Abstract: In order to connect two adjacent elements (E1,E2) joined, for example, onto a satellite solar panel, an antifriction joint (10) is used. The deployment kinematics of the joint enable deployment to be done extremely accurately. The joint comprises two braces (12,14) suitable for rolling one onto the other by two cylindrical surfaces (12a,14a). Guiding of rolling is ensured by two flexible members, such as rolling plates (16,28) extremities are secured to the braces and which pass by crossing between the cylindrical surfaces (12a,14a). A traction prestressing stored in the plates avoids any stray movement between the braces, especially at the time of deployment. The drive torque ensuring the automatic deployment of the joint and its end-of-travel locking are ensured by elastic bands (36) connecting the two braces and each formed of two superimposed plates. Successive joints may be joined using a synchronization deployment mechanism.

Abstract: A system for securing deployable elements, such as solar panels, on a structure, such as a spacecraft, with the aid of a through rod. A mechanism is provided for releasing the through rod from the elements at the moment of deployment thereof, then for returning the rod into its initial position with respect to the outer element.

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

Abstract: A displayable appendix linked to the structure of a space vehicle movable about an articulation axis from a stored position along the structure of the space vehicle to a display position by a control mechanism with abutments on the appendix and on the structure of the space vehicle so distributed and located as to prevent warping or distortion of the articulation axis and the control mechanism by exerting upon the appendix bending prestresses which are reduced near the articulation axis to a pure prestress torque tending to cause the appendix to move to the display position and temporary forces obtained from use of the abutments to hold the displayable appendix in the stored position during launch of the space vehicle.

Abstract: A mechanical release device for releasing a member with respect to another. The device comprises a bonding element disposed on each of the members to be released, a flexible junction element placed on the bonding elements and a device permitting under the action of a mechanism the progressive raising of said flexible element and then the release of the members secured to one another. The invention preferably relates to the displaying of solar panels for a satellite in a space environment.

Abstract: The present invention relates to the arrangement of an artificial satellite provided with foldable solar generators and antennas. According to the invention, extensions are provided on the articulated flaps and the proximal panels, in order to be able optimally to adjust the distance of the solar generators with respect to the satellite, so that the articulation between the proximal panel and the flap is located above the folded antennas of which the ends are housed between said extensions. The invention results in elimination of the shadow cast by a satellite on its solar generators and the thermal influence of said satellite on the cells of said generators.

Abstract: Synchronized angular displacement of articulated elements of an outwardly-extendable solar-cell panel is carried out by means of a device mounted between any two successive panel elements constituting a driving element and a driven element. Two independent and parallel traction members are pivotally mounted on support plates which are rigidly fixed to two successive driving elements. Two link-arms for traction members such as cables are pivotally attached to pins forming anchoring points for the cables. Each support plate has two stationary stops for limiting the angular displacements of the link-arms during the relative pivotal movement of the driven element with respect to the driving element.