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公开(公告)号：US6073889A
公开(公告)日：2000-06-13
申请号：US173922
申请日：1998-10-16
摘要： A sealing device (20) for an airplane (22). The airplane having a wing (24) and a first engine nacelle (26) attached to the wing. The wing having a wing root, a wing tip, a leading edge, a trailing edge and at least a first flap (30b) operatively connected to the leading edge. The flap being actuatable between a retracted position and an extended position. The flap in the extended position defining a gap between the flap and engine nacelle. The sealing device includes a body attached to the engine nacelle. The body having a forward portion (54), a center portion (56) and an aft portion (58). The body being positioned on the engine nacelle to contact the flap when the flap is in the extended position and forming a seal between the flap and nacelle to improve aerodynamic efficiency of the wing. The seal is formed by the flap being nested within the center portion of the body when the flap is in the extended position. The seal contours airflow along a spanwise direction defined by an axis extending between the wing root and tip to improve aerodynamic efficiency of the wing.
摘要翻译： 一种用于飞机（22）的密封装置（20）。 具有机翼（24）和附接到机翼的第一发动机机舱（26）的飞机。 机翼具有翼根，翼尖，前缘，后缘和至少第一翼片（30b），其可操作地连接到前缘。 翼片可在缩回位置和伸出位置之间起动。 延伸位置处的翼片限定翼片和发动机舱之间的间隙。 密封装置包括附接到发动机舱的主体。 主体具有前部（54），中心部分（56）和后部（58）。 当皮瓣处于伸展位置时，身体被定位在发动机舱上以接触皮瓣，并在皮瓣和机舱之间形成密封，以提高机翼的空气动力学效率。 当翼片处于伸展位置时，该密封件由该片状物嵌套在该身体的中心部分内而形成。 密封件沿着翼展方向的气流沿由翼根和尖端之间延伸的轴限定，以提高机翼的空气动力学效率。
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公开(公告)号：US06845944B2
公开(公告)日：2005-01-25
申请号：US10411682
申请日：2003-04-11
申请人： C. Byram Bays-Muchmore , Todd B. Brouwer , Malcolm S. Bryant , Warren D. Burggraf , Daniel S. Little , Douglas G. Miller , Stanley E. Tolzmann , Martin M. Withington , Thomas A. Zierten
发明人： C. Byram Bays-Muchmore , Todd B. Brouwer , Malcolm S. Bryant , Warren D. Burggraf , Daniel S. Little , Douglas G. Miller , Stanley E. Tolzmann , Martin M. Withington , Thomas A. Zierten
IPC分类号： B64C25/00
CPC分类号： B64C25/00 , B64C2025/005
摘要： Multi-positional tail skid assemblies and methods for their use. In one embodiment, a multi-positional tail skid assembly includes a skid member and a skid deployment system operably connected to the skid member. The skid member can include a first portion attachable to an aft portion of a fuselage and a second portion movable relative to the aft portion of the fuselage. The second portion can support a skid surface configured to contact a surface of a runway. The skid deployment system can be configured to move the skid surface between first and second positions. When the skid surface is in the first position, the skid surface is closer to the aft portion of the fuselage than when the skid surface is in the second position.
摘要翻译： 多位置的防滑装配及其使用方法。 在一个实施例中，多位置的滑行组件包括滑动构件和可操作地连接到滑动构件的防滑部署系统。 防滑构件可以包括可附接到机身的后部的第一部分和可相对于机身的后部部分移动的第二部分。 第二部分可以支撑配置成接触跑道表面的滑动表面。 防滑部署系统可以被配置为在第一和第二位置之间移动防滑表面。 当滑动表面处于第一位置时，与滑动表面处于第二位置相比，滑动表面更靠近机身的后部。
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公开(公告)号：US4540143A
公开(公告)日：1985-09-10
申请号：US520826
申请日：1983-08-04
申请人： Timothy Wang , Thomas A. Zierten
发明人： Timothy Wang , Thomas A. Zierten
CPC分类号： B64C7/02 , B64C23/06 , B64D29/02 , Y02T50/162
摘要： In a wing and nacelle combination, where the nacelle is positioned below and forwardly of the wing leading edge, a wake control device to control a turbulent wake which is formed at the upper forward lip portion of the nacelle. This wake control device comprises a forward vortex generating portion to create a vortex which travels over the leading edge of the wing, and also a fence located at the middle third of the nacelle to control boundary layer air and thus properly locate the wake control vortex.
摘要翻译： 在机翼和机舱组合中，其中机舱位于机翼前缘的下方和前方，具有用于控制形成在机舱的上部前唇部分处的湍流尾迹的尾流控制装置。 该尾流控制装置包括前向涡流产生部分，以产生在机翼的前缘上行进的涡流，以及位于机舱中间三分之一处的挡板，以控制边界层空气，从而适当地定位尾流控制涡流。
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公开(公告)号：US5749546A
公开(公告)日：1998-05-12
申请号：US501246
申请日：1995-07-10
CPC分类号： B64C3/50 , B64C23/06 , B64C7/00 , Y02T50/145 , Y02T50/162
摘要： A method and apparatus for reducing noise produced by the airframe of an airplane in flight. The present invention provides a smooth, continuous, arcuate surface, such as a rounded edge cap, for the lateral surface of any airplane flap exposed to fluid having relative motion with respect to the airplane. Tests indicate that a rounded flap edge cap made in accordance with the present invention is effective in attenuating noise levels in the middle and high frequency range, i.e., between about 500 to about 10000 Hz.
摘要翻译： 一种降低飞机机身产生噪音的方法和装置。 本发明提供了一种平滑，连续的弧形表面，例如圆形边缘帽，用于任何暴露于相对于飞机具有相对运动的流体的飞行器翼片的侧表面。 测试表明，根据本发明制成的圆形翼片边缘帽在中和高频范围内即约500至约10000Hz之间有效衰减噪声水平。
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