Abstract: A morphing aircraft that is achieves multi-modality location and camouflage for payload emplacement The morphing aircraft includes a substantially cylindrical fuselage including a shape configured as a packaging container with a first end and a second end A set of wings is coupled to the fuselage The set of wings includes a first position where the set of wings is extended outwards from the fuselage and a second position where the set of wings is retracted inwards towards the fuselage A tail is coupled to the second end of the cylindrical fuselage The tail includes a first position where the tail is extended outward from the fuselage and a second position where the tail is retracted inward towards the fuselage A propeller is mounted to the first end of the fuselage An engine is mechanically coupled to the propeller The engine is enclosed within the fuselage and powers the propeller.

Abstract: Disclosed is a supersonic aircraft design having a single structural component that simultaneously joins the wings to the aircraft fuselage, the engines to the aircraft fuselage, and the wings to the engines, resulting in an airframe planform, which, in combination aerodynamic shaping and structural morphing technologies within the aircraft fuselage, enables the aircraft to be optimized to reduce sonic boom.

Abstract: The human-powered, bird-like flying device of the present invention has wings which may rotate around the keel and legs that let the pilot control rotation of the wings, which is to make the wings flap. The present invention develops one of the more efficient methods of ascending, which is to increase the angle of attack by moving the control bar forward while shifting the pilot's weight to efficiently strike onto the legs that make the wings flap downward. The present invention is secure and stable in the air, particularly while ascending and descending. This is done by selecting the proper shape and sail area of the wings and by proper attachment of the arm, legs and the hang loop, which hold the pilot's body.

Abstract: An aircraft configuration that may reduce the level of noise, infrared radiation, or combination thereof directed towards the ground from an aircraft in flight. An embodiment of an aircraft includes a fuselage, two forward swept wings, at least one engine mounted to the aircraft and higher than the wings, and vertical stabilizers mounted on each wing outboard of the outermost engine. The leading edge of the wing may extend forward of the leading end of the engine, and the trailing edge of the aft deck may extend aft of the trailing end of the engine. The aft deck may include an upwardly rotatable pitch control surface at the trailing edge of the deck. Engine types may vary, including but not limited to turbofans, prop-fans, and turbo-props. Main wings may be mounted above the longitudinal axis of the fuselage, and canards may likewise be mounted above or below the axis.

Abstract: The present invention is an unmanned air vehicle designed for reconnaissance, surveillance, data acquisition, and general research. The air vehicle is a monoplane that consists of several pieces that can easily be assembled using a minimal amount of tools. The air vehicle consists of a forward and aft fuselage section, two identical horizontal stabilizers, and four identical wing sections. The aircraft can fly with all four wing sections, or with just two wing sections (the short wing configuration). Each of the four wing sections of the air vehicle can be interchanged with any of the other wing sections for the purpose of minimizing assembly time and spare parts.

Abstract: A flying object capable of being launched in air is detachably mounted on a wing body of a launching apparatus. The launching apparatus is towed by an aircraft through a cable so as to be run and taken off. After raising the launching apparatus to a launching height of the flying object by the aircraft, the flying object is released from the wing body in air and then the flying object is ignited and launched in air in a launching system. The system for launching in air can be developed without newly developing a platform as a mother ship so that a research cost can be remarkably reduced. In the case that a small artificial satellite is installed in a flying object, it is possible to develop an artificial satellite smoothly and quickly applicable to security matters and disaster observation.

Abstract: An apparatus for use as a flying entertainment vehicle. The apparatus includes a lift system, such as a parawing, that is inflated by air to generate lift and further includes a vehicle frame attached to the lift system such as by suspension lines that also space the lift system apart from the vehicle frame. The apparatus includes a thrust assembly supported on the vehicle frame that is operable to propel the vehicle at a flight speed at which the lift system is operated, e.g., the parawing is inflated, to generate lift to suspend the vehicle frame above the ground. The apparatus includes show elements that may be supported on or by the vehicle frame and be configured to be lift neutral. The show elements function to distract observers away from the lift system such as by appearing to provide the lift or features that cause the vehicle frame to fly.

