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41. 发明授权

US5114102A Boundary layer control 失效
标题翻译：边界层控制
公开(公告)号：US5114102A
公开(公告)日：1992-05-19
申请号：US417910
申请日：1989-10-06
申请人： Timothy Wang
发明人： Timothy Wang
IPC分类号： B64C21/04
CPC分类号： B64C21/04 , B64C2230/04 , B64C2230/16 , Y02T50/166
摘要： Methods of and apparatus for controlling the separation of a boundary layer from a surface on which an adverse pressure gradient exists. A streamwise jet of fluid is so discharged onto the surface at a location adjacent the juncture between the surface and an adjoining structure as to energize the boundary layer and thereby delay the separation of the boundary layer from the airfoil in the vicinity of that juncture.
摘要翻译：用于控制边界层与存在不利压力梯度的表面分离的方法和装置。流体流的流体在与表面和相邻结构之间的接合处相邻的位置处被排出到表面上，以激励边界层，从而延迟边界层在该接合处附近与翼型的分离。

42. 发明授权

US4976349A Aerofoil/hydrofoil 失效
标题翻译：机翼/水翼
公开(公告)号：US4976349A
公开(公告)日：1990-12-11
申请号：US201177
申请日：1988-06-02
申请人： Richard C. Adkins
发明人： Richard C. Adkins
IPC分类号： B64C9/38 , B64C21/04
CPC分类号： B64C21/04 , B64C9/38 , B64C2230/04 , B64C2230/06 , B64C2230/16 , Y02T50/166
摘要： An aerofoil or hydrofoil (1) has a vessel (2) for providing a high velocity jet of fluid directed from a nozzle (3) in a direction having a component of velocity in the same direction as the required direction of lift (L). The aerofoil or hydrofoil (1) also has a curved surface (5) convex on the side of the aerofoil or hydrofoil which is in the direction of the required lift, and which serves to direct the velocity of the jet in a direction which is substantially opposite to the direction of the required lift or thrust force, the primary jet being directed over the convex surface for attachment thereto; and a duct formed over a rear part of the convex surface remote from the nozzle, whereby the primary jet of fluid flowing over and attached to the convex surface causes an enhanced flow through the duct, the duct being directed at least at its exit end in a direction so that the flow therethrough has a component of velocity opposite that of the required direction of lift.

43. 发明授权

US4895323A Rag control for powered lift aircraft 失效
标题翻译：动力升降机的抹布控制
公开(公告)号：US4895323A
公开(公告)日：1990-01-23
申请号：US536739
申请日：1983-09-28
申请人： Fred W. May
发明人： Fred W. May
IPC分类号： B64C9/24 , B64C21/04 , B64C23/00
CPC分类号： B64C9/24 , B64C21/04 , B64C23/00 , B64C2230/04 , B64C2230/06 , B64C2230/16 , B64C2230/20 , Y02T50/166 , Y02T50/32
摘要： A wing (2) has a trailing edge at which jet flow is deflected downwardly to provide lift. A retractable member (4, 4') has a sharp forward edge (6, 6'). When deployed, member (4, 4') extends along at least a portion of the span (preferably substantially the entire span) of the wing (2) at the leading edge of wing (2). Member (4, 4') projects forwardly and upwardly from wing (2). Member (4, 4') causes flow around wing (2) rearwardly of itself to separate from wing (2) to reduce suction and leading edge thrust. Preferably, reattachment of flow is induced at a location spaced rearwardly from member (4, 4'). A jet of high velocity gas is blown along wing (2) in a generally spanwise direction. This induces reattachment to maintain trailing edge thrust so that jet deflection at the trailing edge will efficiently provide lift during a short distance landing.
摘要翻译：翼（2）具有后缘，喷射流向下偏转以提供升力。可伸缩构件（4,4'）具有尖锐的前缘（6,6'）。当展开时，构件（4,4'）沿着机翼（2）的前缘处的翼（2）的跨度（优选地基本上整个跨度）的至少一部分延伸。会员（4,4'）从翼（2）向前和向上突出。会员（4,4'）会使自身后方的机翼（2）流向与机翼（2）分离，以减少吸力和前缘推力。优选地，在与构件（4,4'）向后间隔开的位置处引起流动的重新附接。沿翼（2）沿大致翼展方向吹送高速气体喷射。这导致重新附接以保持后缘推力，使得后缘处的喷射偏转将在短距离着陆期间有效地提供升力。

