A deployable satellite mast consisting of an inflatable tube, which is stored in fan-fold form before deployment and can be deployed by filling the tube with a gas, and which comprises a device for reinforcing and facilitating the deployment of the mast, which device is external to the mast and comprises one or more stays, first ends of which are wound on a reel device and second ends of which are secured to the tube, with the stays unwinding from the reel when the mast is deployed.

The invention relates to a device for unfolding a rolled-up elongate hollow member having: at least one elongate hollow member which has two elongate shell member halves, and an unfolding mechanism which has a fixed base structure and a winding core which is rotatably supported on the base structure and on which the at least one elongate hollow member in a first state is rolled up and compressed and which by rotating moves and unfolds the elongate hollow member from the first state into an unrolled and unfolded second state so that an elongate hollow space is formed between the two shell member halves of the at least one elongate hollow member, wherein the at least one elongate hollow member has as a first end a hollow member root, via which the elongate hollow member is secured to the rotatably supported winding core, wherein the first shell member half of the at least one elongate hollow member is secured in the region of the hollow member root to the rotatably supported winding core, and the unfolding mechanism has an expansion mechanism which in the region of the hollow member root is in engagement with the second shell member half and which moves the second shell member half in the region of the hollow member root away from the rotatably supported winding core in order to expand the cross-section of the at least one elongate hollow member in the region of the hollow member root when the elongate hollow member is unrolled from the rotatably supported winding core.

Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.

A transportation network for providing propellant in space can include optical mining vehicles that concentrate solar energy to spall captured asteroids, capture released volatiles, and store them in reservoirs as propellants. The network can also have orbital transfer vehicles that use solar thermal rocket modules that focus solar energy on heat exchangers to force propellant through nozzles, as well as separable aeromaneuvering tanker modules with reusable heatshields and storage tanks. The network can have propellant depots positioned between Earth and a transport destination. The depots can mechanically couple to accept propellant delivery and to supply it to visiting space vehicles.

To reduce space debris and decrease risks for future space flights and currently operating satellites, NASA requires all satellites to have an end of life deorbiting plan to prevent satellites from having long and indefinite orbit lifespan. Accordingly, disclosed herein are systems and methods for deploying a deorbiting drag device to dramatically decrease the orbit lifespan of satellites. One of the methods comprises: providing power, using a photovoltaic panel, to a central processing unit (CPU) of the satellite; determining, using a health sensor, a health status of the satellite by monitoring activities of the CPU; and releasing a deorbiting drag device based on the health status by diverting power from the photovoltaic panel to a release actuator.

The present disclosure relates to deployable structures and methods of use thereof. In particular, deployable structures with non-cylindrical or irregular shapes and methods of use thereof are disclosed. Non-cylindrical combustion elements can be used to rigidize such non-cylindrical or irregular shapes. The use of gaseous oxidizers along with deployable structures is also disclosed.

A large reflector inflatable telescope. The telescope has an inflatable hull with a conical lower portion and a hemispherical upper portion. The conical portion is transparent to electromagnetic waves so that radio or light waves can reach an inner reflector, which is interposed between the conical portion and the hemispherical portion. The presence of the inner reflector allows the conical portion and the hemispherical portion to be inflated at different pressures such that the reflector becomes spherical or parabolic. If desired, the reflector can be made adjustable with a membrane behind the reflector that provides electro-static force to shape the reflector.

A rocket-powered space launch system comprises both a vehicle segment with an integrally designed propulsion subsystem and a supporting ground facility segment. Elements of a propulsion unit as easily accessed for removal and replacement of individual components. Said launch system is highly reusable, operable, and facilitates governmental agency regulatory compliant safety of occupants and public without passenger escape function and/or commanded vehicle destruction.

Pneumatically supported towers for low gravity applications are disclosed herein. In one aspect, an inflatable tower for use in vacuum environments can have a membrane configured to support a load when inflated with an inflation gas to a pressures less than 100,000 pascals and greater than 0.01 pascal. The inflation gas can be chosen to have a sufficiently low boiling temperature at the inflation pressure of the membrane that the gas will not condense to a liquid or solid within a defined range of temperatures in which the tower is designed to operate. The membrane can be configured to be packaged for transport in deflated condition and rolled onto cylinders from which the membrane can be later unfurled and inflated as part of the tower inflation process. The membrane can be further configured to progressively inflate beginning at a bottom or lowest level of the membrane during the tower inflation process. The membrane can be divided into a plurality of compartments by one or more diaphragms containing valves configured to regulate flow of the inflation gas between the compartments.

The example non-limiting technology herein provides a Synthetic Aperture Radar (SAR) solution on board a micro-satellite that provides global revisit within 1 month; a cost below US$ 10 million; and satellite mass lower than 100 kg. One solution uses an inflatable Cassegrain type antenna with a phased beam steering array in the 1.2 GHz band.