A method for attitude control of a satellite in inclined low orbit in survival mode is disclosed, the satellite including at least one solar generator, at least one solar sensor, magnetic torquers capable of forming internal magnetic moments in a satellite reference frame having three orthogonal axes X, Y, and Z, and inertial actuators capable of forming internal angular momentums in the satellite reference frame. The at least one solar sensor has a field of view at least 180° wide within the XZ plane around the Z axis, the method including a step of attitude control using a first control law, a step of searching for the sun by means of the at least one solar sensor, when a first phase of visibility of the sun is detected, and a step of attitude control using a second control law.
B64G 1/24 - Appareils de guidage ou de commande, p. ex. de commande d'assiette
B64G 1/28 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par inertie ou par effet gyroscopique
B64G 1/32 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par le champ magnétique terrestre
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
2.
Active waveguide transition having a probe and RF amplifier system and which is usable in a transmit/receive communication system
An active waveguide transition includes a waveguide defining a waveguide volume and including a back short wall at a first end. A first probe is mounted on the waveguide in an operable position extending into the waveguide volume, and a first RF electrical signal connector is mounted on the active waveguide transition. A first circuit assembly is mechanically coupled to an exterior surface of the waveguide, the circuit assembly including a first multi-layer ceramic substrate with an RF amplifier system mounted thereon. The RF amplifier system is electrically coupled to the multi-layer ceramic substrate, the first probe, and the first RF electrical signal connector to define an active first signal path for RF communication signals between the probe and first RF signal connector.
H01P 1/213 - Sélecteurs de fréquence, p. ex. filtres combinant ou séparant plusieurs fréquences différentes
H01P 5/103 - Transitions entre guides d'ondes creux et lignes coaxiales
H01P 5/18 - Dispositifs à accès conjugués, c.-à-d. dispositifs présentant au moins un accès découplé d'un autre accès consistant en deux guides couplés, p. ex. coupleurs directionnels
H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
An artificial satellite comprises a satellite structure, an onboard control system including an onboard controller, and a memory system. The memory system is physically coupled to the satellite structure and independently powerable with respect to the onboard controller. The memory system is also arranged to communicatively couple with the onboard controller, and to store data which specifies one or more launch-specific parameters for configuring at least one of the satellite components. The onboard control system is adapted to operate in a transfer phase in response to the satellite separating from a payload dispenser, and to autonomously control, while operating in the transfer phase, one or more aspects of at least one satellite component at least partly based on the data, and particularly the one or more launch-specific parameters specified by or derived from the data.
The present invention concerns a method (50) for attitude control of a satellite (10) in low inclined orbit in survival mode, the satellite (10) comprising at least one solar generator (12), at least one solar sensor (17a, 17b), magneto-couplers (15) designed to form internal magnetic moments in a satellite reference frame having three orthogonal axes X, Y and Z, and inertial actuators (16) designed to form internal kinetic moments in the satellite reference frame. The at least one solar sensor has a field of view at least 180° wide in the XZ plane around the Z axis, the method comprising: - a step (51) of attitude control using a first control law, - a step (52) of searching for the sun by means of the at least one solar sensor (17a, 17b), - when a first phase of visibility of the sun is detected: a step (53) of attitude control using a second control law.
The present invention concerns a method (50) for attitude control of a satellite (10) in low inclined orbit in survival mode, the satellite (10) comprising at least one solar generator (12), at least one solar sensor (17a, 17b), magneto-couplers (15) designed to form internal magnetic moments in a satellite reference frame having three orthogonal axes X, Y and Z, and inertial actuators (16) designed to form internal kinetic moments in the satellite reference frame. The at least one solar sensor has a field of view at least 180° wide in the XZ plane around the Z axis, the method comprising: - a step (51) of attitude control using a first control law, - a step (52) of searching for the sun by means of the at least one solar sensor (17a, 17b), - when a first phase of visibility of the sun is detected: a step (53) of attitude control using a second control law.
An active waveguide transition includes a waveguide defining a waveguide volume and including a back short wall at a first end. A first probe is mounted on the waveguide in an operable position extending into the waveguide volume, and a first RF electrical signal connector is mounted on the active waveguide transition. A first circuit assembly is mechanically coupled to an exterior surface of the waveguide, the circuit assembly including a first multi-layer ceramic substrate with an RF amplifier system mounted thereon. The RF amplifier system is electrically coupled to the multi-layer ceramic substrate, the first probe, and the first RF electrical signal connector to define an active first signal path for RF communication signals between the probe and first RF signal connector.
An active waveguide transition includes a waveguide defining a waveguide volume and including a back short wall at a first end. A first probe is mounted on the waveguide in an operable position extending into the waveguide volume, and a first RF electrical signal connector is mounted on the active waveguide transition. A first circuit assembly is mechanically coupled to an exterior surface of the waveguide, the circuit assembly including a first multi-layer ceramic substrate with an RF amplifier system mounted thereon. The RF amplifier system is electrically coupled to the multi-layer ceramic substrate, the first probe, and the first RF electrical signal connector to define an active first signal path for RF communication signals between the probe and first RF signal connector.
An artificial satellite comprises a satellite structure, an onboard control system including an onboard controller, and a memory system. The memory system is physically coupled to the satellite structure and independently powerable with respect to the onboard controller. The memory system is also arranged to communicatively couple with the onboard controller, and to store data which specifies one or more launch-specific parameters for configuring at least one of the satellite components. The onboard control system is adapted to operate in a transfer phase in response to the satellite separating from a payload dispenser, and to autonomously control, while operating in the transfer phase, one or more aspects of at least one satellite component at least partly based on the data, and particularly the one or more launch-specific parameters specified by or derived from the data.
An artificial satellite comprises a satellite structure, an onboard control system including an onboard controller, and a memory system. The memory system is physically coupled to the satellite structure and independently powerable with respect to the onboard controller. The memory system is also arranged to communicatively couple with the onboard controller, and to store data which specifies one or more launch-specific parameters for configuring at least one of the satellite components. The onboard control system is adapted to operate in a transfer phase in response to the satellite separating from a payload dispenser, and to autonomously control, while operating in the transfer phase, one or more aspects of at least one satellite component at least partly based on the data, and particularly the one or more launch-specific parameters specified by or derived from the data.
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