Abstract: A non-powered pre-stage (10) with a commensurably large wing area is used to launch a variety of single-stage and multiple-stage space vehicles (20), such as conventional ballistic rockets and prospective spaceplanes, from conventional runways. This method of launch eliminates need in dedicated ground launch structures and/or dedicated long runways. The vehicle to be launched (20) is mated to this non-powered aero-assisted pre-stage (NAP) (10), with their flight directions aligned, using a lock-and-release mechanism (30). The resulting stack takes off like a conventional airplane using the propulsion of the vehicle and aerodynamic lift of the NAP. After the desired trajectory of the vehicle is achieved, the vehicle is separated from the NAP and continues its ascent. The NAP returns back to the surface for reuse or disposal. Thus, a wide variety of conventional airfields can be used for launch of ballistic and aero-assisted flight vehicles.

Abstract: An aerial load lifting system features a non-rigid or blimp-type dirigible providing a lighter-than-air envelope that is placed within a structural shell. The system is designed so that the envelope provides essentially neutral buoyancy for the structure, leaving only the cargo weight to be lifted by the rotors. The structural shell supports the engine, fuel tank, rotors, and transmission system that power the lift and vectoring of the aircraft, in addition to supporting the cargo load. The structural shell transfers the weight of the load directly to the location of the rotors, thus avoiding stress on the envelope.

Abstract: A system and method for docking various types of aircraft is disclosed. An aerodynamic lifting structure docking mechanism for docking two or more aircraft is provided comprising an aerodynamic lifting structure. The aerodynamic lifting structure includes a first and second airflow adjustment mechanism. The aerodynamic lifting structure further includes a first hard docking mechanism, and a second hard docking mechanism, and still further includes a soft docking mechanism. The first and second airflow adjustment mechanisms are configured to substantially remove any aerodynamic lifting structure vortices around each of the aerodynamic lifting structure tip areas. The soft docking mechanism is configured to soft dock a first aerodynamic lifting structure with a second aerodynamic lifting structure. The first hard docking mechanism is configured to hard dock with the second hard docking mechanism, thereby temporarily attaching the first aerodynamic lifting structure with the second aerodynamic lifting structure.

Abstract: A flying wing boat is provided, which comprising a fuselage provided with a cockpit at a bow thereof; a pair of main wings, each of which being pivotably connected to one side of the fuselage respectively and being provided with a flap; a pair of pontoons, each of which being provided at a tip of each main wings; at least one propeller provided at a fore part of the fuselage; and a driving system supplying power to the at least one propeller. The flying wing boat of the present invention could improve the safety and comfortabilty of navigation.

Abstract: A heavier-than-air air vehicle, particularly a long endurance, solar powered, unmanned aerial vehicle (UAV) intended for “perpetual” flight within the stratosphere, is carried to its operational altitude suspended on a tether from a helium balloon. The tether is attached at or towards a tip of the UAV's wing so that it is carried in effectively a 90° banked attitude. At the desired altitude the UAV's powerplant is started and it flies on its tether in an upwardly-spiralling path relative to the balloon until a level or near level attitude is attained, when the tether is released and the UAV is permitted to assume free flight.

Abstract: A method of control and a means for control for a vehicle constructed by temporarily integrating a conventionally controlled motorcycle and a fixed wing flight device. The method includes a means of control for maneuvering a vehicle, enabling a handlebar to tilt, rotate and move up and down; translating these movements to a flight device. The control means for vehicle flight control converts to a ground vehicle control means and vice versa. In one preferred embodiment, the method employs a mechanism comprising an apparatus, including a first means for enabling tilting of the handlebar without rotating the front wheel of the motorbike, and for allowing the handlebar to be raised and lowered without raising and lowering the wheel. The movements of the handlebar are translated to control ailerons, elevator and rudder of the flight device for making roll, yaw, and pitch adjustments.

Abstract: This invention relates to improving the tolerance of composite laminate structures to damage and/or delamination, resulting in weakening of the structure and/or to reducing the possibility of such damage and/or delamination. In particular, but not exclusively the invention relates to protecting the end surfaces of composite laminate structures present on aircraft from impact damage. The invention provides an aircraft component comprising a composite laminate structure, the composite laminate structure including an end surface at which a multiplicity of the layers of the laminate structure terminate, wherein the aircraft component further comprises a deformable strip mounted to protect the end surface of the composite laminate structure from direct impacts.

