Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

Abstract: This invention relates to a small-sized radio controlled flying device propelled by a thermal engine (20) with pusher type airscrew (19) for remote sensing, said device enabling short take-off and landing and flying at maximum speed of 35 Km/h.

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: An amphibious airplane having an engine assembly mounted at a top center location in the fuselage, and a tail assembly having a horizontal fin in an elevated position so as to be in the propeller air stream. A lift augmenting aerodynamic surface is positioned at the top middle portion of the aircraft fuselage, with the propeller being at the concavely curved rear end of the lift augmenting surface. A pair of platforms are positioned on opposite sides of the fuselage at lower locations adjacent to a passenger section of the aircraft. These platforms are aerodynamically aligned and also have strakes extending forwardly therefrom along opposite sides of the fuselage. In cruise mode, the increased velocity imparted to the propeller air stream acts on the horizontal fin to exert a downward force, with the various forces of the airplane balancing each other.

Abstract: An improved aerobatic aircraft design having a first engine located in the nose portion of the fuselage and a second engine located in the tail portion of the fuselage. The thrust components of both the first and second engines are coaxial along the long axis of the fuselage. Both engines can individually provide sufficient power for the aircraft to takeoff, maintain altitude, and/or land.

Abstract: A motorized paraglider including a wheeled frame with a steerable nose wheel and a pair of casters arranged in a tricycle configuration. Each of the casters has a trailing wheel and a support bracket rotatably carrying the trailing wheel. A swivel mechanism is positioned atop the support bracket for permitting the trailing wheel to swivel about a substantially vertical axis. A stop is coupled with the support bracket for preventing the trailing wheel from swiveling inwardly. A spring is also coupled with the support bracket for normally urging the support bracket against the stop yet, under the influence of a sufficient lateral force, permitting the trailing wheel to swivel outwardly.

Abstract: A measurement-based method to control and optimize the performance of an airborne vehicle. The stability and control of the vehicle is modified to induce a response in the airborne vehicle as reflected by a plurality of response signals. Excitations signals having multi-term sinusoidal waveforms are generated and applied to control signals controlling one or more control effectors. A time domain response of each of the state variables, response signals, and control signals arising from the application of the excitation inputs to the control signals is then measured. These time domain responses are then transformed into frequency domain models. The effectiveness and vehicle stability and control derivatives may then be identified from the frequency domain models of the state variables, response signals, and control signals.

Abstract: A ground effect vehicle having a jet propulsion means as well as a propeller means. The ground effect vehicle is a watercraft combining the physical and hydrodynamic features of a trimaran, water jet propelled boat and air cushion vehicle that might be considered a hybrid. The vehicle is intended to operate as a multi-modal vehicle in the approximate speed range of 0-100 knots. The vehicle from at rest to operational speed obtains its lift at first from 100% buoyancy of trimaran hulls with jet propulsion, then from powered aerostatic lift from a captured air cushion achieved by means of forward movement achieved by an airplane type motor and propeller.

Abstract: An aircraft, preferably a large capacity passenger aircraft with two passenger decks, has a double-T tail assembly arranged on its tail section. The double-T tail assembly includes a double fin and rudder assembly and a tailplane and elevator assembly, and provides a significant increase in the usable passenger cabin space in the tail section of the aircraft. The double fin and rudder assembly has a U-shaped structure and comprises two upright stabilizer fins connected to each other by a horizontal torsion box that fixedly extends crosswise through the fuselage tail section within the floor of a cabin deck. The tailplane and elevator assembly is pivotably mounted on the upper tips of the two upright stabilizer fins in a double-T arrangement.

Abstract: The device for lift and to reduce forward resistance of aircraft consists of a converging input duct of truncated-cone-shaped or truncated-pyramid-shaped, arranged lengthwise inside the fuselage and inclined to the longitudinal axis, with the larger opening coinciding with the front fuselage contour or periphery of maximum cross-section, and reducing in bore backwards so that its generatrix or lower side coincides with the lower surface of the fuselage parallel to the aircraft's longitudinal axis and the generatrix or upper edge forms an acute angle with the aircraft's longitudinal axis. The narrowest end of the duct discharges into the input of the turbofan, UHD, etc. type drive engines which discharge through a rear outlet duct facing backwards with the rear end curved slightly downward.

