| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244120100 | Airplane and fluid sustained | 73 |
| 20090065631 | EMISSIONLESS SILENT AND ULTRA-EFFICIENT AIRPLANE USING CFJ AIRFOIL - 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). | 03-12-2009 |
| 20090084889 | Aircraft having a reduced acoustic signature - 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. | 04-02-2009 |
| 20100051740 | VTOL VEHICLE WITH COAXIALLY TILTED OR TILTABLE ROTORS - 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. | 03-04-2010 |
| 20100116924 | STABILIZING POWER SOURCE FOR A VEHICLE - 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. | 05-13-2010 |
| 20100270419 | REDUNDANCIES AND FLOWS IN VEHICLES - 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. | 10-28-2010 |
| 20110001000 | AIRCRAFT GENERATING A LIFT FROM AN INTERIOR THEREOF - 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. | 01-06-2011 |
| 20110084162 | Autonomous Payload Parsing Management System and Structure for an Unmanned Aerial Vehicle - 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. | 04-14-2011 |
| 20110101155 | TORQUE PRODUCTION VEHICLE AND METHOD - 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. | 05-05-2011 |
| 20110163198 | Safety flier--a parachute-glider air-vehicle with vertical take-off and landing capability - One embodiment of a Vertical Take-off and Landing (VToL) air-vehicle (FIG. | 07-07-2011 |
| 20110168832 | Multi wing aircraft - 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. | 07-14-2011 |
| 20110168833 | AIRCRAFT HAVING A ROTATING TURBINE ENGINE - 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. | 07-14-2011 |
| 20130099048 | Unmanned Aerial Vehicle and Method of Operation - A method of unmanned aerial vehicle(UAV) flight includes providing horizontal thrust in-line with the direction of forward flight of the UAV( | 04-25-2013 |
| 20140158815 | Zero Transition Vertical Take-Off and Landing Aircraft - A zero transition vertical take-off and landing (VTOL) aircraft, which is stable in all levels of flight, especially the transition phase from vertical to horizontal flight. The zero transition VTOL aircraft is capable of achieving both vertical and horizontal flight without changing the positioning of thrusters, such as through the use of tiltable or rotatable nacelles or wings. Rather a front thruster assembly and a rear thruster assembly are positioned at specific angles in relation to each other along at least one fuselage in order to generate the desired ratio of vertical to horizontal thrust. At least one wing is also positioned at a specific wing angle in order to achieve a desired angle of attack when in horizontal flight. The attitude of the zero transition VTOL aircraft can be controlled through the use of differential thrust alone, or in conjunction with control surfaces. | 06-12-2014 |
| 20150048200 | HIGH-SPEED VTOL AIRCRAFT - This invention can take-off like a helicopter and then roll forward as a single unit to fly faster and further than any conventional helicopter. Just like the seats in a Ferris wheel, the payload of passengers or freight can remain upright and comfortable as this aircraft rotates from take-off to fast forward and back to landing mode. Prior inventions claiming similar performance generate lift for take-off and landing by relative rotation of major aircraft components or by vectoring a thrust through large angles of deflection which produces inherently unstable flight characteristics. This invention requires neither rotation of major assemblies nor highly vectorable thrust, making it simpler and more reliable than the aircraft with major rotating assemblies and more stable and efficient than aircraft relying on vectored thrust for lift. | 02-19-2015 |
| 20150360775 | VERTICAL TAKE-OFF AND LANDING FLIGHT VEHICLE - The invention provides, in vertical and oblique lift and descent, horizontal flight and hovering, for maintenance of attitude of an airframe, using a single wing, large blades and a single large rudder, under divergent airflow. To change attitude in hovering from horizontal to vertical, in case three wings are provided on the airframe, the output of an engine mounted on a wing at the front part of the airframe is increased, the lifting power is increased and the front part of the airframe rises from the horizontal. Then output of an engine of the rear part of the airframe is reduced, and the lifting power of the rear part of the airframe is diminished. When an angle of the airframe is increased, a second wing located in the central part of the airframe is moved to a 90 degrees vertical direction and an output occurs so that the altitude of the airframe does not drop. | 12-17-2015 |
