Abstract: The disclosure provides an information processing apparatus, an information processing system, and an information processing method capable of allowing a user to approach a destination intuitively. An information processing apparatus according to the present technology includes a position-coordinate acquisition part, a direction acquisition part, a direction calculation part, and a haptic-feedback determining part. The position-coordinate acquisition part acquires a position coordinate of the information processing apparatus. The direction acquisition part acquires an apparatus direction that the information processing apparatus faces. The direction calculation part calculates a target direction being a direction of a target with respect to the information processing apparatus from a position coordinate of the target and the position coordinate of the information processing apparatus.

Abstract: Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft.

Abstract: A secondary payload bridge for a payload adapter is disclosed and includes a body portion, plurality of payload ports, and a secondary payload port. The plurality of attachment points are connected to the body portion of the secondary payload bridge. The plurality of attachment points are configured to removably attach the secondary payload bridge to the payload adapter to allow for clockable positioning of the secondary payload bridge around a circumference of the payload adapter. The secondary payload port is connected to the body portion. The secondary payload port is configured to releasably attach to a corresponding secondary payload.

Abstract: 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.

Abstract: A spacecraft having a primary structural frame and a propellant tank, in which the spacecraft may include a tank mount adopted to engage a portion of the propellant tank, the tank mount being configured to transfer launch loads directly from the propellant tank to a lunch vehicle interface ring.

Abstract: Herein is disclosed a propellant transfer system and method for refueling on-orbit spacecraft. The system and method are configured to allow for resupply of spacecraft configured to be fueled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The system and method are particularly suited for resupply of satellites not originally prepared for refueling as well but the system may also be used for as satellites specifically designed for refueling.

Abstract: A system and methods are provided for combining systems of an upper stage space launch vehicle for enhancing the operation of the space vehicle. Hydrogen and oxygen already on board as propellant for the upper stage rockets is also used for other upper stage functions to include propellant tank pressurization, attitude control, vehicle settling, and electrical requirements. Specifically, gases from the propellant tanks, instead of being dumped overboard, are used as fuel and oxidizer to power an internal combustion engine that produces mechanical power for driving other elements including a starter/generator for generation of electrical current, mechanical power for fluid pumps, and other uses. The exhaust gas from the internal combustion engine is also used directly in one or more vehicle settling thrusters. Accumulators which store the waste ullage gases are pressurized and provide pressurization control for the propellant tanks.

Abstract: A vertical takeoff and landing (VTOL) rotary-wing air-craft is sized and configured to match a payload container such as a standardized Joint Modular Intermodal Container (JMIC). The aircraft may be an Unmanned Air Vehicle (UAV) that is capable of autonomously engaging and disengaging the container so that the aircraft can pick up and drop off the JMIC with minimum human intervention.

Abstract: A launch system comprises a nose section comprising a nose coupling surface, a tail section comprising a tail coupling surface facing the nose coupling surface and a mast coupling the nose and tail sections. The mast is configured to expand and retract to displace the nose and tail sections within a range of distances from one another. In a retracted state, the nose and tail sections are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to at least one integrated module located between the nose and the tail sections.

Abstract: A reusable unmanned single-stage boost-glide suborbital Earth launcher, able to propel large or smaller payloads from Earth surface or from air launch, to a nearly Earth-orbital condition, then glide circum-globally to horizontal airstrip landing at its launch site or similar circum-global recovery site. The payload, using its own propulsion, is thus enabled to complete insertion into low-Earth-orbit (LEO) or destinations beyond LEO. This technically feasible capability, beyond conferring economic benefits of reusability and maneuverability, can be adapted to increase payload by adding drop tanks, or solid or liquid “strap on” boosters, and might eventually be modified and evolved to perform manned aerospace missions, as well as single stage to orbit (SSTO) missions.

Abstract: A fluid storage and transport module includes complex plumbing features such as fluid reservoirs, filters, heat exchangers, three-dimensionally routed tubing, valves, mixing chambers, and exit apertures formed in and on a monolithic common bulk material using an additive rapid prototyping process of depositing multiple layers of rapid prototyping materials without welds, adhesives or compression fittings, being made by a method that minimizes leaks, maximizes packing density of the functional components, and increases the plumbing robustness to leaks.

Abstract: A spacecraft may include a module structure having a plurality of module sides. The spacecraft may include a central cylinder extending through a center of the spacecraft. The central cylinder may be the only closed cross-section extending along a longitudinal axis of the spacecraft.

Abstract: A spacecraft may include an upper core structure or a lower core structure. The upper core structure may include an upper cylinder for supporting an upper spacecraft of a dual-manifest launch configuration. The lower core structure may include a lower cylinder for supporting a lower spacecraft with the upper cylinder mounted on top of the lower cylinder. The upper cylinder may have an upper cylinder inner diameter that may be substantially similar to the lower cylinder inner diameter.

Abstract: A spacecraft having a primary structural frame and a propellant tank, in which the spacecraft may include a tank mount adopted to engage a portion of the propellant tank, the tank mount being configured to transfer launch loads directly from the propellant tank to a lunch vehicle interface ring.

