A fluid purifying device includes inlet and emission openings, an outer tube having a first end on a first side of the device relative to a reference plane, the inlet opening at the first end of the outer tube, an inner tube, within the outer tube and having a second end on a second side of the device, opposite to the first side relative to the reference plane, the emission opening at the second end of the inner tube, an intermediate tube between the outer and inner tubes defining a fluid path between the inlet and emission openings, the fluid path including a first stretch between the outer and intermediate tubes, a second stretch between the intermediate and inner tubes, and a third stretch within the inner tube, and a UV-C radiation source within the outer tube to irradiate the fluid at least along the first stretch.
A61L 9/20 - Désinfection, stérilisation ou désodorisation de l'air utilisant des phénomènes physiques des radiations des ultraviolets
C02F 1/32 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout par irradiation par la lumière ultraviolette
F24F 8/22 - Traitement, p. ex. purification, de l'air fourni aux locaux de résidence ou de travail des êtres humains autrement que par chauffage, refroidissement, humidification ou séchage par stérilisation utilisant de la lumière ultraviolette
2.
THRUSTER FOR ORBITAL MANEUVERS, PROPULSION SYSTEM FOR ORBITAL MANEUVERS AND ORBITAL TRANSPORT VEHICLE
A thruster (100) for orbital maneuvers comprises a divergent channel (111) having an axial axis of symmetry (S); a combustion chamber (110); a throat (112) interposed between the combustion chamber (110) and the divergent channel (111); an injection plate (115) facing the combustion chamber (110); a plurality of first injection channels (125) in fluid communication with the combustion chamber (110), each comprising an end portion (126) open in the combustion chamber (110); at least one second injection channel (135) in fluid communication with the combustion chamber (110), comprising an end portion (136) open in the combustion chamber (110); wherein the end portions (126) of the first injection channels (125) are placed in an annular region (127) and extend along respective injection directions (dl); wherein the end portion (136) of the at least one second injection channel (135) is placed radially between said axis of symmetry (S) and the end portions (126) of the first injection channels (125); wherein the injection direction (dl) of the end portion (126) of each first injection channel (125) has an axial component directed toward the combustion chamber (110) and a radial component directed toward the axis of symmetry (S).
F02K 9/80 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par la commande de la poussée ou du vecteur poussée
B01D 53/00 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols
A61L 9/20 - Désinfection, stérilisation ou désodorisation de l'air utilisant des phénomènes physiques des radiations des ultraviolets
C02F 1/32 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout par irradiation par la lumière ultraviolette
F24F 8/22 - Traitement, p. ex. purification, de l'air fourni aux locaux de résidence ou de travail des êtres humains autrement que par chauffage, refroidissement, humidification ou séchage par stérilisation utilisant de la lumière ultraviolette
A satellite module for attitude determination includes a containment body comprising at least one data acquisition board and a connection interface, at least one first-type sensor selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, in communication with the data acquisition board and at least one second-type sensor, different from the first type, selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, and in communication with the data acquisition board. The connection interface may be mounted on a first face of the containment body, the first-type sensor may be mounted on a second face of the containment body, and the second-type sensor may be mounted on a third face of the containment body.
B64G 1/24 - Appareils de guidage ou de commande, p. ex. de commande d'assiette
G01S 3/786 - Systèmes pour déterminer une direction ou une déviation par rapport à une direction prédéterminée utilisant le réglage d'une orientation des caractéristiques de directivité d'un détecteur ou d'un système de détecteurs afin d'obtenir une valeur désirée du signal provenant de ce détecteur ou de ce système de détecteurs la valeur désirée étant maintenue automatiquement
G01J 5/12 - Pyrométrie des radiations, p. ex. thermométrie infrarouge ou optique en utilisant des détecteurs électriques de radiations en utilisant des éléments thermoélectriques, p. ex. des thermocouples
B64G 1/36 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par des capteurs, p. ex. par des capteurs solaires, des capteurs d'horizon
B64G 1/66 - Aménagements ou adaptations d'appareils ou d'instruments, non prévus ailleurs
B64G 1/28 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par inertie ou par effet gyroscopique
09 - Appareils et instruments scientifiques et électriques
39 - Services de transport, emballage et entreposage; organisation de voyages
Produits et services
Motors, other than for land vehicles. Satellites; optical position sensors; sensors for use in the
control of engines; rotation controlling sensors, sensors
for determining position; sensors, detectors and monitoring
instruments; electronic control systems; electronic chip
cards; computers and computer hardware; software. Launching of satellites; launching of satellites for others;
launch and placement in prescribed orbit of satellites of
others.
