A system and method for vaporizing space debris in space. The system includes a spacecraft body, a primary solar concentrator mounted to the spacecraft body that collects and focuses solar flux from the sun, and a secondary solar concentrator positioned at a focal point of the primary solar concentrator that refocuses the focused solar flux. A manipulator arm coupled to the spacecraft body grabs the space debris in space and positions it at a location where the refocused solar flux vaporizes the debris. The secondary solar concentrator can be a point-source concentrator, the primary solar concentrator can be a parabolic mirror, a Fresnel lens or a light focusing element or assembly, and the space debris can be a retired spacecraft or launch vehicle upper stage or component.

A system and method for vaporizing space debris in space. The system includes a spacecraft body, a primary solar concentrator mounted to the spacecraft body that collects and focuses solar flux from the sun, and a secondary solar concentrator positioned at a focal point of the primary solar concentrator that refocuses the focused solar flux. A manipulator arm coupled to the spacecraft body grabs the space debris in space and positions it at a location where the refocused solar flux vaporizes the debris. The secondary solar concentrator can be a point-source concentrator, the primary solar concentrator can be a parabolic mirror, a Fresnel lens or a light focusing element or assembly, and the space debris can be a retired spacecraft or launch vehicle upper stage or component.

A pivot mechanism for guiding in rotation comprises a mobile element connected to a fixed element through flexible connections; with the flexible elements being configured to guide the mobile element according to a rotational movement in a plane, around a pivoting axis perpendicular to the plane; with each of the flexible connections comprising an intermediary junction provided with an expansion slot, the expansion slot being configured to expand during the rotation of the mobile element, so that the mobile element can pivot according to a second angular amplitude that is greater than a first angular amplitude achieved without said expansion slot; with the intermediary junctions being connected to one another by a coupling member; each of the coupling members being configured so as to prevent a movement out of the plane and a lateral movement in the plane of the mobile element. The pivot mechanism has a very high rotational amplitude.

A radiator for a geostationary satellite is disclosed having a radiative panel perpendicular to a radiation axis, and pivoting relative to the radiation axis, a mounting foot for the panel, a motor which rotates the mounting foot about a rotation axis, the radiation axis and the rotation axis being tilted relative to each other by an angle corresponding to the angle of the satellite's orbital plane relative to the ecliptic plane of the planet, and a guidance system for the panel, limiting rotation of the panel about the rotation axis, including a connecting arm pivoting relative to the satellite about a first axis and relative to the panel about a second axis concurrent with the first axis at a point of intersection of all the axes.

The present disclosure relates to a mechanism for releasably securing components of a spacecraft together during launch until such time as the mechanism is commanded to release those components. Upon command, the components are then released with extremely low shock forces being transmitted to the previously secured components due to the release.

A reusable device for holding and releasing a bar. The device includes a tightening component, a hold and release component, and at least one loosening component. The hold and release component includes a plurality of segments, each segment includes a first bearing surface configured to bear on part of the bar, when the plurality of segments is in a holding configuration under the effect of a tightening pressure generated by the tightening component. The plurality of segments includes a second bearing surface configured to bear on one end of the at least one loosening component. The at least one loosening component is made from a first single-acting shape memory material. Each end of the at least one loosening component exerting a loosening pressure compensating for the tightening pressure, so as to place the hold and release component in a configuration in which the part of the arm is released.

Pointing interfaces that can be used to assemble/disassemble instruments/payloads from a spacecraft/host are disclosed. The disclosed interfaces provide structural, communications, power, and fluid connections (for thermal control). Such interfaces also provide active and passive vibration isolation capability for precision pointing. They can further act as an interface to the launch vehicle for secondary delivery of the instrument/payload to the spacecraft

Pointing interfaces that can be used to assemble/disassemble instruments/payloads from a spacecraft/host are disclosed. The disclosed interfaces provide structural, communications, power, and fluid connections (for thermal control). Such interfaces also provide active and passive vibration isolation capability for precision pointing. They can further act as an interface to the launch vehicle for secondary delivery of the instrument/payload to the spacecraft

An exterior panel is configured to accommodate high thermal stresses imposed on exterior surfaces of aerospace transport vehicles during hypersonic flight. The exterior panel is formed of a superplastic material such as a titanium alloy, and includes an exterior skin and a plurality of cooling tubes that extend through the panel. The exterior panel further includes an interior skin configured to be attached to a frame member such as a rib, stringer, or spar of the transport vehicle. The tubes pass through a multicellular core, which is sandwiched between the exterior and interior skins to impart tensile and compressive strength to the exterior panel. In one disclosed method, the core is superplastic formed and diffusion bonded to the exterior skin, the tubes, and the interior skin. A cooling fluid, which may be a gas or liquid, including a fuel, may be pumped through the tubes to cool the exterior panel.

Described is an actuator module (100; 200; 300; 400) for releasing an equipment component, e.g. of a satellite or a rocket, comprising a module base forming a guide sleeve (4; 304), a release body (2; 202; 302) for coupling to the equipment component and inserted into the guide sleeve, which release body (2; 202; 302) is movable relative to the guide sleeve (4; 304) along a sleeve axis thereof from a standby position to a working position, a blocking body (8; 408) mounted on the guide sleeve (4; 304), which, in its blocking position, blocks the release body (2; 202; 302) against movement out of the standby position into the working position and, in its release position, allows movement of the release body (2; 202; 302) from the standby position into the working position, and an actuator unit for moving the blocking body (4; 408) from the blocking position to the release position, the actuator unit comprising at least one actuator wire (12; 13) of shape memory material secured with the wire ends to the module base and coupled to the blocking body for applying an activating force.