A method for the deployment of reconnaissance devices including buoy cameras and robotic devices in a target mission area of a remote location in space utilizing a maneuverable descent de-booster capsule and a buoyant vessel for the deployment is disclosed, including identifying the target area from an orbiting spacecraft; deploying the de-booster into orbit over the target area; initiating gradual descent of the de-booster in the atmosphere of the remote location in space; ejecting the buoyant vessel and its payload from the de-booster; filling the buoyant portion of the buoyant vessel with a lifting gas to cause the buoyant portion to become a large balloon; activating reconnaissance devices on the bay portion of the buoyant vessel, including video and other devices for monitoring and surveiling the target mission area; maneuvering the buoyant vessel to refine mission site selection; opening cargo bay doors at a predetermined altitude to deliver payloads including buoy cameras to the target mission area; causing the at least one buoyant vessel to rise in the atmosphere over the target mission area after payload delivery; and activating communication relay functions in the buoyant vessel while maintaining ongoing reconnaissance activities.

Articles having a hydrophobically-coated region and processes of using such articles are disclosed. The article includes a substrate material and a hydrophobically-coated region on the substrate material, the hydrophobically-coated region being contacted or configured for contact with a fluid. The hydrophobically-coated region is configured to repulse the fluid from the article while the article is moving through the fluid. The process includes using the article by moving the article through the fluid wherein the hydrophobically-coated region repulses the fluid from the article.

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.

Provided are an artificial satellite and a method of controlling the same. The artificial satellite includes a main body flying along an orbit of a planet, an optical payload arranged on the main body to photograph a ground surface of the planet, and a pair of solar cell panels rotatably arranged on both sides of the main body in a first direction, wherein the first direction and a flight direction of the main body form an acute angle with each other.

A method is provided for heating or lighting a designated local area of a planet, moon or other space body in the presence of an ambient flux of cosmic rays by employing either or both muon-catalyzed or particle-target fusion of deuterium-containing fuel material. A series of packages of the fuel are directed to a location that is a specified distance from the local area to be heated or illuminated, for example at a specified altitude above that local area. The fuel material is then released, e.g. chemical explosive, to form a localized cloud that is exposed to and interacts with the ambient flux of cosmic rays and with muons generated from the cosmic rays. The resulting nuclear micro-fusion produces energetic reaction products together with usable heat and light radiating from the localized cloud of material.

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.

This invention serves as the fundamental design for a space-based, nuclear-powered spacecraft for deep space journeys. Nuclear energy is used as the motive power for the propulsion. The spacecraft propellant is a gas (such as helium or hydrogen), which is also the coolant for the onboard nuclear reactor. Nuclear energy is converted to thermal energy in the reactor, which heats up the propellant gas. That superheated gas then expands through the spacecraft nozzle and creates the thrust. The nuclear fuel consists of high enriched uranium. The amount of fuel is mission dependent, and requires declaration of payload, and desired speed, which is limited to sub-light for the first generation of this invention. The spacecraft will be assembled in, and launched from low earth orbit. The spacecraft final assembly consists of modular components delivered to low earth orbit from earth by conventional chemical rockets.

A system for the recovery and management of atmospheric gas is disclosed, such as for use as a vehicle propellant in a vehicle propulsion system. The system can include a compressor configured to compress atmospheric gas and first and second storage tanks configured to store liquefied atmospheric gas from the compressor. The second storage tank can have a heater operable to heat liquefied atmospheric gas therein to convert it to a high pressure gas. The second storage tank includes an outlet duct fluidly coupled to the first storage tank for supplying high pressure gas to the first storage tank.

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.

A method and system for exploring a remote environment from an environment simulator at a local base is disclosed. The system includes: at least one proxy robot in the remote environment with at least one near-field and at least one high resolution 360-degree far field video camera; at least one additional device at the remote environment to capture images and data; a transmitter at the remote environment to transmit the video and data to the local base; a terrain analysis computer at the local base to receive and process the video and data to generate a 360-degree approximated real time (ART) video field representing a terrain surrounding the at least one proxy robot; a display in the environment simulator to display the ART video field for at least one user; a full body motion capture suit marked to the dimensions of the at least one user; and a plurality of motion capture video cameras to capture each position change in the motion capture suit, wherein activities performed virtually in the environment simulator represent the identical activities to be performed by the proxy robot in the terrain of the remote environment.