Abstract: A solar generator deployment device includes at least one primary tape-spring supporting a flexible membrane with a set of flexible photovoltaic cells on one face, at least one secondary tape-spring, and a reinforcing structure attached to the primary tape-spring and secondary tape-spring, said device having a wound state in which the primary tape-spring supporting the flexible membrane and secondary tape-spring and reinforcing structure are co-wound around a mandrel; and an unwound state in which said primary tape-spring and secondary tape-spring are unwound. The device comprises, at the level of said mandrel, means for offsetting, in the unwound state, the root of said secondary tape-spring so that the reinforcing structure is deployed within a volume situated on the side opposite the face of the flexible membrane comprising flexible photovoltaic cells and supports said flexible membrane, the device then being in the deployed state.

Abstract: A process for manufacturing a sintered ceramic composite, based on silicon nitride and ?-eucryptite, includes a step of producing a first powder blend, consisting of a powder of silicon nitride in crystalline form and a powder of a first lithium aluminosilicate in crystalline form, the composition of which is the following: (Li2O)x(Al2O3)y(SiO2)z, the lithium aluminosilicate composition being such that the set of molar fractions (x,y,z) is different from the set (1,1,2).

Abstract: A solar generator deployment device includes an assembly comprising a plurality of tape-springs supporting a windable membrane on a face of which is arranged a plurality of elements capable of converting the solar energy into electrical energy. The tape-springs and membrane are co-wound around a unique radius of curvature equal to the natural radius of curvature of folding of the tape-spring in the wound state. The tape-springs are substantially parallel and interlinked by transversal braces ensuring the rigidity of the bearing structure.

Abstract: A solar generator deployment device includes at least one primary tape-spring supporting a flexible membrane with a set of flexible photovoltaic cells on one face, at least one secondary tape-spring, and a reinforcing structure attached to the primary tape-spring and secondary tape-spring, said device having a wound state in which the primary tape-spring supporting the flexible membrane and secondary tape-spring and reinforcing structure are co-wound around a mandrel; and an unwound state in which said primary tape-spring and secondary tape-spring are unwound. The device comprises, at the level of said mandrel, means for offsetting, in the unwound state, the root of said secondary tape-spring so that the reinforcing structure is deployed within a volume situated on the side opposite the face of the flexible membrane comprising flexible photovoltaic cells and supports said flexible membrane, the device then being in the deployed state.

Abstract: A device supporting a first and a second element of a piece of space equipment. The device includes at least two deployable flexible arms each having a first end and a second end, the ends are secured respectively to the first and second elements and each designed to adopt at least one initial position folded in curves and an unfolded final position, in which positions they hold the first element away from the second element by first and second chosen distances respectively, the second distance being greater than the first.

Abstract: A process for manufacturing a sintered ceramic composite, based on silicon nitride and ?-eucryptite, includes a step of producing a first powder blend, consisting of a powder of silicon nitride in crystalline form and a powder of a first lithium aluminosilicate in crystalline form, the composition of which is the following: (Li2O)x (Al2O3)y (SiO2)z, the lithium aluminosilicate composition being such that the set of molar fractions (x,y,z) is different from the set (1,1,2).

Abstract: A composite having a coefficient of thermal expansion less than 1.3×10?6 K?1 is a sintered ceramic based on an oxide and on ?-eucryptite crystals having a ?-eucryptite content of less than 55% by weight (69% by volume).

Abstract: An optical space observation system comprises a primary mirror, a secondary mirror, a supporting base containing the primary mirror, on which a mechanical structure bearing a support of the secondary mirror is positioned, and an optical measurement means, said mechanical structure comprising a plurality of mechanical arms. The system also has a system comprising a plurality of actuators positioned on the supporting base, said actuators being connected to the lower ends of said mechanical arms and the upper ends of said mechanical arms being connected to the support of the secondary mirror on the periphery of the support. A space telescope is intended to be loaded in a launcher and put into orbit. The invention is intended in particular for a telescope having a deployable secondary mirror and means for active control of the optics.

