Abstract: An aircraft with a wide fuselage having a longitudinal axis, a left and right forward swept wing mounted well back on the fuselage, a tail section extending from the aft portion of the fuselage, a first and second brushless ducted fan with air accelerator ring stationary and integrated into the left and right lateral fuselage, a third brushless ducted fan with integrated air accelerator ring rotatable mounted to the aft tail portion, a solar turbine based external solar film applied on the fuselage and wing surfaces and lateral fan regenerative drive that powers all ducted electric fans, that powers one internal-mounted central master impeller motor, that powers a brushless electric motor that spins three supercharger impellers via pulley chains to enable all three air accelerator rings with super compressed forced air thrust, that recharges ultracapacitors for aircraft propulsion of persistent flight endurance targeted for 30 to 90 days.

Abstract: Secondary air flow is provided for a ducted fan having an engine core driving a fan blisk. The fan blisk incorporates a set of thrust fan blades extending from an outer hub and a set of integral secondary flow blades extending intermediate an inner hub and the outer hub. A nacelle provides a first flow duct for the thrust fan blades and a secondary flow duct carries flow from the integral secondary flow blades.

Abstract: A fixed-wing VTOL aircraft features an array of electric lift fans distributed over the surface of the aircraft. A generator is (selectively) coupled to the gas turbine engine of the aircraft. During VTOL operation of the aircraft, the engine drives the generator to generate electricity to power the lifting fans. Power to the lifting fans is reduced as the aircraft gains forward speed and is increasingly supported by the wings.

Abstract: A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, a pilot's compartment formed in the fuselage between the lift-producing propellers and substantially aligned with one side of the fuselage, a payload bay formed in the fuselage between the lift-producing propellers and opposite the pilot's compartment, and two pusher fans located at the rear of the vehicle. Many variations are described enabling the vehicle to be used not only as a VTOL vehicle, but also as a multi-function utility vehicle for performing many diverse functions including hovercraft and ATV functions. Also described is an Unmanned version of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles.

Abstract: An aircraft provides hovercraft power via fabric fans that produce lift for supporting the craft above an underlying support surface. Fabric fans are specially configured for maximum efficiency. In one embodiment, a helicopter utilizes the fan as part of a tail rotor assembly.

Abstract: Systems and methods for real-time efficiency and aircraft performance monitoring and delta efficiency calculations between various user- or system-selected phases of flight by determining an efficiency messaging index that gets translated into a messaging profile. That messaging profile is then used to obtain necessary flight and other information from multiple sources. The efficiency calculations and deltas can be used to determine real-time or post-processed benefits, which can then be used to optimize flight(s). Additionally, data is post-processed, which allows the calculation, storage and subsequent usage of efficiency coefficients to enhance the accuracy of the efficiency calculations. There are a number of ways to implement the architecture and order of processing.

Abstract: In exemplary embodiments of this invention, a programmable surface comprises an array of cells. Each of the cells can communicate electronically with adjacent cells in the array, can compute, and can generate either normal thrust or shear thrust. Distributed computing is employed. The programmable surface may cover all or part of the exterior of a craft, such as an aircraft or marine vessel. Or, instead, the programmable surface may comprise the craft itself, which may, for example, take the form of a “flying carpet” or “flying sphere”. The thrust generated by the programmable surface can be employed directly to provide lift. Or it can be used to control the orientation of the craft, by varying the relative amount of thrust outputted by the respective cells. The number of cells employed may be changed on a mission-by-mission basis, to achieve “span on demand”. Each cell may carry its own payload.

Abstract: The invention discloses an aircraft generating a larger lift from its interior. The fluid channel inside the aircraft communicates with the engine and the ports on the upper surface of the outer shell. With the powerful suction of the engine, the fluid on the upper surface of the outer shell is quickly sucked into the fluid channel via respective ports under conditions of long path, large area, high speed and low air pressure, which results in large lift from the interior of the aircraft. In the course of generating the lift, the fluid resistances of the fluid wall and the fluid hole are sucked into the fluid channel through the ports at the front and the surrounding area of the aircraft, then high-speed fluid is emitted from the rear port. This approach contributes greatly to the transformation of the existing aircraft. The unified big wing significantly improves the lift, the speed and the carrying capacity of the existing aircraft with lowered energy consumption.

