Abrégé

[Problem] To provide a processing device, a processing program, a processing method, and a processing system that enable more efficient image processing. [Solution] A processing device includes at least one processor that is used for imaging by means of a spacecraft capable of imaging the earth. The at least one processor receives, from a first user terminal device available to a first user, first instruction information for instructing imaging of a first imaging object on the earth, receives, from a second user terminal device available to a second user different from the first user, second instruction information for instructing imaging of a second imaging object on the earth, and determines an imaging schedule for at least either of the first imaging object and the second imaging object on the basis of respective priorities which are set according to at least either of the first user and the second user, respectively, and the first instruction information and the second instruction information, respectively.

Classes IPC  ?

• B64G 1/10 - Satellites artificielsSystèmes de tels satellitesVéhicules interplanétaires

Abrégé

[Problem] To provide a processing device and a computer program that provide an image and/or image data more smoothly to a user that desires imaging by a spacecraft. [Solution] A processing device according to one embodiment is "a processing device including at least one processor used in conjunction with a spacecraft that images the earth, wherein the at least one processor" may be "configured to: receive, from a terminal device of a user, an order condition including coordinates of a location to be imaged or the coordinates and a date and time at which to image the location; send, to the terminal device of the user, determination results expressing whether imaging by the spacecraft based on the order condition is possible; and, if the determination results express that imaging by the spacecraft based on the order condition is possible, send, to the terminal device of the user, at least one candidate condition including a candidate date and time at which imaging of the location is possible."

Classes IPC  ?

• B64G 1/10 - Satellites artificielsSystèmes de tels satellitesVéhicules interplanétaires
• B64G 1/24 - Appareils de guidage ou de commande, p. ex. de commande d'assiette
• G06Q 50/00 - Technologies de l’information et de la communication [TIC] spécialement adaptées à la mise en œuvre des procédés d’affaires d’un secteur particulier d’activité économique, p. ex. aux services d’utilité publique ou au tourisme

Abrégé

[Problem] To provide a spacecraft that has an improved heat discharging capability. [Solution] A spacecraft (1) according to one embodiment of the present invention comprises: a body (300) which has mounted therewithin multiple devices including an oscillator (111) that outputs a signal having a frequency in at least one frequency band; multiple heat radiation plates (402) that are arranged outside the body, extend substantially parallel to a reference direction (D), and are provided so as to face each other; at least one amplifier (112) that is configured to be disposed in a region surrounded by the heat radiation plates (402), to be connected to one of the heat radiation plates (402), and to amplify a signal outputted by the oscillator (111); and an antenna unit (131, 132) that is configured to be disposed outside the body (300), and to radiate electric waves propagating along the reference direction (D) using the signal amplified by the at least one amplifier (112).

Classes IPC  ?

• B64G 1/50 - Aménagements ou adaptations des dispositifs de contrôle de l'environnement ou des conditions de vie pour la commande de la température

Abrégé

Provided are a spacecraft control system, a spacecraft control method, and a server device capable of quickly transmitting control data to a spacecraft. The spacecraft system includes: a plurality of spacecrafts; a plurality of small communicators that transmit control data related to imaging operations of the spacecrafts to the spacecrafts; and at least one ground station that receives, from the spacecrafts, captured image data related to images captured by the spacecrafts and space position data for the spacecrafts, and transmits identification data for the small communicators to the spacecrafts, in which each of the spacecrafts includes at least a first reception device that receives the control data transmitted from the small communicators, a control device that controls an imaging operation of the spacecraft on the basis of the control data received by the first reception device, and an imaging device that executes the imaging operation.

Classes IPC  ?

