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1. 发明授权

US6098925A Adaptive deployable ramp for suppression of aircraft weapons bay acoustic loads 失效
标题翻译：用于抑制飞机武器舱声学载荷的自适应部署坡道
公开(公告)号：US6098925A
公开(公告)日：2000-08-08
申请号：US371970
申请日：1999-08-10
申请人： Charles Wesley Burdsall, II , John Alan Volk
发明人： Charles Wesley Burdsall, II , John Alan Volk
IPC分类号： B64D1/06
CPC分类号： B64D1/06 , B64C23/06 , Y02T50/162
摘要： An adaptive ramp mechanism for an aircraft having a fuselage which includes a fuselage skin, an interior cavity, a forward end and an aft end, and at least one door attached to the fuselage and moveable between an open position exposing the interior cavity and a closed position enclosing the interior cavity. The ramp mechanism comprises a ramp structure which is attached to the fuselage between the forward end and the interior cavity thereof. The ramp structure is movable between an undeployed position whereat it is substantially continuous with the fuselage skin such that when the door is in the closed position, a free stream of air flowing along the fuselage is attached to the fuselage skin and the door, and undeployed position whereat at least a portion thereof extends angularly relative to the fuselage skin such that when the door is in the open position, the free stream of air is deflected over the interior cavity and reattaches to the fuselage skin between the interior cavity and the aft end of the fuselage.
摘要翻译：一种用于具有机身的飞机的自适应斜坡机构，该机身包括机身皮肤，内部空腔，前端和后端，以及至少一个门，其连接到机身并可在露出内部空腔的打开位置和闭合封闭内腔的位置。斜坡机构包括斜坡结构，该斜坡结构在其前端和内部空腔之间附接到机身。斜坡结构可以在与机身皮肤基本上连续的未展开位置之间移动，使得当门处于关闭位置时，沿着机身流动的空气流自由地附接到机身皮肤和门，并且被拆卸其中至少一部分的至少一部分相对于机身皮肤成角度地延伸，使得当门处于打开位置时，自由空气流在内部空腔中偏转并且重新附接到机身内部空腔和后端之间的皮肤的机身。

2. 发明授权

US6089503A Selectively rotatable and torsionally flexible aerodynamic control apparatus 失效
标题翻译：选择性可旋转和扭转灵活的空气动力学控制装置
公开(公告)号：US6089503A
公开(公告)日：2000-07-18
申请号：US231281
申请日：1999-01-15
申请人： John Alan Volk
发明人： John Alan Volk
IPC分类号： B64C3/38
CPC分类号： B64C3/38
摘要： In accordance with the present invention, there is provided an aerodynamic control system which is attachable to an aircraft body and is operable between enhanced control and radar evasive modes. The aerodynamic control system is provided with an aerodynamic support structure which extends from the aircraft body. The support structure is rotatably attached to the aircraft body about a support structure rotational axis. The support structure has an outboard support and an inboard support which is disposed adjacent the aircraft body. The aerodynamic control system is further provided with an elongate torque member which extends from the aircraft body. The torque member has a torque rotational axis which is co-linear with the support structure rotational axis. The torque member further has an outboard end which is fixedly attached to the outboard support of the support structure. In the normal fight mode the inboard and outboard supports cooperatively rotate in response to rotation of the torque member. In the radar evasive mode the outboard support rotates relative to the inboard support in response to rotation of the torque member, thereby altering the aerodynamic characteristics of the aerodynamic control system for aircraft control.
摘要翻译：根据本发明，提供一种可附接到飞行器主体并且可在增强的控制和雷达回避模式之间操作的空气动力学控制系统。空气动力学控制系统具有从飞行器主体延伸的空气动力学支撑结构。支撑结构围绕支撑结构旋转轴线可旋转地附接到飞行器本体。支撑结构具有外侧支撑件和靠近飞行器主体设置的内侧支撑件。空气动力学控制系统还设置有从飞行器主体延伸的细长扭矩构件。扭矩构件具有与支撑结构旋转轴线共线的转矩旋转轴。扭矩构件还具有固定地附接到支撑结构的外侧支撑件的外侧端部。在正常的打斗模式中，内侧和外侧支撑件响应于扭矩构件的旋转协同地旋转。在雷达回避模式中，响应于扭矩构件的旋转，外侧支撑件相对于内侧支撑件旋转，从而改变用于飞行器控制的空气动力学控制系统的空气动力特性。

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