| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244007000 |
Rotary wing
| 38 |
| 244007000 |
Tilting wing
| 16 |
| 244007000 |
Tail sitters | 4 |
| 20080223994 | MOVEABLE WINGS ON A FLYING/HOVERING VEHICLE - The present invention includes an embodiment defined as a flying vehicle having a pair of wings and a transition assembly partially housed within each of the pair of wings. The transition assembly has ends rotatable with respect to each other and separately secured to the wing in which the end is housed. The transition assembly has a first position defined as having each wing positioned at an angle offset from a substantial horizontal orientation and oriented in an opposite direction from the other wing. When the transition assembly is in the first position the vehicle spins and will fly in a substantially hovering vertical orientation. The transition assembly has a second position defined as having each wing positioned in a substantial horizontal position. When the transition assembly is in the second position the vehicle will fly in a substantially horizontal orientation. | 09-18-2008 |
| 20080230656 | Aircraft wings having hinged vanes and aircraft having said wings - Reconfigurable aircraft wings with at least one set of hinged upper and lower vanes and aircraft that are equipped with such wings are provided. When the aircraft are taking off or landing vertically, the hinged vanes are open in order to allow rotor thrust to go through the wings, thereby permitting main rotors to be located above the wings. When the aircraft reach certain airspeeds, the hinged vanes are closed in order to provide normal lift of a fixed wing. The aircraft thereby take advantages of the helicopter and the traditional airplane with a fixed wing. | 09-25-2008 |
| 20080272244 | Hybrid Aircraft - A hybrid aircraft ( | 11-06-2008 |
| 20090008510 | AIRCRAFT HAVING THE ABILITY FOR HOVERING FLIGHT, FAST FORWARD FLIGHT, GLIDING FLIGHT, SHORT TAKE-OFF, SHORT LANDING, VERTICAL TAKE-OFF AND VERTICAL LANDING - Aircraft having two, preferably four or more, rotors ( | 01-08-2009 |
| 20090014599 | Convertible aerial vehicle with contra-rotating wing/rotors and twin tilting wing and propeller units - A micro aerial vehicle can be converted during flight between a fixed wing flight mode and a rotary wing flight mode. The canard design micro aerial vehicle includes a fuselage, two tiltable propellers and airfoils arranged at a forward portion of fuselage, a pair of coaxial drive shafts positioned aft of the tiltable propeller and airfoil arranged for contra-rotation, a stop rotor mechanism, and a pair of wing panels, each of the wing panels attached to one of the coaxial drive shafts. The wing panels act as contra-rotating rotor blades in the rotary wing flight mode, and act as fixed wing panels in the fixed wing mode. | 01-15-2009 |
| 20090184209 | Constant-Velocity Drive System for Gimbaled Rotor Hubs - A constant-velocity drive system for a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. A rotary-wing aircraft having a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. | 07-23-2009 |
| 20090212166 | VTOL/STOL TILT-PROP FLYING WING - An aircraft comprises two wings, a fuselage, a tail planform and a pair of counter-rotating propellers. The two wings are located at a longitudinal center of gravity of the aircraft. The fuselage is located forward of the longitudinal center of gravity and coupled to the two wings. The tail planform is coupled to the two wings and located aft of the longitudinal center of gravity. The pair of counter-rotating propellers are located at the longitudinal center of gravity and between the wings. Further, the pair are coupled to a tilting mechanism for tilting the propellers between a vertical flight position and a forward flight position. One of the propellers located beneath the wings when in the vertical flight position and one of the propellers is located above the wings when in the vertical flight position. | 08-27-2009 |
| 20090261209 | CONVERTIBLE AIRCRAFT - A convertible aircraft comprising a main body integrating at least one substantially triangular wing ( | 10-22-2009 |
| 20100096508 | Aircraft and method of retrieving a rescue cradle into the aircraft fuselage - An aircraft capable of hovering, and having a fuselage defining an access opening; driving means for operating a rescue cradle; and a first wall movable between a closed position engaging a first portion of the opening, and a first open position allowing access to the first portion of the opening. The aircraft has a member connected functionally to the first wall and in turn having at least one flat surface; and the member is movable with respect to the wall into a first position, in which the flat surface defines a supporting surface for the cradle when the first wall is in the first open position. | 04-22-2010 |
| 20100108822 | Method for Suppressing Vibration in a Tiltrotor Aircraft - A method is disclosed for suppressing vibration in an aircraft having at least one pair of multiple-blade rotors. The first step of the method is to install in the aircraft at least one pair of vibration suppression devices to form a system, the devices of each system being mounted on opposing sides of the aircraft. Then, during operation of the aircraft, the next step is to rotate the at least one pair of rotors in a manner that causes the blades one of each pair of rotors to be out of phase from the other of each pair of rotors. The final step is to use the system to suppress vibrations caused by the out-of-phase rotation of the rotors. | 05-06-2010 |
| 20100171001 | Hover Delivery of Cabin Payload in Tilt-Rotor and Tilt-Wing Aircraft - A payload or cargo is delivered from a cargo hold of an aircraft during flight, by orienting the fuselage into a nose-up and tail-down position of at least 30 degrees off horizontal, and lowering the cargo from a cargo hold in the fuselage by means of one or more lines. Preferred vertical takeoff and landing (VTOL) aircraft include tilt-rotor or tilt-wing aircraft, and especially preferred aircraft are capable of generating control moments with their rotors to assist in orientating the fuselage of the aircraft into a nose-up and tail-down position. | 07-08-2010 |
| 20100193644 | Aircraft with Integrated Lift and Propulsion System - A vertical take off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles. Improvements include a high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system that is efficient in both hover and cruise flight. Preferred aircraft use thin inboard and outboard wings, thin rotor blades, and use efficient lightweight design to achieve unusually low empty weight fraction. Inventive methods include utilization of advanced design and analysis techniques, which allow for accurate prediction of an aircraft's physical behavior. | 08-05-2010 |
| 20100270435 | Wing efficiency for tilt-rotor aircraft - Rotorcraft wings disposed between tilt-rotor nacelles have particularly high aspect ratios for tilt-rotor rotorcraft, including for example at least 6, 7, 8, or higher. The increase in wing span and aspect ratio is possible because of the use of rigid and semi-rigid rotors, and/or higher modulus of elasticity materials allows increases the stiffness of the wings to the level required for avoiding whirl flutter. Tilt-rotor aircraft having high aspect ratio wings can advantageously further include a controller that provides reduced RPM in a forward flight relative to hover, and/or a controller that provides variable speed, (a so-called “Optimum Speed Tilt Rotor”) as set forth in U.S. Pat. No. 6,641,365 to Karem (November 2003). | 10-28-2010 |
| 20110031355 | Aircraft with dual flight regimes - The aircraft is capable of two distinct fuel-efficient flight regimes: one is a vertical flight regime supported by two large two-bladed rotors with low disc loading located on right and left longitudinal booms. The booms extend between outboard regions of a front wing and inboard regions of a rear wing that has a larger span an area. The other flight regime is high speed up to high subsonic Mach number with the aircraft supported by wing lift with high wing loading, and with the rotors stopped and faired with minimal local drag contiguous to the booms. The longitudinal location of the aircrafts center of gravity, aerodynamic center and the center of the rotors are in close proximity. The front wing is preferably swept back, and the rear wing is preferably of W planform. | 02-10-2011 |
| 20110114798 | LONG-RANGE AIRCRAFT WITH HIGH FORWARD SPEED IN CRUISING FLIGHT - The present invention relates to an aircraft ( | 05-19-2011 |
| 20110303795 | THREE-WING, SIX TILT-PROPULSION UNIT, VTOL AIRCRAFT - A vertical takeoff and landing aircraft having a fuselage with, preferably, 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 oriented vertically for vertical flight and horizontally for forward flight. Each propulsion unit comprises a propeller having a plurality of blades, where the pitch angle associated with the distal end of each blade and the proximal end of each blade are independently adjustable. As such, each of the propellers can be adjusted to exhibit a first blade pitch angle distribution optimized for vertical flight and a second blade pitch angle distribution optimized for forward flight. | 12-15-2011 |
| 20120168568 | ROTOR UNLOADING APPARATUS AND METHOD - A method and apparatus for enabling high speed flight in a rotorcraft are disclosed. The method may include executing a flight with a rotorcraft. The flight may include a first portion and second portion ordered sequentially. During the first portion, the rotorcraft may be flown with the rotor exclusively in autorotation. Once sufficient airspeed is obtained, the flight may transition to the second portion. Wherein, substantially all of the weight of the rotorcraft may be supported by one or more fixed wing surfaces of the rotorcraft. Thus, during the second portion, the rotor may be completely unloaded. To keep the rotor stable by turning, the rotor may be powered during the second portion by an engine of the rotorcraft by way of a prerotation system. | 07-05-2012 |
| 20120199699 | Tilt Rotor Aircraft with Fixed Engine Arrangement - The system of the present application includes an engine and pylon arrangement for a tilt rotor aircraft in which the engine is fixed in relation to a wing portion of the aircraft, while the pylon is rotatable. The pylon supports a rotor hub having a plurality of rotor blades. Rotation of the pylon allows the aircraft to selectively fly in a helicopter mode and an airplane mode, as well as any combination thereof. | 08-09-2012 |
| 20120261523 | Aircraft with Wings and Movable Propellers - The invention is a flight vehicle, and methods of operation thereof, having wings and movable propeller assemblies which can be rotated to provide vertical and/or horizontal thrust. The propeller assemblies are configured to maximize available engine/propeller thrust and to prevent propwash from striking the wings of the aircraft. | 10-18-2012 |
| 20120280091 | LIFT, PROPULSION AND STABILISING SYSTEM FOR VERTICAL TAKE-OFF AND LANDING AIRCRAFT - 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. | 11-08-2012 |
| 20130026302 | HIGH PERFORMANCE TILT ROTOR AIRCRAFT IN WHICH NACELLE TILT ANGLE AND FLAPERON ANGLE MECHANICALLY INTERWORK WITH EACH OTHER - Provided is a high performance tilt rotor aircraft in which a nacelle tilt angle and a flaperon angle mechanically interlock with each other. In the tilt rotor aircraft having nacelles in which rotors are mounted in left and right main wings and configured so that the nacelles rotate according to whether the tilt rotor aircraft conducts forward flight or vertical take-off and landing flight, each of the main wings is provided with a flaperon, and the nacelle and the flaperon are connected to each other by a power transfer unit, such that the flaperon also rotates together with the nacelle at the time of rotation of the nacelle, thereby allowing a change in a nacelle tilt angle to lead to a change in a flaperon angle. | 01-31-2013 |
| 20130026303 | CONVERTIPLANE - There is described a convertiplane comprising: a pair of semi-wings; at least two rotors which may rotate about relative first axes and tilt about relative second axes together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being, in use, transversal to a longitudinal direction of convertiplane in helicopter mode, and being, in use, substantially parallel to longitudinal direction in aeroplane mode; convertiplane further comprises at least two through openings within which said rotor may tilt, when said convertiplane moves, in use, between said helicopter and said aeroplane mode. | 01-31-2013 |
