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.

Abstract: A vehicle will serve as a road vehicle, as well as can be flown. The vehicle has a fuselage and a wing with a fixed span. The aspect ratio is low, allowing the vehicle to be operated on a normal roadway. An upper winglet extends upward from each side edge of the wing. A lower winglet extends downward from each side edge. Wheels mount to the lower edges of the lower winglets.

Abstract: A vehicle will serve as a road vehicle, as well as can be flown. The vehicle has a fuselage and a wing with a fixed span. The aspect ratio is low, allowing the vehicle to be operated on a normal roadway. An upper winglet extends upward from each side edge of the wing. A lower winglet extends downward from each side edge. Wheels mount to the lower edges of the lower winglets.

Abstract: A reusable flyback satellite system comprises a refly apparatus and accelerating and positioning apparatus. The refly apparatus provides acceleration and injection into orbit, on-orbit functions services for supporting a payload, de-orbiting, re-entering and landing on a runway. The accelerating and positioning apparatus is attached to a carrier aircraft, the accelerating and positioning apparatus releaseably supporting the refly apparatus. The carrier aircraft positions the accelerating and positioning apparatus at a desired first position wherein the accelerating and positioning apparatus is detached from the carrier aircraft. Thereafter, the accelerating and positioning apparatus positions the refly apparatus to a second position wherein the refly apparatus is detachable from the accelerating and positioning apparatus. The second position is such that the refly apparatus can achieve a desired orbit.

Abstract: A space transport architecture (STA) for robotic operations on a planet. The STA comprises and an earth launch vehicle (ELV) (10), adapted to carry a space transfer vehicle (STV) (15) and associated payloads (17) into low earth orbit (LEO). The space transfer vehicle (STV) (15), carried by the ELV (10), is adapted to carry associated payloads from LEO in the planetary orbit and to dispense these payloads (17) from planetary orbit for landing in the locus of at least one planetary exploration site. At least one planetary lander (17) is carried by the STV. The lander (17) is adapted to carry a plurality of robotic operational platforms (58) and deploy these platforms in the locus of the exploration site. A plurality of robotic operational platforms (58) is carried by each of the landers (17).

Abstract: A solar energy concentrator assembly comprises flexible polymeric sheet which carries an integral optical element in the form of a Fresnel lens for concentrating a substantial amount of incoming solar radiation on a desired location on the earth's surface. Lofting elements such as propeller driven wings is attached to the sheet for providing aerodynamic lift thereto to maintain the optical element a predetermined distance above the surface of the earth. The propulsion system is powered electrically with energy derived from sunlight.

Abstract: A survivability enhancement air vehicle adapted to be air launched from a launching aircraft has a fuselage with a top half and a bottom half separable from the top half. A first stage rocket constitutes the bottom half of the fuselage and a second stage rocket and associated avionics constitute the top half of the fuselage. Gull wings are rotatably mounted on the top half of the fuselage for rotation from a stowed position next adjacent the top half to an extended position substantially 90 degrees toward the bottom half upon being air launched. A separation device in the fuselage separates and drops the bottom half of the fuselage from the top half upon burnout of the first stage rocket. A control system in the top half of the fuselage controls the air vehicle in flight either from the launching aircraft or autonomously, whereby the air vehicle may be used to protect the launching aircraft in a hostile environment.

Abstract: A foldable, multisectional air foil with apparatus enabling it to fold or curl up or down about the body of a craft; and to a system to maintain air foil rigidity during flight. This system includes three separate assemblages which may be used in combination: sliding spar, continuous strap and cable pressure. The former includes apparatus for a sliding segmented spar within a segmented spar built into the air foil sections, which allows the air foil to fold when the joints of both spars are aligned yet provides sufficient rigidity when said joints are offset. The continuous strap assemblage provides for the air foil to be encircled by continuous yet segmented straps, each section of which contains hinging and locking mechanisms allowing the air foil sections to fold and unfold yet which--when locked into place as a continuous strap--provide structural strength to the air foil whole.

