The invention is directed to a solid, porous material for generating hydrogen gas, said material having a porosity of 20 to 75 vol %, and a composition comprising, based on the weight of the material, 50 to 99% of a boron hydride compound, and 1 to 30% of a binder. A further aspect of the invention relates to a gas generator comprising said material and use thereof in aerospace applications.

The invention is directed to a solid, porous material for generating hydrogen gas, said material having a porosity of 20 to 75 vol %, and a composition comprising, based on the weight of the material, 50 to 99% of a boron hydride compound, and 1 to 30% of a binder. A further aspect of the invention relates to a gas generator comprising said material and use thereof in aerospace applications.

A multilayer sealed skin, in particular for an inflatable structure and that includes a first polymer film, a reinforcing fabric disposed on the first polymer film and a second polymer film disposed on the reinforcing fabric and adhered by means of an adhesive to the first polymer film through cavities in the reinforcing fabric. The skin can be applied to the production of an inflatable structural element such as an inflatable beam for which the skin forms an outer wall of the structural element and for which the first film of the skin forms an inner face of the outer wall of the structural element, and the second film forms an outer face of the wall.

Methods, systems, and apparatus for designing, constructing and using instrument landers for in situ exploration of small solar system bodies, such as asteroids and comets. In one aspect, a lander includes a CubeSat-style platform; instrument packaging, wherein the CubeSat-style platform and the instrument packaging are configured and arranged for an uncontrolled descent, hopping landing on a surface of a body in a solar system, where a descending trajectory for the lander is designed based on gravitational force and solar radiation, with no lander-based propulsion; and a mobility mechanism configured and arranged to self-orient the lander on the surface of the body in the solar system.

Embodiments of the present invention relate to a launch vehicle fairing recovery system and method using inflatable bags and fairing repositioning mechanisms. Embodiments of the present invention also relate to providing a system or mechanism to flip the fairing into the proper floating position. In some embodiments, the fairing has an inner surface and an outer surface, where the outer surface is exposed to the atmosphere when the fairing is interconnected to a spacecraft, and one or more inflatable bags interconnected to the outer surface of the fairing, where when the fairing is interconnected to the spacecraft the one or more inflatable bags is empty, and after the fairing separates from the spacecraft the one or more airbags are filled with pressurized gas and/or hydraulic liquids.

Embodiments of the present invention relate to a launch vehicle fairing recovery system and method using inflatable bags and fairing repositioning mechanisms. Embodiments of the present invention also relate to providing a system or mechanism to flip the fairing into the proper floating position. In some embodiments, the fairing has an inner surface and an outer surface, where the outer surface is exposed to the atmosphere when the fairing is interconnected to a spacecraft, and one or more inflatable bags interconnected to the outer surface of the fairing, where when the fairing is interconnected to the spacecraft the one or more inflatable bags is empty, and after the fairing separates from the spacecraft the one or more airbags are filled with pressurized gas and/or hydraulic liquids.

Space vehicles configured with a micrometeoroid and orbital debris (MMOD) protection system are described herein. The MMOD protection system can include (a) a front face sheet and a rear face sheet spaced apart from the front face sheet directed outwardly, and the rear face sheet being positioned to attach to the space launch vehicle; (b) at least one absorption core layer and at least one impact resistant fabric layer positioned between the front face sheet and the rear face sheet; and (c) an expandable adhesive layer carried by the rear face sheet to attach the MMOD protection system to the space launch vehicle. The front face sheet and the rear face sheet can comprise a metal matrix composite. The MMOD protection system can protect the space vehicle from damage in space, while withstanding launch loads, and can accordingly eliminate the need for a protective launch fairing.

Severe weather agility thrusters, and associated systems and methods are disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end, and is elongated along a vehicle axis extending between the first and second ends. A propulsion system is carried by the launch vehicle and has at least one main engine having a corresponding nozzle positioned toward the first end to launch the launch vehicle. At least one laterally-directed thruster is positioned toward the second end of the launch vehicle. The system further includes a controller in communication with the launch vehicle and programmed with instructions that, when executed, direct the launch vehicle in a first direction during vehicle ascent, direct the launch vehicle in a second direction, opposite the first direction, during vehicle descent, and direct activation of the at least one laterally-directed thruster to guide the launch vehicle during descent.

Severe weather agility thrusters, and associated systems and methods are disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end, and is elongated along a vehicle axis extending between the first and second ends. A propulsion system is carried by the launch vehicle and has at least one main engine having a corresponding nozzle positioned toward the first end to launch the launch vehicle. At least one laterally-directed thruster is positioned toward the second end of the launch vehicle. The system further includes a controller in communication with the launch vehicle and programmed with instructions that, when executed, direct the launch vehicle in a first direction during vehicle ascent, direct the launch vehicle in a second direction, opposite the first direction, during vehicle descent, and direct activation of the at least one laterally-directed thruster to guide the launch vehicle during descent.

Systems and methods for transferring, storing, and/or processing materials, such as fuel or propellant, in space, are disclosed. A representative system includes a flexible container that is changeable between a stowed configuration in which the flexible container is contained within a satellite, and a deployed configuration in which the flexible container extends away from the satellite. The system can include a tanker with a storage container to dock with and refuel a satellite. Another representative system includes a controller programmed with instructions that position a spacecraft with a storage container in a first orbit, transfer the spacecraft to a second orbit, dock the spacecraft with a satellite in the second orbit, transfer material between the storage container and the satellite, undock the spacecraft from the satellite, and, optionally, return the spacecraft to the first orbit. An androgynous coupling system with mechanical and fluid connectors facilitates docking and material transfer.