| 20130026304 | CONVERTIPLANE - There is described a convertiplane comprising: a pair of semi-wings; a first rotor comprising a shaft which may rotate about first axis and tilt about a second axis together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being transversal to a longitudinal direction of convertiplane in helicopter mode and being substantially parallel to longitudinal direction in aeroplane mode; convertiplane also comprises an electrical power storage device; and an electrical machine which comprises, in turn, a stator electrically connected to storage device; and a second rotor operatively connected to a shaft of first rotor; electrical machine acts as an electric motor for driving in rotation said first rotor by using the electrical power stored in storage device; or as an electrical power generator for re-charging storage device by causing the rotation second rotor under the action of a wind current. | 01-31-2013 |
| 20130026305 | CONVERTIPLANE - There is described a convertiplane comprising a pair of semi-wings, a first and a second rotor which may rotate about relative first axes and tilt about relative second axes together with first axes with respect to semi-wings between a helicopter mode and an aeroplane mode; first axes are, in use, transversal to a longitudinal direction of convertiplane in helicopter mode, and are, in use, substantially parallel to longitudinal direction in aeroplane mode; first and second rotors may tilt about relative second axes independently of each other. | 01-31-2013 |
| 20140061392 | Aircraft With Integrated Lift And Propulsion System - A vertical take-off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles or more, with glide ratios of at least 24. Improvements include a combination of high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system efficient in both hover and cruise flight. Preferred aircraft use narrow chord inboard and outboard wings, and use efficient lightweight design to achieve unusually low empty weight fraction. In some embodiments, the rotors use medium rather than high modulus fibers, with wider blades of lower taper ratio, to provide the stiffness and mass properties required for high performance OSTR rotor blades. Also disclosed are VTOL aircraft with glide ratios from approximately 26 to over 40. | 03-06-2014 |
| 20140084114 | VTOL Aircraft with Propeller tiltable around two Axes and a retractable Rotor - A VTOL aircraft has a rotor, wings, and a propeller providing thrust for take-off and landing and horizontal flight. The propeller, attached through a joint mechanism to the aircraft, is continuously tiltable around to axes, providing the anti-torque forces for the rotor and thrust forces for lifting the aircraft and for horizontal flight. The hubs of rotor blade sets are rotatable to each other for alignment. The rotor assembly, attached to a moveable linkage mechanism, is tiltable in or against the direction of flight and movable towards to or into the fuselage. The folded and retracted rotor reduces the air drag and the high thrust of the propeller increase the speed of winged flight. The flexibility and lower weight of the drive are preferably achieved with an advanced hydrostatic drivetrain. | 03-27-2014 |
| 20140110533 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - A vertical take-off and landing aircraft includes a propulsion mechanism having a fan for generating lift and thrust, an engine for supplying motive power to the propulsion mechanism, a frame coupling the propulsion mechanism and the engine, seating connected to and suspended from the frame so as to be swingable back and forth relative to the frame, a control stick connected to the frame, and a landing undercarriage connected to the seating, wherein the propulsion mechanism is connected to the frame such that the drive shaft of the fan is directed vertically during landing, and the frame is moved relative to the seating by manipulating the control stick, to change the orientation of the propulsion mechanism. The thrust can be controlled with simple configuration, and take-off and landing can be performed safely even in a small space surrounded by obstacles. | 04-24-2014 |
| 20140339372 | SYSTEM, A METHOD AND A COMPUTER PROGRAM PRODUCT FOR MANEUVERING OF AN AIR VEHICLE WITH TILTABLE PROPULSION UNIT - A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle. | 11-20-2014 |
| 20150360774 | ROTARY PYLON CONVERSION ACTUATOR FOR TILTROTOR AIRCRAFT - A tiltrotor aircraft can include a pylon rotatable about a conversion axis. A first differential planetary assembly can include a first housing; a first ring gear; a first differential planetary gear having a first output portion; and a first differential sun gear. A second differential planetary assembly can include a second housing; a second ring gear; a second differential planetary gear having a second output portion; and a second differential sun gear. The first output portion is coupled to the second housing such that the second housing rotates at a first output speed. Further, the second output portion is coupled to the shaft, the shaft being coupled to the pylon such that rotation of the shaft rotates the pylon. | 12-17-2015 |
| 20160023754 | Vertical take-off aircraft - A mechanism for stowing and/or adjusting a ducted propeller of a flying object, the flying object comprising a fuselage and at least one pair of wings, the outer walls of which together define a shell of the flying object, comprising a ducted propeller comprising a substantially cylindrical duct, which defines a longitudinal axis of the ducted propeller and is open at the base faces thereof, a rotor comprising a plurality of rotor blades, which is set up to rotate in a plane perpendicular to the longitudinal axis of the ducted propeller, and a drive device for driving the rotor; a receiving chamber, provided in the fuselage and/or a wing of the flying object, for the ducted propeller; a mechanism which is set up to transfer the ducted propeller from a stowed state into a deployed state. | 01-28-2016 |
| 20160167776 | Modular Flight Vehicle | 06-16-2016 |
| 20160167780 | CONVERTIPLANE WITH NEW AERODYNAMIC AND TECHNICAL SOLUTIONS WHICH MAKE THEAIRCRAFT SAFE AND USABLE | 06-16-2016 |
| 20160200436 | Tri-Rotor Aircraft Capable of Vertical Takeoff and Landing and Transitioning to Forward Flight | 07-14-2016 |
| 20170233069 | HYBRID MULTICOPTER AND FIXED WING AERIAL VEHICLE | 08-17-2017 |
| 20090045294 | Systems and Methods for Rotor/Wing Aircraft - Systems and methods for rotor/wing aircraft are disclosed. In one embodiment, an aircraft includes an airframe, a high-lift canard and tail, a rotor/wing, a propulsion system, and a drive assembly. The drive assembly, which may include a radial inflow turbine, is configured to extract work from the propulsion system to selectively rotate the rotor/wing assembly thus enabling the aircraft to conduct rotary-wing flight, fixed wing flight as well as smoothly transition between the two modes of flight. | 02-19-2009 |
| 20090206208 | Reaction drive rotor/wing variable area nozzle - In an exemplary variable area nozzle, a fixed duct section has an inlet and an outlet oriented approximately perpendicular to the inlet. A controllable nozzle member is disposed adjacent the outlet of the fixed duct section. The controllable nozzle member has an area that is adjustable to maintain a substantially constant nozzle pressure ratio. The controllable nozzle member may include first and second flap doors hinged and pivotable in opposite directions between an open position and a closed position and that also may be hinged and pivotable in a same direction so thrust from gas exiting the nozzle is vectorable. When disposed in rotor tips of an aircraft capable of rotary wing flight and fixed wing flight, the variable area nozzle may maintain a substantially constant nozzle pressure ratio near an optimized nozzle pressure ratio as the aircraft transitions from rotary wing flight to fixed wing flight. | 08-20-2009 |
| 20090266941 | Combination Spar and Trunnion Structure for a Tilt Rotor Aircraft - An aircraft is equipped with a spinnion coupling an inboard wing to a tilting nacelle. The spinnion is advantageously configured to extend across the nacelle from an inboard junction to an outboard junction, and terminates inside the inboard wing. This provides an efficient lightweight structure to support a nacelle and facilitate tilting of the nacelle. The spinnion, which can be configured to be at least partially disposed within the inboard wing, is advantageously concentric with the tilting axis in order to facilitate tilting of a nacelle. A cross-wing driveshaft can be included, disposed at least partly within the inboard wing, and can advantageously be configured to terminate inside the spinnion at a junction with a miter gearbox. The miter gearbox can be disposed at least partly within the spinnion but more preferably lies entirely within the spinnion, and functions to transfer power from an input shaft to the cross-wing driveshaft. | 10-29-2009 |
| 20100025543 | METHODS AND APPARATUS FOR TRANSFORMING UNMANNED AERIAL VEHICLE - Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro. | 02-04-2010 |
| 20100072325 | Forward (Upstream) Folding Rotor for a Vertical or Short Take-Off and Landing (V/STOL) Aircraft - This is an improvement of the 1968 Trailing Rotor V/STOL aircraft (Ref. 1). Rotors are mounted on wing-tip pods which can be tilted from the vertical to the horizontal aft position. Rotors are then stopped in the axial-flow condition and indexed to an azimuth position, aft of the wing trailing-edge. Rotor blades are then folded forward (blade-tips upstream of rotor-hubs) and locked into grooves in the tip-pods. | 03-25-2010 |
| 20100078526 | AIRCRAFT WITH A CONVERTIBLE FLIGHT SYSTEM - The invention relates to an aircraft with a convertible flight system which can function as a helicopter and as an airplane and comprising a fuselage ( | 04-01-2010 |
| 20100243820 | TAKING OFF AND LANDING AIRPLANE USING VARIABLE ROTARY WINGS - This invention is regarding a VTOL aircraft that is designed to enable it to take off by generating lift through rotary wings like a helicopter and then moving forward; and when it flies at high speeds, it is able to use jet engines so that it can generate lift through fixed wings while the rotary wings are transformed into fixed wings to generate lift by adjusting the angles between the individual wings thereby enhancing the efficiency | 09-30-2010 |
| 20100243821 | TAKING OFF AND LANDING AIRPLANE USING VARIABLE ROTARY WINGS - This invention is regarding a VTOL aircraft that is designed to enable it to take off by generating lift through rotary wings like a helicopter and then moving forward; and when it flies at high speeds, it is able to use jet engines so that it can generate lift through fixed wings while the rotary wings are transformed into fixed wings to generate lift by adjusting the angles between the individual wings thereby enhancing the efficiency. | 09-30-2010 |
| 20100276549 | Fail-operational multiple lifting-rotor aircraft - A rotorcraft having multiple rotors, and wings that provide lift in forward flight, has mechanical coupling between rotors that can be disengaged and optionally reengaged, during flight. The coupling can, which can prevent a failure of one rotor from interfering with rotation of the other rotor(s), can be accomplished using many different types of devices, including for example, dog clutches and friction clutches, and collapsible clutches. Disengagement can range from being completely under control of an operator, to partially under operator control, to completely automatic. Among many other benefits, designing, manufacturing, fitting, retrofitting or in some other manner providing an aircraft with a device that can disengage rotation of one of the rotors from that of another one of the rotors during flight can be used to improving survivability in an emergency situation. | 11-04-2010 |
| 20110001020 | QUAD TILT ROTOR AERIAL VEHICLE WITH STOPPABLE ROTORS - The disclosed invention consists of several improvements to well known Quad Tilt-Rotor (QTR) aircraft. The first is that during a wing-borne flight, one pair of tilt-rotors, which can be substantially larger than the other pair, is feathered and stopped. This can promote vehicle aerodynamic efficiency and can be utilized to increase vehicle speed. Second is that the wings are not attached to the fuselage at a fixed angle of incidence like on conventional QTR aircraft, but can also be tilted in respect to the fuselage independently of the tilt-rotors. Furthermore, each rotor and each wing can be tilted with respect to fuselage to any tilt-angle without limit, which gives the vehicle unprecedented ability to position the fuselage in any attitude in respect to the vehicle direction of flight. | 01-06-2011 |
| 20110006166 | ROTARY WING VEHICLE - A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight. | 01-13-2011 |
