| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | Boundary layer induction system for aircraft power plant | US9146349 | 1949-05-05 | US2751168A | 1956-06-19 | STALKER EDWARD A |
| 162 | Airplane wing structure | US18338150 | 1950-09-05 | US2646945A | 1953-07-28 | PERRY JOHN A |
| 163 | Sustaining and propulsive means for aircraft | US75660834 | 1934-12-08 | US2164721A | 1939-07-04 | PRICE ALBERT O |
| 164 | Means for overcoming fluid friction | US18783327 | 1927-04-30 | US1726882A | 1929-09-03 | ARNO BOERNER |
| 165 | Aircraft engine nacelle | US15171306 | 2016-06-02 | US10131443B2 | 2018-11-20 | Howoong Namgoong |
| A gas turbine engine nacelle comprising an intake liner. The liner includes a plurality of cells. Each cell includes an open radially inner end in fluid communication with an interior side of the nacelle, and an open radially outer end in fluid communication with an exterior side of the nacelle. Each open end of each cell defines a respective cross sectional area. The intake liner further comprises radially inner and outer facing sheets overlying a respective radially inner and outer open ends of the respective cell. Each facing sheet defines at least one aperture overlying at least one cell, an overlying portion of the respective aperture having a smaller cross sectional area than the respective open end of the respective cell. | ||||||
| 166 | Aircraft wing rib | US14964032 | 2015-12-09 | US10005545B2 | 2018-06-26 | James Alderman; Stephen Rolston; Jonathan Meyer |
| There is disclosed an aircraft wing rib comprising a structural rib section to which a wing skin can be attached; and a suction conduit to which, in use, a negative pressure can be applied so as to cause air to be drawn through suction holes provided in the outer surface of the wing skin. There is also disclosed an aircraft wing including such a wing rib. | ||||||
| 167 | Panel for controlling the aerodynamic phenomena on a body | US14426334 | 2013-08-30 | US09994297B2 | 2018-06-12 | Danilo Marchetti |
| A panel (3) for controlling the aerodynamic phenomena generated by a body (0) to be positioned on a surface of an aircraft (V). The panel (3) can be associated with the base of the body (0) and includes at least one inlet aperture (322) and at least one outlet aperture (322′) placed in communication with each other, through which a portion of a fluid flow (W) in which the body (0) is immersed can selectively pass. The inlet aperture (322) is located upstream of the body (0) and the outlet aperture (322′) is located downstream of the body (0), with respect to the direction of the fluid flow (W). | ||||||
| 168 | CONTROL SURFACE COMPONENT FOR A HIGH-LIFT DEVICE OF AN AIRCRAFT AND PRODUCTION METHOD THEREFOR | US15826227 | 2017-11-29 | US20180148163A1 | 2018-05-31 | Michael Bauer; Johann Reichenberger |
| A control surface component for reducing a noise level generated by the flow around the control surface component, in particular flap component, for a high-lift device of a wing of an aircraft, having a lift body, which is designed or configured to generate lift and which comprises a lift body end region, a lift body suction side and a lift body pressure side, wherein a foam body, which can be mounted adjoining the lift body end region, is formed separately from the lift body as an integral element and is exposed, is designed or configured to provide, in the mounted state, a plurality of flow paths which fluidically connect the lift body suction side and the lift body pressure side to compensate for a pressure difference prevailing between the lift body suction side and the lift body pressure side. | ||||||
| 169 | Multi-zone active laminar flow control system for an aircraft propulsion system | US14713621 | 2015-05-15 | US09908620B2 | 2018-03-06 | Keith T. Brown; Stuart J. Byrne; Steven M. Kestler |
| A nacelle is provided for an aircraft propulsion system. The nacelle may include an outer barrel and an active laminar flow control system. The active laminar flow control system may include a plurality of suction sources and a plurality of arrays of perforations in the outer barrel. The active laminar flow control system may be configured with a plurality of zones. Each of the zones may include a respective one of the suction sources which is fluidly coupled with a respective one of the arrays of perforations in the outer barrel. | ||||||
| 170 | SOUND ABSORBERS FOR AIRFRAME COMPONENTS | US15535841 | 2015-12-09 | US20170369147A1 | 2017-12-28 | Raymond Lee Man WONG |
| Sound absorbers and airframe components comprising such sound absorbers are disclosed. In one embodiment, an airframe component comprises an aerodynamic surface (48) and a sound absorber (38). The sound absorber (38) comprises a perforated panel (40) having a front side exposed to an ambient environment outside of the airframe component and an opposite back side. The panel (40) comprises perforations extending through a thickness of the panel for permitting passage of sound waves therethrough. The sound absorber (38) also comprises a boundary surface spaced apart from the perforated panel. The boundary surface and the back side of the perforated panel (40) at least partially define a cavity in the airframe component for attenuating some of the sound waves entering the cavity via the perforations in the perforated panel (40). | ||||||
| 171 | METHODS AND SYSTEMS FOR ROTARY WING ACTIVE FLOW CONTROL | US14813216 | 2015-07-30 | US20170029102A1 | 2017-02-02 | Daniel J. Clingman; Randy Lee M. Mallari |
| Within examples, systems for enhanced performance blades for rotor craft are provided and methods for operation. An example system for a rotary device is provided comprising a rotor blade coupled to a rotor hub. The system also comprises an air channel disposed within the rotor blade, where the air channel is sealed proximate to a distal end of the rotor blade. The system also comprises an inlet positioned at a proximal end of the rotor blade, where the inlet is in fluid communication with the air channel. The system also comprises a plurality of outlets positioned along the rotor blade, where each of the plurality of outlets are in fluid communication with the air channel. | ||||||
| 172 | MULTI-ZONE ACTIVE LAMINAR FLOW CONTROL SYSTEM FOR AN AIRCRAFT PROPULSION SYSTEM | US14713621 | 2015-05-15 | US20160375988A1 | 2016-12-29 | Keith T. Brown; Stuart J. Byrne; Steven M. Kestler |
