弹道式火箭制导两点边值问题的一种有效数值解法

A New Efficient Method to the Boundary Value Problem for Ballistic Rocket Guidance

结合航天飞机和飞马火箭的制导律,进行了制导技术的开发,提出了一种新的基于该控制律的火箭真空段运动的多变量边值问题的有效数值迭代解法.数值仿真结果表明,所开发的数值迭代解法在稳定性、鲁棒性、制导精度方面具有相对优良的品质,实时计算方面均为精度很高的代数公式.借助现代DSP高速芯片技术,在一个制导周期内可以实现该算法,以解决较大初始偏差的火箭制导问题.

The exploitation of rocket guidance technology on the basis of the guidance law of Space Shuttle and Pegasus rocket was performed. A new efficient method of numerical iteration solution to the boundary value problem was put forward. The numerical simulation results have shown that the method features good performance of stability, robustness, high precision, and algebraic formulas in real computation. By virtue of modem digital signal processor（DSP）, high speed chip technology, the algorithm can be used in real time and can adapt to the requirements of the big primary bias of rocket guidance.