Abstract: A take-off device includes a telescopic arrangement of three pipes arranged in a frame. The telescopic arrangement can pivot to a limited extent. The frame is mounted on a horizontal axis running through a center of gravity of the device and a centroidal axis of a lift of an airplane wing, whereby the frame can pivot around the axis. Forces exerted between the telescopic arrangement and the frame are transmitted via a bushing wedged on an outer pipe of the three pipes. A compressed gas accumulator can be opened by means of an actuating pressure signal, whereupon the telescopic arrangement extends outward. A bottom portion of an innermost tube knocks against a fixed point on the ground, which allows the airplane to accelerate to a lift-off speed. After the telescopic arrangement has extended outward, the telescopic arrangement retracts inward using a compressed gas stored in a pressure chamber.

Abstract: The product includes a self-propelled aerial pyrotechnic device and an upright launch tube for the device. The device is closely confined within the launch tube so as to be maintained in an essentially truly vertical orientation in preparation for launch. The device itself comprises a body containing pyrotechnic display material and an engine that serves to propel the body when ignited. A stabilizing base, preferably integrally molded from synthetic resinous material, is attached to the lower end of the body and is in the nature of a framework having a plurality of symmetrically disposed, long legs interconnected at various locations by strut structure. The engine is received within a socket at the upper end of the stabilizing base and is adhered to interior surfaces of the legs to provide a secure connection between the body and the base.

Abstract: Aerospace technology, in particular, methods for orbital injection of payloads (communication satellites, monitoring satellites, etc.) into low and medium earth orbits with the aid of aerospace systems comprising a carrier aircraft (CA) and a launch vehicle (LV) with a payload (PL). In the present method, after the CA 1 takeoff from the base aerodrome, its flight in the maximum cruising speed mode to the LV 2 launch area, pitchdown 7 of the CA 1 is effected to gain the maximum permissible horizontal flight speed, and at the moment that speed is attained, CA 1 pitchup 8 with the maximum allowable angle of attack is executed, culminating in transition to an angle of attack with a near-zero g-load (zero-gravity condition), with the pitchup parameters chosen so that at the LV 2 with PL 3 point of separation from the CA 1, the CA 1 has attained a speed VD, flight altitude HD and a trajectory pitch angle Od ensuring a maximum PL 3 and a near-zero normal g-load 9.

Abstract: A mobile aircraft launcher includes a towable, tiltable, wheeled trailer, a launch beam comprising a plurality of sections hinged to one another, an aircraft-engaging shuttle mounted on the launch beam, and a shuttle-moving drive arrangement mounted on the trailer. The launch beam is mounted on the trailer and is movable between a folded, transport condition, in which the beam sections are generally side-by-side, and a launch condition, in which the beam sections are colinear. In the colinear arrangement, a portion of the launch beam extends forward of the trailer, that portion being supportable entirely through the trailer.

Abstract: A reusable first stage (100) includes a booster engine system (102) for providing thrust during launch, a structural assembly (108), canards (118), jet engines (122), wings (124), elevons (126) and retractable landing gear (130). After separation, the jet engines (122) and aerodynamic control surfaces are used to return the first stage to a landing strip. The booster system (102) includes a structurally stable outer skin system such as an isogrid structure. The first stage (100) is thereby adapted for controlled descent and recovery with minimal structural enhancement or added mass.

Abstract: The present invention relates to an aircraft having a plurality of fuselages for increased payload. More specifically, the aircraft has a central fuselage, and first and second side-saddle fuselages mounted on opposite sides of the central fuselage. The first and second side-saddle fuselages further are provided with a mechanism for opening and each of the side-saddle fuselages define a launch tube such that each launch tube is adapted for transporting and launching a large or oversize missile.

