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公开(公告)号：US20130020432A1
公开(公告)日：2013-01-24
申请号：US13552263
申请日：2012-07-18
摘要： A method for providing a controllable side force to an air vehicle having a vertical stabilizer arrangement includes (a) selectively causing the vertical stabilizer arrangement to generate a first side force in a first side direction to provide the controllable side force, the first side force inducing a corresponding first yaw moment in a first yaw direction; and (b) selectively providing to the air vehicle a second yaw moment in a second yaw direction, the second yaw moment being induced by a force component of an auxiliary force applied to the air vehicle, the force component being in a force direction that is non-parallel with respect to the first side direction and the force component being spaced from a center of gravity of the air vehicle; wherein the second yaw direction is opposed to the first yaw direction. Also disclosed is a corresponding auxiliary yaw generating system.
摘要翻译： 一种用于向具有垂直稳定器装置的机动车辆提供可控侧力的方法包括：（a）选择性地使垂直稳定器装置在第一侧方向上产生第一侧力以提供可控的侧向力，第一侧向力 在第一偏转方向上相应的第一横摆力矩; 以及（b）选择性地向所述空中交通工具提供在第二偏转方向上的第二横摆力矩，所述第二横摆力矩由施加到所述空中车辆的辅助力的力分量感应，所述力分量处于 相对于第一侧方向不平行，并且力分量与空中交通工具的重心间隔开; 其中所述第二偏转方向与所述第一偏转方向相对。 还公开了相应的辅助偏航产生系统。
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2.发明申请公开(公告)号：US20120318913A1
公开(公告)日：2012-12-20
申请号：US13162931
申请日：2011-06-17
IPC分类号： B64D41/00
CPC分类号： B64C5/06 , B64C9/326 , B64D41/00 , B64D2041/002
摘要： Aircraft are provided with a pair of auxiliary power units (APUs) adjacently mounted in parallel relative to one another within the tail cone section of the aircraft's fuselage. In some embodiments, the APUs are mounted generally vertically adjacent to one another. Alternatively, the APUs may be mounted generally horizontally adjacent to one another. The aircraft fuselage may include a pair of downwardly and outwardly oriented strakes adjacent the tail cone having lower edges which establish a maximum take-off pitch angle of the fuselage and define a spatial zone therebetween. The APUs are positioned within such a spatial zone defined between the strakes so that the maximum take-off pitch angle is not required to be changed when modifying an existing single APU aircraft with dual APUs.
摘要翻译： 飞机设有一对辅助动力装置（APU），它们在飞机机身的尾锥部分内彼此相对并联。 在一些实施例中，APU大致垂直相邻地安装。 或者，APU可以大致水平地相对于彼此安装。 飞机机身可以包括一对邻近尾锥的向下和向外定向的横梁，其具有下边缘，其建立机身的最大起飞俯仰角并且在它们之间限定空间区域。 APU被定位在这样的空间区域之间，在这样的空间区域之间限定，使得当用双APU修改现有的单个APU飞机时，不需要改变最大起飞俯仰角。
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公开(公告)号：US3384326A
公开(公告)日：1968-05-21
申请号：US48230465
申请日：1965-08-24
申请人： FRANCIS G. NEUBECK
发明人： NEUBECK FRANCIS G
IPC分类号： B64C9/32
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公开(公告)号：US2676772A
公开(公告)日：1954-04-27
申请号：US32842852
申请日：1952-12-29
申请人： SALAZAR MIGUEL N
发明人： SALAZAR MIGUEL N
IPC分类号： B64C9/32
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公开(公告)号：US1773521A
公开(公告)日：1930-08-19
申请号：US39297129
申请日：1929-09-16
申请人： DAVIS GEORGE H
发明人： DAVIS GEORGE H
IPC分类号： B64C13/00
CPC分类号： B64C9/326 , Y10T477/343
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公开(公告)号：US20160355260A1
公开(公告)日：2016-12-08
申请号：US15117211
申请日：2015-01-24
摘要： A cylindrical active airborne platform for determining measurement data is latchable to a carrying cable such that the airborne platform is towable through the air. Sensors are configured to determine the measurement data and a flight position of the airborne platform. Two aerofoils arranged in the middle region of the airborne platform are adjustable and are connected to electrical adjusting devices configured as ailerons so as to vary a vertical flight position. Opposing two first air guide surfaces and two second air guide surfaces have further electrical adjusting devices configured respectively as elevators and as rudders. A computer supported control device comprises an automatic flight management system that is configured to provide self-acting control of the vertical flight position of the airborne platform, and that is configured to control the further electrical adjusting devices.
