating step.

IPC Classes  ?

• B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles
• B64G 1/24 - Guiding or controlling apparatus, e.g. for attitude control
• B64G 1/26 - Guiding or controlling apparatus, e.g. for attitude control using jets
• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

Abstract

An optical flow odometer to determine the position of an object movable relatively to a surface is provided that includes a cluster of digital image sensors intended to be arranged on the movable object at respective reference positions and an electronic processing and control unit electrically connected with the digital image sensors and configured to: operate the digital image sensors in subsequent time instants during movement of the movable object so as to carry out a sequence of multiple digital image capture operations, in each of which the digital image sensors are operated to simultaneously capture respective digital images, and receive from the digital image sensors and process the digital images captured in the multiple digital image capture operations to compute either the positions of the individual digital image sensors or the position of the cluster of digital image sensors at one or more of the multiple digital image capture operations, and compute the position of the movable object at one or more multiple digital image capture operations based on either the positions of one or more individual digital image sensors or the position of the cluster of digital image sensors computed at one or more multiple digital image capture operations.

IPC Classes  ?

• G06T 7/73 - Determining position or orientation of objects or cameras using feature-based methods
• G06T 7/60 - Analysis of geometric attributes
• B64G 1/66 - Arrangements or adaptations of apparatus or instruments, not otherwise provided for

Abstract

The present invention concerns a method for performing SAR acquisitions, which comprises performing SAR acquisitions in Spotlight/Stripmap mode of areas/swaths of earth's surface by means of a SAR system carried by an air or space platform along a flight direction, whereby: an azimuth direction is defined by a ground track of the flight direction on the earth's surface, a nadir direction is defined that is orthogonal to the earth's surface, to the flight direction and to the azimuth direction, an across-track direction is defined that lies on the earth's surface and is orthogonal to the azimuth direction and to the nadir direction, and, for each acquired area/swath of the earth's surface, a respective range direction is defined that extends from the synthetic aperture radar system to said acquired area/swath. Performing SAR acquisitions in Spotlight/Stripmap mode of areas/swaths of earth's surface includes contemporaneously acquiring P areas or portions of P swaths in a pulse repetition interval having a predefined time length, P being an integer greater than one. Said P areas/swaths are separated along the across-track direction and are spaced apart from each other along the across-track direction and from the SAR system along the respective range direction by predefined distances. Said predefined time length and said predefined distances are such that to enable contemporaneous acquisition of said P areas or of portions of said P swaths in said pulse repetition interval.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

The present invention concerns a method for performing SAR acquisitions, which comprises performing, in a time division fashion, SAR acquisitions of areas of a swath of earth's surface by means of a SAR system carried by an air or space platform; wherein performing SAR acquisitions in a time division fashion includes contemporaneously acquiring, in each pulse repetition interval, a plurality of areas of the swath that are separated in azimuth; and wherein the areas acquired in T successive pulse repetition intervals form an azimuth-continuous portion of said swath, T being an integer greater than one.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

The present invention concerns a capacitive feedthrough (1) hermetically sealable to a hybrid module for space applications, comprising a multilayer ceramic structure that has: two opposite external faces including a top face (10) and bottom face (20); and metallized external closed side walls (31, 32, 33, 34) vertically extending between said opposite external faces (10, 20) around the multilayer ceramic structure. The multilayer ceramic structure includes: on the top face (10), a metallized top central region (11) designed to receive an input electrical signal to be filtered, a dielectric top region (12) extending around the metallized top central region (11), and a metallized top peripheral region (13) extending around the dielectric top region (12) up to joining the metallized external closed side walls (31, 32, 33, 34) to act therewith as electrical ground, wherein the dielectric top region (12) is designed to ensure electrical insulation between the input electrical signal and the electrical ground; and, on the bottom face (20), a metallized bottom central region (21) designed to provide an output filtered electrical signal, a dielectric bottom region (22) extending around the metallized bottom central region (21), and a metallized bottom peripheral region (23) extending around the dielectric bottom region (22) up to joining the metallized external closed side walls (31, 32, 33, 34) to act therewith as electrical ground, wherein the dielectric bottom region (22) is designed to ensure electrical insulation between the output filtered electrical signal and the electrical ground. The multilayer ceramic structure further including ceramic layers (41, 42, 43, 44, 45, 46, 47, 48), first metallized layers (51, 53, 55, 57) and one or more second metallized layers (52, 54, 56) stacked on one another such that: each first metallized layer (51, 53, 55, 57) is interposed between two respective ceramic layers (41, 42, 43, 44, 45, 46, 47, 48) arranged immediately on and below said first metallized layer (51, 53, 55, 57); each/the second metallized layer (52, 54, 56) is interposed between two respective ceramic layers (42, 43, 44, 45, 46, 47) arranged immediately on and below said second metallized layer (52, 54, 56); the first and second metallized layers (51, 52, 53, 54, 55, 56, 57) are vertically alternated such that each/the second metallized layer (52, 54, 56) has a respective upper first metallized layer (53, 55, 57) arranged above said second metallized layer (52, 54, 56), and a respective lower first metallized layer (51, 53, 55) arranged below said second metallized layer (52, 54, 56); and two ceramic layers (41, 48) are respectively arranged immediately below the top face (10) and immediately above the bottom face (11). The first metallized layers (51, 53, 55, 57) are joined to the metallized external closed side walls (31, 32, 33, 34), whereby said first metallized layers (51, 53, 55, 57), said metallized external closed side walls (31, 32, 33, 34) and said metallized top and bottom peripheral regions (13, 23) form an electrical ground structure. Each/the second metallized layer (52, 54, 56) is separated from the metallized external closed side walls (31, 32, 33, 34) by a respective first dielectric gap designed to ensure electrical insulation between said second metallized layer (52, 54, 56) and the electrical ground structure. Each/the second metallized layer (52, 54, 56) is connected to: an upper second metallized layer (52, 54, 56), or the metallized top central region (11), by means of a respective first electrically conductive via (62, 63, 64) that vertically extends between said second metallized layer (52, 54, 56) and said upper second metallized layer (52, 54, 56) the metallized top central region (11) through upper ceramic layers (43, 44, 45, 46, 47, 48) and the respective upper first metallized layer (53, 55, 57), wherein said respective first electrically conductive via (62, 63, 64) is separated from said respective upper first metallized layer (53, 55, 57) by a respective second dielectric gap extending around said respective first electrically conductive via (62, 63, 64), thereby forming a respective first capacitor; and a lower second metallized layer (52, 54, 56), or the metallized bottom central region (21), by means of a respective second electrically conductive via (61, 62, 63) that vertically extends between said second metallized layer (52, 54, 56) and said lower second metallized layer (52, 54, 56) the metallized bottom central region (21) through lower ceramic layers (41, 42, 43, 44, 45, 46) and the respective lower first metallized layer (51, 53, 55), wherein said respective second electrically conductive via (61, 62, 63) is separated from said respective lower first metallized layer (51, 53, 55) by a respective third dielectric gap extending around said respective second electrically conductive via (61, 62, 63), thereby forming a respective second capacitor. The metallized top and bottom central regions (11, 21) and the second metallized layer(s) (52, 54, 56) along with the respective electrically conductive vias (61, 62, 63, 64) and the respective capacitors form a capacitive feedthrough structure configured to receive the input electrical signal at/on the metallized top central region (11) and to provide the output filtered electrical signal at/on the metallized bottom central region (21), whereby filtering of the input electrical signal is carried out by the capacitors. The metallized top and bottom central regions (11, 21) are planar regions with no apertures.

IPC Classes  ?

• H01P 1/20 - Frequency-selective devices, e.g. filters
• H01P 3/08 - MicrostripsStrip lines
• H03H 1/00 - Constructional details of impedance networks whose electrical mode of operation is not specified or applicable to more than one type of network
• H01G 4/35 - Feed-through capacitors or anti-noise capacitors
• H05K 1/02 - Printed circuits Details

Abstract

12112212122). The optical receiver (30) demodulates digital data from the optical information signal (OIS).

IPC Classes  ?

• H04B 10/118 - Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
• G01C 11/00 - Photogrammetry or videogrammetry, e.g. stereogrammetryPhotographic surveying
• G01S 17/46 - Indirect determination of position data

Abstract

A supporting frame for aerospace applications comprises a plurality of rods, which are arranged along two bases substantially parallel and opposite each other, and along two sides, which are substantially parallel and opposite to each other and are coupled to each other via the two bases; the rods are coupled to each other in a mutually rotating manner by nodes so as to be able to configure the supporting frame between a deployed operating condition and a compacted operating condition; the nodes are spaced apart from one another in the deployed operating condition and are each hinged to at least two of the rods; in the compacted operating condition, each of the nodes is placed side by side with two adjacent nodes so as to form, together, two supporting members arranged at opposite longitudinal ends of the supporting frame and each being ring-shaped.

IPC Classes  ?

• B64G 1/60 - Crew or passenger accommodations
• B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles

Abstract

A connection unit comprising two female connectors (2, 3) configured to be connected to respective circuit branches of a fluidic line and a coupling element (4) for coupling said connectors (2, 3) together and establish a fluidic connection between the circuit branches, wherein said connectors (2, 3) are provided with first, normally closed sealing elements (30) to define a sealing termination of said circuit branches when the connectors (2, 3) are disconnected from each other; the coupling element (4) includes a double-male connector (50) separable from the female connectors (2, 3) and provided with a pair of shanks (68) that can be coupled to the respective female connectors (2, 3) and a control element (70) movable between a first position where the coupling element (4) can be coupled to the connectors (2, 3) in a mechanical pre-coupling condition without fluidic connection between the female connectors (2, 3) and a second position where the shanks (68) of the double-male connector (50) engage the respective female connectors (2, 3) and establish a fluidic connection therebetween.

IPC Classes  ?

• F16L 37/113 - Couplings of the quick-acting type in which the connection between abutting or axially-overlapping ends is maintained by locking members using a rotary external sleeve or ring on one part the male part having lugs on its periphery penetrating into the corresponding slots provided in the female part
• F16L 37/40 - Couplings of the quick-acting type with fluid cut-off means with fluid cut-off means in only one of two pipe-end fittings with a lift valve being opened automatically when the coupling is applied
• F16L 37/32 - Couplings of the quick-acting type with fluid cut-off means with fluid cut-off means in each of two pipe-end fittings at least one of two lift valves being opened automatically when the coupling is applied
• F16L 37/096 - Couplings of the quick-acting type in which the connection between abutting or axially-overlapping ends is maintained by locking members combined with automatic locking by means of hooks hinged about an axis
• F16L 37/36 - Couplings of the quick-acting type with fluid cut-off means with fluid cut-off means in each of two pipe-end fittings with two lift valves being actuated to initiate the flow through the coupling after the two coupling parts are locked against withdrawal

Abstract

A surface bio-contamination assay kit (1) comprising a disposable swab cartridge (2) comprising a swab (29); a sampler (3) designed to removably receive the cartridge (2) and to wipe the cartridge swab (29) on a surface to be collect a sampled, along a predetermined sampling path (4) designed to cover a predetermined surface area; and a bio-contamination meter (5) designed to removably receive the cartridge (2) after sampling and to measure bio-contamination of the collected sample on the cartridge (2).

IPC Classes  ?