Abstract: An aircraft includes a cockpit permanently connected to a fuselage base. At least one fuselage segment is detachably mounted to the support. In case of an imminent crash the segment is detachable from the remainder of the aircraft and can float to safety after being detached by having at least one parachute and an airbag secured to the segment.

Abstract: To reduce the time required to build spacecraft, and to reduce costs, the spacecraft are members of a set of spacecraft. Each member has the same structural members, such as panels, but different members of the set are elongated by multiples of an increment such as five inches. The structural panels of larger members of the set are elongated in the longitudinal direction, to provide more surface area for mounting payload, and to provide more heat rejection surface. The propellant tank(s), which may be fuel and oxidizer tanks, are spherical in the shortest members of the set, and are increased in length by addition of cylindrical sections, to provide greater volume in larger members to thereby provide longer operating life. Similarly, the solar panels, heat pipes and the like may be elongated.

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 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 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.

Abstract: A twin-hull seaplane comprising two hulls spaced apart by a suitable distance, a cabin provided on the hulls integrally therewith, a front wing and a rear wing provided on the cabin and having a length not greater than the width of assembly of the two hulls or foldable to a length not greater than the width, aero-propulsion engined mounted on the front wing or the cabin, and a rudder attached to the rear wing. Each of the hulls is provided with hydro-propulsion means at a rear portion thereof.

Abstract: A near surface vehicle including a vehicle body including a nose section having a canard with lift and pitch control. The vehicle body including a cockpit or cabin with a main wing mounted adjacent or above the cabin and including ailerons for lift and roll control. The vehicle body further including a tail section having a tail surface and a thrust air fan for providing air for lift and propulsion of the vehicle. The vehicle including an air diverter for deflecting air into a controllable lift area for initial lift and air deflectors or rudders for controlling vehicle direction and vehicle reverse thrust.

Abstract: An unmanned air vehicle system which is intended for launch from a platform such as an aircraft or a ship and to follow other than a ballistic trajectory includes a pair of substantially similar air vehicles in a tandem relationship. A unitary tubular airframe is provided coextensive with both air vehicles. The nose of a second air vehicle is nested in the tail member of a first air vehicle. A rocket booster is mounted in the tail of the second air vehicle and ignited for launch of both air vehicles as a unit. Thereafter, a pyrotechnic separating mechanism is actuated for bisecting the tubular airframe intermediate the tail member of the first air vehicle and the nose of the second air vehicle. Following separation, each air vehicle has a gas turbine engine which is ignited for powering its associated air vehicle to its destination.

Abstract: A multi-use launch system comprises a plurality of different modules releasably securable together into a plurality of different possible launch configurations. The modules include an at least partially expendable, unmanned first stage unit which is capable of single-stage-to-orbit operations on its own carrying internal or external payloads, or as part of a multi-stage-to-orbit system for higher payload capacity launches. The first stage unit is demountably securable to other first stage units, unpowered cargo-carrying units, and/or manned space vehicles. The first stage unit may be completely expendable after launch.

Abstract: A helicar is provided which consists of a body being in the shape of an automobile, a plurality of wheels depending from the body for supporting the body on the ground, a top rotor assembly operatively secured to the body, a rear rotor assembly operatively secured to the body and a mechanism for operating the top rotor assembly and the rear rotor assembly in a helicopter mode for travel through the air and for operating the wheels in an automobile mode for travel on the ground.

Abstract: This invention involves a simple but radical approach to airplane design. Many advantages and benefits result therefrom including improved flight efficiency, better handling and control response, less tail area required, increased safety, increased utility of airplanes, and reduced ground handling and hangar facility requirements. A solution is provided for the inherent problems of combining the utility of a surface conveyance with the freedom and swiftness of flight.

