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公开(公告)号：US5517418A
公开(公告)日：1996-05-14
申请号：US352286
申请日：1994-12-08
CPC分类号： G05D1/0883 , B64G1/24 , B64G1/36
摘要： A feedforward disturbance compensation system and method for use with a spacecraft that compensates for predictable disturbances exerted on the spacecraft. The invention comprises a model of the disturbance that is to be compensated, means for knowing when the disturbance will occur, and means for applying the feedforward compensation to the spacecraft in accordance with the model (a compensation profile). The present invention reduces pointing transients through the application of open-loop, feedforward compensation of actuators used to point the spacecraft. The shape of the feedforward profile is determined by an in-orbit test or is predicted by analytical means. For the in-orbit test case that compensates for an eclipse, for example, the spacecraft is flown through the eclipse once to determine the size and shape of the thermal shock disturbance and this information is stored in a spacecraft control processor. The application of the feedforward compensation is synchronized with the start and end of each day's eclipse. This may be achieved by sensing the change in battery discharge current that occurs in solar panels on the spacecraft, for example. On subsequent days, the invention anticipates the occurrence of the disturbance using the stored data. When the start or end of eclipse is detected, compensation for the expected disturbance is automatically applied to spacecraft actuators. The invention can also compensate for a large variety of known periodic disturbances other than thermal shock. These disturbances may be external or internal to the spacecraft. The present invention can also provide compensation by fine tuning the compensation magnitude and duration of the compensation, and is also applicable to both linear and nonlinear control systems.
摘要翻译： 一种与航天器一起使用的前馈扰动补偿系统和方法，其补偿施加在航天器上的可预测的干扰。 本发明包括待补偿的干扰的模型，用于知道何时发生干扰的装置，以及根据模型（补偿简档）将前馈补偿应用于航天器的装置。 本发明通过应用用于指向航天器的致动器的开环前馈补偿来减少指向瞬变。 前馈曲线的形状由轨道内测试确定，或通过分析手段预测。 对于补偿日食的轨道测试案例，例如，航天器通过日食一次，以确定热冲击干扰的大小和形状，并将该信息存储在航天器控制处理器中。 前馈补偿的应用与每天日食的开始和结束同步。 这可以通过例如感测太空板上的太阳能电池板中发生的电池放电电流的变化来实现。 在随后的几天中，本发明使用所存储的数据来预期发生干扰。 当检测到日食的开始或结束时，预期扰动的补偿将自动应用于航天器执行器。 本发明还可以补偿除了热冲击以外的各种已知的周期性干扰。 这些扰动可能是航天器的外部或内部。 本发明还可以通过微调补偿的补偿幅度和持续时间来提供补偿，并且也适用于线性和非线性控制系统。
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2.发明授权Test range for determining the aerodynamic characteristics of a ball in flight 失效用于确定飞行中球的空气动力学特性的测试范围
公开(公告)号：US5682230A
公开(公告)日：1997-10-28
申请号：US548311
申请日：1995-11-01
申请人： Leonard F. Anfinsen , Burton B. Lieberman , Alexander J. Smits , Bernard C. Soriano , Frank W. Thomas , Henry Thumm-Borst , Robert A. Tygar , Stanley E. Chrapowicki , Mark Zagarola
发明人： Leonard F. Anfinsen , Burton B. Lieberman , Alexander J. Smits , Bernard C. Soriano , Frank W. Thomas , Henry Thumm-Borst , Robert A. Tygar , Stanley E. Chrapowicki , Mark Zagarola
CPC分类号： A63B24/0021 , A63B69/3658 , G01P3/68 , A63B2024/0034 , A63B2225/02
摘要： The test range is provided with a calibration system for calibrating the exact position of a light curtain formed by a ballistic screen. The calibration system uses a model ball which can be moved through a light screen at high speed in order to simulate the actual passage of a driven golf ball through the light screen. Positioning of the model golf ball at a point at which the golf ball just contacts the light screen serves to determine the exact location of the light screen. A laser ranging device is used to locate the calibration system relative to a launch point. Thus, the precise distance of the curtain of light from the launch point can be readily determined. The calibration system may also be used to determine if a ballistic screen is mounted in a true vertical plane.
摘要翻译： 测试范围内设有校准系统，用于校准由弹道屏幕形成的光幕的确切位置。 校准系统使用可以高速移动通过光屏幕的模型球，以模拟驱动的高尔夫球通过光屏的实际通过。 模型高尔夫球在高尔夫球刚刚接触光屏的点处的定位用于确定光屏的确切位置。 使用激光测距装置来相对于发射点定位校准系统。 因此，可以容易地确定来自发射点的光幕的精确距离。 校准系统也可用于确定弹道屏幕是否安装在真正的垂直平面中。
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