Entries |
Document | Title | Date |
20080237392 | COMPOUND AIRCRAFT CONTROL SYSTEM AND METHOD - The Invention is a control system for a compound aircraft. A compound aircraft has features of both a helicopter and a fixed wing aircraft and provides redundant control options. The control system allows an authorized person to select any of plurality of control biases each which is designed to achieve an overall operational objective. The control system applies the selected control bias in allocating the control function among the redundant control options. | 10-02-2008 |
20090032638 | NOVEL HELICOPTER - This invention discloses a helicopter that can directly propel rotors into the hovering state with drive, comprising a fuselage ( | 02-05-2009 |
20090250548 | FLEXIBLE DUCTING SYSTEM INCLUDING AN ARTICULABLE SEALED JOINT - Aircraft including a powerplant mounted on an airframe and a rotor/wing rotatably mounted on the airframe. The rotor/wing has multiple blades extending outward from roots adjacent the airframe to tips opposite the roots and having internal conduits extending between inlets adjacent the roots and downstream outlets. The aircraft also includes multiple intermediate ducts having upstream ends including flanges and downstream ends slidably and pivotally connected to corresponding blade inlets. Moreover, the aircraft includes a manifold having an upstream end in fluid communication with the powerplant and multiple downstream ends including flanges connected to upstream ends of corresponding intermediate ducts. The aircraft further includes multiple covers connected to corresponding manifold flanges and covering corresponding intermediate duct flanges. The aircraft also includes multiple absorbers positioned between corresponding intermediate duct flanges and manifold flanges and between the intermediate duct flanges and corresponding covers to control movement of the intermediate duct flanges. | 10-08-2009 |
20090321554 | FAST HYBRID HELICOPTER WITH LONG RANGE - A hybrid helicopter ( | 12-31-2009 |
20100001120 | High-speed aircraft with vertical lift and self-revolving ability - An aircraft includes a fuselage; a cockpit formed in the fuselage; a coaxial rotor assembly mounted to the top of fuselage, containing an upper rotor and a lower rotor, drivable by a first motor inside the fuselage; wherein, the aircraft also comprises: a couple of fixed wings mounted to the opposite sides of the aircraft respectively; and a rear propeller mounted to the tail end of fuselage, driven by a second motor inside the fuselage. The aircraft of the invention has the advantages of helicopter and autogyro, such as high-safety and high-speed. | 01-07-2010 |
20100065677 | HYBRID HELICOPTER THAT IS FAST AND HAS LONG RANGE - A hybrid helicopter ( | 03-18-2010 |
20100133375 | HYDRAULIC VALVE, A HYBRID HELICOPTER PROVIDED WITH SUCH A HYDRAULIC VALVE, AND A METHOD IMPLEMENTED BY THE HYDRAULIC VALVE - A hydraulic valve assembly includes a hydraulic valve, a control rod configured to be moved in translation along a first longitudinal axis by flight controls of an aircraft, a servocontrol, and an outlet rod configured to be moved in translation along a second longitudinal axis and configured to transfer a hydraulic fluid between the servocontrol and the hydraulic valve. A blocker device is configured to block a movement of the control rod when a difference between a first movement of the control rod and a second movement of the outlet rod exceeds a predetermined threshold and includes at least one moveable abutment configured to block the movement of the control rod when the predetermined threshold is reached and configured to move in longitudinal translation with the outlet rod, and a differential lever configured to mechanically link the control rod to the outlet rod and to cooperate with the at least one moveable abutment. | 06-03-2010 |
20100219286 | FAST HYBRID HELICOPTER WITH LONG RANGE AND AN OPTIMIZED LIFT ROTOR - A hybrid helicopter ( | 09-02-2010 |