Abstract: An air cargo transportation method, a transport plane and an air cargo transport system. In the air cargo transportation method for the transport of various cargoes to different destinations, a transport plane is provided first that flies through at least three air regions respectively associated to a station. The transport plane does not land at one of the stations. Instead, the cargo is transported between the transport plane and one of the stations by an airworthy feeders, the cargo being transferred between the feeder and the transport plane while in the air. The transport plane and two feeders form the air cargo transport system, wherein the transport plane may comprise two interconnected feeders. With the air cargo transportation method, the utilization of the transport plane is enhanced. Further, the transport ways for individual cargo items can be shortened so that the efficiency is improved.

Abstract: A launching vehicle that is lighter than air and capable of lifting a space bound payload to the upper atmosphere, reducing the energy required for spaceflight. Several possible configurations include but are not limited to. First, a single conventional balloon comparable to a large weather balloon for small payload or low orbit launches. Second, a layered configuration of several balloons stacked one on top of another increasing payload capacity. Third, a grouped configuration utilizing a structure lifted with the payload to accommodate more balloons and provide a stable structure from which to launch. Fourth a ring or doughnut shaped balloon could be used to carry the payload allowing fully vertical launch. Fifth, the ring shaped balloons could be stacked vertically and or grouped concentrically to allow for large payloads.

Abstract: A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward flight operation without significantly impacting hover stability. One or more retractable wings are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be detachable.

Abstract: A vehicle that is convertible in its operation between flying as an autogiro and driving as a motorcycle, in which the propeller rotates around a section of the fuselage. The propeller span can be as large as the space between the autogiro lifting rotor blade and the ground.

Abstract: An air vehicle assembly and a corresponding method for launching an air vehicle assembly are provided, along with corresponding control systems and methods. The air vehicle assembly may include a plurality of air vehicles releasably joined to one another during a portion of the flight, such as during take-off and landing. By being releasably joined to one another, such as during take-off and landing, the air vehicles can rely upon and assist one another during the vertical take-off and landing while being designed to have a greater range and higher endurance following the transition to forward flight, either while remaining coupled to or following separation from the other air vehicles. By taking into account the states of the other air vehicles, the control system and method also permit the air vehicles of an air vehicle assembly to collaborate.

Abstract: An aircraft design that is powered by an automotive engine. The aircraft having a specifically designed fan stage of a fan jet gas turbine engine located closer to the fuselage of the aircraft and to the automotive engine, eliminating the need for an expensive gear box. By locating the fan closer to the engine, the drive shaft can be shortened, thereby reducing the resonances associated with a longer drive shaft. The forward location of the fan gives the aircraft additional ground clearance, allowing for a normal rotation amount during take off and landing.

Abstract: System and method for a flyable and roadable vehicle. According to an embodiment, the present invention provides a vehicle capable of air and road travel. The vehicle is adaptable to a flying configuration and a road configuration. The vehicle includes a fuselage having a front end, a rear end, a top side, a bottom side. The vehicle also includes a wing component having a plurality of planes. The plurality of planes includes a first plane and a second plane. The vehicle additionally includes a connecting component for coupling the planes of the wing and the fuselage. The connecting component is able to accommodate a substantial relative rotation between the first plane and the fuselage. The vehicle further includes a plurality of wheels coupled to the bottom side of the fuselage.

Abstract: A multimodal vehicle includes a ground based vehicle with an attached high-capacity airfoil parachute for deployment. The ground based vehicle includes a drive system for use on either land, water or both. Furthermore, the ground based vehicle is sized and dimensioned for transport of multiple vehicles in a cargo plane. The high-capacity airfoil parachute allows high-altitude deployment of the multimodal vehicle. The risers to the parachute may be adjusted for powered parachute flight rather than free fall flight. The ground based vehicle may include a propeller for powered flight.