| 20110036954 | Compound Aircraft with Autorotation - A compound aircraft features variable incidence wings, a thruster, a rotor and a clutch connecting the engines to the rotor. Upon reaching a suitable forward speed, the control system of the compound aircraft unloads the rotor and disengages the clutch, disconnecting the rotor from the engines. The control system configures the cyclic and collective pitch effectors to cause the rotor to autorotate. The control system selects an autorotation rotational speed that is adequately rapid to prevent excessive deformation of the rotor blades due to aerodynamic forces acting on the blade and that is adequately slow to prevent excessive compressibility effects. | 02-17-2011 |
| 20110114797 | Fail-Operational Multiple Lifting-Rotor Aircraft - A rotorcraft having multiple rotors, and wings that provide lift in forward flight, has a mechanical coupling between rotors that can be disengaged and optionally reengaged, during flight. The coupling, which can prevent a failure of one rotor from interfering with rotation of the other rotor(s), can be accomplished using many different types of devices, including for example, dog clutches, friction clutches, and collapsible clutches. Disengagement can range from being completely under control of an operator, to partially under operator control, to completely automatic. Among many other benefits, designing, manufacturing, fitting, retrofitting or in some other manner providing an aircraft with a device that can disengage rotation of one of the rotors from that of another one of the rotors during flight can be used to improve survivability in an emergency situation. | 05-19-2011 |
| 20110180673 | TAKING OFF AND LANDING AIRPLANE USING VARIABLE ROTARY WINGS - This invention is regarding a VTOL aircraft that is designed to enable it to take off by generating lift through rotary wings like a helicopter and then moving forward; and when it flies at high speeds, it is able to use jet engines so that it can generate lift through fixed wings while the rotary wings are transformed into fixed wings to generate lift by adjusting the angles between the individual wings thereby enhancing the efficiency. | 07-28-2011 |
| 20110315827 | Wing Extension Control Surface - A tiltrotor aircraft includes a rotatable nacelle that supports a rotor assembly and is pivotally attached to the air-craft's fuselage. A wing extension attaches to an outboard section of the nacelle. The wing extension provides additional yaw control during helicopter mode and additional lift during airplane mode. A method for controlling at least a portion of yaw movement includes positioning the rotor assembly in helicopter mode, creating rotor wash with the rotor assembly, and pivotally rotating the wing extension in the rotor wash. | 12-29-2011 |
| 20120097801 | SUPERSONIC HOVERING AIR VEHICLE - Embodiments of the present invention include an aircraft capable of sustained out-of-ground-effect hover flight and sustained supersonic flight. At least some embodiments includes two wings powered by an engine to counterrotate while hovering, and to not rotate and sweep while flying at transonic and supersonic speeds. Other embodiments include two rotating wings that generate a force per unit area of under 100 lb/ft2 within the rotating wing disk during hover. Still other embodiment include a vehicle with rotating wings that can increase pitch to accelerate the aircraft, align the chord line of the wings with the airstream, and sweep the wings. Still further embodiments include a power plant that powers unducted rotating wings during hover and disengages from the wings to propel the aircraft at supersonic speeds. | 04-26-2012 |
| 20120223191 | Short Landing Air Vehicle by the use of Rotating Wings - An air vehicle | 09-06-2012 |
| 20120248259 | LONG ENDURANCE VERTICAL TAKEOFF AND LANDING AIRCRAFT - An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode. | 10-04-2012 |
| 20120292456 | Method and Apparatus for In-Flight Blade Folding - A foldable rotor system for a rotorcraft, the foldable rotor system comprising a rotor assembly operably associated with a driveshaft, the driveshaft being operable associated with an engine, the rotor assembly comprising a rotor blade connected to a grip pin. A swashplate is operable associated with the grip pin in order selectively change a pitch of the rotor blade. A blade fold actuator is operably associated with the grip pin such that the blade fold actuator is configured to fold and unfold the rotor blade about a blade fold axis. During an airplane mode, the rotorcraft can stop and fold the rotor blades so that the rotorcraft relies upon thrust from the engine for propulsion. The rotor blades are folded in a spiral fold path so that the rotor blades remain substantially edgewise, or feathered, during the folding process. The spiral fold path minimizes the aerodynamic drag experienced by the rotor blades while being folded during flight of the rotorcraft. | 11-22-2012 |
| 20130105636 | Rotor System Anti-Rotation Wear Protector | 05-02-2013 |
| 20130134264 | Electric Motor Powered Rotor Drive for Slowed Rotor Winged Aircraft - A rotor aircraft has an engine, a propeller, wings, and a rotor. An electric motor is coupled to the rotor drive shaft for applying torque to the rotor drive shaft. The electric motor is sized to supply all of the torque to pre-rotate the rotor to a selected speed prior to liftoff of the aircraft. The wings are capable of providing substantially all of the lift required during forward flight at a cruise speed. The rotor being is capable of being trimmed to provide substantially zero lift and auto-rotate at cruise speed. Sensors sense flight conditions of the aircraft and provide signals to a controller that selectively causes the electric motor to cease applying torque to the rotor drive shaft during autorotation at cruise speed. The controller also causes the electric motor to apply torque to the rotor drive shaft if the sensors indicate additional rotor speed is needed. | 05-30-2013 |
| 20130175404 | AIRCRAFT WITH FIXED AND TILTING THRUSTERS - An aircraft including a fuselage with a yaw axis, a pitch axis and a roll axis, two attitude control thrusters, fixedly connected to the fuselage to provide thrust parallel to the yaw axis, two locomotion and hover thrusters. The aircraft further includes for the locomotion and hover thruster, a mechanism for tilting the locomotion and hover thruster about a tilt axis parallel to the pitch axis to select a direction, parallel to a first plane defined by the yaw and roll axes, in which the locomotion and hover thruster provides thrust. | 07-11-2013 |
| 20130264429 | CONVERTIBLE AIRPLANE - A convertible airplane is described. The convertible airplane has a fuselage, a trapezoidal wing, two counter rotating front rotors, and an aft rotor. | 10-10-2013 |
| 20140217243 | TILT ROTOR AIRCRAFT WITH FIXED ENGINE ARRANGEMENT - The system of the present application includes an engine and pylon arrangement for a tilt rotor aircraft in which the engine is fixed in relation to a wing portion of the aircraft, while the pylon is rotatable. The pylon supports a rotor hub having a plurality of rotor blades. Rotation of the pylon allows the aircraft to selectively fly in a helicopter mode and an airplane mode, as well as any combination thereof. | 08-07-2014 |
| 20140263854 | Tiltrotor Aircraft With Inboard Wing Mounted Fixed Engine Arrangement - A rotor system for tilt rotor aircraft comprises an engine disposed at a first fixed position on a wing member, and a prop-rotor pylon mechanically coupled to the engine along a drive path extending through the wing member. The engine is disposed adjacent a fuselage of the tilt rotor aircraft, and the prop-rotor pylon is configured to selectively rotate between a vertical position and a horizontal position. The prop-rotor pylon is coupled to a plurality of rotor blades. | 09-18-2014 |
| 20140263855 | Spindle Mounted Tiltrotor Pylon with Fixed Engine Arrangement - A rotor system for tilt rotor aircraft comprises an engine disposed at a first fixed location on a wing member; a prop-rotor pylon mechanically coupled to the engine along a drive path, and a gearbox disposed in the drive path. The prop-rotor pylon is rotatably mounted on a spindle, and the prop-rotor pylon is configured to selectively rotate about a rotational axis of the spindle between a vertical position and a horizontal position. The gearbox comprises a rotational axis aligned with the rotational axis of the spindle. | 09-18-2014 |
| 20140312177 | Coaxial rotor/wing aircraft - A system and method which enable efficient, rapid and safe transition between rotary-wing and fixed-wing flight mode in rotor/wings aircrafts is disclosed. The aircraft comprises of two rotor/wings on the same axis of rotation, one above the fuselage and the other one under the fuselage. During rotary-wing mode, the rotor/wings rotate coaxially and provide vertical lift. During transition between rotary-wing and fixed-wing modes, the synchronised operation of the two rotor/wings maintains lateral symmetry of lift on the aircraft. The reaction of the rotor/wings on the fuselage is also canceled. During fixed-wing flight mode, the two rotor/wings are stopped and locked in a biplane configuration, both providing lift as fixed wings. The rotor/wings may be further reconfigured for higher subsonic or supersonic speed. Tandem and multiple rotor/wings aircrafts with increased cargo capacity, speed and range, comprise of multiple of these coaxial rotor/wings. | 10-23-2014 |
| 20140346283 | AIRCRAFT USING TURBO-ELECTRIC HYBRID PROPULSION SYSTEM FOR MULTI-MODE OPERATION - A vehicle incorporating a hybrid propulsion system. In one form, the vehicle may be an aircraft such that the system includes gas turbine engines as a first motive power source, and one or more battery packs as a second motive power source. Through selective coupling to an electric motor that can in turn be connected to a bladed rotor or other lift-producing device, the motive sources provide differing ways in which an aircraft can operate. In one example, the gas turbine engines can provide operation for a majority of the flight envelope of the aircraft, while the battery packs can provide operation during such times when gas turbine-based motive power is unavailable or particularly disadvantageous. In another example, both sources of motive power may be decoupled from the bladed rotor such that the vehicle can operate as an autogyro. In another mode of operation, the movement of a bladed rotor can be both decoupled from the sources of propulsion as well as fixed relative to the aircraft such that the aerodynamic surfaces formed on the bladed rotors can act as a fixed wing. In another particular form, the vehicle may be ground-based or water-based. | 11-27-2014 |
| 20150034772 | Composite Flexure for Tiltrotor Rotor System - According to one embodiment, a composite flexure may secure a rotor blade to a yoke in a tiltrotor rotor system. The composite flexure includes a composite body, a first end configured to couple the composite member to the yoke, and a second end configured to couple the composite member to the rotor blade. | 02-05-2015 |
| 20150048213 | FIXED ENGINE AND ROTATING PROPROTOR ARRANGEMENT FOR A TILTROTOR AIRCRAFT - A tiltrotor aircraft includes a fuselage; a wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin; an engine disposed at a fixed location relative to the wing member; and a proprotor having a spindle gearbox, rotor mast, and a plurality of rotor blades drivable in rotation about the rotor mast, the spindle gearbox being rotatable about a conversion axis. The spindle gearbox is located above the upper wing skin of the wing member. | 02-19-2015 |
| 20150048214 | METHOD AND APPARATUS OF CONNECTING A FIXED DRIVE SYSTEM TO A ROTATING DRIVE SYSTEM FOR A TILTROTOR AIRCRAFT - A quill shaft is configured for transferring torque and accepting misalignments between a fixed gearbox and a rotatable spindle gearbox in a propulsion system of a tiltrotor aircraft, the quill shaft includes a first splined portion configured for coupling to an output gear of the fixed gearbox, and a second splined portion configured for coupling to an input gear of the spindle gearbox. The spindle gearbox includes a rotor mast associated therewith, the spindle gearbox being rotatable so that the tiltrotor aircraft can selectively operate in a helicopter mode and airplane mode. | 02-19-2015 |
| 20150102175 | FIXED WINGED AIRCRAFT WITH FOLDABLE AUTO-ROTATION ROTOR - The subject matter discloses a fixed wing aircraft comprising one or more foldable auto-rotation rotors operating on the fixed wing aircraft, each of the one or more foldable auto-rotation rotors comprising one or more foldable blades; the one or more foldable auto-rotation rotors are stopped while the fixed wing aircraft is flying; the one or more foldable auto-rotation rotors are started while the fixed wing aircraft is flying; the one or more foldable blades are folded while the fixed wing aircraft is flying; the one or more foldable blades are expanded while the fixed wing aircraft is flying; one or more masts, each of the one or more masts connects a foldable auto-rotation rotor of the one or more foldable auto-rotation rotors to the fixed wing aircraft; the one or more masts are foldable while the fixed wing aircraft is flying; the one or more masts are expanded while the fixed wing aircraft is flying; the one or more masts are positioned vertically and rearwards; a disk plane of the one or more auto-rotation rotors is positioned vertically and rearwards with respect to the fixed wing aircraft during forward flight. | 04-16-2015 |
