| 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 | Gas turbine engine fan duct base pressure drag reduction | US531734 | 1990-06-01 | US5141182A | 1992-08-25 | George A. Coffinberry |
| An aircraft is provided with an aircraft base pressure drag reduction apparatus including apparatus for ducting boundary layer air on board an aircraft wherein the air produces ram air drag, apparatus for using the air for work, and apparatus for ducting the used boundary layer air to a low pressure area of an aircraft which otherwise produces base pressure drag on the aircraft to reduce the base pressure drag that the low pressure area would otherwise produce. In a more particular embodiment of the invention the low pressure area of the aircraft is in a fan duct of an aircraft gas turbine engine. In the preferred embodiment the low pressure area in a fan duct of an aircraft gas turbine engine is on the pylon fairing and the means for using the air for work includes at least one means for bleeding boundary layer air from the surface of the aircraft for reducing aircraft boundary layer induced drag. | ||||||
| 82 | Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system | US531718 | 1990-06-01 | US5125597A | 1992-06-30 | George A. Coffinberry |
| An aircraft gas turbine engine is provided with a starting air turbine that is directly connected through the starter gearbox to the high pressure (HP) shaft and is provided with an apparatus to extract excess energy from engine compressor bleed air, return it to the engine, and to start the engine with compressed air from starting air sources, and to cool and provide compressed air for powering the Environmental Control System (ECS) and using the bleed air for cabin refreshening. The air turbine may be connected to a nacelle boundary layer bleed compressor to bleed boundary layer air from a forward portion of the nacelle to reduce nacelle surface drag. The ECS may be provided with a wing boundary layer bleed means which uses a cooling air fan in the ECS to draw cooling air through the heat exchangers in the ECS pack from the boundary layer air from a forward portion of the aircraft's wing to reduce its surface drag. | ||||||
| 83 | Method and apparatus for influencing a laminar turbulent boundary layer transition on bodies in flow | US272627 | 1988-11-17 | US4989810A | 1991-02-05 | Hans U. Meier; Alois Maier; Ming de Zhou |
| A method and an apparatus for influencing a laminar-turbulent boundary layer transition on bodies in flow is indicated. The disturbances are in this case introduced into the boundary layer in an unsteady manner. The disturbances are induced by blowing-out and sucking-off and/or by oscillations of the surface and/or by sound pressure. | ||||||
| 84 | Yaw and pitch control of air vehicles at high angles of attack | US453 | 1987-01-05 | US4786009A | 1988-11-22 | Dhanvada M. Rao; Daniel G. Murri |
| Method and apparatus for controlling the yaw and pitch of air vehicles at high angles of attack by controlling the vortex pattern around the forebodies of the air vehicles by means of deflecting strakes 11 and 16. | ||||||
| 85 | Apparatus and method for manufacturing laminar flow control aircraft structure | US15085 | 1979-02-26 | US4296899A | 1981-10-27 | Jack M. Isenberg |
| A method for manufacturing a laminar flow control aircraft structure, typically a wing or other aerodynamic surface, having an outer skin in which a plurality of spanwise oriented and chordwise spaced recesses have been machined. The method includes the installation of a strip of slot assembly tape in each of said recesses, preferably with an adhesive, and the removal of an element of the tape called a cover plate to expose a spanwise slot through which boundary layer air can be drawn. Also disclosed is a slot assembly tape having a protective cover plate and a pair of sidewalls, and a laminar flow control aircraft structure, typically a wing, in which the slot assembly tape has been employed. | ||||||
| 86 | Helicopter | US971161 | 1978-12-20 | US4216924A | 1980-08-12 | Evan A. Fradenburgh |
