Abstract: A method for controlling an attitude control system (30) for a space vehicle (10), the attitude of the space vehicle being controlled during at least one preparation phase followed by an observation phase during which an image capture is performed. In an attitude control system that includes a maneuvering subsystem (300) which includes at least one reaction wheel, the method includes, during the at least one preparation phase, a preparation step (50), during which commands are issued to the maneuvering subsystem in order to control the attitude of the space vehicle, followed by a step (55) of stopping the at least one reaction wheel prior to the observation phase. In addition, during the observation phase, a fine control subsystem (310) having a lower vibration signature than that of the maneuvering subsystem, is sent commands in order to control the space vehicle's attitude. An attitude control system for a space vehicle is also described.

Abstract: A method and system for estimating a path-length difference between two paths followed by a target signal transmitted by a spacecraft or aircraft to a first receiving antenna and a second receiving antenna of a receiving base, respectively. A useful-phase difference is measured between signals that correspond to the target signal received by the first receiving antenna and second receiving antenna. The path-length difference is estimated in accordance with the useful-phase difference measurements. The measurement of the useful-phase difference comprises either correlating the signals received by the first receiving antenna and second receiving antenna, respectively, with a reference target signal, or analyzing the signals received by the first receiving antenna and second receiving antenna, respectively, using an FFT or a PLL.

Abstract: A satellite support structure to support at least one device of the satellite. The support structure includes structural elements with at least one of the structural elements being a damping connector linking at least two other structural elements of the support structure. The damping connector includes an elastomer element and at least one flat angle bracket having at least two wings to be linked by the respective connectors to the damped structural elements. The elastomer element is made from elastomer material with loss angle ? greater than ten degrees and is arranged such that the transmission of forces between one of the wings of the flat angle bracket and the connectors is achieved entirely via the elastomer element.

Abstract: An image capture instrument implements an addition of accumulation signals for photodetectors which are adjacent within a row of photodetectors. Segments are defined in the row with one and the same common length of segment, while being progressively offset by an offset length which is constant. The accumulation signals are added together for photodetectors which belong to one and the same segment. The offset length is less than the segment length, and greater than half said segment length. Artifacts in the image captured, which are due to spectrum aliasing, are thus decreased. The signal-to-noise ratio of the image is increased.

Abstract: A segmented structure includes at least two panels, one panel referred to as a main panel and at least one panel referred to as a secondary panel. The structure further includes at least one unfurling device configured to bring a secondary panel into a storage position or into an unfurled position. The unfurling device has at least one strip fixed to the secondary panel and connected to the main panel. The strip is elastically preloaded into the storage position thereof so as to unfurl automatically and autonomously when relative movement between the secondary panel and the main panel becomes possible, so as to move the secondary panel.

Abstract: A segmented structure includes a principal panel and a secondary panel, as well as at least one deployment device configured to move the secondary panel into a storage position or into a deployed position. The deployment device includes a translation system having a movable trolley, guided in translation and provided with a connection arm which is connected to the rear face of the secondary panel. The translation system is configured to generate a translation movement of said secondary panel with respect to the principal panel. The deployment device further includes a rotation system is configured to generate at least one rotation of the connection arm to generate a rotational movement of said secondary panel with respect to the principal panel.

Abstract: A device for expelling/containing a predetermined liquid. The device configured to be built into a liquid tank operable at low or zero gravity and comprising a unitary three-dimensional sponge structure. The sponge structure comprises a set of substantially wire-like elements that extend between a peripheral area of the sponge structure and an area for expelling/containing liquid. The wire-like elements are substantially oriented in the direction of flow of the fluid within the device. The wire-like elements are connected together by crosspieces and are arranged such that the capillary gradient is positive or zero in the direction of flow of the fluid from the peripheral area to the area for expelling/containing liquid.

Abstract: A method for managing the service policy applied to a black network comprising a radio link and to a red network connected to this black network managed by a predetermined set of profiles is proposed. The congestion of the radio link is detected by any means by the black domain. The congestion of the radio link is detected by a method for detecting congestion which operates by means of exchanges within the red domain. A service policy profile then established matches for each domain to a detected congestion level.

Abstract: An aircraft is capable of passing from the aerial domain to the spatial domain and method for automatically adapting the configuration of same. An additional breathable gas supply is provided to be activated only during a flight phase during which aerobic propulsion is interrupted, and is capable of supplying the control system of the manned cabin environment instead of the system associated with the aerobic propulsion means.