| 20150122953 | Drive Link for Tiltrotor Rotor System - According to one embodiment, a drive link includes a first bearing housing, a second bearing housing, and a central portion coupled between the first bearing housing and the second bearing housing. The central portion has less torsional stiffness than the first and second bearing housings such that the central portion twists in response to cocking of the first bearing housing relative to the second bearing housing. | 05-07-2015 |
| 20160001878 | EASY LANDING DRONE - Disclosed is an easy landing drone. The drone includes: a propeller changing direction; a propeller tower supporting the propeller; a body connected to the propeller tower; a main wing arranged left-right symmetrically with respect to a horizontal axis of the body and having a pair of holes around a center of gravity of the body; a pair of auxiliary wings disposed in the pair of holes, respectively; and an actuator connected to a base shaft fixed to the main wing through the pair of auxiliary wings and controlling angles of the pair of auxiliary wings. | 01-07-2016 |
| 20160031556 | Impact Resistant Propeller System, Fast Response Electric Propulsion System And Lightweight Vertical Take-Off And Landing Aircraft Using Same - An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight. An aerial vehicle adapted to withstand impacts upon its propellers. An aerial vehicle able to quickly alter the thrust of its propellers. | 02-04-2016 |
| 20160046369 | AIRCRAFT AND METHODS FOR OPERATING AN AIRCRAFT - An aircraft ( | 02-18-2016 |
| 20160101853 | VERTICAL TAKE OFF AND LANDING AIRCRAFT - A vertical takeoff and landing aircraft is provided. The aircraft includes a fuselage having a first end, a second end, and a center of gravity in between the first end and the second end. Wings may extend from the side of the fuselage. The wings may include a canard at the first end, and a wing at the second end. The present invention may further include a pair of engines pivotally attached on either side of the fuselage and substantially aligning with the center of gravity. | 04-14-2016 |
| 20190144107 | Segmented Duct for Tilting Proprotors | 05-16-2019 |
| 20100252690 | AIRCRAFT - An unmanned aerial vehicle (UAV) in the form of a “tail sitter” flying wing adapted for vertical take off and landing and transitions between flight as a helicopter and wing-borne flight. The vehicle is electrically powered from onboard batteries and equipped with rotors on miniature helicopter rotor heads at the tips of the wing for both lift, during take off and landing, and forward thrust. In planform the wing comprises, to each side of its longitudinal axis, an inner section with swept back leading and trailing edges, and an outer section with a leading edge more perpendicular to the longitudinal axis, being only mildly swept back or substantially unswept, and a swept forward trailing edge. | 10-07-2010 |
| 20120286102 | REMOTELY CONTROLLED VTOL AIRCRAFT, CONTROL SYSTEM FOR CONTROL OF TAILLESS AIRCRAFT, AND SYSTEM USING SAME - 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 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. A tailless airplane which uses a control system that takes inputs for a traditional tailed airplane and translates those inputs to provide control utilizing non-traditional control methods. | 11-15-2012 |
| 20160375998 | VERTICAL TAKE-OFF AND LANDING DRAG RUDDER - A system for a tail-sitter aircraft includes a fuselage having one or more propellers, a wing structure coupled to the fuselage, and a drag rudder assembly coupled to the wing structure, the drag rudder assembly including a first planar member that is coupled to a second planar member. The drag rudder assembly is configured to produce a stabilizing force on the wing structure during higher speeds of the aircraft in tandem rotor flight. | 12-29-2016 |
| 20170233070 | VERTICAL TAKEOFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV) | 08-17-2017 |
| 20090045295 | Vertical/Short Take-Off and Landing Aircraft - A vertical/short take-off and landing aircraft with a single proprotor assembly that has a pair of inline counter-rotating rotors. Two inline counter-rotating engines are directly connected to the rotors. One engine is shut down in horizontal flight to improve efficiency. Gimbal mounting the proprotor assembly permits thrust to be directed forward to back and left to right to control pitch and roll when hovering. Varying the relative engine speeds controls yaw. The aircraft is adaptable as an unmanned vehicle. | 02-19-2009 |
| 20090266942 | Tilt outboard wing for tilt rotor aircraft - Tilt-rotor aircraft experience increased efficiency and fuel economy by including wing extensions outboard of the tilting nacelles. Stall and buffeting during conversion from rotor-born hover to wing-born forward flight are reduced to an acceptable level using wide chord flaps deflected upwards by at least 15-20°, preferably in combination with leading edge slats. The outboard wing or wing portion is preferably has a span at least 25-40% of a span of the inboard section, and a total surface area at least 10-20% the total surface area of the corresponding inboard section. | 10-29-2009 |
| 20090283644 | CONTROL LEVER ASSEMBLY FOR A TILT-ROTOR AIRCRAFT - A control lever assembly for a tilt-rotor aircraft, comprises at least one control lever which is movable relative to a control lever support. The control lever support has a rotational position that varies in correspondence with the tilt of the rotor of the aircraft. For example, the control lever support is movable by an actuator between a first position, in the airplane mode of the aircraft, in which the control lever moves substantially horizontally and a second position, in the helicopter mode of the aircraft, in which the control lever moves substantially vertically. | 11-19-2009 |
| 20100230547 | Stop-rotor rotary wing aircraft - Systems and methods for transitioning an aircraft between helicopter and fixed wing flight modes are provided. In one embodiment, an aircraft comprises a plurality of wings each having a spar and a flap; a flap actuator configured to move the flap with respect to the spar; and a center section rotatably coupled to each spar. The center section includes at least one spar actuator configured to rotate at least one of the wings about a rotational axis of the spar when the aircraft transitions between helicopter and fixed wing flight modes. | 09-16-2010 |
| 20100327123 | Rotorcraft with Variable Incident Wing - A twin-rotor side-by-side compound rotorcraft has a fuselage and variable incident wing assembly that pivots relative to fuselage. The aircraft also has landing gear assembly and a tail fin assembly. The variable incident wing assembly is pivotally attached to the fuselage, and includes wing members, engines fixedly mounted to the wing members or another area of the rotorcraft, and a mast attached at a fixed angle relative to the wing members. Then engines may also be located near the fuselage or another area of the rotorcraft. The variable incident wing assembly is capable of pivoting about a pivot axis, thereby allowing mast orientation in at least a hover mast position and a forward flight mast position. The rotors provide additional forward thrust and the wings provide additional lift, when the mast is in the forward flight mast position. | 12-30-2010 |
| 20110036955 | Aircraft with Integrated Lift and Propulsion System - A vertical take off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles. Improvements include a high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system that is efficient in both hover and cruise flight. Preferred aircraft use thin inboard and outboard wings, thin rotor blades, and use efficient lightweight design to achieve unusually low empty weight fraction. Inventive methods include utilization of advanced design and analysis techniques, which allow for accurate prediction of an aircraft's physical behavior. | 02-17-2011 |
| 20120061526 | Rotor Blade Spacing for Vibration Attenuation - A rotor system for a rotorcraft, the rotor system is a rotor hub having six rotor blades attached to a rotor mast via a rotor yoke assembly. Each rotor blade is angularly spaced in 30° and 90° alternating angular increment about a mast axis of rotation. Such rotor blades spacing reduces the vibration that is translated into the rotorcraft through the rotor mast. | 03-15-2012 |
| 20120211608 | TILT-ROTOR AIRCRAFT - A convertiplane having a fuselage with a first axis; and two rotors having respective shafts and fitted to a wing having a fixed portion connected to the fuselage, and a movable portion which supports the rotors, is connected to the fixed portion to rotate about a second axis crosswise to the first axis and to the shafts of the rotors, and is formed in one piece defined by two half-wings located on opposite sides of the fixed portion and each supporting a respective rotor, and by an elongated member extending along the whole wing and connecting the two half-wings; the rotors being powered by a motor via a transmission comprising a transmission shaft connecting the shafts of the rotors and coaxial with the second axis. | 08-23-2012 |
| 20130099065 | TILT-WING AIRCRAFT - A tilt-wing aircraft is provided. The tilt-wing aircraft includes a tail drive and control unit. The control unit is configured to generate a forward thrust. The control unit can also generate an upwardly or downwardly directed thrust component and/or a laterally directed thrust component in hover flight and in climb flight of the aircraft. | 04-25-2013 |
| 20130206921 | 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. | 08-15-2013 |
| 20130256465 | Rotorcraft with Variable Incident Wing - A twin-rotor side-by-side compound rotorcraft has a fuselage and variable incident wing assembly that pivots relative to fuselage. The aircraft also has landing gear assembly and a tail fin assembly. The variable incident wing assembly is pivotally attached to the fuselage, and includes wing members, engines fixedly mounted to the wing members or another area of the rotorcraft, and a mast attached at a fixed angle relative to the wing members. Then engines may also be located near the fuselage or another area of the rotorcraft. The variable incident wing assembly is capable of pivoting about a pivot axis, thereby allowing mast orientation in at least a hover mast position and a forward flight mast position. The rotors provide additional forward thrust and the wings provide additional lift, when the mast is in the forward flight mast position. | 10-03-2013 |
| 20140191088 | Aircraft With Integrated Lift And Propulsion System - A vertical take off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles. Improvements include a high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system that is efficient in both hover and cruise flight. Preferred aircraft use thin inboard and outboard wings, thin rotor blades, and use efficient lightweight design to achieve unusually low empty weight fraction. Inventive methods include utilization of advanced design and analysis techniques, which allow for accurate prediction of an aircraft's physical behavior. | 07-10-2014 |
| 20160031555 | AERODYNAMICALLY EFFICIENT LIGHTWEIGHT VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH PIVOTING ROTORS AND STOWING ROTOR BLADES - An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes. | 02-04-2016 |
| 20160052618 | A TRANSITION ARRANGEMENT FOR AN AIRCRAFT - According to the invention there is provided a transition arrangement ( | 02-25-2016 |
| 20160114885 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - A vertical take-off and landing aircraft includes a propulsion mechanism that generates lift and thrust, a main frame that supports seating and a landing undercarriage, a sub-frame which supports the propulsion mechanism and is arranged so as to be swingable back and forth relative to the main frame, a motive power supply unit supported by the main frame and supplying motive power to the propulsion mechanism, a control stick connected to the sub-frame, and a main wing arranged on the propulsion mechanism, wherein the main wing is formed to be retracted to a position not interfering with an air flow of the propulsion mechanism in a normal time and to be movable to a position where lift is generated when thrust is lost. Gliding is made possible even if thrust is lost while increasing in size of a fuselage is avoided. | 04-28-2016 |
