| 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 | Oscillating air jets for helicopter rotor aerodynamic control and BVI noise reduction | US869725 | 1997-06-05 | US6092990A | 2000-07-25 | Ahmed A. Hassan; Friedrich K. Straub; David B. Domzalski |
| An active control system for reducing blade-vortex-interaction (BVI) noise generated by a rotor blade. The active control system includes a pressure sensor assembly, a device for changing a lift generated by the rotor blade, and a controller for activating the device upon a detected change in air pressure by the sensor assembly. The sensor assembly is disposed in close proximity to the rotor blade, and is adapted to detect a change in air pressure on a surface of the rotor blade near a leading edge of the rotor blade. The device is adapted to be activated by the controller, to thereby change a lift of the rotor blade. The controller activates the device to change a lift of the rotor blade in order to introduce a compensating pressure onto the surface of the rotor blade. This compensating pressure attenuates the magnitude of the change of air pressure. The device for changing a lift generated by the rotor blade can include at least one aperture on the rotor blade and a diaphragm in the interior of the rotor blade. The diaphragm can be activated and moved between a first position and a second position at a frequency. Movement of the diaphragm from the first position to the second position pushes air out of the at least one aperture, and movement of the diaphragm from the second position to the first position draws air into the at least one aperture. | ||||||
| 142 | Vehicular boundary layer control system and method | US978287 | 1997-11-25 | US6068328A | 2000-05-30 | Robert F. Gazdzinski |
| A vehicular boundary layer control system utilizing a series of external perforation arrays and suction sources controlled by a digital signal processor or microprocessor. Each array of perforations in the outer vehicle skin is served by a plenum chamber, which is selectively isolable from a suction manifold. The desired vacuum for each individual plenum and associated array is determined through the sampling of the turbulence associated with that array as well as other sensed environmental parameters. Vacuum is maintained at the desired level in each plenum through the arbitration of various suction sources and the selective restriction of airflow from the plenum(s) to the suction manifold. For terrestrial aerodynamic vehicles, a series of moisture separators are included in the plenums to mitigate the effects of any ingested moisture. The system also includes provision to induce reverse flow through the suction manifold, plenums, and perforation arrays in order to purge the system of dust and other particulates, which may be ingested during operation. | ||||||
| 143 | Leading edge construction for an aerodynamic surface and method of making the same | US977825 | 1997-11-25 | US6050523A | 2000-04-18 | Peter Kraenzien |
| A leading edge structure for an aerodynamic surface includes a support structure made of fiber-reinforced synthetic material and a skin structure made of metal mounted on the support structure. The support structure includes an inner laminate, an outer laminate, and longitudinally extending tubes and channels arranged between the inner and outer laminates, as well as a synthetic foam filler material in the spaces between the tubes, channels, and laminates. The skin structure includes an outer skin having perforations, especially in the form of suction holes, an inner skin, and spacer members interconnected therebetween so as to form a substantially form-stable metal skin structure. Respective holes pass through the inner skin, the outer laminate, and the walls of the tubes and channels in order to communicate the suction hole perforations of the outer skin with the interior spaces within the tubes and channels. The skin structure is adhesively bonded to the support structure. In a method for making the leading edge structure, the prefabricated components of the support structure are laid up, molded and cured in a positive mold, the prefabricated components of the skin structure are formed and soldered together on a positive mold, and then the skin structure is adhesively bonded onto the support structure. | ||||||
| 144 | Ice protection for porous structure | US871904 | 1997-06-12 | US5944287A | 1999-08-31 | Leonard J Rodgers |
| A nacelle having a porous structure is provided with laminar flow control and contamination protection. In region B suction through a composite layer is achieved by evacuating a chamber adjacent the inner surface of the nacelle to provide laminar flow control. At the leading edge of the nacelle a sintered metal sheet is attached to an inner surface of the composite layer to control the flow of a liquid over the leading edge of the nacelle. The liquid is contained in a chamber adjacent the sintered metal sheet which is defined by a backing sheet which has a series of depressions therein. Hot air fed through a perforated pipe impinges upon the backing sheet and the depressions transmit heat to the sintered metal sheet. The sintered metal sheet has good thermal conductivity and in turn heats the porous composite layer to prevent the formation of ice thereon. | ||||||