Abstract: A payload launching method measures the attitude of a booster during a launch with an inertial measurement unit on the payload to compare the actual booster trajectory with a desired trajectory to control the payload at the deployment location, the inertial measurement unit on a booster carrying the payload using said desired trajectory to reach the deployment location

Abstract: A launch assist system for supplementing the launch acceleration forces of a projectile, rocket or missile. An airtight chamber covered by a flexible elastic membrane supports a platform in the center of the membrane; the platform is electromagnetically coupled to a cocking mechanism that withdraws the platform into the chamber. Air within the chamber is removed and compressed to be stored in a holding tank as the platform is lowered into the chamber and as the flexible elastic membrane extends into the chamber. The electromagnetic coupling may be triggered to release the platform to permit the stored energy in the extended flexible elastic membrane, and in supplemental force members, to apply acceleration forces to a launch vehicle; the compressed air stored in the tank is simultaneously released to fill the chamber as the flexible elastic membrane is withdrawn.

Abstract: A spacecraft may be launched into outer space around the earth by magnetically suspending a sky tube having an inlet on earth and an outlet at altitude. The sky tube is evacuated, and the spacecraft is propelled therethrough to achieve escape velocity for reaching outer space.

Abstract: A device for launching a flying structure having a nose end and a tail end, having a cradle member having a first and a second end, a nose engagement member having a first and second end, a tail engagement member, and means for propelling the flying structure. The cradle member retains the flying structure prior to its launch. The second end of the nose engagement member is pivotably attached to the first end of the cradle member. The nose engagement member releasably engages the nose of the flying structure prior to launch. The tail engagement member releasably engages the tail of the flying structure prior to launch and is attached to the second end of the cradle member. When the means for propelling the flying structure is an elastic cord, the cord is attached to both the first end of the nose engagement member and to a stationary object such that the cord supplies motive force to propel the flying structure after the cord is stretched.

Abstract: An airborne pneumatic launch tube ejection system to described for launching an aerospace vehicle/payload into orbit. The system can be installed in a jet transport aircraft without requiring structural modifications.

Abstract: A satellite communication system has a first deployment of a plurality of satellites deployed in a medium earth orbit and two later deployments of a plurality of satellites deployed in the medium earth orbit. The first deployment is spaced so that the second deployment may be easily deployed and interleaved into the first deployment. A ground terminal is used for communicating with the satellites in the first and second deployments.

Abstract: A parasailing assembly to suspend a rider from a parachute which is being towed by a boat, with the rider supported by one of various rider support structures, such as a body harness or a seat assembly. The parasailing assembly includes an improved connecting assembly that is structured to removably interconnect a rider support structure to the canopy of a parachute and preferably, includes two elongated straps, each having an interconnecting link disposed intermediate opposite ends thereof. Preferably, each strap of the connecting assembly has at least one end is connected to rider support structure, on opposite sides of the rider. In addition, either fixedly or removably attached to the interconnecting link is a base portion having a plurality of strap segments, each of which is connected, preferably but not necessarily in a fixed manner, to a separate grouping of riser line sets which extend up to the canopy of the parachute.

Abstract: A method for increasing the payload that can be delivered by a given launch vehicle to a selected target in an interplanetary space mission, without increasing the transfer time to reach the target. In accordance with the disclosed method, a conventional multi-stage launch vehicle is used to accelerate a payload spacecraft to near earth's escape velocity. Then the spacecraft is separated from the upper stage of the launch vehicle and is further accelerated by applying a velocity impulse with an onboard propulsion system into a transfer trajectory that takes the spacecraft to the target planet. Because the upper stage of the launch vehicle is not accelerated into the same transfer trajectory, a larger payload mass can be delivered to the target planet without increasing the transfer time. Alternatively, the transfer time can be reduced without decreasing the payload mass or changing the launch vehicle configuration.

Abstract: An orbital launch vehicle equipped with aerodynamic lifting surfaces is towed as a glider behind a conventional aircraft. The launch vehicle is used to place spacecraft into low earth orbit. The lift from the aerodynamic surfaces enables the launch vehicle to be towed by means of a flexible cable from a conventional runway using existing aircraft. As with "conventional air-launch," this permits spacecraft launch into orbit to originate from any conventional runway consistent with constraints of public safety, thus eliminating the need to build dedicated launch pads at geographic locations from which a full range of orbital inclinations can be reached. The method of towing the launch vehicle, utilizing the lift of its wings to fully offset its weight, permits at least an order of magnitude increase in the weight of vehicle which can be launched compared to "conventional air-launch" methods whereby the launch vehicle is carried on, or within a conventional aircraft.