Abstract: A spacecraft system for achieving LEO and beyond includes a lifting body spacecraft, and an acceleration bed unit for accelerating the spacecraft horizontally on a runway to liftoff. The rocket engines of the spacecraft then power the spacecraft into LEO, and the spacecraft glides back to earth, where it is refurbished for reiterative use. A belly assembly of the spacecraft is removable and replaceable. The hydrogen fuel tanks of the spacecraft are modular units, and each include a bladder that expands to fill the tank when empty to prevent explosion hazards.

Abstract: The method in accordance with the invention is a method of improving aeronautical safety relating to air/ground communications and to the environment of aircraft and it is characterized in that the quality of the air/ground exchanges between the crew and an air traffic control center is monitored automatically aboard the aircraft in which this method is implemented, that the context arising from these exchanges is correlated with the onboard data and those produced by the monitoring of the environment of the aircraft, and that warnings destined for the crew of the aircraft are formulated by allocating these messages a severity level as a function of the degree of dangerousness of a detected threat and/or of gaps or inconsistencies between the instructions and information from the control center and the flight parameters of the aircraft or the intentions of its crew and/or messages destined for the air traffic control.

Abstract: A vehicle adapted for airborne flight and waterborne sailing has a fuselage (20) with left and right wings (52, 54) that pivot independently about a respective longitudinal axis from a generally horizontal orientation for flight to a generally vertical orientation to provide wind-driven propulsion for sailing. Further, the wings (52, 54) pivot about a respective second axis (66) that is generally perpendicular to the longitudinal axis to trim the wings (52, 54) for sailing with a given relative wind direction. The wings (52, 54) are mounted by a respective first pivotal joint (56, 58) to the distal ends of respective stub wing/decks (48, 50). The stub wing/decks form a fixed central wing section (46). Water hulls (28) are mounted below the distal ends of the stub wing/decks (48, 50) on vertical pylons (30) to provide stable flotation. Vertical and horizontal stabilizers (40, 60) are mounted on the back ends of the water hulls (28).

Abstract: A system is disclosed for lifting a rocket into the upper atmosphere and establishing forward flight at several hundred miles per hour, before the rocket engines are ignited and the rocket is released from the lifting system. The main subassemblies of this lifting system comprise: (1) an array of large helium-filled dirigibles, of a size that can provide hundreds or thousands of tons of lifting force; (2) a tank-holding assembly that will be tethered to the dirigibles, and that will contain pumps and high-pressure tanks, to recapture and store the helium for use in subsequent launches; and, (3) a winged platform, with wings that can be rotated vertically during liftoff, and horizontally to establish forward flight after a desired altitude has been reached, and having conventional aircraft engines on each wing. This system enables safer, less expensive, and more efficient launching of rockets and heavy payloads into space, using easily reusable subassemblies.

Abstract: An airship deployment system comprises an airship of unique shape having laminar flow over this shape to enable low power propulsion, capable remote control, comprising an inflatable body; a propeller assembly for station keeping and repositioning said airship and capable of being folded into a compacted position and unfolded into an operational position; and a payload, comprising gas for inflating said inflatable body; and means for transferring data between said airship and a remote location; and a missile for carrying said airship in a compacted state to a predetermined location and altitude, and releasing said airship at said predetermined location and altitude. When said airship is released from said missile said inflatable body is inflated and said propeller assembly is unfolded into said operational position.

Abstract: A multimodal vehicle includes a ground based vehicle with an attached high-capacity airfoil parachute for deployment. The ground based vehicle includes a drive system for use on either land, water or both. Furthermore, the ground based vehicle is sized and dimensioned for transport of multiple vehicles in a cargo plane. The high-capacity airfoil parachute allows high-altitude deployment of the multimodal vehicle. The risers to the parachute may be adjusted for powered parachute flight rather than free fall flight. The ground based vehicle may include a propeller for powered flight.

Abstract: A fly-drive vehicle is disclosed including a vehicle body, a motor mounted on the vehicle body, at least one rotor rotatably attached to the vehicle body, a pair of wheels each rotatably attached to a lower portion of the vehicle body, a drive propeller rotatably coupled to the vehicle body, a transmission for selectively transferring mechanical power from the motor to at least one of the pair of wheels or to the drive propeller, and a front wheel control mechanism. The fly-drive vehicle also includes a landing gear assembly for raising and lowering the pair of wheels with respect to the vehicle body and a folding rotor shaft assembly for raising and lowering the rotor with respect to the vehicle body.

