Abstract: The through-pivot comprises a first ring and a second ring, one of the two rings being able to rotate about a longitudinal axis with respect to the other ring. The pivot further comprises at least one floating frame. The two rings are connected to the floating frame by at least one first set and, respectively, by at least one second set, of several flexible elements running in a direction that is transverse to the two rings. The floating frame may be made up of a ring in the form of a cylinder of revolution about the axis, or of ring portion, it being possible for the floating frame to be positioned either on the inside or on the outside of the rings indifferently. Application to the field of spacecraft such as satellites for the fine rotational guidance of at least one element or piece of equipment, in a predetermined direction of pointing.

Abstract: The present invention relates to a reusable device for securely holding at least one fragile object against a functional surface solidly fixed to the structure of a satellite or spacecraft during at least one operational phase relating to this satellite, making the objects thus held more accessible and intervention on these objects easier, while at the same time preventing damage to these objects under the effect of sudden accelerations, both during this (these) operational phase(s) and while the hold is being established or while the hold is being released. The device according to the invention is characterized in that it comprises a rigid structure which partially grips this (these) object(s) and which supports at least one fixed jaw and at least one moving jaw substantially facing the fixed jaw(s), the object being immobilized between the fixed jaw and the moving jaw throughout the period of firm holding.

Abstract: The invention relates to a frictionless self-driven articulation designed to be mounted between two neighboring elements (E1, E2), comprising two cylindrical fittings (12, 14) rotationally driven through the action of at least one flexible element, of the leaf spring type, the ends of this element being fixed respectively to each of the fittings. According to the invention, the articulation includes means of retaining the fittings (16, 28; 42, 44) and load transfer means (61, 62; 50) separate from the retention means.

Abstract: The invention relates to a deployment system for spatial appendages for example solar generators, comprising at least one two-phase deployment articulation line, furnished with two rotation spindles (10, 20). According to the invention the deployment system comprises a synchronization mechanism (101, 102, 103, 106, 107) for the two rotation spindles so that when the driving spindle (20) rotates during a first deployment phase, the driven spindle (10) does not rotate, and then, when the driving spindle rotates during the second deployment phase, the driven spindle rotates in a manner synchronized with the driving spindle.

Abstract: Through pivot (1) has a stator (2) and a rotor (3). The rotor is capable of turning relative to the stator about an axis of rotation (A) and is capable of accepting a through shaft aligned with the axis of rotation. The rotor is connected to the stator by a plurality of webs (4) capable of being deformed to allow the rotor to rotate, and in that in a condition of rest the webs form an angle of inclination relative to a radial direction passing through the axis of rotation.

Abstract: Actuator for a device for the rotary positioning of a movable element for space equipment comprising a part attached to the fixed portion of said equipment, a bearing, a sleeve designed to actuate the movable portion of said equipment and mounted on an output shaft supported by a first race of said bearing, said actuator comprising a mechanically movable input means and being capable of converting a movement of the input means into a rotary movement of the output shaft about the axis of said bearing, characterized in that said second race of said bearing is connected in rotation to the part of said equipment, in that an adjustable stop so as to angularly limit the relative rotation of the two races of the bearing, and in that the rate of rotation of the output shaft in response to a movement of the input means is different depending on whether or not the sleeve is resting on the adjustable stop.

Abstract: A rotary positioning device of a movable element for space equipment comprising a part attached to a fixed portion of the equipment and a handle actuating the movable portion of the equipment, said handle being rigidly connected to a first race of a ball or roller antifriction bearing and said fixed part being connected to the second race of said antifriction bearing, wherein a link between said fixed part and the second race is an elastic link in rotation about the axis of said antifriction bearing and wherein a stop is rigidly attached to one of the races in order to interact with an element rigidly attached to the other race, so that the relative rotation of the two races of said antifriction bearing is limited angularly.

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.