• B01L 3/00 - Containers or dishes for laboratory use, e.g. laboratory glasswareDroppers
• G01N 1/02 - Devices for withdrawing samples
• G01N 21/76 - ChemiluminescenceBioluminescence

Abstract

A localization method for locating a target that is coupled with a locator transponder associated with a permanent identification code permanently assigned to the locator transponder is provided. The localization method includes: a) transmitting a spread spectrum paging signal carrying the permanent identification code and a shorter temporary identification code temporarily assigned to the locator transponder; b) receiving the spread spectrum paging signal and extracting the temporary identification code carried by the received spread spectrum paging signal; c) transmitting radar signals towards area(s) of earth's surface or sky and receiving echo signals therefrom; d) upon reception by the locator transponder of radar signal(s), generating and transmitting a sequence of watermarked radar echo signals in which a spread spectrum watermarking signal is embedded that includes the temporary identification code; e) carrying out localization operations; f) transmitting frequency-synchronization-aid signal(s); g) receiving the frequency-synchronization-aid signal(s) and estimating a frequency drift affecting a reference frequency provided by a local oscillator of the locator transponder; wherein the locator transponder transmits the sequence of watermarked radar echo signals by using a transmission carrier frequency obtained based on the reference frequency provided by the local oscillator and on the estimated frequency drift.

IPC Classes  ?

• G01S 13/82 - Systems using reradiation of radio waves, e.g. secondary radar systemsAnalogous systems wherein continuous-type signals are transmitted
• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• G01S 7/40 - Means for monitoring or calibrating

Abstract

A release system (1) for the release of satellites from a launch vehicle comprising: (i) a torsion bar (2), having a first end (2a) which is fixed by means of support means (4) to a launch vehicle (3) and is locked in rotation around a longitudinal axis (X) of the torsion bar (2), and a second end (2b) which is connected by means of hinge means (5) to the launch vehicle (3) and is free to rotate around the longitudinal axis (X); (ii) at least one launch arm (6) extending perpendicularly from the torsion bar (2) and comprising (a) a torsion lever (7) having a first end (7a) which is fixed to the torsion bar (2) in an integral manner, and (b) a guide (8) having a first end (8a) connected to a second end (7b) of the torsion lever (7), and a second free end (8b); (iii) at least one slider (10) which is fixed in an integral manner to a satellite (18) to be launched and arranged to engage the guide (8) in a sliding manner; (iv) and a limit stop element (12) designed to act upon the torsion lever (7) to stop the rotation of the launch arm (6) around the longitudinal axis (X).

IPC Classes  ?

• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

Abstract

A passive cyclone separator (3) to treat a fluid in a microgravity environment to separate a liquid phase of the fluid from a gas phase of the fluid, comprising a tubular body (7) having a longitudinal axis (A) and internally defining a separation chamber (8) within which the gas phase of the fluid is separable, in use, from the liquid phase of the fluid; an inlet opening (10) through which the fluid is injectable, in use, into the separation chamber (8) along an injection axis (B); a liquid phase outlet opening (11), through which the liquid phase separated from the gas phase exits, in use, the separation chamber (8); and a gas phase outlet opening (13), through which the gas phase separated from the liquid phase exits, in use, the separation chamber (8); the injection axis (B) is inclined towards the liquid phase outlet opening (11) so as to define a non-zero fluid injection angle (α) with a direction (C) orthogonal to the longitudinal axis (A).

IPC Classes  ?

• B04C 5/04 - Tangential inlets
• B04C 9/00 - Combinations with other devices, e.g. fans

Abstract

An on-orbit servicing spacecraft (1) comprising an engagement system (4) to engage a space vehicle or object (5) to be serviced or tugged, so as to form a space system (6); and an electronic reaction control system (7) to cause the spacecraft (1) to rotate about roll, yaw, and pitch axes to control attitude and displacement along given trajectories to cause the spacecraft (1) to carry out given manoeuvres. The electronic reaction control system (7 ) comprises a sensory system (8 ) to directly sense physical quantities or allow physical quantities to be indirectly computed based on sensed physical quantities comprising one or more of position, attitude, angular rates, available fuel, geometrical features, and onboard systems state; attitude control thrusters (9) mounted so as to allow their positions and orientations to be adjustable; and an attitude control computer (10) in communication with the sensory system (8) and the attitude control thrusters (9) and programmed to receive data from the sensory system (8) and to control, based on the received data, positions, orientations, and operating states of the attitude control thrusters (9) so as to control attitude and position of the spacecraft (l).The attitude control computer (10) is programmed to cause the spacecraft (1) to carry out a given mission comprising an engagement step, in which the engagement system (4) and the attitude control thrusters (9) are controlled by the attitude control computer (10) to engage a space vehicle or object (5) to be serviced or tugged, and one or more operating steps, in each of which the attitude control thrusters (9) are controlled by the attitude control computer (10) to meet one or more requirements established for the operating step. Each operating step may comprise at least one stabilisation sub-step (FS), during which the attitude of the space system (6) is stabilised in accordance with the requirements of the operating step and with a given optimisation criterion, followed by a steady operating sub-step (FR), which starts when the stabilisation sub-step of the attitude of the space system (6) ends. In each operating step the attitude control computer (10) is further programmed to optimise a configuration of the attitude control thrusters (9) in accordance with the requirements of the operating step by implementing an iterative process of optimisation of the configuration of the attitude control thrusters (9).

IPC Classes  ?

• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
• B64G 1/24 - Guiding or controlling apparatus, e.g. for attitude control
• B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles
• B64G 1/26 - Guiding or controlling apparatus, e.g. for attitude control using jets

Goods & Services

Structures and transportable buildings of metal; Shelters of metal. Measuring devices; Temperature measuring instruments; Apparatus and instruments for accumulating and storing electricity; Apparatus and instruments for controlling electricity; Accumulators and power distributors [electrical]; Remote data and communication processing, management and control software. Medical apparatus and instruments none of them being used in extracorporeal treatment or renal insufficiency. Air-conditioning apparatus; Heating; Ventilating; Air treatment equipment; Sanitary apparatus and installations; water supply and sanitation equipment; Water purification, desalination and conditioning installations; Sterilization, disinfection and decontamination equipment; Refrigerating and freezing equipment. Structures and transportable buildings, not of metal; Shelters (Non-metallic -). Treatment and transformation of materials; Air purification and sanitisation.

Goods & Services

Software for online, interactive and virtual reality games. Medical apparatus and instruments. Articles of clothing, footwear and headgear. Sporting goods, gymnastic and sporting articles. Transmission of televised content. Arranging of transportation for travel tours. providing interactive online games; Providing online virtual reality games; Entertainment for matching users with online game software. Development and design of online, interactive and virtual reality games. Providing of food and drink and temporary accommodation.

Abstract

An optical flow odometer (2) to determine the position of an object (1) movable relatively to a surface. The optical flow odometer (1) comprises: a cluster of digital image sensors (3) intended to be arranged on the movable object (1) at respective reference positions; and an electronic processing and control unit (4) electrically connected with the digital image sensors (3) and configured to: operate the digital image sensors (3) in subsequent time instants during movement of the movable object (1) so as to carry out a sequence of multiple digital image capture operations, in each of which the digital image sensors (3) are operated to simultaneously capture respective digital images; and ° receive from the digital image sensors and process the digital images (3) captured in the multiple digital image capture operations to compute either the positions of the individual digital image sensors (3) or the position of the cluster of digital image sensors (3) at one or more of the multiple digital image capture operations; and ° compute the position of the movable object (1) at one or more multiple digital image capture operations based on either the positions of one or more individual digital image sensors (3) or the position of the cluster of digital image sensors (3) computed at one or more multiple digital image capture operations.

IPC Classes  ?

• G06K 9/00 - Methods or arrangements for reading or recognising printed or written characters or for recognising patterns, e.g. fingerprints
• B61L 25/02 - Indicating or recording positions or identities of vehicles or trains
• G01C 22/00 - Measuring distance traversed on the ground by vehicles, persons, animals or other moving solid bodies, e.g. using odometers or using pedometers
• G06K 9/20 - Image acquisition
• G05D 1/02 - Control of position or course in two dimensions
• G06T 7/70 - Determining position or orientation of objects or cameras

Abstract

An optical flow odometer (2) to determine the position of an object (1) movable relatively to a surface. The optical flow odometer (1) comprises: a cluster of digital image sensors (3) intended to be arranged on the movable object (1) at respective reference positions; and an electronic processing and control unit (4) electrically connected with the digital image sensors (3) and configured to: operate the digital image sensors (3) in subsequent time instants during movement of the movable object (1) so as to carry out a sequence of multiple digital image capture operations, in each of which the digital image sensors (3) are operated to simultaneously capture respective digital images; and ° receive from the digital image sensors and process the digital images (3) captured in the multiple digital image capture operations to compute either the positions of the individual digital image sensors (3) or the position of the cluster of digital image sensors (3) at one or more of the multiple digital image capture operations; and ° compute the position of the movable object (1) at one or more multiple digital image capture operations based on either the positions of one or more individual digital image sensors (3) or the position of the cluster of digital image sensors (3) computed at one or more multiple digital image capture operations.

IPC Classes  ?

• G01C 22/00 - Measuring distance traversed on the ground by vehicles, persons, animals or other moving solid bodies, e.g. using odometers or using pedometers
• G06T 7/70 - Determining position or orientation of objects or cameras
• G06V 20/10 - Terrestrial scenes
• G06V 20/56 - Context or environment of the image exterior to a vehicle by using sensors mounted on the vehicle
• B61L 25/02 - Indicating or recording positions or identities of vehicles or trains

Abstract

The invention concerns a satellite deployment system (30) for launch vehicles. Said satellite deployment system (30) comprises an outer dispenser (31) that is fitted, externally, with first releasable attachment means for releasably attaching first satellites (81) to said outer dispenser (31) and, internally, with an internal housing volume (310). Moreover, the satellite deployment system (30) further comprises at least an inner dispenser (32,33) that is externally fitted with second releasable attachment means for releasably attaching second satellites (82,83) to said inner dispenser (32,33), and that is accommodated in the internal housing volume (310) of the outer dispenser (31).

IPC Classes  ?

• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

Abstract

The present invention concerns a method for performing SAR acquisitions, which comprises performing SAR acquisitions in Spotlight/Stripmap mode of areas/swaths of earth's surface by means of a SAR system carried by an air or space platform along a flight direction, whereby: an azimuth direction is defined by a ground track of the flight direction on the earth's surface, a nadir direction is defined that is orthogonal to the earth's surface, to the flight direction and to the azimuth direction, an across-track direction is defined that lies on the earth's surface and is orthogonal to the azimuth direction and to the nadir direction, and, for each acquired area/swath of the earth's surface, a respective range direction is defined that extends from the synthetic aperture radar system to said acquired area/swath. Performing SAR acquisitions in Spotlight/Stripmap mode of areas/swaths of earth's surface includes contemporaneously acquiring P areas or portions of P swaths in a pulse repetition interval having a predefined time length, P being an integer greater than one. Said P areas/swaths are separated along the across-track direction and are spaced apart from each other along the across-track direction and from the SAR system along the respective range direction by predefined distances. Said predefined time length and said predefined distances are such that to enable contemporaneous acquisition of said P areas or of portions of said P swaths in said pulse repetition interval.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

The present invention concerns a method for performing SAR acquisitions, which comprises performing, in a time division fashion, SAR acquisitions of areas of a swath of earth's surface by means of a SAR system carried by an air or space platform; wherein performing SAR acquisitions in a time division fashion includes contemporaneously acquiring, in each pulse repetition interval, a plurality of areas of the swath that are separated in azimuth; and wherein the areas acquired in T successive pulse repetition intervals form an azimuth-continuous portion of said swath, T being an integer greater than one.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

TTT being an integer greater than one.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

A Reference Time Scale Dissemination System (RTS-DS) is provided that includes a RTS Dissemination Data Provider (RTS-DDP) and a User Terminal. The RTS Dissemination Data Provider is equipped with a radio receiver designed to receive radio signals and to compute a RTS-DDP Computed Time Scale based on received radio signals. The User Terminal (UT) is equipped with a Radio Receiver designed to receive radio signals and to compute a UT Computed Time Scale based on received radio signals, and with a Clock Device designed to be locked to the UT Computed Time Scale and to provide a UT Local Time Scale resultingly locked to the UT Computed Time Scale. The RTS-DPP is designed to receive a Reference Time Scale, and compute, at a RTS-DDP Computed Time, Time Quantities indicative of a difference between the RTS-DDP Computed Time Scale and the received Reference Time Scale, including a Time Scatter indicative of a difference between the RTS-DDP Computed Time and a corresponding Reference Time, and a Time Offset indicative of a mean value, computed over a timespan, of a number of differences between RTS-DDP Computed Times and corresponding Reference Times.