Abstract: A shoulder launched unmanned reconnaissance system for providing overhead visual surveillance of remote targets is disclosed. The present system includes a reconnaissance air vehicle which may be fired from a portable launcher, accelerated to flight speed, and remotely controlled using a ground control system. The vehicle is flown to the target area to enable an onboard wide angle video system to transmit video images of the target by radio or fiber optics link to the ground control system for processing and display. The ground control system enables the reconnaissance vehicle to be flown to a recovery area and to descend in a stall mode after the flight is completed for maintenance prior to reuse. The air vehicle includes collapsible wings which are deployable after launch by a spring actuated mechanism. The fuselage of the air vehicle carries an onboard video camera, an electric motor, a battery, a global positioning system receiver, flight controls, and a data link system.

Abstract: An amphibious airplane having an engine assembly mounted at a top center location in the fuselage, and a tail assembly having a horizontal fin in an elevated position so as to be in the propeller air stream. A lift augmenting aerodynamic surface is positioned at the top middle portion of the aircraft fuselage, with the propeller being at the concavely curved rear end of the lift augmenting surface. A pair of platforms are positioned on opposite sides of the fuselage at lower locations adjacent to a passenger section of the aircraft. These platforms are aerodynamically aligned and also have strakes extending forwardly therefrom along opposite sides of the fuselage. In cruise mode, the increased velocity imparted to the propeller air stream acts on the horizontal fin to exert a downward force, with the various forces of the airplane balancing each other.

Abstract: An aircraft structure has an arrangement of aircraft components that provide inherent directional stability for a flight vehicle throughout an angle-of-attack range, even at very high angles-of-attack where conventional means of stabilization are ineffective. Components attached to an aircraft fuselage include a wing, horizontal stabilizers and vertical stabilizers. The wing is mounted forward of the horizontal stabilizers and is carried high on the fuselage. The horizontal stabilizer is mounted toward the rear of the aircraft and is attached near the bottom of the fuselage. The wing and horizontal stabilizers are joined on either side of the aircraft by forwardly sweeping aerodynamically shaped surfaces serving as the vertical stabilizers. The inclination of the vertical stabilizers preferably ranges from 45 degrees (top edge canted outboard) to 90 degrees (panels vertical).

Abstract: A Satellite Weather Modification System (SWMS) uses earth satellites to harness solar energy to modify the thermodynamics and composition of the earth's atmosphere. SWMS has three subsystems: The first subsystem includes a network of earth satellites called Satellite Engines (SEs) used to reflect solar energy and/or transform solar energy into other forms of energy beams discharged at specified locations. The media at these locations and the media through which the energy beams pass absorb these energies and change them into heat. The second subsystem includes a large network of Remote Sensing Devices (RSDs). These sensors are used to measure local media compositions, dynamic parameters and thermodynamic properties. Sensor measurements are fed back to the third subsystem, which includes a network of Ground Control Stations (GCSs). GCSs provide energy beam guidance by estimating each beam's characteristics and its aim point trajectory as functions of time.

Abstract: In an aircraft (1) according to the invention the engine drives a blower and the compressed air is used to increase the lift of the wing (18) and the canard (22) using jet flap propulsion.The airfoil profile has maximum thickness just forward of the control surface device (12) which has large included trailing edge angle and large leading edge radius. The control surface device hinge (17) is positioned close to the mean line (19) of the plane, and air slots (10) in the plane are blowing the control surface device.

Abstract: An aircraft of the type having twin booms (14): which connects the main wing (28) with two fin stabilizers (16) and an optional trim stabilizer (22) articulate to change aircraft direction and airspeed.

Abstract: A powered parachute or pendulum flying machine which includes a mechanism for shortening the chord length of the parachute wing, a mechanism for shortening the distance between the upper and lower airflow surfaces of the parachute wing, and a mechanism for adjusting position of the pilot module relative to the wing so as to adjust the center of gravity of the powered parachute. The mechanism for shortening chord length includes a tube running along the trailing edge of the parachute wing and control lines running from the tube to the pilot module. Pulling in the lines draws the tube forwardly and shortens the chord length. Preferably at the same time as the chord length is decreased, wing height is decreased by the mechanism for shortening the distance between the upper and lower airflow surfaces. Such is accomplished by collapsing a wall disposed between the upper and lower airflow surfaces to the pilot module.