20100243792 | METHOD AND A DEVICE FOR OPTIMIZING THE OPERATION OF PROPULSIVE PROPELLERS DISPOSED ON EITHER SIDE OF A ROTORCRAFT FUSELAGE - A method of optimizing the operation of left and right propellers disposed on either side of the fuselage of a rotorcraft including a main rotor. Left and right aerodynamic surfaces include respective left and right flaps suitable for being deflected, yaw stabilization of the rotorcraft being achieved via first and second pitches respectively of the left and right propellers, and the deflection angles of the left and right flaps are adjusted solely during predetermined stages of flight in order to minimize a differential pitch of the left and right propellers so as to optimize the operation of the left and right propellers, the predetermined stages of flight including stages of flight at low speed performed at an indicated air speed (IAS) of the rotorcraft that is below a predetermined threshold, and stages of yaw-stabilized flight at high speed performed at an indicated air speed of the rotorcraft greater than the predetermined threshold. | 09-30-2010 |
20100308154 | METHOD OF CONTROLLING A HYBRID HELICOPTER IN YAW, AND A HYBRID HELICOPTER PROVIDED WITH A YAW CONTROL DEVICE SUITABLE FOR IMPLEMENTING SAID METHOD - A method of controlling the yaw attitude of a hybrid helicopter including a fuselage and an additional lift surface provided with first and second half-wings extending from either side of the fuselage, each half-wing being provided with a respective first or second propeller. The hybrid helicopter has a thrust control suitable for modifying the first pitch of the first blades of the first propeller and the second pitch of the second blades of the second propeller by the same amount. The hybrid helicopter includes yaw control elements for generating an original order for modifying the yaw attitude of the hybrid helicopter by increasing the pitch of the blades of one propeller and decreasing the pitch of the blades of the other propeller, the original order is optimized as a function of the position of the thrust control to obtain an optimized yaw control order that is applied to the first and second blades. | 12-09-2010 |
20110024551 | VARIABLE DAMPING OF HAPTIC FEEDBACK FOR A FLIGHT-ATTITUDE CHANGING LINKAGE OF AN AIRCRAFT - The present invention relates to haptic feedback for operating at least one manual flight control device ( | 02-03-2011 |
20110024552 | Anhedral Tip Blades for Tiltrotor Aircraft - A tiltrotor aircraft having a fixed wing and tilting rotors has a rotor blade with a shaped tip portion that provides improved hover performance. The shaped tip portion preferably has a terminal anhedral of at least 20° with respect to its stacking line, and the blade has an overall twist from root to tip of at least 20°, and a thickness ratio between 19% and 30% at a radial station of 10%. These features advantageously conspire to provide a hover figure of merit of at least 0.84 and a cruise propulsive efficiency of at least 0.85. A controller preferably limits the rotor speed in sustained airplane-mode forward flight cruise of at most 40% of a hover maximum rotor speed, and alternatively or additionally limits a rotor edgewise advance ratio to at most 0.20. | 02-03-2011 |
20110272519 | Aircraft with Helicopter Rotor, Thrust Generator and Assymetric Wing Configuration - An aircraft features a source of forward thrust on a fuselage having a helicopter rotor assembly and an asymmetric primary wing configuration providing more wing-generated lift on one side of the fuselage than the other. The primary wing configuration counteracts the rotor's dissymmetry of lift during forward cruising, and reliance on the separate thrust source for such cruising reduces demand on the main rotor, keeping the angle of attack on the rotor blades low to avoid the stalling and violent vibration experienced by conventional helicopters at relatively high speeds. In some embodiments, an oppositely asymmetric tail wing or horizontal stabilizer acts alone, or together with an offset vertical stabilizer laterally outward from the tail, to counteract yaw-inducing drag of the primary wing. | 11-10-2011 |
20120012692 | Personal Aircraft - A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight. | 01-19-2012 |
