A solar array wing includes an extension mast to be extended from a wound state, and a support member, around which the extension mast is wound, to support the extension mast after the extension mast is extended. The support member is made of a fiber reinforced composite material. A coefficient of linear expansion of the fiber reinforced composite material, a unit of which is for each degree Celsius, in a direction that is orthogonal to an extension direction of the extension mast, is higher than or equal to −1×10.sup.−6 and lower than or equal to 1×10.sup.−6.

A satellite observation system and method of deploying a satellite system are disclosed. The system includes a plurality of observation satellites comprising one or more sensors, each of the plurality of observation satellites configured with at least a solar array and a mechanical stabilization element. Each of the plurality of observation satellites is constructed without positioning components. The plurality of observation satellites is positioned in a dawn/dusk sun-synchronous orbital plane about a celestial body such that the one or more observation sensors are oriented toward the celestial body. The system further includes one or more servicing vehicles configured to engage each of the plurality observational satellites to configure at least the solar array and mechanical stabilization element

Cell-based systems may interlock in a reconfigurable configuration to support a mission. Space systems, for example, of a relatively large size may be assembled using an ensemble of individual “cells”, which are individual space vehicles. The cells may be held together via magnets, electromagnets, mechanical interlocks, etc. The topology or shape of the joined cells may be altered by cells hopping, rotating, or “rolling” along the joint ensemble. The cells may be multifunctional, mass producible units. Rotation of cell faces, or of components within cells, may change the functionality of the cell. The cell maybe collapsible for stowage or during launch.

Systems and methods for pointing photovoltaic arrays for optimal power generation. One or more methods among a plurality of methods for pointing an array may be used by a spacecraft control system to point the array. Example methods to use to point the photovoltaic array relate to analyzing current output, analyzing image data, and analyzing computational knowledge of reflective bodies or light sources. The spacecraft may be further controlled to reduce shadow by re-orienting, receiving light reflected off spacecraft, and orienting a photovoltaic array relative to incoming light sources based on topographic properties of the array such as cell grooves.

A space vehicle electromechanical system may employ an architecture that enables convenient and practical testing, reset, and retesting of solar panel and antenna deployment on the ground. A helical antenna winding fixture may facilitate winding and binding of the helical antenna.

An array of antenna assemblies each generate solar power and utilize the generated solar power at that antenna assembly, which enables large amounts of power to be generated. An antenna assembly having a flat antenna layer forming a first outer surface of said antenna assembly, a flat solar layer forming a second outer surface of said antenna assembly, and a flat structural layer having a flat support structure sandwiched between the antenna layer and the solar layer. The antenna layer has a flat antenna plate with one or more antennas at the first outer surface of the antenna assembly to communicate with Earth. The solar layer has a flat solar plate with one or more solar cells at the second outer surface of the antenna assembly to receive solar energy and generate power.

A deployable structure for use in establishing a reflectarray antenna is provided that includes a flexible reflectarray and a deployment structure that includes an endless pantograph for deploying the flexible reflectarray from a folded, undeployed state towards a deployed state in which the flexible reflectarray is substantially planar. In a particular embodiment, the deployment structure includes a plurality of tapes that engage the endless pantograph and are used to establish a positional relationship between the deployed reflectarray and another component of the reflectarray antenna.

A space-grade solar array includes relatively small cells with integrated wiring embedded into or incorporated directly onto a printed circuit board. The integrated wiring provides an interface for solar cells having back side electrical contacts. The single side contacts enable the use of pick and place (PnP) technology in manufacturing the space-grade solar array. The solar cell is easily and efficiently packaged and electrically interconnected with other solar cells on a solar panel such as by using PnP process. The back side contacts are matched from a size and positioning standpoint to corresponding contacts on the printed circuit board.

An example of a satellite includes a first radiator panel with first heat-generating components attached to its surface and a second radiator panel with second heat-generating components attached to its surface. One or more actuators are configured to deploy the first and second radiator panels from a compact configuration in which the first and second radiator panels are overlapping to a deployed configuration in which the first and second radiator panels are non-overlapping.

An apparatus includes a satellite in the form of a plate having a thickness being smaller than a width of the satellite. The apparatus also includes a plurality of contact points distributed on a face of the satellite, allowing for one or more additional satellites to be stacked upon the satellite.