Abstract: A method of unmanned aerial vehicle(UAV) flight includes providing horizontal thrust in-line with the direction of forward flight of the UAV(110)using at least one electric motor(120), providing primary vertical lift for the UAV(110) during the forward flight using a fixed and non-rotating wing(125), repositioning the at least one electric motor(120?)to provide vertical thrust during transition of the UAV(110)to vertical flight(A) for descent(E),landing the UAV(110)on a surface(270) using a vertical approach after the motor repositioning, and deploying an anchor(150) to secure the UAV(110)to a surface(270).

Abstract: A VTOL vehicle includes a forward rotor, an aft rotor and a fuselage, the forward and aft rotor lying in a longitudinal axis of the vehicle, with the fuselage located axially between the forward and aft rotors. The vehicle has an in-flight configuration wherein the forward rotor is tilted downwardly at a negative tilt angle relative to the fuselage and the aft rotor is tilted upwardly at a positive tilt angle relative to the fuselage.

Abstract: The lift, propulsion and stabilising system for vertical takeoff and landing aircraft of the invention consists of applying during vertical flight on, below or in the interior of the fixed-wing aircraft one or more rotors or large fans each one with two or more horizontal blades, said rotors are activated by means of turboshafts, turbofans or turboprops with a mechanical, hydraulic, pneumatic or electrical transmission, and the respective motors. Using lifting and/or stabilising and/or controlling fans and/or oscillating fins and/or air blasts. Placing the horizontal lifters near at least one end of the longitudinal axis and of the transverse axis of the aircraft. Generally said stabilising elements form 90° with one another and with the central application point of the rotor or application of that which results from the lift forces.

Abstract: A torque production vehicle includes a plenum body having a wall with a central port and a radial port formed within the wall, an impeller disposed within the plenum body to move air through the central port, an engine coupled to the impeller to rotate the impeller about an axis, at least one arm coupled to the plenum body, and a plurality of foils disposed in the radial port to direct air about the plenum body to provide a torque force about the plenum body.

Abstract: A system and method to control flight of an aircraft. The aircraft having an engine with a rotatably nozzle assembly configured to create forward propulsion and yaw control of the aircraft. The engine exhaust passing through the nozzle is redirected with a valve disposed within the nozzle. Lift is created with a lift system carried by the wing of the aircraft. Additional lift is created during flight with a retractable wing extension disposed within the wing of the aircraft.

Abstract: The invention is a modular vehicle having an air vehicle that can be coupled to cargo containers, land vehicles, sea vehicles, medical transport modules, etc. In one embodiment the air vehicle has a plurality of propellers positioned around a main airframe, which can provide vertical thrust and/or horizontal thrust. The propellers are mounted on supports which have an airfoil shape to generate additional lift. One or more of the propellers may be configured to tilt forward, backward, and/or side-to-side with respect to the airframe.

Abstract: A flying cycle apparatus comprises a fuselage and a pair of wings extending laterally from the fuselage to provide lift. A jet engine is mounted within the fuselage with the air intake thereof extending through the front of the fuselage. The jet engine has a jet exhaust extending through the rear thereof with one or more jet exhaust ports extending downwardly through the bottom thereof. The one or more jet exhaust ports provide vertical take off and landing capability. A pilot seat is positioned on top of the fuselage with the pilot seat being adapted to have a pilot's legs straddle the fuselage. The pilot seat if further adapted to have an occupant able to access to a control panel. The control panel has means for controlling the proportion of jet exhaust exiting from each of the jet exhaust and jet exhaust ports. The control panel further including a control joystick which allows the user to maintain a stable position during vertical take off and landing maneuvers and to turn and bank when flying.

Abstract: A multi-wing, airfoil fuselage aircraft that is capable of flying in a ground-effect mode includes a main airfoil fuselage wing, a fin that extends vertically from this wing, a pivot mount that is affixed to the fin, an auxiliary wing that connects to the pivot mount so as to allow its angle of attack to be adjusted and changed during different flight conditions, a main landing gear, an adjustable-length, stabilizing landing gear, assorted control surfaces that are movably affixed to the auxiliary wing and fin, and a ground-effect control system that is adapted to control the operation and movement of these control surfaces when the aircraft is flying in a ground-effect mode of flight.

