| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | Lift and control augmenter for airfoils | US3583660D | 1969-08-18 | US3583660A | 1971-06-08 | HURKAMP CHARLES H; JACOBS WILLI F |
| Means is herein provided for augmenting the lift and controllability of an aircraft by blowing compressed air through spanwise slots in a multiple trailing edge flap system on the aircraft''s airfoils. The mechanism consists of a main flap, with rotary and translation motion relative to the associated airfoil; a lower surface flap which is hinged to both the airfoil and the main flap; and an airflow directional control device rotatably mounted to the aft end of the main flap. Downward deflection of the flap mechanism creates a spanwise duct between the main and lower surface flaps, through which compressed air, extracted from a suitable source, is allowed to flow. The air is ejected at high velocity from multiple spanwise slots provided in the flap mechanism. The resultant jet sheets impart a downward momentum to the air passing over the associated airfoil increasing the circulating flow around its chordwise sections and imparting an upward reaction. The airflow directional control device may be utilized both to vary lift symmetrically on the aircraft and to provide roll control by differential action.
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| 42 | Method and apparatus for modifying airfoil fluid flow | US3480234D | 1967-08-18 | US3480234A | 1969-11-25 | CORNISH JOSEPH J |
| 43 | Transpiration cooled window | US3452553D | 1967-03-17 | US3452553A | 1969-07-01 | DERSHIN HARVEY; LEONARD CHARLES A |
| 44 | Foils for movement in a fluid | US34983464 | 1964-03-06 | US3275266A | 1966-09-27 | SYDNEY COCKERELL CHRISTOPHER |
| 965,748. Aircraft. HOVERCRAFT DEVELOPMENT Ltd. Oct. 5, 1960 [Oct. 20, 1959], No. 35593/59. Headings B7G and B7W. An aerofoil member has at least one surface provided with at least one supply port extending adjacent to and substantially parallel to the periphery of said surface, including means for supplying a gas to the supply port to issue therefrom and form a curtain of moving gas which, in operation, with the surface of the aerofoil bounds a space in contact with the surface whereby a cushion of pressurised gas is formed in said space on movement of the aerofoil member through the air. An aircraft 1 has wings 2 each provided with a peripherally extending supply port 3. Gas turbine engines 4 discharge air into ducts 5 which communicate with supply ports 3 to form curtains 11, which as a result of forward motion of the wing, are swept aft, as shown in Fig. 3, to form wedgeshape cushions of pressure gas which form an effective part of the aerofoil profile to influence lift. To increase stability of the aircraft, a further curtain 12 is supplied from a duct 14. In the embodiment of Fig. 6 a vertical stabilizer 25, e.g. a rudder, is formed on each surface with a peripheral supply port 29 each connected to a supply duct 30 through respective intermediate ducts 31, 32, provided with flap valves 33, 34. In operation, when rudder action is required, one or other of the flaps 33, 34 is opened by linkage 35 or 36 to cause gas to issue from the peripheral slots to form an appropriate wedge-shape cushion of pressure gas on the appropriate side of the stabilizer, to produce a rudder effect. An installation for a deltawing aircraft is described. Specification 894,644 is referred to. | ||||||
| 45 | Aircraft panel construction for boundary air control | US33017563 | 1963-12-12 | US3194518A | 1965-07-13 | WALSH ROBERT L |
| 46 | Devices for producing and controlling airflow around airfoils | US69610757 | 1957-11-13 | US3026067A | 1962-03-20 | GRANT CHARLES H |
| 47 | Airfoil structure with boundary layer control means | US64625257 | 1957-03-15 | US2959377A | 1960-11-08 | KAPLAN LEO I |
| 48 | Boundary layer control means for obtaining high lift for aircraft | US72986458 | 1958-04-21 | US2951662A | 1960-09-06 | THEODORE THEODORSEN |
| 49 | Jet propelled aircraft with wingmounted jet engines | US42153954 | 1954-04-07 | US2756008A | 1956-07-24 | MACAULAY DAVIDSON IVOR |
| 50 | Propelling device | US5847136 | 1936-01-10 | US2108652A | 1938-02-15 | HENRI COANDA |
| 51 | Aircraft | US1040935 | 1935-03-11 | US2041794A | 1936-05-26 | STALKER EDWARD A |
| 52 | ACTIVE FLOW CONTROL ON A VERTICAL STABILIZER AND RUDDER | EP16199645.9 | 2011-10-03 | EP3150485B1 | 2018-12-12 | WHALEN, Edward A.; GOLDHAMMER, Mark I |
| Systems and methods described herein provide for the control of airflow over a vertical control surface of an aircraft to enhance the forces produced by the surface. According to one aspect of the disclosure provided herein, the vertical control surface of the aircraft is engaged by active flow control actuators that interact with the ambient airflow to alter one or more characteristics of the airflow. An actuator control system detects a flow control event, and in response, activates the active flow control actuators to alter the airflow. According to various aspects, the flow control event is associated with a separation of the airflow, which is corrected through the activation of the appropriate active flow control actuators, increasing the forces produced by the vertical control surface of the aircraft. | ||||||
| 53 | ACTIVE FLOW CONTROL ON A VERTICAL STABILIZER AND RUDDER | EP16199645.9 | 2011-10-03 | EP3150485A1 | 2017-04-05 | WHALEN, Edward A.; GOLDHAMMER, Mark I |
Systems and methods described herein provide for the control of airflow over a vertical control surface of an aircraft to enhance the forces produced by the surface. According to one aspect of the disclosure provided herein, the vertical control surface of the aircraft is engaged by active flow control actuators that interact with the ambient airflow to alter one or more characteristics of the airflow. An actuator control system detects a flow control event, and in response, activates the active flow control actuators to alter the airflow. According to various aspects, the flow control event is associated with a separation of the airflow, which is corrected through the activation of the appropriate active flow control actuators, increasing the forces produced by the vertical control surface of the aircraft.