09 - Appareils et instruments scientifiques et électriques
39 - Services de transport, emballage et entreposage; organisation de voyages
Produits et services
(1) Motors for satellites, other than for land vehicles
(2) Satellites; optical position sensors; sensors for determining velocity for use in the control of engines; rotation controlling sensors; sensors for determining position; sensors, detectors and monitoring instruments, namely, automatic altitude and orbit sensor indicators; electronic control systems for launching of satellites; electronic chip cards, namely, electronic circuit cards, electronic identification cards, DVR cards, encoded electronic chip cards for identifying particular users of computers and mobile phones; computers and computer hardware; downloadable software, namely, onboard flight software and ground segment software for database management and launching of satellites; all of the aforesaid goods not for use in the field of irrigation systems, home automation systems and components of irrigation systems and home automation systems. (1) Launching of satellites; launching of satellites for others; launch and placement in prescribed orbit of satellites of others.
09 - Appareils et instruments scientifiques et électriques
39 - Services de transport, emballage et entreposage; organisation de voyages
Produits et services
Motors, other than for land vehicles Satellites; optical position sensors; sensors for use in the control of engines; rotation controlling sensors; sensors for determining position; sensors, detectors and monitoring instruments, namely, altitude and orbit determination sensors; computers and computer hardware; downloadable software, namely, onboard flight software and ground segment software for database management and launching of satellites; excluding from all of the foregoing irrigation systems, home automation systems and components of irrigation systems and home automation systems Launching of satellites for others; launch and placement in prescribed orbit of satellites of others
09 - Appareils et instruments scientifiques et électriques
39 - Services de transport, emballage et entreposage; organisation de voyages
Produits et services
Motors, other than for land vehicles. Satellites; Optical position sensors; Sensors for use in the control of engines; Rotation controlling sensors; Sensors for determining position; Sensors, detectors and monitoring instruments; Electronic control systems; Electronic chip cards; Computers and computer hardware; Software; excluding from all of the foregoing irrigation systems, home automation systems and components of irrigation systems and home automation systems. Launching of satellites; Launching of satellites for others; Launch and placement in prescribed orbit of satellites of others.
A satellite module (10) for attitude determination comprises a containment body (11) comprising at least one data acquisition board (17) and a connection interface (14), at least one first-type sensor (12) selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, in communication with the data acquisition board (17) and at least one second-type sensor (13), different from the first type, selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, and in communication with the data acquisition board (17). The connection interface (14) is mounted on a first face (19) of the containment body (11), the first-type sensor (12) is mounted on a second face (20) of the containment body (11), and the second-type sensor (13) is mounted on a third face (21) of the containment body (11).
B64G 1/36 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par des capteurs, p. ex. par des capteurs solaires, des capteurs d'horizon
B64G 1/66 - Aménagements ou adaptations d'appareils ou d'instruments, non prévus ailleurs
G01S 3/786 - Systèmes pour déterminer une direction ou une déviation par rapport à une direction prédéterminée utilisant le réglage d'une orientation des caractéristiques de directivité d'un détecteur ou d'un système de détecteurs afin d'obtenir une valeur désirée du signal provenant de ce détecteur ou de ce système de détecteurs la valeur désirée étant maintenue automatiquement
A satellite module (10) for attitude determination comprises a containment body (11) comprising at least one data acquisition board (17) and a connection interface (14), at least one first-type sensor (12) selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, in communication with the data acquisition board (17) and at least one second-type sensor (13), different from the first type, selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, and in communication with the data acquisition board (17). The connection interface (14) is mounted on a first face (19) of the containment body (11), the first-type sensor (12) is mounted on a second face (20) of the containment body (11), and the second-type sensor (13) is mounted on a third face (21) of the containment body (11).
B64G 1/36 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par des capteurs, p. ex. par des capteurs solaires, des capteurs d'horizon
B64G 1/66 - Aménagements ou adaptations d'appareils ou d'instruments, non prévus ailleurs
G01C 21/24 - NavigationInstruments de navigation non prévus dans les groupes spécialement adaptés pour la navigation des cosmonautes
11.
Method for the safe release of artificial satellites in earth's orbit
A method for the safe release of artificial satellite in Earth orbit includes the steps of providing an orbital transport spacecraft able to move at orbital height and comprising a plurality of PODs for releasing satellites transported by the orbital transport spacecraft, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height; generating a release signal and transmitting it to the orbital transport spacecraft to release the orbital transport spacecraft from the space launcher, in case of failure to release the orbital transport spacecraft or in case of breakdown of the orbital transport spacecraft after releasing from the space launcher, activating a safety subsystem of the orbital transport spacecraft to generate a POD activation sequence to release the satellites.