Abstract: This aircraft comprises both propulsion units (7, 16, 17) for conventional aircraft flight in the atmosphere and for high-altitude operation as a rocket. It is divided into a payload compartment (8) and a compartment (13) essentially containing rocket propulsion unit ergols. It comprises a long transverse wing (3) with a small back-sweep to favour the lift in the dense layers of the atmosphere and make it possible to climb to high altitudes at a subsonic speed before using the rocket propulsion units. The return is performed by gliding or controlled as for a conventional aircraft.

Abstract: An aircraft including a wing and a pylon, wherein the pylon provides an airfoil inverted for an airfoil of the wing, and an improvement and method for improved flight dynamics for 20 and 30 Series LEARJET® is provided. The improvement includes an increased distance between a leading edge of a wing and an intake of an engine of the aircraft, which reduces drag and increases lift for improved flight dynamics of the aircraft. The inverted airfoil of the pylon negates an influence of the pylon on flight dynamics for improved overall flight dynamics of the aircraft. The method includes steps of removing an original engine from an original pylon, removing the original pylon from the fuselage of the aircraft, and mounting a new pylon in a new location adjacent to the fuselage, wherein the new location is aft of the original location.

Abstract: An improved structure and method for powering the flight of a model airplane by positioning the motors and propellers on the back side of the top wings of an airplane using a single or double-deck wing design so that the propellers and motors of the airplane are better protected from damage in the event of a crash. The fuselage of the airplane is formed of a deformable material such as a foam to aid in crash resistance.

Abstract: A solar powered aerial vehicle includes an elongated airframe incorporating lifting and control surfaces, a mechanism for propelling the airframe through the air such that lift developed by the lifting surface is equal to or greater than the weight of the aerial vehicle, a planar solar sail coupled to the airframe and having at least one surface adapted to collect solar energy during the day and to power the propelling mechanism with a first portion of the energy collected, and an apparatus such as a fuel cell/electrolyzer for storing a second portion of the solar energy collected by the solar sail during the day and for powering the propelling mechanism with the second portion of energy during the night. The vehicle is capable of continuous operation at northern latitudes and during the winter months for extended periods without landing or refueling.

Abstract: A method of transitioning from a complex response flight state to a ground operation control state. Pilot intent is determined through collective position information to control the transition. An independent cockpit switch activates an emergency surface contact transition function for use with a fly-by-wire (FBW) flight control system. Once the surface contact transition function is active, FBW control laws transition from a fully augmented flight state, through an augmentation deactivation state and into the surface contact state.

Abstract: An air vehicle comprising only one wing, which is thin and substantially flat, the wing being elongate and preferably diamond-shaped, and a pod removably coupled to the wing for relative rotation about an axis normal to the major surfaces of the wing, the pod bearing a propulsor for the air vehicle. The propulsor may be a propeller with a Custer duct for static lift.

Abstract: An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.

Abstract: A light multi-purpose aircraft comprises a fuselage (1); a wing (2); a fin assembly (3); a landing gear (4); a main power plant (5); an auxiliary power plant (7); pylons (10); outboard suspension objects (9) arranged on the undersurface and at the ends of the wing (2); at least one outboard suspension object (9) being arranged on the undersurface of the wing (2) and at least one outboard suspension object (9) being arranged at each end of the wing (2); a gun mount (8) or a guidance and tracking mount arranged in the lower part of the fuselage (1); a controlling integrated complex of airborne electronic equipment (17) with an electric power supply system (16) and an armament control complex (19) incorporating an on-board electronic guidance and tracking system (20); a defense system (21); a multi-purpose control panel (22); a group interaction system (23); an armament control system (24) which are related to each other and to the controlling integrated complex of airborne electronic equipment (17) through a mu

Abstract: A high-speed transport aircraft. In one embodiment, the aircraft includes a fuselage, delta wings, and integrated engine nacelles. The fuselage is configured to carry a payload and has a forward portion and an aft portion. The aft portion defines a generally constant-width planform and includes first, second, third, and fourth passenger seat sections, with each of the seat sections having at least two passenger seats positioned abreast at least generally normal to a longitudinal axis of the fuselage. In one aspect of this embodiment, the wings extend from the fuselage adjacent to the aft portion, and the fuselage further includes first and second rows of windows above the wings. The first row of windows are positioned in the fuselage directly adjacent the first seat section and the second row of windows are positioned in the fuselage directly adjacent the fourth seat section.

