An apparatus comprises both a first side and a second side that is opposite the first side. The apparatus includes a plurality of photovoltaic cells disposed on the first side of the substrate and a plurality of microwave antennas disposed on both the first side of the substrate and the second side of the substrate. In addition, the apparatus comprises at least one photonic integrated circuit operably coupled to the substrate and to at least one of the plurality of photovoltaic cells to thereby receive electrical power therefrom. By one approach, the apparatus can further comprise at least one atomic clock supported by the substrate. By one approach, at least some of the aforementioned plurality of microwave antennas that are disposed on the first side of the substrate can comprise an optically transparent portion that serves as both a protective cover and a focusing lens.

An apparatus includes a primary device, a secondary device, and an umbilical system. The umbilical system comprises an umbilical linking the primary device and the secondary device, and a control system configured alter a directionality of the umbilical during deployment of the secondary device away from the primary device by at least controlling a configuration of a shape memory material comprising the umbilical.

A method for manufacturing in space a rigid structure having a lattice is disclosed. The method includes creating of at least two framework elements from a coil of metal strip or wire, and creating of the lattice by cold-connecting the framework elements.

A plate folding and unfolding device and a solar panel structure are provided. The plate folding and unfolding device includes a cam fixed with first plate piece, and a rotating shaft is disposed inside the cam in an axial direction of the cam; a connecting rod, where the connecting rod includes a first end and a second end that are opposite to each other, the first end is connected vertically to the rotating shaft, and the second end is fixed to a second plate piece; a positioning shaft, where the positioning shaft is disposed, on the connecting rod; and an elastic piece, where the elastic piece is disposed on the connecting rod, one end of the elastic piece is connected to the positioning shaft, where a groove that accommodates the positioning shaft is disposed at at least one location of the outer peripheral surface of the cam.

A damper for an object is placed in a medium subjected to vibrations. The damper has an idle state in the absence of vibrations, a first operating state in case of vibrations of a first type, and a second operating state in case of vibrations of a second type. The level of each vibration of the first type is less than the level of each vibration of the second type. The damper includes an outer support structure, an inner support structure, and at least one pair of membranes formed of a first membrane and a second membrane. Each membrane is formed of a viscoelastic material including fibers aligned substantially in a same direction.

A damper for an object is placed in a medium subjected to vibrations. The damper has an idle state in the absence of vibrations, a first operating state in case of vibrations of a first type, and a second operating state in case of vibrations of a second type. The level of each vibration of the first type is less than the level of each vibration of the second type. The damper includes an outer support structure, an inner support structure, and at least one pair of membranes formed of a first membrane and a second membrane. Each membrane is formed of a viscoelastic material including fibers aligned substantially in a same direction.

A spacecraft panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members, and each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure.

A spacecraft panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members, and each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure.

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.

The invention relates to a flywheel for stabilising the position of a spacecraft, comprising a hub means (1) for fastening the flywheel, a flywheel ring (4), which externally surrounds the hub means (1) circumferentially at a distance, a support means (3) for supporting the flywheel ring (4) on the hub means (1), and a vibration damping device (6, 8) having a tuned mass damper means (8) which is axially movable back and forth relative to the flywheel ring with respect to a rotation axis of the flywheel.