Abstract: An aircraft comprises a vehicle (1) suspended in flight by a steering control rod (68) pivotally mounted to the body of the vehicle and having outer ends (12, 14) connected to the lower ends of load suspension lines (3, 5, 6) connected at their upper ends to a flexible wing portion (2) of a ram air inflatable type of airfoil canopy. Steering of the aircraft is by pivotal movement of control rod (68) to manipulate the load suspension lines and thereby the canopy surfaces. The aircraft may be radio controlled by a radio receiver (112) in the vehicle body for operating the speed of a drive motor (36) for driving a propeller (38) and a steering drive motor (98) coupled to the control rod (68) by a suitable linkage system. Battery pack (104) is removably mounted in the vehicle body for providing power to the receiver and motors therein. The radio controlled aircraft is controlled by a remote transmitter which controls the steering and speed of the aircraft.

Abstract: An improved launch vehicle having a central vehicle stack with an upper stage, a lower stage and payload, and having one or more additional parallel burning stages burning in parallel with the lower stage. Interstage propellant transfer is provided from the shorter to longer burning parallel stages. The additional parallel stages are preferably of substantially the same, or greater, length as the central lower stage. The central lower stage and parallel additional stages may preferably have substantially the same thrust capabilities at liftoff and sufficient thrust to provide redundancy and hence increased reliability, in the event of loss of one of the parallel stages.

Abstract: A hybrid electric vehicle (10) capable of ground travel and air travel is described. The vehicle provides for movement over the ground by wheel motors (20) mounted at each of four ground engaging wheels (14 and 16). The wheel motors are supplied with electric power by a battery pack (24) or an electric generator (32) powered by a combustion engine (22). The combustion engine is also geared to vertically oriented ducted fans (40) and a horizontally oriented ducted fan or propeller (76) for providing the vehicle with the capability of travel through the air. Pressure jets (62), supplied with compressed air from a compressor (66) driven by the combustion engine, augment the lift of the ducted fans and provide steering for the vehicle. The vehicle can also be provided with photo-electric cells (82) for supplying a portion of the electric power for the vehicle.

Abstract: An improved multistage launch vehicle provides a redundant stage wherein, for N stages in total, N-1 stages will suffice to lift the payload into earth orbit. At least two of the N stages are ignited in parallel at lift off. Interstage coupling and payload stage coupling mechanisms allow the successful completion of the mission and lifting of the payload into orbit irrespective failure of a stage. Interstage propellant transfer is provided to increase efficiency of the parallel stages and allow the increased thrust of parallel ignition at lift off.

Abstract: A first stage earth to low orbit shuttle having mixed-mode propulsion and dual fuel rocket engines. A cargo bay is designed to receive a second stage dart vehicle capable of attaining geosynchronous orbit, deep space and lunar capabilities from launch at low earth orbit from the space shuttle. Upon return from geosynchronous orbit, the dart vehicle would reenter the atmosphere, and rebound toward an outward trajectory. At this point, projectiles would be launched for reentry and the dart vehicle can deviate cross range to a landing site.

Abstract: A recreational vehicle combines a flying vehicle and a motorized surface vehicle, such as a boat, car, or truck or snowmobile. The flying vehicle is tethered to the surface vehicle by four rods, each of which is rotatably connected to the flying vehicle and surface vehicle, so that the angle of attack of the flying vehicle relative to the surface vehicle remains constant or decreases, depending only on altitude. On/off, throttling, and steering of the motorized surface vehicle are controlled by the pilot of the flying vehicle. The flaps of the flying vehicle are automatically lowered for landing to increase drag and lower the stall speed and raised following take-off to reduce drag. Ailerons are automatically controlled to roll the flying vehicle during turns.

