### 基于落点预测的高旋火箭弹弹道修正算法

1. 1. 西北工业大学 航天学院, 西安 710072;
2. 上海航天技术研究院, 上海 201109
• 收稿日期:2019-09-02 修回日期:2019-09-28 出版日期:2020-02-15 发布日期:2019-11-07
• 通讯作者: 谷良贤 E-mail:gulx@nwpu.edu.cn
• 基金资助:
国家自然科学基金（51505385）

### Ballistic trajectory correction algorithms of high-spin rocket based on impact point prediction

YANG Sizhi1, GONG Chunlin1, HAO Bo2, WU Weinan1, GU Liangxian1

1. 1. College of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. Shanghai Academy of Spaceflight Technology, Shanghai 201109, China
• Received:2019-09-02 Revised:2019-09-28 Online:2020-02-15 Published:2019-11-07
• Supported by:
National Natural Science Foundation of China (51505385)

Abstract: The trajectory corrective control of high-spin rocket is a two-dimensional correction control based on equivalent force. Due to gyro precession and the Magnus effect of high-spin rocket, the equivalent force is formed by the control force, and the force caused by the additional angle of attack under the action of the control force, the magnitude and direction of the equivalent force is constantly changing during the control. Therefore, the direction of control force can't be determined simply by the proportional relation of deviation (correction quantity). Based on this, the relationship between control force and equivalent force is analyzed in this paper. A corrective algorithm based on trajectory impact point prediction is proposed. At first, the deviation between the rocket's landing point and its target position is predicted in real-time using the impact point prediction model. Then the paper established corrective sensitivity coefficient matrix based on the small perturbation method, and the control quantity in both longitudinal and transverse directions were obtained through the deviation and sensitivity coefficient matrix. The combined vector and azimuth of the control quantity were obtained by using the relationship of velocity vector before and after the correction control, and the control period was calculated by using the control quantity and the equivalent force. In the control period, the direction of the control force was adjusted according to the azimuth of the equivalent force angle, the accurate control of the high-spin rocket was obtained, and the problem of non-linear coupling was solved. The simulation results show that the algorithm has high control accuracy, providing theoretical basis for engineering application.