| 20150367932 | Delta M-Wing Unmanned Aerial Vehicle - An aerial vehicle compromising of a streamline delta wing structure, an M-wing structure accomplished through dihedral and dropped wing tips, and a variable incidence tail. The structure of the vehicle produces high lift and drag while maintaining stability and control at high angles of attack. | 12-24-2015 |
| 244120200 | Circular | 8 |
| 20080223979 | AERODYNAMIC LIFTING DEVICE AND AIRBORNE CRAFT - An airborne craft is provided comprising an aerodynamic lifting device having a radial drum fan and a thrust vectoring shroud. The radial drum or vertical axis fan comprises a fan with a rotor, the rotor having a rotational axis and comprising a plurality of rotor blades disposed in an annular ring about the rotational axis and a driving means for the rotor such that, on operation of the driving means, lift is generated. | 09-18-2008 |
| 20090242689 | CRAFT HAVING A ROTATABLE FLUID PROPULSION DEVICE - The invention arose in the design of vertical takeoff craft where a bladed rotor directs a jet of fluid over a curved surface so that the jet is turned from a radial direction towards an axial direction to create lift. These craft have stability problems when an attempt is made to hover close to the ground or to a vertical surface and for this reason such craft have been confined to paper proposals and unsuccessful experimental models. In accordance with the invention, the craft is designed so that its rotor and other moving parts have a large angular momentum. In this way, a gyroscopic effect is achieved, sufficient to give positive stability to the craft, eliminating the aforementioned problem. | 10-01-2009 |
| 20100147993 | HYBRID POWER FOR DUCTED FAN UNMANNED AERIAL SYSTEMS - A propulsion system for a vertical take-off and landing ducted fan aerial vehicle is provided, the propulsion system comprising an internal combustion engine, an electric motor that comprises a motor generator, a motor drive and a battery. The motor drive and battery are integrated into the aerial vehicle and provide power to the ducted fan aerial vehicle. The electric motor may comprise a ring motor generator. In operation, this dual propulsion system serves as a weight-efficient option to allow for two sources of power on a ducted fan unmanned aerial vehicle. | 06-17-2010 |
| 20100270420 | CIRCULAR FIXED WING VTOL AIRCRAFT - An aircraft used for short distance flights may have very different design characteristics than VTOL designs of conventional aircraft. The aircraft defined herein is radically different from existing aircraft and is intended to be used for short distance flights. This aircraft is horizontally circular (or at least symmetrical) with a thrust generating power source in the center. The structure around the power center has a cross sectional shape like a conventional airplane wing, such that air flowing over the top surface generates lift. This main structure is shaped like a donut and acts as both the aircraft fuselage and wing. The aircraft also may utilize lighter-than-air gas within the body structure or in attached external bladders to reduce the relative weight of the aircraft, thereby artificially increasing the power to weight ratio and improving operational efficiency. | 10-28-2010 |
| 20100294878 | FLYING BODY - A flying body is provided with: an air blower including an upper blower equipped with rotating blades for pumping air in an axial flow direction and a lower blower equipped with rotating blades for pumping the air pumped from the upper blower in a centrifugal direction, with the upper blower and the lower blower disposed on the same axis and rotating in the opposite directions to each other; and a fixed wing having at least an inner surface formed in a skirt shape to provide a circular conical surface, and mounted concentrically with the air blower. The lower blower is mounted below an inner top face of the fixed wing such that the air pumped and sent in the centrifugal direction strikes the circular conical surface (T) of the fixed wing. The top portion of the fixed wing has no opening except for a passage through which an axial flow is pumped from the upper blower to the lower blower. | 11-25-2010 |
| 20110215191 | Vortex left platform - Apparatus and method of using a generated vortex contained in a cylindrical enclosure to generate aerodynamic lift. | 09-08-2011 |