| 20180024571 | SYSTEMS AND PROCESSES FOR CALIBRATING UNMANNED AERIAL VEHICLES | 01-25-2018 |
| Entries |
| Document | Title | Date |
|---|
| 20080223994 | MOVEABLE WINGS ON A FLYING/HOVERING VEHICLE - The present invention includes an embodiment defined as a flying vehicle having a pair of wings and a transition assembly partially housed within each of the pair of wings. The transition assembly has ends rotatable with respect to each other and separately secured to the wing in which the end is housed. The transition assembly has a first position defined as having each wing positioned at an angle offset from a substantial horizontal orientation and oriented in an opposite direction from the other wing. When the transition assembly is in the first position the vehicle spins and will fly in a substantially hovering vertical orientation. The transition assembly has a second position defined as having each wing positioned in a substantial horizontal position. When the transition assembly is in the second position the vehicle will fly in a substantially horizontal orientation. | 09-18-2008 |
| 20080230656 | Aircraft wings having hinged vanes and aircraft having said wings - Reconfigurable aircraft wings with at least one set of hinged upper and lower vanes and aircraft that are equipped with such wings are provided. When the aircraft are taking off or landing vertically, the hinged vanes are open in order to allow rotor thrust to go through the wings, thereby permitting main rotors to be located above the wings. When the aircraft reach certain airspeeds, the hinged vanes are closed in order to provide normal lift of a fixed wing. The aircraft thereby take advantages of the helicopter and the traditional airplane with a fixed wing. | 09-25-2008 |
| 20080272244 | Hybrid Aircraft - A hybrid aircraft ( | 11-06-2008 |
| 20090008510 | AIRCRAFT HAVING THE ABILITY FOR HOVERING FLIGHT, FAST FORWARD FLIGHT, GLIDING FLIGHT, SHORT TAKE-OFF, SHORT LANDING, VERTICAL TAKE-OFF AND VERTICAL LANDING - Aircraft having two, preferably four or more, rotors ( | 01-08-2009 |
| 20090014599 | Convertible aerial vehicle with contra-rotating wing/rotors and twin tilting wing and propeller units - A micro aerial vehicle can be converted during flight between a fixed wing flight mode and a rotary wing flight mode. The canard design micro aerial vehicle includes a fuselage, two tiltable propellers and airfoils arranged at a forward portion of fuselage, a pair of coaxial drive shafts positioned aft of the tiltable propeller and airfoil arranged for contra-rotation, a stop rotor mechanism, and a pair of wing panels, each of the wing panels attached to one of the coaxial drive shafts. The wing panels act as contra-rotating rotor blades in the rotary wing flight mode, and act as fixed wing panels in the fixed wing mode. | 01-15-2009 |
| 20090184209 | Constant-Velocity Drive System for Gimbaled Rotor Hubs - A constant-velocity drive system for a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. A rotary-wing aircraft having a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. | 07-23-2009 |
| 20090212166 | VTOL/STOL TILT-PROP FLYING WING - An aircraft comprises two wings, a fuselage, a tail planform and a pair of counter-rotating propellers. The two wings are located at a longitudinal center of gravity of the aircraft. The fuselage is located forward of the longitudinal center of gravity and coupled to the two wings. The tail planform is coupled to the two wings and located aft of the longitudinal center of gravity. The pair of counter-rotating propellers are located at the longitudinal center of gravity and between the wings. Further, the pair are coupled to a tilting mechanism for tilting the propellers between a vertical flight position and a forward flight position. One of the propellers located beneath the wings when in the vertical flight position and one of the propellers is located above the wings when in the vertical flight position. | 08-27-2009 |
| 20090261209 | CONVERTIBLE AIRCRAFT - A convertible aircraft comprising a main body integrating at least one substantially triangular wing ( | 10-22-2009 |
| 20100096508 | Aircraft and method of retrieving a rescue cradle into the aircraft fuselage - An aircraft capable of hovering, and having a fuselage defining an access opening; driving means for operating a rescue cradle; and a first wall movable between a closed position engaging a first portion of the opening, and a first open position allowing access to the first portion of the opening. The aircraft has a member connected functionally to the first wall and in turn having at least one flat surface; and the member is movable with respect to the wall into a first position, in which the flat surface defines a supporting surface for the cradle when the first wall is in the first open position. | 04-22-2010 |
| 20100108822 | Method for Suppressing Vibration in a Tiltrotor Aircraft - A method is disclosed for suppressing vibration in an aircraft having at least one pair of multiple-blade rotors. The first step of the method is to install in the aircraft at least one pair of vibration suppression devices to form a system, the devices of each system being mounted on opposing sides of the aircraft. Then, during operation of the aircraft, the next step is to rotate the at least one pair of rotors in a manner that causes the blades one of each pair of rotors to be out of phase from the other of each pair of rotors. The final step is to use the system to suppress vibrations caused by the out-of-phase rotation of the rotors. | 05-06-2010 |
| 20100171001 | Hover Delivery of Cabin Payload in Tilt-Rotor and Tilt-Wing Aircraft - A payload or cargo is delivered from a cargo hold of an aircraft during flight, by orienting the fuselage into a nose-up and tail-down position of at least 30 degrees off horizontal, and lowering the cargo from a cargo hold in the fuselage by means of one or more lines. Preferred vertical takeoff and landing (VTOL) aircraft include tilt-rotor or tilt-wing aircraft, and especially preferred aircraft are capable of generating control moments with their rotors to assist in orientating the fuselage of the aircraft into a nose-up and tail-down position. | 07-08-2010 |
| 20100193644 | Aircraft with Integrated Lift and Propulsion System - A vertical take off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles. Improvements include a high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system that is efficient in both hover and cruise flight. Preferred aircraft use thin inboard and outboard wings, thin rotor blades, and use efficient lightweight design to achieve unusually low empty weight fraction. Inventive methods include utilization of advanced design and analysis techniques, which allow for accurate prediction of an aircraft's physical behavior. | 08-05-2010 |
| 20100270435 | Wing efficiency for tilt-rotor aircraft - Rotorcraft wings disposed between tilt-rotor nacelles have particularly high aspect ratios for tilt-rotor rotorcraft, including for example at least 6, 7, 8, or higher. The increase in wing span and aspect ratio is possible because of the use of rigid and semi-rigid rotors, and/or higher modulus of elasticity materials allows increases the stiffness of the wings to the level required for avoiding whirl flutter. Tilt-rotor aircraft having high aspect ratio wings can advantageously further include a controller that provides reduced RPM in a forward flight relative to hover, and/or a controller that provides variable speed, (a so-called “Optimum Speed Tilt Rotor”) as set forth in U.S. Pat. No. 6,641,365 to Karem (November 2003). | 10-28-2010 |
| 20110031355 | Aircraft with dual flight regimes - The aircraft is capable of two distinct fuel-efficient flight regimes: one is a vertical flight regime supported by two large two-bladed rotors with low disc loading located on right and left longitudinal booms. The booms extend between outboard regions of a front wing and inboard regions of a rear wing that has a larger span an area. The other flight regime is high speed up to high subsonic Mach number with the aircraft supported by wing lift with high wing loading, and with the rotors stopped and faired with minimal local drag contiguous to the booms. The longitudinal location of the aircrafts center of gravity, aerodynamic center and the center of the rotors are in close proximity. The front wing is preferably swept back, and the rear wing is preferably of W planform. | 02-10-2011 |
| 20110114798 | LONG-RANGE AIRCRAFT WITH HIGH FORWARD SPEED IN CRUISING FLIGHT - The present invention relates to an aircraft ( | 05-19-2011 |
| 20110303795 | THREE-WING, SIX TILT-PROPULSION UNIT, VTOL AIRCRAFT - A vertical takeoff and landing aircraft having a fuselage with, preferably, 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 oriented vertically for vertical flight and horizontally for forward flight. Each propulsion unit comprises a propeller having a plurality of blades, where the pitch angle associated with the distal end of each blade and the proximal end of each blade are independently adjustable. As such, each of the propellers can be adjusted to exhibit a first blade pitch angle distribution optimized for vertical flight and a second blade pitch angle distribution optimized for forward flight. | 12-15-2011 |
| 20120168568 | ROTOR UNLOADING APPARATUS AND METHOD - A method and apparatus for enabling high speed flight in a rotorcraft are disclosed. The method may include executing a flight with a rotorcraft. The flight may include a first portion and second portion ordered sequentially. During the first portion, the rotorcraft may be flown with the rotor exclusively in autorotation. Once sufficient airspeed is obtained, the flight may transition to the second portion. Wherein, substantially all of the weight of the rotorcraft may be supported by one or more fixed wing surfaces of the rotorcraft. Thus, during the second portion, the rotor may be completely unloaded. To keep the rotor stable by turning, the rotor may be powered during the second portion by an engine of the rotorcraft by way of a prerotation system. | 07-05-2012 |
| 20120199699 | Tilt Rotor Aircraft with Fixed Engine Arrangement - The system of the present application includes an engine and pylon arrangement for a tilt rotor aircraft in which the engine is fixed in relation to a wing portion of the aircraft, while the pylon is rotatable. The pylon supports a rotor hub having a plurality of rotor blades. Rotation of the pylon allows the aircraft to selectively fly in a helicopter mode and an airplane mode, as well as any combination thereof. | 08-09-2012 |
| 20120261523 | Aircraft with Wings and Movable Propellers - The invention is a flight vehicle, and methods of operation thereof, having wings and movable propeller assemblies which can be rotated to provide vertical and/or horizontal thrust. The propeller assemblies are configured to maximize available engine/propeller thrust and to prevent propwash from striking the wings of the aircraft. | 10-18-2012 |
| 20120280091 | LIFT, PROPULSION AND STABILISING SYSTEM FOR VERTICAL TAKE-OFF AND LANDING AIRCRAFT - 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. | 11-08-2012 |
| 20130026302 | HIGH PERFORMANCE TILT ROTOR AIRCRAFT IN WHICH NACELLE TILT ANGLE AND FLAPERON ANGLE MECHANICALLY INTERWORK WITH EACH OTHER - Provided is a high performance tilt rotor aircraft in which a nacelle tilt angle and a flaperon angle mechanically interlock with each other. In the tilt rotor aircraft having nacelles in which rotors are mounted in left and right main wings and configured so that the nacelles rotate according to whether the tilt rotor aircraft conducts forward flight or vertical take-off and landing flight, each of the main wings is provided with a flaperon, and the nacelle and the flaperon are connected to each other by a power transfer unit, such that the flaperon also rotates together with the nacelle at the time of rotation of the nacelle, thereby allowing a change in a nacelle tilt angle to lead to a change in a flaperon angle. | 01-31-2013 |
| 20130026303 | CONVERTIPLANE - There is described a convertiplane comprising: a pair of semi-wings; at least two rotors which may rotate about relative first axes and tilt about relative second axes together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being, in use, transversal to a longitudinal direction of convertiplane in helicopter mode, and being, in use, substantially parallel to longitudinal direction in aeroplane mode; convertiplane further comprises at least two through openings within which said rotor may tilt, when said convertiplane moves, in use, between said helicopter and said aeroplane mode. | 01-31-2013 |