| 145 | Rudder assembly with a controlled boundary layer control for an aircraft | US953913 | 1997-10-20 | US5899416A | 1999-05-04 | Juergen Meister; Juergen Pfennig; Werner Held |
| The boundary layer flow along the surface of an aircraft rudder assembly is controlled by suction applied through perforations primarily installed in the leading edge of the rudder assembly. The control is such that a laminar flow is enforced or at least such that any turbulent flow is displaced so that it begins downstream of the rudder assembly leading edge. Suction air chambers are arranged along the leading edge inside a nose box of the rudder assembly and these boxes are connected through air ducts and a valve system to an exhaust fan. The valve system and the exhaust fan are controlled by a central processing unit providing a flow controller for the suction in response to control signals produced from rated values and sensed actual valves to provide a uniform distribution of the suction along the leading edge of the rudder assembly. The suction system may be switched over to a de-icing mode by blowing warm air out through the perforations in a controlled manner. | ||||||
| 146 | Airfoil lift management device | US929133 | 1997-09-05 | US5806808A | 1998-09-15 | Patrick J. O'Neil |
| A passive porosity airfoil lift management device employed on a leading edge region of said airfoil whereby the lift on said airfoil may be varied and controlled by passively transferring air pressure between the upper surface and lower surfaces of said leading edge region of the airfoil through upper and lower porous skin regions, upper and lower plenum cavities disposed in said airfoil, and controllably monitoring and regulating said passive air pressure transference with at least one valve and a microprocessor. | ||||||
| 147 | Ram air drive laminar flow control system | US569907 | 1995-12-08 | US5779196A | 1998-07-14 | Thomas Timar |
| An improvement to supersonic laminar flow control suction systems, including an inlet air duct (32) for providing subsonic ram engine inlet air, is provided. The inlet air duct (32) supplies air pressure power to one or more turbines of suction system compressor units alone for flight conditions at or above a particular minimum speed and minimum altitude, and in conjunction with engine compressor bleed air for flight conditions below the minimum speed and minimum altitude. The inlet air duct (32) is angled in the direction of subsonic airflow approximately 30 degrees from the horizontal off an opening in an upper wall of a subsonic diffuser of an engine inlet on a supersonic aircraft, and is connected to a power input line that feeds one or more compressor unit turbines. A check valve prevents backflow of air toward the engine inlet. The suction system further includes a short compressor output duct (38) and a short turbine output duct (40). These two ducts join to form a single exhaust passage (42), ensuring a moderate overall suction air exhaust gas temperature. | ||||||
| 148 | Aircraft boundary layer control system with discharge transpiration panel | US566584 | 1995-11-30 | US5772156A | 1998-06-30 | Pradip G. Parikh; Frank D. Neumann |
| An improvement to boundary layer control system, including a transpiration panel (58) for transpiring suction air in a distributed manner, is provided. The transpiration panel (58) replaces the discharge nozzle of prior art flow control systems. The transpiration panel (58) is generally a rigid panel having a plurality of small holes (62) extending from an inner panel surface (56) to a smooth outer panel surface (54). The transpiration panel (58) is positioned flush with an external aircraft surface in a region where laminar flow control is not being attempted. Exemplary subsonic and supersonic boundary layer control systems including the transpiration panel (58) are provided. A preferred location of the transpiration panel (58) for the subsonic application is the underside of a wing (80), near the leading edge. A preferred location of the transpiration panel (58) for the supersonic application including on the upper surface of a wing (114) near the fuselage (118), in a turbulent wedge region. | ||||||
| 149 | Movable sheet for laminar flow and deicing | US333483 | 1994-11-02 | US5590854A | 1997-01-07 | 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. | ||||||
| 150 | Laminar flow control apparatus for aerodynamic surfaces | US956323 | 1992-10-05 | US5366177A | 1994-11-22 | Steven P. DeCoux |
| Aerodynamic boundary layer control apparatus comprising a panel assembly having one surface for immersion in an ambient fluid flow and provided with perforations, a first array of fluid transporting channels fluidly coupled with various ones of the perforations, a second array of fluid transporting channels overlapping the first array of channels, and a suction-generating apparatus fluidly coupled with the second array of channels. An opposing surface of the panel assembly has a contour congruent with that of the aircraft wing or body structure to which it is to be removably attached. The suction-generating apparatus applies a suction force to the second array of channels to draw the ambient fluid into the first array of channels to enable conformace of the fluid with the one surface. Apertures couple the first and second fluid-transporting channels, and movable passage-blocking plates positioned in the apertures can be moved to enable creation of different magnitude suction forces at various predetermined locations at the exterior surface of the panel assembly. | ||||||
