A passive insulating tank support structure includes a first interface ring mounted to a first tank, a first support ring surrounding and spaced apart from the first interface ring, a second interface ring mounted to a second tank, a plurality of first struts coupling the first and second interface rings, a plurality of second struts coupling the first support ring and second interface ring, a plurality of third struts coupling the first support ring and a first heat source, a third interface ring mounted to the second tank, and a plurality of fourth struts coupling the third interface ring and a second heat source.

Enclosures for facilitating activities in space, and associated systems and methods, are disclosed. A representative system includes a spacecraft having an enclosed interior volume (which can be formed by an inflatable membrane) and one or more unmanned aerial vehicles (UAVs) carried by the spacecraft and positioned to deploy into the enclosed interior volume. The system can include a remote-control system to control the one or more UAVs from a terrestrial location while the spacecraft is in space. A wireless charging system can provide electrical power to the one or more UAVs. A representative method includes configuring one or more controllers to launch a first spacecraft to a first orbit, launch a second spacecraft to a second orbit, move the first spacecraft to the second orbit, dock the first spacecraft with the second spacecraft, and broadcast an event within an interior volume of the first spacecraft to a terrestrial location.

A spacecraft includes a body defining an interior payload region and a particle dispersion layer disposed between the interior payload region and one or more exterior surfaces of the body. The particle dispersion layer is formed of one or more magnets having a persistent magnetic field. The spacecraft including the particle dispersion layer may be manufactured by obtaining a particle dispersion layer having a persistent magnetic field, identifying a directionality of the persistent magnetic field of the particle dispersion layer, and installing the particle dispersion layer between an interior payload region formed by a body of a spacecraft and one or more exterior surfaces of the body according to the identified directionality of the persistent magnetic field.

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.

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.

A system to create a magnetic field or fields around the outside of a spacecraft to provide protection from cosmic and solar radiation. Electromagnets are placed within one or more layers of the outer shell or surface of a spacecraft and are used to generate magnetic fields. Side electromagnets are placed within one or more of the side layers of the outer shell or surface of the spacecraft and separate configurations of electromagnets are positioned within one or more layers of the outer shell or surface of the spacecraft, in a cross shaped configuration, either Quadrupole electromagnet configuration or two right-angled electromagnet configuration, at the front and rear of the spacecraft in geometric alignment with the opposite poled side positioned electromagnets. Magnetic field lines are channeled around the outside of the spacecraft by use of the right-angled electromagnet configuration or centered on the center of the quadrupole electromagnet configuration.

A moon/planet complex, an orbiting docking spaceport, and transportation vehicles therebetween that includes i) moon/planet base station having a landing platform with a plurality of charged plates; ii) a moon/planet orbiting craft, docking spacecraft having landing platform with a plurality of charged plates; iii) a personnel transport spacecraft to shuttle personnel between an orbiting craft and planetary/moon base station having rotating electromagnetic rings 320 and/or rotating electromagnetic plates to interact with charged plates; iv) a large personnel/cargo transport spacecraft to shuttle personnel between an orbiting craft and planetary base station having rotating electromagnetic plates to interact with charged plates.

Disclosed is a micrometeoroid and debris protection system (MDPS) for a thermal control system on a spacecraft. The MDPS comprises a radiator face-sheet, a truss attached to the radiator face-sheet, and a thermally transparent bumper disposed on the truss. The thermally transparent bumper shields the radiator face-sheet from micrometeoroids and debris and enables thermal transfer from the radiator face-sheet through the thermally transparent bumper.

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.

There is provided an oriented wire electrostatic radiation protection system for a spacecraft. The system has a wire management system, and first and second wires coupled to the wire management system. A first wire orientation apparatus orients the first wire in a first wire direction toward, and in parallel alignment with, an approach path of approaching solar particles. A second wire orientation apparatus orients the second wire in a second wire direction opposite to the first wire direction. The system has a control system, and a power supply to charge the first wire to a positively-charged wire and to charge the second wire to a negatively-charged wire. When the approaching solar particles travel alongside the positively-charged wire toward the spacecraft, the positively-charged wire deflects the approaching solar particles away from the spacecraft, via electrostatic repulsion, and the positively-charged wire creates a radiation protection shielded region around the spacecraft.