Abstract: A method and apparatus for strong bonded wide joints for cryogenic applications. In one advantageous embodiment, an apparatus may comprise a three-dimensional preform and a plastic matrix. The plastic matrix may be impregnated in the three-dimensional preform to form a softening strip that may be capable of remaining flexible at a temperature at which a gas may have a liquid form.

Abstract: A launch system is provided which includes a secondary payload. The secondary payload includes a propellant tank and at least one module that is supported by an adapter ring that is commonly used to secure an upper stage to a primary payload. The propellant tank is launched empty and subsequently filled with residual propellant from the upper stage.

Abstract: A device (1) for draining a tank of fluid under pressure pertaining to a space system includes a pyrotechnic actuator that is suitable to perforate a conduit (2) in fluid communication with the tank, the device including a collar (4) that is suitable to enclose the conduit, the collar bearing: a pyrotechnic cartridge (5) for perforation, oriented radially towards the conduit (2), and an anvil (11), diametrically opposed to the cartridge in relation to the conduit, that is suitable to collect debris generated by the perforation.

Abstract: The invention relates to a craft comprising an energy storage system of the RFCS (regenerative fuel cell system) type and a system for pressurizing the propellants used for propulsion. The craft also comprises a plurality of means (31 to 38) for coupling the tanks of the fuel cell to the propellant-pressurizing tanks of the propulsion system of the craft when the tanks of the propellant-pressurizing system are no longer used. The invention also relates to the method of coupling the tanks of the propellant-pressurizing means to the energy storage system. The invention applies particularly to telecommunication satellites and more generally to spacecraft.

Abstract: The bundle comprises two pairs of same-volume cylindrical tanks, each pair comprising two tanks containing a same-density propellant suitable for flowing at the same volume flow rate, the four tanks being fastened directly to one another via reinforcing hoops in such a manner that the center of gravity of each of said pairs remains continuously on the axis of said bundle while the propellants are flowing.

Abstract: A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot.

Abstract: A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot.

Abstract: A method and apparatus for forming a joint. A composite insert may be placed into a joint region for a first structure. The composite insert may comprise a structure having a first portion, a second portion, and a third portion all extending from a junction; and a resin impregnated into the structure to form the composite insert. The second structure may be laid up. The composite insert may be bonded to the first structure and the second structure.

Abstract: A propellant depot (40, 150) includes a utility box (42, 42?) that has space flight equipment. A propellant cartridge adaptor (95) is coupled to the utility box (42, 42?) and to an exchangeable propellant cartridge system (41). The propellant depot (40, 150) also includes a docking adaptor (44) for coupling to an approaching spacecraft (24). A controller (66) controls the transfer of propellant from within the exchangeable propellant cartridge system (41) to the spacecraft (24). A method of providing propellant to a spacecraft in space includes launching an orbital propellant depot (40, 150) into space. The spacecraft is docked to the orbital propellant depot (40, 150) in space. Propellant is transferred to the spacecraft. The spacecraft is separated from the orbital propellant depot (40, 150).

Abstract: One embodiment of the invention includes a spacecraft system. The system includes a spacecraft payload system coupled to a spacecraft frame. The system also includes a plurality of spacecraft panels disposed about the spacecraft frame. Each of the plurality of spacecraft panels can be communicatively coupled together via a network and configured substantially identically with respect to each other, and can include a processor and associated spacecraft control components. The processors of each of the spacecraft panels controlling the respective spacecraft control components independently to cooperatively and autonomously implement spacecraft control functions to implement a common mission objective.

Abstract: A replaceable cartridge for coupling to a consumer or to a filling station, wherein the replaceable cartridge comprises at least one disconnectable connection coupling for connection to the consumer or the filling station. Furthermore, the replaceable cartridge comprises a tank for holding liquid hydrogen.

Abstract: An aircraft including a fuselage including a cabin to accommodate persons and/or a load, and a propulsion system. The propulsion system includes at least one tank and/or one combustion chamber, wherein part of the propulsion system can be used as an extension of the cabin to accommodate persons and/or a load, the part of the propulsion system lying adjacent the cabin and separated from the cabin by a partition.

Abstract: A propellant depot (40, 150) includes a utility box (42, 42?) that has space flight equipment. A propellant cartridge adaptor (95) is coupled to the utility box (42, 42?) and to an exchangeable propellant cartridge system (41). The propellant depot (40, 150) also includes a docking adaptor (44) for coupling to an approaching spacecraft (24). A controller (66) controls the transfer of propellant from within the exchangeable propellant cartridge system (41) to the spacecraft (24). A method of providing propellant to a spacecraft in space includes launching an orbital propellant depot (40, 150) into space. The spacecraft is docked to the orbital propellant depot (40, 150) in space. Propellant is transferred to the spacecraft. The spacecraft is separated from the orbital propellant depot (40, 150).

