子分类：
- B64C27/001： .{减振装置}
- B64C27/006： .{保护装置}
- B64C27/008： .{旋翼跟踪或平衡装置}
- B64C27/02： .旋翼飞机
- B64C27/04： .直升飞机
- B64C27/20： .以具有带罩旋翼,例如飞行平台为特点的旋翼机
- B64C27/22： .混合式旋翼机,即飞行中利用飞机和旋翼机两者特征的飞行器
- B64C27/32： .旋翼(旋翼和螺旋桨共有的特征入B64C11/00)
- B64C27/51： .{叶片运动的减震}
- B64C27/52： .整个旋翼相对机身的倾斜(翘翘板型结构入B64C27/43)
- B64C27/54： .用于控制叶片相对于旋翼毂的调节或运动,例如滞后提前运动的机构
- B64C27/82： .以装有用于平衡升力旋翼扭矩或改变旋翼机方向的辅助旋翼或流体喷射装置为特点的
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 201 | Rotary wing device | US883653 | 1978-03-06 | US4390148A | 1983-06-28 | Patrick J. Cudmore |
| A rotary wing device adapted to be rotated about its longitudinal axis and to be propelled forwardly with its longitudinal axis having a small upward pitch angle relative to the forward flight direction in order to generate an upward lifting force on the device. The rotary wing device has a plurality of laterally spaced-apart cylindrically disposed wing segments. Preferably, the wing segments are parallel to each other, are parallel to the longitudinal axis of the device, and have streamlined edges. Preferably, the wing segments are mounted for rotation about the longitudinal axis of the device by front and rear mounting rings which engage and stabilize the front and rear tips of the wing segments. The mounting rings are perpendicular to the wing segments and have streamlined edges. The preferred embodiment is a throwable aerial toy having its center of mass located on the forward half of its longitudinal axis and being statically and dynamically balanced relative to said longitudinal axis. The throwable aerial toy flies a considerable distance with a surprisingly flat straight line trajectory. | ||||||
| 202 | Mode controlled attachment of rotor mounted components | US028341 | 1979-04-09 | US4275992A | 1981-06-30 | James R. Andrews; Rodney W. Balke; Victor L. Berry |
| An above-rotor mount (30) for a helicopter (10) comprises an upper plate (32) coupled to a lower plate (34) by means of links (42, 44, 46 and 48). The lower plate (34) is connected to a rotating rotor shaft (16) and a non-rotating stand pipe (40) extending inside the rotor shaft. The links (42, 44, 46 and 48) are focused to control the mode shapes and dynamic response of the mounted components at a preselected frequency, such as the predominant rotor harmonic. Springs (50, 52) are connected between the plates (32, 34) for damping. | ||||||
| 203 | Aircraft with counterrotating members | US956005 | 1978-10-30 | US4273302A | 1981-06-16 | Heinz Jordan |
| A rotationally symmetrical supporting member provides lift in response to movement of air over its upper surface, and such air movement is produced by the impeller of a coaxially arranged drive unit, the base of which is connected to the supporting member so that counter torque from the drive unit imparts rotational movement to the supporting member. A carrier which may hold a load or supporting steering flaps is rotatably mounted in relation to the supporting means and to the driving unit. | ||||||
| 204 | Method and apparatus for aerial wire stringing through areas without vertical access | US615480 | 1975-09-22 | US4006884A | 1977-02-08 | Donald A. Lederhos; L. E. Lindsey |
| A releasable connector is provided in an aerially placed pulling cable which is deposited in a catching device wherein the connector is disconnected and reconnected to connectors carried by the ends of a preplaced loop cable passing through the area to be strung, all responsively to forces of cable stringing. The particularly configured catcher provides a guiding through to support the pulling cable and its connector and upon appropriate positioning of the cable therein to release the connector so that the rearward portion of the pulling cable moves rearwardly by reason of its gravity bias to connect with one end of the preplaced loop cable and the forward end of the pulling cable moves forwardly to connect with the forward end of the loop cable to reform a continuous compound pulling cable with the loop cable incorporated therein. The loop cable is preplaced in a stringing block supported in the area through which it is desired that the pulling cable pass, with the loop cable ends passing from the serving block in a single loop to the catcher. | ||||||
| 205 | Rotating aircraft and aircraft control system | US46738074 | 1974-05-06 | US3915414A | 1975-10-28 | SHOULDERS KENNETH R |
| An aircraft is described which in configuration is simply a pod from which a single wing extends. The aircraft flies by rotation within an air mass to produce lift with the wing. The rotation is obtained by jet flow from the trailing edge of the wing adjacent its tip, which jet flow is provided by a separately rotating impeller within the pod. The impeller also acts by centrifugal force to normally set a pitch plane for the wing of the craft. A detector which interacts with the magnetic field of the earth generates a signal which is indicative of the angular orientation of the aircraft at any time, and a synchronous sensing and remote control system is provided which takes into account such orientation in operating a control flap positioned in the jet stream as desired to change the plane of rotation and, hence, the direction of translational motion, of the rotating aircraft.
|
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| 206 | Flexible sail rotor devices | US3633850D | 1969-01-06 | US3633850A | 1972-01-11 | FELDMAN LEWIS |
| A launched, self-sustaining station-keeping vehicle is maintained in flight by flexible rotor blades deployed and tensioned by the centrifugal forces acting on a mass (which takes the form of a rocket or the like) located at the tip of each rotor, the rockets sustaining rotation of the rotor blades. The blades are wrapped around a normally rotatable spool portion of the vehicle during launch. A spin is imparted to the vehicle during flight which aids in deploying the blades when the tip rockets are released. A vehicle-mounted control system controls stabilization and station keeping through control of the blade angle setting of the rotor blades. Improvements of general application include improving the aerodynamic shape of such blades by securing appropriately shaped fairings thereto.