Abstract: The invention is a cable restraint system for an aircraft having first and second main landing gears equally spaced from the longitudinal axis of the aircraft; the system for securing the aircraft from movement during engine run-up testing when the aircraft is positioned such that the main landing gears are in front of and the longitudinal axis thereof is aligned with a ground attachment fitting mounted to the ground. In detail, the system includes first and second coupling members. First and second cables having first and second ends, have their first ends attachable to the ground attachment fitting and the second ends attached to the first and second coupling members, respectively. A third cable is attached by its ends to the first and second coupling members. Fourth and fifth cables having first and second ends, are attached by their first ends to the first and second coupling members and attachable by their second ends main landing gears.

Abstract: An internal combustion catapult for loads such as an aircraft using much of the conventional steam system in that an existing elongated launch tube is utilized with an existing movable piston. The steam generation system may be replaced and a plurality of combustors positioned at the aft end of the launch tube facing the trailing end of the piston. Each of these combustors includes an injector assembly for supplying a combustible propellant. At least one igniter is operatively positioned with respect to the combustor to ignite the combustible propellant to form hot launch gases at high pressure to project the piston down the launch tube to launch the aircraft. A water manifold injects water into the combustion gases to cool them and form steam to propel the piston down the launch tube.

Abstract: A system for enabling an aircraft to accomplish extremely short takeoffs and landings, which includes an integrated flight control system; a takeoff system; a landing system and a high thrust-to-weight propulsion system. The integrated flight propulsion control system includes a multi-axis thrust vectoring system. The takeoff system is operably engageable with the multi-axis thrust vectoring system. The takeoff system includes means for rotating the aircraft nose upwardly below stall speed without substantial use of thrust vectoring from the multi-axis thrust vectoring system. The landing system is operably engageable with the multi-axis thrust vectoring system. It includes means for de-rotating the aircraft from a high angle of attack to a main gear touchdown angle of attack sufficiently low to avoid scraping the tail of the aircraft.

Abstract: The invention relates to a temporary towing device intended to impart a very high acceleration to a mobile mass (A, TAV, CF). It comprises a guidance device (G), a carriage (C) mounted so that it can slide with respect to this guidance device (G), a motive device (M, PI) for imparting a movement of acceleration along this guidance device (8, 9) to the carriage (C) in a direction running in the direction of acceleration of the mass (A, TAV, CF). Coupling means (CR) make it possible temporarily to secure the mass and the carriage together as they are accelerated. A braking device (F) makes it possible to brake the carriage at the end of the acceleration of the mass.A device (1) for modulating the towing force (EC) is designed to bring the elements (TAV, CF) of the mass (A, TAV, CF) to the state of rest with respect to one another, or close to this state of rest, the moment the connection is broken.Application to the catapult of an aircraft carrier.

Abstract: An improved system is disclosed for upending/reclining an extraterrestrial vehicle. In one embodiment, first and second trunnion supports may be positioned on opposing sides of a u-shaped opening provided at the rearward end of a mobile support platform. A launch vehicle may be pivotably supported via trunnions received by the first and second trunnion supports for pivotal movement between a reclined position on top of the support platform to an upended position. In the upended position a launch vehicle will extend through the u-shaped opening. A bridge assembly may be selectively interconnected to the launch vehicle to facilitate handling, transport and storage therewith.

Abstract: A wing structure for hang gliders, ultralites, gliders, heavy aircraft, ornithopters and sailsoaring flying boats which has a first wing set that pivots on two axis, and a second wing set that remains substantially immobile relative to the fuselage or keel. The wing pivots on the lateral axis of the fuselage or keel by moving along a slider assembly that allows it to move from a swept position to a more perpendicular position relative to the keel to control the amount of lift. The wing also pivots on the longitudinal axis of the fuselage or keel to control banking. On hang glider versions of the device, optional ducted fan, propeller, or jet propulsion units provide power to maintain flight. An optional bungee launch assembly assists takeoff from relatively flat surfaces. An optional "telepresence" wing controller allows the pilot to control wing motion with minimal physical exertion.