Abstract: A launch vehicle for a space station includes a crew transport vehicle having an orbiter, a cylindrical cargo module separable from the orbiter when in low earth orbit, and a first liquid fuel rocket engine section coupled to the cargo module operable to assist in placement of the launch vehicle in low earth orbit. The first engine section is separable from the cargo module in low earth orbit. The launch vehicle also includes booster rockets operable to place the launch vehicle in low earth orbit, and a liquid fuel tank, which is convertible to form living and working spaces for the space station. The space station includes rentable space that is used to recover launch and assembly costs associated with the space station.

Abstract: A reservoir safely accommodates a fuel using a barrier layer, which at least partly separates the contact areas of the reservoir and/or contact elements to be protected. The barrier layer is formed of a fire-proof medium which displaces volatile and ignitable fuel having a density less than the density of the fire-proof medium, providing a chemical-physical separation of hydrogen from the air surrounding the reservoir. In vehicles, particularly aircraft, safe operation may be improved by application of the barrier in the reservoir. In one embodiment, there is an additional reservoir filled with an inert material that surrounds the hydrogen reservoir.

Abstract: A fuel tank of a spacecraft stores a liquid fuel and a pressurized propellant gas that drives the fuel out of the tank though a fuel extraction arrangement including a reservoir or fuel collection container and a tank outlet. A spiraling or J-shaped or hook-shaped fuel collection channel and plural obliquely sloping fuel flow channels connect the fuel collection container to an outlet pipe of the tank outlet. The channels are configured, dimensioned, oriented and arranged to ensure that fuel will be retained in the outlet pipe without leaking back into the fuel tank, even when the tank is oriented horizontally and has a low tank filling level. These structures produce a capillary pumping effect and use the surface tension to separate the fuel from the propellant gas, and allow the inner space of the collection container to be completely filled with liquid fuel.

Abstract: A rocket includes a front warhead, a rear propellant actuator, and a propulsion enhancement arrangement which comprises at least two propulsion impulse generators longitudinally cascadedly mounted between the warhead and the rear propellant actuator, wherein each propulsion impulse generator comprises a storage barrel for storing a predetermined amount of explosive materials to provide propelling impulse upon controlled explosion thereof, and a time-internal control arrangement comprising a time-interval control device mounted on a bottom of the front warhead, a time-interval trigger wire operatively connected with the time-interval control device, and at least two time-interval triggers mounted along the time-interval trigger wire and inside of each of the storage chambers respectively, wherein the time-interval triggers trigger the explosion of the explosive material stored in the storage chamber from the bottom propelling impulse generator to the top propelling impulse generator one by one at a predetermin

Abstract: A propellant depot (40, 150) includes a utility box (42, 42?) that has space flight equipment. A propellant cartridge adaptor (95) is coupled to the utility box (42, 42?) and to an exchangeable propellant cartridge system (41). The propellant depot (40, 150) also includes a docking adaptor (44) for coupling to an approaching spacecraft (24). A controller (66) controls the transfer of propellant from within the exchangeable propellant cartridge system (41) to the spacecraft (24). A method of providing propellant to a spacecraft in space includes launching an orbital propellant depot (40, 150) into space. The spacecraft is docked to the orbital propellant depot (40, 150) in space. Propellant is transferred to the spacecraft. The spacecraft is separated from the orbital propellant depot (40, 150).

Abstract: A fuel pickup includes a fuel pickup tube having a plurality of holes for receiving fuel from inside a fuel container; and a wicking material enveloping at least one of the plurality of holes. Aircraft fuel systems including a fuel pickup comprising a wicking material are also disclosed.

Abstract: An aerospace frame accommodates propellant tanks for facilitating propellant operations in space. The frame includes at least two plates for supporting the propellant tanks; at least one brace supporting the plates; and a cavity between two plates that accommodates a removable propellant tank.

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: An orbital stage system has an orbital stage and one or more launch stages. The orbital stage incorporates an orbital maneuvering system (OMS) and an abort propulsion system which both utilize the same propellants, propellant tankage, and propellant pressurization system, but which employ radically different engines. The OMS engines are comprised of at least two engines which have a combined thrust in the neighborhood of 1/10 the weight of the orbital stage, an area ratio of 50 or more and an operating life of many hundred seconds, preferably many thousands of seconds or more. The abort engine may be a single engine and typically has a thrust of three, four, or more times the weight of the vehicle and an area ratio in the neighborhood of two and an operating life of at most a few tens of seconds.

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: 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: The present development relates to an improved wing having a tip tank assembly. The tip tank assembly is attached to a distal end of an outer wing section. The tip tank assembly includes a tank, a pair of mounting brackets and a fairing assembly. The fairing assembly includes a nose piece, a central piece, a tail piece, an inner end plate, and an upper close out piece. The inner end plate extends perpendicularly downward from a lower surface of the outer wing section eventually terminating at a bottom portion of the central piece. The inner end plate acts as an air dam to trap high pressure air that is generated during flight, substantially increasing the lift of the wing. Lastly, the upper close out piece extends between an upper wing surface and an upper portion of the central piece increasing the overall wingspan of the aircraft.