• B64G 1/10 - Satellites artificielsSystèmes de tels satellitesVéhicules interplanétaires
• H04B 7/185 - Stations spatiales ou aériennes

Abrégé

To provide a connection adapter and a horn antenna measurement device capable of measuring the performance of a system of a horn antenna on the ground without removing the horn antenna mounted on a spacecraft even immediately before the launch, while suppressing radio wave leakage to an external space. A connection adapter (200) includes a first waveguide (201) that is provided inside the connection adapter and connected to a waveguide portion (260) connected to a horn antenna (100), in which the connection adaptor is detachably fitted into the horn antenna, is connected to a measurement instrument (300) via a second waveguide (250) coupled to the first waveguide, and guides radio waves radiated from the horn antenna to the measurement instrument in a closed system.

Classes IPC  ?

• G01R 29/08 - Mesure des caractéristiques du champ électromagnétique

Abrégé

[Problem] To provide a spacecraft having a more effective arrangement of amplifiers. [Solution] Provided is a spacecraft comprising: a main body having a housing space for housing an electronic device within; an oscillator configured to output a radio wave including a frequency in a predetermined frequency band; an amplifier disposed on an exterior of the main body so as to be exposed to space and configured to amplify the power of the radio wave output by the oscillator; and an antenna, disposed on the exterior of the main body, for emitting the radio wave to the outside at the power amplified by the amplifier.

Classes IPC  ?

• B64G 1/10 - Satellites artificielsSystèmes de tels satellitesVéhicules interplanétaires
• B64G 1/66 - Aménagements ou adaptations d'appareils ou d'instruments, non prévus ailleurs
• H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons

Abrégé

[Problem] To provide a spacecraft control system, a spacecraft control method, and a server device whereby it is possible to quickly transmit control data to a spacecraft. [Solution] In this invention, a spacecraft system includes: a plurality of spacecraft; a plurality of small communicators that transmit control data related to the imaging operation of the spacecraft to the spacecraft; and at least one ground station that receives, from the spacecraft, image data related to images captured by the spacecraft and the space position data of the spacecraft and transmits, to the spacecraft, the identification data of the small communicators. The spacecraft has at least a first reception device that receives the control data transmitted from the small communicators, a control device that controls the imaging operation of the spacecraft on the basis of the control data received by the first reception device, and an imaging device that performs the imaging operation.

Classes IPC  ?

• B64G 1/10 - Satellites artificielsSystèmes de tels satellitesVéhicules interplanétaires
• H04B 7/155 - Stations terrestres
• H04L 9/32 - Dispositions pour les communications secrètes ou protégéesProtocoles réseaux de sécurité comprenant des moyens pour vérifier l'identité ou l'autorisation d'un utilisateur du système

Abrégé

[Problem] To provide a connection adapter and a horn antenna measurement device that can measure, on the ground, the performance of a horn antenna system even just before a launch without removing a horn antenna mounted on a spacecraft while suppressing the leakage of radio waves to an external space. [Solution] A connection adapter (200) internally includes a first waveguide (201) connected to a waveguide unit (260) leading to a horn antenna (100). The connection adapter (200) is connected to a measurement device (300) via a second waveguide (250) that is detachably fitted to the horn antenna and connected to the first waveguide, and guides radio waves emitted from the horn antenna to the measurement device via a closed system.

Classes IPC  ?

• H01P 1/00 - Dispositifs auxiliaires
• H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
• H01Q 13/02 - Cornets de guide d'onde

Abrégé

Spacecraft and antenna apparatus that can be more easily deployed from a stored state can include: a main-reflection unit including a plurality of ribs formed to be deployable in a stored state in which the ribs are folded and a sheet body provided between a plurality of the ribs and configured to be capable of reflecting a radio wave radiated from a radiator and emitting the radio wave outside, and a restriction member configured to restrict deployment of the plurality of ribs in the stored state, and release the restriction by operation of a restriction release member different from the main-reflection unit.

Classes IPC  ?