IPC Classes  ?

• H04L 43/106 - Active monitoring, e.g. heartbeat, ping or trace-route using time related information in packets, e.g. by adding timestamps
• H04W 56/00 - Synchronisation arrangements
• G04G 5/00 - Setting, i.e. correcting or changing, the time-indication
• G04G 7/00 - Synchronisation
• H04J 3/06 - Synchronising arrangements
• H04B 7/26 - Radio transmission systems, i.e. using radiation field for communication between two or more posts at least one of which is mobile
• H04W 84/06 - Airborne or Satellite Networks
• H03K 5/135 - Arrangements having a single output and transforming input signals into pulses delivered at desired time intervals by the use of time reference signals, e.g. clock signals
• H04L 9/32 - Arrangements for secret or secure communicationsNetwork security protocols including means for verifying the identity or authority of a user of the system
• H02P 6/15 - Controlling commutation time

Abstract

A supporting frame (1) for aerospace applications comprises a plurality of rods (2a,2b,2c,2d,2e), which are arranged along two bases (3) substantially parallel and opposite each other, and along two sides (10), which are substantially parallel and opposite to each other and are coupled to each other via the two bases (3); the rods are coupled to each other in a mutually rotating manner by nodes (15,16) so as to be able to configure the supporting frame (1) between a deployed operating condition and a compacted operating condition; the nodes (15,16) are spaced apart from one another in the deployed operating condition and are each hinged to at least two of the rods (2a,2b,2c,2d); in the compacted operating condition, each of the nodes is placed side by side with two adjacent nodes so as to form, together, two supporting members (18) arranged at opposite longitudinal ends of the supporting frame (1) and each being ring-shaped.

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
• B61D 17/04 - Construction details of vehicle bodies with bodies of metalConstruction details of vehicle bodies with composite, e.g. metal and wood, body structures
• B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• B64G 1/60 - Crew or passenger accommodations
• B64G 99/00 - Subject matter not provided for in other groups of this subclass
• E04B 1/344 - Structures characterised by movable, separable, or collapsible parts, e.g. for transport with hinged parts

Abstract

The invention concerns a localization method for locating a target that is coupled with a locator transponder (24) associated with a permanent identification code permanently assigned to said locator transponder (24). The localization method comprises: a) upon reception of a user request for locating the target, transmitting, by a radio communications system (22), a spread spectrum paging signal carrying the permanent identification code and a temporary identification code temporarily assigned to the locator transponder (24), wherein said temporary identification code is shorter than said permanent identification code; b) receiving, by the locator transponder (24), the spread spectrum paging signal and extracting, by said locator transponder (24), the temporary identification code carried by the received spread spectrum paging signal; c) transmitting, by a radar-based system (23), radar signals towards one or more areas of earth's surface or sky and receiving, by said radar-based system (23), echo signals from said one or more areas of the earth's surface or sky; d) upon reception by the locator transponder (24) of one or more radar signals transmitted by the radar-based system (23), generating and transmitting, by said locator transponder (24), a sequence of watermarked radar echo signals in which a spread spectrum watermarking signal is embedded, wherein said spread spectrum watermarking signal carries the temporary identification code extracted; and e) carrying out, by the radar-based system (23), localization operations that include: detecting, in the received echo signals, the sequence of watermarked radar echo signals transmitted by the locator transponder (24); extracting the temporary identification code carried by the spread spectrum watermarking signal embedded in the detected sequence of watermarked radar echo signals; and determining a location of the locator transponder on the basis of the detected sequence of watermarked radar echo signals; f) transmitting, by the radio communications system (22), one or more frequency-synchronization-aid signals; g) receiving, by the locator transponder (24), the frequency-synchronization-aid signal(s) and estimating, by said locator transponder (24), based on the received frequency-synchronization-aid signal(s), a frequency drift affecting a reference frequency provided by a local oscillator (86) of said locator transponder (24); wherein the locator transponder (24) transmits the sequence of watermarked radar echo signals by using a transmission carrier frequency obtained based on the reference frequency provided by the local oscillator (86) and on the estimated frequency drift.

IPC Classes  ?

• G01S 7/40 - Means for monitoring or calibrating
• G01S 13/82 - Systems using reradiation of radio waves, e.g. secondary radar systemsAnalogous systems wherein continuous-type signals are transmitted
• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

The invention relates to a microwave circular polarizer including: a first outer conductor; a second outer conductor connected to the first outer conductor forming a first step discontinuity therewith; and a third outer conductor connected to the second outer conductor forming a second step discontinuity therewith. An inner conductor is provided which extends inside and is spaced apart from the first, second and third outer conductors. The first and second outer conductors are axially asymmetric with respect to the inner conductor, and the third outer conductor is axially symmetric with respect to the inner conductor. The microwave circular polarizer includes first and second rectangular waveguide ports in signal communication with an internal cavity through, respectively, a first rectangular aperture and a second rectangular aperture formed through the first outer conductor. The microwave circular polarizer further includes a first septum and a second septum.

IPC Classes  ?

• H01P 1/17 - Auxiliary devices for rotating the plane of polarisation for producing a continuously rotating polarisation, e.g. circular polarisation
• H01P 5/02 - Coupling devices of the waveguide type with invariable factor of coupling
• H01P 1/10 - Auxiliary devices for switching or interrupting
• H01P 1/06 - Movable joints, e.g. rotating joints
• H01P 3/12 - Hollow waveguides

Abstract

A surface bio-contamination assay kit (1) comprising a disposable swab cartridge (2) comprising a swab (29); a sampler (3) designed to removably receive the cartridge (2) and to wipe the cartridge swab (29) on a surface to be collect a sampled, along a predetermined sampling path (4) designed to cover a predetermined surface area; and a bio-contamination meter (5) designed to removably receive the cartridge (2) after sampling and to measure bio-contamination of the collected sample on the cartridge (2).

IPC Classes  ?

• G01N 1/02 - Devices for withdrawing samples
• B01L 3/00 - Containers or dishes for laboratory use, e.g. laboratory glasswareDroppers
• G01N 21/76 - ChemiluminescenceBioluminescence

Abstract

The invention relates to an interconnection network for forward error correction encoders and decoders, including N input terminals, N output terminals, and M stages. Each stage includes switching elements having input pins and output pins. The input pins of the switching elements of the first stage are connected to the input terminals, and the output pins of the switching elements of the last stage are connected to the output terminals. The input and output pins of the switching elements of immediately successive stages are connected in a hardwired fashion so as to form a plurality of interconnection sub-networks for routing respective input values from respective output pins of the switching elements of the first stage to respective input pins of the switching elements of the last stage.

IPC Classes  ?

• G06F 11/10 - Adding special bits or symbols to the coded information, e.g. parity check, casting out nines or elevens
• G06F 13/40 - Bus structure

Abstract

The invention concerns a monitoring method that comprises coupling in an integral manner at least one electromagnetic mirror of passive type with a given target to be monitored and monitoring the given target; wherein monitoring the given target includes: acquiring, via one or more synthetic aperture radar(s) installed on board one or more satellites and/or one or more aerial platforms, SAR images of a given area of the earth's surface where the given target is located; and determining, via a processing unit, a movement of the electromagnetic mirror on the basis of the acquired SAR images.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• G01S 13/75 - Systems using reradiation of radio waves, e.g. secondary radar systemsAnalogous systems using transponders powered from received waves, e.g. using passive transponders
• H01Q 15/18 - Reflecting surfacesEquivalent structures comprising plurality of mutually inclined plane surfaces, e.g. corner reflector

Abstract

The present invention concerns a localization method for locating a target that is coupled with a locator transponder associated with a permanent identification code permanently assigned to said locator transponder; the localization method comprising: upon reception of a user request for locating the target, transmitting, by a paging system or by a radar-based system, a spread spectrum paging signal carrying the permanent identification code and a temporary identification code temporarily assigned to the locator transponder, wherein said temporary identification code is shorter than said permanent identification code; receiving, by the locator transponder, the spread spectrum paging signal and extracting, by said locator transponder, the temporary identification code carried by said spread spectrum paging signal received; transmitting, by the radar-based system, radar signals towards one or more areas of earth's surface or sky, and receiving, by said radar-based system, echo signals from said one or more areas of the earth's surface or sky; upon reception by the locator transponder of one or more radar signals transmitted by the radar-based system, generating and transmitting, by said locator transponder, a sequence of watermarked radar echo signals in which a spread spectrum watermarking signal is embedded, wherein said spread spectrum watermarking signal carries the temporary identification code extracted.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• G01S 7/00 - Details of systems according to groups , ,
• G01S 13/76 - Systems using reradiation of radio waves, e.g. secondary radar systemsAnalogous systems wherein pulse-type signals are transmitted

Abstract

A SAR imaging method for interferometric analyses is provided, including: receiving raw SAR data related to two or more SAR acquisitions of one and the same area of the earth's surface carried out by one or more synthetic aperture radars; and processing the raw SAR data to generate SAR images. For each SAR acquisition, the respective raw SAR data is processed based on two different sets of processing parameters: a first set that is the same for all the SAR acquisitions and which comprises focusing Doppler parameters computed based on physical Doppler parameters related to all the SAR acquisitions; and a second set which comprises respective radiometric equalization Doppler parameters related to the SAR acquisition and computed based on respective physical Doppler parameters related to the SAR acquisition. Processing includes: focusing the raw SAR data related to all SAR acquisitions based on the focusing Doppler parameters and, for each SAR acquisition, applying a respective radiometric equalization, based on the respective radiometric equalization Doppler parameters, to the respective SAR data to compensate for possible differences in pointing of the synthetic aperture radar(s), without degrading azimuth resolution and without introducing radiometric distortions.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• G01S 7/40 - Means for monitoring or calibrating
• G01S 7/04 - Display arrangements

Abstract

CTCTTTTT) at a respective resonator section where magnetic field component coupled by said respective pair of slots (24) is null.

IPC Classes  ?

• H01P 1/208 - Cascaded cavitiesCascaded resonators inside a hollow waveguide structure

Abstract

The invention concerns a method and a related system for measuring thermo-elastic deformations of objects. The invention uses an interferometric metrology instrument (2) configured to carry out optical measurements, and a thermal chamber (1), whose internal temperature is controllable and which is fitted with an inspection window (11) closed by a medium (110) that is transparent to light emitted by the interferometric metrology instrument (2). Said interferometric metrology instrument (2) is arranged outside the thermal chamber (1) in front of the inspection window (11), thereby being operable to carry out optical measurements through said inspection window (11). The invention is characterized by an innovative preliminary calibration step including: determining refraction and phase shift compensation laws based on calibration measurements performed through the inspection window with and without the medium. According to an aspect of the invention, said refraction and phase shift compensation laws are used to correct optical measurements of an object under test in order to compensate for propagation through the medium (110) of the light emitted by the interferometric metrology instrument (2).