Abstract: A radiosonde balloon launching system including a silo for housing an array of radiosonde balloon modules and for sheltering radiosonde balloons during inflation, a base for containing radiosonde balloon inflation and launch apparatus and a device for shielding the silo until the radiosonde balloons are ready to be launched.

Abstract: A radiosonde balloon launching system including a silo for housing an array of radiosonde balloon modules and for sheltering radiosonde balloons during inflation, a base for containing radiosonde balloon inflation and launch apparatus and a device for shielding the silo until the radiosonde balloons are ready to be launched.

Abstract: A module for automatically launching a radiosonde balloon having a battery powered radiosonde tethered thereto, the module including a housing for the radiosonde balloon and radiosonde; and an automatic balloon inflation and launch apparatus.

Abstract: An attenuation ring assembly for mounting between the payload section and the booster section of a launch vehicle is disclosed. The ring assembly acts as a transient filter to delete or minimize harmful shock and vibration frequencies which might otherwise reach and possibly damage delicate electronic components and the like in the launch vehicle payload.

Abstract: A nose assembly and method for controlling the rotation and stabilizing the orientation of a vehicle during landing maneuvers. The vehicle includes a nose assembly that is coupled to an airframe thereof and that has a frame and flap assembly. The flap assembly includes an actuating means and a flap coupled to the frame such that the actuating means moves the flap from and between a fully retracted position and a fully extended position in response to a guidance signal received from a flight control computer. In a preferred embodiment of the present invention, the flap assembly includes a plurality of flaps each coupled to the nose assembly frame and an actuating means that selectively positions the plurality of flaps in response to a signal.

Abstract: A radiosonde balloon launching system including a silo for housing an array of radiosonde balloon modules and for sheltering radiosonde balloons during inflation, a base for containing radiosonde balloon inflation and launch apparatus and a device for shielding the radiosonde balloons until they are ready to be launched.

Abstract: A radiosonde balloon launching system including a silo for housing an array of radiosonde balloon modules and for sheltering radiosonde balloons during inflation, a base for containing radiosonde balloon inflation and launch apparatus and a device for shielding the silo until the radiosonde balloons are ready to be launched.

Abstract: A method and a system of assembling a launch vehicle vertically on an aboveground platform are presented in the present invention. The method of the present invention enables a rapid assembly of the launch vehicle; thus substantially reducing the final cost of the launch vehicle. The system of the present invention includes a plurality of specially designed tools that enable the rapid assembly of the launch vehicle.

Abstract: A modular launch pad for a launch vehicle which comprises a frame and a plurality of building units separably connected to the frame by means of connectors. The building unit comprise a concrete slab and a peripheral frame made of U-shaped channel sections connected to one another to form a frame, wherein the legs of the U are directed inwardly to engage the major surfaces of the slab. At least one of the legs of the channel sections is partially embedded in the slab so that the outer surfaces of the legs lie flush with the portion of the major surface extending between the legs. A plurality of longitudinally and transversely extending reinforcement bars are embedded in the concrete slab and a plurality of connecting means are secured to the slab. The pad has a launch vehicle mount for supporting a launch vehicle and defines exhaust gas channels in flow communication with an exhaust gas opening in the mount.

Abstract: The invention relates to a mass transit method including a docking terminal where passengers are loaded onto a craft with integral passenger pod. The craft lifts vertically from the docking terminal until it reaches an appropriate commuting altitude within 1,000 feet of the ground at which time the craft will fly to a second docking terminal and vertically descend to the second terminal for unloading of passengers. The commuting routes are networked to create an urban-suburban-rural mass transit system. The utility area of the craft can be detached and replaced. For instance, a passenger pod can be interchanged with a cargo, an emergency medical service (rescue) or a military unit pod for an innovative and versatile means of transportation.