| 20120241552 | Damage Resistant Aircraft - An aircraft which an inflatable, indestructible self righting “Beach Ball” with almost helicopter performance. A means to make a ball that can roll. also a flying machine that can take off and land vertically. A means of making a helicopter less dangerous. A means of making a helicopter damage resistant. A method to fold up an aircraft like an umbrella. | 09-27-2012 |
| 20130062454 | LIFT GENERATING DEVICE - A lift generating device is provided enabling vertical flight. The lift generating device includes a first revolution structure having a funnel shape and a second revolution structure having a funnel shape. Each revolution structure includes a circular open surface and an open stem. The second revolution structure is attached to the first revolution structure by a plurality of connectors so as to form a gap between the first revolution structure and the second revolution structure. A propeller is coupled to an open stem at a bottom end of the first revolution structure and a motor is operatively connected to the propeller to provide power for the propeller to suction air into the lift generating device. | 03-14-2013 |
| 244120300 | Dual propulsion | 9 |
| 20090127379 | VTOL AIRCRAFT WITH FORWARD-SWEPT FIXED WING - 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. | 05-21-2009 |
| 20100224720 | FAST HYBRID HELICOPTER WITH LONG RANGE WITH LONGITUDINAL TRIM CONTROL - A hybrid helicopter includes an airframe provided with a fuselage and a lift-producing surface together with stabilizer surfaces and a drive system including:
| 09-09-2010 |
| 20100224721 | VTOL AERIAL VEHICLE - 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. | 09-09-2010 |
| 20110168834 | DUCTED FAN VTOL VEHICLES - 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. | 07-14-2011 |
| 20110284683 | Amphibious Large Aircraft Without Airstairs - An amphibious large aircraft without airstairs is provided. The fuselage ( | 11-24-2011 |
| 20120119016 | Modular Flight Vehicle With Wings - 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. | 05-17-2012 |
| 20120234968 | AIRCRAFT WITH FREEWHEELING ENGINE - An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | 09-20-2012 |
| 20130062455 | HYBRID JET/ELECTRIC VTOL AIRCRAFT - 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. | 03-14-2013 |
| 20160129998 | UNMANNED AERIAL VEHICLE CONFIGURATION FOR EXTENDED FLIGHT - This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pushing motor and propeller assembly that is oriented at approximately ninety degrees to one or more of the lifting motors. When the UAV is moving horizontally, the pushing motor may be engaged and the pushing propeller will aid in the horizontal propulsion of the UAV. | 05-12-2016 |
| 244120400 | Thrust tilting | 23 |
| 20090084890 | Aircraft - An aircraft, in particular a VTOL craft, comprises a fuselage supporting at least a pair of wings. According to the disclosure, several propeller devices are connected to the fuselage and optionally to the pair of wings. The propeller devices may be pivoted about pivot axes independently of each other. The pivot axes are at an angle ≠0° to each other. | 04-02-2009 |
| 20100181414 | Personal transportation vehicle - This is a Vertical/Short Takeoff and Landing (VSTOL) vehicle for personal transportation of at least one person, to a destination. The four main engine-driven rotors or propellers are pivot-mounted and can be varied in angular position. The main engines are operated by a vector-control system permitting the thrust of the vehicle engines to change from horizontal to vertical and vice versa for takeoff, forward or backwards flight, and landing procedures. This vehicle is also capable of hovering, ascending, and descending during flight. The other four rotors or propellers are mounted at fixed positions, two at the rear, and two at the front, of the vehicle. The vehicle also consists of landing gear of virtually any type. | 07-22-2010 |
| 20110042508 | CONTROLLED TAKE-OFF AND FLIGHT SYSTEM USING THRUST DIFFERENTIALS - 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. | 02-24-2011 |
| 20110042509 | Lightweight Vertical Take-Off and Landing Aircraft and Flight Control Paradigm Using Thrust Differentials - An 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 at least two dimensions relative to the horizontal during takeoff, and which may also control regular flight in some aspects by the use of differential thrust of the engines. | 02-24-2011 |