44. 发明授权

US3971534A Method of and apparatus for controlling flow attachment to the wing and flap surfaces of an upper surface blowing type aircraft 失效
标题翻译：用于控制与上表面吹风式飞行器的机翼和翼片表面的流动连接的方法和装置
公开(公告)号：US3971534A
公开(公告)日：1976-07-27
申请号：US429658
申请日：1973-12-28
申请人： Charles A. Grotz
发明人： Charles A. Grotz
IPC分类号： B64C9/20 , B64C21/00
CPC分类号： B64C9/20 , B64C2230/04 , B64C2230/06 , B64C2230/16 , Y02T50/166
摘要： A method of controlling flow attachment to the wing and flap surfaces of an upper surface blowing type aircraft by horizontally controlling the divergence of the jet exhaust of the aircraft engines to control the vertical thickness of the exhaust is disclosed. In addition to controlling the thickness of the exhaust, control of the divergent exhaust also provides control over the outward velocity component of the exhaust which further provides control over flow attachment by controlling the flow of ambient air under the jet exhaust. In one form, the apparatus of the invention comprises one or more side panels, located at the end of the engine exhaust nozzle, adjacent to the surface of the wing. When the panels are moved outwardly, openings are formed which allow the exhaust to horizontally diverge. When the panels are moved inwardly, the openings are closed and the exhaust is no longer diverted and thinned. In an alternate form, the apparatus of the invention comprises movable vanes mounted on the wing, slightly rearwardly of the end of the exhaust nozzle. The vanes are movable so as to either divert the exhaust outwardly and thin it, or to be aligned with the exhaust stream to have little or no effect on the exhaust whereby it remains unthinned.
摘要翻译：公开了一种通过水平地控制飞机发动机的喷气排气的散度以控制排气的垂直厚度来控制与上表面吹风式飞行器的机翼和翼片表面的连接的方法。除了控制排气的厚度之外，扩散排气的控制还提供对排气的向外速度分量的控制，其进一步通过控制喷射排气下的环境空气的流动来进一步提供对流动附着的控制。在一种形式中，本发明的装置包括位于发动机排气喷嘴的端部处的与翼的表面相邻的一个或多个侧板。当面板向外移动时，形成允许排气水平分开的开口。当面板向内移动时，开口关闭，排气不再转向和变薄。在替代形式中，本发明的装置包括安装在机翼上的可移动叶片，稍稍在排气喷嘴端部的后方。叶片是可移动的，以便将排气向外转移并使其变薄，或者与排气流对齐，对排气具有很小的或不起作用，从而使废气保持不变。

45. 发明授权

US3355125A Flap systems for aircraft 失效
标题翻译：飞机翼片系统
公开(公告)号：US3355125A
公开(公告)日：1967-11-28
申请号：US49923965
申请日：1965-10-21
申请人： POWER JETS RES & DEV LTD
发明人： RODNEY ALLCOCK ALASTAIR WILLIA
IPC分类号： B64C21/02 , B64C21/04 , B64C23/00
CPC分类号： B64C21/04 , B64C21/02 , B64C23/005 , B64C2230/04 , B64C2230/16 , Y02T50/166
摘要： 1,083,267. Aircraft trailing edge flaps. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. Dec. 13, 1965 [Dec. 11, 1964], No. 50618/64. Heading B7G. [Also in Division F2] An aircraft wing trailing edge blown flap has a discontinuity in its surface to promote separation, and means are provided for shielding the discontinuity from the flow over the flap. The flap 2 described may have in its nose a notch 5 which is covered by the wing shroud until the flap is lowered to more than, say, 60 degrees; or a passage (6, Fig. 3, not shown), leading from the nose to the lower surface, which is normally closed by the wing shroud; or a step (9, Fig. 4, not shown) below which the nose is cut away to form a passage through which air can flow from the lower to the upper surface when the flap is lowered sufficiently; or a spoiler plate may be pivotally mounted on the flap nose and spring biased to extend away from the flap surface when it is not constrained by the shroud. The discontinuity is intended to produce an increase in drag and reduction in lift after landing or aborted take-off. The aircraft may be a jet flap aircraft.

