| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | CONVERTIBLE AIRCRAFT PROVIDED WITH TWO DUCTED ROTORS AT THE WING TIPS AND WITH A HORIZONTAL FAN IN THE FUSELAGE | US14650231 | 2013-12-09 | US20150314865A1 | 2015-11-05 | Gérome BERMOND; Etienne VANDAME |
| The invention relates to a convertible aircraft comprising a fuselage (F), a pair of wings (A1, A2) arranged one on each side of the fuselage (F), at least one ducted rotor (1) installed in a horizontal position at one of the ends of the fuselage (F) and a first and a second nacelle (N1, N2) arranged respectively at the tip of each wing (A1, A2) and each comprising a ducted rotor (R1, R2) and being pivotably mounted relative to the fuselage (F). The nacelles comprise at least a first and a second movable flap (V1, V2), which flaps are arranged respectively at the outlet of the ducted rotor (R1) of the first nacelle (N1) and at the outlet of the ducted rotor (R2) of the second nacelle (N2). The aircraft according to the invention thus represents an advantageous solution to any applications involving helicopters and airplanes, particularly emergency preparedness missions, rescue missions, and public or private transport. | ||||||
| 142 | Coaxial counter-rotating rotor system | US13401110 | 2012-02-21 | US09169012B2 | 2015-10-27 | John Corrigan; Frank Bradley Stamps |
| A system and method to tilt coaxial counter-rotating rotor hub assemblies relative to a fuselage. The system includes a first rotor hub assembly and a second rotor hub assembly spaced apart from the first hub assembly and carried by the fuselage. The method includes pivotally attaching the first rotor hub assembly and the second rotor hub assembly to a pivot joint and thereafter tilting the first rotor hub assembly and the second rotor hub assembly about the pivot joint with a driver. | ||||||
| 143 | Folding of rotorcraft rotor blades | US13949698 | 2013-07-24 | US09156545B1 | 2015-10-13 | Carlos A. Fenny; Troy Schank; Frank B. Stamps |
| According to one embodiment, a rotor blade rotation system includes a hub, a rotor blade in mechanical communication with the hub and pivotable about an axis of rotation, a swashplate, a pitch link, and an actuator. The swashplate includes a rotating portion and a non-rotating portion. The pitch link is coupled to the rotating portion of the swashplate and in mechanical communication with the rotor blade. The actuator is coupled to the non-rotating portion of the swashplate and operable to reposition the swashplate from a first position to a second position such that the pitch links pivot the rotor blade from a deployed position to a folded position. | ||||||
| 144 | FOLDING OF ROTORCRAFT ROTOR BLADES | US13949698 | 2013-07-24 | US20150274290A1 | 2015-10-01 | Carlos A. Fenny; Troy Schank; Frank B. Stamps |
| According to one embodiment, a rotor blade rotation system includes a hub, a rotor blade in mechanical communication with the hub and pivotable about an axis of rotation, a swashplate, a pitch link, and an actuator. The swashplate includes a rotating portion and a non-rotating portion. The pitch link is coupled to the rotating portion of the swashplate and in mechanical communication with the rotor blade. The actuator is coupled to the non-rotating portion of the swashplate and operable to reposition the swashplate from a first position to a second position such that the pitch links pivot the rotor blade from a deployed position to a folded position. | ||||||
| 145 | Aircraft | US14350326 | 2012-10-03 | US20140284419A1 | 2014-09-25 | Felix Errol Groenewald; David Lucas Groenewald |
| An aircraft includes a fuselage or wing; a rotor mast; two rotors spaced axially along, and rotatably connected to the rotor mast; permanent and/or electro magnets on each of the rotors; and a rotor mast joint connecting the rotor mast to the fuselage or wing, wherein the rotor mast joint, in use, permits the rotor mast to tilt relative to the fuselage or wing in at least one plane. | ||||||
| 146 | SOFT IN-PLANE AND STIFF OUT-OF-PLANE ROTOR SYSTEM | US13804832 | 2013-03-14 | US20140271182A1 | 2014-09-18 | Ken Shundo; Mithat Yuce; Frank B. Stamps |