| 20130026304 | CONVERTIPLANE - There is described a convertiplane comprising: a pair of semi-wings; a first rotor comprising a shaft which may rotate about first axis and tilt about a second axis together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being transversal to a longitudinal direction of convertiplane in helicopter mode and being substantially parallel to longitudinal direction in aeroplane mode; convertiplane also comprises an electrical power storage device; and an electrical machine which comprises, in turn, a stator electrically connected to storage device; and a second rotor operatively connected to a shaft of first rotor; electrical machine acts as an electric motor for driving in rotation said first rotor by using the electrical power stored in storage device; or as an electrical power generator for re-charging storage device by causing the rotation second rotor under the action of a wind current. | 01-31-2013 |
| 20130026305 | CONVERTIPLANE - There is described a convertiplane comprising a pair of semi-wings, a first and a second rotor which may rotate about relative first axes and tilt about relative second axes together with first axes with respect to semi-wings between a helicopter mode and an aeroplane mode; first axes are, in use, transversal to a longitudinal direction of convertiplane in helicopter mode, and are, in use, substantially parallel to longitudinal direction in aeroplane mode; first and second rotors may tilt about relative second axes independently of each other. | 01-31-2013 |
| 20140061392 | Aircraft With Integrated Lift And Propulsion System - A vertical take-off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles or more, with glide ratios of at least 24. Improvements include a combination of high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system efficient in both hover and cruise flight. Preferred aircraft use narrow chord inboard and outboard wings, and use efficient lightweight design to achieve unusually low empty weight fraction. In some embodiments, the rotors use medium rather than high modulus fibers, with wider blades of lower taper ratio, to provide the stiffness and mass properties required for high performance OSTR rotor blades. Also disclosed are VTOL aircraft with glide ratios from approximately 26 to over 40. | 03-06-2014 |
| 20140084114 | VTOL Aircraft with Propeller tiltable around two Axes and a retractable Rotor - A VTOL aircraft has a rotor, wings, and a propeller providing thrust for take-off and landing and horizontal flight. The propeller, attached through a joint mechanism to the aircraft, is continuously tiltable around to axes, providing the anti-torque forces for the rotor and thrust forces for lifting the aircraft and for horizontal flight. The hubs of rotor blade sets are rotatable to each other for alignment. The rotor assembly, attached to a moveable linkage mechanism, is tiltable in or against the direction of flight and movable towards to or into the fuselage. The folded and retracted rotor reduces the air drag and the high thrust of the propeller increase the speed of winged flight. The flexibility and lower weight of the drive are preferably achieved with an advanced hydrostatic drivetrain. | 03-27-2014 |
| 20140110533 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - A vertical take-off and landing aircraft includes a propulsion mechanism having a fan for generating lift and thrust, an engine for supplying motive power to the propulsion mechanism, a frame coupling the propulsion mechanism and the engine, seating connected to and suspended from the frame so as to be swingable back and forth relative to the frame, a control stick connected to the frame, and a landing undercarriage connected to the seating, wherein the propulsion mechanism is connected to the frame such that the drive shaft of the fan is directed vertically during landing, and the frame is moved relative to the seating by manipulating the control stick, to change the orientation of the propulsion mechanism. The thrust can be controlled with simple configuration, and take-off and landing can be performed safely even in a small space surrounded by obstacles. | 04-24-2014 |
| 20140339372 | SYSTEM, A METHOD AND A COMPUTER PROGRAM PRODUCT FOR MANEUVERING OF AN AIR VEHICLE WITH TILTABLE PROPULSION UNIT - A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle. | 11-20-2014 |
| 20150360774 | ROTARY PYLON CONVERSION ACTUATOR FOR TILTROTOR AIRCRAFT - A tiltrotor aircraft can include a pylon rotatable about a conversion axis. A first differential planetary assembly can include a first housing; a first ring gear; a first differential planetary gear having a first output portion; and a first differential sun gear. A second differential planetary assembly can include a second housing; a second ring gear; a second differential planetary gear having a second output portion; and a second differential sun gear. The first output portion is coupled to the second housing such that the second housing rotates at a first output speed. Further, the second output portion is coupled to the shaft, the shaft being coupled to the pylon such that rotation of the shaft rotates the pylon. | 12-17-2015 |
| 20160023754 | Vertical take-off aircraft - A mechanism for stowing and/or adjusting a ducted propeller of a flying object, the flying object comprising a fuselage and at least one pair of wings, the outer walls of which together define a shell of the flying object, comprising a ducted propeller comprising a substantially cylindrical duct, which defines a longitudinal axis of the ducted propeller and is open at the base faces thereof, a rotor comprising a plurality of rotor blades, which is set up to rotate in a plane perpendicular to the longitudinal axis of the ducted propeller, and a drive device for driving the rotor; a receiving chamber, provided in the fuselage and/or a wing of the flying object, for the ducted propeller; a mechanism which is set up to transfer the ducted propeller from a stowed state into a deployed state. | 01-28-2016 |
| 20160167776 | Modular Flight Vehicle | 06-16-2016 |
| 20160167780 | CONVERTIPLANE WITH NEW AERODYNAMIC AND TECHNICAL SOLUTIONS WHICH MAKE THEAIRCRAFT SAFE AND USABLE | 06-16-2016 |
| 20160200436 | Tri-Rotor Aircraft Capable of Vertical Takeoff and Landing and Transitioning to Forward Flight | 07-14-2016 |
| 20170233069 | HYBRID MULTICOPTER AND FIXED WING AERIAL VEHICLE | 08-17-2017 |
| 20090045294 | Systems and Methods for Rotor/Wing Aircraft - Systems and methods for rotor/wing aircraft are disclosed. In one embodiment, an aircraft includes an airframe, a high-lift canard and tail, a rotor/wing, a propulsion system, and a drive assembly. The drive assembly, which may include a radial inflow turbine, is configured to extract work from the propulsion system to selectively rotate the rotor/wing assembly thus enabling the aircraft to conduct rotary-wing flight, fixed wing flight as well as smoothly transition between the two modes of flight. | 02-19-2009 |
| 20090206208 | Reaction drive rotor/wing variable area nozzle - In an exemplary variable area nozzle, a fixed duct section has an inlet and an outlet oriented approximately perpendicular to the inlet. A controllable nozzle member is disposed adjacent the outlet of the fixed duct section. The controllable nozzle member has an area that is adjustable to maintain a substantially constant nozzle pressure ratio. The controllable nozzle member may include first and second flap doors hinged and pivotable in opposite directions between an open position and a closed position and that also may be hinged and pivotable in a same direction so thrust from gas exiting the nozzle is vectorable. When disposed in rotor tips of an aircraft capable of rotary wing flight and fixed wing flight, the variable area nozzle may maintain a substantially constant nozzle pressure ratio near an optimized nozzle pressure ratio as the aircraft transitions from rotary wing flight to fixed wing flight. | 08-20-2009 |
| 20090266941 | Combination Spar and Trunnion Structure for a Tilt Rotor Aircraft - An aircraft is equipped with a spinnion coupling an inboard wing to a tilting nacelle. The spinnion is advantageously configured to extend across the nacelle from an inboard junction to an outboard junction, and terminates inside the inboard wing. This provides an efficient lightweight structure to support a nacelle and facilitate tilting of the nacelle. The spinnion, which can be configured to be at least partially disposed within the inboard wing, is advantageously concentric with the tilting axis in order to facilitate tilting of a nacelle. A cross-wing driveshaft can be included, disposed at least partly within the inboard wing, and can advantageously be configured to terminate inside the spinnion at a junction with a miter gearbox. The miter gearbox can be disposed at least partly within the spinnion but more preferably lies entirely within the spinnion, and functions to transfer power from an input shaft to the cross-wing driveshaft. | 10-29-2009 |
| 20100025543 | METHODS AND APPARATUS FOR TRANSFORMING UNMANNED AERIAL VEHICLE - Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro. | 02-04-2010 |
| 20100072325 | Forward (Upstream) Folding Rotor for a Vertical or Short Take-Off and Landing (V/STOL) Aircraft - This is an improvement of the 1968 Trailing Rotor V/STOL aircraft (Ref. 1). Rotors are mounted on wing-tip pods which can be tilted from the vertical to the horizontal aft position. Rotors are then stopped in the axial-flow condition and indexed to an azimuth position, aft of the wing trailing-edge. Rotor blades are then folded forward (blade-tips upstream of rotor-hubs) and locked into grooves in the tip-pods. | 03-25-2010 |
| 20100078526 | AIRCRAFT WITH A CONVERTIBLE FLIGHT SYSTEM - The invention relates to an aircraft with a convertible flight system which can function as a helicopter and as an airplane and comprising a fuselage ( | 04-01-2010 |
| 20100243820 | TAKING OFF AND LANDING AIRPLANE USING VARIABLE ROTARY WINGS - This invention is regarding a VTOL aircraft that is designed to enable it to take off by generating lift through rotary wings like a helicopter and then moving forward; and when it flies at high speeds, it is able to use jet engines so that it can generate lift through fixed wings while the rotary wings are transformed into fixed wings to generate lift by adjusting the angles between the individual wings thereby enhancing the efficiency | 09-30-2010 |
| 20100243821 | TAKING OFF AND LANDING AIRPLANE USING VARIABLE ROTARY WINGS - This invention is regarding a VTOL aircraft that is designed to enable it to take off by generating lift through rotary wings like a helicopter and then moving forward; and when it flies at high speeds, it is able to use jet engines so that it can generate lift through fixed wings while the rotary wings are transformed into fixed wings to generate lift by adjusting the angles between the individual wings thereby enhancing the efficiency. | 09-30-2010 |
| 20100276549 | Fail-operational multiple lifting-rotor aircraft - A rotorcraft having multiple rotors, and wings that provide lift in forward flight, has mechanical coupling between rotors that can be disengaged and optionally reengaged, during flight. The coupling can, which can prevent a failure of one rotor from interfering with rotation of the other rotor(s), can be accomplished using many different types of devices, including for example, dog clutches and friction clutches, and collapsible clutches. Disengagement can range from being completely under control of an operator, to partially under operator control, to completely automatic. Among many other benefits, designing, manufacturing, fitting, retrofitting or in some other manner providing an aircraft with a device that can disengage rotation of one of the rotors from that of another one of the rotors during flight can be used to improving survivability in an emergency situation. | 11-04-2010 |
| 20110001020 | QUAD TILT ROTOR AERIAL VEHICLE WITH STOPPABLE ROTORS - The disclosed invention consists of several improvements to well known Quad Tilt-Rotor (QTR) aircraft. The first is that during a wing-borne flight, one pair of tilt-rotors, which can be substantially larger than the other pair, is feathered and stopped. This can promote vehicle aerodynamic efficiency and can be utilized to increase vehicle speed. Second is that the wings are not attached to the fuselage at a fixed angle of incidence like on conventional QTR aircraft, but can also be tilted in respect to the fuselage independently of the tilt-rotors. Furthermore, each rotor and each wing can be tilted with respect to fuselage to any tilt-angle without limit, which gives the vehicle unprecedented ability to position the fuselage in any attitude in respect to the vehicle direction of flight. | 01-06-2011 |
| 20110006166 | ROTARY WING VEHICLE - A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight. | 01-13-2011 |
