Abstract: An aerospace system, which comprises a carrier aircraft, a launch vehicle and a payload.

Abstract: The invention concerns a launch vehicle comprising a shroud (1a, 5a) supporting auxiliary propellers (2, 3) applying in operation excess flow of stresses to the shroud (1a, 5a), said device comprising means for coupling the payload (4) with the launch vehicle shroud. The invention is characterized in that the coupling means are designed to ensure a mechanical coupling between the payload (4) and the shroud along the direction of the launch vehicle longitudinal axis (X), and to cause them to be disengaged along radial and tangential directions. The invention is useful for neutralizing the effects on the payload of excess stresses applied on the launch vehicle shroud by the auxiliary propellers (2, 3).

Abstract: The present invention relates to a vehicle for land and air transport and, more specifically, to a vertical take-off and landing vehicle for land, water and air transport which is submersible and utilizes compressed air to lift and propel said vehicle during travel. The land-based drive train and the aviatic air compression system are powered mechanically by the vehicle's engine or electrically by rechargeable battery banks and generators or a combination thereof thereby effectively reducing the present invention's reliance upon fossil fuel sources.

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: An improved VTOL aircraft or flying car mechanism that utilizes counter-rotating blades (18) spinning inside a duct (14) causing varying speeds and volumes of atmosphere to pass across an exposed plurality of wing shaped lift generating airfoils, referred to as sucked flaps (36), at an opening in that duct (70). The volumes of atmosphere will then pass through to a lift amplifying, turbulence reducing, radial, spiral airflow generator (68) and then into thrust vector airfoils (26), which will then pass through the duct (70) again as it forms a circular path (72) back to the sucked flaps (36), where it is then re-circulated. The air pressure flowing over the top of the airfoils is reduced relative to the air pressure below the airfoils causing relatively large amounts of lift to be generated to overcome the force of gravity.

Abstract: A flying vehicle having a pair of counter rotating propeller blades which provide lift for the vehicle when the vehicle is in a flight mode of operation. The counter rotating blades have in flight adjustable pitch and are connected to a control and steering system in the cockpit of the vehicle. A gas turbine engine located in the aft section of the vehicle is connected through a drive shaft and transmission to the counter rotating propeller blades When the vehicle transitions to the flight mode, the user has aircraft controls available in the cockpit to make the transitions from a driver to a pilot in a short time period. Yaw pedals located on the floor board of the cockpit as well as a pitch control handle and the steering wheel allow the user to steer and control the altitude of the vehicle when the vehicle is in the flight mode.

Abstract: A reusable spacecraft system having two substantially identically reusable return flight space vehicles, one of which is preferably a booster and the other an orbiter, each of which have identical flight control and propulsion systems and have identical but selectably installable components, such as thermal protection disposed on the orbiter but not on the booster. Each vehicle further includes identical payload bays for receiving mission specific payloads, that may be for example, a propellant tankage payload for the booster and a manned mission payload for the orbiter. The use of identical booster and orbiter vehicles reduces costs of development, production and reusable missions.

Abstract: A flying vehicle having a pair of counter rotating propeller blades which provide lift for the vehicle when the vehicle is in a flight mode of operation. The counter rotating blades have in flight adjustable pitch and are connected to a control and steering system in the cockpit of the vehicle. A gas turbine engine located in the aft section of the vehicle is connected through a drive shaft and transmission to the counter rotating propeller blades When the vehicle transitions to the flight mode, the user has aircraft controls available in the cockpit to make the transitions from a driver to a pilot in a short time period. Yaw pedals located on the floor board of the cockpit as well as a pitch control handle and the steering wheel allow the user to steer and control the altitude of the vehicle when the vehicle is in the flight mode.

Abstract: A configurable space launch system of multiple different vehicle configurations that use a common reusable spaceplane and cost effective external tanks is presented. Each vehicle configuration in the system incorporates one or more reusable spaceplanes and most or all ascent propellant in multiple releasable external tanks. The flight trajectory of each vehicle has multiple in-flight staging points to increase vehicle performance efficiency. The system is governed and configured by a unique set of eight prescripts that together minimize launch costs.

