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91. 发明授权

US4995575A Wing trailing edge flap mechanism 失效
标题翻译：翼缘翼缘机构
公开(公告)号：US4995575A
公开(公告)日：1991-02-26
申请号：US365994
申请日：1989-06-14
申请人： Martin F. Stephenson
发明人： Martin F. Stephenson
IPC分类号： B64C9/16
CPC分类号： B64C9/16 , Y02T50/32
摘要： Actuation and support mechanisms for wing trailing edge flap systems wherein each flap system has a streamwise or chordwise pair of geometrically similar flap support assemblies. Each of the flap support assemblies has a chordwise aligned cantilever support beam fixedly attached to wing structure. The beam incorporates multiple cam tracks for providing guidance and support to a movable dual carriage assembly upon which a wing trailing edge flap assembly is mounted. The dual carriage assembly comprises a fore-carriage which is articulatably connected to an aft-carriage. The wing trailing edge flap assembly is mounted upon the aft-carriage. Both the fore-carriage and the aft-carriage are individually supported by rollers constantly engaging a separate cam track for each of said carriages. For actuation of the dual carriage assembly and the wing trailing edge assembly mounted thereon, a ball screw drive mechanism is incorporated between the cantilever beam and the dual carriage assembly.
摘要翻译：用于翼缘后缘襟翼系统的致动和支撑机构，其中每个翼片系统具有一个几何相似翼片支撑组件的流向或弦向对。每个翼片支撑组件具有固定地附接到机翼结构的弦向对齐的悬臂支撑梁。梁包括多个凸轮轨道，用于向可移动的双支架组件提供引导和支撑，在该可移动双支架组件上安装有机翼后缘翼片组件。双托架组件包括可滑动地连接到后托架的前托架。机翼后缘翼片组件安装在后托架上。前托架和后托架都分别由用于每个所述托架的单独的凸轮轨道接合的辊单独支撑。为了致动双滑架组件和安装在其上的机翼后缘组件，滚珠丝杠驱动机构结合在悬臂梁和双滑架组件之间。

92. 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。

93. 发明授权

US4718619A Manoeuverable supercritical wing section 失效
标题翻译：可操纵的超临界翼段
公开(公告)号：US4718619A
公开(公告)日：1988-01-12
申请号：US652445
申请日：1984-07-20
申请人： Patrick R. Ashill , Donald Pierce , Desmond A. Treadgold , John L. Fulker
发明人： Patrick R. Ashill , Donald Pierce , Desmond A. Treadgold , John L. Fulker
IPC分类号： B64C3/14 , B64C3/48 , B64C9/02
CPC分类号： B64C3/48 , B64C3/14 , B64C9/02 , B64C2003/149 , Y02T50/12 , Y02T50/145 , Y02T50/32
摘要： The manoeuverable supercritical wing section with a t/c ratio of 8-9%, flexible at 70%-80% chord by means of a flap to induce expansion thereover, and perhaps having a minimum curvature region on the upper surface just ahead of the flexing region.
摘要翻译：具有at / c比为8-9％的可操纵的超临界翼段，通过翼片灵活地达到70％-80％的弦，以在其上引起膨胀，并且可能在刚好在弯曲之前的上表面具有最小曲率区域地区。

94. 发明授权

US4702442A Aircraft trailing edge flap apparatus 失效
标题翻译：飞机后缘翼装置
公开(公告)号：US4702442A
公开(公告)日：1987-10-27
申请号：US679203
申请日：1984-12-06
申请人： Richard H. Weiland , William L. Franklin
发明人： Richard H. Weiland , William L. Franklin
IPC分类号： B64C9/16 , B64C9/20
CPC分类号： B64C9/16 , B64C9/20 , Y02T50/32 , Y02T50/44
摘要： An aircraft trailing edge flap assembly including a main flap and an aft flap are repositioned by a dual arm rotary actuator. One arm of the rotary actuator repositions the main flap by driving a carriage assembly along a linear track. The other arm of the rotary actuator repositions the aft flap by driving a bell crank assembly which is operatively connected to an aft flap support member extending downward from the aft flap. The aft flap support member is operatively connected to a main flap support member which extends downwardly and rearwardly from the rear portion of the main flap to operatively connect with a mounting member extending downwardly and rearwardly from the track so that the track mounting member supports the majority of aerodynamic load forces applied to the flap assembly. Both arms of the rotary actuator rotate together through a predetermined arc so that the aft flap and main flap remain in a nested configuration. The main flap rotary arm engages a stop pin resulting in the aft flap rotary arm continuing to rotate the aft flap an additional amount relative to the main flap.