Abstract: A flying vehicle assembly apparatus comprises a winged flying craft and a powered craft for propelling the flying craft and a tether assembly comprising one or more first rigid struts having a first end pivotally secured to first biased pivot connections adjacent to the flying craft and a second end pivotally secured to second biased pivot connections, and one or more second rigid struts having a first end pivotally secured adjacent to the powered craft and a second end pivotally secured to a second biased pivot connection. The first and second biased pivot connections urge the flying craft and the powered craft toward one another, and whereby during flying operation, the powered craft is generally forward of the flying craft.

Abstract: A composite combination for launching a payload into space including a hypersonic spacecraft carrying the payload and a carrier aircraft, the spacecraft design to take off from the ground on the aircraft and then, upon separation from the carrier aircraft, to propel the payload on its own toward an assigned trajectory. The combination further includes a separation mechanism for separating the vehicle from the aircraft, and measuring elements for measuring physical data operative in the evaluation of the safety of a phase of separation of the vehicle and the aircraft, which data is evaluated by a computer component to authorize a prohibit activation of the separation mechanism.

Abstract: A combination powered parachute and motorcycle modifies an initially conventional motorcycle with the addition of various flight components to provide sustained flight for the machine. A peripheral and overhead safety structure is installed upon the motorcycle, with a second flight engine, propeller, folding propeller guard, and fuel system also installed. The flight engine and all of its systems are completely independent of the conventional motorcycle engine used for surface propulsion. A set of laterally disposed stabilizer wheels is also provided for transition from ground to flight and from flight to ground operation. Lift is provided by a folding parafoil device of either the ram air inflated or partially pneumatically inflated type. For flight operations, the lateral wheels are lowered and extended, the folding propeller guard is extended, and the parafoil is deployed behind the motorcycle, with the parafoil lifting conventionally upon attaining flight speed.

Abstract: A system for launching, refuelling and recovering in flight an aircraft (10) such as an unmanned aerial vehicle (UAV) from a larger carrier aircraft (16) comprising a holder (22) on the carrier aircraft (16) to which the UAV (10) is detachably connectable and an extendable and retractable refuelling device (23, 24) on the carrier aircraft (16) detachably connectable to the UAV (10) whereby to launch the UAV it is disconnected from the holder (22), the refuelling device (23, 24) is extended with the UAV connected thereto to cause the UAV to trail behind the carrier aircraft and the UAV is then disconnected from the refuelling device.

Abstract: A method wherein a vehicle is capable of movement on or over land, and/or on, over, or under water. Various body, wing, tail, and/or outrigger shapes facilitate movement and develop lift. Buoyancy or semi-buoyancy is developed utilizing various chambers to contain controlled volumes of gaseous or liquid substances. Motion is augmented by propulsion or repulsion mechanisms, including pressurized liquid stream jet (PJET) propulsion. The vehicle is capable of modifying its shape and/or the curvature of various parts, such as wings, tails, and/or outriggers, by manipulating the internal skeleton, the internal compartments supporting the external surfaces, and/or the internal pressure of the shape. Control Agents with mechanized or manual support manage the vehicle's operations controlling various movement particular information, as well as baseline algorithms, such as wind speed, currents, and location.

Abstract: A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.

Abstract: A VSTOL vehicle including a fuselage with two pairs of ducted rotors fully enclosed fore and aft of the fuselage respectively. The fuselage is aerodynamically shaped to generate lift in forward flight. All four ducts are configured such that their center axes are at angles tilted sufficiently forward from the vertical axis of the fuselage. Each ducted rotor is powered by one engine inside the duct behind the rotor. All four rotors and engine shafts rotates counterclockwise, generating substantial angular momentum for gyroscopic effect. Variable inlets of the ducted rotors and vector thrusting of the airflow out of the ducted rotors combine to provide efficient power and control during all phases of flight. The vehicle is configured to meet motor vehicle requirements to drive on streets.

Abstract: The main idea is using hydrogen inside a bard shell, to create a lighter than air ship. It would be very aero dynamic, and using the newest carbon-carbon fiber and resins that would make up the internal beams, rods and skin. The top of the ship will be covered with solar cells. The bottom with liquid nitrogen tubes running through out to cool during re-entry.

