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本文针对运载火箭快速控制问题,介绍应用最优控制理论,导出满足空间制导要求的一种路线自适应制导方法——迭代制导方法。文中叙述了该方法的基本思想和基本结论。给出了一组近似最优制导方程。并且结合发射地球卫星,介绍了一个迭代制导方案,列出了迭代制导方案的工作程序,以及模拟计算得出的制导精度。从而表明,迭代制导方法的制导精度较Delta最小制导方法的制导精度高得多,是一种可供广泛用于运载火箭制导的新方法。
Aiming at the problem of rapid control of launch vehicle, this paper introduces the application of optimal control theory and derives an adaptive route guidance method - iterative guidance method that meets the requirements of space guidance. The article describes the basic ideas and basic conclusions of the method. A set of approximate optimal guidance equations is given. In combination with the launching of the earth satellites, an iterative guidance scheme is introduced. The working procedures of the iterative guidance scheme and the guidance accuracy of the simulation are given. It shows that the guidance accuracy of iterative guidance method is much higher than that of Delta minimum guidance method, which is a new method that can be widely used in guidance of launch vehicle.