Abstract: A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, a pilot's compartment formed in the fuselage between the lift-producing propellers and substantially aligned with one side of the fuselage, a payload bay formed in the fuselage between the lift-producing propellers and opposite the pilot's compartment, and two pusher fans located at the rear of the vehicle. Many variations are described enabling the vehicle to be used not only as a VTOL vehicle, but also as a multi-function utility vehicle for performing many diverse functions including hovercraft and ATV functions. Also described is an Unmanned version of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles.

Abstract: The present invention describes an aircraft having a rotating engine. The aircraft comprises a means for rotating the engine 360° to allow directional control of the aircraft via rotation of the engine's thrust output. The aircraft can further comprise a plurality of flap members located on the wings of the aircraft and in communication with the rotating gas turbine engine to further control and stabilize flight of the aircraft. The gas turbine engine of the aircraft can comprise a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating more thrust from a single engine.

Abstract: One embodiment of a Vertical Take-off and Landing (VToL) air-vehicle (FIG. 1.) having a horizontal rotor, a. providing lift and propulsion, and communicating at or near its centre to structural elements, or fuselage, b. Upon or within the fuselage structure is attached a platform, to which a payload, or occupant or pilot, d. is secured in such a manner as to permit a movement, or range-of-motion, of the payload, as a means of weight-shifting, or mass-balancing, of the vehicle for stability and control in flight. At least two planar elements, or descent-vanes, c.i & c.ii are connected to a structural element of the fuselage at a location which provides vertical and horizontal separation between the rotor and the descent-vanes, thus creating a tandem, biplane arrangement of two aerodynamically active elements which are aerodynamically balanced to provide stability and controllability in hovering flight, in forward flight, and in un-powered gliding and vertical descents.

Abstract: A torque production vehicle includes a plenum body having a wall with a central port and a radial port formed within the wall, an impeller disposed within the plenum body to move air through the central port, an engine coupled to the impeller to rotate the impeller about an axis, at least one arm coupled to the plenum body, and a plurality of foils disposed in the radial port to direct air about the plenum body to provide a torque force about the plenum body.

Abstract: An unmanned aerial vehicle (UAV) for making partial deliveries of cargo provisions includes a UAV having one or more ducted fans and a structural interconnect connecting the one or more fans to a cargo pod. The cargo pod has an outer aerodynamic shell and one or more internal drive systems for modifying a relative position of one or more cargo provisions contained within the cargo pod. Control logic is configured to, after delivery of a partial portion of the cargo provisions contained within the cargo pod, vary a position of at least a portion of the remaining cargo provisions to maintain a substantially same center of gravity of the UAV relative to a center of gravity prior to delivery of the partial portion. Other center of gravity compensation mechanisms may also be controlled by the control logic to aid in maintaining the center of gravity of the UAV.

Abstract: A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in least two dimensions relative to the horizontal during takeoff. An aerial vehicle which uses a rotating platform of engines in fixed relationship to each other and which rotates relative to the wings of the vehicle for takeoff and landing.

Abstract: The invention discloses an aircraft generating a larger lift from its interior. The fluid channel inside the aircraft communicates with the engine and the ports on the upper surface of the outer shell. With the powerful suction of the engine, the fluid on the upper surface of the outer shell is quickly sucked into the fluid channel via respective ports under conditions of long path, large area, high speed and low air pressure, which results in large lift from the interior of the aircraft. In the course of generating the lift, the fluid resistances of the fluid wall and the fluid hole are sucked into the fluid channel through the ports at the front and the surrounding area of the aircraft, then high-speed fluid is emitted from the rear port. This approach contributes greatly to the transformation of the existing aircraft. The unified big wing significantly improves the lift, the speed and the carrying capacity of the existing aircraft with lowered energy consumption.

Abstract: A tethered airborne electrical power generation system which may utilize a strutted frame structure with airfoils built into the frame to keep wind turbine driven generators which are within the structure airborne. The primary rotors utilize the prevailing wind to generate rotational velocity. Electrical power generated is returned to ground using a tether that is also adapted to fasten the flying system to the ground. The flying system is adapted to be able to use electrical energy to provide power to the primary turbines which are used as motors to raise the system from the ground, or mounting support, into the air. The system may then be raised into a prevailing wind and use airfoils in the system to provide lift while the system is tethered to the ground. The motors may then resume operation as turbines for electrical power generation. The system may be somewhat planar in that many turbines may have their rotors substantially in one or more planes or planar regions.

