Abstract: A system of blinds comprising louvers that are inclined in such a way as to maximize the direct solar illumination received during the winter months and to minimize same during the summer months is described. The inclinations are determined according to the terrestrial latitude of the building supporting these blinds, and the orientation of the surface of the building that is to be protected. The longitudinal slope of the louvers is determined such that the longitudinal direction of the louvers is substantially parallel to the straight line of intersection of the plane of the surface and the equatorial plane seen from the building. The transverse tilt of the louvers is determined such that these louvers face in a direction comprised between 12° and 24° below the direction of the equatorial plane.

Abstract: The invention relates to a blade of a brise-soleil device, said blade being noteworthy in that it is produced in one piece comprising: substantially planar elongate, separate and parallel solid lamellae, discontinuous cutouts separating the solid lamellae, connecting spacers providing connection and spacing between solid lamellae, said cutouts being enclosed by the edges of the lamellae and the edges of the connecting spacers. The invention also relates to a method and a device for manufacturing such a blade.

Abstract: A method for controlling the temperature of an electric propulsion system. The electric propulsion system includes a discharge channel, an anode, a cathode, an injection system and a magnetic circuit. The injection system injects propellant gas into the discharge channel and the magnetic circuit has at least one magnetic winding to generate a magnetic field in the discharge channel. The temperature at a reference thermal point of the electric propulsion system is determined. The electric propulsion system is heated by the Joule effect by applying a current to the magnetic circuit when the determined temperature is below a minimum temperature predetermined during a stop phase of the electric propulsion system.

Abstract: A method for controlling the temperature of an electric propulsion system. The electric propulsion system includes a discharge channel, an anode, a cathode, an injection system and a magnetic circuit. The injection system injects propellant gas into the discharge channel and the magnetic circuit has at least one magnetic winding to generate a magnetic field in the discharge channel. The temperature at a reference thermal point of the electric propulsion system is determined. The electric propulsion system is heated by the Joule effect by applying a current to the magnetic circuit when the determined temperature is below a minimum temperature predetermined during a stop phase of the electric propulsion system.

Abstract: This invention consists of a system of blinds made up of louvers that are inclined in such a way as to maximize the direct solar illumination received during the winter months and to minimize same during the summer months. The inclinations are defined according to the terrestrial latitude of the building supporting these blinds, and the orientation of the surface of the building that is to be protected, generally glazing. The longitudinal slope of the louvers is defined such that the longitudinal direction of the louvers is substantially parallel to the straight line of intersection of the plane of the said surface and the equatorial plane seen from said building. The transverse tilt of the louvers is defined such that these louvers face in a direction comprised between 12° and 24° below the direction of the equatorial plane.

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 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 method of using an image sensor onboard a satellite or an aircraft comprises two simultaneous sequences of image capture. The first sequence corresponds to a capture of observation images, and the second sequence corresponds to a capture of images dedicated to the detection of a shifting of the observation images. The images dedicated to the detection of the shifting are restricted to windows that are at least in part contained in a main window the of observation images. Furthermore, said images dedicated to the detection of shifting are captured at a frequency greater than a frequency of the observation images.

Abstract: A method for controlling the attitude of a satellite in orbit around a celestial object, the satellite including an observation instrument, a solar panel, a radiator and a star sensor which are arranged on the satellite such that, in a reference frame associated with the satellite and defined by three orthogonal axes X, Y, and Z, the observation instrument has its observation axis parallel to the Z-axis, the solar panel is parallel to the Y-axis, the radiator is arranged on one of the sides ?X, +Y, or ?Y of the satellite, and the star sensor points to the negative X values side. The roll and pitch attitudes of the satellite are controlled during an activity period to direct the observation instrument towards areas of the celestial object to be observed, and the yaw attitude of the satellite is controlled to keep the sun on the positive X values side and ensure that a solar panel minimum insolation constraint is satisfied during observation phases of the activity period.

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 method of determining angles of sight between a receiver device having at least two reception antennas and at least one transmitter device having at least one transmission antenna for the transmission of radioelectric signals including at least two wavelengths. The determining method is based on angular phase measurements of the radioelectric signals, which are measured modulo 2? and are therefore ambiguous since they are known to within an integer number of times 2?. The ambiguity in the phase measurements is resolved in the case of an application of the determining method to a receiver device dimensioned by applying a method of design of a system for determining angles of sight. A receiver device implements the determining method, and a system for determining angles of sight includes the receiver device and at least one transmitter device.

Abstract: A method for controlling the attitude of a satellite in orbit around a celestial object, the satellite including an observation instrument, a solar panel, a radiator and a star sensor which are arranged on the satellite such that, in a reference frame associated with the satellite and defined by three orthogonal axes X, Y, and Z, the observation instrument has its observation axis parallel to the Z-axis, the solar panel is parallel to the Y-axis, the radiator is arranged on one of the sides ?X, +Y, or ?Y of the satellite, and the star sensor points to the negative X values side. The roll and pitch attitudes of the satellite are controlled during an activity period to direct the observation instrument towards areas of the celestial object to be observed, and the yaw attitude of the satellite is controlled to keep the sun on the positive X values side and ensure that a solar panel minimum insolation constraint is satisfied during observation phases of the activity period.

Abstract: A method of determining angles of sight between a receiver device having at least two reception antennas and at least one transmitter device having at least one transmission antenna for the transmission of radioelectric signals including at least two wavelengths. The determining method is based on angular phase measurements of the radioelectric signals, which are measured modulo 2? and are therefore ambiguous since they are known to within an integer number of times 2?. The ambiguity in the phase measurements is resolved in the case of an application of the determining method to a receiver device dimensioned by applying a method of design of a system for determining angles of sight. A receiver device implements the determining method and a system for determining angles of sight includes the receiver device and at least one transmitter device.