A spacecraft radiation shield system (2) is disclosed for improving the protection from ionising radiation from the external environment and providing an improved freedom of orientation to the spacecraft. The spacecraft radiation shield system includes: at least two magnets arranged in a magnetic multipole (6), a magnetometer (14), and an adjustable magnet (10). The magnetometer (14) is configured to measure the magnetic field experienced at the spacecraft, and the magnetic field orientation of the adjustable magnet (10) is controlled in response to the measured magnetic field thereby controlling the direction and magnitude of the overall dipole moment of the system

A method and apparatus uses a VLF transmitter, a VLF receiver, and/or a low earth orbit satellite including a rocket engine. A VLF wave transmitted into space is converted to an ambient wave. The ambient wave acts as a signal wave for a whistler traveling wave parametric amplifier. Rocket exhaust is generated in atmospheric plasma. The rocket exhaust includes kinetic energy acting as a Lower Hybrid wave source. The Lower Hybrid wave source produces a Lower Hybrid wave, which acts as a pump wave for the parametric amplifier. Nonlinear mixing of the signal wave and the pump wave in the atmospheric plasma simultaneously parametrically amplifies the ambient wave and generates an idler wave and a parametrically amplified wave. The parametrically amplified wave (1) reduces the density of energetic protons or killer electrons in the Van Allen radiation belt, and (2) improves communications between the VLF transmitter and VLF receiver.

A method and apparatus uses a VLF transmitter, a VLF receiver, and/or a low earth orbit satellite including a rocket engine. A VLF wave transmitted into space is converted to an ambient wave. The ambient wave acts as a signal wave for a whistler traveling wave parametric amplifier. Rocket exhaust is generated in atmospheric plasma. The rocket exhaust includes kinetic energy acting as a Lower Hybrid wave source. The Lower Hybrid wave source produces a Lower Hybrid wave, which acts as a pump wave for the parametric amplifier. Nonlinear mixing of the signal wave and the pump wave in the atmospheric plasma simultaneously parametrically amplifies the ambient wave and generates an idler wave and a parametrically amplified wave. The parametrically amplified wave (1) reduces the density of energetic protons or killer electrons in the Van Allen radiation belt, and (2) improves communications between the VLF transmitter and VLF receiver.

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.

A spacecraft structure for transporting propellant to be consumed by a thruster includes storing the propellant in the spacecraft in a solid state during at least a portion of a take-off procedure and supplying the propellant to the thruster in a liquid or vaporous state when the spacecraft is in space.

A ruggedizing apparatus for electronic equipment in a spacecraft is provided that can achieve both a radiation shielding effect and a heat-dissipation effect. The ruggedizing apparatus includes: a pressure vessel that is filled with a coolant and places at least a heat-generating electronic circuit of the electronic equipment within the pressure vessel, wherein the heat-generating electronic circuit is immersed in the coolant; and a forced liquid-flow generator placed within the pressure vessel, wherein the forced liquid-flow generator causes the coolant on the heat-generating electronic circuit to move away from the heat-generating electronic circuit.

The invention relates to space engineering, in particular, to electric propulsion systems (EP) with electric rocket engines with electrodeless plasma source and acceleration stage using a wide variety of substances as a propellant, designed mainly for installation onboard a spacecraft for transferring it from parking orbit to the target orbit, orbit maintenance, attitude control, altitude control, unloading attitude control systems, maneuvers between orbits, and de-orbiting. The bi-directional wave plasma thruster for spacecraft consists of a gas discharge chamber defining thrust axis, antenna, RF-generator module electrically coupled with antenna, magnetic systems, wherein the gas discharge chamber is configured open to outer atmosphere from two opposite end-faces to form two thrust vectors opposite in direction and having common axis being the axis of the gas discharge chamber, while the antenna is on the outer side of the gas discharge chamber and is surrounded by a ring of dielectric material from its outer side, and there is one magnetic system on each opposite end of the gas discharge chamber, while the gas discharge chamber has a gas dynamic connection line with a propellant supply and storage system by means of two radial gas feedthroughs tightly connected to the gas discharge chamber in two places upstream of the magnetic systems. The technical result is the reduction of thruster weight and dimensions, increase of the specific thrust and specific impulse per consumed power unit, elimination of parasitic discharges damaging thruster and spacecraft structure components, elimination of power losses on the antenna-plasma electromagnetic coupling line, elimination of electromagnetic radiation to the propulsion system components and spacecraft structure components resulting in spacecraft rotation in space.

In some aspects, this disclosure relates to improved Z-grade materials, such as those used for shielding, systems incorporating such materials, and processes for making such Z-grade materials. In some examples, the Z-grade material includes a diffusion zone including mixed metallic alloy material with both a high atomic number material and a lower atomic number material. In certain examples, a process for making Z-grade material includes combining a high atomic number material and a low atomic number material, and bonding the high atomic number material and the low atomic number together using diffusion bonding. The processes may include vacuum pressing material at an elevated temperature, such as a temperature near a softening or melting point of the low atomic number material. In another aspect, systems such as a vault or an electronic enclosure are disclosed, where one or more surfaces of Z-grade material make up part or all of the vault/enclosure.

A system to create a magnetic field around the outside of a spacecraft to afford human occupants and electronic equipment with protection from cosmic and solar radiation. Using electromagnets to generate magnetic fields placed on the outer surface of the spacecraft, cosmic and solar radiation may be deflected from entering the main body of the spacecraft. In addition, the magnetic field lines are kept away from the human occupants and interior electronic equipment. Side electromagnets are placed on the side outer surface of the spacecraft and separate electromagnetics are positioned in a cross shaped configuration at the front and rear of the spacecraft in alignment with the side electromagnets. Magnetic field lines are channeled around the outside of the spacecraft or centered on the center of quadrupole magnets placed either at the front of rear of the spacecraft.

Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, a rocket propulsion system is configured to produce thrust for a spacecraft and includes: one or more optical elements configured to receive solar energy. The optical elements include: a first window configured to allow energy to enter the rocket propulsion system and form a concentrated energy beam, and a second window positioned to allow the concentrated energy beam to pass to the heat exchanger. The second window is spaced away from the first window to form a pressurized plenum chamber therebetween. The system further includes: a heat exchanger configured to receive the energy and use it to heat and pressurize a propulsion gas, and a rocket nozzle configured to expel the pressurized propulsion gas.