| An improved helicopter designed to create minimum drag and turbulence in which the main rotor pylon has a top surface having a forward portion defining the rotor head well aperture so as to have a selectively curved lip on the rearward side thereof to eliminate flow separation therefrom of the air being discharged rearwardly from the rotor head well, further having a central portion curving slightly away from the direction of helicopter flight and including a laterally extending boundary layer slot a selected distance downstream of the curved lip through which fluid is expelled substantially parallel to the direction of helicopter flight to energize the surface flow along the pylon top surface, further having a rear portion at a lower elevation extending approximately in the direction of helicopter flight, and having engine and other exhaust ports positioned a selected distance downstream of the boundary layer control slot through which the exhaust fluids are directed over the rear portion in a direction substantially parallel to the direction of helicopter flight, and terminating in a sharp lip to separate the exhaust flow from the pylon surface thereat. | ||||||
| 87 | Aerodynamic flow body | US667245 | 1976-03-15 | US4033526A | 1977-07-05 | William Benson |
| Disclosed is an increased lift aircraft or similar device having an airfoil shaped forward structure. A mass flow engine, such as a jet engine, is positioned to the rear of this structure. In operation, the intake air flow for the engine flows around the forward structure, generating lift. | ||||||
| 88 | Aircraft outer surface covering | US59317556 | 1956-06-22 | US3065940A | 1962-11-27 | ECKSTEIN EMIL L |
| 89 | Sail, parachute, airplane wing, and the like | US47905630 | 1930-08-30 | US1864964A | 1932-06-28 | VAILE PEMBROKE A |
| 90 | AERODYNAMIC ELEMENT OF AN AIRCRAFT, COMPRISING A SET OF PROTRUDING ELEMENTS | US16239730 | 2019-01-04 | US20190210714A1 | 2019-07-11 | Mathias Farouz-Fouquet |
| An aerodynamic element is provided with at least one set of protruding elements, each of the protruding elements is produced in the form of an elongate and profiled rib projecting from a surface of the aerodynamic element. The protruding elements are arranged at the surface of the aerodynamic element, one beside the other, being oriented substantially parallel to one another so that each of them generates a vortex, the set of vortices thus generated making it possible to reduce crossflow instability. | ||||||
| 91 | LOW-NOISE AIRFOIL FOR AN OPEN ROTOR | US15675239 | 2017-08-11 | US20190048724A1 | 2019-02-14 | Daniel Lawrence Tweedt |
| An airfoil section of a blade for an open rotor includes: a pressure side and a suction side, the pressure side and the suction side intersecting at a leading edge and a trailing edge, wherein a chord of the airfoil section is defined as a straight-line distance between the leading edge and the trailing edge; the airfoil section has a meanline defined midway between the pressure side and the suction side; and the meanline is shaped such that, in the presence of predetermined transonic or supersonic relative velocity conditions, maximum and minimum ideal Mach numbers on the suction side will lie within a 0.08 band, between 25% and 80% percent of the chord. | ||||||
| 92 | DEDICATED FANS FOR BOUNDARY LAYER INGESTION | US15606051 | 2017-05-26 | US20180339765A1 | 2018-11-29 | Alan H. Epstein; Gabriel L. Suciu; Jesse M. Chandler |
| A propulsion system for an aircraft comprises at least two main gas turbine engines and a plurality of dedicated boundary layer ingestion fans. An aircraft is also disclosed. | ||||||
| 93 | Aircraft and missile forebody flow control device and method of controlling flow | US13151640 | 2011-06-02 | US10137979B1 | 2018-11-27 | Troy Prince; Frederick J. Lisy; Mehul P. Patel; Jack M. DiCocco; Reed Carver; Robert N. Schmidt |
| A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal associated therewith, the at least one sensor being used for determining or estimating flow separation or side forces on the missile forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor. | ||||||
| 94 | Stabilizer assembly for an aircraft AFT engine | US15191586 | 2016-06-24 | US10106265B2 | 2018-10-23 | Jixian Yao; Andrew Breeze-Stringfellow |
| An aerodynamic stabilizer assembly for stabilizing an aft fan mounted to a fuselage of an aircraft is presented. The stabilizer assembly includes one or more generally horizontal stabilizers for mounting to a nacelle of the aft fan and the fuselage so as to stabilize the aft fan. Each of the generally horizontal stabilizers includes an inner portion and an outer portion. The inner portions are mounted to a nacelle of the aft fan and the fuselage at a predetermined downward angle with respect to a central axis of the aft fan so as to direct airflow upwards and into the aft fan, the outer portion being mounted to the inner portion. | ||||||