IPC Classes  ?

• G01B 9/02 - Interferometers

Abstract

A Reference Time Scale (RTS) Dissemination System (RTS-DS) comprising: ▪ a RTS Dissemination Data Provider (RTS-DDP), and ▪ a User Terminal (UT); the RTS Dissemination Data Provider (RTS-DDP) is equipped with a Radio Receiver designed to receive radio signals and to compute a RTS-DDP Computed Time Scale based on received radio signals; the User Terminal (UT) is equipped with a Radio Receiver designed to receive radio signals and to compute a UT Computed Time Scale based on received radio signals, and with a Clock Device designed to be locked to the UT Computed Time Scale and to provide a UT Local Time Scale resultingly locked to the UT Computed Time Scale; the RTS Dissemination Data Provider (RTS-DDP) is designed to: ▪ receive a Reference Time Scale (RTS), and ▪ compute, at a RTS-DDP Computed Time, Time Quantities indicative of a difference between the RTS-DDP Computed Time Scale and the received Reference Time Scale, and comprising: ◦ a Time Scatter indicative of a difference between the RTS-DDP Computed Time and a corresponding Reference Time, and ◦ a Time Offset indicative of a mean value, computed over a timespan, of a number of differences between RTS-DDP Computed Times and corresponding Reference Times, and ▪ transmit RTS Dissemination Data containing the computed Time Quantities, the RTS-DDP Computed Time when the Time Quantities are computed, and the RTS-DDP Computed Time when the RTS Dissemination Data is transmitted; the User Terminal (UT) is designed to: ▪ receive transmitted RTS Dissemination Data, ▪ compute, at a UT Computed Time corresponding to the RTS-DDP Computed Time when the Time Quantities are computed: ◦ a first quantity indicative of a difference between the UT Computed Time and a corresponding UT Local Time, and ◦ a second quantity indicative of a difference between the Time Scatter and the Time Offset contained in the received RTS Dissemination Data, ◦ check whether a validation criterion is met by the first and second computed quantities, ◦ if the validation criterion is determined to be met: - compute a UT RTS-Aligned Time Scale in time alignment with the Reference Time Scale based on the Time Offset contained in the received RTS Dissemination Data, and - expose the UT RTS-Aligned Time Scale, along with an indication that the exposed UT RTS-Aligned Time Scale is in time alignment with the Reference Time Scale.

IPC Classes  ?

• G04G 7/00 - Synchronisation
• G04G 5/00 - Setting, i.e. correcting or changing, the time-indication

Abstract

The invention concerns a microwave antenna module for use in an antenna system installed on board a space platform. The disclosed microwave antenna module includes a transmit/receive module, which comprises: a first package and a second package, that are hermetically sealed to one another and that are multilayer ceramic substrate packages; and an interposer connector, that is interposed between the first and second packages and comprises a body and connection means provided in the body. First and second electronic circuitries are connected to the connection means of the interposer connector for routing microwave, control and power signals through the connection means. The first electronic circuitry includes a directional coupler in stripline-coplanar configuration. Each microwave connection assembly includes: a respective first metal element, that extends through the body perpendicularly to a top surface and a bottom surface of the body, protruding from the top and bottom surfaces; a respective first dielectric element, that is coaxial with, and extends around, the respective first metal element surrounding completely the respective first metal element, and extends through the body between the top surface and the bottom surface thereof; and respective second metal elements, that are spaced apart from, and surround at least partially, the respective first dielectric element, extend through the body perpendicularly to the top and bottom surfaces thereof, protruding from the top and bottom surfaces, and are in electrical contact with the body, thereby being at the same electrical potential as the body.

IPC Classes  ?

• H01Q 13/18 - Resonant slot antennas the slot being backed by, or formed in boundary wall of, a resonant cavity
• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• H04B 7/185 - Space-based or airborne stations
• H01Q 13/08 - Radiating ends of two-conductor microwave transmission lines, e.g. of coaxial lines, of microstrip lines
• H01Q 1/38 - Structural form of radiating elements, e.g. cone, spiral, umbrella formed by a conductive layer on an insulating support
• H01Q 1/42 - Housings not intimately mechanically associated with radiating elements, e.g. radome
• H01P 5/18 - Conjugate devices, i.e. devices having at least one port decoupled from one other port consisting of two coupled guides, e.g. directional couplers
• G01S 7/03 - Details of HF subsystems specially adapted therefor, e.g. common to transmitter and receiver
• G01S 7/40 - Means for monitoring or calibrating
• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
• H01Q 19/17 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave the primary radiating source comprising two or more radiating elements
• H01P 3/12 - Hollow waveguides
• H01Q 3/26 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elementsArrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the distribution of energy across a radiating aperture
• H01P 3/00 - WaveguidesTransmission lines of the waveguide type
• H01P 3/06 - Coaxial lines
• G01S 13/02 - Systems using reflection of radio waves, e.g. primary radar systemsAnalogous systems
• G01S 7/02 - Details of systems according to groups , , of systems according to group

Abstract

The invention concerns a satellite deployment system (30) for launch vehicles. Said satellite deployment system (30) comprises an outer dispenser (31) that is fitted, externally, with first releasable attachment means for releasably attaching first satellites (81) to said outer dispenser (31) and, internally, with an internal housing volume (310). Moreover, the satellite deployment system (30) further comprises at least an inner dispenser (32,33) that is externally fitted with second releasable attachment means for releasably attaching second satellites (82,83) to said inner dispenser (32,33), and that is accommodated in the internal housing volume (310) of the outer dispenser (31).

IPC Classes  ?

• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

Abstract

b) segments is caused, thus enabling release of the first and second structures from one another.

IPC Classes  ?

• B23K 1/00 - Soldering, e.g. brazing, or unsoldering
• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
• B23K 1/002 - Soldering by means of induction heating
• B62D 33/06 - Drivers' cabs
• B62D 21/06 - Understructures, i.e. chassis frame on which a vehicle body may be mounted of X-shaped or fork-shaped construction, i.e. having members which form an X or fork as the frame is seen in plan view
• B23K 1/005 - Soldering by means of radiant energy
• B23K 3/047 - Heating appliances electric
• B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles

Abstract

A hybrid processor system for use on board a telecommunications multi-beam satellite is provided that is controllable by a network control center via one or more control channels. The system links to ground terminals by: providing uplink and downlink traffic channels on several satellite beams; routing atomic switched information blocks from the uplink traffic channels to the downlink traffic channels; and exchanging signaling data with the ground terminals on one or more uplink signaling channels and one or more downlink signaling channels. The atomic switched information blocks have the same given time duration and the same given baseband bandwidth. The hybrid processor system includes a burst switching processor and an on-board processor controller which is configured to store service information items indicative of: the given time duration and the given baseband bandwidth of the atomic switched information blocks; the respective uplink bandwidth, the respective uplink frequencies, a respective time length of the respective uplink time slots, and respective structure features of the respective uplink time frames and superframes of each uplink channel; the respective downlink bandwidth, the respective downlink frequencies, a respective time length of the respective downlink time slots, and respective structure features of the respective downlink time frames and superframes of each downlink channel; and quality of service and priority rules for serving the ground terminals. The on-board processor controller is further configured to extract, from incoming signaling data capacity requests sent by the ground terminals by demodulating and decoding the incoming signaling data.

IPC Classes  ?

• H04B 7/204 - Multiple access
• H04Q 3/00 - Selecting arrangements
• H04B 7/0404 - Diversity systemsMulti-antenna systems, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas the mobile station comprising multiple antennas, e.g. to provide uplink diversity
• H04B 7/0408 - Diversity systemsMulti-antenna systems, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas using two or more beams, i.e. beam diversity
• H04B 7/185 - Space-based or airborne stations
• H04B 7/0456 - Selection of precoding matrices or codebooks, e.g. using matrices for antenna weighting

Abstract

Disclosed herein is a double-reflector antenna (1) for use on board a satellite or space platform for data downlink or for telemetry, tracking and command. Said double-reflector antenna (1) comprises a main reflector (11) and a sub-reflector (12) arranged coaxially with, and in front of, one another. Additionally, the double-reflector antenna (1) further comprises a coaxial feeder, that is arranged coaxially with the main reflector (11) and the sub-reflector (12), and that includes inner (14) and outer (13) conductors arranged coaxially with, and spaced apart from, one another. The coaxial feeder is designed to be fed with downlink microwave signals to be transmitted by the double-reflector antenna (1), and to radiate said downlink microwave signals through a feed aperture (15), that is located centrally with respect to the main reflector (11) and that gives onto the sub-reflector (12). The inner conductor (14) protrudes axially and outwardly from the feed aperture (15) up to the sub-reflector (12) and is rigidly coupled to said sub-reflector (12) thereby supporting said sub-reflector (12).

IPC Classes  ?

• H01Q 19/19 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces comprising one main concave reflecting surface associated with an auxiliary reflecting surface
• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
• H01Q 5/47 - Imbricated or interleaved structuresCombined or electromagnetically coupled arrangements, e.g. comprising two or more non-connected fed radiating elements using two or more feeds in association with a common reflecting, diffracting or refracting device with a coaxial arrangement of the feeds
• H01Q 21/00 - Antenna arrays or systems
• H01Q 25/00 - Antennas or antenna systems providing at least two radiating patterns
• H01Q 21/28 - Combinations of substantially independent non-interacting antenna units or systems
• H01Q 21/29 - Combinations of different interacting antenna units for giving a desired directional characteristic
• H01Q 1/36 - Structural form of radiating elements, e.g. cone, spiral, umbrella
• H01Q 9/04 - Resonant antennas

Abstract

The invention relates to a microwave circular polarizer (1) including: a first outer conductor (110), which is cylindrically shaped and internally hollow; a second outer conductor (120), which is cylindrically shaped, internally hollow, and is connected to the first outer conductor (110) forming a first step discontinuity (141) therewith; and a third outer conductor (130), which is cylindrically shaped, internally hollow, and is connected to the second outer conductor (120) forming a second step discontinuity (142) therewith. A first longitudinal axis of the first outer conductor (110), a second longitudinal axis of the second outer conductor (120), and a third longitudinal axis of the third outer conductor (130) are parallel to one another. The microwave circular polarizer (1) further includes an inner conductor (150), which is cylindrically shaped, extends inside the first, second and third outer conductors (110,120,130), and is spaced apart from said first, second and third outer conductors (110,120,130), thereby resulting in an internal cavity being present between said inner conductor (150) and said first, second and third outer conductors (110,120,130). A fourth longitudinal axis of the inner conductor (150) coincides with the third longitudinal axis and is parallel to the first and second longitudinal axes, thereby resulting in an axially asymmetrical configuration of the first and second outer conductors (110,120) with respect to the inner conductor (150), and an axially symmetrical configuration of the third outer conductor (130) with respect to said inner conductor (150). The microwave circular polarizer (1) further includes a first rectangular waveguide port (161) and a second rectangular waveguide port (162), that are: coupled to the first outer conductor (110) externally to the internal cavity; oriented orthogonally to the first longitudinal axis; positioned relative to one another so as to form a 90-degree angle with respect to said first longitudinal axis; and in signal communication with the internal cavity through, respectively, a first rectangular aperture and a second rectangular aperture formed through the first outer conductor (110). The microwave circular polarizer (1) further includes a first septum (171) and a second septum (172). The first septum (171) is arranged on the first outer conductor (110) inside the internal cavity and is positioned, relative to the first and second rectangular waveguide ports (161,162), so as to form, with each of said first and second rectangular waveguide ports (161,162), a respective 45- degree angle with respect to the first longitudinal axis. The second septum (172) is arranged on the inner conductor (150) inside the internal cavity and is positioned, relative to the first and second rectangular waveguide ports (161,162), so as to form, with each of said first and second rectangular waveguide ports (161,162), a respective 135- degree angle with respect to the first longitudinal axis.

