| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | METHOD OF LAMINAR FLOW CONTROL USING A DOOR ASSEMBLY | US13551474 | 2012-07-17 | US20120280088A1 | 2012-11-08 | Seiya Sakurai; Matthew D. Fevergeon |
| A method of operating a door assembly may include pivoting a first door about a first pivot axis from a closed position to an open position such that the first door acts as an inlet. The method may further include pivoting the first door to the closed position, and pivoting a second door about a second pivot axis from a closed position to an open position when the first door is in the closed position such that the second door acts as an outlet facing in a direction opposite the first door. The method may additionally include pivoting the second pivot axis about the first pivot axis when pivoting the second door, the second door being of a smaller size than the first door and forming at least a portion of the first door. | ||||||
| 122 | Door assembly for laminar flow control system | US12356029 | 2009-01-19 | US08245976B2 | 2012-08-21 | Seiya Sakurai; Matthew D. Fevergeon |
| A door assembly has a first door integrated with a second door. The first door has a first door cowl. The second door is pivotably mounted to the first door and has a second door cowl forming at least a portion of the first door cowl. The door assembly includes at least one actuator coupled to the first and second doors. Each one of the first and second doors is pivotable between open and closed positions and defines an opening when moved to the open position. The openings of the first and second doors face in opposite directions. The actuator is operative to pivotably move at least one of the first and second doors between the open and closed positions. | ||||||
| 123 | DEVICE FOR BOUNDARY LAYER SUCTION AND COMPOSITE COMPONENT THEREFOR | US13435078 | 2012-03-30 | US20120187252A1 | 2012-07-26 | Martin Gerber |
| The invention relates to a device for boundary layer suction on the outer skin of an aircraft, on which outer skin a surface where drawing off by suction can take place comprising openings is connected to a suction source by way of at least one suction line, wherein the surface where drawing off by suction can take place is formed by at least one panel-shaped composite component that comprises an extruded profile, made of light metal, as a base body, which extruded profile comprises several suction channels that are open towards the outer skin, onto which base body, for the purpose of forming the outer skin, a micro-perforated metal cover sheet has been applied in the region of the surface where drawing off by suction can take place.Furthermore, the invention also relates to a method for producing such a panel-shaped composite component. | ||||||
| 124 | Apparatus and method for passive purging of micro-perforated aerodynamic surfaces | US12356018 | 2009-01-19 | US08128037B2 | 2012-03-06 | Arthur G. Powell; Paul M. Vijgen |
| A purging system for a laminar flow control system comprises an air scoop and a diffuser fluidly connected thereto. The air scoop is disposable into an external flow of an external atmosphere. The diffuser is configured to fluidly connect the air scoop to a suction cavity of the laminar flow control system wherein the suction cavity may be disposed adjacent a porous skin of an airfoil such as adjacent a leading edge of the airfoil. The laminar flow control system may be configured to suction boundary layer flow passing over the porous skin by drawing a portion of the boundary layer flow through a plurality of pores formed in the porous skin. The diffuser ducts high pressure flow captured by the air scoop to the suction cavity for discharge through the pores to reduce the potential of blockage thereof. | ||||||
| 125 | LAMINAR FLOW PANEL | US12856667 | 2010-08-15 | US20120037760A1 | 2012-02-16 | Henry J. Koppelman; Paul S. Gregg |
| An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. At least one hollow member is coupled to the inner surface and is operable to suction air from the outer surface and through the perforated panel skin. The at least one hollow member is oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body. | ||||||
| 126 | Reduction of frictional losses in the region of boundary layers on surfaces, around which a fluid flows | US11911138 | 2006-04-05 | US08091837B2 | 2012-01-10 | Eckart Frankenberger; Matthias Meussen |
| An aerodynamic body with a plurality of nozzles for throttling a fluid flow to be removed by suction through the nozzles in a self-regulated fashion is disclosed. The aerodynamic body according to one example, includes a plurality of throttling nozzles with a throttle section that is defined by an inlet and an outlet. In one example, the interior wall of the throttle section may be designed such that an effective flow cross section is reduced in a self-regulated fashion due to the creation of turbulences on the interior wall of the throttle section as the pressure differential between the inlet and the outlet of the throttle section increases. | ||||||
| 127 | Passive removal of suction air for laminar flow control, and associated systems and methods | US11763569 | 2007-06-15 | US07866609B2 | 2011-01-11 | Pradip G. Parikh |