Abstract: A system and method for wind-powered flight, comprising a low-speed, high-drag leading aircraft such as a kite, tethered to a low-speed, low-drag trailing aircraft, such as a glider. The leading aircraft is launched, and when the leading aircraft ascends into winds which are significantly greater than winds at the ground level and the takeoff velocity of the trailing aircraft, the leading aircraft begins to tow the trailing aircraft. The trailing aircraft becomes airborne and can be flown at a low air speed to maintain a constant drag on the leading aircraft, which in turn provides thrust to maintain the trailing aircraft aloft at the lower altitude.

Abstract: A vehicle that combines the freedom and swiftness of flight with the utility of surface travel. A simple, light weight, safe and stable conveyance with positive yaw-roll coupling, special safety features, no fold wing stowage and a unique single power source. It can be built using common tools and techniques with readily available materials at a cost competitive with the family automobile.

Abstract: The reusable space launch system has a first stage vehicle or aerospacecraft, a second stage vehicle or reusable spacecraft and a third stage vehicle or reusable orbit transfercraft. All the stages have the basic aerodynamic vehicle elements of a fuselage, wings, and tail, with the incorporation of control surfaces to supply lift, stability and control. The aerospacecraft is configured to use ejector ramjet engines for powered flight and includes equipment to capture air to supplement oxidizer for the ejector ramjet engine during take-off and extreme high altitude In order to optimize aerospacecraft performance in a pull up movement to exit the sensible atmosphere, the aerospacecraft may include auxiliary ascent rocket engines. The aerospacecraft payload bay is accessed by nose load re-closable payload fairings. The reusable spacecraft is mounted on tracks on each lower side of the aerospacecraft payload bay.

Abstract: A recoverable/reusable booster stage has a restartable center liquid-fueled rocket engine mounted in the aft portion of a vehicle body in alignment with the center axis of the body. The booster stage may also include two side liquid-fueled rocket engines mounted in the aft portion of the body in symmetrical relation to the center rocket engine. After booster stage separation, the center engine is restarted to direct the booster stage towards a recovery site.

Abstract: A composite aircraft comprising an aerostat containing a lighter than air gas, and a rotor assembly mounted to and below the aerostat, via an axle. The aerostat provides buoyancy to lift the weight of the aircraft plus a significant portion of the payload connected to the aircraft. The rotor assembly statically connects to the aerostat in all aspects except rotationally about the axle, and provides the remaining lift and propulsion to the aircraft and payload. The rotor assembly includes a hub, a plurality of blades, a plurality of winglets, and engine-powered propellers that provide rotational thrust to the rotor assembly. The plurality of blades and winglets have adjustable angles of attack to generate lift and forward propulsion to the aircraft. The blades mount radially from the axle and horizontally from an outboard end of the hub. The winglets mount above and below each blade. The engine-powered propellers mount to the outboard end of the hub.

Abstract: A fordable ascending/descending wing stand for a flying apparatus is disclosed. The wind stand includes a base supported on a car by a number of supporting rods. A frame is mounted on the base, provided with four propellers capable of generating a required upward and forward force to the flying apparatus. The angle of the propellers are controllable by a number of hydraulic actuators mounted on the frame. A tail helm is arranged on the frame for controlling the frying orientation of the car during flying. The base is further provided with a leftward/rightward mass center adjusting mechanism and a forward/rearward mass center adjusting mechanism for adjusting the mass center of the car during flying.