IPC Classes  ?

• H01P 1/17 - Auxiliary devices for rotating the plane of polarisation for producing a continuously rotating polarisation, e.g. circular polarisation
• H01P 5/02 - Coupling devices of the waveguide type with invariable factor of coupling
• H01P 5/103 - Hollow-waveguide/coaxial-line transitions

Abstract

NNMNMNNMNNNNMNNMNSii smii smii Sii = N/smii smii iMsmii smii smii smii smii smii sm11 N/sm11 N/sm11 N/sm11 sm11 MNN, which is associated with the first stage.

IPC Classes  ?

• H04L 1/00 - Arrangements for detecting or preventing errors in the information received
• H03M 13/27 - Coding, decoding or code conversion, for error detection or error correctionCoding theory basic assumptionsCoding boundsError probability evaluation methodsChannel modelsSimulation or testing of codes using interleaving techniques

Abstract

Disclosed herein is a method for managing aeronautical safety-critical services or data links, comprising: receiving quality measurement data indicative of a quality parameter measured for an aeronautical safety-critical service or data link used by an aircraft; receiving a four-dimensional position associated with the quality measurement data, wherein said four-dimensional position includes a three-dimensional space position and a corresponding time that are computed based on a Global Navigation Satellite System and related to the measured quality parameter; tagging the quality measurement data with the associated four-dimensional position; determining, on the basis of the tagged quality measurement data and of a predefined task policy, a task to be performed, which task includes an adaptation of the aeronautical safety-critical service used by the aircraft or of resources allocated to the aeronautical safety-critical data link used by the aircraft, wherein said adaptation is based on said tagged quality measurement data; and performing the determined task.

IPC Classes  ?

• H04B 7/185 - Space-based or airborne stations
• G08G 5/00 - Traffic control systems for aircraft
• H04L 12/70 - Packet switching systems
• H04L 29/00 - Arrangements, apparatus, circuits or systems, not covered by a single one of groups
• H04W 4/02 - Services making use of location information
• H04L 29/08 - Transmission control procedure, e.g. data link level control procedure
• H04W 4/44 - Services specially adapted for particular environments, situations or purposes for vehicles, e.g. vehicle-to-pedestrians [V2P] for communication between vehicles and infrastructures, e.g. vehicle-to-cloud [V2C] or vehicle-to-home [V2H]
• H04W 72/04 - Wireless resource allocation
• H04W 72/08 - Wireless resource allocation based on quality criteria
• H04L 12/26 - Monitoring arrangements; Testing arrangements

Abstract

The present invention concerns a localization method for locating a target that is coupled with a locator transponder (5) associated with a permanent identification code permanently assigned to said locator transponder (5); the localization method comprising: upon reception of a user request for locating the target, transmitting, by a paging system (3,200) or by a radar-based system (4,300,500), a spread spectrum paging signal carrying the permanent identification code and a temporary identification code temporarily assigned to the locator transponder (5), wherein said temporary identification code is shorter than said permanent identification code; receiving, by the locator transponder (5), the spread spectrum paging signal and extracting, by said locator transponder (5), the temporary identification code carried by said spread spectrum paging signal received; transmitting, by the radar-based system (4,300,500), radar signals towards one or more areas of earth' s surface or sky, and receiving, by said radar-based system (4,300,500), echo signals from said one or more areas of the earth' s surface or sky; upon reception by the locator transponder (5) of one or more radar signals transmitted by the radar- based system (4,300,500), generating and transmitting, by said locator transponder (5), a sequence of watermarked radar echo signals in which a spread spectrum watermarking signal is embedded, wherein said spread spectrum watermarking signal carries the temporary identification code extracted. In particular, generating and transmitting, by the locator transponder (5), the sequence of watermarked radar echo signals includes: generating a sequence of radar echo signals on the basis of the radar signal (s) received; modulating the generated sequence of radar echo signals on the basis of the spread spectrum watermarking signal, thereby obtaining the sequence of watermarked radar echo signals; and transmitting said sequence of watermarked radar echo signals. The spread spectrum watermarking signal includes a synchronization portion and an information portion; wherein the synchronization portion of the spread spectrum watermarking signal is generated on the basis of a first predefined pseudo noise code; wherein the information portion of the spread spectrum watermarking signal is generated by applying a first predefined spread spectrum technique to a given signal carrying the temporary identification code extracted; wherein said first predefined spread spectrum technique is applied by using a second predefined pseudo noise code, that is the same as, or different than, the first predefined pseudo noise code. Moreover, the localization method further comprises carrying out, by the radar-based system (4,300,500), localization operations that include: detecting, in the received echo signals, the sequence of watermarked radar echo signals transmitted by the locator transponder (5) by detecting the synchronization portion of the spread spectrum watermarking signal embedded in said sequence of watermarked radar echo signals; extracting the temporary identification code carried by the spread spectrum watermarking signal embedded in the sequence of watermarked radar echo signals detected, by extracting said temporary identification code from the information portion of the spread spectrum watermarking signal embedded in said sequence of watermarked radar echo signals detected; and determining a location of the locator transponder (5) on the basis of the sequence of watermarked radar echo signals detected.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• G01S 13/76 - Systems using reradiation of radio waves, e.g. secondary radar systemsAnalogous systems wherein pulse-type signals are transmitted
• G01S 7/00 - Details of systems according to groups , ,

Abstract

The invention concerns a monitoring method that comprises coupling in an integral manner at least one electromagnetic mirror of passive type (1, 2, 3, 4, 5, 6, 10, 11, 13, 15, 18, 20, 25, 26) with a given target (7, 9, 14, 17, 24, 30) to be monitored and monitoring the given target (7, 9, 14, 17, 24, 30); wherein monitoring the given target (7, 9, 14, 17, 24, 30) includes: acquiring, via one or more synthetic aperture radar (s) installed on board one or more satellites (12, 16, 22, 27, 29) and/or one or more aerial platforms, SAR images of a given area of the earth' s surface where the given target (7, 9, 14, 17, 24, 30) is located; and determining, via a processing unit, a movement of the electromagnetic mirror (1, 2, 3, 4, 5, 6, 10, 11, 13, 15, 18, 20, 25, 26) on the basis of the acquired SAR images.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• H01Q 15/18 - Reflecting surfacesEquivalent structures comprising plurality of mutually inclined plane surfaces, e.g. corner reflector

Abstract

A non-porous composite is provided that includes a textile substrate impregnated with a first fluoropolymer and a film of polymeric material comprising at least one second fluoropolymer filled with porous particles of a silicate having a granulometric dimension d50 less than or equal to 5 μm and a porosity ranging from 30 to 60% in volume and loaded with antibacterial ions of at least one metal selected from the group consisting of silver, copper, zinc and nickel. A method for production of the composite and a containing and/or transport element for a fluid, preferably water, produced with the composite, are also provided.

IPC Classes  ?

• C09D 5/14 - Paints containing biocides, e.g. fungicides, insecticides or pesticides
• B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
• C08K 9/10 - Encapsulated ingredients
• B32B 27/30 - Layered products essentially comprising synthetic resin comprising vinyl resinLayered products essentially comprising synthetic resin comprising acrylic resin
• A01N 65/20 - Fabaceae or Leguminosae [Pea or Legume family], e.g. pea, lentil, soybean, clover, acacia, honey locust, derris or millettia
• A01N 65/16 - Ericaceae [Heath or Blueberry family], e.g. rhododendron, arbutus, pieris, cranberry or bilberry
• A01N 25/10 - Macromolecular compounds
• A01N 59/16 - Heavy metalsCompounds thereof
• C03C 25/305 - Polyfluoroolefins
• C09D 127/18 - Homopolymers or copolymers of tetrafluoroethene
• C08K 3/08 - Metals
• C08K 7/28 - Glass
• C08K 7/26 - Silicon-containing compounds
• C08K 3/40 - Glass
• C08K 3/015 - Biocides
• B32B 37/00 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
• C08K 3/34 - Silicon-containing compounds
• C08K 9/02 - Ingredients treated with inorganic substances

Abstract

A computer-aided FEM-based structure design system configured to: ■ acquire an initial structure design configuration comprising: - a design domain (Ω), - an applied load (f), and - constrained, unconstrained and loaded areas (ΓD, ΓF, ΓΝ); ■ compute an initial mesh (Toh) of the design domain (Ω); ■ compute a topological^ optimized structure model by iterating, until a termination criterion is fulfilled: - computing an optimized structure topology by properly implementing the SIMP (Solid Isotropic Material with Penalization) algorithm based on a density function (p) that represents the distribution of the material in the structure; - computing an anisotropic recovery-based a posteriori error estimator (η) that quantifies the error between the gradient of the exact structure material density (p) and the gradient of the FEM-computed approximation thereof, - computing a metric (Mk+1) for anisotropic mesh adaptation based on the anisotropic recovery-based a posteriori error estimator (η), and - computing an adapted anisotropic mesh (Tkh+ 1 ) based on the metric (Mk+1).

IPC Classes  ?

• G06F 17/50 - Computer-aided design
• G06T 17/20 - Wire-frame description, e.g. polygonalisation or tessellation

Abstract

The present invention concerns a SAR imaging method (40) for interferometric analyses, comprising: receiving raw SAR data related to two or more SAR acquisitions of one and the same area of the earth's surface carried out by means of one or more synthetic aperture radars; and processing the raw SAR data so as to generate SAR images. The method is characterized in that, for each SAR acquisition, the respective raw SAR data related to said SAR acquisition are processed on the basis of two different sets of processing parameters, which include: a first set that is the same for all the SAR acquisitions and which comprises focusing Doppler parameters computed on the basis of physical Doppler parameters related to all the SAR acquisitions; and a respective second set, which comprises respective radiometric equalization Doppler parameters related to said SAR acquisition and computed on the basis of respective physical Doppler parameters related to said SAR acquisition. In particular, processing includes: focusing the raw SAR data related to all the SAR acquisitions on the basis of said focusing Doppler parameters; and, for each SAR acquisition, applying a respective radiometric equalization, based on the respective radiometric equalization Doppler parameters, to the respective SAR data to compensate for possible differences in pointing of the synthetic aperture radar(s) used to carry out the SAR acquisitions, without degrading azimuth resolution and without introducing radiometric distortions.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• G01S 7/40 - Means for monitoring or calibrating

Abstract

The present invention concerns a SAR imaging method (40) for interferometric analyses, comprising: receiving raw SAR data related to two or more SAR acquisitions of one and the same area of the earth's surface carried out by means of one or more synthetic aperture radars; and processing the raw SAR data so as to generate SAR images. The method is characterized in that, for each SAR acquisition, the respective raw SAR data related to said SAR acquisition are processed on the basis of two different sets of processing parameters, which include: a first set that is the same for all the SAR acquisitions and which comprises focusing Doppler parameters computed on the basis of physical Doppler parameters related to all the SAR acquisitions; and a respective second set, which comprises respective radiometric equalization Doppler parameters related to said SAR acquisition and computed on the basis of respective physical Doppler parameters related to said SAR acquisition. In particular, processing includes: focusing the raw SAR data related to all the SAR acquisitions on the basis of said focusing Doppler parameters; and, for each SAR acquisition, applying a respective radiometric equalization, based on the respective radiometric equalization Doppler parameters, to the respective SAR data to compensate for possible differences in pointing of the synthetic aperture radar(s) used to carry out the SAR acquisitions, without degrading azimuth resolution and without introducing radiometric distortions.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• G01S 7/40 - Means for monitoring or calibrating

Abstract

Space system comprising a structure formed by structure components, an on-board equipment carried by the structure, and a passive device designed to facilitate demise of the space system during re-entry into the Earth's atmosphere. The passive device comprises connecting members designed to stably connect the structure components. The connecting members comprise at least a portion made of a primer material with characteristics such as to decay at re-entry altitudes higher than those at which the current connecting members melt so as to make unstable the connection created by the connecting members to such an extent as to early triggering demise of the structure of the space system during re-entry into the Earth's atmosphere.

