Asteroid redirection systems are provided that use cosmic ray and muon-catalyzed micro-fusion. These systems include a micro-fusion propulsion system providing thrust for redirecting an asteroid, as well as micro-fusion electrical generation powering an ion drive. The systems deploy deuterium-containing fuel material as a localized cloud interacting with incoming ambient cosmic rays to generate energetic fusion products. Dust or other particulate matter in the fuel material converts some cosmic rays into muons that also catalyze fusion. The fusion products provide thrusting upon the asteroid, or when produced near turbines facilitates electrical generation, which can then power an ion drive.

Cosmic ray and muon-catalyzed micro-fusion electrical generation provides electrical power for mining operations, including any asteroid habitats and mining equipment. The micro-fusion generator systems deploy deuterium-containing fuel material as a localized cloud interacting with incoming ambient cosmic rays to generate energetic fusion products. Dust or other particulate matter in the fuel material, in the localized cloud, and in the space surrounding the asteroid being mined converts some cosmic rays into muons that also catalyze fusion. The fusion products drive turbines to facilitate the electrical generation.

A multi-stage traveling wave thermoacoustic engine is disclosed. A plurality of heat engine stages are formed as a toroidal spiral cascade of N stages inside a pressure vessel. Each stage feeds into the next stage such that all of the thermoacoustic power cycles past a common set of thermal interfaces multiple times with the single domed pressure vessel. The inventive thermoacoustic engine is simpler and cheaper to manufacture and more reliable due to the minimization of hot joints.

A multi-stage traveling wave thermoacoustic engine is disclosed. A plurality of heat engine stages are formed as a toroidal spiral cascade of N stages inside a pressure vessel. Each stage feeds into the next stage such that all of the thermoacoustic power cycles past a common set of thermal interfaces multiple times with the single domed pressure vessel. The inventive thermoacoustic engine is simpler and cheaper to manufacture and more reliable due to the minimization of hot joints.

A system and methods are disclosed for an upper stage space launch vehicle that uses gases from the propellant tanks to power an internal combustion engine that produces mechanical power for driving other components including a generator for generation of electrical current for operating compressors and fluid pumps and for charging batteries. These components and others comprise a thermodynamic system from which system enthalpy may be leveraged by extracting and moving heat to increase the efficient use of propellant and the longevity and performance of the launch vehicle.

A space transportation system for providing high volume, high mass access to space that includes tethers that extend between the earth and one or more space stations or platforms. One or more counterweights may be utilized at the terminal end of the tethers in space. The tethers utilize may be made of carbon nanotubes or other advanced materials and woven into cables with electromagnets embedding therein. The tethers include tapering profiles along their lengths to facilitate operation of the system. Transport vehicles for passengers and cargo travel up the tethers using electromagnetic levitation and impulsion. Energy from solar panels or movement of the vehicles along the tethers may be generated for use in the system or for supplemental uses.

A hybrid power source and control moment gyroscope (HPCMG) is disclosed. The HPCMG includes a control moment gyroscope (CMG), a first conductive bearing, and a second conductive bearing. The CMG includes a first transverse gimbal assembly, a central mass that produces a voltage potential, and a second gimbal assembly rotationally connected to the first transverse gimbal assembly. The first transverse gimbal assembly is rotationally connected to the central mass along a first axis of rotation and the central mass is configured to spin about the first axis of rotation and the first transverse gimbal assembly is configured to rotate about a second axis of rotation of the second gimbal assembly. The first conductive bearing rotationally connects the central mass with the first position of the first transverse gimbal assembly along the first axis of rotation.

An exploration method includes: a step of exploring a natural resource on a satellite, a minor planet, or a planet; a step of acquiring the natural resource detected by the exploration; and a step of storing the acquired natural resource.

A rotation suppressing device 1 includes: a body 10; a shaft 20 extending outward from the body 10 and configured to rotate about a first rotation axis A.sub.1; a rotation part 30 configured to rotate about a second rotation axis A.sub.2 together with the shaft 20; a capture part 40 fixed to the rotation part 30 and configured to capture space debris D; a braking part 50 configured to suppress rotation of the shaft 20; and a body rotation suppressing part 60 configured to suppress rotation of the body 10 occurring when the braking part 50 operates.

A magnetohydrodynamic (MHD) power generation system for powering an electrical system of a spacecraft using space plasma. The system includes an MHD generator and a power control unit. The MHD generator includes an MHD channel and a plasma scoop in fluid communication with the MHD channel. The MHD channel includes a channel oriented in a first direction, magnets operable to provide a magnetic field inside the channel in a second direction orthogonal to the first direction, and electrodes disposed inside the channel within the magnetic field in a third direction orthogonal to the first and second directions. The plasma scoop may be formed by a funnel fitted over the outer periphery of a plasma guide and is operable to direct a flow of space plasma into the channel to pass orthogonally through the magnetic field, generating electrical power output through the electrodes. The electrodes are electrically coupled to the electrical system of the spacecraft via a power control unit, which manages the electrical power output to the electrical system of the spacecraft. A method of using the system for powering an electrical system a spacecraft is also described.