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| 54 | Tile assembly for boundary layer modification | EP13275337.7 | 2013-12-24 | EP2889217A1 | 2015-07-01 | The designation of the inventor has not yet been filed |
A tile assembly which, in use, is fitted to a base structure to form at least part of a fluid washed surface. The tile assembly comprises a housing with at least one plenum being provided within the housing. A wall of the housing is provided with a plurality of flow passages which extend from the plenum side of the wall to an outer surface of the wall. Flow passage closures are provided which are operable to open and close at least some of the flow passages.
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| 55 | AEROFOIL WITH GAS DISCHARGE | EP02769636.8 | 2002-05-09 | EP1392562B1 | 2011-07-20 | Grove, Graham Bond |
| Upper surface (13) of an aerofoil (or rotor blade) is provided with nozzles or slots (14, 16) at leading portion (15) and trailing portion (17) to assist attachment of airflow by discharging gas towards trailing edge (11). Gas discharged may be heated, eg coming from rocket-type combustion chambers within the aerofoil. The aerofoil may be adjustable between high profile (as shown) and low profile (for supersonic flight) using jacks that pivot sections of upper surface (13) at leading and trailing edges (10-11). | ||||||
| 56 | METHOD AND SYSTEM FOR PRODUCING A POTENTIAL OVER A BODY | EP02803943.6 | 2002-11-29 | EP1453726B1 | 2006-09-20 | Kristiansen, Arne |
| This application concerns a method and system using a hydrodynamical effect for producing a potential over a body. The force obtained this way is useful for the propulsion and manoeuvering of ships, submarines, aeroplanes, and airships. A body immersed in a fluid at rest is subject to equal pressures on all sides. A stream close to one side of the body will reduce the local pressure and produce a potential over the body. This is currently done by moving the body in the fluid, cf. aeroplane wings. The potential may be produced by setting up a stream or streams over one side of the body. Bodies attached to aeroplanes by hinges are useful for their lift, propulsion and manoeuvering, and will make them independent of velocity for lift and manoeuvering. The same will be the case for submarines. Airships and seagoing vessels may be designed so as to have their propulsive bodies integrated in their form. The streams are produced from nozzles, holes, or slits in tubes placed near the stagnation line of each body, thus defining its leading edge. Used on a ship, this technique lowers its bow wave and removes the dynamical losses connected with screw propulsion. The manoeuvering force and precision are enhanced. | ||||||
| 57 | Method and apparatus for modulating airfoil lift | EP03254503.0 | 2003-07-18 | EP1384896A3 | 2006-08-16 | Saddoughi, Seyed Gholmali; Leyva, Ivett Alejandra; Dean, Anthony John; Robic, Bernard Francois; Butler, Lawrence |
An apparatus (100) comprising: an airfoil (110) adapted for generating a lift force; and a first pulse detonation actuator (120) disposed inside the airfoil (110) and adapted for impulsively detonating a fuel/air mixture to produce a pressure rise and velocity increase of combustion products therein, the airfoil (110) having a plurality of lift control holes (130) adapted for communicating combustion product flows from the first pulse detonation actuator (120) to an airfoil surface (140) to modulate the lift force.
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| 58 | METHOD AND SYSTEM FOR PRODUCING A POTENTIAL OVER A BODY | EP02803943.6 | 2002-11-29 | EP1453726A1 | 2004-09-08 | Kristiansen, Arne |
| This application concerns a method and system using a hydrodynamical effect for producing a potential over a body. The force obtained this way is useful for the propulsion and manoeuvering of ships, submarines, aeroplanes, and airships. A body immersed in a fluid at rest is subject to equal pressures on all sides. A stream close to one side of the body will reduce the local pressure and produce a potential over the body. This is currently done by moving the body in the fluid, cf. aeroplane wings. The potential may be produced by setting up a stream or streams over one side of the body. Bodies attached to aeroplanes by hinges are useful for their lift, propulsion and manoeuvering, and will make them independent of velocity for lift and manoeuvering. The same will be the case for submarines. Airships and seagoing vessels may be designed so as to have their propulsive bodies integrated in their form. The streams are produced from nozzles, holes, or slits in tubes placed near the stagnation line of each body, thus defining its leading edge. Used on a ship, this technique lowers its bow wave and removes the dynamical losses connected with screw propulsion. The manoeuvering force and precision are enhanced. | ||||||
| 59 | TANGENTIALLY DIRECTED ACOUSTIC JET CONTROLLING BOUNDARY LAYERS | EP00944573.5 | 2000-02-25 | EP1156962B1 | 2004-06-02 | MCCORMICK, Duane, C.; GYSLING, Daniel, L. |
| 60 | Verfahren zur Verminderung des Reibungswiderstandes einer von einem Medium umströmten Oberfläche | EP02015472.0 | 2002-07-12 | EP1277655A1 | 2003-01-22 | Zabka, Werner, Dr.-Ing. |
Um eine Reduzierung des Reibungswiderstandes an umströmten Oberflächen (1) zu erzielen, wird erfindungsgemäß vorgesehen, daß ein gasförmiges Medium (4) über in der umströmten Oberfläche vorhandene Austrittsöffnungen (3) zwischen die Grenzschicht des Stömungsmediums und die feste Oberfläche ausgeblasen wird, und daß ein gasförmiges Medium (4) verwendet wird, dessen molekularen Eigenschaften sich von denjenigen des Strömungsmediums unterscheiden. |
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