Abstract: An orbital assist module and an interstage for a launch vehicle. The orbital assist module includes a cylindrical outer wall and a support structure secured to an inner surface of the cylindrical outer wall. The support structure defines a plurality of fuel tank supporting zones, at least one of the zones supporting a fuel tank by means of securing formations. A plurality of nozzles are connected to the fuel tanks by means of fuel lines and a plurality of valves are mounted in the fuel lines. The interstage comprises a cylinder having a leading and a trailing end and an explosive connector at the leading end for connecting the interstage to a trailing end of a launch vehicle motor. A connecting bracket is secured to the trailing end of the cylinder for connecting a second launch vehicle motor to the cylinder.

Abstract: A parasailing assembly designed to suspend a rider from a parachute being towed by a boat, the assembly including a rider support structure formed of a rigid yet lightweight and buoyant material and having a front end, a rear end, a pair of oppositely disposed sides, a top side, a bottom side, and a hollow interior, accessible from one of the sides. A reclining seat structure is disposed within the hollow interior and is structured to support at least one rider in a generally reclined position. A pair of straps are further provided and formed of a flexible yet high strength material, with each one of the straps securely yet removably connected to one of the opposite sides of the rider support structure such that when the assembly is disposed in a launched orientation each of the straps is disposed in spaced parallel relation to the other and provides for balance and stable movement of the rider support structure.

Abstract: A low-cost, liquid-propellant rocket launch vehicle having a central pod that carries an optional final-stage rocket engine cluster, and having additional engine clusters arranged in diametrically opposed pairs of clusters. The pairs of clusters are burned and separated in a staging sequence until the final stage is reached. In the presently preferred embodiment, there are three pairs of engine clusters arranged in a hexagonal configuration about the central pod and each engine cluster contains seven identical engines. The engines are made from light-weight, low-cost materials, without gimbals or other moving parts. Steering of the vehicle is effected by differential control of the engine thrusts of selected engines, using duty-cycle modulation of a plurality of on/off propellant supply valves and, additionally, control of other on/off valves controlling the supply of an inert cryogenic fluid to secondary injection ports on the engine.

Abstract: Systems (10, 10a) and a methods (40) that employ a spin-stabilized spacecraft (12) in combination with a support and deployment module (14) to carry a plurality of probes (16) containing scientific instruments that are to enter a planet's atmosphere and/or are to be landed on a planet (19) that is to be explored. The spacecraft (12) functions as a probe carrier using the support and deployment module (14), and near the planet (19), it functions as an orbiting communications satellite (12) that relays data and commands between the aerocraft (16) and Earth. The support and deployment module (14) secures the probes (16) and is interposed between the spacecraft (12) and the launch vehicle (11). The support and deployment module (14) passes all structural loads due to the added mass of the aerocraft (16) directly to the launch vehicle (11), which is designed (nominally) for the total launch mass, and does not impose any structural loads on the satellite (12).

Abstract: A launch vehicle payload housing and assembly joint for a launch vehicle, the housing comprising a shroud having first and second shell sections, and a frusto-conical payload adapter mounted in the shroud. The shell sections are connected together to form a housing. A peripherally extending explosive seam and a pair of longitudinally extending explosive seams hold the shell sections together. Each seam comprises a plurality of seam elements which include a pair of brackets attached to opposed ends of those parts of the shell abutting the longitudinally and peripherally extending seams. The brackets are spaced from one another to define a cavity. The cavity accommodates a deformable tube which houses explosive material in the form of an explosive cord. Detonation of the explosive material causes the shell sections to separate from one another.

Abstract: The orbital launch system is a three stage vehicle to launch orbital payloads. The system uses a turbofan powered aircraft as the first stage with an aerospacecraft attached by an underling aerospacecraft pylon at an aircraft engine mount for carriage. The aerospacecraft is the second stage and is powered by an ejector ramjet engine. The aerospacecraft has a cargo bay with cargo bay doors in its midsection. A booster rocket with payload is launched from the cargo bay by use of an ejection system. Normally the payload is mounted on a rocket booster to be placed in the proper orbit. The orbital launch system may also have a parachute drop recovery system to recover the booster rocket after it deorbits.

