Strategy on Multi-Rate Gyroscopes Application to Attitude Control of Launch Vehicles

被引：0
|
作者：
Wang J.-M. [1 ,2 ]
Zhang D.-M. [2 ]
Hong L.-Y. [2 ]
Li N. [3 ]
机构：
[1] Science and Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing
[2] Beijing Institute of Structure and Environment Engineering, Beijing
[3] Beijing Institute of Astronautical Systems Engineering, Beijing
来源：
Yuhang Xuebao/Journal of Astronautics | 2020年 / 41卷 / 03期
关键词：
Attitude control; Launch vehicle; Mode shape slope; Rate gyroscope;
D O I：
10.3873/j.issn.1000-1328.2020.03.010
中图分类号：
学科分类号：
摘要：
The method of replacing a single-rate gyroscope with multi-rate gyroscopes is researched in this paper, the grouping slope strategy of any number of gyroscopes is proposed, and the strategy is applicable to the design of the large launch vehicle attitude control in use of the rate gyroscopes. The uncertainty degree formula of the grouping slopes is proposed and used in the calculation of the grouping slopes coefficient matrix, which makes it feasible in engineering to replace the single-rate gyroscope with the multi-rate gyroscopes in the attitude control elasticity stability design. The example in the real engineering demonstrates the advantages of using the multi-rate gyroscopes. The use of the multi-rate gyroscopes may decrease the requirements of the gyroscope installation position selection and the mode shape slopes measurement precision in the modal test of the vehicle, which makes it possible for future launch vehicles not to conduct integrated modal test. © 2020, Editorial Dept. of JA. All right reserved.
引用
收藏
页码：337 / 342
页数：5
相关论文
共 10 条
  • [1] Yang D.-S., Attitude control system of a large-scale strap-on launch vehicle, Aerospace Control, 1, pp. 1-6, (1991)
  • [2] Xu X.-H., Shao Z.-M., Chen B.-C., Et al., LM-4 guidance, attitude control and trajectory measurement system, Journal of Astronautics, 4, pp. 3-9, (1989)
  • [3] Zhang W.-D., Liu Y.-X., Liu H.-B., Et al., Development trend and prospect of attitude control technologies of launch vehicle, Aerospace Control, 35, 3, pp. 85-89, (2017)
  • [4] Yuan J.-P., Chen S.-L., Positioning of sensors for flexible flight vehicles, Journal of Astronautics, 1, pp. 81-88, (1987)
  • [5] Song X.-J., Yue B.-Z., Yan Y.-L., Et al., Hybrid control for attitude maneuver of liquid-filled spacecraft with multiple modal liquid sloshing, Journal of Astronautics, 36, 7, pp. 819-825, (2015)
  • [6] Yang Y.-F., Li J.-W., Chen Y., Et al., Study on attitude dynamic model of large strap-on launch vehicle, Science in China(Part E: Technical Science), 39, 3, pp. 490-499, (2009)
  • [7] Wang Y., Zhu L.-W., Wang M.-Y., Et al., Summary of some key technologies on dynamics of large launch vehicle, Missiles and Space Vehicles, 1, pp. 29-37, (2000)
  • [8] Qiu J.-B., Wang J.-M., The recent progresses on research into modal test simulation techniques for launch vehicles, Journal of Astronautics, 3, pp. 515-521, (2007)
  • [9] Sun P.-L., Analysis and research on the redundant concept of the attitude control system of launch vehicle, Missiles and Space Vehicles, 6, pp. 9-14, (2001)
  • [10] Sun N.-S., The redundancy designs for guidance and control system of launch vehicle, Aerospace Control, 2, pp. 68-80, (2003)
1