Abstract: A roadable airplane consists of a single-seat three-wheeled vehicle with wing panels hung longitudinally on the sides of the chassis for road use and attached transversely to a spar box for flight. A power train is used that enables the simultaneous powering of two rear wheels and an overhead pusher propeller for transition from road to air travel. A transaxle for a four-wheel automotive vehicle was found to be advantageously suitable for this purpose. Multiple gears and differential outputs drive the wheels, providing a normal automotive performance on the road. Multiple gears are also available to drive the propeller, thereby providing the function of variable-pitch performance using a fixed-pitch propeller. The vehicle includes a standard automotive gear shift and pedal controls for clutch, brake and accelerator operation; a novel joystick assembly is used to steer the front wheel and to control wing flaps, an elevator and a rudder.

Abstract: A fixed-wing four-to-six-seat light aircraft that can be easily converted to a roadway vehicle within minutes by a single person in the field, comprising a one-piece wing center panel with foldable wing tips on each sides. The whole wing unit is then rotatably mounted on top of the fuselage. The aircraft features a conventional front-engine-and-propeller lay-out, with a foldable tail section for convenient roadability and garageability. All the wheels are retractable in flight, and it has a long-span, high aspect-ratio wing for exceptional climb and cruise efficiency. The vehicle has a low ride-height with a low center of gravity, four wheels with independent suspension, nose-height leveling for take-off and landing, and anti-sway mechanism for good ground handling ability. Ground propulsion is by automotive-style transmission driving the rear wheels or by hydraulic motors in the all-wheel retractable version.

Abstract: A reusable rocket airplane which may be utilized to launch satellites and other payloads into space. The airplane may also be used for rapid surface to surface flight. The reusable rocket airplane may be safely supplied with oxidizer in mid-air, achieve an altitude outside the Earth's atmosphere, and return safely to be used again. The rocket airplane utilizes unique concepts to secure its gas turbine engines for high speed flight, minimize fluid spillage during mid-air oxidizer transfer, as well as employs design features advantageous to the economical building and reuse of the rocket airplane.

Abstract: A store interface for routing different types of store signal formats to multiple wing stations using pre-existing aircraft wing wiring. The store interface provides an interface between an aircraft and an associated store adapted to bidirectionally communicate with the aircraft according to one of a plurality of predetermined store signal formats. The store interface includes a store identifier that determines the type of the associated store, and an interface that bidirectionally communicates between the aircraft and the store, includinga first and second communication links that communicate with the store using either a first set of store control signals configured in accordance with a first store signal format or a second set of store control signals configured in accordance with a second store signal format.

Abstract: A roadable aircraft includes three symmetrically lateral flight surfaces, comprising a forward main wing generally centrally located relative to the fuselage or body, a rearwardly located stabilizing surface acting as an empennage support, and a rear stabilizer and elevator located at the rearward end of the empennage tail booms. The wheel or landing gear configuration is of a rhomboid pattern, with forward and rearward main wheels along the centerline of the craft, and left and right outboard wheels. The outboard wheels extend and retract individually to a limited degree to compensate for centrifugal forces in ground operations, and together in coordination with the main wheels for flight operations. The powerplant drives the rearward main wheel from one end of its output shaft, and the propeller from the opposite end of the output shaft.

Abstract: A roadable aircraft capable of flying as well as road travel. The wings of the roadable aircraft are defined by inner and outer wing panels. The outer wing panels are folded with a fold mechanism that rotates each of the outer wing panels from a substantially horizontal extended flying position to a substantially vertical extended position and then folds each of the outer panels into a direction parallel to the travel direction defined by the fuselage. An operator controlled selectable drive mechanism allows the operator to select either the propeller or drive wheel to receive power from the engine shaft.

Abstract: A wiper device has a tubular plate, a tubular element provided in the tubular plate for supporting a driven shaft, a bearing bushing in which the tubular element is introduced, the bearing bushing and the tubular element being fixed with one another in a form-locking manner.

