运载火箭轨迹预测制导方法研究

Research on Trajectory Prediction Guidance for Launch Vehicle

针对运载火箭入轨多约束需求,提出一种将迭代制导与数值积分相结合的轨迹预测制导方法,该方法计算量较小、适合箭上实时计算,能够同时满足终端姿态约束和轨道参数约束要求。探讨提高轨迹预测制导算法收敛性和实时性的工程实现方法,并分别给出解决方案;通过数学仿真算例验证了该方法的性能,结果分析表明该算法具有较高的制导精度,在增加终端姿态约束而其它条件不变的情况下,算法很好地满足了各项终端指标要求,同时增加的推进剂消耗在可接受范围内。

According to multi - constraint requirements of the launch vehicle, a Trajectory Prediction Guidance（TPG） method combining iterative guidance model and explicit integration was proposed. This method could meet both terminal attitude constraints and orbital parameter requirements. Furthermore, its calculation was relative small and thus suitable for real - time calculation. In addition, the engineering realization for improving convergence and calculation speed of TPG was discussed and the solutions were provided. The performance of this method was verified through mathematical simulation examples. The results indicated that the method had excellent precision. It could meet the additional terminal attitude requirements and orbit requirements, and at the same time, propel- lant consumption was acceptable.