| 20110042510 | Lightweight Vertical Take-Off and Landing Aircraft and Flight Control Paradigm Using Thrust Differentials - An 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 uses a rotating platform of engines in fixed relationship to each other and which rotates relative to the main body of the vehicle for takeoff and landing. 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 at least two dimensions relative to the horizontal during takeoff, and which may also control regular flight in some aspects by the use of differential thrust of the engines. | 02-24-2011 |
| 20110089287 | Power assisted toy flying device - A power assisted flying device is disclosed, wherein a vector control apparatus is used to help lift and fly a kite or kite-like object. Two servo motors may be used to move a gimbal mechanism to which the control motor is attached. Another kite-like object is disclosed wherein there are brackets to directly connect servos and propulsion motors to a kite. An added structure is shown to quickly connect and disconnect a vector control apparatus from a kite frame. In addition, new kite frame fittings are disclosed and a vector control apparatus to lift and fly a rotating kite. | 04-21-2011 |
| 20110089288 | POWER ASSISTED TOY FLYING DEVICE - A power assisted flying device is powered via a vector thrust control apparatus supporting the motor where the vector thrust control apparatus includes a gyratory group that allows the motor to pivot up and down and from side to side. At least two servo motors are attached to the vector thrust control apparatus to move said motor up and down and from side to side. Alternatively, the flying device may incorporate a non-rotating outer ring and a rotating inner ring disposed around a shaft. At least two servo motors are connected to the non-rotating outer ring and the rotating inner ring in relation to the rotational axis. At least two linkage rods connect between the rotating inner ring and the propeller. Tilting of the non-rotating outer ring is transmitted to the propeller to effectuate at least one of cyclic pitch modulation or teetering hub modulation of the propeller. | 04-21-2011 |
| 20110168835 | Three Wing, Six Tilt-Propulsion Units, VTOL Aircraft - A vertical takeoff and landing aircraft having a fuselage with three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are vertical for vertical flight, and horizontal for forward flight. The aircraft wings are placed such that the rear wing is above the middle wing which is placed above the front wing. The placement of each of the propulsion units relative to the center of gravity of the aircraft about the vertical axis inherently assures continued stability in vertical flight mode, following the loss of thrust from any one propulsion unit. The placement of the propulsion units, viewing the aircraft from the front, is such that each propulsion units' thrust wake does not materially disturb the propulsion unit to its rear. When engine driven propellers or rotors are utilized, flapped wing panels are attached outboard of the forward and/or rearward propulsion units to provide yaw control during vertical flight. | 07-14-2011 |
| 20110284684 | HIGH TORQUE AERIAL LIFT (HTAL) - An aircraft includes a housing and a powerplant coupled to the housing and configured to rotate a drive shaft around its longitudinal axis. The aircraft may include at least one lift fan assembly coupled to its housing and including a gearbox and at least one lift fan. The gearbox is coupled to the drive shaft and configured to transfer rotational energy from the drive shaft to the lift fan or fans. The lift fan assembly or assemblies may include at least two pivot assemblies, the first pivot assembly configured to pivot the lift fan assembly on a first axis and the second pivot assembly configured to pivot the lift fan assembly on a second axis that is substantially perpendicular to the first axis. | 11-24-2011 |
| 20110315809 | THREE WING, SIX-TILT PROPULSION UNIT, VTOL AIRCRAFT - A vertical takeoff and landing aircraft having at least three wings and at least six propulsion units, each of which are located radially from two adjacent propulsion units, by equal or substantially equal angles. The at least six propulsion units together being located symmetrically, or at substantially symmetric positions, about the approximate center of gravity of the aircraft, when viewed from above. A vertical stabilizer may or may not be employed. If no vertical stabilizer is employed, yaw control during horizontal flight may be achieved through differential thrust using the at least six propulsion units. Yaw control during vertical flight may be provided by a plurality of yaw control panels. Absent yaw control panels, yaw control during vertical flight may be provided using differential propulsion unit tilt angles. | 12-29-2011 |
