宇航学报

宇航学报 ›› 2020, Vol. 41 ›› Issue (3): 337-342.doi: 10.3873/j.issn.1000-1328.2020.03.010

• 制导、导航、控制与电子 • 上一篇    下一篇

运载火箭姿态控制稳定性多速率陀螺组合策略

王建民，张冬梅，洪良友，李宁   

  1. 1. 北京强度环境研究所可靠性与环境工程技术重点实验室，北京 100076； 2. 北京强度环境研究所，北京 100076；3. 北京宇航系统工程研究所，北京 100076
  • 收稿日期:2018-12-13 修回日期:2019-04-15 出版日期:2020-03-15 发布日期:2020-03-25

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

WANG Jian min, ZHANG Dong mei, HONG Liang you, LI Ning   

  1. 1. Science and Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing 100076, China; 2. Beijing Institute of Structure and Environment Engineering, Beijing 100076, China; 3. Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China
  • Received:2018-12-13 Revised:2019-04-15 Online:2020-03-15 Published:2020-03-25

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摘要： 针对运载火箭飞行姿态控制中采用多速率陀螺组合代替单速率陀螺的问题，提出了任意数量速率陀螺组合的斜率计算方法，方法适用于大型运载火箭一级飞行速率陀螺组合姿态控制方式。推导了组合斜率不确定度的计算公式，并将不确定度纳入组合系数矩阵的计算当中，从而给出了一套工程实用的多速率陀螺组合姿态控制弹性稳定性策略。利用工程实例说明了组合速率陀螺较单个陀螺的优势。多速率陀螺的使用降低了对全箭模态试验振型斜率选位和斜率测量精度的要求，可为未来运载火箭不开展全箭试验提供支撑。

关键词: 运载火箭, 姿态控制, 模态振型斜率, 速率陀螺

Abstract: 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.

Key words: Launch vehicle, Attitude control, Mode shape slope, Rate gyroscope

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