Abstract: A nose landing gear assembly for an airplane which can be launched with catapult assistance. The landing gear assembly includes a nose strut, upper drag link, lower drag link, launch bar and launch bar actuator. When the nose shut is in the extended position, the upper drag link, lower drag link and launch bar form a direct load path between the catapult shuttle and the airplane thereby avoiding subjecting the nose strut to loads reacted from the shuttle. The nose strut, launch bar, launch bar actuator and airplane fuselage form a first four bar linkage. Furthermore, the nose strut, upper drag link, lower drag link and airplane fuselage form a second four bar linkage such that during retraction of the nose strut, the launch bar, launch bar linkage, upper drag link and lower drag link are caused to move up and into the airplane wheel well.

Abstract: A spacecraft includes heat-radiating panels. Heat-generating boxes such as TWTs are mounted on shelves which are inside the spacecraft, where they cannot radiate to space. The shelves are coupled by bent heat pipes to the exterior radiating panels.

Abstract: A launch system for an unmanned aerial vehicle (UAV) that is contained in a portable trailer where all the components of the launch platform can be unfolded and/or attached to each other by hand using removable pins attached to the platform by lanyards. The platform includes launch extension mechanisms that insure a proper launch angle. Wing rails that fold into and are pinned into position to support the UAV before a launch. The launcher also includes a crane that provides a fixed position lifting crank and a movable boom with a lifting cable that is not exposed to getting tangled during movements of the boom when positioning the UAV on the launcher. The trailer has an air compressor and air tanks, and a foot operated release valve that supplies compressed air for a piston based launch mechanism that is controlled by the pilot. The system includes enclosed compartments that are capable of storing components for several vehicles.

Abstract: A special set of elliptical satellite orbits are described which allow preferential coverage of one parameter over another. According to a first modification, the orbits are retrograde, and preferentially cover one geographical location or time of day as compared with another. A second modification uses prograde orbits and allows the apogee of the orbit to be offset a constant amount with respect to the sun, to thereby cover a different time of day relative to the others. According to a special preferred mode of the invention, the apogee is always pointing towards the sun.

Abstract: A reusable single-stage-to-orbit spacecraft and a reusable launch assist platform provide a new system for space transportation. The platform has a frame with a cradle for supporting the spacecraft. Rocket engines attached to the launch assist platform propel the launch assist platform and the spacecraft substantially vertically through the atmosphere for release of the spacecraft. The launch assist platform returns to a predetermined landing site in a power-controlled, vertical descent.The spacecraft is in the shape of a cone having a large, rounded base with a primary load-bearing structure substantially perpendicular to the base. The spacecraft reenters the atmosphere in a base-first reentry, and is slowed and guided to a landing site by using a rocket engine in the base. The spacecraft lands base first on a resilient landing device.

Abstract: A submarine launched unmanned aerial vehicle comprises an elongated genery cylindrically-shaped body. Tail fins are stored in the body and are self-deployable to extend outwardly from the body. A booster motor is fixed to an aft end of the body and is self-releasable from the body. A propeller is disposed at the aft end of the body and is self-deployable to an exposed position at the aft end of the body after release of the booster motor. A propulsion motor is mounted in the body and is operative to drive the propeller. Rotors are stored in the body and are self-deployable to an exposed position wherein the rotors provide lift to the vehicle.

Abstract: A mechanical regulation system for controlling tow line payout between the aerobody and a towing vehicle. The system comprises a housing, a nonrotating spool, and a tow line wound around the spool that is coupled between the aerobody and the vehicle. The regulation portion of the present system comprises a rotatable wedge-shaped tube, having the tow line wrapped around it. A rotatable mechanical regulator is slidably coupled to the wedge-shaped tube. The regulator is adapted to rotate with the tube and move transversely along the length of the tube as the tow line is removed from the spool. A brake mechanism is provided as part of the regulator, and a brake drum is disposed adjacent the periphery of the regulator that is contacted by the brake mechanism.