Abstract: A system is disclosed whereby a sensor, communication device, or other payload may be lofted to an operational altitude and maintained over an area of interest for some time by a relatively inexpensive and disposable buoyant aircraft, then returned intact to its point of origin or another desired location by a reusable but also relatively inexpensive non-buoyant aircraft. Automatic unpiloted control is used for all stages of flight, including ascent, loiter, return, and landing Specialized equipment can be provided to simplify launch procedures, reducing the number of personnel required to operate the system.

Abstract: An apparatus for increasing an aerodynamic surface area of an aircraft, e.g., a wing thereof, includes coaxially disposed first and second elongated airfoils and an inflatable device arranged to move the first airfoil coaxially relative to the second airfoil. The second airfoil has a root end fixed to the vehicle and an opposite outboard end, and the first airfoil is arranged to move axially between a retracted position generally inboard of the outboard end of the second airfoil and a deployed position generally outboard thereof. When the movable airfoil is deployed, a latching mechanism locks it in position. The inflatable device can include a collapsible duct that is sealed at one end and coupled at a second end to an inflating source, such as a reservoir of a compressed gas or a pyrotechnic gas generator.

Abstract: A wing load alleviation structure for use on an aircraft, comprising a front spar, wherein the front spar includes a plurality of alternating rigid spar structures and inflatable spar structures; and a rear spar, wherein the rear spar includes a plurality of alternating rigid spar structures and pivot joints, such that when a load is applied to the front and rear spars, deflection of each of the front and rear spars continues at a first rate until a critical load is reached, and then as the loading increases, deflection of each of the front and rear spars continues at a second rate.

Abstract: An aircraft is provided with a wing assembly mounted in a slipstream of a source of propulsion of the aircraft. The aircraft includes a body having a longitudinal axis, a wing assembly carried by the body and including a moveable portion moveable relative to the body and a wing carried by the moveable portion. A first actuator is coupled to the moveable portion to move it relative to the body in a direction generally parallel to the axis of the body. A second actuator is coupled to the wing to move the wing relative to the moveable portion and between first and second positions. The second actuator at least selectively permits uninhibited pivoted movement of the wing relative to the body in response to aerodynamic forces acting on the wing so that the wing may pivot to a position wherein the forces acting on the wing are balanced.

Abstract: A flight control system for an aircraft receives a selected value of a first parameter, which is either the airspeed or inertial velocity of the aircraft. A primary feedback loop generates a primary error signal that is proportional to the difference between the selected value and a measured value of the first parameter. A secondary feedback loop generates a secondary error signal that is proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, which is the other of the airspeed and inertial velocity. The primary and secondary error signals are summed to produce a velocity error signal, and the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal. The actuator command signal is then used for operating aircraft devices to control the first parameter to minimize the primary error signal.

Abstract: An aircraft includes a fuselage, and first and second freewings. Each of the first and second freewings is separately mounted to the fuselage and independently freely pivotable about respective pivot axes. The aircraft includes an angular rate sensor configured to measure a roll rate of the fuselage and to output a first roll rate signal. The aircraft includes a controller in communication with the angular rate sensor and configured to receive a second roll rate signal from the pilot and to compare the first and second roll rate signals to generate first and second control surface control signals. The aircraft includes at least one control actuator in communication with the controller and configured to actuate a first control surface of the first freewing and a second control surface of the second freewing in response to the first and second control surface control signals, respectively, to control the roll rate of the aircraft.

Abstract: A method of air transport includes improved reliability and safety of passengers and cargo transported by an aircraft having three fuselages. The method includes locating a cockpit of the aircraft at a forward portion of the first fuselage and isolating the cockpit from a remaining portion of the aircraft. The cockpit is then shielded and independently pressurized from the remainder of the aircraft by controls housed in the cockpit. The method further includes distributing passengers and cargo among the three fuselages, such as by locating dangerous or suspicious passengers or cargo in the second and third fuselages away from the cockpit. Also, dangerous or suspicious passengers or cargo may be located in the second and third fuselages and, thereby, isolated from the remaining passengers and cargo.