| 151 | Method and apparatus for laminar flow control | US113585 | 1993-08-27 | US5316032A | 1994-05-31 | Steven P. DeCoux |
| A method and apparatus for establishing discrete zones of pressure at the surface of a perforated panel of the type typically used for laminar fluid flow control includes a first array of channel members fluidly communicating with perforations in the panel, all of the channel members in the first array extending in a first direction and being substantially parallel to one another, and a second array of channel members fluidly communicating with the fluid in the first array of channel members, all of the channel members in the second array extending in a second direction and being substantially parallel to one another, where the first and second arrays of channel members being disposed in crossing relationship with a source of pressure being applied to the second array of channel members. By this arrangement, control of fluid flow in at least one of the first and second arrays results in discrete zones of pressure at the surface of the panel. Various additional embodiments include variable sized apertures in the second array of channels and various condition-responsive actuators for the apertures. | ||||||
| 152 | Passive venting technique for shallow cavities | US250468 | 1988-09-28 | US5018688A | 1991-05-28 | Robert L. Stallings, Jr.; Floyd J. Wilcox, Jr. |
| A device for reducing drag and store separation difficulties caused by shallow cavities on aircraft in supersonic flight consisting of a slab of porous material cut to fit precisely inside the cavity. This slab is mounted inside the cavity such that a plenum chamber is formed between the slab and the floor of the cavity. This device allows air to flow through the chamber opposite to the direction of flow outside the chamber. This results in reduced drag and improved store separation characteristics. | ||||||
| 153 | Laser perforating process and article produced therein | US171800 | 1988-03-22 | US4857698A | 1989-08-15 | Kenneth R. Perun |
| A process for perforating a metal sheet with clean holes of substantially uniform size and shape comprises placing a suitable transparent backing tape, such as an adhesive polyethylene tape, on one surface of the metal sheet. The assembly is placed in a fixture, a laser beam generated by a pulsed Nd:YAG laser is impinged on the opposite surface of the metal sheet, and the laser parameters are chosen to control the laser beam to penetrate the metal sheet and form a plurality of small tapered holes therein without penetrating the tape. A clean metal surface results around the holes with no recast structure or dross present in and around the holes. A drilled titanium sheet of the above type is particularly suited for utility as an outer wing leading edge of an aircraft and which provides good laminar flow control efficiency. | ||||||
| 154 | Method of reducing sound generation in fluid flow systems embodying foil structures and the like | US3779338D | 1972-01-27 | US3779338A | 1973-12-18 | HAYDEN R; CHANAUD R |
| This disclosure deals with preventing or at least reducing sound generation that normally results from fluid flow in various rotor and stator systems about the foil or blade surfaces from the developed fluid forces, by rendering at least portions of the blade of reduced flow impedance, as by rendering the same porous in various degrees.
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| 155 | Transpiration cooled window | US3452553D | 1967-03-17 | US3452553A | 1969-07-01 | DERSHIN HARVEY; LEONARD CHARLES A |
| 156 | Aircraft aerodynamic structures | US49639065 | 1965-10-15 | US3309042A | 1967-03-14 | BRIEN EDWARDS JOSEPH |
| 1,125,121. Boundary layer control. HANDLEY PAGE Ltd., and J. B. EDWARDS. 1 Sept., 1965 [20 Oct., 1964], No. 42806/64. Heading F2R. [Also in Division B7] An aircraft wing to which boundary layer suction is applied comprises an outer skin 11 containing spanwise extending lines 10 of porous elements, e.g. slots, holes, or inserted porous material, spanwise chambers 15 beneath the skin, each in communication with a line 10, spanwise ducts 16 each in communication with a chamber 15, and chordwise ducts 25 communicating with the spanwise duets. The chordwise ducts lead to one or more main ducts and contain valves for adjusting the flow rate on final assembly or during servicing. The main ducts may be of glass fibre construction and be located between two wing spars. The invention may be applied to other aircraft surfaces. | ||||||
| 157 | Method of making permeable airfoil skin material | US16039061 | 1961-11-27 | US3213527A | 1965-10-26 | ARDELLE GLAZE |
| 158 | Aircraft panel construction for boundary air control | US33017563 | 1963-12-12 | US3194518A | 1965-07-13 | WALSH ROBERT L |
| 159 | Wing structure incorporating boundary layer control | US38513553 | 1953-10-09 | US2945644A | 1960-07-19 | COLMAN PHILIP A |
| 160 | Porous area-suction flap for aircraft | US52431155 | 1955-07-25 | US2876966A | 1959-03-10 | COOK WOODROW L |
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