IPC Classes  ?

• B64G 1/62 - Systems for re-entry into the earth's atmosphereRetarding or landing devices
• B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles
• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
• F16B 31/00 - Screwed connections specially modified in view of tensile loadBreak-bolts

Abstract

The invention concerns a hybrid processor system (1) for use on board a telecommunications multi-beam satellite, that is controllable by a network control centre via one or more control channels and is designed to link ground terminals by: providing uplink and downlink traffic channels on several satellite beams; routing atomic switched information blocks from the uplink traffic channels to the downlink traffic channels; and exchanging signaling data with the ground terminals on one or more uplink signaling channels and one or more downlink signaling channels. All the atomic switched information blocks have one and the same given time duration and one and the same given baseband bandwidth. Each uplink traffic channel has a respective uplink bandwidth including respective uplink frequencies, and carries, at said respective uplink frequencies, respective atomic switched information blocks in respective uplink time slots organized into respective uplink time frames forming respective uplink time superframes. Each downlink traffic channel has a respective downlink bandwidth including respective downlink frequencies, and carries, at said respective downlink frequencies, respective atomic switched information blocks in respective downlink time slots organized into respective downlink time frames forming respective downlink time superframes. The hybrid processor system (1) comprises a burst switching processor (11), and an on-board processor controller (12), which is configured to store service information items indicative of: said given time duration and said given baseband bandwidth of the atomic switched information blocks; the respective uplink bandwidth, the respective uplink frequencies, a respective time length of the respective uplink time slots, and respective structure features of the respective uplink time frames and superframes of each uplink channel; the respective downlink bandwidth, the respective downlink frequencies, a respective time length of the respective downlink time slots, and respective structure features of the respective downlink time frames and superframes of each downlink channel; and quality of service and priority rules for serving the ground terminals. The on-board processor controller (12) is further configured to extract, from incoming signaling data received on the uplink signaling channel(s), capacity requests sent by the ground terminals, wherein the capacity requests are extracted by the on-board processor controller (12) by demodulating and decoding the incoming signaling data. Moreover, the on-board processor controller (12) is also configured to assign to each pair or set of ground terminals to be linked respective frequency, space and time resources on the basis of the stored service information items and of all the capacity requests received from the ground terminals, wherein said respective frequency, space and time resources includes: one or more respective uplink frequencies of one or more respective uplink channels provided on one or more respective satellite beams; one or more respective uplink time slots in one or more respective uplink time frames in one or more uplink time superframes of said one or more respective uplink channels; one or more respective downlink frequencies of one or more respective downlink channels provided on said one or more respective satellite beams; and one or more respective downlink time slots in one or more respective downlink time frames in one or more downlink time superframes of said one or more respective downlink channels. Additionally, the on-board processor controller (12) is further configured to: generate resource assignment messages indicative of the frequency and time resources assigned to the ground terminals; generate outgoing signaling data to be transmitted to the ground terminals on the downlink signaling channel(s), wherein the outgoing signaling data are generated by the on-board processor controller (12) by encoding and modulating the resource assignment messages; generate a routing map on the basis of the frequency, space and time resources assigned to the ground terminals; generate switching commands based on the routing map; extract, from control data received on the control channel(s), control messages sent by the network control centre, wherein the control messages are extracted by the on-board processor controller (12) by demodulating, decoding and decrypting the control data; and update the stored service information items on the basis of the control messages. The burst switching processor (11) is configured to route the atomic switched information blocks on the basis of the switching commands generated by the on-board processor controller (12). Whereby: the on-board processor controller (12) is configured to operate in a regenerative way with respect to the signaling data, and is reconfigurable by the network control centre; and the burst switching processor (11) is configured to operate in a digital transparent way with respect to the atomic switched information blocks, and is operable by the on-board processor controller (12) to route the atomic switched information blocks in frequency, space and time domains.

IPC Classes  ?

• H04B 7/185 - Space-based or airborne stations

Abstract

The present invention relates to a release system (1, 2, 3, 4, 5), that includes a segmented structural element (10) comprising : a first segment (10a) designed to be coupled to a first structure, a second segment (10b) designed to be coupled to a second structure, and a solder joint (11) joining respective ends of said first (10a) and second (10b) segments, thus holding down the first and second structures with respect to one another; wherein said solder joint (11) is electromagnetically heatable and includes a solder alloy having a predefined melting temperature. The release system (1, 2, 3, 4, 5) is characterized by further including magnetic field generating means (13, PW1, PW2, PW3, PW4, PW5) configured to, upon reception of a release command, generate a time-varying magnetic field through the solder joint (11) such that to cause heating thereof up to the predefined melting temperature of the solder alloy, thereby causing melting of said solder alloy; whereby separation of the first (10a) and second (10b) segments is caused, thus enabling release of the first and second structures from one another.

IPC Classes  ?

• B23K 1/002 - Soldering by means of induction heating
• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

Abstract

Disclosed herein is a double-reflector antenna (1) for use on board a satellite or space platform for data downlink or for telemetry, tracking and command. Said double-reflector antenna (1) comprises a main reflector (11) and a sub- reflector (12) arranged coaxially with, and in front of, one another. Additionally, the double-reflector antenna (1) further comprises a coaxial feeder, that is arranged coaxially with the main reflector (11) and the sub-reflector (12), and that includes inner ( 14 ) and outer (13) conductors arranged coaxially with, and spaced apart from, one another. The coaxial feeder is designed to be fed with downlink microwave signals to be transmitted by the double- reflector antenna (1), and to radiate said downlink microwave signals through a feed aperture (15), that is located centrally with respect to the main reflector (11) and that gives onto the sub-reflector (12). The inner conductor (14) protrudes axially and outwardly from the feed aperture (15) up to the sub-reflector (12) and is rigidly coupled to said sub-reflector (12) thereby supporting said sub-reflector (12).

IPC Classes  ?

• H01Q 19/19 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces comprising one main concave reflecting surface associated with an auxiliary reflecting surface
• H01Q 5/47 - Imbricated or interleaved structuresCombined or electromagnetically coupled arrangements, e.g. comprising two or more non-connected fed radiating elements using two or more feeds in association with a common reflecting, diffracting or refracting device with a coaxial arrangement of the feeds
• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons

Abstract

Disclosed herein is a method for managing aeronautical safety-critical services or data links, comprising: receiving quality measurement data indicative of a quality parameter measured for an aeronautical safety-critical service or data link used by an aircraft; receiving a four-dimensional position associated with the quality measurement data, wherein said four-dimensional position includes a three-dimensional space position and a corresponding time that are computed based on a Global Navigation Satellite System and related to the measured quality parameter; tagging the quality measurement data with the associated four-dimensional position; determining, on the basis of the tagged quality measurement data and of a predefined task policy, a task to be performed, which task includes an adaptation of the aeronautical safety-critical service used by the aircraft or of resources allocated to the aeronautical safety-critical data link used by the aircraft, wherein said adaptation is based on said tagged quality measurement data; and performing the determined task.

IPC Classes  ?

• G08G 5/00 - Traffic control systems for aircraft
• H04L 12/70 - Packet switching systems
• H04B 7/185 - Space-based or airborne stations
• H04L 29/00 - Arrangements, apparatus, circuits or systems, not covered by a single one of groups
• H04L 29/06 - Communication control; Communication processing characterised by a protocol
• H04W 4/02 - Services making use of location information

Abstract

The present invention relates to attitude control and, in particular, to control of the attitude of a space platform. The space platform may take the form of or be part of a satellite and/or a spacecraft. An aspect of the present invention concerns the use, in an attitude control system, of several control moment gyroscopes with limited gimbal revolutions. Another aspect of the present invention concerns an improved logic for controlling a control moment gyroscope assembly of an attitude control system.

IPC Classes  ?

• B64G 1/28 - Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
• B64G 1/24 - Guiding or controlling apparatus, e.g. for attitude control
• B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles
• G01C 19/06 - Rotors

Abstract

The present invention concerns a method for making a microsatellite, comprising providing: modules of a first type (1) configured to house electronic boards (11,12,13,14) of a microsatellite; modules of a second type (2) configured to house devices and systems (21,22,23,24) of a microsatellite; and modules of a third type (3) comprising first and second interface means (31,32) configured to be coupled to a launch vehicle and to external appendages of a microsatellite, respectively; said modules of a third type (3) being designed to cause a body (4,9) of a microsatellite (5,6,7,8) to have a predefined height; wherein all the modules of the first, second and third types (1,2,3) are configured to be stacked regardless of the type. The method further comprises making a body (4,9) of a microsatellite (5,6,7,8) by stacking modules of different types, wherein the stacked modules include at least one module of the second type (2) and at least one module of the third type (3).

IPC Classes  ?

• B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles

Abstract

Space system (1) comprising a structure (2) formed by structure components (3), an on-board equipment (5) carried by the structure (2), and a passive device designed to facilitate demise of the space system (1) during re-entry into the Earth's atmosphere. The passive device comprises connecting members (4) designed to stably connect the structure components (3). The connecting members (4) comprise at least a portion made of a primer material with characteristics such as to decay at re-entry altitudes higher than those at which the current connecting members melt so as to make unstable the connection created by the connecting members (4) to such an extent as to early triggering demise of the structure (2) of the space system (1) during re-entry into the Earth's atmosphere.

IPC Classes  ?

• B64G 1/62 - Systems for re-entry into the earth's atmosphereRetarding or landing devices
• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
• B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles

Abstract

Space system (1) comprising a structure (2) formed by structure components (3), an on-board equipment (5) carried by the structure (2), and a passive device designed to facilitate demise of the space system (1) during re-entry into the Earth's atmosphere. The passive device comprises connecting members (4) designed to stably connect the structure components (3). The connecting members (4) comprise at least a portion made of a primer material with characteristics such as to decay at re-entry altitudes higher than those at which the current connecting members melt so as to make unstable the connection created by the connecting members (4) to such an extent as to early triggering demise of the structure (2) of the space system (1) during re-entry into the Earth's atmosphere.

IPC Classes  ?