| 20110036954 | Compound Aircraft with Autorotation - A compound aircraft features variable incidence wings, a thruster, a rotor and a clutch connecting the engines to the rotor. Upon reaching a suitable forward speed, the control system of the compound aircraft unloads the rotor and disengages the clutch, disconnecting the rotor from the engines. The control system configures the cyclic and collective pitch effectors to cause the rotor to autorotate. The control system selects an autorotation rotational speed that is adequately rapid to prevent excessive deformation of the rotor blades due to aerodynamic forces acting on the blade and that is adequately slow to prevent excessive compressibility effects. | 02-17-2011 |
| 20110114797 | Fail-Operational Multiple Lifting-Rotor Aircraft - A rotorcraft having multiple rotors, and wings that provide lift in forward flight, has a mechanical coupling between rotors that can be disengaged and optionally reengaged, during flight. The coupling, which can prevent a failure of one rotor from interfering with rotation of the other rotor(s), can be accomplished using many different types of devices, including for example, dog clutches, friction clutches, and collapsible clutches. Disengagement can range from being completely under control of an operator, to partially under operator control, to completely automatic. Among many other benefits, designing, manufacturing, fitting, retrofitting or in some other manner providing an aircraft with a device that can disengage rotation of one of the rotors from that of another one of the rotors during flight can be used to improve survivability in an emergency situation. | 05-19-2011 |
| 20110180673 | TAKING OFF AND LANDING AIRPLANE USING VARIABLE ROTARY WINGS - This invention is regarding a VTOL aircraft that is designed to enable it to take off by generating lift through rotary wings like a helicopter and then moving forward; and when it flies at high speeds, it is able to use jet engines so that it can generate lift through fixed wings while the rotary wings are transformed into fixed wings to generate lift by adjusting the angles between the individual wings thereby enhancing the efficiency. | 07-28-2011 |
| 20110315827 | Wing Extension Control Surface - A tiltrotor aircraft includes a rotatable nacelle that supports a rotor assembly and is pivotally attached to the air-craft's fuselage. A wing extension attaches to an outboard section of the nacelle. The wing extension provides additional yaw control during helicopter mode and additional lift during airplane mode. A method for controlling at least a portion of yaw movement includes positioning the rotor assembly in helicopter mode, creating rotor wash with the rotor assembly, and pivotally rotating the wing extension in the rotor wash. | 12-29-2011 |
| 20120097801 | SUPERSONIC HOVERING AIR VEHICLE - Embodiments of the present invention include an aircraft capable of sustained out-of-ground-effect hover flight and sustained supersonic flight. At least some embodiments includes two wings powered by an engine to counterrotate while hovering, and to not rotate and sweep while flying at transonic and supersonic speeds. Other embodiments include two rotating wings that generate a force per unit area of under 100 lb/ft2 within the rotating wing disk during hover. Still other embodiment include a vehicle with rotating wings that can increase pitch to accelerate the aircraft, align the chord line of the wings with the airstream, and sweep the wings. Still further embodiments include a power plant that powers unducted rotating wings during hover and disengages from the wings to propel the aircraft at supersonic speeds. | 04-26-2012 |
| 20120223191 | Short Landing Air Vehicle by the use of Rotating Wings - An air vehicle | 09-06-2012 |
| 20120248259 | LONG ENDURANCE VERTICAL TAKEOFF AND LANDING AIRCRAFT - An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode. | 10-04-2012 |
| 20120292456 | Method and Apparatus for In-Flight Blade Folding - A foldable rotor system for a rotorcraft, the foldable rotor system comprising a rotor assembly operably associated with a driveshaft, the driveshaft being operable associated with an engine, the rotor assembly comprising a rotor blade connected to a grip pin. A swashplate is operable associated with the grip pin in order selectively change a pitch of the rotor blade. A blade fold actuator is operably associated with the grip pin such that the blade fold actuator is configured to fold and unfold the rotor blade about a blade fold axis. During an airplane mode, the rotorcraft can stop and fold the rotor blades so that the rotorcraft relies upon thrust from the engine for propulsion. The rotor blades are folded in a spiral fold path so that the rotor blades remain substantially edgewise, or feathered, during the folding process. The spiral fold path minimizes the aerodynamic drag experienced by the rotor blades while being folded during flight of the rotorcraft. | 11-22-2012 |
| 20130105636 | Rotor System Anti-Rotation Wear Protector | 05-02-2013 |
| 20130134264 | Electric Motor Powered Rotor Drive for Slowed Rotor Winged Aircraft - A rotor aircraft has an engine, a propeller, wings, and a rotor. An electric motor is coupled to the rotor drive shaft for applying torque to the rotor drive shaft. The electric motor is sized to supply all of the torque to pre-rotate the rotor to a selected speed prior to liftoff of the aircraft. The wings are capable of providing substantially all of the lift required during forward flight at a cruise speed. The rotor being is capable of being trimmed to provide substantially zero lift and auto-rotate at cruise speed. Sensors sense flight conditions of the aircraft and provide signals to a controller that selectively causes the electric motor to cease applying torque to the rotor drive shaft during autorotation at cruise speed. The controller also causes the electric motor to apply torque to the rotor drive shaft if the sensors indicate additional rotor speed is needed. | 05-30-2013 |
| 20130175404 | AIRCRAFT WITH FIXED AND TILTING THRUSTERS - An aircraft including a fuselage with a yaw axis, a pitch axis and a roll axis, two attitude control thrusters, fixedly connected to the fuselage to provide thrust parallel to the yaw axis, two locomotion and hover thrusters. The aircraft further includes for the locomotion and hover thruster, a mechanism for tilting the locomotion and hover thruster about a tilt axis parallel to the pitch axis to select a direction, parallel to a first plane defined by the yaw and roll axes, in which the locomotion and hover thruster provides thrust. | 07-11-2013 |
| 20130264429 | CONVERTIBLE AIRPLANE - A convertible airplane is described. The convertible airplane has a fuselage, a trapezoidal wing, two counter rotating front rotors, and an aft rotor. | 10-10-2013 |
| 20140217243 | TILT ROTOR AIRCRAFT WITH FIXED ENGINE ARRANGEMENT - The system of the present application includes an engine and pylon arrangement for a tilt rotor aircraft in which the engine is fixed in relation to a wing portion of the aircraft, while the pylon is rotatable. The pylon supports a rotor hub having a plurality of rotor blades. Rotation of the pylon allows the aircraft to selectively fly in a helicopter mode and an airplane mode, as well as any combination thereof. | 08-07-2014 |
| 20140263854 | Tiltrotor Aircraft With Inboard Wing Mounted Fixed Engine Arrangement - A rotor system for tilt rotor aircraft comprises an engine disposed at a first fixed position on a wing member, and a prop-rotor pylon mechanically coupled to the engine along a drive path extending through the wing member. The engine is disposed adjacent a fuselage of the tilt rotor aircraft, and the prop-rotor pylon is configured to selectively rotate between a vertical position and a horizontal position. The prop-rotor pylon is coupled to a plurality of rotor blades. | 09-18-2014 |
| 20140263855 | Spindle Mounted Tiltrotor Pylon with Fixed Engine Arrangement - A rotor system for tilt rotor aircraft comprises an engine disposed at a first fixed location on a wing member; a prop-rotor pylon mechanically coupled to the engine along a drive path, and a gearbox disposed in the drive path. The prop-rotor pylon is rotatably mounted on a spindle, and the prop-rotor pylon is configured to selectively rotate about a rotational axis of the spindle between a vertical position and a horizontal position. The gearbox comprises a rotational axis aligned with the rotational axis of the spindle. | 09-18-2014 |
| 20140312177 | Coaxial rotor/wing aircraft - A system and method which enable efficient, rapid and safe transition between rotary-wing and fixed-wing flight mode in rotor/wings aircrafts is disclosed. The aircraft comprises of two rotor/wings on the same axis of rotation, one above the fuselage and the other one under the fuselage. During rotary-wing mode, the rotor/wings rotate coaxially and provide vertical lift. During transition between rotary-wing and fixed-wing modes, the synchronised operation of the two rotor/wings maintains lateral symmetry of lift on the aircraft. The reaction of the rotor/wings on the fuselage is also canceled. During fixed-wing flight mode, the two rotor/wings are stopped and locked in a biplane configuration, both providing lift as fixed wings. The rotor/wings may be further reconfigured for higher subsonic or supersonic speed. Tandem and multiple rotor/wings aircrafts with increased cargo capacity, speed and range, comprise of multiple of these coaxial rotor/wings. | 10-23-2014 |
| 20140346283 | AIRCRAFT USING TURBO-ELECTRIC HYBRID PROPULSION SYSTEM FOR MULTI-MODE OPERATION - A vehicle incorporating a hybrid propulsion system. In one form, the vehicle may be an aircraft such that the system includes gas turbine engines as a first motive power source, and one or more battery packs as a second motive power source. Through selective coupling to an electric motor that can in turn be connected to a bladed rotor or other lift-producing device, the motive sources provide differing ways in which an aircraft can operate. In one example, the gas turbine engines can provide operation for a majority of the flight envelope of the aircraft, while the battery packs can provide operation during such times when gas turbine-based motive power is unavailable or particularly disadvantageous. In another example, both sources of motive power may be decoupled from the bladed rotor such that the vehicle can operate as an autogyro. In another mode of operation, the movement of a bladed rotor can be both decoupled from the sources of propulsion as well as fixed relative to the aircraft such that the aerodynamic surfaces formed on the bladed rotors can act as a fixed wing. In another particular form, the vehicle may be ground-based or water-based. | 11-27-2014 |
| 20150034772 | Composite Flexure for Tiltrotor Rotor System - According to one embodiment, a composite flexure may secure a rotor blade to a yoke in a tiltrotor rotor system. The composite flexure includes a composite body, a first end configured to couple the composite member to the yoke, and a second end configured to couple the composite member to the rotor blade. | 02-05-2015 |
| 20150048213 | FIXED ENGINE AND ROTATING PROPROTOR ARRANGEMENT FOR A TILTROTOR AIRCRAFT - A tiltrotor aircraft includes a fuselage; a wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin; an engine disposed at a fixed location relative to the wing member; and a proprotor having a spindle gearbox, rotor mast, and a plurality of rotor blades drivable in rotation about the rotor mast, the spindle gearbox being rotatable about a conversion axis. The spindle gearbox is located above the upper wing skin of the wing member. | 02-19-2015 |
| 20150048214 | METHOD AND APPARATUS OF CONNECTING A FIXED DRIVE SYSTEM TO A ROTATING DRIVE SYSTEM FOR A TILTROTOR AIRCRAFT - A quill shaft is configured for transferring torque and accepting misalignments between a fixed gearbox and a rotatable spindle gearbox in a propulsion system of a tiltrotor aircraft, the quill shaft includes a first splined portion configured for coupling to an output gear of the fixed gearbox, and a second splined portion configured for coupling to an input gear of the spindle gearbox. The spindle gearbox includes a rotor mast associated therewith, the spindle gearbox being rotatable so that the tiltrotor aircraft can selectively operate in a helicopter mode and airplane mode. | 02-19-2015 |
| 20150102175 | FIXED WINGED AIRCRAFT WITH FOLDABLE AUTO-ROTATION ROTOR - The subject matter discloses a fixed wing aircraft comprising one or more foldable auto-rotation rotors operating on the fixed wing aircraft, each of the one or more foldable auto-rotation rotors comprising one or more foldable blades; the one or more foldable auto-rotation rotors are stopped while the fixed wing aircraft is flying; the one or more foldable auto-rotation rotors are started while the fixed wing aircraft is flying; the one or more foldable blades are folded while the fixed wing aircraft is flying; the one or more foldable blades are expanded while the fixed wing aircraft is flying; one or more masts, each of the one or more masts connects a foldable auto-rotation rotor of the one or more foldable auto-rotation rotors to the fixed wing aircraft; the one or more masts are foldable while the fixed wing aircraft is flying; the one or more masts are expanded while the fixed wing aircraft is flying; the one or more masts are positioned vertically and rearwards; a disk plane of the one or more auto-rotation rotors is positioned vertically and rearwards with respect to the fixed wing aircraft during forward flight. | 04-16-2015 |