20120043412 | Rotor Hub and Controls for Multi-Bladed Rotor System - A rotor system for a rotorcraft includes a rotor hub having a plurality of rotor blade pairs mechanically coupled to a rotor mast. A pitch link assembly is mechanically coupled to each rotor blade pair for controlling the pitch angle of each rotor blade pair in tandem. Each rotor blade pair has an upper rotor blade and a lower rotor blade. The plurality of rotor blade pairs rotor in a single direction and about a single axis of rotation. | 02-23-2012 |
20120318908 | VTOL twin fuselage amphibious aircraft with tilt-center wing, engine and rotor - VTOL amphibious aircraft comprising two fuselages spaced apart to enable the placement of center wing and ailerons, engine and rotor or fan such that they may be rotated from vertical flight to horizontal flight and back while center wing ailerons counter rotor torque. Out board wings remain fixed and the twin fuselages provide hulls to facilitate water landings. Standard aircraft components are employed such as a vertical tails and horizontal stabilizers. | 12-20-2012 |
20130020429 | Personal Aircraft - A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight. | 01-24-2013 |
20130082135 | HYBRID AIRCRAFT HAVING A ROTARY WING - An aircraft ( | 04-04-2013 |
20130175383 | ROTARY-WING AND FIXED-WING AIRCRAFT - An aircraft ( | 07-11-2013 |
20130214086 | Personal Aircraft - A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight. | 08-22-2013 |
20130334359 | AIRCRAFT WING EXTENSION AND NOZZLE SYSTEM - A system and method to control flight of an aircraft. The aircraft having an engine with a rotatably nozzle assembly configured to create forward propulsion and yaw control of the aircraft. The engine exhaust passing through the nozzle is redirected with a valve disposed within the nozzle. Lift is created with a lift system carried by the wing of the aircraft. Additional lift is created during flight with a retractable wing extension disposed within the wing of the aircraft. | 12-19-2013 |
20140034774 | FAST, LONG-RANGE AIRCRAFT - An aircraft ( | 02-06-2014 |
20140061366 | COMPOUND HELICOPTER WITH TAIL BOOMS - The present invention is related to a compound helicopter ( | 03-06-2014 |
20140061367 | COMPOUND HELICOPTER - The invention relates to a compound helicopter ( | 03-06-2014 |
20140084105 | METHOD OF CONTROLLING THE WING FLAPS AND HORIZONTAL STABILIZER OF A HYBRID HELICOPTER - A method of controlling a high speed rotary wing aircraft ( | 03-27-2014 |
20140084106 | METHOD OF CONTROLLING THE WING FLAPS AND HORIZONTAL STABILIZER OF A HYBRID HELICOPTER - A method of controlling a high-speed rotary wing aircraft ( | 03-27-2014 |
20140097290 | ELECTRICALLY POWERED AERIAL VEHICLES AND FLIGHT CONTROL METHODS - An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control. | 04-10-2014 |
20140151494 | VERTICAL TAKE-OFF AND LANDING (VTOL) AERIAL VEHICLE AND METHOD OF OPERATING SUCH A VTOL AERIAL VEHICLE - A Vertical Take-off and Landing (VTOL) aerial vehicle ( | 06-05-2014 |
20140217229 | UNMANNED AERIAL VEHICLE - An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes. | 08-07-2014 |
20140239116 | TWIN-FUSELAGE ROTORCRAFT - A rotorcraft ( | 08-28-2014 |
20140319265 | METHOD OF AUTOMATICALLY TRIGGERING AN EMERGENCY BUOYANCY SYSTEM FOR A HYBRID HELICOPTER - A method of automatically triggering an emergency buoyancy system ( | 10-30-2014 |
20140353419 | ROTARY WING ROTORCRAFT HAVING A PLURALITY OF PROPELLERS - A hybrid aircraft ( | 12-04-2014 |
20140353420 | ROTARY WING ROTORCRAFT HAVING A PLURALITY OF PROPELLERS - A hybrid aircraft ( | 12-04-2014 |
20150014475 | Vertical Takeoff and Landing (VTOL) Air Vehicle - A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing. | 01-15-2015 |
20150028151 | Aerodynamically Efficient Lightweight Vertical Take-Off And Landing Aircraft With Multi-Configuration Wing Tip Mounted Rotors - An aerial vehicle adapted for vertical takeoff and landing using a set of wing tip mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the wings in a horizontal flight attitude then transitions to a horizontal flight path. An aerial vehicle which uses different configurations of its wing tip mounted, VTOL enabling rotors to reduce drag in all flight modes. | 01-29-2015 |
20150136897 | AIRCRAFT, PREFERABLY UNMANNED - The invention relates to an aircraft ( | 05-21-2015 |