Abstract: A hybrid aircraft with a large non-rotating balloon chamber containing a lighter-than-air gas which provides a large static lifting force having a magnitude substantially greater than the weight of the aircraft with a support structure system which is substantially longer in length than in width which is encased by the balloon chamber the support structure system having two ends which protrude from the balloon chamber at opposite sides along the center line of the balloon chamber with a rotatable rotor frame suspended from the ends of the support structure system about the non-rotating balloon chamber. The craft has a plurality of blade airfoils connected to the rotor frame and oriented radially relative to the balloon chamber and which the angle of attack of each blade can be varied. A thrust means is mounted at or near the outboard end of the blade airfoils.

Abstract: The device comprises an arch-like structure (3), shaped similar to a cage, which can be fixed to the motorcycle (1), essentially to its frame and sides; a parafoil sail (5), which can be mounted at the top of the cage, the sail ends being lowerable by a pedal or handle control; a propeller propulsion system (8) mounted at the rear of the motorcycle on the arch-like structure; and a clutching and declutching mechanism which, on control, drives either the driving wheel or the propeller.

Abstract: A method and system for supporting an airborne vehicle in space over a predetermined location and for an extensive period, comprises coupling the airborne vehicle by cables to a plurality of unmanned aircraft each having its own propulsion system; controlling the unmanned aircraft to fly in circular orbits at equally-spaced angles around the airborne vehicle while coupled to the airborne vehicle, to tension the cables and thereby to support the airborne vehicle in space over the predetermined location; and supplying the unmanned aircraft with energy from an external source to maintain the unmanned aircraft in flight over an extended or indefinite period of time.

Abstract: A vehicle chassis is supported on front and rear wheels for road and runway engagement. A propeller assembly is disposed between the front and rear wheels and faces the rear. Wing assemblies on opposite sides of the chassis are foldable along the sides of the chassis to form side panels for the road form of the vehicle. A tail assembly on the chassis is shiftable forwardly and rearwardly and has a pair of vertical stabilizers connected together at the top by a horizontal laterally extending stabilizer. A pressure regulated retractable stabilizing wheel is provided between the front and rear wheels and is arranged to engage a runway and provide stabilizing functions for take off and landing.

Abstract: A heavier-than-air craft having a cylindrical external configuration comprising a single annular airfoil forming a circumferential lift wing. This fixed circular wing is surrounded by a circular fuselage of substantially the same diameter, closely spaced axially above and below the outer periphery of the annular airfoil, to allow radial air flow over and under substantially the full circumference of the airfoil. The radial air flow is induced through an axial opening in the center of one surface of the circular fuselage by an engine driven propeller, fan or jet effect.

Abstract: Disclosed is a woven fabric having a plurality of fabric layers which are integrated through combined portions formed by interlacing warps or wefts of one of adjacent layers of some of warps or wefts of said one layer and warps or wefts of the other layer or some of warps or wefts of said other layer with common wefts or warps, wherein a set of adjacent four layers comprises recurring structural units comprising (A) a part having one combined portion formed by intermediate two layers, (B) a first non-combined part having no combined portion, (C) a part having two combined portions formed by subsequent two layers, respectively, and (B) a second non-combined part having no combined portion. A honeycomb structure having cells of a shape of tetragons, hexagons or a combination thereof is formed among the entire layers when the multi-layer fabric is expanded. 40-100 wt. % of the fibers constituting the fabric are organic fibers which are infusible or have a melting point of at least 300.degree. C.

Abstract: The Flying Multi-Purpose Aircraft Carrier (FMPAC) comprises a runway body which is provided with V/STOL capability by at least two rotary wings, located outside the two lateral ends of the runway body in a side-by-side configuration. The rotary wings are, preferably, of a large diameter helicopter rotor blade type, and are powered by respective shaft turbine engines. A substantially flat runway platform is provided along the middle portion of the runway body, between the left and right helicopter rotary wings. The runway platform is located as low as possible, in order to secure flight stability of the composite aircraft. The top surface of the runway platform has a substantially flat and rectangular-like shape defining a conventional runway, and may allow a fixed wing CA to take-off from or to land on it, during flight of the FMPAC, allowing the pilot of the CA to operate his aircraft with a considerable margin of error.