Abstract: A pusher canard aircraft convertible for road use. Canard outer sections are removable and are stored within the aircraft fuselage and the outer main wing sections rotate horizontally for storage on the fuselage top. The fuselage is designed as a lifting body which gives the aircraft three lifting surfaces. The lifting body takes advantage of ground effect, resulting in a lower landing speed. In road mode the vehicle as a 2 or 4 passenger model is smaller than a full size automobile. Hydraulic motor wheels propel the aircraft/vehicle for road use. An internal combustion engine within the fuselage drives the propeller for air operation. The propeller is disengaged, not removed, for land operation and the engine is used to drive an hydraulic pump to power the motor wheels for road use. A single nose wheel or two front wheels are used for both steering in landing/taxiing and for road use. In road mode, the appearance is as much like a van than as an aircraft.

Abstract: An Aircraft Escape (AEC) is designed for manned atmospheric or space vehicles having a fly away capability at any time during the flight of the parent aircraft. The AEC houses the crew, passengers, life support systems, aircraft flight controls, propulsion, navigation instruments, communications equipment, and deceleration devices to permit safe landing of the escape cabin on land or water. A rocket or mechanical device provides the means to actively separate the escape cabin from the parent aircraft during an emergency.

Abstract: A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.

Abstract: A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.

Abstract: A vehicle is in the general shape of a land vehicle, such as a car, but has a plurality of rotors so the vehicle is capable of flight in the manner of a VTOL or a helicopter. The vehicle has foot pedals and steering that can be operated in the manner similar to that of a car.

Abstract: This machine is a mutated creature of all or most technology to produce either a platform that can be bolted to an existing power supply; as well as could be a complete unit that produces the same result of the ability to fly, hover, &/or drive. This solves many problems by offering an alternative; many parking lots already have helicopter pad(s) so being able to fly in & then hover to a parking spot is an asset. Then if you only add the ability to drive on existing streets/highways; you get the most universal transportation available. Later calculating in the factor that you can convert your existing motorcycle or ATV that is in your garage, into this highly sophisticated futuristic flying machine keeps cost down for a smooth transition is the “Pas-Key” to the future. Imagine driving out bound on the freeway & at the fly zone limit, you flip a switch and fly right off the pavement.

Abstract: A method and apparatus for actuating an aircraft nose portion. The aircraft can have a longitudinal axis and a pitch axis generally transverse to the longitudinal axis. The fuselage can include a pressure bulkhead and a pressurized payload portion aft of the pressure bulkhead. The nose portion can be positioned forward of the pressure bulkhead and can be changeable from a first configuration to a second configuration while the pressurized payload portion is capable of being pressurized relative to a region external to the aircraft. For example, the nose portion can be inclined upwardly relative to the longitudinal axis when pivoted from a first position to a second position. Accordingly, the length of the aircraft can be reduced, for example, to accommodate the aircraft at a loading gate or other ground support area.

Abstract: The invention is a system for ferrying at least one aircraft by a ferrying aircraft, the at least one aircraft and ferrying aircraft having vehicle management systems. In detail, the invention includes an attachment device for joining a wing tip of the at least one aircraft to one of the wing tips of the ferrying aircraft. A system is included for controlling the at least one aircraft and the ferrying aircraft such that the at least one aircraft flight characteristics are controlled by the ferrying aircraft.

Abstract: This invention provides another basic important means of transportation after motor vehicle, airplane, helicopter: helicarplane. Helicarplane can run on ground roads, take off and land in fixed-wing style or in helicopter style; can fly quickly and economically in fixed-wing airplane style.

Abstract: A recoverable/reusable booster stage has air-breathing jet engines mounted on the inter-tank ring in alignment with the center axis of the booster body. The jet engines provide supplemental lift on ascent, power the booster on a return flight, and hover the spent booster for a vertical, tail-down landing at the launch site.

Abstract: The invention is a system for ferrying at least one aircraft by a ferrying aircraft, the at least one aircraft and ferrying aircraft having vehicle management systems. In detail, the invention includes an attachment device for joining a wing tip of the at least one aircraft to one of the wing tips of the ferrying aircraft. A system is included for controlling the at least one aircraft and the ferrying aircraft such that the at least one aircraft flight characteristics are controlled by the ferrying aircraft.