20150329204 | Vertical Takeoff Winged Multicopter - An unmanned aerial vehicle (UAV) comprising a plurality of propeller drives rigidly mounted to a foldable frame with the motor rotors aligned in a vertical direction to provide a means of vertical takeoffs and landings. The foldable frame mounts a sheet sail at an angle with the horizontal that provides lift during the forward motion and tilt of the UAV. In one embodiment the shape of the sheet sail and frame are triangular with one or two propeller drives being mounted in close proximity to each of the three vertices. In another embodiment, the shape of the sheet sail and frame are triangular with one or two propeller drives being mounted in close proximity to each of the three vertices, and one or two propeller drives being mount in close proximity to the trailing edge of the spine, in between the trailing edge propeller drives. In some embodiments, the frame spars may be comprised of carbon fiber rods and the sheet sail may be comprised of ripstop nylon fabric. | 11-19-2015 |
20160009387 | Hybrid Axial/Cross-Flow Fan Multi-Rotor Aerial Vehicle | 01-14-2016 |
20160023753 | VEHICLE WITH ASYMMETRIC NACELLE CONFIGURATION - A vehicle is provided and includes a wing having opposite surfaces and opposite sides and first and second engines disposed to drive wing movement and being respectively supported asymmetrically on the opposite surfaces and at the opposite sides of the wing. | 01-28-2016 |
20160031554 | CONTROL SYSTEM FOR AN AIRCRAFT - An aircraft control system includes a vertical thrust system, a horizontal thrust system, and an aerodynamic system. The system further includes a controller in at least indirect communication with the vertical thrust system, the horizontal thrust system, and the aerodynamic system. The controller is configured to substantially simultaneously control, based on at least one of a single yaw input, a single pitch input, and a single roll input, the aerodynamic system and a differential thrust generated by the plurality of vertical thrust rotors of the vertical thrust system to adjust at least one of pitch, yaw, and roll of a vertical takeoff and landing aircraft in at least one of a plurality of flight stages. The controller is further configured to independently and substantially simultaneously control the vertical and horizontal thrust systems to generate vertical and horizontal thrust in at least one of the plurality of flight stages. | 02-04-2016 |
20160039515 | Tail Spar Spring - According to one embodiment, an empennage attachment system features an aft attachment mechanism and a forward attachment system. The aft attachment mechanism is configured to be coupled to a tail section of a body of an aircraft and to an empennage proximate to an aft spar of the empennage. The aft attachment mechanism defines a pitch axis such that the aft attachment mechanism allows the empennage to rotate about the pitch axis. The forward attachment system is configured to be coupled to the tail section of the body and to the empennage proximate to a forward spar of the empennage. The forward attachment system is configured to restrict rotation of the empennage about the pitch axis to an allowable range of motion. | 02-11-2016 |
20160052626 | HYBRID GYRODYNE AIRCRAFT EMPLOYING A MANAGED AUTOROTATION FLIGHT CONTROL SYSTEM - An aircraft includes at least one propulsion engine, coupled to a fuselage, and configured to provide forward thrust to propel the aircraft along a first vector during forward flight. Each of at least two of multiple rotors coupled to the fuselage is coupled to a motor configured to supply power to that rotor and/or to draw power from that rotor. At least two of the rotors are configured to operate during forward flight to provide at least some lift to the aircraft along a second vector. A flight control system is configured to control the rotors that are configured to operate during forward flight in a power managed regime in which a net electrical power, consisting of the sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. | 02-25-2016 |
20160144957 | HIGH SPEED MULTI-ROTOR VERTICAL TAKEOFF AND LANDING AIRCRAFT - This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back. | 05-26-2016 |