Abstract: An advanced internal combustion-electric hybrid airplane, having at least double the flight range and flight duration than a conventional equivalent airplane, while using the same amount of any desirable fuel. This is achieved by using 2-3× smaller and ultra-lightweight engine for cruising, and ultra-lightweight electric motor powered by lithium batteries during take-off and climbing. The electric motor becomes a generator during cruising and descent, recharging said batteries. The airplane has also temporary silent electric stealth capability and added safety by the electric back-up power. Due to its high efficiency, the operational cost is substantially reduced. Additional features include highly advanced, minimum drag and weight airframe.

Abstract: There is declared an aircraft with a lifting fuselage, comprising a wing, on outboard wing panels of which there are mounted engines, the fuselage width is considerably more than its height, but a front portion of the fuselage in plane smoothly transforms from a narrower nose portion into a wide base portion, therewith, the tail assembly has two stabilizers with control surfaces, the stabilizers are spaced from one another along the fuselage width aside from the longitudinal vertical plane of the aircraft and are installed at angle with respect to it, on each of the stabilizers it is installed an all-movable arrow-type yaw rudder with forming a T-shaped tail assembly, the axis of turn of said yaw rudder is positioned on the stabilizer in the plane of the yaw rudder, but construction planes of the stabilizers intersect with one another in the plane of the aircraft symmetry plane on the base longitudinal axis of the aircraft or below it.

Abstract: An unmanned air vehicle designed for reconnaissance, surveillance, data acquisition, and general research. The vehicle is a monoplane that is comprised of several pieces that can easily be assembled using a minimal amount of tools. The aircraft consists of a forward and aft fuselage section, two identical horizontal stabilizers, and four identical wing sections. The aircraft can fly with all four wing sections, or with just two wing sections (the short wing configuration). This makes the aircraft usable for missions requiring short takeoff and landing and high endurance (long wing), or missions requiring higher speed and range (short wing). No other UAV (or other aircraft) has this unique feature. Another novel aspect of the present invention is the wing control can be specially designed to increase the effectiveness of the wing control surface while minimizing the effect the control surface has on the overall aerodynamics of the wing, namely drag.

Abstract: A propeller includes a plurality of propeller blades. Each blade has an adjustable drag coefficient. A plurality of actuators adjusts the drag coefficients of the propeller blades. A controlling unit controls the plurality of actuators such that the drag coefficients of each propeller blade is adjusted according to a pattern that is dependent upon the rotational angle of the particular propeller blade so that the drag of each propeller blade is maximized at the same point through a course of revolution and minimized throughout the remainder of that revolution.

Abstract: The Hypersonic Orbital Fighter and the methods of flying it are disclosed. The Hypersonic Orbital Fighter is characterized by a winged, modified lifting body shape with the forward ventral section comprising an X-30 type compressive air inlet, throttleable supersonic combustion ramjet array under the center of gravity and half-cone exhaust outlet at the back, fore mounted canards, cockpit/payload area top front and mid section and one or more tailplanes at the top back. Flight profile comprising runway takeoff, high subsonic climb up to 65,000 feet, alternatively full power climb from zero to 65,000 feet, with progressive acceleration from there up to Mach 24 @ required orbital altitude. Able to intercept missiles from early through post-boost phase from chosen orbit or suborbital arc, to intercept aircraft and to interdict surface targets. Winged dynamic soaring capability in reentry followed by powered runway landing.

Abstract: An improved structure and method for powering the flight of a model airplane by positioning the motors and propellers on the back side of the top wings of an airplane using a single or double-deck wing design so that the propellers and motors of the airplane are better protected from damage in the event of a crash. The fuselage of the airplane is formed of a deformable material such as a foam to aid in crash resistance.

Abstract: A wing is presented that unfolds in a chordwise direction upon the launch of its aircraft at some velocity as it is projected into the air or launched from a moving craft at altitude. The wing is made up of two or more stiff, upper segments including the leading edge with foam used to complete the underneath wing shape. The foam is covered with a film of plastic or composite material to makeup the underneath shape of the wing as supported by the foam. The foam can be pressurized to enhance its final shape in support of the underneath film. The upper segments are joined by hinges using twisted, staked pins to provide force for the desired wing unfolding. Aerodynamic forces also enhance the unfolding motion. The wing can be used on a craft to be deployed at higher air speeds than any other type of folding wing of comparable stowing efficiency.