• H01Q 1/24 - SupportsMoyens de montage par association structurale avec d'autres équipements ou objets avec appareil récepteur
• H01Q 1/08 - Moyens pour replier tout ou partie des antennes
• H01Q 1/12 - SupportsMoyens de montage
• H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
• H01Q 15/20 - Réflecteurs pliables
• H01Q 19/19 - Combinaisons d'éléments actifs primaires d'antennes avec des dispositifs secondaires, p. ex. avec des dispositifs quasi optiques, pour donner à une antenne une caractéristique directionnelle désirée utilisant des surfaces réfléchissantes comportant plusieurs surfaces réfléchissantes comprenant une surface réfléchissante principale concave associée à une surface réfléchissante auxiliaire

Abrégé

A spacecraft includes: a main-reflection unit configured to reflect and emit a radio wave outside, a sub-reflection unit configured to face the main-reflection unit, a radiator arranged to face the sub-reflection unit and configured to radiate the radio wave in a direction of the sub-reflection unit, a main body configured to be able to accommodate at least one part of the sub-reflection unit therein, and a delivery device connected to the sub-reflection unit and configured to deliver the sub-reflection unit, at least one part of which is accommodated in the main body, to a position where the sub-reflection unit is able to reflect the radio wave radiated from the radiator to the main-reflection unit and cause the main-reflection unit to radiate the radio wave outside.

Classes IPC  ?

• H01Q 1/24 - SupportsMoyens de montage par association structurale avec d'autres équipements ou objets avec appareil récepteur
• H01Q 1/08 - Moyens pour replier tout ou partie des antennes
• H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
• H01Q 19/19 - Combinaisons d'éléments actifs primaires d'antennes avec des dispositifs secondaires, p. ex. avec des dispositifs quasi optiques, pour donner à une antenne une caractéristique directionnelle désirée utilisant des surfaces réfléchissantes comportant plusieurs surfaces réfléchissantes comprenant une surface réfléchissante principale concave associée à une surface réfléchissante auxiliaire

Abrégé

Deployable reflectors and antennas and spacecraft using such reflectors are disclosed. An example disclosed reflector includes: a hub having a cross-section formed in a circular, elliptical or polygonal shape; a plurality of ribs, each rib having an inner side surface facing an outer peripheral side of the hub when folded, and an outer side surface that is a surface opposite to the inner side surface, the plurality of ribs being folded to be wound around an outer periphery of the hub such that the inner side surface of each rib and the outer side surface of its adjacent rib partially face each other or the outer side surface of each rib and the inner side surface of its adjacent rib partially face each other, each rib being deployed in a parabolic shape; and a sheet installed across each of the plurality of ribs and capable of reflecting radio waves.

Classes IPC  ?

• H01Q 15/16 - Surfaces réfléchissantesStructures équivalentes courbes suivant deux dimensions, p. ex. paraboloïdales
• H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
• H01Q 15/20 - Réflecteurs pliables

Abrégé

[Problem] To provide a spacecraft having a more effective arrangement of amplifiers. [Solution] Provided is a spacecraft comprising: a main body having a housing space for housing an electronic device within; an oscillator configured to output a radio wave including a frequency in a predetermined frequency band; an amplifier disposed on an exterior of the main body so as to be exposed to space and configured to amplify the power of the radio wave output by the oscillator; and an antenna, disposed on the exterior of the main body, for emitting the radio wave to the outside at the power amplified by the amplifier.

Classes IPC  ?

• B64G 1/66 - Aménagements ou adaptations d'appareils ou d'instruments, non prévus ailleurs
• G01S 13/90 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour la cartographie ou la représentation utilisant des techniques d'antenne synthétique
• H01Q 15/16 - Surfaces réfléchissantesStructures équivalentes courbes suivant deux dimensions, p. ex. paraboloïdales

Abrégé

[Problem] To provide: an antenna device which can be unfolded from a state of being more compactly stored; and a space navigation body. [Solution] Provided is a space navigation body comprising: a main reflector configured to reflect a radio wave and radiate the radio wave to the outside; a sub-reflector configured to be arranged facing the main reflector; a radiator arranged to face the sub-reflector and configured to radiate the radio wave toward the sub-reflector; a main body configured to be able to accommodate at least a portion of the sub-reflector therein; and a delivery device connected to the sub-reflector and configured to deliver the sub-reflector, of which at least a portion is accommodated in the main body, to a position where the radio wave radiated by the radiator can be reflected by the main reflector and can be radiated from the main reflector to the outside.