|
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| 207 | Modernized helicopter | US3542317D | 1968-04-25 | US3542317A | 1970-11-24 | IRBY JAMES EDWARD |
| 208 | Accumulator | US63156256 | 1956-12-31 | US2941549A | 1960-06-21 | MARD KENNETH C |
| 209 | Helicopter | US37803241 | 1941-02-08 | US2348249A | 1944-05-09 | CASIMIRO FERRO |
| 210 | Airplane | US31333240 | 1940-01-11 | US2300268A | 1942-10-27 | JOSEPH STUART |
| 211 | Autorotative-winged aircraft | US1430435 | 1935-04-02 | US2174946A | 1939-10-03 | RAY JAMES G; PITCAIRN HAROLD F; LARSEN AGNEW E |
| 212 | Airship | US31716428 | 1928-11-05 | US1744257A | 1930-01-21 | BESS GUSTAVUS A |
| 213 | Flying-machine | US25944318 | 1918-10-23 | US1327514A | 1920-01-06 | ALLMAN WILLIAM H |
| 214 | BUBBLE COLLECTOR FOR SUCTION FUEL SYSTEM | PCT/US2014059258 | 2014-10-06 | WO2015099860A2 | 2015-07-02 | SMITH DAVID R; SHIELDS DANIEL JOHN |
| A fuel feed system for a rotary-winged aircraft includes a fuel feed line extending from a fuel source to an engine and an engine fuel suction pump disposed at the fuel feed line to urge a flow of fuel through the fuel feed line to the engine. A collector is located along the fuel feed line between the fuel source and the engine to collect air-vapor bubbles which form in the flow of fuel. An air-vapor line extends from the top of the collector and merges with the fuel line section between the collector and the engine fuel pump. The air-vapor line is sized and configured to limit the flow of air-vapor from the collector to the engine fuel suction pump to a rate which the engine fuel suction pump can tolerate. | ||||||
| 215 | ROCKET OR BALLISTIC LAUNCH ROTARY WING VEHICLE | PCT/EP2012059637 | 2012-05-23 | WO2012160111A3 | 2013-03-28 | GREEN JOHN; GEOGHEGAN PHILIP; SNOOK MICHAEL ALEXANDER |
| Embodiments of the present invention relate to a rocket or ballistic launch rotary wing air vehicle. | ||||||
| 216 | CONTROL SYSTEMS FOR USE WITH FLYING CRAFT AND OTHER REMOTE ELEMENTS | PCT/GB0304742 | 2003-11-04 | WO2004041381A3 | 2004-09-16 | JERMYN PHIL |
| A method and apparatus for controlling a powered craft in flight by an unsupported hand held control element. The position and attitude of the craft are controlled by the position and attitude of the control element. The position and attitude of the craft is determined with respect to a straight line between the controller and the craft, for example a beam of radiation. The controller and the craft are both provided with transducers comprising emitter and/or detector arrays in communication with one another. | ||||||
| 217 | SYSTEM AND METHOD FOR DISPLAYING VERTICAL REFERENCE ON A ROTORCRAFT SYSTEM | EP15150993.2 | 2015-01-13 | EP2921825B1 | 2018-10-10 | Case, Timothy John; Meeker, John |
| A method and system for maintaining visual vertical reference on a rotorcraft display during rotorcraft landing is provided. The method generates vertical poles and positions them on the rotorcraft display such that vertical reference as well as roll information may be quickly and easily comprehended by a pilot. | ||||||
| 218 | ROTORCRAFT FUEL SYSTEM HAVING ENHANCED CRASH RESISTANCE | EP16172307.7 | 2016-05-31 | EP3241756B1 | 2018-08-01 | PERYEA, Martin; SMITH, Michael Reaugh; HAMELWRIGHT Jr., Douglas; BRAND, Albert G.; PLAGIANOS, Nicholas J.; EMRICH, Joshua; CARR, Timothy |
| A rotorcraft (10) includes a fuselage (16) having a fuel tank receiving assembly (24) with a fuel tank (28) positioned therein. The fuel tank (28) including a plurality of interconnected fuel bags operable to contain liquid fuel. A network of straps is disposed about the fuel tank (28) forming a restraint assembly (130; 172; 182; 202). The network of straps includes at least one perimeter strap (132, 134, 136, 138, 140) extending at least partially about at least two fuel bags and at least one surrounding strap (142, 144, 146) extending at least partially about the at least two fuel bags. The at least one perimeter strap (132, 134, 136, 138, 140) has at least two intersections (156, 158) with the at least one surrounding strap (142, 144, 146). | ||||||
| 219 | PROCEDE DE PILOTAGE ASSISTE D'UN AERONEF A VOILURE TOURNANTE COMPRENANT AU MOINS UNE HELICE PROPULSIVE, DISPOSITIF DE PILOTAGE ASSISTE ET AERONEF | EP17175700.8 | 2012-10-26 | EP3242181B1 | 2018-06-27 | SALESSE-LAVERGNE, Marc; QUEIRAS, Nicolas; EGLIN, Paul |
| 220 | STOCKAGE D'ENERGIE A PILES THERMIQUES POUR AERONEF A VOILURE TOURNANTE | EP16178931.8 | 2016-07-12 | EP3125343B1 | 2018-05-02 | CONNAULTE, Matthieu |
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