46. 发明授权

US3298636A Airfoil 失效
标题翻译：翼型
公开(公告)号：US3298636A
公开(公告)日：1967-01-17
申请号：US42585365
申请日：1965-01-15
申请人： ERIC ARNHOLDT
发明人： ERIC ARNHOLDT
IPC分类号： B64C21/02 , B64C23/00
CPC分类号： B64C23/005 , B64C21/02 , B64C2230/04 , B64C2230/16 , B64C2230/20 , Y02T50/166

47. 发明授权

US3262659A Thrust control apparatus 失效
标题翻译：推力控制装置
公开(公告)号：US3262659A
公开(公告)日：1966-07-26
申请号：US36406764
申请日：1964-04-29
申请人： COPELAND JOHN E
发明人： COPELAND JOHN E
IPC分类号： B64C21/04 , B64D35/00
CPC分类号： B64C21/04 , B64C2230/04 , B64C2230/06 , B64C2230/16 , B64D35/00 , Y02T50/166

48. 发明授权

US3240445A Ventilated aircraft elements 失效
标题翻译：通风飞机元件
公开(公告)号：US3240445A
公开(公告)日：1966-03-15
申请号：US17666862
申请日：1962-03-01
申请人： ELLZEY FLOYD P
发明人： ELLZEY FLOYD P
IPC分类号： B64C21/04
CPC分类号： B64C21/04 , B64C2230/04 , B64C2230/06 , B64C2230/16 , Y02T50/166

49. 发明授权

US3005496A Airfoil boundary layer control means 失效
标题翻译：翼型边界层控制装置
公开(公告)号：US3005496A
公开(公告)日：1961-10-24
申请号：US83562759
申请日：1959-08-24
申请人： HILLER AIRCRAFT CORP
发明人： NICHOLS JOHN B
IPC分类号： B64C21/04 , B64C27/18 , B64C27/46
CPC分类号： B64C27/463 , B64C21/04 , B64C27/18 , B64C2230/04 , B64C2230/06 , B64C2230/16 , B64C2230/28 , Y02T50/166
摘要： 898,203. Boundary layer control on helicopter blades. HILLER AIRCRAFT CORPORATION. Aug. 22, 1960 [Aug. 24, 1959], No. 28934/60. Class 4. A helicopter rotor blade, adjustably mounted for pitch change, has boundary layer control means including operating means therefor comprising a first member fixed on the blade, and a second member movable on the blade under the control of restraining means operative in response to conditions of flight independent of the angle of attack of the blade, relative movement between the first and second members operating the boundary layer control means. Fig. 2 shows a rotor blade tip, a hollow spar 3 receiving compressed air through the hollow rotor shaft from a compressor or gas turbine engine, and communicating through valves (not shown) with ducts 9 leading to a trailing edge slot 10. The valves are controlled by a rod 12 secured to an arm 13 on which are a small aerofoil 14 and a mass balance 15. The aerofoil 14 keeps the arm 13 aligned with the relative wind direction W, and when the angle of attack of the retreating blade increases, rotation of the blade relatively to rod 12 opens the valve so that an air jet 10a is discharged from slot 10, to increase the lift of the blade and delay the onset of stall by energising the boundary layer. In an alternative, the rod 13 has two masses, one at each end so that the rod remains parallel to the tip path plane by gyroscopic effect as the rotor rotates. In either embodiment, power consumption is minimized by discharging compressed air only when needed. The compressor may be driven from the gearbox of an engine driving the rotor shaft.

50. 发明授权

US2756008A Jet propelled aircraft with wingmounted jet engines 失效
标题翻译：喷气式飞机搭载翼式喷气发动机
公开(公告)号：US2756008A
公开(公告)日：1956-07-24
申请号：US42153954
申请日：1954-04-07
申请人： POWER JETS RES & DEV LTD
发明人： MACAULAY DAVIDSON IVOR
IPC分类号： B64C3/38 , B64C23/00 , B64D27/02 , B64D27/18 , B64D39/00 , F02K1/00 , F02K1/52
CPC分类号： F02K1/52 , B64C3/385 , B64C23/00 , B64C2230/04 , B64C2230/16 , B64D27/02 , B64D27/18 , F02K1/006 , Y02T50/166

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