Abstract: A retractable wing assembly for a flying vehicle includes a vane support member, a wing with vanes, and a wing extending and retracting assembly. Each vane includes a base portion and an end portion and is pivotally secured to the vane support member at its base portion. The wing extending and retracting assembly includes link members and an articulating assembly. Each link member pivotally connects two of the vanes together between the base portions and end portions of the two vanes. The articulating assembly is secured to a vehicle body and mechanically coupled to the vane support member and at least one of the vanes. The articulating assembly is manipulable to reposition the vane support member relative to the vehicle body while simultaneously spreading the end portions of the vanes apart from each other.

Abstract: The present invention is a method of earth orbit space transportation and return utilizing a reusable flyback satellite. A reusable flyback satellite is positioned to a desired release point which provides the capability of the satellite to achieve a desired orbit. The satellite is deployed from that release point. It is then injected into orbit. On-orbit function and services to a payload of the satellite are provided. The satellite is de-orbited, re-entered and landed with airplane-like functionality and utility.

Abstract: A supersonic ground vehicle having a housing configured from a pair of back-to-back symmetric housing components, and a shock-reflecting surface which extends in the direction of travel of the housing and which aerodynamically interacts with the housing to form a supersonic biplane, thereby substantially reducing aerodynamic pressure drag.

Abstract: The invention relates to a ground-effect vehicle for the rapid transport of people and/or freight, with at least one body, a drive train and ground-effect bearing surfaces, a guidance system for directional control and a drive system on the body and/or bearing surface in the form of propeller or fan drives. The aim of the invention is to provide a ground-effect vehicle which is inexpensive to build, avoids the prior art drawbacks in particular and is especially economical to operate. According to the invention, the ground-effect vehicle consists of at least one aircraft fuselage (1), the ground-effect bearing surfaces (2) are secured directly at least to parts of the existing bearing surfaces (6) of the aircraft or at least on the existing spars (12) surrounding them or secured thereto beneath the existing bearing surfaces (6) and that the drive system (4; 15; 16) has means which increase the power and/or reduce friction in the take-off and landing phases.

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: A fixed wing aircraft that can be automatically and rapidly converted to a roadway vehicle within seconds while driving in the highway, comprising a one-piece wing rotatably mounted on top of the fuselage. The aircraft features a 3-horizontal-surface design allowing good pitch stability and damping in a very short fuselage, stall-resistant feature and reduction in induced drag at cruise speed. The aircraft's wing is enlargeable with additional wing tip segments allowing boost in aspect ratio hence improving efficiency at high loads. The vehicle has low center of gravity, four wheels with independent suspension, nose-height leveling for take-off and landing, and anti-sway mechanism in order to prevent roll-over in a tight turn. Ground propulsion is by both a ducted fan and hydraulic rear wheel drive allowing rapid accleration in the roadable mode.

Abstract: A roadable helicopter according to various aspects of the present invention comprises a vehicle that drives like a conventional car in its road configuration, and converts to fly like a helicopter in its flight configuration. The operator of the helicopter only needs to press a button to initiate the conversion from one configuration to the other. To facilitate the flight configuration, the helicopter is preferably equipped with a dual, coaxial counterrotating rotor system to provide lift, propulsion, and control in the flight configuration. In the road configuration, however, the rotor system automatically folds into a rotor bay formed in the rear of the helicopter. The roadable helicopter may also include an automatic control/stability/navigation system that permits fully automatic flight.

Abstract: Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

Abstract: A launch vehicle which employs a rotor similar to a helicopter. The vehicle has a four bladed rotor which is mounted on the vehicle body. The body of the vehicle includes propellant tanks and a payload compartment contained within an integral aeroshell. Rocket engines used to propel the vehicle into earth orbit are mounted at the ends of the rotor blades. The engines are connected by propellant feed lines to a propellant transfer hub surrounding the axis of rotation of the rotor. Propellants are fed from an oxidizer tank and a fuel tank through a propellant transfer coupling to oxidizer and fuel lines which extend to the engines at the rotor blades ends. The rotor blades incorporate air foils. To operate the vehicle the vehicle is positioned on a concrete or asphalt pad and fueled with liquid oxygen and kerosene. The engine are positioned tangent to the blade paths and ignited.