Abstract: A device for damping of vibrations for an item of equipment comprising a structure to which a first element and a second fragile element having to be protected from the vibrations are coupled. The device comprises first piezoelectric transducer means inserted between the structure and the first element and charged with converting energy of vibration of the structure into electric energy, at least one sensor coupled to the structure and arranged to deliver measurement signals representative of vibrations, control means electrically supplied by the electric energy generated and charged with deducing at least one amplitude of movement to compensate at least partially for the vibration, and to deliver control signals representative of each determined amplitude, and second piezoelectric transducer means inserted between the structure and the second element and charged with converting the control signals into movement to damp at least partially for the second element the vibrations.

Abstract: A device (D) is dedicated to fixing a first piece of equipment (E1) relative to a second piece of equipment (E2). The device has (i) a structure having a rigid central body (CC) prolonged by two approximately identical terminal bodies (CT1, CT2) each having a neck defining a flexible intermediate part (PD1, PD2) that is symmetric relative to a symmetry element, prolonged by a rigid internal part (PI1, PI2) that is symmetric relative to the symmetry element and joined to one of the ends of the central body (CC), and by a rigid external part (PE1, PE2) that is symmetric relative to a symmetry element, spaced from the internal part, and intended to be joined to the first (E1) or second (E2) piece of equipment. The device has (ii) at least two piezoelectric transducers (T11-T22) with each responsible for converting either an axial dimensional change into a measurement current representing the amplitude of the change, or a control current into a corresponding axial dimensional change.

Abstract: The invention relates to a measuring tape (10) comprising a stack of at least two layers, characterized in that it also includes a first layer, called support layer, based on composite material (11) and a layer, called top layer, (12) based on a polymer having a high glass transition temperature so that, in conditions of use, said polymer is in a glassy state to maintain the element in the wound or folded position. The invention also relates to a deployable structure including said measuring tape intended notably for space applications.

Abstract: The invention relates to a measuring tape (10) comprising a stack of at least two layers, characterized in that it also includes a first layer, called support layer, based on composite material (11) and a layer, called top layer, (12) based on a polymer having a high glass transition temperature so that, in conditions of use, said polymer is in a glassy state to maintain the element in the wound or folded position. The invention also relates to a deployable structure including said measuring tape intended notably for space applications.

Abstract: A device is dedicated to the damping of vibrations for an item of equipment (I) designed to be moved and comprising a structure (S1, S2) to which a first element (E1) and a second fragile element (E2) having to be protected from the vibrations are coupled.

Abstract: A device (D) is dedicated to fixing a first piece of equipment (E1) relative to a second piece of equipment (E2). The device has (i) a structure having a rigid central body (CC) prolonged by two approximately identical terminal bodies (CT1, CT2) each having a neck defining a flexible intermediate part (PD1, PD2) that is symmetric relative to a symmetry element, prolonged by a rigid internal part (PI1, PI2) that is symmetric relative to the symmetry element and joined to one of the ends of the central body (CC), and by a rigid external part (PE1, PE2) that is symmetric relative to a symmetry element, spaced from the internal part, and intended to be joined to the first (E1) or second (E2) piece of equipment. The device has (ii) at least two piezoelectric transducers (T11-T22) with each responsible for converting either an axial dimensional change into a measurement current representing the amplitude of the change, or a control current into a corresponding axial dimensional change.

Abstract: A device (D) is devoted to supporting a first (M1) and a second (M2) element of a piece of space equipment, such as a telescope for example. This device (D) comprises at least two deployable flexible arms (O11 to O32) each comprising a first end (EX1) and a second end (EX2) which ends are secured respectively to the first (M1) and second (M2) elements and each designed to adopt at least one initial position folded in curves and an unfolded final position, in which positions they hold the first element (M1) away from the second element (M2) by first and second chosen distances respectively, the second distance being greater than the first.