Abstract: A control system for a vehicle having plural control elements actuated at a single actuation point including a redundant electric actuator assembly including a control rod moveable linearly in two opposite directions mounting n electric motors, each motor having a controller and a feedback sensor for controlling linear movement of said rod, each motor contributing approximately 1/n of total control power required for adjusting one or more of said plural control elements, such that failure of any of said motors controllers or feedback sensors leaves sufficient predetermined minimum control power available for operating said control system.

Abstract: A vertical take off and landing (VTOL) aircraft, which may be a UAV aircraft, is disclosed. The VTOL is capable of vertical takeoff and landing, hovering and traveling of slow speeds. In addition the VTOL permits high-speed forward flight that allows for increasing the range of the aircraft.

Abstract: A fixed-wing VTOL aircraft features a forward-swept wing configuration coupled with a tripod arrangement of the engines (two forward, one rear), a forward-swept empennage or tail assembly, and a forward canard. The engines and wings/empennage are located relative to each other such that the engine outlet nozzles, which pivot downwardly to provide lift-off thrust, are minimally covered by the wings/empennage, if at all. The wings and empennage may include lifting fans to supplement lift and provide pitch and/or roll control.

Abstract: A power source for a vehicle includes at least one toroidal ring positioned in a housing. The toroidal ring includes magnetic material such as permanent magnets. The toroidal ring is magnetically levitated in the housing. A propulsion winding is coupled with the housing and energizable via a power signal to move the toroidal ring. Once moving, the magnetic material and the propulsion winding cooperate to produce electrical power and/or provide a stabilizing effect for the vehicle. In some applications, such as in an aircraft application, two or more toroidal rings may be used and rotated at counter directions so as to produce a predetermined net angular momentum.

Abstract: A VTOL vehicle includes a forward rotor, an aft rotor and a fuselage, the forward and aft rotor lying in a longitudinal axis of the vehicle, with the fuselage located axially between the forward and aft rotors. The vehicle has an in-flight configuration wherein the forward rotor is tilted downwardly at a negative tilt angle relative to the fuselage and the aft rotor is tilted upwardly at a positive tilt angle relative to the fuselage.

Abstract: A cross-flow propulsion mechanism for use in providing propulsion to an aircraft, includes a housing defining an inlet, a rotor compartment, and an outlet. The inlet is adapted to receive an inflow of air along a first longitudinal axis. The rotor is mounted within the rotor compartment and adapted to receive the airflow introduced into the housing through the inlet and rotate about a second longitudinal axis that is substantially perpendicular to the first longitudinal axis. The outlet is adapted to receive the airflow processed through the rotor and exhaust air along a third longitudinal axis that is substantially parallel to the first longitudinal axis. The propulsion mechanism can be applied in a personal aircraft, an STOL aircraft, and a hybrid automobile and aircraft.

Abstract: Rotorcraft including an airframe having a fuselage extending between a forward and an aft end and a powerplant producing high-pressure fluid. The rotorcraft includes a rotor assembly rotatably mounted on the airframe and having a plurality of rotor blades extending from a hub. Each rotor blade has a base, a tip, a leading edge extending between the base and tip, and a trailing edge extending between the base and tip opposite the leading edge. Each rotor blade has a jet adjacent its trailing edge in fluid communication with the powerplant by way of a fluid path. Each jet is adjustable between an open position in which the jet allows the high-pressure fluid from the power plant to pass through the jet and out of the rotor blade and a closed position in which the jet prevents the high-pressure fluid from passing through the jet and out of the rotor blade.

Abstract: A fixed-wing VTOL aircraft features a forward-swept wing configuration coupled with a tripod arrangement of the engines (two forward, one rear), a forward-swept empennage or tail assembly, and a forward canard. The engines and wings/empennage are located relative to each other such that the engine outlet nozzles, which pivot downwardly to provide lift-off thrust, are minimally covered by the wings/empennage, if at all. The wings and empennage may include lifting fans to supplement lift and provide pitch and/or roll control.

Abstract: A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.

Abstract: An aircraft the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following, air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers.

Abstract: The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust rather than a conventional propulsion system (i.e., a propeller or jet engine).

