| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | High-lift, low-drag dual fuselage aircraft | US11046034 | 2005-01-27 | US20060016931A1 | 2006-01-26 | Frank Malvestuto; John Hanscomb |
| Disclosed is an aircraft including forward and aft wings, interposed between a port fuselage and a starboard fuselage, the port fuselage being substantially parallel to and coplanar with the starboard fuselage; a T-tail stabilizer system mounted aft and topside of the fuselages having a spanning horizontal stabilizer in some embodiments; propulsion systems mounted to each of the fuselages; and, in some embodiments, deflectable canards, tillable wings and wing-mounted propulsion systems. | ||||||
| 182 | Counter-quad tilt-wing aircraft design | US11093309 | 2004-06-04 | US20050230519A1 | 2005-10-20 | Francis Hurley |
| The invention consists of a specific, matched arrangement of aeronautical elements which (1) eliminates aerodynamic interference of, and (2) adds variable-cycle propulsion to, the level flight mode of a four-propulsor tilt-wing VTOL (vertical takeoff & landing) aircraft, without an additional element of variable geometry. This is achieved by configuring the components such that the rotor planes on either side pass through each other in the transition maneuver to form adjacent, close-coupled, counter-rotating pairs in level flight. | ||||||
| 183 | Spacecraft and aerospace plane having scissors wings | US10277687 | 2002-10-22 | US06745979B1 | 2004-06-08 | Zhuo Chen |
| A spacecraft such as a fly back booster or a reusable launch vehicle, or an aerospace plane has a fuselage and a set of scissors wings consisting of two main wings. Both of the main wings are rotatably mounted on the fuselage and can be yawed at opposite directions. If the spacecraft is launched vertically, both of its main wings can be yawed to be generally parallel with its fuselage so that it can connect with other vehicle or vehicles to form different launch configurations. When the spacecraft or aerospace plane is flying in the air, landing, or taking off horizontally, it can yaw both of its main wings in opposite directions to maximize its lift-to-drag ratio by optimizing the yaw angle of the main wings according to flying conditions. It can also produce desired aerodynamic characteristics such as forming a high drag configuration by adjusting the yaw angle of its main wings. The scissors wings can be used on a spacecraft that is launched vertically on the ground, or a spacecraft that is carried to the air and launched in the mid-air, or a spacecraft that takes off horizontally like an aircraft or glider. The scissors wings can also be used on an aerospace plane. | ||||||
| 184 | Lifting arrangement for lateral aircraft surfaces | US09907993 | 2001-07-18 | US06669142B2 | 2003-12-30 | Manuel Munoz Saiz |
| Lifting arrangement for lateral aircraft surfaces that consists of numerous lateral flutings, grooves, splines, flutes or riblets parallel to each other, arranged on the lateral surfaces of fuselages, fin units, pylons and gondolas of aircraft with a downward slope from the nose to the tail, with the flow of air passing through such flutings, grooves, etc., towards the rear and downwards, generating lifting by reaction, using small planes or fins to support the engines and flight control fins. | ||||||
| 185 | Air vehicle having rotor/scissors wing | US10227955 | 2002-08-26 | US06669137B1 | 2003-12-30 | Zhuo Chen |
| An air vehicle, such as a manned or unmanned air vehicle, has a fuselage, a rotor/scissors wing, and a scissors wing. At helicopter mode, the rotor/scissors wing rotates to make the air vehicle fly like a helicopter to achieve vertical and/or short take-off and landing, hovering, and low speed flying. At airplane mode, the rotor/scissors wing and scissors wing form a scissors wings configuration to maximize the air vehicle's flying efficiency at a wide range of speed and flying conditions by adjusting the yaw angle of the rotor/scissors wing and scissors wing. During the conversion from helicopter mode to airplane mode, the scissors wing generates lift to offload the rotating rotor/scissors wing and eventually the offloaded rotor/scissors wing's rotating speed is slowed and stopped so that the rotor/scissors wing can be locked at a specific position and the conversion can be achieved. In a reverse order, the air vehicle can convert from airplane mode to helicopter mode. Either turbofan or turbojet engine, or turboshaft/turbofan convertible engine can be used to power the air vehicle. | ||||||