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: This invention relates to a parachute supported aircraft having a frame and a seat for supporting at least a pilot. A parachute is coupled to the frame by a plurality of riser lines for allowing the parachute to inflate and form a wing for lifting the frame. A pair of upwardly extending masts are coupled to the frame. Each mast supports a vertically displaceable sleeve receiving a group of riser lines. Control cables connected to a winch raise and lower the sleeves to allow the pilot to selectively collapse and inflate the wing in a controlled fashion. A wing elevating cord can be used by the pilot to help pull the parachute from a generally vertical, partially inflated, lockout position into a generally horizontal, more inflated, flight position.

Abstract: The aircraft has a main body 1 and a pair of sub bodies 4 and 5 positioned substantially in parallel with the main body 1 and respectively in both of the left and right sides of the main body 1. A canard 3 and main wings 8 and 9 each have a central portion fixed to the main body 1 and portions fixed respectively to the sub bodies 4 and 5, near left and right ends of the wings. Engines 6 and 7 are respectively mounted on outer surfaces of the sub bodies 4 and 5. The sub bodies 4 and 5 are thinner than the main body 1. The canard 3, which is positioned closest to the fore end of the aircraft, has a shorter wing span than the other wings. The sub bodies 4 and 5 contain fuel. The fuel is supplied to the engines 6 and 7 assuring high safety. The main wings 8 and 9 are positioned, shifted respectively forth and back relative to the main body 1. Therefore, stability is not impaired even if cargos are loaded into the main body over a wide range from the bow to the tail.

Abstract: A modular automated air transport system comprising an unmanned autonomous aircraft having a selectively detachable control systems portion and a structural air frame portion, wherein the structural air frame portion contains an interior cargo hold, aerodynamic members having control surfaces and at least one propulsion device attached to the structural air frame portion; and wherein the control system portion includes a control computer for autonomously controlling the flight of said air transport system from one known location to a second known location.

Abstract: The “Tailed Flying Wing Aircraft” idea represents new aerodynamic concepts for large high subsonic aircraft. Large high subsonic aircraft based on these new aerodynamic concepts are having a significantly higher lift capacity and longer range, as well as a significantly lower fuel consumption of at least two times less than the aircraft based on classical fuselage concept with the same external dimensions. In addition, the aircraft based on the new concepts are having a significantly better longitudinal stability and maneuverability, as well as aerodynamic efficiency at high subsonic speed than aircraft based on “Tailless Flying Wing” concepts. The aircraft based on the “Tailed Flying Wing Aircraft” idea satisfy all safety requirements for civil aircraft. They also have simple shapes for manufacturing, hence this idea provides for new realistic advanced aerodynamic concepts for the next generations of large subsonic aircraft.

Abstract: A process and system for noise reduction in multi-engine propeller-driven aircraft. The parameters of at least two propellers are adjusted with regard to frequency, amplitude, and phase so that the sound fields of the propellers are attenuated or completely extinguished by interference in the area of the closest aircraft fuselage.

Abstract: The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

Abstract: An extremely large aircraft which is suitable for overseas cargo transport and which includes a fuselage defining a central storage cavity, a wing assembly defining a pair of wing storage cavities, an altitude control system, and a plurality of independently steerable landing gear units. The central storage cavity has a length, height and width of at least 100 feet, at least 16 feet and at least 24 feet, respectively. The wing assembly has a wingspan of at least 300 feet and is configured with a moderate aspect ratio to permit both ground-effect and high altitude operation. The altitude control system controls the aircraft in ground effect such that the aircraft is maintained at about a predetermined altitude. The landing gear units are coupled to the fuselage and are arranged in at least two discrete columns and at least ten discrete rows. The central storage cavity and the wing storage cavities are configured to receive cargo including intermodal re-usable cargo containers.

Abstract: The invention relates to aircrafts, in particular to aircrafts, which are embodied in a passenger, cargo or cargopassenger variants thereby making it possible to improve performance characteristics by improving the aerodynamic properties thereof. The inventive aircraft having a carrying fuselage comprises a wing, an engine, and a fuselage whose width considerably exceeds the height thereof. A lower surface of the basic and the tail parts of the fuselage have a caved-in form in a cross-section thereof. A lower surface of the flattened front part of the fuselage is arranged at an attack angle with respect to the longitudinal horizontal plane of the aircraft. In addition, the front part of the aircraft has a curvilinear form in the plan view, which successively passes from the narrow front part to the basic large part of the fuselage.

