| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Method of making a perforated metal sheet | US08779459 | 1997-01-07 | US06202304B1 | 2001-03-20 | Solomon Shatz |
| A movable sheet overlying a wing is disclosed that creates laminar flow over its exposed surface. The movable sheet serves as an integral, retractable shield for protecting a suction support structure of a wing against contamination, and also serves as a movable, conductive substrate for deicing by means of electrical resistance or hot-gas heating. The invention includes a movable sheet that is mounted scroll-like on two motor-driven rollers. The sheet has a solid area without perforations that protects the suction support structure from contamination, and a porous area with perforations therethrough that allows boundary layer suction. The motor-driven rollers scroll the sheet to cover the suction support structure with either the solid area or the perforations of the sheet. Contact rollers at the edge of the sheet supply electrical current to resistively heat the sheet and melt any accumulated ice. The movable sheet can also be moved back and forth to dislodge the ice. | ||||||
| 82 | Extended reaction acoustic liner for jet engines and the like | US298599 | 1999-04-23 | US6135238A | 2000-10-24 | Noe Arcas; Frederick M. Hutto; Charles A. Parente |
| An extended reaction acoustic liner for use in jet engine noise mitigation has a substantially non-porous outer layer, a honeycomb core disposed in laminar juxtaposition to the outer layer, and a porous inner layer in laminar juxtaposition to the honeycomb core such that the honeycomb core is sandwiched between the outer layer and the inner layer. The honeycomb core comprises a plurality of cell walls defining a plurality of cells. Some of the cells are in fluid communication with one another via the openings formed in the cell walls. The openings in the cell walls cause viscous acoustic losses, resulting in acoustic energy dissipation and enhanced noise attenuation. | ||||||
| 83 | Oscillating air jets on aerodynamic surfaces | US869372 | 1997-06-05 | US5938404A | 1999-08-17 | David B. Domzalski; Ahmed A. Hassan; Dennis K. Kennedy |
| An active control device for use on an aerodynamic structure is provided. The aerodynamic structure includes an outer aerodynamic skin and an interior volume, wherein the outer aerodynamic skin surrounds the interior volume. The active control device includes at least one aperture disposed on the outer aerodynamic skin and a diaphragm disposed in the interior volume of the aerodynamic structure. The at least one aperture connects the outer aerodynamic skin to the interior volume, and the diaphragm in the interior volume is movable between a first position and a second position. Movement of the diaphragm from the first position to the second position pushes air through the at least one aperture and out of the interior volume. Movement of the diaphragm from the second position to the first position draws air through the at least one aperture and into the interior volume. The diaphragm may be circular, or may be oval-shaped. | ||||||
| 84 | Control and augmentation of passive porosity through transpiration control | US887002 | 1992-05-22 | US5901929A | 1999-05-11 | Daniel W. Banks; Richard M. Wood; Steven X. S. Bauer |
| A device for controlling pressure loading of a member caused by a fluid moving past the member or the member moving through a fluid. The device consists of a porous skin mounted over the solid surface of the member and separated from the solid surface by a plenum. Fluid from an area exerting high pressure on the member may enter the plenum through the porous surface and exit into an area exerting a lower pressure on the member, thus controlling pressure loading of the member. A transpirational control device controls the conditions within the plenum thus controlling the side force and yaw moment on the forebody. | ||||||
| 85 | Method of manufacturing a porous material | US539606 | 1995-10-05 | US5618363A | 1997-04-08 | Andrew J. Mullender; Leonard J. Rodgers |
| A porous material is manufactured by weaving polycarbonate fibres through a tow of carbon fibres which has been pre-impregnated with an epoxy resin. A second layer of pre-impregnated carbon fibres are superimposed on the woven layer and the epoxy resin is cured to bond the fibres together. A ceramic slurry is applied and allowed To penetrate through the second layer of fibres and part way through the woven layer of fibres to a controlled depth before being dried to form a mask. A thermoplastic powder is then applied to the unmasked region of the woven layer of fibres and sintered. Finally the mask and the polycarbonate fibres are removed chemically to produce a porous material which comprises a sintered thermoplastic layer reinforced with carbon fibres through which channels are provided. | ||||||
| 86 | Aircraft wing having a super critical profile and a venting device for reducing compression shock | US27862 | 1993-03-08 | US5335885A | 1994-08-09 | Rainer Bohning |
