A roll-out solar array includes a first mandrel having first and second ends and a second mandrel having first and second ends. A hinge extends between the first and second mandrels, such that the roll-out solar array can transition between a stowed position where the mandrels are in a substantially parallel configuration and a deployed position where the mandrels are in a series configuration. A latch may be provided to lock the roll-out solar array in the stowed configuration.

A deformable boom device includes a pair of shells, each shell of a substantially same arc length. A pair of hinges is mechanically coupled to the pair of shells to join the pair of shells into an open cross section as deployed in an extended state, and into about a flat structure in a flattened state. At least one of the pair of shells can include an about semi-circular cross section.

Systems, devices, and methods are provided for extendible membranes, such as solar arrays. Some embodiments include an extendible membrane system that may include: an extendible central column; one or more membranes; and/or one or more foldable membrane supports configured to support the one or more membranes. Each of the one or more foldable membrane supports may be configured to extend from the extendible central column. In some embodiments, one or more of the one or more foldable membrane supports includes two or more segments that may be configured to couple with each other. Some embodiments include a method of deploying one or more membranes that may include unfolding one or more foldable membrane supports from a folded configuration to a linear configuration. Some embodiments include an extendible membrane device with one or more membranes and one or more foldable membrane supports configured to support the one or more membranes.

An elastically deployable panel structure for space solar array applications includes a support structure having a first stowed configuration and a second deployed configuration. The stowed configuration has elastic strain energy that powers deployment of the support structure. The elastically deployable panel structure does not include a boom. Longitudinal edges of the support structure may be curved downward to form an open cylinder when in the deployed configuration. The support structure is configured to be operable as a mounting surface for solar cell arrays.

A spacecraft includes a structural interface adapter for mating to a launch vehicle, an aft surface disposed proximate thereto, and a forward surface disposed opposite thereto, a main body structure, including a plurality of sidewalls, disposed between the aft surface and the forward surface and a plurality of unfurlable antenna reflectors. At least one unfurlable antenna reflector is configured to be illuminated, in an on-orbit configuration, by a respective feed array. The spacecraft is reconfigurable from a launch configuration to the on-orbit configuration. In the launch configuration, the at least one unfurlable antenna reflector is disposed, undeployed, forward of the respective feed array, proximate to and outboard of one of the plurality of sidewalls. In the on-orbit configuration, the forward surface is substantially earth-facing and the at least one unfurlable antenna reflector is disposed, deployed, so as to be earth-facing from a position aft of the respective feed array.

A method for solar array (28a, 28b) deployment includes deploying a first portion of solar cells of a solar array responsive to a first drag condition, charging a battery (26) with the first portion of solar cells, activating an electric thruster (24) at a first power level using the first portion of solar cells, deploying a second portion of solar cells of the solar array responsive to a second drag condition that is lower than the first drag condition, and activating the electric thruster at a second power level that is higher than the first power level using the first portion of solar cells and the second portion of solar cells.

A space-based solar power station, a power generating satellite module and/or a method for collecting solar radiation and transmitting power generated using electrical current produced therefrom is provided. Each solar power station includes a plurality of satellite modules. The plurality of satellite modules each include a plurality of modular power generation tiles including a photovoltaic solar radiation collector, a power transmitter and associated control electronics. The power transmitters can be coordinated as a phased array and the power generated by the phased array is transmitted to one or more power receivers to achieve remote wireless power generation and delivery. Each satellite module may be formed of a compactable structure capable of reducing the payload area required to deliver the satellite module to an orbital formation within the space-based solar power station.

A foil deployment mechanism comprises a first drum rotatable about a first longitudinal axis, and a second drum rotatable about a second longitudinal axis. The foil deployment mechanism further comprises a cable, the cable comprising a first section which extends from a lower part of the second drum to an upper part of the first drum, a second section which is wound around a part of the first drum facing away from the second drum, a third section which extends from a lower part of the first drum to an upper part of the second drum, and a fourth section which is wound around a part of the second drum facing away from the first drum, wherein the first section and the third section intersect each other between the first drum and the second drum when being viewed along the first longitudinal axis.

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.

The invention provides an extendible member (10) which is configurable between a coiled form (11) and an extended form (12). The extendible member (10) comprises: a primary member (14) comprising a sheet of material resiliently biased in a slit tube form, wherein the slit tube can be opened out at the slit to assume an open form in which it has a flattened cross section; at least one resilient secondary member (15) having first and second connections to the primary member (14) at respective different circumferential positions on the primary member (14), wherein in the extended form, the primary member (14) is in its slit tube form and the resiliency of the secondary member (15) causes at least part of the secondary member (15) to displace towards the slit in the primary member (14) to provide torsional and axial stiffness to the primary member (14), and wherein in the coiled form (11), the primary member (14) is in its open form and the secondary member (15) conforms to the flattened cross section of the primary member (149) so that primary and secondary member can be co-coiled. Corresponding methods are also provided.