Abstract: A multi stage high-altitude data acquisition system comprising a first stage manned lighter-than-air, engine propelled aircraft and a second stage air-buoyant vehicle of stratospheric altitude attaining capability statically sustainable aloft by a sufficient quantity of lighter-than-air gas contained within an expandable envelope balloon to carry the vehicle to a stratospheric float altitude and transportable from ground level to a tropospheric launching altitude by the first stage aircraft from which the air buoyant vehicle and its partially expanded gas containing envelope is releasable at the launching level while the first stage aircraft is established in a flight condition of substantially zero airspeed.

Abstract: A fixed wing aircraft that can be converted to an automotive vehicle, comprising a generally rectangular planform fuselage having four wheels as in conventional automobile practice, and a telescopic wing which retracts into a housing in the roof of the fuselage. Telescopic horizontal and vertical stabilizers are provided at the rear end of the fuselage, as well as a retractable pusher propeller that is driven by an engine mounted on the front end of the fuselage. Both the propeller and the rear wheels are connected by a transmission box to the engine, so that either can be driven to operate the vehicle as an aircraft or as an automobile. On take-off, the rear wheels are partially retracted so as to place the aircraft at a proper angle of attack at the same time that the elevators are raised by pulling back on the control wheel. The control wheel is also connected to both the front wheels and the ailerons, and when turned 90.degree.

Abstract: A heli-hover amphibious craft which includes a main hover craft fuselage body structure including a single hull provided with a deck. The hull is defined by a compartmental under base cavity extending downward with divisional and perimeter walls formed by air cushion containing structure for containing suspension air. The fuselage body is provided with at least one built-in duct extending through said deck to said base cavity. At least one deck mounted fan is provided for delivering pressurized air through the duct. A superstructure is attached to the fuselage body. At least one horizontally rotating heli-rotor assembly is supported well above the deck by the superstructure, with the heli-rotor assembly being driven by a substantially vertically fixed shaft. An anti-torque device provided on an aft portion of the fuselage body. A drive mechanism is operatively connected to the heli-rotor assembly and the anti-torque device for propelling the craft.

Abstract: A coherent fire-resisting flexible sheet material for aerospace applications is provided consisting of a layer of ceramic fibers embedded in a silicone rubber compound. The ceramic fibers may be in the form of a plain woven fabric of monofilament fibers of alumino-boro-silicate and the silicone rubber compound can be a curable non-foaming methylphenyl silicone compound. In production, the silicone compound is applied to the fabric as a thixotropic paste in sufficient quantity to entirely cover and impregnate the fabric and is forced through the interstices of the fabric by the application of pressure. The coated and impregnated fabric is then placed in an oven to cure the silicone compound.

Abstract: A rescue craft includes a self-propelled car or elevator type of flying machine for rescuing persons from high-rise buildings, during fires, or other emergencies. The craft is powered by fan-jet engines capable of lifting the unit in vertical take-offs. A cable attached to a ground structure is used to control the craft and facilitate descent to ground level. An internal guidance system provides 360.degree. maneuverability around the cable and facilitates docking against the sides of buildings, etc. The ground structure comprises a flat-bed tractor/trailer equipped to transport the craft to the scene of an emergency. The ground structure is fully self-contained with diesel power, a winch for the cable, lighting, refueling capability, and is fully ballasted and outrigged and capable of launching and receiving the rescue craft.

Abstract: An aerial aircraft carrier is disclosed having a first and a second shuttlecraft that have a cantilever fluselage extending between the first and second shuttlecraft. The cantilever fuselage is disposed at both ends within a fuselage housing that depends from the under-carriage of the first (lead) and second (aft) shuttlecraft, the cantilever fuselage forming a longitudinal member therebetween. A means for elevating a plurality of aerodynamically stable platforms, (wing assemblies), is affixed to the cantilever fuselage. The wing assemblies each have a wing span member attached thereto, with control surfaces, for stabilizing an aircraft (a payload) that is secured in a mount assembly.