| 95 | PROPULSOR | US15899481 | 2018-02-20 | US20180237126A1 | 2018-08-23 | Martin N. GOODHAND; Matthew MOXON |
| A boundary layer propulsor comprises a rotor and a plurality of first aerofoil blades. The rotor has an axis of rotation. The plurality of first aerofoil blades extends radially from the rotor and is arranged in a circumferential array around the axis of rotation. Each of the first aerofoil blades has, in a radially outward sequence, a radially proximal portion, a middle portion, and a radially distal portion. The radially proximal portion has a first cambered cross-section, the middle portion has a second uncambered cross-section, and the radially distal portion has a third cambered cross-section. The first cambered cross-section is cambered in an opposite sense to the third cambered cross-section. | ||||||
| 96 | Optical window system with aero-optical conductive blades | US15678589 | 2017-08-16 | US10023290B2 | 2018-07-17 | David A. Vasquez; Michael Ushinsky; Joseph J. Ichkhan |
| A method of improving optical characteristics of an optical window operating in a flow of fluid and having first and second panes of optically transmissive material—each having an edge adjacent to, parallel with, and at least partially coextensive with each other—is described herein. The method includes inserting a thermally conductive blade between two adjacent edges of the first and second panes of optically transmissive material; and lifting an adverse flow stagnation zone forward of the optical window by protruding the thermally conductive blade into the flow of fluid from an outer surface of the panes of the optical window. | ||||||
| 97 | AIRCRAFT AIRFLOW MODIFICATION DEVICE AND VORTEX GENERATOR ARRANGEMENT FOR AN AIRCRAFT | US15819560 | 2017-11-21 | US20180155013A1 | 2018-06-07 | Dirk Elbracht; Bruno Stefes |
| An aircraft airflow modification device, comprising: at least one resiliently deformable base member; and at least one resiliently deformable flap member that extends from the resiliently deformable base member. Deformation of the resiliently deformable base member from a first state to a second state results in corresponding deformation of the resiliently deformable flap member from a first state to a second state. | ||||||
| 98 | ROTORCRAFT CONFIGURATION AND METHOD OF ROTORCRAFT DESIGN | US15513886 | 2015-09-29 | US20170297697A1 | 2017-10-19 | Blake Almy Moffitt; Brian E. WAKE; Peter F. Lorber |
| A rotorcraft is provided and includes a fuselage. The fuselage includes drag generating portions, a main rotor assembly and an auxiliary propulsor having an expected propulsion efficiency. The auxiliary propulsor is disposed to ingest boundary layer flows and in wake regions associated with the drag generating portions and is provided with a corresponding increase in the expected propulsion efficiency thereof. | ||||||
| 99 | DISTRIBUTED ELECTRIC DUCTED FAN WING | US15374771 | 2016-12-09 | US20170190436A1 | 2017-07-06 | David G. Ullman; Vincent Homer |
| The Distributed Electric Ducted Fan Wing concept incorporates multiple electric ducted fans on lifting surfaces configured to provide integrated aerodynamics and propulsion resulting in enhanced aerodynamic characteristics and thus aircraft performance. The concept uses a plurality of electric ducted fans (EDFs) to not only provide thrust, but to also blow air across the upper surface of a substantial portion of the lifting surface area increasing lift at little loss in efficiency. Not only can the total lift on the surfaces be enhanced, but the lift distribution managed: to aid in aircraft control; ameliorate the effects of turbulence: reduce shed vortices; mitigate the effects of system failures; eliminate stalls; and compensate for crosswinds. This concept offers the potential for increasing electric airplane efficiency and performance, enhancing Short Takeoff and Landing (STOL) capabilities, improving passenger comfort, and reducing the structural stress and cost of aircraft. | ||||||
| 100 | Aircraft and missile afterbody flow control device and method of controlling flow | US13457686 | 2012-04-27 | US09637223B1 | 2017-05-02 | Jack DiCocco; Troy Prince; Mehul Patel; Tsun Ming Terry Ng |
| An afterbody flow control system is used for aircraft or missile flow control to provide enhanced maneuverability and stabilization. A method of operating the flow control system is also described. The missile or aircraft comprises an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor. | ||||||
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