摘要翻译： 用于确定测量数据的圆柱形主动式空中平台可锁定到承载电缆，使得机载平台可通过空气拖动。 传感器被配置为确定测量数据和机载平台的飞行位置。 布置在机载平台中部区域的两个翼型可调，并连接到配置为副翼的电气调节装置，以便改变垂直飞行位置。 相反的两个第一空气引导表面和两个第二空气引导表面具有分别配置为电梯和方向舵的电气调节装置。 计算机支持的控制装置包括自动飞行管理系统，其被配置为提供对空中平台的垂直飞行位置的自动控制，并且被配置为控制另外的电气调节装置。
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公开(公告)号：US08231079B2
公开(公告)日：2012-07-31
申请号：US12415088
申请日：2009-03-31
申请人： Hiroki Oyama
发明人： Hiroki Oyama
IPC分类号： B64D17/80
摘要： A speed brake apparatus reduces the airspeed of an aircraft by increasing aerodynamic drag. First and second brake panels are located on opposite sides of a portion of the aircraft, such as the fuselage, and are adapted to swing outward about a downstream hinge axis into deployed positions extending into the air stream. The panels are controlled by an operating device that includes a linear actuator. The actuator moves an operating head connected to a pair of toggle assemblies to convert linear movement of the operating head to the deployment and retraction movement of the brake panels.
摘要翻译： 速度制动装置通过增加空气动力学阻力来降低飞行器的空速。 第一和第二制动面板位于飞机的诸如机身的一部分的相对侧上，并且适于围绕下游铰链轴向外摆动到延伸到空气流中的展开位置。 面板由包括线性致动器的操作装置控制。 致动器移动连接到一对肘节组件的操作头，以将操作头的线性运动转换成制动面板的展开和缩回运动。
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公开(公告)号：US06398167B1
公开(公告)日：2002-06-04
申请号：US09609684
申请日：2000-07-03
申请人： Eddie Ortiz
发明人： Eddie Ortiz
IPC分类号： B64C932
摘要： An aircraft braking system including a port formed in a side of an airplane. The port has an openable door disposed therein. The openable door is in operative communication with a computerized hydraulic system of the airplane whereby the openable door will open once the airplane begins a turn and will not close until the turn is complete.
摘要翻译： 一种飞机制动系统，包括形成在飞机侧面的端口。 该端口具有可开启的门。 可开启的门与飞机的计算机化液压系统操作性地通信，一旦飞机开始转弯，可开启的门将打开，并且在转弯完成之前不会关闭。
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公开(公告)号：US4165849A
公开(公告)日：1979-08-28
申请号：US860588
申请日：1977-12-14
申请人： Anthony Fox
发明人： Anthony Fox
IPC分类号： B64C9/32
摘要： A combination air brake and engine shield for a jet powered aircraft. A hydraulically operated, hinged shield member, shaped so as to conform to the surface of the aircraft fuselage when in its retracted position, may be swung outwardly therefrom so as to be disposed in front of the air intake of the jet engine powering the craft, to thereby divert any foreign objects from being drawn into the intake and damaging the engine. The same arrangement may also serve as an air brake to effect deceleration of the aircraft. Spring loaded louvers are provided in the shield to permit sufficient air to reach the engine such that problems due to cavitation are avoided.
摘要翻译： 用于喷气动力飞机的组合空气制动器和发动机罩。 当处于其缩回位置时，成形为符合飞行器机身表面的液压操作的铰接屏蔽构件可从其向外摆动，以便设置在为飞行器供电的喷气发动机的进气口的前方， 从而将任何异物转移到进气口并损坏发动机。 同样的布置也可以用作空气制动器来实现飞行器的减速。 弹簧加载的百叶窗设置在护罩中，以允许足够的空气到达发动机，从而避免由于空穴引起的问题。
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公开(公告)号：US2987277A
公开(公告)日：1961-06-06
申请号：US76720958
申请日：1958-10-14
CPC分类号： B64C9/326 , B64C9/32 , B64C9/323 , B64C13/00 , B64C21/02 , B64C2230/06 , B64C2230/20 , Y02T50/166
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