Abstract: The in-flight refuelling of a squadron (1) of aircraft by a tanker (2) by means of the same refuelling hose requires the formation of a queue and the determination of the number of passes, one or possibly two, by each aircraft to the refuelling hose, which constitutes a refuelling sequence. Although the order in the queue is simple to establish, since it often corresponds to a classification by decreasing quantities of fuel demanded, the same does not apply to the number of passes to the refuelling hose, which must be minimized while still respecting the endurances of the aircraft to be refuelled before their actual refuelling starts. The method described, which may be implemented by a computer, automates the search for a refuelling sequence that satisfies the endurance requirements of the various aircraft to be refuelled, while still having the minimum number of passes to the refuelling hose by the aircraft in the squadron.

Abstract: A system and method for facilitating design and analysis of a selected component, subsystem, system, or structure of an aircraft. In one embodiment the system and method analyzes an aircraft's electrical power generation and distribution system (EPGDS). The system and method autonomously estimates all screen variables from two inputs, those being the number of engines and maximum takeoff weight, and further allows a designer to override any variables relating to the EPGDS of the aircraft, including the configuration of the EPGDS. Variables can be locked in by the designer such that the system will use those locked in variables in subsequent calculations. The invention enables the designer to quickly predict the system attributes of dependability cost, reliability and maintainability at the same time the normal mass properties of weight and body station center of gravity are estimated for a wide range of components and subsystems of the EPGDS, in addition to the overall EPGDS itself.

Abstract: An apparatus and method for preparing and dispensing a liquid deicer is disclosed. The apparatus and method allow deicer ingredients or precursors to be combined in an exothermic reaction to produce a heated deicer at the location where it will be used. In one implementation, potassium hydroxide and acetic acid are combined using the apparatus and method to make hot potassium acetate for use in numerous deicer applications, including deicing of airport runways.

Abstract: An unmanned air vehicle includes a singular rear landing gear wheel on the aft end of the fuselage. Port and starboard wings with rear facing propellers are retractable to the aft of the fuselage. Upon retraction, the propellers may freewheel and a reversible motor-generator is provided to convert the freewheeling propeller energy into electric power. Photovoltaic cells also provide electric power to the unmanned air vehicle. Port and starboard nose fairings are control surfaces for the vehicle. The port and starboard nose fairings also include landing gear wheels. A method of flying an unmanned air vehicle includes retracting port and starboard wings to achieve a ballistic dive.

Abstract: An aircraft and associated method of manufacture and operation. The aircraft can include a fuselage having a first portion and a second portion projecting upwardly from the first portion, with the first portion housing a passenger deck and the second portion being positioned above the passenger deck. A first wing can extend outwardly from the first portion of the fuselage and the second wing can extend outwardly from the second portion of the fuselage, with the second wing being positioned above and forward of the first wing. Accordingly, the fuselage can include a plurality of passenger doors simultaneously accessible to ground-based passenger load/unload equipment with at least one of the passenger doors positioned beneath the second wing.

Abstract: The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state.

Abstract: The present invention provides one pair or two pairs of horizontal propellers incorporated on the two opposite sides of an aircraft, which propellers by their rotating external blades create through their frontal shell opening a very strong frontal depression, stronger than their drag, providing an horizontal motion subsonic or supersonic, but their main advantage arise from the supersonic speed power requirement which is less than 20% of that of equivalent supersonic aircraft's, with consequent economy of construction, of maintenance and mainly in flight cost, and also a multiple in flight range and obviously respectively decrease of air pollution.

Abstract: An extremely large aircraft which is suitable for overseas cargo transport and which includes a fuselage defining a central storage cavity, a wing assembly defining a pair of wing storage cavities, an altitude control system, and a plurality of independently steerable landing gear units. The central storage cavity has a length, height and width of at least 100 feet, at least 16 feet and at least 24 feet, respectively. The wing assembly has a wingspan of at least 300 feet and is configured with a moderate aspect ratio to permit both ground-effect and high altitude operation. The altitude control system controls the aircraft in ground effect such that the aircraft is maintained at about a predetermined altitude. The landing gear units are coupled to the fuselage and are arranged in at least two discrete columns and at least ten discrete rows. The central storage cavity and the wing storage cavities are configured to receive cargo including intermodal re-usable cargo containers.