Abstract: A large transport aircraft, for more than 400 passengers, with a first wing (3) extending from an intermediate point on the fuselage (1) and a second wing (4) extending from the rear of the fuselage, in proximity to the fin (2). The first wing comprises two halfwings (3a, 3b) swept backward, while the two halfwings (4a, 4b) of the second wing (4) are swept forward. The first and second wings lie on two vertically spaced planes and are connected to one another by respective aerodynamic surfaces (5a, 5b) rigid in their plane in correspondence with the respective halfwings lying on the same side of the fuselage. The first wing (3) can be either at a higher level than the second wing (4) or at a lower level.

Abstract: The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section, a lower section, and fabric ribs disposed therebetween. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded, extracted from an aircraft and deployed in the air.

Abstract: This disclosure provides a solar rechargeable aircraft that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Travelling at relatively slow speeds, and 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. Each of five sections of the wing has one or more engines and photovoltaic arrays, and produces its own lift independent of the other sections, 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. The aircraft is capable of a top speed of about ninety miles per hour, which enables the aircraft to attain and can continuously maintain altitudes of up to sixty-five thousand feet.

Abstract: A para-plane (parachute or parafoil airplane), ultralight, or the like is provided with a ducted propeller or fan to increase efficiency of the powerplant, thus reducing the size of the powerplant required. In addition, the duct may reduce propeller and/or engine noise and enhance safety for pilot, passengers and bystanders. Axial vanes may be provided upstream or downstream of the propeller within the duct to counteract the torque effect of the propeller. In another embodiment, a novel inflatable parafoil may be provided to reduce the effort required to initially inflate a prior art parafoil and reduce the incidence of ground strikes of the parafoil. The inflatable parafoil may be inflated with a buoyant gas such as helium or hot air to further reduce ground contacts and provide limited buoyancy to the aircraft.

Abstract: An unmanned aerial vehicle (UAV) has a toroidal fuselage and a rotor assembly having a pair of counter-rotating rotors secured in fixed coaxial combination with the toroidal fuselage to provide a vertical takeoff and landing (VTOL) capability for the UAV. One embodiment of the VTOL UAV is especially configured for ground surveillance missions by the inclusion of an externally mounted, remotely controllable stowable sensor subsystem that provides an azimuthal scanning capability and a predetermined elevation/depression scanning capability to accomplish the ground surveillance mission and a foldable landing gear subsystem to facilitate landing of the VTOL UAV at unprepared ground surveillance sites.

Abstract: An improved circular planform wing generally comprised of three different shaped wing sections which combine to form a peripherally circular planform body with a substantial central opening as determined by the wing sections interior trailing and leading edges. Twin vertical stabilizers, being parallel and substantially longitudinal in form, extend across the central opening about the longitudinal axis while being generally bisected by the common horizontal plane of the circular planform body. The vertical stabilizers are connected to the forward and aft sections of the circular planform body with a pusher propeller centrally positioned between the vertical stabilizers about the forward edge of the central opening. The propeller is connected forwardly to a power source which is connected to a cockpit and the forward areas of the circular planform body. Control surfaces are generally located about all interior and exterior trailing edges and can be further characterized as a low aspect ratio vehicle.

Abstract: A light-duty multipurpose aeroplane has a fuselage having a cabin at its center, a tail portion with a pusher propeller in a ring and a front portion with an all-swiveling horizontal "canard" type empennage. The wings of the aeroplane are articulated with low-mounted and high-mounted wing segments with opposite sweeps. The tips of the wing segments are connected with arrow-shaped pylons provided with heading control rudders.

Abstract: An unmanned, remotely controlled microwave-powered aircraft for use as a stationary communications platform. The aircraft is generally a flying wing with a large, flat inner wing having a rectenna on the underside. Rectennas may also be provided on the underside of the wings, the combined output from the rectenna being used to provide power to two electric motors housed within torpedo-shaped nacelles which drive two rear propellers. The rectenna converts a microwave signal at 35 GHz generated by a ground power station utilizing dual gyrotrons and a 34-meter diameter antenna dish. The aircraft has a preferred airfoil cross section throughout and is constructed of lightweight but strong materials in order to provide an enhanced flying time of several months. A power management and distribution system manages the DC power produced by the rectenna to supply power to the flight controls, propulsion system and payload.

Abstract: An aircraft has an airframe including a fuselage having major structural members made of a composite material. The airframe also includes a sweepforward main wing mounted on top of the fuselage and a T or cruciform tail on the fuselage. The aircraft has no canard. The aircraft has a pair of main landing gear units attached to the fuselage below the main wing, the main landing gear units having short strut assemblies which allow the crew and passengers to get on and off the aircraft easily. The sweepforward main wing allows a wide and comfortable cabin space to be created in the fuselage.

