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首页> 外文会议>Annual AAS (American Astronautical Society) Rocky Mountain Guidance and Control Conference Feb 5-9, 2003 Breckenridge, Colorado, U.S.A. >COUPLED ATTITUDE AND ORBIT DYNAMICS AND CONTROL IN FORMATION FLYING SYSTEMS
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COUPLED ATTITUDE AND ORBIT DYNAMICS AND CONTROL IN FORMATION FLYING SYSTEMS

机译：飞行系统中的姿态和轨道耦合动力学与控制

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摘要

In this paper, generalized equations of motion for a leader/follower satellite pair are derived. The equations are generalized to include non-circular reference orbits by regularizing the governing equations to be true-anomaly dependent rather than time dependent. In addition, the vehicles are considered to have finite dimensions and are pointed to a specific location on the Earth (i.e., their attitude and orbit dynamics are coupled). An Euler angle attitude representation was chosen and each vehicle is assumed gravity gradient stabilized (i.e., each satellite's z-axis points to its own nadir). Finally, an attitude controller based on the sliding mode concept was developed and implemented to control the attitude of the follower relative to the leader. For the close-loop scenario, both vehicles are required to point to the same position on the surface of the earth (i.e., the nadir of the leader). Simulation results illustrate the capability/performance of the controller developed.
机译：在本文中，导出了领先/跟随卫星对的广义运动方程。通过将控制方程正则化为与真实异常相关，而不是与时间相关，将这些方程推广为包括非圆形参考轨道。另外，认为飞行器具有有限的尺寸，并指向地球上的特定位置（即，它们的姿态和轨道动力学是耦合的）。选择了欧拉角姿态表示法，并假设每辆车的重力梯度都稳定（即每颗卫星的z轴指向其自己的最低点）。最后，开发并实现了基于滑模概念的姿态控制器，以控制跟随者相对于领导者的姿态。对于闭环情况，要求两辆车都指向地球表面上的同一位置（即引导者的最低点）。仿真结果说明了所开发控制器的功能/性能。

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