| An aircraft wing having a super critical profile is equipped with a venting device extending in the direction of the span width along the upper side of the wing. The ventilating device includes a compensation chamber in the wing and the chamber is covered with a perforated wall strip on both sides of the compression shock. The forward end of the compensation chamber has a gap shaped exit for blowing out the venting medium in the flow direction of the flow across the wing tangentially to the wing. | ||||||
| 87 | Aircraft pylon | US37764 | 1987-04-13 | US5156353A | 1992-10-20 | Philip R. Gliebe; Rudramuni K. Majjigi |
| An aircraft propulsion system includes at least one pusher propeller mounted to a nacelle mounted to the aircraft by a pylon which produces a wake which impinges upon the propeller. The wake from the pylon is modified to reduce noise and vibration produced by the propeller interaction with the wake. The propulsion system may include a pair of counterrotating pusher propellers. | ||||||
| 88 | Combination lift thrust device | US757387 | 1985-07-22 | US4666104A | 1987-05-19 | Charles C. Kelber |
| A combination lift and thrust device for increasing the performance of an aircraft by simultaneously reducing drag and augmenting the thrust of a turbojet engine carried within the device. The device comprises a wing of generally airfoil shape having numerous geometrically spaced apertures penetrating its surface, a turbojet engine carried within the wing, an elongated exhaust plenum attached to the turbojet having a number of strategically positioned exhaust nozzles, and a mixing chamber having a forward opening and a rear nozzle also carried within the wing. The mixing chamber forward opening is cooperatively associated with the exhaust nozzles to form an ejector drawing air through the apertures in the wing into the forward opening, mixing the air with the exhaust gases from the turbojet to provide thrust augmentation, and exhausting the air and gas mixture from the rear nozzle of the mixing chamber. The air drawn through the apertures in the wing surface reduces the turbulent boundary layer on the wing thus reducing the aerodynamic drag of the wing. | ||||||
| 89 | Method for reducing drag of vertical takeoff type aircraft | US3801048D | 1971-06-23 | US3801048A | 1974-04-02 | RICCIUS R |
| Method of reducing drag on an aircraft of the vertical takeoff variety and having a particular power plant for production of vertical thrust as well as a main engine for producing forward thrust during aerodynamic flight; the vertical thrust producing power plant is used as power source for controlling the boundary layer flow along at least part of the surface of the aircraft during aerodynamic flight, residual thrust of that plant is deflected to contribute to forward thrust, supplementing the forward thrust produced by the main engine.
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| 90 | Aircraft skin laminates | US3516895D | 1964-02-03 | US3516895A | 1970-06-23 | HARTMAN RICHARD E |
| 1,088,536. Laminates. B. F. GOODRICH CO. Jan. 27, 1965 [Feb. 3, 1964], No. 3605/65. Heading B5N. [Also in Divisions B7 and F2] A laminated airframe structure constructed for the removal of turbulent boundary layer air comprises an outer skin 10 slotted at 15 and bonded to an inner panel 11 formed with channels 16 aligned with each row of slots 15. A honeycomb core 12 bonded to panel 11 and to a further panel 13 is formed with apertures 18 which communicate at one end with holes in the channels 16 and at the other end with holes in panel 13, each of which is provided with a nipple connected to a suction pump whereby boundary layer air may be drawn through the structure from the outer surface of skin 10. | ||||||
| 91 | Method of making a permeable airfoil skin | US49974765 | 1965-10-21 | US3266130A | 1966-08-16 | ARDELLE GLAZE |
| 92 | Means for removing boundary layer air from aircraft | US16214261 | 1961-12-26 | US3203648A | 1965-08-31 | ARAM VANESIAN |
| 93 | Lift modification for aircraft | US24501462 | 1962-12-17 | US3184185A | 1965-05-18 | RENE BROCARD JEAN MARIE |
| 94 | Helicopter rotor blade | US13134061 | 1961-08-14 | US3100539A | 1963-08-13 | HULBERT JOHN K |
| 95 | Permeable airfoil skin material | US58167856 | 1956-04-30 | US3056432A | 1962-10-02 | ARDELLE GLAZE |
| 96 | Controllable and variable configuration effect system for aircraft | US51709955 | 1955-06-21 | US2956760A | 1960-10-18 | ATTINELLO JOHN S |
| 97 | Airfoils, variable permeability material and method of fabrication thereof | US56004156 | 1956-01-18 | US2843341A | 1958-07-15 | DANNENBERG ROBERT E; WEIBERG JAMES A |
| 98 | Dual unit jet propulsion plant for aircraft | US48596555 | 1955-02-03 | US2820599A | 1958-01-21 | JAKOB ACKERET; CURT KELLER |
| 99 | Outer surfaces for craft moving in one fluid | US25324051 | 1951-10-26 | US2742247A | 1956-04-17 | VICTOR LACHMANN GUSTAV |
| 100 | Aircraft surface with boundary layer control | US16714350 | 1950-06-09 | US2659552A | 1953-11-17 | STALKER EDWARD A |
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