Small cubesat systems may be available for a lower cost, have a higher reliability, and be much simpler to use than conventional cubesats. A complete turnkey system solution may be provided, including the ground station and remote field units. The satellite, ground station, and field unit may be provided separately as kits that are ready to go out-of-the-box as soon as they arrive. This enables universities, researchers, and hobbyists to obtain and deploy their own functional satellites. Furthermore, theoretical designs and functionality may be rapidly prototyped and demonstrated, which allows for proof-of-concept without needing to build a larger, more expensive satellite system and hope that the new design or functionality works as intended.

A “black box” space vehicle solution may allow a payload developer to define the mission space and provide mission hardware within a predetermined volume and with predetermined connectivity. Components such as the power module, radios and boards, attitude determination and control system (ADCS), command and data handling (C&DH), etc. may all be provided as part of a “stock” (i.e., core) space vehicle. The payload provided by the payload developer may be plugged into the space vehicle payload section, tested, and launched without custom development of core space vehicle components by the payload developer. A docking station may facilitate convenient development and testing of the space vehicle while reducing handling thereof.

A space body has at least two space modules which can be interchangeably connected to one another. At least one closable connection opening is in each case provided on the space modules, via which a passage is produced when the space modules are connected. Furthermore, at least one coupling device connects in each case the space modules to one another. A supply interface is provided for coupling a supply line of the space modules.

The PanelSat serves to launch one, better several satellites into space, whereby besides unfurling of the thin film solar cell panels off their rolls no further deployment is needed. PanelSats are small agile spacecraft thought especially for observation and communication services in LEO, which are using their thin film solar cell panels for both, harvesting electric energy as well as for fuel less station keeping, steering, pointing and propulsion. In contrast to conventional satellites with their 3-axis control design, PanelSats are not locked to only 3 axles and can tilt and point into several directions (depending on the number of panels). Besides Roller Reefing for fuel less attitude control PanelSats feature “Soso Steering” (switch on, switch off) which adds even better fuel less agility compared to prior art satellites.

Systems and methods for describing, simulating and/or optimizing spaceborne systems and missions. Configurations for spaceborne systems are generated and validated based on simulation output.

A joint system for constructing orbital and extra-terrestrial structures includes a node receptacle having a node surface and a finger receiver projecting outwardly of the node surface, and a strut element including a support member, a finger element shiftably supported on the support member, a shell system shiftably supported on the support member and connected to the finger element, and an actuator mounted to the support member and operatively connected with the shell system. The actuator is operable to shift the finger element and the shell system into contact with the node receptacle. The finger element cooperates with the finger receiver to form a first load path and the shell system cooperating with the node surface to form a second load path.

A modular satellite testing platform system having an upper and a lower member along with a plurality of support members, intermediate members, and lower bar members that are interconnected to the upper member and the lower member. The system further includes a plurality of shelf members that are attached to the support members. The satellite also includes a plurality of bottom cover members that are attached to the lower member by a plurality of hinge members that allow the cover members to selectively rotated about an axis to be rotatably translated between an opened position and a closed position. The system yet further includes a thermal control system to allow maintaining the thermals of the satellite as desired.

Method and apparatus to efficiently launch spacecraft from underwater. Unfortunately, the prior art processes of launching spacecraft from sea either make no use of water buoyancy or waste use rocket fuel to overcome water resistance. As a result, payloads are smaller than are ideal. The instant invention however adds water buoyancy to increase the overall thrust of the spacecraft and therefore makes the spacecraft more efficient than if launched outside of water.

The present invention provides a space vehicle comprising an optical system having a field of view, the optical system comprising at least two optical elements spaced from one another along an optical axis of the optical system, thereby defining an interior cavity of the optical system; at least one control system, the control system comprising at least one physical element configured for performing one or more functions for enabling operation of the vehicle; and at least one holding assembly for holding the at least one control system, the holding assembly comprising a folding mechanism configured and operable to move between a folded position corresponding to an inoperative mode of the optical system, and a deployed position corresponding to an operative mode of the optical system, such that in the folded position of the folding mechanism, the control system that is held by the holding assembly is at least partially located in the interior cavity of the optical system for stowage, and in the deployed position of the folding mechanism, the control system that is held by the holding assembly is located outside the interior cavity and outside the field of view of the optical system, thereby allowing operation of the optical system.

A method for coupling an energy supplying device to an energy consuming device in space and to a system including an energy supplying device, an energy consuming device and a mobile assembly unit residing in space. The energy supplying device is operable in space and includes solar panel units to convert received light into electrical energy, first coupling members to couple the solar panel units with each other, and a second coupling member to electrically couple the energy supplying device with the energy consuming device. The energy supplying device is configured to supply electrical energy to the energy consuming device in space. A configuration of the solar panel units is changeable in space according to an operational requirement of the energy consuming device.