Abstract: A space transportation propellant depot has multiple locations, sources and capabilities. Maximizing known mature technologies coupled with realistic industrial techniques results in the incremental development of a propellant source on the moon. Propellant depots are economically driven locations with defined services, sources of propellant and innovation in the pursuit of transportation related commerce as mankind explores for resources beyond Earth.

Abstract: A two-stage space vehicle is provided for achieving low earth orbit that includes a carrier and an orbiter. The carrier has a large airfoil area relative to its dry weight, and the thrust of the rocket engine is controlled such that the carrier achieves a launch altitude and speed for the orbiter without exceeding a wingloading pressure beyond 3,500 Pa., which allows the carrier to be inexpensively constructed. Liquid propellant for the rocket engine is advantageously stored within the relatively large airfoil of the carrier, which is preferably a delta wing. The ratio of airfoil area to dry weight is about 33 m2 per ton, which allows the carrier to descend and land after launching the orbiter with low wingloading on the order of 300 Pa.

Abstract: A vehicle and method for enabling propulsive flight from suborbital altitudes and velocities directly to far space, or beyond Low Earth Orbit (LEO), preferably without requiring injection into or refueling in LEO. The vehicle is preferably reusable and can withstand re-entry speeds and temperatures higher than those that are typical for LEO vehicles. The vehicle preferably lands horizontally, for example on a runway. The vehicle forms the upper stage of a booster vehicle system which can be launched either from the ground or from a subsonic air platform. The vehicle may optionally be used for LEO missions.

Abstract: A preferred In Orbit Transportation & Recovery System (IOSTAR™)(10) includes a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

Abstract: A reversible aerospace plane includes an air intake at a first end of the aerospace plane, at least one heat exchanger disposed in the aerospace plane, an engine at a second end of the aerospace plane, wherein the aerospace plane is configured to accelerate in a first direction and configured to glide and land in a second direction, wherein the second direction is substantially in a reverse direction from the first direction.

Abstract: The present invention provides a method, system and apparatus for robotic refueling of satellites. The system may include a dedicated refueling satellite launched directly from either earth, or alternatively it could be launched from another larger mother spacecraft or space station in which the refueling satellite is ferried into space in the case of the larger space craft or it may be stored on the space station until needed from which it can be launched. The system includes a robotic arm, suitable tools which can be affixed to the end effector of the robotic arm required for accessing, opening and closing the fuel fill valve on the satellite being serviced, storage and retrieval stations on a tool caddy on which the tools and various fuel fill valve caps are stored. The system is under teleoperation by a remotely located operator, for example located on earth, in the mother station or in the space station.

Abstract: A cryocooler is located on a spacecraft bus, such as a bus box, separate from the cryogenic propellant tanks disposed on a separable and distinct propellant cartridge system spacecraft docked to the spacecraft bus. In operation, propellant may be continuously pumped from the tanks through the cryocooler cold heat exchanger and then back to the tanks on the separable propellant cartridge system spacecraft through temporarily couplable lines. After the propellant tanks are depleted, the propellant cartridge system is then undocked from the bus and typically discarded. A new propellant cartridge system spacecraft comprising a full set of tanks may then be docked to the bus and the cryocooler supply/return lines coupled. The remote cryocooler may function as part of a larger space depot for spacecraft resupply, although it is not limited to such applications.

Abstract: A fuel tank for a spacecraft stores a liquid fuel and a pressurized propellant gas that drives the fuel out of the tank through a fuel extraction arrangement including a reservoir or collection container and a tank outlet. The collection container bounds a fuel reservoir space that communicates with the interior space of the tank, and fuel flow channels connect the reservoir space to an outlet pipe. A side or area of the collection container opposite the fuel flow channels is provided with one or more grooves. These structures produce a capillary pumping effect and use the surface tension to separate the fuel from the propellant gas.

Abstract: Using at least one pressure sensor (14, 15, 16) in an emptying pipe (3, 4) or a feed pipe (7, 8, 9) between emptying valves (5, 6) at the outlets from tanks (1, 2) and feed valves (10, 11) for feeding nozzles (12, 13), to detect the pressure waves that result form opening and closing a feed valve (10, 11), and then following operation of said valve (10, 11), detecting the damping or disappearance of the pressure waves, indicating that the transition between the liquid propellant component and the pressurization gas is going past said pressure sensor (14, 15, 16), and thus that the tank (1, 2) is completely empty. This detection of complete emptying is a step in a method of managing propellant that makes it possible to allocate the remaining propellant to a residual lifetime for the satellite in orbit and/or to re-orbiting or de-orbiting the satellite.

Abstract: A reversible aerospace plane includes an air intake at a first end of the aerospace plane, at least one heat exchanger disposed in the aerospace plane, an engine at a second end of the aerospace plane, wherein the aerospace plane is configured to accelerate in a first direction and configured to glide and land in a second direction, wherein the second direction is substantially in a reverse direction from the first direction.

Abstract: A system for transportation and storage of cargo in space includes one or more platforms. The platforms are operable to hold multiple removable propellant tanks and rendezvous with one or more other platforms in space. The platforms also include one or more thruster systems and positioners. Each positioner has an effector operable to grip a band disposed around each propellant tank. Each positioner is operable to facilitate the transfer of the multiple removable propellant tanks between platforms during the rendezvous.

Abstract: An arrangement and a method are proposed for the generation of water on board an aircraft with the use of one or more fuel cells, whereby low-temperature fuel cells are provided as fuel cells. It is proposed that several single-cell or few-cell fuel cells may form a fuel-cell panel or cell array and several cell panels or cell arrays may be arranged close to the inside of the aircraft fuselage and the cathode side of the at least one fuel cell has a chamber pointing to the exterior of the aircraft for the condensation of the water contained in the air and the anode side has a chamber carrying a combustion gas, for example hydrogen. With the proposed solution, a reduction in the storage capacity for drinking water and its quality-assured provision may be enabled and moreover, with the use of fuel cells as a virtual power station, the energy demand on engine generators, auxiliary power unit (APU) or ram air turbine (RAT) may be reduced.

Abstract: A rocket includes: 1) an air-breathing external combustion rocket engine including: a fuel tank configured to contain a fuel combustible with air; a working medium tank configured to contain a working medium; a combustor connected to the fuel tank and configured to combust the fuel with air to form a hot product gas; a heat exchanger connected to the combustor and configured to heat the working medium with the hot product gas via heat conducting walls of the heat exchanger so as to generate a high-energy working medium having a high pressure; and a nozzle connected to at least one of the working medium tank and the heat exchanger and configured to expand the high-energy working medium so as to generate thrust; and 2) accommodations for a human passenger sufficient to allow the human passenger to fly on the rocket.

Abstract: The invention, presents a new concept of spacecraft vehicle design and method of utilization in space flight operations. The system examines the major elements of launch, to orbit flight and return format. The system relies heavily on current space flight technology. Two spacecraft vehicles are utilized in conjunction to achieve Earth orbit. The vehicles are launched simultaneously in a joined configuration. Reaching approximately half distance to orbit, the vehicles separate with the booster vehicle returning to land and the transport vehicle continuing to Earth orbit. Terminating orbit space flight, the transport vehicle reenters the atmosphere returning to land. The details of spacecraft construction and space flight operations are complex and will not be discussed.

Abstract: An In Orbit Transportation & Recovery System (IOSTAR™) (10) One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.