Abstract: By air, land and sea. Extending the function and performance of a multi-function aircraft.

Abstract: A road/air vehicle is able to quickly and easily convert between two configurations, air configuration and road configuration, to facilitate practical operation as both an aircraft and as an automobile. In air configuration the craft includes two laterally symmetrically flight surfaces; a smaller forward canard wing, generally horizontally disposed and a larger rearward main wing generally horizontally disposed with fin surfaces, generally vertically disposed, at each tip. Control surfaces on the main wing, the canard wing and the tip fins severally provide roll control, pitch control and yaw control in flight. The wheels/undercarriage are of a laterally symmetrical rectangular pattern, with the lateral distance between the two forward wheels and the two rearward wheels being similar. The forward wheels are steerable for ground operations. A suitable powerplant drives the rear wheels for ground operations. A second suitable powerplant provides direct atmospheric thrust for flight operations.

Abstract: According to one embodiment of the invention, a rocket booster for launching a payload into space includes a fuselage adapted to support one or more fuel tanks inside the fuselage and a booster engine coupled to an aft portion of the fuselage. The booster engine is operable to provide thrust during an ascent phase of operation of the rocket booster. The rocket booster further includes a nacelle coupled to a forward portion of the fuselage and a flyback engine disposed within and coupled to the nacelle. The flyback engine is operable to provide thrust during a flyback phase of operation of the rocket booster. The rocket booster also includes one or more control surfaces coupled to the fuselage that are operable to control a flight pattern of the rocket booster during the flyback phase of operation. The flyback engine of the rocket booster is located forward of an aerodynamic center of the rocket booster.

Abstract: A signal conditioning system for translating communications between an aircraft and an associated store includes a store umbilical element that electrically and mechanically couples the aircraft and the store. The system also includes a signal conditioning element having an ASIC and electrically connected between the aircraft the store. The signal conditioning element is capable of being incorporated within the umbilical element and includes a translation element for receiving first predetermined format communications from the aircraft at the first predefined transfer rate and thereafter outputting corresponding second predetermined format communications to the store at at least one second transfer rate. Conversely, the translation element is also capable of receiving second predetermined format communications from the store at the at least one second transfer rate and thereafter outputting corresponding first predetermined format communications to the aircraft at the first predefined bit rate.

Abstract: A flyback booster (200) comprising an aircraft (203) housing a launch vehicle stage as a removable rocket propulsion module (502) and several space launch vehicles using variations of the flyback booster (200) are disclosed. This flyback booster (200) functions as the first stage of a multistage space launch vehicle. The stage used in the flyback booster (200) and the upper stages of the multistage space launch vehicle (213) are selected to optimize the launch cost for a specific payload.

Abstract: A flyable automobile comprising a right main wing connected to the flyable automobile and comprising a right wing inner portion and a right wing outer portion, the right wing outer portion hingedly connected to the right wing inner portion so that the right wing outer portion can be folded above the right wing inner portion, and the right main wing connected to the flyable automobile so that the right main wing can pivot into a storage compartment underneath in the flyable automobile, and a left main wing connected to the flyable automobile and having a left wing inner portion and an left wing outer portion, the left wing outer portion hingedly connected to the left wing inner portion so that the left wing outer portion can be folded above the left wing inner portion, the left main wing connected to the flyable automobile so that the left main wing can pivot into the storage compartment in the flyable automobile.

Abstract: An aircraft carrier adapted to carry and release a carried store for air launch purposes. The aircraft carrier includes a carrying station coupled to a part of the aircraft carrier and being a priori adapted to carry a load other than the carried store to be launched. The carried store to be launched is mountable to a coupling device that is mountable to the carrying station. The aircraft carrier also includes a control system capable of communicating with the coupling device for selectively releasing the carried store.

Abstract: A method for velocity match transfer alignment between a carrier vehicle and a carried vehicle. The method includes repeatedly measuring a velocity difference between the carrier vehicle and the carried vehicle, updating a state vector that include a predicted value of the velocity difference, propagating the vector forward in time, and moving the carrier vehicle and the carried vehicle along a trajectory.

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