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1. 发明申请

US20030122038A1 Method of lift control of aircraft and system therefor 失效
标题翻译：飞机及其系统的升降机控制方法
公开(公告)号：US20030122038A1
公开(公告)日：2003-07-03
申请号：US10026881
申请日：2001-12-27
申请人： TOYOTA JIDOSHA KABUSHIKI KAISHA
发明人： Yoshiki Fukada
IPC分类号： B64C013/16
CPC分类号： B64C9/12 , Y02T50/32
摘要： The present invention is structured such that lift control apparatus such as flaps and flaperons operate in association with elevator operation performed by a pilot. Lift control conforming to elevator operation by the pilot is performed.
摘要翻译：本发明的结构使得诸如襟翼和襟副翼的升降机控制装置与由飞行员执行的电梯操作相关联地操作。执行与飞行员的电梯操作一致的升降控制。

2. 发明申请

US20030057332A1 Flap arrangement for varying the aerodynamic lift generated by an aerodynamic element of an aircraft 有权
标题翻译：用于改变由飞行器的空气动力学元件产生的空气动力升力的翼片装置
公开(公告)号：US20030057332A1
公开(公告)日：2003-03-27
申请号：US10255765
申请日：2002-09-25
发明人： Detlev Schwetzler , Peter May
IPC分类号： B64C013/16
CPC分类号： B64C9/18
摘要： An auxiliary flap is movably arranged on a planar trailing edge of an aerodynamic element such as a wing, rudder, stabilizer, or flap. The auxiliary flap is rotatable and/or slidable relative to the aerodynamic element, to move selectively into three positions. In a first position, a free edge of the auxiliary flap protrudes into an airflow boundary layer on one side of the aerodynamic element, to decrease lift. In a second position, a free edge of the aerodynamic element protrudes into an airflow boundary layer on the other side of the aerodynamic element, to increase lift. In a third neutral position, the auxiliary element does not protrude into either boundary layer, so as not to influence lift. The auxiliary flap is simple and rapidly acting. The flap protrudes substantially perpendicularly into the boundary layer flow. The auxiliary flap has a planar plate shape.
摘要翻译：辅助翼片可移动地布置在诸如翼，舵，稳定器或翼片的空气动力学元件的平面后缘上。辅助翼片可相对于空气动力学元件旋转和/或滑动，以选择性地移动到三个位置。在第一位置，辅助翼片的自由边缘突出到空气动力元件的一侧上的气流边界层中，以减小升力。在第二位置，空气动力元件的自由边缘突出到空气动力元件的另一侧上的气流边界层中，以增加升力。在第三中立位置，辅助元件不突出到任一边界层中，以便不影响升力。辅助翼片简单快速。翼片基本上垂直地突出到边界层流中。辅助翼片具有平板形状。

3. 发明申请

US20030234319A1 GLIDING VEHICLE GUIDANCE 失效
标题翻译：车辆指导
公开(公告)号：US20030234319A1
公开(公告)日：2003-12-25
申请号：US10175527
申请日：2002-06-21
发明人： Craig A. Phillips , David S. Malyevac
IPC分类号： B64C003/18 , B64C013/16 , B64C017/00
CPC分类号： G05D1/12
摘要： Guidance of a gliding vehicle is disclosed. A method of the invention allows the range of the glide phase of a gliding vehicle to be maximized, while satisfying final flight path angle and aimpoint requirements. The method controls the time-of-flight of the gliding value to a desired value. The time-of-flight control can correct for winds, off-nominal launch conditions, and rocket motor variations, among other factors. Both time-of-flight control and range and cross-range maximization can be achieved by the inventive method, utilizing a compact closed-loop approach.
摘要翻译：披露滑翔车辆的指导。本发明的方法允许滑行车辆的滑行相的范围最大化，同时满足最终飞行路径角度和目标要求。该方法将滑行值的飞行时间控制到所需的值。飞行时间控制可以纠正风，非标称发射条件和火箭发动机变化等因素。通过本发明的方法，利用紧凑的闭环方法，可以实现飞行时间控制和范围和跨范围最大化。