| 20120043413 | APPARATUS AND METHOD FOR VERTICAL TAKE-OFF AND LANDING AIRCRAFT - An aircraft may have a fuselage having a longitudinal axis, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, a first ducted fan rotatably mounted to the left wing, a second ducted fan rotatably mounted to the right wing, and an engine disposed in the fuselage which is connected to the first and second ducted fans. | 02-23-2012 |
| 20120091257 | AIR VEHICLE - In embodiments, a system and method for providing propulsion and control to an air vehicle, and for operating the vehicle, include at least three propulsion units that provide vertical thrust for vectored thrust flight, in which at least one or two of the propulsion units also provide thrust for vectored thrust cruising or aerodynamic flight by suitably tilting the respective propulsion units for changing the thrust vector thereof. At the same time, the three or more propulsion units are operated to generate controlling moments to the air vehicle about three orthogonal axes, pitch, roll and yaw, during vectored thrust flight (hover, cruising, etc.) or during aerodynamic flight for controlling the vehicle. | 04-19-2012 |
| 20120298789 | Aircraft - An aircraft comprising a fuselage and one or more propulsion motor devices attached to the fuselage. Each of the propulsion motor devices further includes means for controlling it with regard to its thrust amplitude and orientation about two axes of rotation. Each motor device can be controlled independently of the other motors. The aircraft may further include rudder and elevation means. The aircraft includes four propulsion motor devices, each motor generally located on the perimeter of the | 11-29-2012 |
| 20140061368 | VERTICAL/SHORT TAKE-OFF AND LANDING PASSENGER AIRCRAFT - The present aircraft comprises a pair of spaced apart and parallelly disposed fuselages, a pair of wings, each wing is attached to an outer portion to each fuselage, a pyramid structure adapted to connect the pair of fuselages and an articulated propulsion system having a thrust axis, wherein the articulated propulsion system is pivotably attached to the pyramid structure and configured for angle of rotation of from about 0 degrees corresponding to the thrust axis disposed substantially parallel but at an offset to a longitudinal axis of the aircraft to about 90 degrees corresponding to the thrust axis disposed substantially at right angle to the longitudinal axis. The thrust axis substantially intersects the center of gravity when the thrust axis is disposed substantially at right angle to the longitudinal axis and the thruster is capable of angle of rotation of about 0 degrees or 90 degrees during take-off or landing. | 03-06-2014 |
| 20140124613 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH TILTROTOR POWER FOR USE ON LAND AND IN AIR - A vertical take-off and landing aircraft with tiltable power for use on land and in the air includes: a body ( | 05-08-2014 |
| 20140158816 | Vertical Takeoff and Landing Aircraft - The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. By moving the rotor units, the aircraft can transition from a hover mode to a transition mode and then to a forward flight mode and back. | 06-12-2014 |
| 20140339354 | Vertical Takeoff and Landing ("VTOL") Aircraft - The invention is to an optionally piloted aircraft that can takeoff and land conventionally or vertically, and can convert between the two. The aircraft is immune to one or more engine failures during vertical flight through multiple engines and the use of a virtual nozzle. Aerodynamic controls are similarly redundant. Hovering flight is enabled with a novel stabilization system. Long range efficient cruise is achieved by turning off some engines in flight and sealing them into an aerodynamic fairing to achieve low drag. The resulting aircraft is capable of CTOL and VTOL, and is capable of converting between the two modes while in the air or on the ground. The aircraft can also be easily taxied on the ground in the conventional manner. Automatic controls considerably reduce the amount of training a pilot needs to fly and land the aircraft in either VTOL or CTOL mode. | 11-20-2014 |
| 20140367509 | AIRCRAFT WITH FREEWHEELING ENGINE - An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | 12-18-2014 |
| 20150336663 | SYSTEM, APPARATUS AND METHOD FOR LONG ENDURANCE VERTICAL TAKEOFF AND LANDING VEHICLE - A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends. | 11-26-2015 |