Abstract: A fixed-wing four-seat light aircraft that can be easily converted to a roadway vehicle within minutes by a single person in the field, comprising a one-piece wing center panel with foldable wing tips on each sides. The whole wing unit is then rotatably mounted on top of the fuselage. The aircraft features a conventional front-engine-and-propeller lay-out, with a short fuselage for convenient roadability and garageability, with horizontal stabilizer of significant span with foldable tips for adequate flight stability. The vehicle has a low ride-height with a low center of gravity, four wheels with independent suspension, nose-height leveling for take-off and landing, and anti-sway mechanism for adequate ground handling. Ground propulsion is by automotive-style transmission driving the front wheels.

Abstract: A hybrid aircraft is taught having VTOL, R-VTOL and S-STOL capabilities. The aircraft has a lifting body hull and four wing sections arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers to the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system.

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: Tandem-engine aircraft propulsion module attachable to an aircraft fuselage and/or to the aircraft wings directly. This propulsion module contains fore-and-aft in-line engines and an intermediate fuel compartment. A subhousing of this module has engine instrumentation and controls placed for overhead introduction into an underlying aircraft fuselage cabin when the module is secured on top thereof. Propulsion modules of this invention are readily removable and replaceable for ease of inspection and maintenance, and if like-sized are mutually interchangeable. These modules are inherently economical and enable cost-effective fuselage and dry-wing construction. They also enhance flight safety, not only in comparison with single-engine aircraft but also especially as compared with off-axial twin-engine aircraft.

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: 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: Orbital launch vehicles equipped with aerodynamic lifting surfaces enabling them to be towed as gliders behind conventional aircraft, and the method of towing these launch vehicles using a flexible cable to connect them with a conventional aircraft, for placing spacecraft into low earth orbit at greatly reduced cost compared to current orbital launch systems. The lift from the aerodynamic surfaces enables the launch vehicles 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.

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.

Abstract: The present invention relates to construction of aircraft engines and has particular reference to the development of novel airborne vehicles. The invention is aimed at providing novel airborne vehicles capable of long-range nonstop flights with a specified amount of cargo, as well as at solving a complex of problems involved in extending the functional capabilities of the existing airborne vehicles. The airborne vehicle comprises a fuselage 1 carrying a suspension unit 6 held thereto and consisting of additional fuel reservoirs 7, an additional power plant 8, a landing gear 4, and an additional landing gear 18 of the suspension unit 6 which can be held to the fuselage 1 either through a hinge joint 5 or with the aid of panels.

Abstract: The spacecraft comprises a fuselage (1), a wing (2), a power unit incorporating two liquid-propellant launching rocket engines (3), two liquid-propellant boost rocket engines (4), six transverse-thrust rocket engines (5) located in the spacecraft fuselage (1) on a rotatable ring (6), solid-propellant emergency deceleration rocket engines (7), and solid-propellant additional boosting rocket engines (8), a payload compartment (9), a crew compartment (10), a tail unit with two vertical fin struts (11) a bottom tailplane (12), and a top tailplane (13). The fuselage (1) is provided with a movable center conical body (14). The spacecraft landing gear has a swivelling tail wheel (21). The crew compartment (10) is interposed between the fin struts (11) under the top tailplane (13). The spacecraft is provided with an orbital maneuvering system whose final control elements are in fact low-thrust rocket engines (22) and (23), and gyrodynes.

Abstract: A duplex complementary carrier includes a flight vehicle floating above the ground, a control system moving on the ground for controlling movement of the flight vehicle, and a connecting system connecting between the control system and the flight vehicle. When the control system is moving on the ground, the flight vehicle above the ground is able to follow movement of the control system due to the connection provided by the connecting system such that the pressure of the control system on the ground and the frictional force of the ground on the control system are reduced by the buoyancy of the flight vehicle. The flight vehicle is able to move above the ground stably by the directing and guiding effects of the control system.

