Abstract: A transmitter device of a bi-static or multi-static radar system is disclosed and implemented for aerial surveillance. The transmitter device is intended to be on board a satellite orbiting the Earth. Once in orbit, the transmitter device is configured to obtain information relating to a region of interest monitored by at least one receiver device of the radar system, and to transmit a signal in a radio beam illuminating at least one portion of the region of interest.

Abstract: A transmitter device of a bi-static or multi-static radar system is disclosed and implemented for aerial surveillance. The transmitter device is intended to be on board a satellite orbiting the Earth. Once in orbit, the transmitter device is configured to obtain information relating to a region of interest monitored by at least one receiver device of the radar system, and to transmit a signal in a radio beam illuminating at least one portion of the region of interest.

Abstract: Disclosed is a satellite including a cylindrical main body, the main body having an inner wall defining an inner space and an outer wall, and extending along a main axis between a lower end surface and an upper end surface, at least one of the lower end surface and the upper end surface including an interface mechanism intended for engaging with a complementary interface mechanism of another satellite or of a launcher, the satellite also including at least one external device attached to the outer wall of the main body, the outer device extending to project transversely from the outer wall relative to the main axis.

Abstract: Disclosed is a satellite including a cylindrical main body, the main body having an inner wall defining an inner space and an outer wall, and extending along a main axis between a lower end surface and an upper end surface, at least one of the lower end surface and the upper end surface including an interface mechanism intended for engaging with a complementary interface mechanism of another satellite or of a launcher, the satellite also including at least one external device attached to the outer wall of the main body, the outer device extending to project transversely from the outer wall relative to the main axis.

Abstract: The invention provides a deployable radiator for a space vehicle such as a satellite. The radiator of the invention has two radiating faces, one of which is insulating over a portion of its area so that during launch and while the satellite is being moved onto station, with the radiator in the stored position, it naturally serves to keep the highest possible temperature on board the vehicle.

Abstract: The invention provides a deployable radiator for a space vehicle such as a satellite. The radiator of the invention has two radiating faces, one of which is insulating over a portion of its area so that during launch and while the satellite is being moved onto station, with the radiator in the stored position, it naturally serves to keep the highest possible temperature on board the vehicle.

Abstract: A satellite stabilized about a roll axis, a yaw axis and a pitch axis, for travel on an orbit with geocentric pointing towards a heavenly body, embodying a body and a solar generator adapted to collect solar radiation, characterized in that the generator includes a single wing supported in a medium portion by an arm extending at least approximately along the yaw axis away from the heavenly body, the arm being connected to the body by a single rotation mechanism with a single rotation axis substantially parallel to the yaw axis, the wing having a constant inclination .alpha. to the yaw axis.

Abstract: In order to connect two adjacent elements (E1,E2) joined, for example, onto a satellite solar panel, an antifriction joint (10) is used. The deployment kinematics of the joint enable deployment to be done extremely accurately. The joint comprises two braces (12,14) suitable for rolling one onto the other by two cylindrical surfaces (12a,14a). Guiding of rolling is ensured by two flexible members, such as rolling plates (16,28) extremities are secured to the braces and which pass by crossing between the cylindrical surfaces (12a,14a). A traction prestressing stored in the plates avoids any stray movement between the braces, especially at the time of deployment. The drive torque ensuring the automatic deployment of the joint and its end-of-travel locking are ensured by elastic bands (36) connecting the two braces and each formed of two superimposed plates. Successive joints may be joined using a synchronization deployment mechanism.