Abstract: An active flight control arrangement for an air vehicle that includes a split span vee fin tail control arrangement whereby inner and outer spans of each fin are independently operable to provide yaw, roll, and pitch control for an air vehicle in flight. The inner and outer spans of each fin are preferably not, but may be, in the same plane. An intermediate controllable span may also be provided between the inner and outer spans of each fin.

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

Abstract: An all-wing aircraft is disclosed that has novel foreplane and depending aftplane, a center wing section and outer wing panel flying surfaces which cooperate aerodynamically to eliminate the need for conventional fuselage and tail structures. The foreplanes are strategically located to create a positive pitching moment which is sufficient to significantly reduce elevator forces and to balance the negative pitching moment induced by the outer wing panels and the downwardly extending aftplane units that provide static and dynamic pitch and yaw stability. At the same time, the foreplane structures serve as an unobstructed means to mount engines forward on the airframe to established a forward empty center of gravity. Additionally the aftplane structure serves as a means to mount main landing gears, elevators, ruddervators and to provide structural means for interconnecting outboard wing sections of the airplane.

Abstract: Disclosed is a parawing with an automatic canopy withdrawing mechanism having a canopy, a frame to which the canopy is fastened and on which a pilot can be carried, a propeller mounted on the frame, and a plurality rows of suspension lines interconnecting the canopy and the frame. Also mounted on the frame is an automatic canopy withdrawing mechanism including a reel which may be operated to pull back the suspension lines for withdrawing the canopy. Further, a front pulling rope interconnecting the reel and two rows of suspension lines near the leading edge of the canopy, a rear pulling rope interconnecting the reel and the trailing edge of the canopy, and a plurality of guide rollers for guiding the movement of the front pulling rope and the rear pulling rope are provided so that the suspension lines and the canopy may be withdrawn by the automatic canopy withdrawing mechanism. With the canopy and the suspension lines being withdrawn.

Abstract: A glider, comprising a tubular body open at each end and having a leading edge and a trailing edge, has a two-ring frame assembly disposed about the perimeter of the leading edge to provide body shape and rigidity. A two-ring frame assembly comprises a base ring and a clamping ring configured to matingly engage the base ring. The base ring is placed about the inner perimeter of the leading edge of the tubular body and the clamping ring is placeable about the outer perimeter of the leading edge of the tubular body to retain the tubular body between the base and the clamping ring when the rings are matingly engaged.

Abstract: Load lines connect chordwise spaced portions of a ram air inflated, airfoil canopy to spaced anchors connected to a pilot supporting vehicle frame on which a forward thrust producing unit is removably mounted. The geometry of the assembled aircraft enhances take-off inflation of the canopy, establishes a stable flight frame when airborne, and enables simple engine throttle control of the thrust producing unit to regulate climb, descent and level flight. Common control is applied for both ground steering of the vehicle frame and air-borne steering of the canopy.

Abstract: Load lines connect chordwise spaced portions of a ram air inflated, airfoil canopy to spaced anchors connected to a pilot supporting vehicle frame on which a forward thrust producing unit is removably mounted. The geometry of the assembled aircraft enhances take-off inflation of the canopy, establishes a stable flight frame when airborne, and enables simple engine throttle control of the thrust producing unit to regulate climb, descent and level flight. Common control is applied for both ground steering of the vehicle frame and airborne steering of the canopy.

Abstract: A light aircraft having a parachute-wing, a single propeller, and means for controlling the direction and speed of the aircraft by simple control lines to the canopy. The carriage is supported by at least two support lines which are secured at attachment points spaced apart laterally with respect to the fore and aft direction of the craft. By ensuring that the support lines are of different lengths a side-to-side suspension bias is created which compensates for the propeller torque reaction. This is a permanent adjustment which allows the aircraft to be balanced so that control of flight may be effected without difficulty. Preferably, the carriage is constructed to use a longitudinal base strut on which a foldable tricycle under carriage is mounted. An upright strut is pivotally mounted to the base strut. The frame of the pilot's seat is used as an integral structural member which rigidly links the base strut to the upright strut in the running condition. The two struts and the sear frame form a triangle.

