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1. 发明申请

WO2007061641A3 WING LOAD ALLEVIATION APPARATUS AND METHOD 审中-公开
标题翻译： WING LOAD ALLEVITING设备和方法
公开(公告)号：WO2007061641A3
公开(公告)日：2007-07-05
申请号：PCT/US2006043672
申请日：2006-11-10
申请人： BOEING CO , DEES PAUL W , SANKRITHI MITHRA
发明人： DEES PAUL W , SANKRITHI MITHRA
IPC分类号： B64C13/16 , G05D1/02
CPC分类号： B64C13/16 , B64C9/323 , Y02T50/44
摘要： A wing load alleviation system (10) and method for alleviating the lift-inducing structural-bending force (i.e., moment) experienced by each of the wings (12) of an aircraft (14). The apparatus includes a deployable panel and an actuator mounted in each wing. The actuators are responsive to a command generator (15B). The actuator is mounted inside the wing and the panel is mounted flush with an outer surface of its respective wing. Each panel can be moved between a retracted position, where it has no affect on airflow moving over the wing, to a deployed position in which it deflects air off of the wing. Each panel is preferably located at a span-wise location at least about halfway along the length of the wing toward the wing tip (16), and more preferably at least in part outboardly of the outboard-most trailing edge device (42) in the wing. The apparatus effectively shifts the lift-inducing structural-bending forces experienced by the wing more inboard towards the fuselage.
摘要翻译：一种用于减轻飞机（14）的每个翼（12）经历的升力诱导结构弯曲力（即，力矩）的机翼加载减轻系统（10）和方法。该装置包括可展开的面板和安装在每个翼中的致动器。致动器响应于命令发生器（15B）。致动器安装在机翼的内部，并且面板与其相应机翼的外表面齐平地安装。每个面板可以在缩回位置之间移动，在缩回位置，其对在机翼上移动的气流没有影响，在其中使空气偏离机翼的展开位置移动。每个面板优选地位于沿着翼的长度的至少大约一半的翼展位置处，朝向翼尖（16），并且更优选地至少部分地位于外侧最后缘装置（42）的外侧翅膀。该装置有效地将机身所经受的升力引起的结构弯曲力更多地转移到机身上。

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