| 20150336666 | SYSTEM, APPARATUS AND METHOD FOR LONG ENDURANCE VERTICAL TAKEOFF AND LANDING VEHICLE - A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends. | 11-26-2015 |
| 20150344135 | AIRCRAFT WITH INTEGRATED SINGLE SENSOR - An aircraft is provided and includes a single sensor and wings extending outwardly in opposite directions from a fuselage. Each wing includes a main section, an engine section supported on the main section and tail surfaces extending transversely relative to the main section. The single sensor is mountable to one of the tail surfaces with a field of view (FOV) representable as a spherical wedge having a dihedral angle exceeding 180°. | 12-03-2015 |
| 20150375860 | TILT-ROTOR VERTICAL-LIFT AIRCRAFT - Described herein is an aircraft that includes a fuselage with a higher portion and a lower portion. The aircraft also includes two fixed wings that are coupled to and extend from opposing sides of the lower portion of the fuselage. Additionally, the aircraft includes a tilt-rotor assembly that is coupled to each of the two fixed wings. | 12-31-2015 |
| 20190144109 | Extended Range Quad Tiltrotor Aircraft | 05-16-2019 |
| 244120500 | With thrust diverting | 16 |
| 20080290213 | Turbofan Engine for Stol Aircraft | 11-27-2008 |
| 20090001216 | Aircraft engine balanced thrust vectoring system - A balanced thrust vectoring system for an aircraft designed to provide even weight distribution, simple thrust vectoring, and hover stability. The system includes a main diverter that connects to a jet output port. Located inside the diverter is a 4 way splitter that divides the diverter into four equal volumes. Attached to the diverter and adjacent to the two upper volumes are two front upward extending ducts. Attached to the diverter and adjacent to the two lower volumes are two rear upward extending ducts. Each duct includes an upper bend that and diagonally aligned nozzle opening. Each duct has only two bends which help vector the exhaust downward in an efficient manner. The diameter of each duct is consistent to allow their entire length to maximize air flow. | 01-01-2009 |
| 20090026308 | SHORT TAKE-OFF AIRCRAFT - An aircraft capable of making short takeoffs and landings includes essentially a fuselage, a wing secured to the fuselage, a front horizontal stabilizer secured to the fuselage on the front end of the fuselage and at least two jet engines for propulsion. According to the architecture proposed, the propulsion engines are arranged side by side above the fuselage in a rear part of the fuselage with a width at least equal to the width of the propulsion group, a fuselage flap device is arranged in the back of the fuselage so that the fuselage flaps adopt at least a position in which the flaps are considerably in a horizontal plane and take at least a high-lift position in which the flaps are turned downward in such a way that the blast created by the jet engines is channeled towards the top surface of the fuselage flaps to induce a blowing effect. | 01-29-2009 |
| 20090121073 | Aircraft having a jet engine, an adjustable aft nozzle, and an electric vertical fan - An adjustable nozzle is mounted on the airframe downstream from the powerplant for selectively directing powerplant exhaust to exit the aircraft at an angle between about rearward and downward. An electricity source mounted on the airframe powers a magnetically driven fan positioned in front of the powerplant in the fuselage. | 05-14-2009 |
| 20090242690 | DUCTED PROPULSION VECTOR SYSTEM - A ducted propulsion vector system that vectors thrust generated from ducted fan powered aircraft. The system has hinged duct flaps may be vectored from +10 degrees up and turned through −90 degrees downward. Vectored downward 90 degrees, the flaps vector thrust enabling vertical/short takeoff and landing of an aircraft. Hover control is facilitated by internal mounted vanes in line of the thrust stream. The duct flaps are transitioned at operator's input to enable the aircraft to achieve forward flight. | 10-01-2009 |
| 20100001121 | SYSTEM FOR TILTING A POWER UNIT - System for tilting a power unit ( | 01-07-2010 |