95. 发明授权

US4645144A Method and apparatus for effecting fine control of aircraft velocity 失效
标题翻译：实现飞机速度精细控制的方法和装置
公开(公告)号：US4645144A
公开(公告)日：1987-02-24
申请号：US808544
申请日：1985-12-13
申请人： Joseph E. Zupanick
发明人： Joseph E. Zupanick
IPC分类号： B64C9/32
CPC分类号： B64C9/32 , B64C9/326 , Y02T50/32
摘要： In order to achieve fine control of the velocity of an aircraft flying a predetermined flight path at a predetermined nominal speed in the presence of such perturbations as wind gusts, a low inertia, fast acting device is extended or deployed into the aircraft dragstream and is rapidly position-modulated in response to sensed acceleration/deceleration to instanteneously slightly alter the total system drag to an amount which causes the aircraft to maintain the predetermined velocity. Among the exemplary alternative low inertia devices disclosed are: fuselage and wing mounted flaps which are rapidly more or less extended, a trailing cable which is rapidly reeled in or out, and a trailing inflatable member whose degree of inflation is rapidly changed, all in response to sensed acceleration/deceleration from an on-board system.
摘要翻译：为了在存在诸如阵风等扰动的情况下以预定的标称速度实现飞行预定飞行路径的飞行器的速度的精细控制，将低惯性快速作用的装置延伸或部署到飞行器的牵引流中并迅速地响应于感测到的加速/减速而进行位置调制以便将总系统阻力瞬时稍微改变为导致飞行器保持预定速度的量。所公开的示例性的替代性低惯量装置是：机身和机翼安装的翼片快速或多或少地延伸，快速卷入或离开的拖缆，以及充气程度迅速改变的拖尾充气构件，全部作为响应以检测车载系统的加速/减速。

96. 发明授权

US4605187A Wing flap mechanism 失效
标题翻译：翼片机构
公开(公告)号：US4605187A
公开(公告)日：1986-08-12
申请号：US588161
申请日：1984-03-09
申请人： Martin F. Stephenson
发明人： Martin F. Stephenson
IPC分类号： B64C9/04 , B64C9/16 , B64C9/18
CPC分类号： B64C9/04 , B64C9/16 , B64C9/18 , Y02T50/32 , Y02T50/44
摘要： A carrier unit for chordwise extending and rotatably positioning an auxiliary airfoil mounted adjacent to the trailing edge of a relatively fixed main airfoil of an airplane. When the auxiliary airfoil is in a fully retracted and stowed position, the actuation and positioning linkage mechanism of the carrier unit is completely housed within the combined auxiliary and main airfoil envelope with no external protrusions or fairings. For auxiliary airfoil extension, to increase the overall chord plane by approximately eight percent, a first set of four-bar linkages is utilized comprising: a beam member supported at a forward portion by a pair of approximately parallel links pivoted to wing structure and swingable chordwise in a generally parallel relationship for translatably shifting the auxiliary airfoil which is pivoted to a rearward portion of the beam member. For changing the auxiliary airfoil angle-of-incidence relative to the main airfoil, one or more sets of four-bar linkages are integrated with the first set for a unified rotation programming and extension drive that functions to produce an aerodynamic slot opening when the auxiliary airfoil is extended to takeoff and landing positions whereat it is deflected up to approximately forty degrees relative to the main airfoil reference chord plane. For an aerodynamic braking action during landing roll-out, the geometrical relationship of the sets of four-bar linkages functions to deflect the auxiliary airfoil chord plane greater than forty degrees, to approximately ninety degrees or more relative to the main airfoil reference chord plane.
摘要翻译：一种用于弦线延伸并可旋转地定位邻近飞机的相对固定的主翼面的后缘的辅助翼型的载体单元。当辅助翼型件处于完全收起和收起位置时，承载单元的致动和定位联动机构完全容纳在组合的辅助和主翼型外壳内，没有外部突起或整流罩。对于辅助翼型延伸，为了将整个弦平面增加大约8％，使用第一组四杆连杆，其包括：梁构件，其通过一对大致平行的连接件支撑在前部，枢转到机翼结构和可摆动的弦在大致平行的关系中，可平移地移动辅助翼型件，该辅助翼型件枢转到梁构件的后部。为了改变相对于主翼面的辅助翼型角入射角，一组或多组四杆连杆与第一组一体化，用于统一的旋转编程和延伸驱动，其用于当辅助翼型辅助翼机翼延伸到起飞和着陆位置，在那里它相对于主翼型参考弦平面偏转到大约四十度。对于在着陆推出期间的空气动力学制动作用，四杆连杆组的几何关系用于使辅助翼型翼弦平面相对于主翼型参考弦平面大于四十度，大约九十度或更大。