Classes IPC  ?

• H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
• H01Q 1/08 - Moyens pour replier tout ou partie des antennes
• H01Q 19/19 - Combinaisons d'éléments actifs primaires d'antennes avec des dispositifs secondaires, p. ex. avec des dispositifs quasi optiques, pour donner à une antenne une caractéristique directionnelle désirée utilisant des surfaces réfléchissantes comportant plusieurs surfaces réfléchissantes comprenant une surface réfléchissante principale concave associée à une surface réfléchissante auxiliaire

Abrégé

[Problem] To provide an antenna device and spacecraft that can be more easily deployed from a stowed state. [Solution] Provided is an antenna device comprising: a main reflector comprising a plurality of ribs formed so as to be deployable from a folded-up stowed state, and planar elements erected between the plurality of ribs and configured to be capable of reflecting and radiating outward radio waves that have been radiated by a radiator; and a restricting member that restricts the deployment of the plurality of ribs in the stowed state, and is configured so that the restriction is released by the operation of a restriction release member different from the main reflector.

Classes IPC  ?

• H01Q 15/20 - Réflecteurs pliables
• H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
• H01Q 19/19 - Combinaisons d'éléments actifs primaires d'antennes avec des dispositifs secondaires, p. ex. avec des dispositifs quasi optiques, pour donner à une antenne une caractéristique directionnelle désirée utilisant des surfaces réfléchissantes comportant plusieurs surfaces réfléchissantes comprenant une surface réfléchissante principale concave associée à une surface réfléchissante auxiliaire

Abrégé

An expandable antenna includes: a plurality of ribs arranged with a regulated angular pitch at an outer circumferential portion of a hub; and a metal mesh installed between the plurality of adjacent ribs, wherein each of the plurality of ribs is formed in a horizontally elongated thin flat plate shape with elasticity, and a segment to which the metal mesh is attached is formed in a parabolic shape. A flat plane of each of the plurality of ribs is arranged so as to be substantially parallel to a central axis of the hub. The object of the present invention is to provide the expandable antenna which can be easily expanded in outer space with a simple structure and can realize a desired shape after expansion.

Classes IPC  ?

• H01Q 15/16 - Surfaces réfléchissantesStructures équivalentes courbes suivant deux dimensions, p. ex. paraboloïdales
• H01Q 15/20 - Réflecteurs pliables
• B64G 1/22 - Parties de véhicules spatiaux ou équipements spécialement destinés à être fixés dans ou sur ces véhicules
• B64G 1/66 - Aménagements ou adaptations d'appareils ou d'instruments, non prévus ailleurs
• H01Q 1/08 - Moyens pour replier tout ou partie des antennes

Abrégé

[Purpose] To provide a reflector that can be developed in an easier way and a developed antenna and an aerospace vehicle that use the reflector. [Solution] Provided is a reflector comprising: a hub the cross section of which is formed in a circular shape, an elliptical shape or a polygonal shape; a plurality of ribs each of which has an inner surface facing the perimeter of the hub when the rib is folded, each rib also having an outer surface that is the opposite surface to the inner surface, the plurality of ribs being able to be folded in such a manner that the inner surface of each rib and the outer surface of the rib adjacent thereto or the outer surface of each rib and the inner surface of the rib adjacent thereto partially overlap each other and are wound about the perimeter of the hub, the plurality of ribs being able to be developed, from the terminal end connected to the hub toward the front end located oppositely to the terminal end, into a parabolic shape; and sheet-like bodies that are installed between respective ones of the plurality of ribs and that can reflect radio waves.

Classes IPC  ?

