Abstract: The present invention relates to a device making it possible to study the solar corona on a space mission requiring the formation flight of two satellites: an occulting satellite (OCC), the role of which is to create an artificial eclipse of the sun from the point of view of a coronagraph (10) onboard a second satellite, called carrying satellite (COR). The invention presents the advantage of proposing a formation flight device intended for a solar coronagraphy mission comprising fixed solar panels (11a), requiring no deployment, thanks to a dissymmetrical accommodation of the coronagraph (10) reflected in a shifting of said coronagraph (10) to a side of the carrying satellite (COR).

Abstract: The present invention relates to an absolute target system intended to be incorporated in observation satellites. To establish an absolute target system provided with maximum accuracy, the present invention proposes coupling a star sensor (4) to an optical metrological system (5N, 5R). Since these two items of equipment are normally already on board the satellites, in particular for formation flight missions, this solution adds no extra weight or cost.

Abstract: A satellite intended to travel in a constellation of satellites in an area of space in which the dominant disturbing forces and torques are for the most part caused by differential solar pressure between the satellites of the constellation comprises a satellite structure and a sunshield to prevent at least a portion of the satellite structure from being illuminated by solar rays. The reflectivity of the reflective surfaces of the sunshield is adjusted as a function of the angle of incidence of the solar rays.

Abstract: The invention relates to a satellite metrology system for satellite formation flight comprising at least one reference satellite (SR) and one secondary satellite (SS). In the reference satellite, an optical source (SO) emits a light beam intended to illuminate the secondary satellite (SS) and a set of light detectors (CCD) detects the light reflected by the secondary satellite. A measuring circuit (CI) is used for detecting the detector or detectors that receive the light from the secondary satellite. In the secondary satellite (SS) at least one reflector (RR1) receives the illumination light from the reference satellite and reflects it towards the set of detectors (CCD) of the reference satellite.

Abstract: The present invention relates to an absolute target system intended to be incorporated in observation satellites. To establish an absolute target system provided with maximum accuracy, the present invention proposes coupling a star sensor (4) to an optical metrological system (5N, 5R). Since these two items of equipment are normally already on board the satellites, in particular for formation flight missions, this solution adds no extra weight or cost.

Abstract: The present invention relates to a device making it possible to study the solar corona on a space mission requiring the formation flight of two satellites: an occulting satellite (OCC), the role of which is to create an artificial eclipse of the sun from the point of view of a coronagraph (10) onboard a second satellite, called carrying satellite (COR). The invention presents the advantage of proposing a formation flight device intended for a solar coronagraphy mission comprising fixed solar panels (11a), requiring no deployment, thanks to a dissymmetrical accommodation of the coronagraph (10) reflected in a shifting of said coronagraph (10) to a side of the carrying satellite (COR).

Abstract: A satellite comprises a main body and, in orbit, at least one free object floating in space including a portion of the payload transferred from the main body. The free object is restricted to a precise position and attitude relative to the main body. An electromagnetic force and an electromagnetic torque are produced for controlling the position and the attitude of the free object in accordance with a master-slave relationship.

Abstract: The invention relates to a satellite metrology system for satellite formation flight comprising at least one reference satellite (SR) and one secondary satellite (SS). In the reference satellite, an optical source (SO) emits a light beam intended to illuminate the secondary satellite (SS) and a set of light detectors (CCD) detects the light reflected by the secondary satellite. A measuring circuit (CI) is used for detecting the detector or detectors that receive the light from the secondary satellite. In the secondary satellite (SS) at least one reflector (RR1) receives the illumination light from the reference satellite and reflects it towards the set of detectors (CCD) of the reference satellite.

Abstract: A satellite intended to travel in a constellation of satellites in an area of space in which the dominant disturbing forces and torques are for the most part caused by differential solar pressure between the satellites of the constellation comprises a satellite structure and a sunshield to prevent at least a portion of the satellite structure from being illuminated by solar rays. The reflectivity of the reflective surfaces of the sunshield is adjusted as a function of the angle of incidence of the solar rays.

Abstract: A satellite comprises a main body and, in orbit, at least one free object floating in space including a portion of the payload transferred from the main body. The free object is restricted to a precise position and attitude relative to the main body.

Abstract: An electronic device offering protection against connection of a direct current power supply unit with reverse polarity includes a branch disposed between two potential lines and including a reverse biased diode and a first component sensitive to a flow of current. A first switch is disposed on the downstream side of this branch, on one of the potential lines. A control circuit has two terminals receiving a control signal and, connected in series between those terminals, a second switch and a second component sensitive to a flow of current. The first switch, normally open, is closed by the second sensitive element if the latter detects a flow of current. The second switch, normally closed, is opened by the first sensitive component if the latter detects a flow of current.

Abstract: In the event of failure of a processor module (PMI) which is part of a data processing system the processor module (III.1) is turned off and then on; preferably, complete reconfiguration (III.2) of the module is commanded only if at least one other fault, the number of which can be chosen at will, is detected in a given time (T.sub.max) from the first fault replacing it with another available cold redundant processor module.