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.

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.

An enclosed volume is provided for performing operations in space, or on any astronomical object, in a manner separated from aspects of the external environment. The enclosed volume can be a flexible container for a satellite. The enclosed volume can include a membrane having a fluid barrier layer and being configured to contain a propellant gas or fluid; and an expulsion device configured to expel material from the membrane. In a stowed configuration, the flexible container is contained within the satellite, and in a deployed configuration, the flexible container extends away from the satellite. The flexible container can inflate from one shape, in the undeployed configuration, to another shape, in a deployed configuration. The other shape can be toroidal or other appropriate shapes. The flexible container can provide bipropellant, blowdown, and gas/fluid metering functionality. Entertainment and game play can be enabled by the enclosed volume involving robots and other devices.

A method for the deployment of reconnaissance devices including buoy cameras and robotic devices in a target mission area of a remote location in space utilizing a maneuverable descent de-booster capsule and a buoyant vessel for the deployment is disclosed, including identifying the target area from an orbiting spacecraft; deploying the de-booster into orbit over the target area; initiating gradual descent of the de-booster in the atmosphere of the remote location in space; ejecting the buoyant vessel and its payload from the de-booster; filling the buoyant portion of the buoyant vessel with a lifting gas to cause the buoyant portion to become a large balloon; activating reconnaissance devices on the bay portion of the buoyant vessel, including video and other devices for monitoring and surveiling the target mission area; maneuvering the buoyant vessel to refine mission site selection; opening cargo bay doors at a predetermined altitude to deliver payloads including buoy cameras to the target mission area; causing the at least one buoyant vessel to rise in the atmosphere over the target mission area after payload delivery; and activating communication relay functions in the buoyant vessel while maintaining ongoing reconnaissance activities.

A lightweight flexible BNNT mat or fabric provides improved thermal stability and shielding capabilities under a hypersonic thermal flux. The BNNT mat reduces the stagnation temperature and maintains a low regression rate. An in-situ passivation layer may be formed on the BNNT mat or fabric under high thermal flux. The passivation layer minimizes or prevents penetration of the atmosphere (air or gas) as well as heat and radiation through the thickness of the BNNT material, and it effectively diffuses heat throughout the mat or fabric laterally and radially to minimize localized excessive heat. A BNNT mat according to the present disclosure may also efficiently transfer heat from the BNNT material via radiation due to the high thermal emissivity (0.92) of the BNNT material.

A joint assembly thermally isolates a warm structure, such as a payload, from a cold structure, such as a cryogenic fuel tank, in a space vehicle while maintaining structural interconnection within the joint assembly. The joint assembly includes a primary joint that is capable of separating, and a secondary joint connected to and adjacent to the primary joint. The secondary joint includes an inflatable annulus structure and one or more restraining members, where separation of the primary joint causes the inflatable annulus structure to be in compression and the one or more restraining members to be in tension.

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.

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.

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.

The present invention generally is a system and method for ground, atmospheric and space based solar powered electrical energy generation and transmission of beamed microwave power. Specifically it is a system and method for generating electrical energy from a plurality of photovoltaic cells dispersed on a flexible surface each in close proximity to and functionally connected to microwave generating and transmitting means for controllably forming one or more stronger microwave beams by combining a plurality of much weaker individual microwave beams. The invention can be a microwave beam weapon for detecting and transferring microwave energy to non-cooperative targets or it clear orbital debris by momentum transfer to space object through microwave radiation pressure. Most practically it can provide electric power and microwave beam weapon defense to remote military and civilian facilities, including forward operating bases.