• H01Q 15/20 - Réflecteurs pliables
• B64G 1/66 - Aménagements ou adaptations d'appareils ou d'instruments, non prévus ailleurs

Abrégé

This expandable antenna is provided with a plurality of ribs which are arranged with a regular angular pitch around the outer circumference of a hub, and a metal mesh which is suspended between a plurality of adjacent ribs, wherein: each of the plurality of ribs is formed in the shape of a resilient horizontally elongated thin, flat plate, and segments thereof to which the metal mesh is attached are formed with a parabolic shape; and the plurality of ribs are arranged in such a way that the plane of each of the plurality of ribs is substantially parallel to the central axis of the hub. The objective of the present invention is to enable the antenna to be expanded easily in outer space a using a simple configuration, and to enable a desired shape to be achieved after the antenna has been expanded.

Classes IPC  ?

• H01Q 15/20 - Réflecteurs pliables
• B64G 1/22 - Parties de véhicules spatiaux ou équipements spécialement destinés à être fixés dans ou sur ces véhicules
• B64G 1/66 - Aménagements ou adaptations d'appareils ou d'instruments, non prévus ailleurs

Abrégé

The present invention has the object of simplifying apparatus configuration and avoiding a requirement for calibration. The present invention achieves the above object by forming a detection sheet element that retains in a predetermined array pitch a plurality of conductive detection lines that are lead lines formed by etching or the like on a non-conductive thin film that can be exposed in a space environment. A detection circuit connected to each detection line of the detection sheet element is provided. When an object flying in space collides with the detection sheet body, since a detection line on the detection sheet element is ruptured, constant monitoring of the conductivity of the detection line by the detection circuit enables detection of the object flying in space that has collided with the detection sheet element when a detection line is ruptured. Furthermore a means of solution is adopted in which an effective diameter of a colliding object flying in space can be detected from the number of severed detection lines.

Classes IPC  ?

• G08B 23/00 - Alarmes réagissant à des conditions indésirables ou anormales, non spécifiées

Abrégé

Provided is a detecting device, which can be made so simple in constitution as to require no calibration. A thin film (2) of an inconductive material, which can be exposed to the space environment, is etched to form many detection lines (3) to become conductors at a predetermined array pitch, thereby to form a detection sheet element (1). The detecting device includes a detecting circuit (4) connected with the individual detection lines (3) of the detection sheet element (1). The detection lines (3) of the detection sheet element (1) are ruptured by space floating matters, when these space floating matters collide against the detection sheet element (1). Therefore, the conductions of the detection lines (3) are monitored at all times by the detecting circuit (4), so that the space floating matters having collided against the detection sheet element (1) are detected when the detection lines (3) are ruptured. A solving means can be adopted for detecting the effective diameter of the collided space floating matters from the number of the detection lines (3) cut out.

Classes IPC  ?

• B64G 1/68 - Aménagements ou adaptations d'appareils ou d'instruments, non prévus ailleurs des détecteurs de météoroïdes ou de débris spatiaux

Abrégé

The present invention has the object of simplifying apparatus configuration
and
avoiding a requirement for calibration. The present invention achieves the
above
object by forming a detection sheet element (1) that retains in a
predetermined array
pitch a plurality of conductive detection lines (3) that are lead lines formed
by etching
or the like on a non-conductive thin film (2) that can be exposed in a space
environment.
A detection circuit (4) connected to each detection line (3) of the detection
sheet
element (1) is provided. When an object flying in space collides with the
detection
sheet body (1), since a detection line (3) on the detection sheet element (1)
is ruptured,
constant monitoring of the conductivity of the detection line (3) by the
detection circuit
(4) enables detection of the object flying in space that has collided with the
detection
sheet element (1) when a detection line (3) is ruptured. Furthermore a means
of
solution is adopted in which an effective diameter of a colliding object
flying in space
can be detected from the number of severed detection lines (3).

Classes IPC  ?

• B64G 1/68 - Aménagements ou adaptations d'appareils ou d'instruments, non prévus ailleurs des détecteurs de météoroïdes ou de débris spatiaux