Abstract: The satellite solar generator structure comprises a plurality of solar panels (PR, PS) each having a plane surface, the panels being disposed in superposition in said structure (ST), the structure including at least one rod (TI) holding said panels (PR, PS) pressed against one another, two successive panels being in contact via bearing points (AL) disposed at the peripheries of the panels. In this structure, spacers (CA) are distributed over the surfaces of the panels (PR, PS) and are disposed between pairs of successive panels in order to improve contact between two successive panels so that the structure presents better mechanical strength during the satellite launch stage. With this arrangement, a fraction of the forces is taken up by the spacers instead of being taken up by the panels, thus making it possible to optimize the solar generator, for example by reducing the weight of the panels constituting it.

Abstract: The satellite solar generator structure comprises a plurality of solar panels (PR, PS) each having a plane surface, said panels being disposed in superposition in said structure (ST), said structure including at least one rod (TI) holding said panels (PR, PS) pressed against one another, two successive panels being in contact via bearing points (AL) disposed at the peripheries of said panels. In this structure, spacers (CA) are distributed over the surfaces of the panels (PR, PS) and are disposed between pairs of successive panels in order to improve contact between two successive panels so that the structure presents better mechanical strength during the satellite launch stage. With this arrangement, a fraction of the forces is taken up by the spacers instead of being taken up by the panels, thus making it possible to optimize the solar generator, for example by reducing the weight of the panels constituting it.

Abstract: A system including a retaining member passing through an element and connected at one end to a structure and bearing at the other end on an external side of the element; a separating mechanism for separating the member from the structure to move the element from a folded position to a deployed position; and a drive mechanism for pulling the corresponding part of the retaining member outwards after actuation of the separator mechanism. The system has a device which includes a barrel receiving the retaining member concentrically, cut-outs in the wall of the barrel forming spring tongues adapted to be bent wholly or partially towards the inside of the barrel in order to come into contact with the part, an enlargement of which is adapted to cooperate with the tongues to hold the member after actuation of the drive mechanism.

Abstract: At least three stacked panels are articulated by means of adjacent members so that they can pivot toward a deployed configuration. A mechanism includes an immobilizer mounted on a first member, cooperating with a second member to lock the two panels in the deployed configuration and constrained to rotate with a lug which can rotate on the first member and is abutted against a surface of a member constrained to rotate with the second member and configured so that, when the deployed configuration is reached, the lug escapes from it and brings the immobilizer into contact with the second member to bring about locking. A first finger of the mechanism, which is constrained to rotate with the lug, cooperates with a second finger of the third panel to hold it stacked until the two panels reach the deployed configuration, at which time rotation of the lug releases the second finger.

Abstract: To control a relative rotation between two elements (10, 12), such as flaps of a deployable mechanical structure, on a space vehicle, a torsion bar (16) is used made of a bistable shape memory alloy, heated over its whole length by heaters stuck on the bar and retained by hooping rings. A stop (22) restricts pivoting to the pre-set pivoting angle to be controlled. Excess pivoting of the torsion bar (16) is applied to a mechanical fuse (18), interposed between the bar and one (12) of the elements.

Abstract: A unit for controlling the retraction of a mobile structure such as a mirror used for calibrating an optical system on board a spacecraft, which includes a spring which permanently forces the mobile structure towards its retracted position and a memory material member, wherein a change of state of the memory material disconnects a connecting system placed in a transmission mechanism normally connecting a control motor to the mobile structure. The connecting system normally ensures the joining by friction of two parts of the transmission mechanism between which the spring acts. A heating system controls the change of state of the memory material member.

Abstract: A system for maintaining in a folded position a set of elements that are hinged to one another and to a structure (e.g. solar panels on a spacecraft), which elements are capable of occupying either said folded position in which said elements form a stack, or else a deployed position in which said elements are in end-to-end alignment, said system comprising:a retaining member passing through said elements in the folded positive and connected by a first one of its ends to said structure and bearing via a second one of its ends against the outermost element of said set;locking means for locking said retaining member in the folded position of said elements; andcontrol means for unlocking said locking means and releasing said retaining member, thereby enabling said set of elements to pass from the folded position to the deployed position.

Abstract: So as to dampen the shock occuring at the end of deploying a deployable lengthening piece of a space instrument, such as a solar generator, without resorting to using a complex speed regulation or synchronization mechanism for deployment, the present invention offers a torque limiter device (28a) to be placed between each joint (12) and at least one of the adjacent elements (10a) of the lengthening piece. This device includes an elastic system, such as a stack of Belleville washers (48a) which presses the plate (24a) of the joint against the edge of the element (10a) with a predetermined and preferably adjustable force. At the end of deployment, this elastic system absorbs the energy of the shock by deforming, then it brings the two pieces (24a, 10a) back into contact with each other thus giving the lengthening piece with the desired rigidity. An accurate relative positioning is then ensured by a flexible plate (34a) whose lateral edges are secured to each of the pieces.

Abstract: A device for temporary edge to edge securement in space of two parts along a contacting surface comprising:a plurality of retaining members distributed in pairs on either side of such contacting surface on each of said respective parts and a plurality of temporary connection members adapted to maintain them coupled to one another, with the rataining members in each pair being provided with complementary raised members for retainment thereof one relative to the other according to a longitudinal direction parallel to said contacting surface in at least one direction, said retaining members in each pair forming conjointly a bulging tenon oriented longitudinally engaging a narrowing groove formed in a rider constituting a temporary connection member for such pair of retaining members, andan automatic release mechanism comprising a coordination element connected to the plurality of temporary connection members and adapted to disengage the latter relative to said plurality of retaining members under the action of a