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1.发明申请Lightweight Vertical Take-Off and Landing Aircraft and Flight Control Paradigm Using Thrust Differentials 审中-公开轻型垂直起飞和着陆飞机和使用推力差速器的飞行控制范式公开(公告)号：US20110042510A1
公开(公告)日：2011-02-24
申请号：US12766850
申请日：2010-04-23
IPC分类号： B64C29/00
CPC分类号： B64C29/0033
摘要： An aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which uses a rotating platform of engines in fixed relationship to each other and which rotates relative to the main body of the vehicle for takeoff and landing. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in at least two dimensions relative to the horizontal during takeoff, and which may also control regular flight in some aspects by the use of differential thrust of the engines.
摘要翻译： 一种适用于垂直起飞和着陆的飞行器，使用相同的发动机起飞和着陆以及向前飞行。 一种飞行器，其使用彼此固定关系并且相对于车辆主体旋转的发动机的旋转平台用于起飞和着陆。 一种飞行器，其适于在垂直方向上与翼起飞，而不是水平飞行姿态，以垂直姿态起飞，然后转变到水平飞行路径。 一种飞行器，其在起飞和着陆期间通过交替发动机的推力来控制车辆的姿态，发动机的推力在起飞期间相对于水平在至少两个维度上分离，并且还可以通过使用 发动机差动推力。
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2.发明授权公开(公告)号：US08733690B2
公开(公告)日：2014-05-27
申请号：US12766833
申请日：2010-04-23
IPC分类号： B64C27/22
CPC分类号： B64C29/0033
摘要： An aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in at least two dimensions relative to the horizontal during takeoff, and which may also control regular flight in some aspects by the use of differential thrust of the engines.
摘要翻译： 一种适用于垂直起飞和着陆的飞行器，使用相同的发动机起飞和着陆以及向前飞行。 一种飞行器，其适于在垂直方向上与翼起飞，而不是水平飞行姿态，以垂直姿态起飞，然后转变到水平飞行路径。 一种飞行器，其在起飞和着陆期间通过交替发动机的推力来控制车辆的姿态，发动机的推力在起飞期间相对于水平在至少两个维度上分离，并且还可以通过使用 发动机差动推力。
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3.发明申请Lightweight Vertical Take-Off and Landing Aircraft and Flight Control Paradigm Using Thrust Differentials 有权轻型垂直起飞和着陆飞机和使用推力差速器的飞行控制范式公开(公告)号：US20110042509A1
公开(公告)日：2011-02-24
申请号：US12766833
申请日：2010-04-23
IPC分类号： B64C29/00
CPC分类号： B64C29/0033
摘要： An aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in at least two dimensions relative to the horizontal during takeoff, and which may also control regular flight in some aspects by the use of differential thrust of the engines.
摘要翻译： 一种适用于垂直起飞和着陆的飞行器，使用相同的发动机起飞和着陆以及向前飞行。 一种飞行器，其适于在垂直方向上与翼起飞，而不是水平飞行姿态，以垂直姿态起飞，然后转变到水平飞行路径。 一种飞行器，其在起飞和着陆期间通过交替发动机的推力来控制车辆的姿态，发动机的推力在起飞期间相对于水平在至少两个维度上分离，并且还可以通过使用 发动机差动推力。
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公开(公告)号：US20100230546A1
公开(公告)日：2010-09-16
申请号：US12566675
申请日：2009-09-25
CPC分类号： F03D5/00 , F05B2240/40 , F05B2240/92 , F05B2240/921 , F05B2240/922 , Y02E10/70
摘要： A control system and method for control of a cyclical flying system which uses lift segments, which may be airfoils, which rotate around a central hub, similar to the mechanics of an autogyro. The airfoils may achieve speeds significantly above the wind speed feeding the system. The airfoils may be linked to the central hub by flexible radial tethers which stiffen considerably as the speed of the airfoil increases. The central hub may be linked to the ground with an extendible main tether. Power generation turbines may reside on the airfoils and utilize the high apparent wind speed for power generation. The generated power may travel down the radial tethers and across a rotating power conduit to the main tether and to the ground. The airborne assembly may have the rotational speed of the airfoils, its altitude, and its attitude controlled by using control surfaces linked to the airfoils, or by control of the angle of attack of the airfoils relative to a central hub, or relative to each other. The attitude and altitude sensors and the control system may be airborne and may be part of the rotating assembly. The airborne assembly can be moved to areas of appropriate wind speed for the system using these controls.
摘要翻译： 一种用于控制循环飞行系统的控制系统和方法，该系统使用类似于自动驾驶仪的机构的围绕中心轮毂旋转的提升段，其可以是翼型件。 机翼可以实现明显高于馈送系统的风速的速度。 翼型件可以通过柔性的径向系链连接到中心毂，当翼型件的速度增加时，翼状件可以相当大地加强。 中心枢纽可以与可扩展的主系绳连接到地面。 发电涡轮机可以驻留在翼型上并利用高的表观风速用于发电。 所产生的功率可以沿着径向系绳并且穿过旋转的动力导管移动到主系绳和地面。 机载组件可以具有翼型件的旋转速度，其高度及其通过使用与翼型件连接的控制表面控制的姿态，或者通过控制翼型件相对于中心轮毂的迎角或相对于彼此控制 。 姿态和高度传感器和控制系统可以是机载的并且可以是旋转组件的一部分。 机载组件可以移动到使用这些控制系统的适当风速的区域。
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