Abstract: An ultralight aircraft having a generally rectangular, swept-back, single-surface wing. The wing, which is formed by fabric mounted on exposed spars and ribs, has a reflex profile to provide pitch stability which is further augmented by horizontal stabilizers projecting rearwardly from the wing adjacent the tips. Roll and yaw control are provided by a pair of rudders pivotally mounted at each wing tip. The forward ends of the rudders pivot inwardly to alter the magnitude of the wing's lift. The rudders pivoted simultaneously act as spoilers and speed brakes controlling the rate of descent. Pivoting one of the rudders individually moves the center of lift for one wing inwardly and increases the drag of that wing to roll the aircraft into that wing. The rudders tilt upwardly and outwardly in a dihedral configuration to provide roll stability. Stationary end plates mounted at each wing tip adjacent the rudders provide yaw stability.

Abstract: A VTOL/STOL aircraft of simple design and construction. The aircraft has a central semi-venturi shaped airfoil surface defining a channel integral to the fuselage, a canard system and a horizontal stabilizer system at the respective ends of the channel, and a propulsion unit for accelerating airflow through the channel to achieve stable and easily maneuverable flight.

Abstract: An airplane having a number of airfoils including a delta nose wing, a winglet, a midspan wing, a V-tail delta wing without an upswept fuselage, a vertical tail and upper body stabilizer. These airfoils are coupled with a system of four jet engines and an aft center of gravity. Full control of the airplane is possible under high maneuverability conditions, extremely high accelerations and at large angles of attack. The delta nose wing creates swirling vortices that contribute substantially to the lift of the nose section. The winglet, an extension of the delta nose wing, allows the turbulent wake from the leading edge of the delta nose wing to flow over its upper surface to create additional lift while the midspan wing causes the turbulent flow over its upper surface to form a turbulent wake at its leading edge. The V-tail delta wing with a V-shaped underside and blunt leading edge gives additional lift and control to the airplane.

Abstract: In a lightweight aircraft having a principal longitudinal load-carrying member, a wing structure mounted on the load-carrying member, a tail rudder and elevator assembly mounted on the load-carrying member, a propeller mounted on the load-carrying member for rotation about the member's longitudinal center line, an engine mounted on the load-carrying member, and means drivingly connecting the engine to the propeller.

Abstract: A ducted propeller aircraft from which visibility is excellent and which is capable of operating quietly and efficiently has a propeller shroud which serves as a primary load path to pass bending and torsional stresses to which the mainplane is subject in use between the portions of the mainplane either side of the shroud, the shroud defining a duct which is unimpinged upon by any portion of the turbulent airflow emanating from the mainplane.

Abstract: A kit for converting a motorcycle to an aircraft or airborne vehicle includes a glider type parachute with fore and aft lines for connecting to and supporting a motorcycle, in a balanced position, with a propeller system including counter rotating propellers mounted on a pair of concentric shafts and driven by rollers drivingly engaging the rear drive wheel of the motorcycle. Directional control by means of control lines attached to the rear of teeter bars suspended below the wing and connected by directional control lines to outriggers attached to the front wheel structure of the motorcycle.

Abstract: The invention is an improved method and device for utilizing the principles of lift achieved through the dynamic physics of the airfoil. In the case of the present invention, the airfoil utilized is a parafoil. The parafoil of the present invention is a multi-layered or multi-tiered arrangement to provide an improved directly vertical lift without the less efficient angular lift of the common parafoil horizontal dispersement of lifting power. The present parafoil vertical lift mechanism consists of a plurality of parafoils assembled in a multi-layered vertical configuration, a plurality of positioning stabilization rods to maintain the basic vertical spacing of the plurality of parafoils for an immediate ballooning effect at the start for take-off, a lifting frame suitably affixed to the assembled plurality of parafoils, a plurality of stabilization tether lines, at least one counter-drag tie line, and a load connector for suitably removably affixing the load to be lifted to the lifting frame.

Abstract: A fixed wing powered light aircraft has a fuselage formed by laterally spaced longitudinal tubular booms supporting a twin vertical stabilizer and rudder assembly and a horizontal stabilator. A tubular framework pylon structure is secured to the fuselage booms for supporting a propulsion engine driving a propeller arranged in a pusher configuration. An open cockpit is partially shrouded by a streamlined nose cowl and longitudinal cockpit side panels which meet along the longitudinal center line aft of the pylon. Two piece removable wing root fairings minimize drag and streamline airflow approaching the empennage. The aircraft is adapted for military applications with adjustable support brackets for aiming plural missile launch tubes on each wing. A pilot seat is mounted on an adjustable support structure comprising in eccentric arm and track for supporting longitudinal seat support rails.