Abstract: A system and method for detecting and locating an insulation flaw in a solar generator on a spacecraft. The solar generator comprises a plurality of flaps. Each flap bears at least one solar cell that is connected to an electrical distribution network and electrically insulated from the flap. Each flap is connected, by a first load and by a second load, to a first electrical line and a second electrical line, respectively. The ratio of the impedances of the first load and of the second load of a flap being denoted as an impedance ratio of the flap. The solar generator comprises at least two flaps exhibiting different respective impedance ratios. The system comprises a component for evaluating the currents flowing in the first and second electrical lines, and a detector for detecting and locating an insulation flaw in the solar generator based on the evaluations of the currents.

Abstract: A method and a toolset for manufacturing a metal liner for a composite vessel includes a mandrel configured in several mandrel elements forming support elements of primary parts constituting the metal liner.

Abstract: A telecommunications satellite stabilized on three axes includes a set of dissipative equipment constituting a payload of the satellite. The satellite includes support data transmission antennas and is substantially parallelepipedal in shape with the panels forming two opposite faces, east and west faces. The panels form two additional opposite faces, north and south faces, and include radiator surfaces on their external faces. The radiator surfaces are configured to cool the electronic equipment of the satellite. The equipment installed on the north and south panels dissipate thermal power corresponding to less than 25% of the total dissipated power.

Abstract: A segmented structure includes at least two panels, a so-called main panel and a so-called secondary panel, as well as at least one deployment device configured to move the connected secondary panel into a storage position or into a deployed position. The deployment device includes a translation system provided with at least one helical geared motor configured to translate the secondary panel relative to the main panel. The translation system further includes a rotation system configured to rotate the translation system and the secondary panel connected to the translation system, relative to said main panel.

Abstract: A segmented structure includes at least two panels, wherein a first panel is referred to as main panel, and a second panel is referred to as secondary panel. The structure also includes at least one deployment device having a connecting arm secured to the rear face of the secondary panel and connected to the rear face of the main panel. The deployment device includes a movement system with a rotation unit that generates a rotation of the connecting arm about a reference axis, and a translation unit that generates a movement of the connecting arm in translation along this reference axis, so as bring the secondary panel into a stowed position or into a deployed position.

Abstract: A segmented structure comprising at least two panels, one panel referred to as a main panel and at least one panel referred to as a secondary panel, together with at least one unfurling device able to bring a secondary panel into a storage position or into an unfurled position, the unfurling device comprising at least one strip fixed to the secondary panel and connected to the main panel, the strip being elastically preloaded into the storage position thereof so as to unfurl automatically and autonomously when relative movement between the secondary panel and the main panel becomes possible, so as to move the secondary panel.

Abstract: A telecommunications system for intermittent data transfer from and to at least one user located substantially on the surface of a celestial body. The system comprises at least one surface transmitter/receiver terminal associated with each user, one or more signal repeater means for the signals transmitted and/or received from the surface terminals. Each moving repeater means has at least one antenna oriented toward the surface of the celestial body, and adapted to allow communications from and to surface terminals. Each antenna produces a transmission/reception beam, the track of which on the surface of the celestial body forms the ground track, the progressive sweeping of the surface by this ground track forming a strip called a swath.

Abstract: A method and telecommunications system for identifying uplink multiplexing resources of a multi-beam satellite that are usable in a land-based telecommunications system, e.g., a transmitting station for transmitting radio signals to a receiving station. The transmitting station or the receiving station being a base station having a range defining a coverage area. For a given uplink multiplexing resource, a maximum allowable interference level, with respect to the satellite, for radio-electric signals transmitted from the coverage area is estimated. A potential interference level of the transmitting station is estimated. The transmitting station determines the usability of the given uplink multiplexing resource by comparing the potential interference level with the maximum allowed interference level for the given uplink multiplexing resource.

Abstract: The invention relates to a satellite having a structure that includes a circular launching interface ring and at least two main planar apparatus-holding walls that are substantially parallel to the axis of the ring and rigidly connected to one another and to the ring. Each wall directly bears on the ring by a base of the wall, and each wall is rigidly and directly attached to the ring by at least one somewhat point-by-point connection on at least one point or area of tangency or intersection with the base of the wall and the ring.

Abstract: The invention relates to a propulsion unit for a reusable launch vehicle including a rocket engine supported by a cradle. According to the invention, the cradle includes at least three attachment elements for assembling the unit on the structure of the vehicle to which the unit is to be connected, the at least three attachment elements defining a plane for removing the unit, and in which the unit includes one or more fluid and/or electric links of the engine, each one of the links including a free end to be assembled with a corresponding circuit for supplying the vehicle, to which the unit is to be connected, the tip of at least some of the free ends being contained in the removal plane.

Abstract: According to the present invention, use is made of a probe provided with a central sensor, with off-centred sensors and lateral sensors, and said probe is articulated on the aircraft around two orthogonal axes.