| 186 | Air vehicle having scissors wings | US10227130 | 2002-08-23 | US06601795B1 | 2003-08-05 | Zhuo Chen |
| An air vehicle, such as an aircraft, an unmanned air vehicle, a missile, or an aero bomb that has a fuselage and two main wings each of which has a left side wing and a right side wing. Both of the main wings are rotatably mounted on the fuselage via one or two pivots or hollow turrets so that both of them can be yawed during flight to optimize flying efficiency under various flying conditions. | ||||||
| 187 | Aircraft and torque transmission | US09605411 | 2000-06-28 | US06467726B1 | 2002-10-22 | Rokuro Hosoda |
| An aircraft including an airframe having a fuselage which extends longitudinally, and having fixed wings including a main wing, a horizontal tail wing and a vertical tail wing. A propeller-rotor torque transmission has a bevel gear which transmits the rotation of an input shaft simultaneously to a propeller shaft and to a rotor shaft. An engine gearbox supplies the above-mentioned input shaft with rotationalal motive power. The aircraft further includes a propeller collective pitch controller, a rotor collective pitch controller, an engine power controller which controls the output of the above-mentioned engine gearbox for the purpose of changing the rotational speed of the input shaft, and a flight control system having a directional (yaw) control system which controls the flight direction of the aircraft by controlling the positions of the above-mentioned control surfaces. | ||||||
| 188 | Lifting arrangement for lateral aircraft surfaces | US09907993 | 2001-07-18 | US20020023985A1 | 2002-02-28 | Manuel Munoz Saiz |
| Lifting arrangement for lateral aircraft surfaces that consists of numerous lateral flutings, grooves, splines, flutes or riblets parallel to each other, arranged on the lateral surfaces of fuselages, fin units, pylons and gondolas of aircraft with a downward slope from the nose to the tail, with the flow of air passing through such flutings, grooves, etc., towards the rear and downwards, generating lifting by reaction, using small planes o fins to support the engines and flight control fins. | ||||||
| 189 | Aircraft structure to improve directional stability | US42278 | 1998-03-13 | US6098923A | 2000-08-08 | Spence E. Peters, Jr. |
| An aircraft structure has an arrangement of aircraft components that provide inherent directional stability for a flight vehicle throughout an angle-of-attack range, even at very high angles-of-attack where conventional means of stabilization are ineffective. Components attached to an aircraft fuselage include a wing, horizontal stabilizers and vertical stabilizers. The wing is mounted forward of the horizontal stabilizers and is carried high on the fuselage. The horizontal stabilizer is mounted toward the rear of the aircraft and is attached near the bottom of the fuselage. The wing and horizontal stabilizers are joined on either side of the aircraft by forwardly sweeping aerodynamically shaped surfaces serving as the vertical stabilizers. The inclination of the vertical stabilizers preferably ranges from 45 degrees (top edge canted outboard) to 90 degrees (panels vertical). Preferably, the surface area of the vertical stabilizers is concentrated aft such that the aerodynamic center of the vertical stabilizers is located behind the center-of-gravity of the aircraft. | ||||||
| 190 | Aircraft for passenger and/or cargo transport | US18959 | 1998-02-05 | US06070831A | 2000-06-06 | Anatoli J. Vassiliev; Karl-Heinz Eibel |
| Aircraft for carrying passengers and/or freight based on a known aircraft design with a fuselage having a nose section, center section, and tail section and with airfoils mounted on the center section near the center of gravity of the aircraft and calculated for the required lift and with vertical and/or horizontal stabilizers located in the vicinity of the tail section for creating stabilizing and steering moments, with the fuselage of said aircraft being stretched by means of an additional section inserted between the nose section and the center of gravity of the aircraft model in order to increase the carrying capacity of the aircraft based on predetermined known aircraft designs, and with the additional section, as viewed in the direction of flight, being equipped forward of the airfoils of the aircraft model that serve as the main airfoils with airfoils that serve as additional airfoils, with previously designed and calculated airfoils of suitable size from a known aircraft design being used as the additional airfoils. | ||||||