| Passive removal of suction air for producing a laminar flow, and associated systems and methods are disclosed. One such method includes forming a laminar flow region over an external surface of an aircraft by drawing air through the external surface and into a plenum. The method can further include passively directing the air from the plenum overboard the aircraft. For example, the air can be passively directed to a region external to the aircraft having a static pressure lower than a static pressure in the plenum, as a result of the motion of the aircraft. Flows from different sections of the external surface can be combined in a common plenum, and the corresponding massflow rates can be controlled by the local porosity of the external surface. | ||||||
| 128 | DEVICE FOR REDUCING THE AERODYNAMIC DRAG OF A LEADING SURFACE OF AN AIRCRAFT | US12783856 | 2010-05-20 | US20100294892A1 | 2010-11-25 | Freerk SYASSEN |
| A device for reducing the aerodynamic drag of a leading surface of an aircraft includes at least one air permeable structure disposed in an area of the leading surface and a suction device configured to interact with the at least one air permeable structure. | ||||||
| 129 | Surface Ventilator For A Compliant-Surface Flow-Control Device | US12681750 | 2008-03-03 | US20100236637A1 | 2010-09-23 | James Edward Hendrix, JR. |
| A compliant-surface flow-control device for reducing drag on objects moving through fluids is described. The device has a substrate having a plurality of ridges, a porous membrane covering the substrate, and interior spaces between the porous membrane and the substrate ridges. | ||||||
| 130 | DOOR ASSEMBLY FOR LAMINAR FLOW CONTROL SYSTEM | US12356029 | 2009-01-19 | US20100181435A1 | 2010-07-22 | Seiya Sakurai; Matthew D. Fevergeon |
| A door assembly has a first door integrated with a second door. The first door has a first door cowl. The second door is pivotably mounted to the first door and has a second door cowl forming at least a portion of the first door cowl. The door assembly includes at least one actuator coupled to the first and second doors. Each one of the first and second doors is pivotable between open and closed positions and defines an opening when moved to the open position. The openings of the first and second doors face in opposite directions. The actuator is operative to pivotably move at least one of the first and second doors between the open and closed positions. | ||||||
| 131 | Flow surface for a three-dimensional boundary-layer flow, especially on a swept wing, a swept tail plane or a rotor | US11496760 | 2006-08-01 | US07735782B2 | 2010-06-15 | Markus Kloker; Ralf Messing |
| A flow surface (16), e.g. on a swept aircraft wing, has a three-dimensional boundary-layer flow. The surface is defined by a spanwise direction (z) and a chordwise direction (x). In or on the flow surface excitation locations (22) are arranged, exciting primary disturbances. The disclosure is characterized in that the excitation locations (22) are arranged such that benign steady primary disturbances are excited and maintained on a sufficiently-high amplitude level as longitudinal vortices respectively crossflow vortices, suppressing naturally growing nocent primary disturbances by a non-linear physical mechanism. The benign primary disturbances preserve a laminar flow, such that unsteady secondary disturbances, which may initiate turbulence and which, otherwise, are excited in streamwise direction by nocent primary vortices, are suppressed or at least stabilized. | ||||||
| 132 | Aircraft component exposed to streaming surrounding air | US11568916 | 2005-05-11 | US07673832B2 | 2010-03-09 | Juergen Meister |
| An aircraft component, such as a wing, has perforations through an outer wall for boundary layer suction. In the space between the outer wall and an inner wall partition walls form pressure channels and suction channels that are adjacent to each other and alternate, which channels communicate with the perforations. For example, alternating channels may be formed by a corrugated structure having trapezoidal corrugations providing a larger area for the suction channels than for the pressure channels. The pressure channels may be coupled to a hot-air reservoir by a control device, lines and valves, and the suction channels may be coupled to a vacuum reservoir, unless a short-circuit valve is used to cross connect the lines. | ||||||
| 133 | REDUCTION OF FRICTIONAL LOSSES IN THE REGION OF BOUNDARY LAYERS ON SURFACES, AROUND WHICH A FLUID FLOWS | US11911138 | 2006-04-05 | US20090266937A1 | 2009-10-29 | Eckart Frankenberger; Matthias Meussen |
| An aerodynamic body with a plurality of nozzles for throttling a fluid flow to be removed by suction through the nozzles in a self-regulated fashion is disclosed. The aerodynamic body according to one example, includes a plurality of throttling nozzles with a throttle section that is defined by an inlet and an outlet. In one example, the interior wall of the throttle section may be designed such that an effective flow cross section is reduced in a self-regulated fashion due to the creation of turbulences on the interior wall of the throttle section as the pressure differential between the inlet and the outlet of the throttle section increases. | ||||||
| 134 | PASSIVE REMOVAL OF SUCTION AIR FOR LAMINAR FLOW CONTROL, AND ASSOCIATED SYSTEMS AND METHODS | US11763569 | 2007-06-15 | US20090212165A1 | 2009-08-27 | Pradip G. Parikh |
