Abstract: A landing system of a body and a space probe provided with such a system for landing on a bearing ground. The landing system includes landing legs (5), each with a footpad (6) at the end thereof, intended for braking the landing impact of the body when coming into contact with the ground and for supporting the body on the ground after landing. The footpads (6) are not coplanar.

Abstract: The present disclosure relates to a system in space for reinforcing photosynthesis on earth, comprising a satellite with at least one first optical assembly intended for collecting sunlight, the position of which is stationary; a second optical assembly, smaller in size and with less inertia than the first optical element, intended for retransmitting the collected light with higher density of the retransmitted flux density than the collected flux density, and with an adjustable orientation; a remotely controllable means capable of adjusting the orientation of the second optical assembly; and a light-transmitting means which transmits the collected light from the first optical assembly to the second optical assembly. The second optical assembly retransmits light only in specified frequency hands around 450 nm and 660 nm.

Abstract: A system includes a mother probe forming a carrier space vehicle (1) and a plurality of daughter probes (2a, 2b, 2c) aligned in a longitudinal axis (A) of the mother probe, in which the attachment of the daughter probes to the mother probe is carried out by a plurality of probe-supporting annular segments (5a, 5b, 5c) each provided with an annular collar (3a, 3b, 3c) for attaching a daughter probe.

Abstract: A space probe including a descent module with a mobile exploration vehicle, wherein the descent module is a landing module inside which the mobile exploration vehicle is fastened, the landing module being provided with landing legs which can be deployed under the lower level of the mobile exploration vehicle.

Abstract: The invention relates to an electric thruster for a spacecraft. According to the invention, the thruster (II) comprises a jet generating portion (G1) and a jet accelerating portion (A2), pivotably connected (H1) such that the jet accelerating portion (A2) can rotate in relation to the jet generating portion (G1).

Abstract: Disclosed are a method and device for supplying a combustion chamber of a space propulsion engine with cryogenic liquid fuel and oxidizer propellants. The propellants are mixed at constant pressure to produce a propellant mixture, with the propellants being mixed at a location upstream of an orifice of a propellant injector. The propellant mixture is fed to an enclosure of the propellant injector, and from the propellant injector enclosure, the propellant mixture is injected into the combustion chamber. The flow rate of the propellant mixture from the propellant injector enclosure into the combustion chamber is varied by adjustment of the propellant injector, with the injection of the propellant mixture from the propellant injector enclosure into the combustion chamber being at constant pressure.

Abstract: The present disclosure relates to a monitoring system which comprises at least one monitoring satellite placed in orbit at a lower altitude than that of the satellites of the satellite constellation so as to be capable of receiving the positioning signals emitted towards the Earth by said satellites, and which comprises a processing unit intended for verifying the integrity of said received positioning signals, using position information that is separate from said signals for this purpose.

Abstract: According to the invention, the system comprises: at least three position beacons (3) arranged about said location (2) and emitting in the long-wave range, and an apparatus associated with the user (1) and including means for receiving, processing and displaying the information transmitted by said beacons (3).

Abstract: A system includes a mother probe forming a carrier space vehicle (1) and a plurality of daughter probes (2a, 2b, 2c) aligned in a longitudinal axis (A) of the mother probe, in which the attachment of the daughter probes to the mother probe is carried out by a plurality of probe-supporting annular segments (5a, 5b, 5c) each provided with an annular collar (3a, 3b, 3c) for attaching a daughter probe.

Abstract: A landing system of a body and a space probe provided with such a system for landing on a bearing ground. The landing system includes landing legs (5), each with a footpad (6) at the end thereof, intended for braking the landing impact of the body when coming into contact with the ground and for supporting the body on the ground after landing. The footpads (6) are not coplanar.

Abstract: A space probe including a descent module with a mobile exploration vehicle, wherein the descent module is a landing module inside which the mobile exploration vehicle is fastened, the landing module being provided with landing legs which can be deployed under the lower level of the mobile exploration vehicle.

Abstract: The present disclosure relates to a system in space for reinforcing photosynthesis on earth, comprising a satellite with at least one first optical assembly intended for collecting sunlight, the position of which is stationary; a second optical assembly, smaller in size and with less inertia than the first optical element, intended for retransmitting the collected light with higher density of the retransmitted flux density than the collected flux density, and with an adjustable orientation; a remotely controllable means capable of adjusting the orientation of the second optical assembly; and a light-transmitting means which transmits the collected light from the first optical assembly to the second optical assembly. The second optical assembly retransmits light only in specified frequency hands around 450 nm and 660 nm.

Abstract: The present disclosure relates to a monitoring system which comprises at least one monitoring satellite placed in orbit at a lower altitude than that of the satellites of the satellite constellation so as to be capable of receiving the positioning signals emitted towards the Earth by said satellites, and which comprises a processing unit intended for verifying the integrity of said received positioning signals, using position information that is separate from said signals for this purpose.

Abstract: A satellite terrestrial positioning system is disclosed in which navigation satellites verify, in an autonomous manner, essential information that is transmitted to users using unidirectional links received from reference beacons.

Abstract: The invention relates to an electric thruster for a spacecraft. According to the invention, the thruster (II) comprises a jet generating portion (G1) and a jet accelerating portion (A2), pivotably connected (H1) such that the jet accelerating portion (A2) can rotate in relation to the jet generating portion (G1).

Abstract: According to the invention, the system comprises: at least three position beacons (3) arranged about said location (2) and emitting in the long-wave range, and an apparatus associated with the user (1) and including means for receiving, processing and displaying the information transmitted by said beacons (3).

Abstract: According to the invention, upstream of the injection means, the combustible propellant and the oxidant propellant are mixed at constant pressure; and to inject the said mixture of propellants at constant pressure into the combustion chamber (1), injection means (7 to 11) are chosen, making it possible to vary the flow rate of the said injected mixture.

Abstract: According to the present invention, each navigation satellite (1) verifies in an autonomous manner the essential information that it transmits to the users, by virtue of unidirectional links received from reference beacons (11).