| 20150122953 | Drive Link for Tiltrotor Rotor System - According to one embodiment, a drive link includes a first bearing housing, a second bearing housing, and a central portion coupled between the first bearing housing and the second bearing housing. The central portion has less torsional stiffness than the first and second bearing housings such that the central portion twists in response to cocking of the first bearing housing relative to the second bearing housing. | 05-07-2015 |
| 20160001878 | EASY LANDING DRONE - Disclosed is an easy landing drone. The drone includes: a propeller changing direction; a propeller tower supporting the propeller; a body connected to the propeller tower; a main wing arranged left-right symmetrically with respect to a horizontal axis of the body and having a pair of holes around a center of gravity of the body; a pair of auxiliary wings disposed in the pair of holes, respectively; and an actuator connected to a base shaft fixed to the main wing through the pair of auxiliary wings and controlling angles of the pair of auxiliary wings. | 01-07-2016 |
| 20160031556 | Impact Resistant Propeller System, Fast Response Electric Propulsion System And Lightweight Vertical Take-Off And Landing Aircraft Using Same - An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight. An aerial vehicle adapted to withstand impacts upon its propellers. An aerial vehicle able to quickly alter the thrust of its propellers. | 02-04-2016 |
| 20160046369 | AIRCRAFT AND METHODS FOR OPERATING AN AIRCRAFT - An aircraft ( | 02-18-2016 |
| 20160101853 | VERTICAL TAKE OFF AND LANDING AIRCRAFT - A vertical takeoff and landing aircraft is provided. The aircraft includes a fuselage having a first end, a second end, and a center of gravity in between the first end and the second end. Wings may extend from the side of the fuselage. The wings may include a canard at the first end, and a wing at the second end. The present invention may further include a pair of engines pivotally attached on either side of the fuselage and substantially aligning with the center of gravity. | 04-14-2016 |
| 20190144107 | Segmented Duct for Tilting Proprotors | 05-16-2019 |
| 20100252690 | AIRCRAFT - An unmanned aerial vehicle (UAV) in the form of a “tail sitter” flying wing adapted for vertical take off and landing and transitions between flight as a helicopter and wing-borne flight. The vehicle is electrically powered from onboard batteries and equipped with rotors on miniature helicopter rotor heads at the tips of the wing for both lift, during take off and landing, and forward thrust. In planform the wing comprises, to each side of its longitudinal axis, an inner section with swept back leading and trailing edges, and an outer section with a leading edge more perpendicular to the longitudinal axis, being only mildly swept back or substantially unswept, and a swept forward trailing edge. | 10-07-2010 |
| 20120286102 | REMOTELY CONTROLLED VTOL AIRCRAFT, CONTROL SYSTEM FOR CONTROL OF TAILLESS AIRCRAFT, AND SYSTEM USING SAME - 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 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. A tailless airplane which uses a control system that takes inputs for a traditional tailed airplane and translates those inputs to provide control utilizing non-traditional control methods. | 11-15-2012 |
| 20160375998 | VERTICAL TAKE-OFF AND LANDING DRAG RUDDER - A system for a tail-sitter aircraft includes a fuselage having one or more propellers, a wing structure coupled to the fuselage, and a drag rudder assembly coupled to the wing structure, the drag rudder assembly including a first planar member that is coupled to a second planar member. The drag rudder assembly is configured to produce a stabilizing force on the wing structure during higher speeds of the aircraft in tandem rotor flight. | 12-29-2016 |
| 20170233070 | VERTICAL TAKEOFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV) | 08-17-2017 |
| 20090045295 | Vertical/Short Take-Off and Landing Aircraft - A vertical/short take-off and landing aircraft with a single proprotor assembly that has a pair of inline counter-rotating rotors. Two inline counter-rotating engines are directly connected to the rotors. One engine is shut down in horizontal flight to improve efficiency. Gimbal mounting the proprotor assembly permits thrust to be directed forward to back and left to right to control pitch and roll when hovering. Varying the relative engine speeds controls yaw. The aircraft is adaptable as an unmanned vehicle. | 02-19-2009 |
| 20090266942 | Tilt outboard wing for tilt rotor aircraft - Tilt-rotor aircraft experience increased efficiency and fuel economy by including wing extensions outboard of the tilting nacelles. Stall and buffeting during conversion from rotor-born hover to wing-born forward flight are reduced to an acceptable level using wide chord flaps deflected upwards by at least 15-20°, preferably in combination with leading edge slats. The outboard wing or wing portion is preferably has a span at least 25-40% of a span of the inboard section, and a total surface area at least 10-20% the total surface area of the corresponding inboard section. | 10-29-2009 |
| 20090283644 | CONTROL LEVER ASSEMBLY FOR A TILT-ROTOR AIRCRAFT - A control lever assembly for a tilt-rotor aircraft, comprises at least one control lever which is movable relative to a control lever support. The control lever support has a rotational position that varies in correspondence with the tilt of the rotor of the aircraft. For example, the control lever support is movable by an actuator between a first position, in the airplane mode of the aircraft, in which the control lever moves substantially horizontally and a second position, in the helicopter mode of the aircraft, in which the control lever moves substantially vertically. | 11-19-2009 |
| 20100230547 | Stop-rotor rotary wing aircraft - Systems and methods for transitioning an aircraft between helicopter and fixed wing flight modes are provided. In one embodiment, an aircraft comprises a plurality of wings each having a spar and a flap; a flap actuator configured to move the flap with respect to the spar; and a center section rotatably coupled to each spar. The center section includes at least one spar actuator configured to rotate at least one of the wings about a rotational axis of the spar when the aircraft transitions between helicopter and fixed wing flight modes. | 09-16-2010 |
| 20100327123 | Rotorcraft with Variable Incident Wing - A twin-rotor side-by-side compound rotorcraft has a fuselage and variable incident wing assembly that pivots relative to fuselage. The aircraft also has landing gear assembly and a tail fin assembly. The variable incident wing assembly is pivotally attached to the fuselage, and includes wing members, engines fixedly mounted to the wing members or another area of the rotorcraft, and a mast attached at a fixed angle relative to the wing members. Then engines may also be located near the fuselage or another area of the rotorcraft. The variable incident wing assembly is capable of pivoting about a pivot axis, thereby allowing mast orientation in at least a hover mast position and a forward flight mast position. The rotors provide additional forward thrust and the wings provide additional lift, when the mast is in the forward flight mast position. | 12-30-2010 |
| 20110036955 | Aircraft with Integrated Lift and Propulsion System - A vertical take off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles. Improvements include a high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system that is efficient in both hover and cruise flight. Preferred aircraft use thin inboard and outboard wings, thin rotor blades, and use efficient lightweight design to achieve unusually low empty weight fraction. Inventive methods include utilization of advanced design and analysis techniques, which allow for accurate prediction of an aircraft's physical behavior. | 02-17-2011 |
| 20120061526 | Rotor Blade Spacing for Vibration Attenuation - A rotor system for a rotorcraft, the rotor system is a rotor hub having six rotor blades attached to a rotor mast via a rotor yoke assembly. Each rotor blade is angularly spaced in 30° and 90° alternating angular increment about a mast axis of rotation. Such rotor blades spacing reduces the vibration that is translated into the rotorcraft through the rotor mast. | 03-15-2012 |
| 20120211608 | TILT-ROTOR AIRCRAFT - A convertiplane having a fuselage with a first axis; and two rotors having respective shafts and fitted to a wing having a fixed portion connected to the fuselage, and a movable portion which supports the rotors, is connected to the fixed portion to rotate about a second axis crosswise to the first axis and to the shafts of the rotors, and is formed in one piece defined by two half-wings located on opposite sides of the fixed portion and each supporting a respective rotor, and by an elongated member extending along the whole wing and connecting the two half-wings; the rotors being powered by a motor via a transmission comprising a transmission shaft connecting the shafts of the rotors and coaxial with the second axis. | 08-23-2012 |
| 20130099065 | TILT-WING AIRCRAFT - A tilt-wing aircraft is provided. The tilt-wing aircraft includes a tail drive and control unit. The control unit is configured to generate a forward thrust. The control unit can also generate an upwardly or downwardly directed thrust component and/or a laterally directed thrust component in hover flight and in climb flight of the aircraft. | 04-25-2013 |
| 20130206921 | 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. | 08-15-2013 |
| 20130256465 | Rotorcraft with Variable Incident Wing - A twin-rotor side-by-side compound rotorcraft has a fuselage and variable incident wing assembly that pivots relative to fuselage. The aircraft also has landing gear assembly and a tail fin assembly. The variable incident wing assembly is pivotally attached to the fuselage, and includes wing members, engines fixedly mounted to the wing members or another area of the rotorcraft, and a mast attached at a fixed angle relative to the wing members. Then engines may also be located near the fuselage or another area of the rotorcraft. The variable incident wing assembly is capable of pivoting about a pivot axis, thereby allowing mast orientation in at least a hover mast position and a forward flight mast position. The rotors provide additional forward thrust and the wings provide additional lift, when the mast is in the forward flight mast position. | 10-03-2013 |
| 20140191088 | Aircraft With Integrated Lift And Propulsion System - A vertical take off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles. Improvements include a high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system that is efficient in both hover and cruise flight. Preferred aircraft use thin inboard and outboard wings, thin rotor blades, and use efficient lightweight design to achieve unusually low empty weight fraction. Inventive methods include utilization of advanced design and analysis techniques, which allow for accurate prediction of an aircraft's physical behavior. | 07-10-2014 |
| 20160031555 | AERODYNAMICALLY EFFICIENT LIGHTWEIGHT VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH PIVOTING ROTORS AND STOWING ROTOR BLADES - An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes. | 02-04-2016 |
| 20160052618 | A TRANSITION ARRANGEMENT FOR AN AIRCRAFT - According to the invention there is provided a transition arrangement ( | 02-25-2016 |
| 20160114885 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - A vertical take-off and landing aircraft includes a propulsion mechanism that generates lift and thrust, a main frame that supports seating and a landing undercarriage, a sub-frame which supports the propulsion mechanism and is arranged so as to be swingable back and forth relative to the main frame, a motive power supply unit supported by the main frame and supplying motive power to the propulsion mechanism, a control stick connected to the sub-frame, and a main wing arranged on the propulsion mechanism, wherein the main wing is formed to be retracted to a position not interfering with an air flow of the propulsion mechanism in a normal time and to be movable to a position where lift is generated when thrust is lost. Gliding is made possible even if thrust is lost while increasing in size of a fuselage is avoided. | 04-28-2016 |
| 20180024571 | SYSTEMS AND PROCESSES FOR CALIBRATING UNMANNED AERIAL VEHICLES | 01-25-2018 |