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 linear acoustic pulsejet (LAP) including a body having a first side panel and an opposing substantially parallel second side panel. A plurality of substantially parallel intercostals are orthogonally connected to each of the first and second side panels to create a plurality of pulsejet cells within an interior of the body. The LAP additionally includes a linear inlet cap over a top of the body that forms an air flow pathway (AFP) between the linear inlet cap and an exterior of an inlet section of the body. The linear inlet cap forms the AFP to have a substantially 180° turn between an exterior of the body and an interior of the pulsejet cells.

Abstract: The flying body includes a body (100a), a lift engine (102a1), and reaction control engines. The lift engine includes, a gas generator (200a1) for generating a turbine driving gas, a first thrust device (204a1, 208a1, 210a1) for providing a power by the turbine driving gas and exhausting a gas (20a1) in a predetermined direction to generate a first thrust force, a second thrust device (214a1, 218a1, 220a1) driven by the power to suck and compress a surrounding gas (21a1) and to accelerate and exhaust the surrounding gas substantially in a direction of a flow of the gas exhausted by the first thrust device to generate a second thrust force to be added to the first thrust force. The gas generator generates a gas by using a raw material (10, 11a) for gas generation carried by the flying body.

Abstract: A rotary wing aircraft is provided with longitudinally oriented counter-rotating rotors with circumferentially spaced variable pitch elongated rotor blades connected at their opposite ends to rotatable support rings mounted on the aircraft fuselage. Rotor downwash may be guided laterally and longitudinally by respective sets of moveable guide vanes. Propulsion may be obtained by an engine providing thrust and power take-off for driving the rotors. An auxiliary or second engine may be drivingly connected to the rotors.

Abstract: The aircraft incorporates a single ducted propeller. The fuselage Bridges over the ducted propeller assembly, and is shaped in a way that the incoming air can smoothly flow into the propeller area. The duct has an aerodynamically shaped frontal area, and an aft extension, which forms the tail section. The wings are attached to the side of the duct. The ducted propeller assembly also contains louvers, which run span wise, to redirect the outgoing air in horizontal direction. During vertical take-off or landing, the propeller has a horizontal plane of rotation, after take-off the whole craft entirely tilts forward approximately 26 degrees to transition into horizontal wing born flight. During vertical flight, the aircraft is controlled by control louvers installed inside the ducted propeller assembly in the propeller slipstream.

Abstract: A hover aircraft employs an air impeller engine having an air channel duct and a rotor with outer ends of its blades fixed to an annular impeller disk that is driven by magnetic induction elements arrayed in the air channel duct. The air-impeller engine is arranged vertically in the aircraft frame to provide vertical thrust for vertical takeoff and landing. Preferably, the air-impeller engine employs dual, coaxial, contra-rotating rotors for increased thrust and gyroscopic stability. An air vane assembly directs a portion of the air thrust output at a desired angle to provide a horizontal thrust component for flight maneuvering or translation movement. The aircraft can employ a single engine in an annular fuselage, two engines on a longitudinal fuselage chassis, three engines in a triangular arrangement for forward flight stability, or other multiple engine arrangements in a symmetric, balanced configuration.

Abstract: An air-based thrust recovery system for use in a powered lift platform utilizing fixed-pitch propellers is provided. The system utilizes an air compressor coupled to the drive motor of the platform and an on-board, high pressure tank for air storage. The fixed-pitch propellers are coupled to the primary drive system with over-running clutches, thus allowing the thrust recovery system to rotate the propellers faster than if driven solely by the primary drive system. Preferably the propellers are surrounded by air ducts. The thrust recovery system uses individually, or in combination, cold air jets mounted at the tips of the propellers, a circulation control system which blows out the leading or trailing edge of the propellers, and one or more perforated tubing segments surrounding at least a portion of the platform's air ducts.

Abstract: A VTOL aircraft includes a wing, a propulsion system, and an air dam. The propulsion system is located in a central void formed in the wing to cause air flow from an outer perimeter of the wing over the wing and down through the void to generate lift. The air dam is located over the central void to promote flow of air over the wing. The aircraft also may utilize sub-atmospheric pressure gas to reduce the relative weight of the aircraft.