Abstract: A vehicle usable in the air, on water, or on ground is described. Outer wing portions are connected to a central portion by a mechanism which allows the outer wing portions to pivot about first axes for placing the outer wing portions in stored positions. The outer wing portions are also rotatable about a second axis for placing them in positions whereby they are useful as sails for driving the vehicle without the use of an engine. The wheels are capable of being pivoted to non-positions.

Abstract: A hybrid wing assembly is made up of a load supporting center frame with laterally outwardly extending, articulated, wing sections. A parafoil is attached to the wing sections by flexible lines in flight, and rigid rods hold the parafoil in spaced relation to the wing at rest. Control lines extend from the parafoil to the user for controlling the assembly.

Abstract: A ground-air-water craft comprises a fuselage body with a passenger compartment mounted thereon, a box-type main wing connected to the fuselage and extending outwardly on both sides thereof, the main wing comprising an upper wing and a lower wing which are substantially horizontal and which have a total wing span in the range of 5 to 10 feet, as well as a right side member and a left side member, each side member extending substantially vertically and connected between the lateral ends of the upper and lower wings on the respective right and left sides of the craft. The craft also comprises a control or canard wing connected to the fuselage and extending outwardly on both sides of the fuselage with a wing span no greater than 10 feet.

Abstract: An end plate is provided for a ram-wing boat having two airfoils (7-8) and (7a-8a), in the form of ailettes, disposed at a distance from each other and in tandem at approximately the same height, which airfoils are connected with each other at their outer ends by flat end plates (1). Each end plate (1) is configured as a hollow body with an essentially trapezoidal cross section, and consists of upper chord (2) and lower chord (3) connected by planking (4 and 5) along the length thereof. To complete the static assemblage, ribs (6) which divide the hollow body into compartments (9) are disposed at a distance from each other in the hollow space of the end plate (1).

Abstract: A fixed wing aircraft that can be converted to an automotive vehicle, comprising a generally rectangular planform fuselage having four wheels as in conventional automobile practice, and a telescopic wing which retracts into a housing in the roof of the fuselage. Telescopic horizontal and vertical stabilizers are provided at the rear end of the fuselage, as well as a retractable pusher propeller that is driven by an engine mounted on the front end of the fuselage. Both the propeller and the rear wheels are connected by a transmission box to the engine, so that either can be driven to operate the vehicle as an aircraft or as an automobile. On take-off, the rear wheels are partially retracted so as to place the aircraft at a proper angle of attack at the same time that the elevators are raised by pulling back on the control wheel. The control wheel is also connected to both the front wheels and the ailerons, and when turned 90.degree.

Abstract: A convertible airplane to automobile and visa versa, having a fuselage and three wings, including a forward canard wing, a foldable main wing and a secondary lift wing. The foldable wing is capable of folding to a size for safely driving the automobile on a roadway. All wings are used as ground effect airfoils for roadway use.

Abstract: A multi-media craft particularly designed and constructed for efficient and economical utilization on land, water and in the air and comprising a light weight body constructed in modular form for economy and power by a removable lightweight engine of the motorcycle type for fuel efficiency and ease of maintenance. The craft is provided with forward and rearward sections constructed in a manner for variable in-flight or in-use alteration or molding thereof for achieving the optimum planar or contour design for the craft as required during variable fluid conditions when airborne, thus providing efficient and safe flying operation for either an unskilled or skilled operator.

Abstract: An airborne craft with at least four propellers arranged in a front propeller pair and a rear propeller pair having substantial vertical or forwardly inclined axes has hydraulic motors which drive the propellers. A pumping device supplies two pairs of separated flows to the motors. One pair of the flows has fixed delivery and equal flow quantities per revolution of the pump while the other pair has variable flow-rates but the flow quantities of both flows of the variable flow pair are also equal relatively to each other. One of the flow pairs drives the front propellers at equal speeds and the other pair of flows drives the rear propellers with equal speeds. But the variability of the rates of flow of one of the pairs of flows is utilized to let one of the pairs run with a different rotary velocity of the propellers than the other pair.

