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: 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 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.