| A rotor assembly includes a yoke operably associated with a rotor blade. The yoke includes a first device and a second device that attach the rotor blade to the yoke. The first device is configured to allow transverse movement of the rotor blade about a chord axis and rotational movement about a pitch-change axis. The second device is configured to allow rotational movement of the rotor blade solely about the pitch-change axis. The method includes rotating rotor assembly about a first plane of rotation, while retaining a relatively stiff out-of-plane rotation and a relatively soft in-plane rotation during flight. | ||||||
| 147 | Modular Flying Vehicle | US13907975 | 2013-06-03 | US20140151496A1 | 2014-06-05 | Donald Orval Shaw |
| The invention is a modular vehicle having an air vehicle that can be coupled to cargo containers, land vehicles, sea vehicles, medical transport modules, etc. In one embodiment the air vehicle has a plurality of propellers positioned around a main airframe, which can provide vertical thrust and/or horizontal thrust. One or more of the propellers may be configured to tilt forward, backward, and/or side-to-side with respect to the airframe. | ||||||
| 148 | Apparatus to eliminate back drive in push pull system of rotor aircraft and related methods | US13532213 | 2012-06-25 | US08739679B2 | 2014-06-03 | Jay W. Carter, Jr.; M. Keith Robinson; Jeffrey R. Lewis |
| Apparatus and methods for eliminating back drive in a push pull type control system, are provided. An exemplary apparatus includes a control rod including a pair of spaced apart piston displacement members each configured to carry a check valve. The apparatus also includes a pair of opposite-face check valves each configured to seal against respective opposing face of a piston head to form a hydraulic lock, preventing back drive in the control system. | ||||||
| 149 | Aircraft with freewheeling engine | US13442544 | 2012-04-09 | US08720814B2 | 2014-05-13 | Frick A. Smith |
| An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft. | ||||||
| 150 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT | US14142403 | 2013-12-27 | US20140110533A1 | 2014-04-24 | Masayoshi TSUNEKAWA; Tetsuya TAMURA |
| 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. | ||||||
| 151 | Coaxial Counter-Rotating Rotor System | US13401110 | 2012-02-21 | US20130214087A1 | 2013-08-22 | John Corrigan; Frank B. Stamps |
| A system and method to tilt coaxial counter-rotating rotor hub assemblies relative to a fuselage. The system includes a first rotor hub assembly and a second rotor hub assembly spaced apart from the first hub assembly and carried by the fuselage. The method includes pivotally attaching the first rotor hub assembly and the second rotor hub assembly to a pivot joint and thereafter tilting the first rotor hub assembly and the second rotor hub assembly about the pivot joint with a driver. | ||||||
| 152 | SYSTEM, APPARATUS AND METHOD FOR LONG ENDURANCE VERTICAL TAKEOFF AND LANDING VEHICLE | US13397569 | 2012-02-15 | US20130206921A1 | 2013-08-15 | James Donald Paduano; Paul Nils Dahlstrand; John Brooke Wissler |
| 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. | ||||||
| 153 | Constant-Velocity Drive System for Gimbaled Rotor Hubs | US13677146 | 2012-11-14 | US20130156580A1 | 2013-06-20 | Richard Rauber; Frank B. Stamps; James Lee Braswell, JR. |
| 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. | ||||||
| 154 | LIFE-SAVING VEHICLE | US13702995 | 2011-06-07 | US20130153706A1 | 2013-06-20 | Jan-Evert Lindmark; Juhani Niinivaara |
| The invention concerns a life-saving vehicle (10) designed as a hollow body with the form of a sphere or disk essentially flattened along a vertical axis (16) that demonstrates its greatest width in a horizontal plane (15) and which body, composed of an upper part (11) and a lower part (13), limits an internal passenger compartment (25), whereby the body comprises a stabilizing arrangement (12) that stabilizes the vehicle when it is in water, a telescopic arrangement (40), a stabilization means (14) arranged at the lower part, which stabilization means can be displaced in a vertical direction downwards from the lower part through activation of the telescopic arrangement (40). The vehicle, in order for it to travel not only in the air but also in water, comprises: a first and second rotor (52, 17), a motor (55) with an associated transmission (54), a pair of propulsion units (60) and a stabilizing fin (65). | ||||||
| 155 | Counter-rotational inertial control of rotorcraft | US12761842 | 2010-04-16 | US08464978B2 | 2013-06-18 | Mark Yim; Christopher Everett Thorne |