Abstract: The life of a target satellite is modified, i.e., extended or terminated by docking an extension spacecraft with the target satellite to form a docked satellite-spacecraft combination. The extension spacecraft is docked with and mechanically connected to the target satellite and includes guidance, navigation, and control systems for performing the rendezvous and docking maneuvers and for controlling the position of the docked spacecraft-satellite combination. The extension spacecraft also includes an onboard propellant supply for accomplishing the rendezvous and docking of the spacecraft with the satellite and for controlling the position of the docked spacecraft-satellite combination.

Abstract: A shuttle launch system for a model rocket which includes a model rocket engine having a propellant charge for propelling the model rocket in a first direction and an ejection charge for ejecting matter in a second direction generally opposite the first direction consists of a booster rocket having a longitudinally extended tube with a peripheral sidewall, an inner chamber and top and bottom ends and an engine-receiving chamber adjacent the bottom end of the tube. A shuttle glider support structure is mounted on the booster rocket for releasably supporting a shuttle glider thereon. A fluid passage extends between the inner chamber of the booster rocket and the shuttle glider support structure such that a portion of gas within the inner chamber is redirected from the inner chamber through the fluid passage and out of the shuttle glider support structure.

Abstract: A flying vehicle has wheels for highways, and a body and an engine. The body, engine and load define a center of mass (CG). Shrouded fans are located about the CG so as to produce, in conjunction with air jet redirection apparatus, the torques required to assume various attitudes. In one embodiment, an upper shrouded fan, with a diameter no greater than eight feet, produces an air jet, centered above the CG, for lifting the body. A second shrouded fan, smaller than the first, produces an air jet for lift, centered below the center of mass, on the longitudinal axis of the vehicle, forward of the CG. Third and fourth paired shrouded fans produce air jets for lift, centered below the CG, on either side of the longitudinal axis of the vehicle, toward the rear of the body. The paired second and third fans have equal diameters, no greater than half of the diameter of the upper fan, to keep the total width eight feet.

Abstract: A method and apparatus for automatically jettisoning cargo carried by a dual-point suspension system when a suspension system failure is detected. Three conditions must be satisfied before a load is jettisoned. The average value of the load and an instantaneous value of the load on a hook must have fallen below a threshold value (zero load condition). A threshold amount of the load must have shifted from one hook to the other (dynamic load split condition). A threshold amount of an initial hook load must have been lost within a short period of time (rapid rate-of-decrease condition). For all three conditions, the threshold amount or value is adaptively set based on the actual load carried by the dual-point suspension. If all three conditions are satisfied for either the forward or the aft hook, the cargo is jettisoned. Additionally, a fourth condition that detects whether a structural limit of a hook has been exceeded is evaluated. If the structural limit has been exceeded, the load is jettisoned.

Abstract: A method is provided for controlling a carrier which is used to carry a flight vehicle, the method including (a) providing a carrier and a control system mounted on a lower side thereof; (b) sending a signal to a flight vehicle to decrease a velocity thereof for landing; (c) sensing a flight direction of the flight vehicle and instantaneous velocities thereof; and (d) accelerating the carrier to catch up with the flight vehicle at a location therebeneath and adjusting the velocity of the carrier to match with that of the flight vehicle such that the flight vehicle is able to smoothly land so as to be supported on a top surface of the carrier.

Abstract: This invention relates to a composite aircraft comprising a conventional aircraft (2) and a carrier aircraft (4) connected together during flight as a composite aircraft by way of a connector (6). The carrier aircraft has a vertical takeoff and/or landing capability and the conventional aircraft is provided with a directable propulsion nozzle so that during operations as a composite aircraft lift is shared by components of lift from the propulsion systems of both aircraft. Therefore, by connecting itself to the carrier aircraft, the conventional aircraft may takeoff and/or land vertically as the case may be, but without the requirement for a vertical takeoff and/or landing capability of its own and all the weight penalties associated therewith.