• B64G 1/62 - Systems for re-entry into the earth's atmosphereRetarding or landing devices
• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
• F16B 31/00 - Screwed connections specially modified in view of tensile loadBreak-bolts

Abstract

A SAR imaging method performs N SAR acquisitions in stripmap mode of the earth's surface using a synthetic aperture radar transported by an aerial or satellite platform and including a single, non-partitioned antenna and a single receiver coupled thereto. All N SAR acquisitions are performed using the same predetermined elevation angle relative to the nadir of the synthetic aperture radar and using a respective squint angle relative to the flight direction of the synthetic aperture radar. Radar transmission and reception operations are time interleaved with other N-1 SAR acquisitions, resulting in the respective acquisition directions being parallel to each other and not parallel to acquisition directions of other N-1 SAR acquisitions. Radar beams in two immediately successive time instants and related to two different SAR acquisitions are contiguous along the azimuth. SAR images may be generated using all the N SAR acquisitions having an enhanced azimuth resolution.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• G06T 1/00 - General purpose image data processing
• G06T 7/60 - Analysis of geometric attributes

Abstract

A SAR imaging method is provided that performs N SAR acquisitions in stripmap mode of areas of the earth's surface by means of a synthetic aperture radar transported by an aerial or satellite platform and which includes a single, non-partitioned antenna and a single receiver coupled to the single, non-partitioned antenna, N being an integer greater than one. Each SAR acquisition in stripmap mode is performed using a respective squint angle with respect to the flight direction of the synthetic aperture radar and a respective elevation angle with respect to the nadir of the synthetic aperture radar. The method may further generate SAR images of areas of the respective swath observed via the SAR acquisition in stripmap mode. All SAR images have the same azimuth resolution that is equal to half the physical or equivalent length along the azimuth direction of the single, non-partitioned antenna of the synthetic aperture radar.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• G06T 1/00 - General purpose image data processing
• G06T 7/60 - Analysis of geometric attributes

Abstract

The invention concerns a method for reducing the costs of a satellite remote sensing service. The method comprises providing a satellite remote sensing system that includes only one satellite equipped with a sensor configured to acquire images of areas of the earth's surface, the satellite remote sensing system being designed to provide a satellite remote sensing service based on the images acquired by the sensor on board the satellite. In particular, the satellite follows a predefined orbit around the earth with an orbit repeat cycle shorter than three days, whereby a satellite remote sensing service with very good time performance, excellent interferometric capabilities and with drastically reduced costs is obtained.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
• G06F 17/10 - Complex mathematical operations
• B64G 1/40 - Arrangements or adaptations of propulsion systems
• B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles
• B64G 1/24 - Guiding or controlling apparatus, e.g. for attitude control

Abstract

A projective optical metrology system including a first optical unit, which includes: an optical input that receives a first light signal; a number of optical paths; and a separator, which is optically interposed between the optical input and the optical paths and separates a number of components of the first light signal received by the optical input and couples each of the separate components to a corresponding optical path. The first optical unit also includes a light target, which emits a second light signal and is formed by a number of light elements, each light element being optically coupled to a corresponding optical path, so as to be illuminated, in use, by the component of the first light signal coupled to the corresponding optical path. The metrology system also includes a second optical unit, which generates the first light signal and receives the second light signal.

IPC Classes  ?

• G01S 5/00 - Position-fixing by co-ordinating two or more direction or position-line determinationsPosition-fixing by co-ordinating two or more distance determinations
• G01B 11/14 - Measuring arrangements characterised by the use of optical techniques for measuring distance or clearance between spaced objects or spaced apertures
• G01S 17/74 - Systems using reradiation of electromagnetic waves other than radio waves, e.g. IFF, i.e. identification of friend or foe
• G01S 5/16 - Position-fixing by co-ordinating two or more direction or position-line determinationsPosition-fixing by co-ordinating two or more distance determinations using electromagnetic waves other than radio waves

Abstract

A large deployable reflector for an antenna suitable for being installed on board a satellite and provided with a support structure, a parabolic mirror carried by the support structure and a connection arm for mounting the support structure on the satellite; the support structure being a jointed reticulate structure that is able to assume a compact inoperative stowed configuration and an operative deployed configuration and is composed of ‘n’ elements articulated to form tetrahedrons having respective triangular bases, which are connected to each other at the axial ends of respective first sides and have respective external vertices, which are opposite to said respective first sides and, when the reflector is arranged in the deployed configuration, ideally lie on a cone tangent to the parabolic mirror.

IPC Classes  ?

• H01Q 15/16 - Reflecting surfacesEquivalent structures curved in two dimensions, e.g. paraboloidal
• B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
• B64G 1/66 - Arrangements or adaptations of apparatus or instruments, not otherwise provided for

Abstract

The present invention relates, in general, to attitude control and, in particular, to control of the attitude of a space platform, conveniently of a satellite and/or a spacecraft. In detail, an aspect of the present invention concerns the use, in an attitude control system (100), of several Control Moment Gyroscopes (3,41,42,43,44,61,62,63,64) with limited gimbal revolutions. Moreover, another aspect of the present invention concerns an improved logic for controlling a Control Moment Gyroscope assembly (4,6,120) of an attitude control system (100).

IPC Classes  ?

• B64G 1/28 - Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
• G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
• G01C 19/00 - GyroscopesTurn-sensitive devices using vibrating massesTurn-sensitive devices without moving massesMeasuring angular rate using gyroscopic effects

Abstract

The present invention regards a method of operation of a real aperture radar system for surveillance of the Earth's surface, said real aperture radar system being installed on a space vehicle/platform that moves in a direction of flight and comprising a transceiving antenna, or a transmitting antenna and a receiving antenna, which is/are electronically steerable. All the radar pulses are transmitted: with a predefined pulse repetition frequency and a predefined timing of the scanning cycle such that to guarantee a complete coverage of each of the N swaths parallelly to the direction of flight; and by using a frequency agility technique.

IPC Classes  ?

• G01S 13/02 - Systems using reflection of radio waves, e.g. primary radar systemsAnalogous systems
• G01S 13/42 - Simultaneous measurement of distance and other coordinates
• G01S 13/24 - Systems for measuring distance only using transmission of interrupted, pulse modulated waves using frequency agility of carrier wave
• G01S 13/00 - Systems using the reflection or reradiation of radio waves, e.g. radar systemsAnalogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified

Abstract

The present invention concerns a SAR imaging method, which comprises performing N SAR acquisitions in stripmap mode of areas of the earth's surface by means of a synthetic aperture radar that is transported by an aerial or satellite platform (30) and which comprises a single, non-partitioned antenna and a single receiver coupled to said single, non-partitioned antenna, N being- an integer greater than one. Each SAR acquisition in stripmap mode is performed using a respective squint angle with respect to the flight direction of the synthetic aperture radar, said respective squint angle being equal to, or different from, the squint angles used for performing the other N-1 SAR acquisitions in stripmap mode. Each SAR acquisition in stripmap mode is performed using a respective elevation angle with respect to the nadir of the synthetic aperture radar, said respective elevation angle being different from the elevation angles used for performing the other N-1 SAR acquisitions in stripmap mode, thereby resulting in that each SAR acquisition in stripmap mode is related to a respective swath of the earth's surface which is different from the swaths observed via the other N-1 SAR acquisitions in stripmap mode. Each performed SAR acquisition in stripmap mode comprises respective radar transmission and reception operations that are time interleaved, individually or in groups, with single, or groups of, radar transmission and reception operations of the other N-1 SAR acquisitions in stripmap mode performed, and which comprise the transmission and reception of respective radar beams in respective acquisition directions that are defined by the respective squint angle and by the respective elevation angle used for said SAR acquisition in stripmap mode, thereby resulting in that said respective acquisition directions are parallel to each other and not parallel to the acquisition directions of the other N-1 SAR acquisitions in stripmap mode performed. The method further comprises generating, on the basis of each SAR acquisition in stripmap mode performed, SAR images of areas of the respective swath observed via said SAR acquisition in stripmap mode. All the SAR images generated have one and the same azimuth resolution that is equal to half the physical or equivalent length along the azimuth direction of the single, non-partitioned antenna of the synthetic aperture radar.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

The present invention concerns a SAR imaging method, which comprises performing N SAR acquisitions in stripmap mode of areas of the earth's surface by means of a synthetic aperture radar (20) that is transported by an aerial or satellite platform and which comprises a single, non-partitioned antenna and a single receiver coupled to said single, non-partitioned antenna, N being an integer greater than one- All the N SAR acquisitions in stripmap mode are performed using one and the same predetermined elevation angle with respect to the nadir of the synthetic aperture radar (20) so that said N SAR acquisitions in stripmap mode all regard one and the same specific swath of the earth's surface. Each SAR acquisition in stripmap mode is performed using a respective squint angle with respect to the flight direction of the synthetic aperture radar (20), said respective squint angle being different from the squint angles used for performing the other N-1 SAR acquisitions in stripmap mode. Each performed SAR acquisition in stripmap mode comprises respective radar transmission and reception operations that are time interleaved, individually or in groups, with single, or groups of, radar transmission and reception operations of the other N-1 SAR acquisitions in stripmap mode performed, and which comprise the transmission and reception of respective radar beams in respective acquisition directions that are defined by the predetermined elevation angle and by the respective squint angle used for said SAR acquisition in stripmap mode, thereby resulting in that said respective acquisition directions are parallel to each other and not parallel to the acquisition directions of the other N-1 SAR acquisitions in stripmap mode performed. The radar beams transmitted and received in two radar transmission and reception operations performed in two immediately successive time instants and related to two different SAR acquisitions in stripmap mode are contiguous along the azimuth, thereby increasing the integration times with respect to those obtainable via any one of the N SAR acquisitions in stripmap mode performed. The method further comprises generating SAR images of areas of the specific swath on the basis of all the N SAR acquisitions in stripmap mode performed, said SAR images having an azimuth resolution that is enhanced by a factor up to N with respect to a nominal stripmap azimuth resolution that is equal to half the physical or equivalent length along the azimuth direction of the single, non-partitioned antenna of the synthetic aperture radar (20).

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

The present invention concerns a SAR imaging method, which comprises performing N SAR acquisitions in stripmap mode of areas of the earth's surface by means of a synthetic aperture radar that is transported by an aerial or satellite platform (30) and which comprises a single, non-partitioned antenna and a single receiver coupled to said single, non-partitioned antenna, N being- an integer greater than one. Each SAR acquisition in stripmap mode is performed using a respective squint angle with respect to the flight direction of the synthetic aperture radar, said respective squint angle being equal to, or different from, the squint angles used for performing the other N-1 SAR acquisitions in stripmap mode. Each SAR acquisition in stripmap mode is performed using a respective elevation angle with respect to the nadir of the synthetic aperture radar, said respective elevation angle being different from the elevation angles used for performing the other N-1 SAR acquisitions in stripmap mode, thereby resulting in that each SAR acquisition in stripmap mode is related to a respective swath of the earth's surface which is different from the swaths observed via the other N-1 SAR acquisitions in stripmap mode. Each performed SAR acquisition in stripmap mode comprises respective radar transmission and reception operations that are time interleaved, individually or in groups, with single, or groups of, radar transmission and reception operations of the other N-1 SAR acquisitions in stripmap mode performed, and which comprise the transmission and reception of respective radar beams in respective acquisition directions that are defined by the respective squint angle and by the respective elevation angle used for said SAR acquisition in stripmap mode, thereby resulting in that said respective acquisition directions are parallel to each other and not parallel to the acquisition directions of the other N-1 SAR acquisitions in stripmap mode performed. The method further comprises generating, on the basis of each SAR acquisition in stripmap mode performed, SAR images of areas of the respective swath observed via said SAR acquisition in stripmap mode. All the SAR images generated have one and the same azimuth resolution that is equal to half the physical or equivalent length along the azimuth direction of the single, non-partitioned antenna of the synthetic aperture radar.