| A rotorcraft with two counter-rotating rotors and method for inertially controlling the rotorcraft. The rotorcraft includes a hinged frame configured such that at least one inter-rotor angle of the two counter-rotating rotors is controlled by at least one actuated hinge of the hinged frame and the rotational axes of the two counter-rotating rotors are substantially collinear when the actuated hinge is in a fully open position. The sum of the magnitudes of torque applied to the two counter-rotating rotors is varied to control the lift of the rotorcraft. The difference of the magnitudes of torque applied to the two counter-rotating rotors is varied to control the yaw of the rotorcraft. The at least one inter-rotor angle is varied using the at least one actuated hinge to control the pitch and/or roll of the rotorcraft. | ||||||
| 156 | Power Safety Instrument System | US13641325 | 2010-12-22 | US20130120165A1 | 2013-05-16 | James M. McCollough; Erik Oltheten; Nicholas Lappos |
| A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available. | ||||||
| 157 | Tilt rotor aircraft with tilting tail rotor—TT | US13064855 | 2011-04-21 | US08196854B2 | 2012-06-12 | Tom Kusic |
| A vertical take-off aircraft comprising a main power plant 1 at the top of the aircraft which consists of an assembly of blades 2, 3, a rotor 4 and a main engine assembly 5. The main power plant is connected to the main body 6 of the aircraft by a tilt enabling joint 7. The tilt enabling joint is connected to the main body by a telescopic tube assembly comprising tubes 12 and 13. To counter the rotational force exerted on the main body 6 of the aircraft by the rotation of the blades 2, 3, an additional power plant 15 is attached to the main power plant. Tilting the main power plant causes tilting of the additional power plant. | ||||||
| 158 | Method for Compensation of Gyroscopic Forces of a Rotor in a Helicopter | US13318484 | 2010-05-05 | US20120056031A1 | 2012-03-08 | Gert Lading |
| In order to suppress induction of precession when the rotor (24, 26) of a helicopter is tilted relative to a fuselage (31), the tilt trajectory is supplemented by transverse components. The helicopter is of the type with a bendable, actuated joint (34) between the rotor and a fuselage. A controller (2) receives an input signal (4) from a steering device (1) and transforms this input signal in an output signal (7) for an actuating system (3) for movement in the joint. The controller calculates on the basis of the input signal an estimation for further input signals, and adds a transverse component to the input trajectory before sending the output trajectory (11). | ||||||
| 159 | Tandem powered tilt rotor aircraft | US12659594 | 2010-03-15 | US07992820B2 | 2011-08-09 | Tom Kusic |
| An aircraft with a long body 1 which has a forward end 2 and an aft end 3, which is able to achieve vertical take-off by means of a tilt-able rotor and blade assembly 4 at the forward part of the aircraft and a tilt-able turbojet 19 at the rear of the aircraft. The rotor and blade assembly is rotated by an engine assembly 8, with the engine assembly, the rotor and blades all positioned on top a multi-directional tilt enabling joint 9. The turbojet is fitted to a multi-directional tilt enabling joint 27 to allow control of lateral movement of the aircraft as well as providing vertical lift and forward propulsion during forward flight. The turbojet is connected to the tilt enabling joint 27 by a rivet 30 such that the turbojet can be rotated relative to the tilt enabling joint. | ||||||
| 160 | Tandem powered power tilting aircraft | US11584620 | 2006-10-23 | US07753310B2 | 2010-07-13 | Tom Kusic |
| An aircraft with a long body 1 which has a forward end 2 and an aft end 3, which is able to achieve vertical take-off by means of a tilt-able rotor and blade assembly 4 at the forward part of the aircraft and a tilt-able turbojet 19 at the rear of the aircraft. The rotor and blade assembly is rotated by an engine assembly 8, with the engine assembly, the rotor and blades all positioned on top a multi-directional tilt enabling joint 9. The turbojet is fitted to a multi-directional tilt enabling joint 27 to allow control of lateral movement of the aircraft as well as providing vertical lift and forward propulsion during forward flight. The turbojet is connected to the tilt enabling joint 27 by a rivet 30 such that the turbojet can be rotated relative to the tilt enabling joint. | ||||||
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