This new and useful invention provides personnel and equipment protection from radiation threats in space. It supplements or replaces current board radiation shielding of spacecraft. and is a scalable individual space borne enclosure (or system of enclosures) large enough to enclose various manned spacecraft types. This enclosure, which is comprised of proven radiation shielding material like hydrogen rich polyethylene, is deployable from the Earth's surface into an elliptical orbit around the Earth or other planetary bodies with a perigee in LEO and its apogee substantially above the Earth's Van Allen Radiation Belts.

The inventions functionality is that spacecraft which must traverse the Earth's Van Allen Radiation Belts may match orbits with and dock inside the enclosure during such transits. After passing through the zones of highest radiation the spacecraft may emerge from the protective orbital shield and commence any further maneuvers. The enclosure deploys on orbit after launch from the Earth using centrifugal force.

A sample collection system for an extraterrestrial vehicle and method of operating is provided. The system includes an inlet conduit configured to receive a gas stream. A chamber having an inlet is fluidly coupled to the inlet conduit, the inlet and chamber configured to induce cyclonic flow. A container is removably disposed within the chamber, the container having a first opening fluidly coupled to the inlet and an outlet. An exhaust conduit is fluidly coupled to the outlet. A filter is disposed between the exhaust conduit and the chamber.

A thermoelectric converter including a thermoelectric generator and a radiation source. The thermoelectric generator includes a hot source, a cold source, n-type material, and p-type material. The radiation source emits ionizing radiation that increases electrical conductivity. Also detailed is a method of using radiation to reach high efficiency with a thermoelectric converter that includes providing a thermoelectric generator and a radiation source, with the thermoelectric generator including a hot source, a cold source, n-type material, and p-type material, and emitting ionizing radiation with the radiation source to increase the electrical conductivity which strips electrons in the n-type material, the p-type material, or both the n-type material and p-type material from their nuclei with the electrons then free to move within the material.

Methods of launching a vehicle using impulsive force are disclosed. In one instance, a vehicle is launched easterly with impulsive force in a plane corresponding to the vehicle's elliptical orbital path. In another instance, a method of closing a timing difference is disclosed. The vehicle undergoes a series of forces after impulsive launch. The first force establishes an orbit having a period significantly different from the orbital period of a satellite or desired vehicle location, closing the difference in an integer number of orbits. The second force establishes the vehicle in circular orbit with the satellite or desired vehicle location. In another instance, the vehicle launched impulsively from a first celestial body travels a first path, and the vehicle experiences a second force along a hyperbolic path about the second celestial body and enters circular orbit about the second celestial body.

A method of space travel using a high acceleration thrust vehicle in combination with a plurality of low acceleration thrust vehicles. A primary spacecraft has a kinetic launcher that is utilized to discharge a plurality of subsidiary spacecraft in order to navigate the primary spacecraft along a flight path. Each of the plurality of subsidiary spacecraft has a propulsion system, allowing each of the plurality of subsidiary spacecraft to navigate to a refueling point. The refueling point for each of the plurality of subsidiary spacecraft may be a central location or a unique position along a subsequent flight path. Each of the plurality of subsequent spacecraft is then reloaded onto the primary spacecraft or loaded onto a subsequent spacecraft for another voyage. The kinetic launcher can be repositioned in order to control the direction of the acceleration experienced by the primary spacecraft.

A lunar base supply method which enables supplying a base on a surface of the moon more easily than carrying materials from the earth to the moon and building the base on the surface of the moon. The lunar base supply method includes the steps of: (a) carrying materials to be used to build a structure to sky of the earth, and causing the materials to revolve along an orbit around the earth; (b) building the structure by using the materials on the orbit around the earth; and (c) moving the built structure from the orbit around the earth toward the moon, and causing the built structure to make a soft landing onto a surface of the moon and thereby to be available as a base.

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 first step of propelling a transport ship from a low earth orbit or a geostationary transfer orbit to a targeted orbit or a destination with electric propulsion is provided.

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 spacecraft propulsion system operated in the presence of an ambient flux of cosmic rays is provided, wherein the cosmic rays interact with deuterium-containing nuclear micro-fusion fuel material to generate products having useful kinetic energy. The propulsion system comprises a supply of the deuterium-containing particle fuel material, along with means (such as a gun) for projecting the material (e.g. as successive packages in the form of shell projectiles) outward from a spacecraft. The spacecraft has means (such as a pusher mechanism) for receiving at least some portion of the generated kinetic-energy-containing products to produce thrust upon the spacecraft.