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

The present invention concerns a SAR imaging method, which comprises performing N SAR acquisitions in stripmap mode of areas of the earth's surface by means of a synthetic aperture radar (20) that is transported by an aerial or satellite platform and which comprises a single, non-partitioned antenna and a single receiver coupled to said single, non-partitioned antenna, N being an integer greater than one- All the N SAR acquisitions in stripmap mode are performed using one and the same predetermined elevation angle with respect to the nadir of the synthetic aperture radar (20) so that said N SAR acquisitions in stripmap mode all regard one and the same specific swath of the earth's surface. Each SAR acquisition in stripmap mode is performed using a respective squint angle with respect to the flight direction of the synthetic aperture radar (20), said respective squint angle being different from the squint angles used for performing the other N-1 SAR acquisitions in stripmap mode. Each performed SAR acquisition in stripmap mode comprises respective radar transmission and reception operations that are time interleaved, individually or in groups, with single, or groups of, radar transmission and reception operations of the other N-1 SAR acquisitions in stripmap mode performed, and which comprise the transmission and reception of respective radar beams in respective acquisition directions that are defined by the predetermined elevation angle and by the respective squint angle used for said SAR acquisition in stripmap mode, thereby resulting in that said respective acquisition directions are parallel to each other and not parallel to the acquisition directions of the other N-1 SAR acquisitions in stripmap mode performed. The radar beams transmitted and received in two radar transmission and reception operations performed in two immediately successive time instants and related to two different SAR acquisitions in stripmap mode are contiguous along the azimuth, thereby increasing the integration times with respect to those obtainable via any one of the N SAR acquisitions in stripmap mode performed. The method further comprises generating SAR images of areas of the specific swath on the basis of all the N SAR acquisitions in stripmap mode performed, said SAR images having an azimuth resolution that is enhanced by a factor up to N with respect to a nominal stripmap azimuth resolution that is equal to half the physical or equivalent length along the azimuth direction of the single, non-partitioned antenna of the synthetic aperture radar (20).

IPC Classes  ?

• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

The invention concerns a method for reducing the costs of a satellite remote sensing service. Said method comprises providing a satellite remote sensing system (1) that includes only one satellite (11) equipped with a sensor (111) configured to acquire images of areas o;f the Earth's surface, said satellite remote sensing system (1) being designed to provide a satellite remote sensing service based on the images acquired by the sensor (111) on board the satellite (11). In particular, the satellite (11) follows a predefined orbit around the Earth with an orbit repeat cycle shorter than three days whereby a satellite remote sensing service with very good time performances and excellent interferometric capabilities and with drastically reduced costs is obtained.

IPC Classes  ?

• B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles
• B64G 1/24 - Guiding or controlling apparatus, e.g. for attitude control
• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

A large deployable reflector (1) for an antenna suitable for being installed on board a satellite (2) and provided with a support structure (6), a parabolic mirror (5a) carried by the support structure (6) and a connection arm (7) for mounting the support structure (6) on the satellite; the support structure (6) being a jointed reticulate structure that is able to assume a compact inoperative stowed configuration and an operative deployed configuration and is composed of 'n' elements (13) articulated to form tetrahedrons (8) having respective triangular bases (9), which are connected to each other at the axial ends of respective first sides (9a) and have respective external vertices (11), which are opposite to said respective first sides (9a) and, when the reflector (1) is arranged in the deployed configuration, ideally lie on a cone tangent to the parabolic mirror (5a).

IPC Classes  ?

• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
• B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• H01Q 15/16 - Reflecting surfacesEquivalent structures curved in two dimensions, e.g. paraboloidal

Abstract

A large deployable reflector (1) for an antenna suitable for being installed on board a satellite (2) and provided with a support structure (6), a parabolic mirror (5a) carried by the support structure (6) and a connection arm (7) for mounting the support structure (6) on the satellite; the support structure (6) being a jointed reticulate structure that is able to assume a compact inoperative stowed configuration and an operative deployed configuration and is composed of 'n' elements (13) articulated to form tetrahedrons (8) having respective triangular bases (9), which are connected to each other at the axial ends of respective first sides (9a) and have respective external vertices (11), which are opposite to said respective first sides (9a) and, when the reflector (1) is arranged in the deployed configuration, ideally lie on a cone tangent to the parabolic mirror (5a).

IPC Classes  ?

• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
• H01Q 15/16 - Reflecting surfacesEquivalent structures curved in two dimensions, e.g. paraboloidal
• B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles

Abstract

A navigation system for exploring and/or monitoring unknown and/or difficult environments is provided that includes a mission control module, an unmanned vehicle operable for carrying out the exploration and/or monitoring mission, a primary node coupled to the mission control module that includes an ultra-wideband radio interface, and a plurality of secondary nodes for deployment in the unknown and/or difficult environment, each secondary node including an ultra-wideband radio interface. The primary node and secondary nodes are configured to form a hierarchical communication and localization network in which the primary node is associated with a primary hierarchical level and each secondary node is associated with a respective secondary hierarchical level lower than the primary hierarchical level. On the basis of distance measurements and distance-related messages associated with the system, a local reference coordinate system indicative of the positions of the secondary nodes with respect to the primary node is established.

IPC Classes  ?

• G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
• G05D 3/00 - Control of position or direction
• G06F 7/00 - Methods or arrangements for processing data by operating upon the order or content of the data handled
• G07F 17/00 - Coin-freed apparatus for hiring articlesCoin-freed facilities or services

Abstract

The present invention relates to a method for acquiring SAR images for interferometric processing. The method comprises acquiring, by one or more airborne SAR sensors, SAR images of one and the same area with an acquisition geometry such that to enable interferometric processing of said SAR images. The method is characterized by an acquisition geometry in which each SAR image of the area is acquired in a respective direction of acquisition that defines a respective squint angle with respect to the direction of flight, and in which the squint angles are such that to determine a mean squint angle different from zero.

IPC Classes  ?

• G01S 13/00 - Systems using the reflection or reradiation of radio waves, e.g. radar systemsAnalogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
• G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

Abstract

Described herein is a projective optical metrology system including: a light target formed by a first number of light sources having a pre-set spatial arrangement; and an optical unit including an optoelectronic image sensor, which receives a light signal coming from the light target and defines two different optical paths for the light signal towards the optoelectronic image sensor. The two optical paths are such that the light signal forms on the optoelectronic image sensor at most an image of the light target that can be processed for determining at least one quantity indicating the mutual arrangement between the light target and the optical unit.

IPC Classes  ?

• G01B 11/26 - Measuring arrangements characterised by the use of optical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of optical techniques for testing the alignment of axes
• G01C 1/00 - Measuring angles

Abstract

Described herein is a projective optical metrology system including: a light target equipped with a plurality of light sources having a pre-set spatial arrangement; an optoelectronic image sensor; an optical unit receiving a light signal coming from the light target and defining two different optical paths for the light signal towards the optoelectronic image sensor, the two optical paths being such as to cause simultaneous formation on the optoelectronic image sensor of at least two images of the light target; and an electronic processing unit coupled to the optoelectronic image sensor and determining a plurality of different quantities indicating the position and attitude of the light target with respect to the optical unit, on the basis of the two images.

IPC Classes  ?

• G01B 11/14 - Measuring arrangements characterised by the use of optical techniques for measuring distance or clearance between spaced objects or spaced apertures

Abstract

The present invention regards an antenna system comprising a reflection system that comprises a reflector having a rotational symmetry with respect to an axis of symmetry. Moreover, the antenna system also comprises an electronically steerable planar radiating array that is arranged in a focal region of the reflection system, has a rotational symmetry with respect to the axis of symmetry and is operable to radiate a primary radiofrequency beam oriented in a predefined direction of illumination with respect to the axis of symmetry in such a way as to cause a specific region of the reflector to be illuminated by said primary radiofrequency beam. Said specific region of the reflector is designed, when illuminated by said primary radiofrequency beam, to generate by reflection a secondary radiofrequency beam oriented in at least one predefined direction of transmission with respect to the axis of symmetry.

IPC Classes  ?

• H01Q 19/10 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
• H01Q 13/10 - Resonant slot antennas
• H01Q 3/26 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elementsArrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the distribution of energy across a radiating aperture
• H01Q 15/14 - Reflecting surfacesEquivalent structures
• H01Q 19/17 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave the primary radiating source comprising two or more radiating elements
• H01Q 19/19 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces comprising one main concave reflecting surface associated with an auxiliary reflecting surface

Abstract

A method for acquiring a direct sequence spread spectrum signal, which is transmitted on a carrier frequency and is modulated with a code signal of length equal to Nc chips, for determining a code delay of the spread spectrum signal and a Doppler shift with respect to the carrier frequency, the determination being performed on a discrete two-dimensional space of M possible code delays and F possible frequency shifts, includes: receiving and sampling the spread spectrum signal to obtain a sampled spread spectrum signal; performing a despreading operation of the sampled spread spectrum signal with a local replica signal of the code signal, by performing the despreading for a plurality of possible code delays between the sampled signal and the replica signal; and performing a parallel frequency search on the result of the despreading step, by performing a step of computing a Fourier transform on the result. The Fourier transform is a fractional Fourier transform.

IPC Classes  ?

• H04B 1/00 - Details of transmission systems, not covered by a single one of groups Details of transmission systems not characterised by the medium used for transmission

Abstract

A method of and a system for synchronizing a plurality of spaced apart nodes of a network to a reference time of a control center, the method comprising receiving measurement data from each of the plurality of nodes; ranking the plurality of nodes with respect to one another according to the measurement data; selecting one or more master nodes from the plurality of nodes according to the ranking; assigning each of the plurality of nodes to a corresponding master node; determining a first time offset between the local time measured at each node and the local time measured at its corresponding master node and determining a second time offset between each of the master nodes and the reference time such that the time offset between the local time measured at each node and the reference time can be determined.

IPC Classes  ?

• H04B 7/212 - Time-division multiple access

Abstract

A method (100) is described, for acquiring a direct sequence spread spectrum signal (s(t)), which is transmitted on a carrier frequency and is modulated with a code signal of length equal to Nc chips, for determining a code delay of said spread spectrum signal and a Doppler shift with respect to said carrier frequency, said determination being performed on a discrete two-dimensional space of M possible code delays and F possible frequency shifts, the method (100) comprising the following steps: - receiving and sampling (102) said spread spectrum signal in order to obtain a sampled spread spectrum signal; - performing a despreading operation (103) of said sampled spread spectrum signal with a local replica signal of said code signal, by performing said despreading for a plurality of possible code delays between said sampled signal and said replica signal; - performing a parallel frequency search (104, 105, 107, 108, 109) on the result of said despreading step, by performing a step (104) of computing a Fourier transform on said result. The Fourier transform is a fractional Fourier transform.

IPC Classes  ?

• H04B 1/707 - Spread spectrum techniques using direct sequence modulation

Abstract

A method of and a system for synchronising a plurality of spaced apart nodes of a network to a reference time of a control centre, the method comprising receiving measurement data from each of the plurality of nodes; ranking the plurality of nodes with respect to one another according to the measurement data; selecting one or more master nodes from the plurality of nodes according to the ranking; assigning each of the plurality of nodes to a corresponding master node; determining a first time offset between the local time measured at each node and the local time measured at its corresponding master node and determining a second time offset between each of the master nodes and the reference time such that the time offset between the local time measured at each node and the reference time can be determined.

IPC Classes  ?

• H04B 7/26 - Radio transmission systems, i.e. using radiation field for communication between two or more posts at least one of which is mobile