| 20100006695 | VERTICAL TAKE-OFF AND LANDING VEHICLE WHICH DOES NOT HAVE A ROTARY WING - A vertical take-off vehicle includes two thermoreactors/turbine engines having a rectangular air inlet opening into a positive-displacement rotary compressor supplying compressed air to a tank connected to (i) a combustion chamber whose exhaust gases actuate a compressor-driving turbine and discharge onto the fixed rear wing upper surface, and (ii) the combustion chamber of the main engine whose exhaust gases discharge directly onto the wing upper surface, the variable incidence of which, in take-off mode, generates a lift force adding to the forces that develop on the front wings. In take-off mode, the variable-geometry upper surfaces of the front wings have a maximum camber onto which the exhaust gases produced in an internal combustion chamber flow at great speed. In cruise mode, the combustion chamber is off and the upper surface returns to a reduced camber position as the rear wing returns to an incidence optimizing total drag and lift forces. | 01-14-2010 |
| 20100012766 | FLYING APPARATUS - A flying apparatus having a thrust directing wing is disclosed. The flying apparatus can include a wing that receives a thrust flow from a thrust flow generator, and selectively redirect the flow in at least one of a plurality of directions. The wing can redirect the thrust flow so as to generate vertical thrust, forward thrust, and combinations thereof. The thrust flow generator can include a gas turbine engine, which can include two rotating shafts and a common burner, with each shaft coupling a compressor with a turbine. | 01-21-2010 |
| 20100044496 | ANNULAR AIRBORNE VEHICLE - An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends. A propulsion system is provided comprising one or more pairs of propulsion devices, each pair comprising a first propulsion device mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device mounted to the wing-body and positioned on a second side of the plane including the wing-body axis. A direction of thrust of the first propulsion device can be adjusted independently of the direction of thrust of the second propulsion device and/or a magnitude of thrust of the first propulsion device can be adjusted independently of the magnitude of thrust of the second propulsion device. In certain embodiments the wing-body appears swept forward when viewed from a first viewing angle, and swept backward when viewed from a second viewing position at right angles to the first viewing angle. | 02-25-2010 |
| 20100301158 | AIRCRAFT HAVING A LIFT/PROPULSION UNIT - An aircraft having a lift/propulsion unit which includes a power unit such as a turboshaft engine which drives a fan through a transmission mechanism. The fan discharges to vectoring nozzles which can be independently swivelled to provide lift or propulsion thrust. An output shaft of the transmission mechanism serves as the main shaft of a motor/generator of modular form. The motor/generator can act as a generator to charge an electrical storage device such as a battery, or as a motor to drive the fan, either alone or to supplement the output of engine. Reaction control nozzles are provided at extremities of the aircraft to provide stabilising thrust. The aircraft is capable of vertical take off and hovering, with the vectoring nozzles swivelled to a lift position, and forward thrust with the vectoring nozzles swivelled to a propulsion position. | 12-02-2010 |
| 20110001001 | FLYING-WING AIRCRAFT - A vertical take-off and landing (VTOL) flying-wing aircraft has a pair of thrust-vectoring propulsion units ( | 01-06-2011 |
| 20110226890 | Aircraft with this VTOL technology can achieve VTOL even its thrust-to-weight ratio is smaller than 1 - An aircraft with this VTOL technology (the Invention) ( | 09-22-2011 |
| 20120119017 | Aircraft Wing Extension and Nozzle System - 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. | 05-17-2012 |
| 20120187236 | Vertical and horizontal flight aircraft "Sky Rover" - Novel aircraft for vertical and horizontal flight having powered air acceleration means installed within its structure drawing air thereinto and delivering the resulting airflow upon airfoils installed in opposed pairs on opposite sides of its exterior structure thereby producing lift without forward travel of the aircraft. | 07-26-2012 |
| 20150298805 | VTOL aircraft with a thrust-to-weight ratio smaller than 0.1 - VTOL aircraft with a thrust-to-weight ratio smaller than 0.1, during vertical take-off/landing, obtains another vertical lift, besides traditional vertical lift generated by low-temp bypass duct directing, under the closing of the propelling nozzle ( | 10-22-2015 |
| 20150336665 | VTOL aircraft with a thrust-to-weight ratio smaller than 0.08 - VTOL aircraft with a thrust-to-weight ratio smaller than 0.08, during vertical take-off/landing, obtains most vertical lift, besides traditional small vertical lift by high-temp bypass slot outlet ( | 11-26-2015 |
| 244120600 | Channel wing | 1 |
| 20100140389 | AIR VEHICLE - 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. | 06-10-2010 |