97. 发明授权

US4585192A Leading edge arrangements for aircraft wings 失效
标题翻译：飞机机翼的前沿安排
公开(公告)号：US4585192A
公开(公告)日：1986-04-29
申请号：US595358
申请日：1984-03-30
申请人： John B. Clifford-Jones
发明人： John B. Clifford-Jones
IPC分类号： B64C3/50 , B64C9/24
CPC分类号： B64C9/24 , B64C3/50 , Y02T50/145 , Y02T50/32
摘要： A leading edge arrangement includes a fixed wing portion 10, a slat member 18 slidably mounted with respect thereto by an arm 14. The arm 14 is provided with an internal trackway 15 and external cam surfaces 16' and 16", the trackway co-operating with roller bearings 12 on the fixed wing portion and the cam surfaces co-operating with respective roller bearings 13' and 13" on the fixed wing portion. The profiles of the trackway and cam surface are selected so that from a stowed cruise condition the slat member initially moves to a take-off setting along a path in which the ratio of downward deflection to extension movement is low, and subsequently moves to a landing setting along a path in which the said ratio is high. A modification is also described in which the rearward heel of the slat member which is exposed when the slat is extended is formed of a flexible panel portion, so that it may blend smoothly with the remainder of the rearward surface of the slat member.
摘要翻译：前缘布置包括固定翼部分10，通过臂14相对于其可滑动地安装的板条构件18.臂14设置有内部轨道15和外部凸轮表面16'和16“ 在固定翼部分上的滚子轴承12和与固定翼部分上的相应滚子轴承13'和13“配合的凸轮表面进行操作。选择轨道和凸轮表面的轮廓，使得从收起的巡航状态开始，板条构件最初沿向下偏转与延伸运动的比率低的路径移动到起飞设置，并且随后移动到着陆沿着所述比率高的路径设置。还描述了一种修改，其中当板条延伸时露出的板条构件的后跟由柔性板部分形成，使得其可以平滑地与板条构件的后表面的其余部分共混。

98. 发明授权

US4575030A Laminar flow control airfoil 失效
标题翻译：层流控制翼型
公开(公告)号：US4575030A
公开(公告)日：1986-03-11
申请号：US416923
申请日：1982-09-13
申请人： Louis B. Gratzer
发明人： Louis B. Gratzer
IPC分类号： B64C9/14 , B64C21/06
CPC分类号： B64C21/06 , B64C9/146 , B64C2230/04 , B64C2230/06 , B64C2230/22 , Y02T50/166 , Y02T50/32
摘要： A laminar flow control aircraft wing combines suction surfaces and slots in its leading and trailing edge regions, with natural laminar flow over its main box region to achieve laminar boundary layer flow over a majority of the wing surface area. The wing includes a leading edge flap that is used to protect the leading edge region of the wing from insect accumulation and surface erosion caused by the impact of dirt, rain, or other airborne materials when the leading edge flap is deployed in a low-speed position. At high aircraft speeds, the leading edge flap is stored in the surface of the leading edge region of the wing and forms part of the suction system for that area of the wing. The wing also includes a flexible trailing edge suction surface spoiler system that allows the spoilers to bend downwardly when the trailing edge flap is deployed into a low-speed position.
摘要翻译：层流控制飞机机翼将其前缘和后缘区域中的吸力表面和狭缝组合，在其主箱区域上具有天然层流，以实现多数机翼表面区域上的层流边界层流动。机翼包括一个前缘翼片，用于保护机翼的前缘区域免受由于污垢，雨水或其他空气传播材料的影响而引起的昆虫积聚和表面侵蚀，当前缘翼片以低速位置。在高飞机速度下，前缘翼片被存储在机翼的前缘区域的表面中，并且形成机翼区域的抽吸系统的一部分。机翼还包括一个柔性的后缘吸力表面扰流器系统，当后缘挡板部署到低速位置时，它能够使扰流板向下弯曲。

