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1. 发明授权

US5100084A Method and apparatus for inclined orbit attitude control for momentum bias spacecraft 失效
标题翻译：用于母体偏移量的嵌入式姿态控制的方法和装置
公开(公告)号：US5100084A
公开(公告)日：1992-03-31
申请号：US579117
申请日：1990-09-07
申请人： Christopher D. Rahn , John A. Lehner , Donald W. Gamble
发明人： Christopher D. Rahn , John A. Lehner , Donald W. Gamble
IPC分类号： B64G1/24 , B64G1/26 , B64G1/28 , B64G1/36 , B64G1/38 , G05D1/08
CPC分类号： B64G1/38 , B64G1/24 , B64G1/28 , B64G1/36 , G05D1/0883 , B64G1/26 , B64G1/283 , B64G1/285
摘要： The present invention is a method and apparatus to control a pointing trajectory of an aim point with respect to one or more targets for a momentum bias spacecraft in an orbit inclined relative to an equatorial geosynchronous orbit wherein the spacecraft is provided with an onboard computer capable of using orbit information available to the spacecraft and spacecraft hardware to move the aim point according to a predetermined tracking model which may be either time-varying or invariant. The tracking model allows the controller to remove short-term nutational and long-term orbit rate dynamical disturbances, beyond simple-order sinusoidal functions having a single frequency.

2. 发明授权

US4521855A Electronic on-orbit roll/yaw satellite control 失效
标题翻译：电子轨道滚转/偏航卫星控制
公开(公告)号：US4521855A
公开(公告)日：1985-06-04
申请号：US288230
申请日：1981-07-27
申请人： John A. Lehner , Kenneth L. Lebsock
发明人： John A. Lehner , Kenneth L. Lebsock
IPC分类号： B64G1/24 , B64G1/28 , G05D1/08 , B64G1/10
CPC分类号： B64G1/285 , G05D1/0883
摘要： Disclosed is a method and apparatus estimating yaw error and roll and yaw disturbance torques from measured roll error and yaw momentum on a continuous on-orbit basis in an orbiting satellite. The information thus obtained can be used to continuously correct for the yaw error by means of, for example, activating a magnetic torquer. Two control loops are used in this invention, a fast loop to damp nutations by changing momentum wheel speed, and a slow loop of the Luenberger observer variety. The latter is a yaw error correction loop which also serves to unload yaw momentum. The satellite in which the invention was first incorporated is of the type having three momentum wheels, all situated in the plane orthogonal to the roll axis. In normal operation, two wheels, each having major momentum component along the pitch axis and minor momentum component along the yaw axis, are operable. A third backup wheel aligned along the yaw axis becomes operable only in the eventuality that one of the primary wheels suffers a breakdown during the life of the satellite. The slow speed yaw loop is used to adjust a magnetic coil torquer. It can be implemented in a number of forms including a hard-wired analog form or a digital computer with certain constant scaling factors programmed into the memory of the computer.
摘要翻译：公开了一种方法和装置，其在轨道卫星中在连续的轨道基础上从测量的滚动误差和横摆动量估计偏航误差和滚转和偏航干扰转矩。这样获得的信息可以用于通过例如激活磁性装置来连续地校正偏航误差。在本发明中使用两个控制回路，通过改变动量轮速度来阻止螺母的快速回路，以及Luenberger观察器种类的慢循环。后者是偏航误差校正回路，其也用于卸载偏航动量。首先引入本发明的卫星是具有三个动量轮的类型，全部位于与辊轴正交的平面中。在正常操作中，可操作两个轮，每个轮沿着俯仰轴具有主要动量分量，并且沿着偏转轴线具有较小的动量分量。沿着偏航轴对准的第三备用轮只有在主轮中的一个在卫星的寿命期间遭受击穿的情况下才可操作。慢速偏航环路用于调整电磁线圈装置。它可以以多种形式实现，包括硬编线模拟形式或具有编程到计算机的存储器中的某些恒定缩放因子的数字计算机。

3. 发明授权

US5618012A Satellite stabilization system 失效
标题翻译：卫星稳定系统
公开(公告)号：US5618012A
公开(公告)日：1997-04-08
申请号：US371821
申请日：1995-01-12
申请人： John A. Lehner , Thomas Holmes
发明人： John A. Lehner , Thomas Holmes
IPC分类号： B64G1/24 , B64G1/40 , B64G1/44 , G05D1/08
CPC分类号： G05D1/0883 , B64G1/24 , B64G1/407 , B64G1/44
摘要： A satellite stabilization system compensates for the destabilizing torque introduced by solar radiation pressure by the emplacement of tabs of material angled relative to the back surfaces of the antenna reflectors to intercept solar rays. The material of the tabs interacts with the solar radiation in substantially the same manner as the interaction of the material on the back surface of each antenna reflector to produce a radiation pressure and consequential increment in a torque about an axis of the satellite. Each of the tabs is constructed in the manner of a plate or disk, and is attached by means of a spring mount to the back surface of one of the reflectors. The reflectors are angled relative to each other, as well as to a body of the satellite which holds feeds for illuminating the reflectors, for directing beams of radiation from the feeds towards the earth. Due to the angulation of the reflectors to each other, the total solar energy incident upon a pair of of the reflectors is generally unequal, this resulting in a net torque from the solar radiation pressure which tends to rotate the satellite. By virtue of the angulation of the tabs relative to the reflectors, an increased amount of solar radiation is received by the reflector which is angled away from the sun's rays, thereby to equalize the torque from both of the reflectors.
摘要翻译：卫星稳定系统补偿由太阳辐射压力引入的不稳定扭矩，通过放置相对于天线反射器的后表面成角度的突片，以拦截太阳光线。翼片的材料以与每个天线反射器的背面上的材料的相互作用基本相同的方式与太阳辐射相互作用，以产生围绕卫星的轴线的转矩的辐射压力和相应的增量。每个突片以板或盘的方式构造，并且通过弹簧安装件附接到一个反射器的背面。反射器相对于彼此成角度，以及卫星的主体，其保持用于照射反射器的馈送物，用于将来自馈电的辐射束引导到地球。由于反射器彼此成角度，入射到一对反射器上的总太阳能通常是不相等的，这导致来自倾向于使卫星旋转的太阳辐射压力的净转矩。由于凸片相对于反射器的角度，太阳辐射量的增加被反射器所接收，该反射器远离太阳光线成角度，从而平衡来自两个反射器的转矩。

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