Abstract: An aircraft having a vertical take-off and landing (VTOL) propulsion system. The aircraft includes a fuselage, the VTOL propulsion system, at least one forward thruster, a power source used for both the VTOL propulsion system and forward thruster, fore and aft wings and a plurality of spars attached to and spanning the space between the two wings. The VTOL propulsion system includes a plurality of VTOL cells (including a motor, motor controller, and propeller) attached in a spaced relation along each spar. The VTOL cells are used exclusively for vertical flight or hovering and are powered down as the aircraft develops forward flight velocity and corresponding wing lift. During forward flight the VTOL propellers are articulated to allow the aircraft to take on a low drag configuration. The present invention is suitable for use in manned or un-manned aircraft of any scale.

Abstract: An unmanned air vehicle comprises a fuselage that defines aerodynamic flight surfaces, an engine mounted to the fuselage having an engine shaft arranged to rotate about a longitudinal axis with respect to the fuselage, and a propeller mounted to the engine shaft so as to rotate to thereby provide thrust. The aircraft also comprises a gyroscopic stabilization member coupled to the shaft such that rotation of the engine shaft results in rotation of the gyroscopic member. Thus, there is more stability during the entire flight envelope. In one embodiment, the gyroscopic stabilization member is comprised of a ring that is attached to the outer ends of the blades of the propeller and the ring is also selected so as to have a mass that will result in the gyroscopic stabilization member having a sufficient angular momentum so as to gyroscopically stabilize the aircraft.

Abstract: A hover aircraft employs an air impeller engine having an air channel duct and a rotor with outer ends of its blades fixed to an annular impeller disk that is driven by magnetic induction elements arrayed in the air channel duct. The air-impeller engine is arranged vertically in the aircraft frame to provide vertical thrust for vertical takeoff and landing. Preferably, the air-impeller engine employs dual, coaxial, contra-rotating rotors for increased thrust and gyroscopic stability. An air vane assembly directs a portion of the air thrust output at a desired angle to provide a horizontal thrust component for flight maneuvering or translation movement. The aircraft can employ a single engine in an annular fuselage, two engines on a longitudinal fuselage chassis, three engines in a triangular arrangement for forward flight stability, or other multiple engine arrangements in a symmetric, balanced configuration.

Abstract: Personal Aircraft capable of vertical take-off and landing (“VTOL”) which comprises: (a) a fuselage having a front end, a rear end and two lateral sides, the fuselage having a central longitudinal axis extending from the front end to the rear end, between the two lateral sides; (b) at least one, and preferably two or more, ducted fans, each arranged in the fuselage between the front end and the rear end and between the two lateral sides, for providing vertical lift; and (c) at least one substantially horizontal wing attached to each side of the fuselage and extending outward with respect to the central longitudinal axis. The wings and fuselage of the aircraft are designed to provide a lift-to-drag (L/D) ratio during flight, when flying at an airspeed in the range of 50 to 100 MPH, of at least 4:1.

Abstract: A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a fixed wing and a fuselage with a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters, preferably integrated into the wing, on each side of the fuselage. The aircraft has a lift to drag ratio equal to or greater than 2. The thrusters, which are ducted fan units capable of providing a vertically upward force to the aircraft, are provided with such redundancy that the aircraft can hover with at one thruster inoperative on each side of the fuselage. At least one thruster on each side of the fuselage preferably comprises a “levitator” which creates lift from the airfoil-like air inlet as well as from the acceleration of air from inlet to outlet.

Abstract: An aircraft has a flying wing and two wingtip hulls installed on the wingtips of the flying wing. Both of the wingtip hulls contain lighter-than-air gas to generate static lift. These wingtip hulls not only contribute to lift-generating but also help the aircraft achieve roll stability and control. Forward propulsion systems are installed at the upper-front positions of the flying wing. When vertical and/or short take-off and landing (V/STOL) capability is required, one or more lift-fan propulsion systems can be installed on the flying wing. The lift-fan propulsion systems can either be driven by their own engines or by the power transmitted from the forward propulsion systems. Payload can be carried inside the flying wing or be hung under or held above the flying wing.

Abstract: A microjet based control system helps control the feedback loop that is created by an impinging jet of a STOVL aircraft. A plurality of microjets circumferentially encompass the outer periphery of the impinging jet and each issues a jet flow toward the jet flow created by the impinging jet. A control system is connected to the microjets for adaptively controlling the microjets based on various operating parameters collected by various input devices.