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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。

2. 发明申请

WO2007062005A1 AIRCRAFT TRAILING EDGE DEVICES, INCLUDING DEVICES WITH NON-PARALLEL MOTION PATHS, AND ASSOCIATED METHODS 审中-公开
标题翻译：飞机牵引装置，包括具有非平行运动装置的装置及相关方法
公开(公告)号：WO2007062005A1
公开(公告)日：2007-05-31
申请号：PCT/US2006/045001
申请日：2006-11-20
申请人： THE BOEING COMPANY , LACY, Douglas, S. , BEYER, Kevin, W. , BROWN, Stephen, T. , DEES, Paul, W. , HUYNH, Neal, V. , KORDEL, Jan, A. , PROW, Clayton, A. , SAKURAI, Seiya
发明人： LACY, Douglas, S. , BEYER, Kevin, W. , BROWN, Stephen, T. , DEES, Paul, W. , HUYNH, Neal, V. , KORDEL, Jan, A. , PROW, Clayton, A. , SAKURAI, Seiya
IPC分类号： B64C9/16
CPC分类号： B64C9/16 , B64C2009/143
摘要： Aircraft trailing edge devices (230) , including devices with non-parallel motion paths (241, 242, 243) , and associated methods are disclosed. A device in accordance with one embodiment includes a wing (220) and an inboard trailing edge (231) device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path (241) . An outboard trailing edge (232) device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path (242) that is non-parallel to the first motion path. An intermediate trailing edge device (260) can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path (243) that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.
摘要翻译：公开了包括具有非平行运动路径（241,242,243）的装置和相关方法的飞机后缘装置（230）。根据一个实施例的装置包括机翼（220）和联接到机翼的内侧后缘（231）装置，并且可沿着第一运动路径（241）相对于机翼在第一收起位置和第一展开位置之间移动，。外侧后缘（232）装置可以联接到内侧后缘装置的翼外侧，并且可以沿着不平行于第一运动路径的第二运动路径（242）相对于机翼移动。中间后缘装置（260）可以联接在内侧和外侧后缘装置之间，并且可以沿着不平行于第一和第二运动路径的第三运动路径（243）移动。每个后缘装置可以在移动到它们各自的展开位置时相对于机翼打开间隙。

3. 发明申请

WO2007061641A2 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：WO2007061641A2
公开(公告)日：2007-05-31
申请号：PCT/US2006/043672
申请日：2006-11-10
申请人： THE BOEING COMPANY , 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 and method for alleviating the lift-inducing structural-bending force (i.e., moment) experienced by each of the wings of an aircraft. The apparatus includes a deployable panel and an actuator mounted in each wing. The actuators are responsive to a command generator. 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, and more preferably at least in part outboardly of the outboard-most trailing edge device 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：一种用于减轻由飞行器的每个翼经历的升力诱导结构弯曲力（即力矩）的机翼加载减轻系统和方法。该装置包括可展开的面板和安装在每个翼中的致动器。致动器响应命令发生器。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，并且更优选地至少部分地在机翼中的最外侧后缘装置的外侧。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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