| Passive removal of suction air for producing a laminar flow, and associated systems and methods are disclosed. One such method includes forming a laminar flow region over an external surface of an aircraft by drawing air through the external surface and into a plenum. The method can further include passively directing the air from the plenum overboard the aircraft. For example, the air can be passively directed to a region external to the aircraft having a static pressure lower than a static pressure in the plenum, as a result of the motion of the aircraft. Flows from different sections of the external surface can be combined in a common plenum, and the corresponding massflow rates can be controlled by the local porosity of the external surface. | ||||||
| 135 | MAST FOR AN AIRCRAFT NACELLE INCORPORATING MEANS FOR LIMITING THE APPEARANCE OF VIBRATIONS, IN PARTICULAR IN CERTAIN FLIGHT REGIMES, AT A HIGH MACH NUMBER AND LOW LIFT | US12043157 | 2008-03-06 | US20080217468A1 | 2008-09-11 | Thierry FOL |
| A mast for connection between a power plant and the rest of an aircraft that includes an outside surface (14) that is in contact with the air flows, characterized in that it includes, in the outside surface (14), at least one recess (22) that is blocked by a porous wall (24), with a porosity of 3 to 6%, coming into the extension of the outside surface (14), whereby the recess makes it possible to have the high-pressure zone (18) communicate with the low-pressure zone (20), zones that are arranged on both sides of a shock wave (16). | ||||||
| 136 | Aerofoils | US10958589 | 2004-10-06 | US07264444B2 | 2007-09-04 | Shaun Stephen Dunn |
| An aerofoil has a body, and at least one flow control device, the flow control device including a passage within the body of the aerofoil, and a passage outlet at an upper aerofoil surface of the aerofoil, whereby in use, air from the passage passes through the passage outlet to affect airflow over the upper surface of the aerofoil over at least a range of incidence angles, wherein the passage outlet is provided by an outlet fitting which is secured relative to the upper surface of the aerofoil, the outlet fitting including a surface part which lies contiguously with the surrounding upper aerofoil surface so there is no or only a minimal discontinuity where the surface part and the surrounding upper aerofoil surface interface, the surface part of the fitting further including an opening which communicates with the passage within the body of the aerofoil. | ||||||
| 137 | Aerofoils | US10958589 | 2004-10-06 | US20050207895A1 | 2005-09-22 | Shaun Dunn |
| An aerofoil has a body, and at least one flow control device, the flow control device including a passage within the body of the aerofoil, and a passage outlet at an upper aerofoil surface of the aerofoil, whereby in use, air from the passage passes through the passage outlet to affect airflow over the upper surface of the aerofoil over at least a range of incidence angles, wherein the passage outlet is provided by an outlet fitting which is secured relative to the upper surface of the aerofoil, the outlet fitting including a surface part which lies contiguously with the surrounding upper aerofoil surface so there is no or only a minimal discontinuity where the surface part and the surrounding upper aerofoil surface interface, the surface part of the fitting further including an opening which communicates with the passage within the body of the aerofoil. | ||||||
| 138 | Movable surface plane | US10187953 | 2002-07-03 | US06622973B2 | 2003-09-23 | Ahmed Z. Al-Garni; Amro M. Al-Qutub |
| Movable surface planes include opposed independently movable endless surfaces over the majority of opposite sides of the planes. By moving one surface in the same direction as the fluid flow about the plane, and the opposite surface in a direction opposite the fluid flow, the flow is accelerated across the surface moving in the same direction to produce a lesser pressure, and retarded across the surface moving in the opposite direction to produce a greater pressure. The net result is a force urging the plane toward the surface moving in the direction of ambient fluid flow. The two surfaces of the present invention may be operated independently of one another, to move in the same or opposite directions and to have the same or different velocities. The movable surfaces are porous and communicate with ductwork within the structure, to provide fluid flow through the surfaces for boundary layer control. | ||||||
| 139 | Method for controlling and delaying the separation of flow from a solid surface by suction coupling (controlling separation by suction coupling, CSSC) | US10073579 | 2002-02-12 | US20030150962A1 | 2003-08-14 | Bela Orban |
| A method to delay flow separation from a solid body in a fluid stream by coupling the region of the suction peak with the region of adverse pressure gradient. This method is particularly applicable for increasing the lift of a wing or for increasing the effectiveness of machines designed to move fluid or control fluid flow. | ||||||
| 140 | Boundary layer control of aerodynamic airfoils | US09718397 | 2000-11-24 | US06488238B1 | 2002-12-03 | Lorenzo Battisti |
| Boundary layer control of a structural element in a fluid stream is achieved by the following operations: providing in such structural element at least one region equipped with micro porous structure by an electroforming technique; having a fluid stream flow through the external surface of the said at least one region, inwards or outwards with respect to the environment in which that element is placed. | ||||||
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