A method of releasing artificial satellites into Earth's orbit includes providing an orbital transport spacecraft able to move at orbital height and comprising a cargo area, hooking a plurality of satellites in said cargo area, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height, releasing said orbital transport spacecraft at orbital height, when said space launcher reaches orbital height, by imparting a separation thrust to said orbital transport spacecraft, releasing satellites in sequence from the cargo area. The release of each satellite from the cargo area occurs in a respective predetermined direction and upon the orbital transport spacecraft has reached a respective predetermined position.
The invention relates to a method of releasing artificial satellites into Earth's orbit comprising providing an orbital transport spacecraft (1) able to move at orbital height and comprising a cargo area (12a), hooking a plurality of satellites (12) in said cargo area (12a), housing said orbital transport spacecraft in a space launcher (100) configured to reach an orbital height, releasing said orbital transport spacecraft (1) at orbital height, when said space launcher (100) reaches orbital height, by imparting a separation thrust to said orbital transport spacecraft (1), releasing satellites (12) in sequence from the cargo area (12a). The release of each satellite (12) from the cargo area (12a) occurs in a respective predetermined direction and upon the orbital transport spacecraft (1) has reached a respective predetermined position.
The invention relates to a method for the safe release of artificial satellite in Earth orbit comprising providing an orbital transport spacecraft (1) able to move at orbital height and comprising a plurality of PODs (11) for releasing satellites (12) transported by the orbital transport spacecraft (1), housing said orbital transport spacecraft (1) in a space launcher (100) configured to reach an orbital height; generating a release signal and transmitting it to the orbital transport spacecraft (1) to release the orbital transport spacecraft (1) from the space launcher (100), in case of failure to release the orbital transport spacecraft (1) or in case of breakdown of the orbital transport spacecraft (1) after releasing from the space launcher (100), activating a safety subsystem (21) of the orbital transport spacecraft (1) to generate a POD (11) activation sequence to release the satellites (12).
The invention relates to a method of releasing artificial satellites into Earth's orbit comprising providing an orbital transport spacecraft (1) able to move at orbital height and comprising a cargo area (12a), hooking a plurality of satellites (12) in said cargo area (12a), housing said orbital transport spacecraft in a space launcher (100) configured to reach an orbital height, releasing said orbital transport spacecraft (1) at orbital height, when said space launcher (100) reaches orbital height, by imparting a separation thrust to said orbital transport spacecraft (1), releasing satellites (12) in sequence from the cargo area (12a). The release of each satellite (12) from the cargo area (12a) occurs in a respective predetermined direction and upon the orbital transport spacecraft (1) has reached a respective predetermined position.
The invention relates to a method for the safe release of artificial satellite in Earth orbit comprising providing an orbital transport spacecraft (1) able to move at orbital height and comprising a plurality of PODs (11) for releasing satellites (12) transported by the orbital transport spacecraft (1), housing said orbital transport spacecraft (1) in a space launcher (100) configured to reach an orbital height; generating a release signal and transmitting it to the orbital transport spacecraft (1) to release the orbital transport spacecraft (1) from the space launcher (100), in case of failure to release the orbital transport spacecraft (1) or in case of breakdown of the orbital transport spacecraft (1) after releasing from the space launcher (100), activating a safety subsystem (21) of the orbital transport spacecraft (1) to generate a POD (11) activation sequence to release the satellites (12).
A propulsion system for small artificial satellites comprises a plurality of engines (2) fixable to a frame (101) of a satellite (100); a control unit (3) connected functionally to the engines (2) for sending at least one activation signal (AS) for activating at least one engine (2); the system is selectively configurable at least between a first configuration in which at least one of the engines (2) is activated for correcting the orbit of the satellite (100) and a second configuration in which at least one of the engines (2) is activated for dispersing said satellite (100) relative to another adjacent satellite.
coupler for mechanically coupling the device with the satellite before the satellite is launched.
The propulsion system is enabled by the controller on receipt of control signals for deorbiting the satellite and transferring it to a given orbit.
coupler for mechanically coupling the device with the satellite before the satellite is launched.
The propulsion system is enabled by the controller on receipt of control signals for deorbiting the satellite and transferring it to a given orbit.
The present invention relates to a device (10, 20, 40, 50) for coupling with a space satellite (20', 20") before the latter is launched for the purpose of re-orbiting said satellite and/or returning it to Earth. The device comprises. means for controlling the device (10, 20, 40, 50); propulsion means operatively connected with the control means; means for receiving control signals operatively connected with the control means; means for electrically powering the device (10, 20, 40, 50); means (310, 320, 330, 340', 340", 350, 360) for mechanically coupling the device (10, 20, 40, 50) with said satellite (20', 20") before the latter is launched. The propulsion means are enabled by the control means on receipt of control signals for de- orbiting the satellite (20', 20") and transferring it to a given orbit.