| A nacelle is provided for an aircraft propulsion system. The nacelle may include an outer barrel and an active laminar flow control system. The active laminar flow control system may include a plurality of suction sources and a plurality of arrays of perforations in the outer barrel. The active laminar flow control system may be configured with a plurality of zones. Each of the zones may include a respective one of the suction sources which is fluidly coupled with a respective one of the arrays of perforations in the outer barrel. | ||||||
| 173 | Profile plate portion for use as an outer wall of a flow body, method for manufacturing a profile plate portion and flow body component comprising a suction-extraction device for fluid | US13650669 | 2012-10-12 | US09511848B2 | 2016-12-06 | Martin Gerber; Freerk Syassen |
| A profile plate portion is disclosed for use as an outer wall of a flow body including a first profile plate panel that is fluid permeable, a second profile plate panel extending along the first profile plate panel, and a reinforcing device for supporting the first profile plate panel and the second profile plate panel on one another. Fluid can flow through the reinforcing device, and/or fluid of the flow present at the first profile plate panel, which flows through the first profile plate panel, can flow through the reinforcing device in the local profile plate thickness direction from the first profile plate panel to the second profile plate panel and in some regions can flow through to an inside that is situated opposite the flow side. A method is disclosed for manufacturing a profile plate portion and a flow body component with a suction-extraction device for fluid. | ||||||
| 174 | HEAT EXCHANGER FOR LAMINAR-FLOW AIRCRAFT | US15107970 | 2015-03-04 | US20160332724A1 | 2016-11-17 | Carsten Ralf Mehring |
| A laminar flow control surface having a foraminous section (also referred to below as a foraminous portion, 251) of a skin (250) of a vehicle to permit low temperature fluid to flow through the foraminous section to a heat exchanger (236), to reduce drag of the vehicle and to dissipate heat from the heat exchanger. The foraminous section (251) and the heat exchanger (236) synergistically reduce drag and transfer heat from the heat exchanger. The vehicle may be an aircraft with a laminar flow control system including a foraminous portion on a leading edge of the aircraft. While the aircraft is in flight, a portion of air impinging near the foraminous portion may flow laminarly about the leading edge, and another portion of the impingingair may flow through the foraminous portion to a heat exchanger to transfer heat from the heat exchanger to the air. | ||||||
| 175 | OPTIMIZED NACELLE PROFILE AND PLENUM SHAPE FOR BOUNDARY LAYER INGESTION ACTIVE LAMINAR FLOW CONTROL | US14692414 | 2015-04-21 | US20160311520A1 | 2016-10-27 | Ann E. Khidekel |
| Aspects of the disclosure are directed to a nacelle of an aircraft, comprising a surface that is profiled such that during cruise flight operation lines of constant static pressure of a boundary layer around the nacelle in a given region are substantially contained within a plane that is normal to an engine axis. | ||||||
| 176 | HIGH-LIFT DEVICE OF FLIGHT VEHICLE | US15052497 | 2016-02-24 | US20160167769A1 | 2016-06-16 | Kazuhide ISOTANI; Kenji HAYAMA |
| A high-lift device of a flight vehicle includes: a flap main body provided at a trailing edge portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in a wing span direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of a tip end portion of the flap main body to an upper surface of the tip end portion. | ||||||
| 177 | Laminar Flow Panel | US15043152 | 2016-02-12 | US20160159465A1 | 2016-06-09 | Henry J. Koppelman; Michael K. Klein |
| 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. A micro-lattice support structure is coupled to the inner surface and defines airflow gaps allowing suctioning of air from the outer surface through the perforated panel skin and into a plenum of the aerodynamic body. Rows of main beams of the micro-lattice support structure are aligned along land lines oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body. | ||||||
| 178 | AIRCRAFT WING RIB | US14964032 | 2015-12-09 | US20160159464A1 | 2016-06-09 | James Alderman; Stephen Rolston; Jonathan Meyer |
| There is disclosed an aircraft wing rib comprising a structural rib section to which a wing skin can be attached; and a suction conduit to which, in use, a negative pressure can be applied so as to cause air to be drawn through suction holes provided in the outer surface of the wing skin. There is also disclosed an aircraft wing including such a wing rib. | ||||||
| 179 | Reactive orthotropic lattice diffuser for noise reduction | US13764062 | 2013-02-11 | US09227719B2 | 2016-01-05 | Mehdi R. Khorrami |
| An orthotropic lattice structure interconnects porous surfaces of the flap with internal lattice-structured perforations to equalize the steady pressure field on the flap surfaces adjacent to the end and to reduce the amplitude of the fluctuations in the flow field near the flap end. The global communication that exists within all of the perforations provides the mechanism to lessen the pressure gradients experienced by the end portion of the flap. In addition to having diffusive effects (diffusing the incoming flow), the three-dimensional orthogonal lattice structure is also reactive (acoustic wave phase distortion) due to the interconnection of the perforations. | ||||||
| 180 | LEADING EDGE NOSE STRUCTURE ON THE VERTICAL STABILIZER OF AN AIRCRAFT | US14729632 | 2015-06-03 | US20150360766A1 | 2015-12-17 | Martin Gerber |
| An aircraft with a fuselage, wings, horizontal stabilizers and a vertical stabilizer, wherein on a front portion of the vertical stabilizer an elongated one-piece nose element is mounted which forms lateral air guide surfaces. To the front end of the nose element a perforated metal plate nose member is attached. The front end of the nose element being closed and between this closed front end and the nose member an elongated air channel is formed. | ||||||
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