4. 发明申请

US20040251383A1 Use of aerodynamic forces to assist in the control and positioning of aircraft control surfaces and variable geometry systems 失效
标题翻译：使用空气动力来帮助控制和定位飞机控制面和可变几何系统
公开(公告)号：US20040251383A1
公开(公告)日：2004-12-16
申请号：US10482314
申请日：2003-12-30
发明人： William R McDonnell
IPC分类号： B64C013/16
CPC分类号： B64C9/10 , B64C13/505 , B64C27/615 , Y02T50/32 , Y02T50/34 , Y02T50/44
摘要： The current invention relates primarily to the control of rotary wing and fixed wing aircraft where a small electric actuator (7, 104) changes the pitch on a small aerodynamic surface (5, 66) and the resulting airloads on said small aerodynamic surface are used to change the pitch on a significantly larger aerodynamic surface (3, 60). In the preferred embodiment the resulting airloads on said larger aerodynamic surface is then used to change the pitch on a still larger aerodynamic surface (1, 62). As a result small electric actuators are capable of moving and controlling large aircraft control surfaces with an effective two step amplification of power utilizing the energy in the airstream. The current invention also discloses means to control and prevent undesirable motion of said aerodynamic surfaces.
摘要翻译：本发明主要涉及旋转翼和固定翼飞行器的控制，其中小的电动致动器（7,104）在小的空气动力学表面（5,66）上改变桨距，并且将所得小的空气动力学表面上的空气载荷用于在更大的空气动力学表面上改变沥青（3,60）。在优选实施例中，所述较大空气动力学表面上的所得空气载荷然后被用于改变更大的空气动力学表面上的桨距（1,62）。因此，小型电动执行器能够利用气流中的能量以有效的两步放大功率来移动和控制大型飞行器控制表面。本发明还公开了控制和防止所述空气动力学表面的不期望运动的手段。

5. 发明申请

US20040079835A1 Control system for alleviating a gust load on an aircraft wing 有权
公开(公告)号：US20040079835A1
公开(公告)日：2004-04-29
申请号：US10280512
申请日：2002-10-25
发明人： John A. Volk
IPC分类号： B64C013/16
CPC分类号： B64C9/32 , B64C9/22 , B64C9/323 , B64C13/16 , G05D1/0066 , Y02T50/32 , Y02T50/44
摘要： Disposed on each wing of an aircraft adjacent the wing tip is at least one deflector mechanism for twisting the wings as part of a control system for alleviating a gust load on the wing. The wing twisting is performed in conjunction with a vertical motion sensor, a sensor signal processor, and a deflector controller. The vertical motion sensor measures the vertical motion of the wing tip in response to the gust load on the wing and generates a sensor output signal. A sensor signal processor generates a deflector control signal in response to the sensor output signal. The deflector control signal represents the duration and degree of the deflector mechanism movement effective to counteract an increase in bending moment on the wing due to a gust load on the wing. A deflector controller regulates the deflector mechanism movement in response to the deflector control signal such that the deflector mechanism is alternately deployed and retracted into and out of the airstream.

6. 发明申请

US20030001046A1 Apparatus and method for flight control of an aircraft 失效
标题翻译：飞机飞行控制的装置和方法
公开(公告)号：US20030001046A1
公开(公告)日：2003-01-02
申请号：US09898631
申请日：2001-07-02
发明人： Billy R. Carpenter
IPC分类号： B64C013/16
CPC分类号： B64C15/02 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/048 , B64C2201/22 , B64D27/02 , Y02T50/12 , Y02T50/44
摘要： An apparatus and method for flight control of an aircraft provides a body with adjustable intake ports ducting air into an internal intake manifold. Adjusting the openings of the intake ports changes the amount of air flowing over the surfaces surrounding the intakes, changing the amount of lift created by those surfaces. The intake manifold feeds air to at least one engine, and an exhaust manifold communicates the exhaust of the engine to exhaust exit ports. The exhaust manifold contains a plurality of moveable components that direct exhaust within the exhaust manifold and to particular exhaust exit ports for producing various levels of force imbalance among the exit ports. A compressor powered by the engine provides air to bleed-air ports on the wings. Varying lift on the forward surfaces with the intake ports, vectored exhaust, and bleed air are used to control and stabilize the aircraft during flight, obviating the need for aerodynamic control surfaces
摘要翻译：用于飞机飞行控制的装置和方法为身体提供了将空气引导到内部进气歧管中的可调节进气口。调整进气口的开口可改变在进气口周围的表面上流动的空气量，从而改变由这些表面产生的升力量。进气歧管将空气供给至少一个发动机，并且排气歧管将发动机的排气与排气出口连通。排气歧管包含多个可移动部件，其将排气歧管内的排气引导到特定排气出口，用于在出口之间产生不同程度的力不平衡。由发动机供电的压缩机为机翼上的排气口提供空气。前进表面上带有进气口，向导排气和排气的不同升降机用于在飞行过程中控制和稳定飞机，避免了空气动力学控制面的需要

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