Abstract: A launching and regulation system that incorporates an expendable towing and deployment mechanism for use with a towed aerobody that provides for launching and controlled tow line payout between the towed aerobody and a towing vehicle. The system comprises a housing, a nonrotating spool disposed in the housing, and a tow line wound around the spool that is coupled between the aerobody and the vehicle. The tow line preferably comprises a photonic, fiber optic, link. The launching mechanism comprises a plurality of impulse cartridges for deploying the aerobody and severing the tow line at a predetermined time. A spring piston is disposed inside a wedge-shaped tube that confines expanding gasses within the tube that are generated by an impulse cartridge and moves the spring piston to launch the aerobody. The regulation mechanism may comprise a mechanical system or adhesive resin system. The mechanical system comprises a rotatable wedge-shaped tube, and the tow line is wrapped around it.

Abstract: The present invention relates in general to aeronautical engineering and concerns specifically transport vehicles for transportation of liquid and loose cargoes. The invention provides an airborne vehicle capable of carrying a multiton cargo from a limited ground area. The object of the invention is accomplished due to the fact that in the airborne vehicle of the present invention the lifting aerodynamic airfoil system is made of two parts, that is, a stationary part in the form of a ring-shaped fuselage 1, consisting of aerodynamic members 2 and 3 curved spanwise, and a movable part in the form of lifting rotor units 6 arranged along the ring perimeter. A power unit of the vehicle comprises a gas-generator, propulsive units, ramjet ducts, and flywheel members interconnected through a reversible rotary-reciprocating engine-supercharger 22 and a fluid converter.

Abstract: A self-contained fueling module (10) provides the exact amount of hydrazine necessary to fuel a satellite (50) prior to launch. The fueling module (10) includes a propellant tank (14), a vacuum tank (12) and a pressurant tank (16). The propellant tank, filled with hydrazine, is shipped to the launch site where it is installed in the fueling module. Prior to launch, the fueling module is connected to the satellite and the hydrazine is driven with Helium pressurant into the satellite fuel tank. The Helium also pressurizes the satellite fuel tank to flight pressure. Any remaining fuel is evacuated from the connections (45) and fuel transfer lines (42) with the vacuum tank. Personnel do not have to wear self-contained atmospheric pressurized environment (SCAPE) suits because there is no risk of hydrazine exposure.

Abstract: A method of launching a two stage vehicle and a trajectory for use with a two stage vehicle which allows recovery of both stages at the launch site. This is accomplished by launching the first stage completely vertically so that on burnout the first stage is positioned directly above the recovery site. In order to get maximum benefit from launching the stage vertically gravitational losses are minimized by a first stage thrust to weight ratio of 1.6. The high thrust to weight ratio results in burnout at approximately 100,000 feet altitude within the atmosphere. Therefore the vehicle employs engines which produce at altitude approximately 15 percent of the sea level thrust of the first stage and consume the last 5 percent of propellant over a time period of 40 seconds. Staging is accomplished at 200,000 feet altitude. The second stage employs uprated RL-10 engines and has a thrust to weight ration of 1.45 and can achieve orbit with a velocity change of approximately 24,500 feet per second.

Abstract: Systems and methods that employ a spin-stabilized spacecraft in combination with a support and deployment module to carry a plurality of probes containing scientific instruments that are to enter a planet's atmosphere and/or are to be landed on a planet that is to be explored. The spacecraft functions as a probe carrier using the support and deployment module, and near the planet, it functions as an orbiting communications satellite that relays data and commands between the aerocraft and Earth. The support and deployment module secures the probes and is interposed between the spacecraft and the launch vehicle, and passes all structural loads due to the added mass of the aerocraft directly to the launch vehicle. The structural loads on the satellite are essentially the same as if the satellite was launched by itself with no added structure attached thereto. Therefore, existing spin-stabilized satellites may be used as probe carriers without structural redesign.

Abstract: A high altitude launch platform, used to launch a payload into earth orbit, is part of a payload launch system having a payload launching rocket with an engine carried by the high altitude launch platform. A first amount of fuel, substantially less than the capacity of the fuel tanks, is provided to the fuel tanks of the engines for the launch platform while the launch platform is on the ground. The launch platform is flown to a first altitude and the fuel tanks are provided with a second amount of fuel while the high altitude launch platform is at the first altitude. The addition of the second amount of fuel is sufficient to allow the payload to be launched into orbit.