Abstract: An aircraft carrier (1) is provided that can be moved by the thrust of the aircraft (2) positioned on the carrier (1). The carrier (1) comprises a steering system that is powered by the nosewheel (9) of the aircraft (2).

Abstract: An aerospace vehicle having multiple propulsion systems on a relatively rotatable flying wing capable of takeoff and subsequent landing with intermediate space flight in the manner of a conventional aircraft and rocket, respectively, comprising an elongated wing member having internal passenger and crew, cargo and fuel storage compartments. A plurality of propulsion systems are distributed about the wing member for providing thrust and aerodynamic control. The vehicle also includes rotating means for controlling the direction of the thrust of the propulsion systems relative to the longitudinal axis of the wing whereby to rotate the wing member relative to the direction of flight. The vehicle takes off and lands with the longitudinal wing axis being transverse to the direction of thrust and therefore to the flight direction in a manner similar to that of conventional aircraft.

Abstract: A space transporation system comprises several different modular units usable in a plurality of different configurations for different payloads and space missions. The units include a first stage unit for providing primary propulsive force during launch, a payload carrying unit, which may be an orbital vehicle or simple payload canister, and an auxiliary propulsion unit for providing additional power either during launch or space flight. The units are all demountably securable together, and preferably all include aerodymanic devices such as fixed or swing wings for a controlled return to Earth. The first stage unit can act either as a single-stage-to-orbit vehicle carrying internal or external payload, or as the first stage of a multiple stage launch configuration including a payload unit and auxiliary propulsion units.

Abstract: A recovery system for decelerating/stabilizing and protecting space vehicles, boosters, astronauts, equipment and like payloads, including a paracanopy defined by a frusto-conical flexible uninflated skin forming a decelerator/stabilizer surface having a small inflated torus at it leading end and a larger trailing torus at its trailing end with an inflated annular protective sheath therebetween protecting the payload housed therein, duct means between the toruses and the annular sheath for forming a fluidically rigidified frame, and the fluidically rigidified frame maintaining the flexible skin in taut though uninflated condition during entry and recovery, The paracanopy further can include an inflated buoyant section for recovery at sea, and depending upon the payload to be recovered, the paracanopy can be deployed as a single structure from one end of the payload or from opposite ends of the payload as two separate cooperative structures.

Abstract: A lightweight, low cost, powered launch vehicle for carrying a hang glider aloft and releasing the glider for free flight provides an integral glider support frame for positioning the glider in flight-ready configuration and a selectively actuatable release device accessible to the glider operator for separation from the vehicle at a desired altitude. The support frame positions the glider so that the wing of the glider provides added lift to the launch vehicle during combined flight.

Abstract: This invention is directed toward providing a transatmospheric launch system that is essentially totally reusable, provides wide flexibility in choice of orbit, and may be launched quickly on short notice. The system of the invention is a two-stage horizontal takeoff and landing system. An orbiter vehicle (50) is integrated into the underside of an aircraft (2). Aircraft (2) has a cavity (4) opening aftwardly and downwardly to receive vehicle (50). Vehicle (50) and aircraft (2) are releasably connected by struts (30, 32). Aircraft (2) and vehicle (50) proceed to staging conditions under air breathing and then rocket power. Rocket engine (22) of aircraft (2) is throttled to produce a thrust differential with rocket engine (66) of vehicle (50). This differential causes vehicle (50) to automatically pivot away from aircraft (2) on struts (30, 32). After pivoting out of cavity (4), vehicle (50) is disengaged from struts (30, 32) and proceeds on its own to orbit. Aircraft (2) makes a conventional landing.