Abstract: A model aircraft of the flying canopy type employs a cloth canopy wing of the type shown in the U.S. patent of Jalbert, U.S. Pat. No. Re. 24,427, and includes a platform, a power plant on the platform, and a plurality of upstanding pylons mounted on the platform which attach to the triangular gussets of the Jalbert wing for supporting the wing in superimposed relation over the platform.

Abstract: An assembly for mounting a propeller, which is driven by an aircraft engine, on a longitudinal member of a lightweight aircraft. The assembly includes a sleeve positioned about the longitudinal member, and a pair of opposed adjustable cups securing the sleeve at its ends longitudinally relative to the longitudinal member. A rotating mechanism mounted to the propeller, rotatable about the sleeve, and driven by the aircraft engine rotates the propeller concentrically about a longitudinal axis of the longitudinal member. Suitable bearings are disposed between the rotating mechanism and the sleeve and the rotating mechanism rotates on these bearings. Vibration dampening rings are placed between the cups and the sleeve and dampen the vibration transmitted between the rotating mechanism and the longitudinal member.

Abstract: An aircraft of the hang glider type includes a wing (11) with a keel (12) in its plane of symmetry serving as a fastening point for a trapeze and a harness by which the pilot is suspended below the wing, the trapeze and the harness being disposed in conventional manner for suspending a pilot in the prone position. The invention provides a motor propeller unit (15) which is mounted in such a manner as to be movable at least in the longitudinal direction along the keel axis under pilot control, thereby enabling the pilot to displace both the center of gravity of the motor propeller unit and his own center of gravity between an extreme forward position ahead of the center of lift of the wing and an extreme rearward position behind the center of lift (1).

Abstract: A free flyable structure includes a wing formation (2) including an inflatable container of such form that when it is inflated the container (2) has an aerofoil shaped cross-section whereby relative displacement between the container and surrounding air enables free flight conditions. A substantially rigid means (19) carries the pay load from the wing formation (2). Flight path control of the flyable structure includes producing relative displacement between the load and wing formation. Additional flight path controls may be used. A canard wing assembly (82) is suggested. The structure is power driven and in the disclosure a power unit (85) having a propeller (86) is proposed.

Abstract: An airplane airframe having wings connected to the fuselage by spars of smaller cross section than the wings. Movable winglets may be provided at the outboard ends of the wings. The fuselage may be an airfoil shaped lifting body structure with longitudinal splines at its edges. The splines may be movable in flight, and may be provided with flaps which are also movable in flight so that the splines can be readjusted to alter the aerodynamic characteristics of the airframe during flight. The undersurface of the fuselage may include cambers symmetrical about the center plane of the fuselage.

Abstract: An ultralight aircraft of lightweight minimal construction includes a collapsible Rogallo type wing from which a hang cage is suspended by a main hinge assembly. The wing includes a longitudinal keel of lightweight tubular construction, leading edge members and a cross brace. A flexible lifting panel is secured along and between the wing members to define a lifting surface. The hinge includes a pitch hinge bracket having an upper longitudinal sleeve in which the keel is clamped. A ball joint connection secured to the bracket is connected to upwardly extending hang cage struts by means of hinge connecting plates to permit free rotation of the wing about a spanwise axis extending longitudinally through the cross brace.

Abstract: An aircraft having a fuselage provided with an internal duct extending longitudinally therethrough to provide an internal wing for the craft, the internal duct having the forward end open for receiving an air stream therethrough and the aft end thereof open for discharge of the air stream therefrom, the internal contour of the duct being alterable in accordance with required operational conditions for the flight of the craft, and a plurality of control flaps and/or vanes provided at the aft end of the duct for proving operational controls for the craft in the manner of a more conventional external wing craft.

Abstract: An ultra-light aircraft of light-weight minimal construction includes a rigid wing from which a hang cage is suspended by a main hinge assembly. Rotation of the wing without pilot intervention induced by positive or negative wind gusts striking the wing causes the angle of pitch between the wing and hang cage to vary via the hinge so that the wing presents a relatively constant angle of attack to relative wind enabling the aircraft to be essentially stall free during flight. Twist and/or dihedral of the wing is maintained by first and second sets of tensioned cables or landing wires connecting leading and trailing wing edges to a kingpost projecting upward from the wing, and by first and second sets of flying wires connecting the wing to the hang cage. Each first and second set of flying wires is a stress distributing arrangement including a pair of tubes respectively connected at upper ends thereof to leading and trailing wing edges and at lower ends to a plate suspended between the wing and hang cage.