99. 发明授权

US4566657A Span loaded flying wing control 失效
标题翻译：跨度装载飞翼控制
公开(公告)号：US4566657A
公开(公告)日：1986-01-28
申请号：US211517
申请日：1980-12-01
申请人： Harlow B. Grow
发明人： Harlow B. Grow
IPC分类号： B64C9/20 , B64C9/32 , B64C9/00
CPC分类号： B64C9/20 , B64C9/32 , B64C9/323 , Y02T50/32
摘要： A flying wing aircraft control for angle of attack and direction thereof, comprising retractile controlling surfaces rearward of the center of lift and along the trailing edges and extensible over the top and bottom cambers of the wing in spaced relation to the trailing portions thereof and with variable angular dispositions with respect to air flow over the cambers so as to establish the desired moment arm with respect to the lift center of the flying wing to control the same into and out of a nose-up attitude with respect to the line of flight and with respect to direction, as required.
摘要翻译：一种飞翼飞机控制攻角及其方向，包括在升降中心后方并沿着后缘的伸缩控制表面，并与机翼尾部的后部相隔一定距离可伸展，相对于弧形空气流动的角度配置，以便相对于飞翼的电梯中心建立所需的力矩臂，以将其相对于飞行线和与根据需要尊重方向。

100. 发明授权

US4553721A Spoiler device for attachment to a leading edge slat 失效
标题翻译：用于连接到前缘板条的扰流装置
公开(公告)号：US4553721A
公开(公告)日：1985-11-19
申请号：US520796
申请日：1983-08-05
申请人： Bernard J. Jorgensen
发明人： Bernard J. Jorgensen
IPC分类号： B64C9/22 , B64C9/32
CPC分类号： B64C9/32 , B64C9/22 , B64C9/323 , Y02T50/32
摘要： The invention is a spoiler device for an aircraft having a leading edge slat (50) mounted on at least a portion of the leading edge of the wing of the aircraft. A rear portion (52) of the leading edge slat (50) is rotatably mounted thereto and movable from a retracted position to an extended position (52') so as to act as a spoiler. A latch mechanism comprising links 56, 60, 68 and spring member (76) which yieldably hold the rear portion (52) of the slat (50) in the retracted position. An actuator (80) is provided which is mounted to the wing and which is in detachable contact with the latch mechanism of the slat (50). Upon actuation the rear portion (52) is extended and is returned to the retracted portion by the spring member (76). The actuator (80) can be either mechanical, pneumatic, hydraulic or electrical.
摘要翻译：本发明是一种用于飞行器的扰流装置，其具有安装在飞行器机翼的前缘的至少一部分上的前缘板条（50）。前缘板条（50）的后部（52）可旋转地安装在其上并可从缩回位置移动到延伸位置（52'），以作为扰流板。包括连杆56,60,68和弹簧构件（76）的闩锁机构，其可收缩地将缝翼（50）的后部（52）保持在缩回位置。提供一个致动器（80），其被安装到机翼上，并且可与板条（50）的闩锁机构分离接触。在启动时，后部（52）延伸并且通过弹簧构件（76）返回到缩回部分。致动器（80）可以是机械的，气动的，液压的或电的。

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