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| A NEW EFFICIENT METHOD TO BOUNDARY VALUE PROBLEM FOR BALLISTIC ROCKET GUIDANCE | |
| 引用本文： | 刘新建 袁天保. A NEW EFFICIENT METHOD TO BOUNDARY VALUE PROBLEM FOR BALLISTIC ROCKET GUIDANCE[J]. 应用数学和力学(英文版), 2005, 26(10): 1375-1381. DOI: 10.1007/BF03246242 |
| 作者姓名： | 刘新建 袁天保 |
| 作者单位： | Institute of Aerospace Engineering，National University of Defense Technology，Changsha 410073，P.R.China，Institute of Aerospace Engineering，National University of Defense Technology，Changsha 410073，P.R.China |
| 基金项目： | Project supported by the National High-Tech Research and Development Program of China （ 863 Program） （ No. 8637020 11 ） |
| 摘 要： | IntroductionThe problem of motion control for the mass center of ballistic rocket pertained typicallyto the boundary value problem for two points with the non-linear and multi-variables,namely,given the initial states of rocket,in order to satisfy the res… |
| 关 键 词： | 火箭 制导控制 边值问题 数字模拟 稳定性 |
| 文章编号： | 0253-4827（2005）10-1375-07 |
| 收稿时间： | 2003-11-11 |
| 修稿时间： | 2005-03-15 |
A new efficient method to boundary value problem for ballistic rocket guidance |
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| Xin-jian Liu,Tian-bao Yuan. A new efficient method to boundary value problem for ballistic rocket guidance[J]. Applied Mathematics and Mechanics(English Edition), 2005, 26(10): 1375-1381. DOI: 10.1007/BF03246242 | |
| Authors: | Xin-jian Liu Tian-bao Yuan |
| Affiliation: | 1. Institute of Aerospace Engineering, National University of Defense Technology, Changsha, 410073, P. R. China |
| Abstract: | 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 performances of stability, robustness, high precision, and algebraic formulas in real computation. By virtue of modern DSP(digital signal processor) 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. |
| Keywords: | rocket guidance and control boundary value problem numerical iteration |
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