| 摘要: |
| 试验运载器在姿控动力系统空间布置紧张、控制力臂有限的情况下，要实现初始起控阶段大初始姿态偏差及气动干扰条件下的稳定控制，以及有效载荷释放阶段的多通道多次连续大角度调姿控制，给姿控系统的设计造成了困难。为此，通过鸭式直接力控制方案设计、多通道连续大角度调姿方案设计等技术，设计出了满足任务要求且性能良好的姿控总体方案。 |
| 关键词: 运载器 姿态控制 姿控发动机 |
| DOI： |
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| 基金项目: |
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| The Optimization of Attitude Control System for Testing-Purpose Launch Vehicle |
| ZHENG Xin,ZHAO Min,YU Yubin,LIU Lin |
| (Beijing Institute of Ａstronautical Systems Engineering, Beijing 100076,China;;China Academy of Launch Vehicle Technology, Beijing 100076,China) |
| Abstract: |
| Design of the attitude control system is facing obstacles as it aims not only at the stability control at the starting flight phase when initial attitude error and aerodynamic interference are inevitable, but also at the continuous attitude control with wide angle at the release phase.Due to the limit of the spatial arrangement of attitude control's dynamical system and the limit of the control of the arm of force, attitude control system design is not an easy work considering the time pressure and the shortage of the project fund.Despite all these difficulties, attitude control design team, relying on canard reaction force controlling design technique and multi-tunnel continuous wide angle attitude adjusting design technique, etc., has successfully come up with an optimal solution package, thus making significant contribution to the research work and the flight experiment. |
| Key words: Launch vehicle Attitude control Reaction control engine |