| 191 | Unmanned boom/canard propeller v/stol aircraft | US711058 | 1991-06-06 | US5145129A | 1992-09-08 | David F. Gebhard |
| An unmanned aircraft is provided which dual turbo shaft engines diving contra-rotating propellers. A bow plane provides pitch control during normal aircraft cruising. The contra-rotating propellers generate a slipstream for wing and tail sections that permit the aircraft to execute hover without the use of complicated tiltable rotor or jet assemblies. | ||||||
| 192 | Vertical/short takeoff or landing aircraft having a rotatable wing and tandem supporting surfaces | US446188 | 1989-11-24 | US5098034A | 1992-03-24 | William C. Lendriet |
| An improved vertical/short takeoff or landing aircraft (10). The aircraft has a canard wing (14), attached to the forward section of the aircraft body, that has an engine (26) on each side. Each engine drives a pusher propeller (42). Located aft of the canard wing (14) is a primary wing (16) that includes a number of control surfaces and that is rotatably attached to the fuselage (12). The primary wing (16) is rotated downwardly about its chordwise axis when the aircraft takes off or lands vertically. When short takeoffs and landings are required the wing is partially rotated and during conventional flight, the wing is rotated to a position that is approximately parallel to the longitudinal axis of the aircraft (12). The aircraft also has a tail control group that consists of a horizontal stabilizer (22) and elevator (34) to where on each side is attached a vertical stabilizer (22) and rudder (36). | ||||||
| 193 | High lift aircraft | US453658 | 1989-11-29 | US5071088A | 1991-12-10 | Edward E. Betts |
| A high lift vertical takeoff and landing aircraft has first and second fuselages connected by a central airfoil. Jet engines at the leading edge of the airfoil expel propulsive streams simultaneously over top and bottom surfaces of the foil. Extendable flaps are utilized at a trailing edge of the airfoil with a horizontal control blade being attached to the leading edge of the foil. The control blade is within the jet's propulsive stream to permit proportioning of the stream above and below the airfoil.An extendable augmenter wing is attached between the fuselages aft and above the main airfoil to permit airflow in this region to be directed downwardly, accelerating the flow and providing additional lift.The main airfoil is positioned so that the fuselage walls extend above and below the foil. Lateral flow of the main engine exhaust is restrained by these walls. Above the wing the walls and airfoil create a venturi to speed airflow and decrease pressure. Below the wing the walls and extended flaps dam exhaust and ambient flow to create a high pressure region. Outboard wings provide seconary lift and reduce main wing loading.A canard is attached between the fuselages to provide pitch control. Both top and bottom canard surfaces are blown by forward mounted engines or exhaust ducts to add lift to the aircraft and to permit upward tilting of the aircraft during takeoff and landing. Tilting the aircraft permits the resultant of the engine thrust and wing lift vectors to be vertical. | ||||||
| 194 | Compound wing aircraft | US081198 | 1979-10-02 | US4336913A | 1982-06-29 | Eric B. Hall |
| An aircraft, either rigid-wing or a collapsible hang-glider, is provided which is a bi-plane of apparent annular-wing construction in plan view, but the wing tips of an anhedral foreplane are separated from and above the wing tips of a dihedral aftplane. In a hang-glider construction the wing tips of the foreplane may be supported above the wing tips of the aftplane by struts, the trailing edges of the foreplane wing tips being supported by the struts above the leading edges of the aftplane wings. Also in the hang-glider, the geometry of the fore and aftplanes can be varied by moving their points of connection to the keel therealong. | ||||||
| 195 | Aircraft | US55198166 | 1966-05-23 | US3385538A | 1968-05-28 | HODGES ALGERNON F |
| 196 | Aircraft | US41620364 | 1964-12-07 | US3284028A | 1966-11-08 | ROBERTSON ROBERT L |
| 197 | Aircraft with high lift airfoil construction | US6223260 | 1960-10-12 | US3108768A | 1963-10-29 | COELHO THOMAS WILLIAM |
| 198 | Boundary layer control apparatus relating to aircraft | US52482655 | 1955-07-27 | US2910254A | 1959-10-27 | KENNETH RAZAK CHARLES |
| 199 | Aeroplane. | US22008918 | 1918-03-02 | US1295398A | 1919-02-25 | MILMORE BEN ERNEST |
| 200 | Flying-machine. | US20716617 | 1917-12-14 | US1289967A | 1918-12-31 | TORRES FRANK |
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