Passively deployable thermal management devices, systems, and methods are provided in accordance with various embodiments. For example, some embodiments include a passively deployable radiator device that may include: one or more thermally conductive layers; and/or one or more strain energy components configured to deploy passively the one or more thermally conductive layers. The one or more thermally conductive layers may include one or more carbon layers. The one or more carbon layers may include at least one or more graphite layers or one or more graphene layers. At least the one or more graphite layers or the one or more graphene layers include at least one or more pyrolytic graphite sheets or one or more pyrolytic graphene sheets.

According to the present invention, the device, which is provided with a male element secured to one of the parts and a female element secured to the other of said parts, comprises a plurality of resilient fastening strips forming a flared receptacle for said male element inside said female element. This receptacle is slidably movable so as to capture, pull and hold said male element inside said female element.

A hinge (1) attaches between two elements (4) in a deployable structure. The hinge (1) includes support members (2) for attaching to or forming part of the elements (4). The hinge (1) also includes two gears (8) in mesh with each other, each gear (8) attached to a support member (2), with the gears (8) rotating about parallel axes. The hinge also includes a tape spring (16) attached to and extending between the support members (2). The tape spring (16), when extended longitudinally, lies substantially in a plane parallel to the axes of the gears. The tape spring (16) is arranged to actuate the hinge from a folded configuration towards an extended configuration. The hinge (1) also includes a retaining member (18) attached to the gears (8) and/or the support members (2). The retaining member (18) is arranged to restrict the separation of the gears (8) in a direction extending between the axes of the gears.

Methods, systems, and devices for furlable antenna blade components are provided in accordance with various embodiments. For example, some embodiments include a device that may include one or more furlable antenna blade components; each of the one or more furlable antenna blade components may include one or more conductive elements. In some embodiments, each of the one or more furlable antenna blade components include one or more laminate layers. Some embodiments include a method that may include: furling one or more furlable antenna blade components around a central axis; and/or securing the one or more furlable antennae blade components when in a furled state.

Disclosed is a device for controlled separation of a first so-called stationary part and a second so-called mobile part, the stationary part having a stationary connecting surface opposite a mobile connecting surface of the mobile part, the stationary part having a different thermal expansion coefficient from that of the mobile part, the separation device including: at least one connecting agent arranged in a layer between the stationary connecting surface and the mobile connecting surface, at least one device for heating at least one of the stationary part and the mobile part, and at least one system for controlling the heating device.

A release apparatus includes a coiled restraining wire with each end attached to a corresponding fuse wire. The fuse wires are supplied with respective actuation electric currents by respective independent current sources. Flow of actuation current through a fuse wire causes that fuse wire to break; breakage of either one or both fuse wires allows the restraining wire to partially uncoil and allow the release apparatus to transition from a retained condition to a released condition, by allowing disengagement of retention members from a release member that can then move out of the release apparatus. The release apparatus can be employed to attach a deployable component to a satellite or spacecraft, and can be readily repaired, refurbished or reset for repetitive ground testing.

A spacecraft includes an aft surface, a forward surface and a main body structure disposed therebetween, a stowage and deployment arrangement (SDA) joined to the main body structure by a first mechanical coupling, and an antenna that includes a respective feed element and a rigid antenna reflector coupled with the main body by way of the SDA. The feed element is joined to the main body structure by a second, different, mechanical coupling. The spacecraft is reconfigurable from a launch configuration, with the reflector is disposed forward of the forward surface, with its aperture plane substantially parallel to the forward surface, to an on-orbit configuration. The SDA repositions the reflector to a second position corresponding to the on-orbit configuration. In the second position, the reflector is disposed, Earth facing, substantially aft of the forward surface and outboard of the main body structure and is illuminated by the respective feed element.

One aspect of the present invention involves a hold-down and release mechanism (HDRM) that includes a hold-then-release mechanism configured to hold an element until the hold-then-release mechanism is commanded to release the element; and an integral sensor configured to sense an amount of a parameter of interest associated with the HDRM and to communicate the sensed amount of the parameter of interest to a receiving device. The parameter of interest comprises one of tensile preload, temperature, vibration, shock, and time from application of an HDRM firing current to HDRM release of the element.

A release apparatus includes a coiled restraining wire with at least one end attached to a fuse wire. Actuation current through the fuse wire causes it to break; breakage of the fuse wire allows the restraining wire to partially uncoil and allow the release apparatus to transition from a retained condition to a released condition, by allowing disengagement a sleeve from retention members and disengagement of retention members from a release member that can then move out of the release apparatus. The sleeve isolates the restraining wire and fuse wire from load forces on the release member. Rolling bearings within the sleeve against the retention members reduces resistance to disengagement of the sleeve. The release apparatus can be employed to attach a deployable component to a satellite or spacecraft, and can be readily repaired, refurbished or reset for repetitive ground testing.

An example of an apparatus includes a spacecraft body and a solar array that is attached to the spacecraft body. In addition, a solar array spring element is configured to provide a force between the solar array and one or more components of a neighboring spacecraft in a stack of spacecraft.