Deployable devices, systems, and methods are provided. Some embodiments include a system that may include: multiple frames configured to support multiple elements; multiple longerons; multiple diagonals coupled with the multiple longerons; and multiple battens. One or more battens may be coupled with at least one or more longerons and one or more frames such that the respective batten is offset at least along a length of the respective longeron with respect to at least a hinge point between the respective longeron and another longeron from the multiple longerons or along a length of the respective frame with respect to a hinge point between the respective frame and another frame from the multiple frames. Some embodiments include a method for ensuring synchronous deployment of a system that may include orienting a hinge axis coupled with at least one longeron substantially perpendicular to a hinge axis coupled with two or more frames.

At least first and second solar panels are provided, wherein: each of the first and second solar panels is comprised of a substrate having one or more solar cells bonded thereto, and a frame for supporting the substrate and the solar cells; the frame has a cutout or opening in a center of the frame under the solar cells and, when deployed, the cutout or opening enables cooling of the solar cells through the substrate by exposing a back side of the substrate for transferring or radiating heat directly through the cutout or opening of the frame; and the frame of the first solar panel is configured to be nested inside the cutout or opening of the frame of the second solar panel when the first and second solar panels are stowed in a stacked configuration.

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.

A multijunction solar cell including a substrate and a top (or light-facing) solar subcell having an emitter layer, a base layer, and a window layer adjacent to the emitter layer, the window layer composed of a material that is optically transparent, has a band gap of greater than 2.6 eV, and includes an appropriately arranged multilayer antireflection coating on the top surface thereof.

A system for harvesting solar energy on a spacecraft includes a stiff substrate layer and a working layer disposed on the substrate layer to provide at least one of a photovoltaic or a reflective function. In a first operational state, the substrate layer is arranged as a tape spring to store potential energy which causes the substrate layer to uncoil and provide, in a second operational state, a photovoltaic module and/or a solar concentrator.

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.

A satellite in accordance with the present teachings has plural “thin” (i.e., panel-like) segments, which are coupled together and extendable along the in-track direction of movement of the satellite. One or more of these segments, which is advantageously an antenna panel, has the ability to “roll” relative other segments. This enables the satellite to establish and maintain direct pointing of the antenna panel to a targeted area on the ground. The antenna panel includes linear, electronically steerable array.