宇航学报 ›› 2022, Vol. 43 ›› Issue (4): 393-402.doi: 10.3873/j.issn.1000-1328.2022.04.001

• 飞行器设计与力学 • 上一篇    下一篇

运载火箭加速度计反馈主动减载实施效果评价

赵永志,王紫扬,宋征宇,张普卓   

  1. 1. 北京宇航系统工程研究所,北京 100076; 2. 中国运载火箭技术研究院,北京 100076
  • 收稿日期:2021-10-08 修回日期:2022-03-01 出版日期:2022-04-15 发布日期:2022-04-15

Assessment on Accelerometer Based Load Relief Control for Launch Vehicle

ZHAO Yong zhi, WANG Zi yang, SONG Zheng yu, ZHANG Pu zhuo   

  1. 1. Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China;2. China Academy of Launch Vehicle Technology, Beijing 100076, China
  • Received:2021-10-08 Revised:2022-03-01 Online:2022-04-15 Published:2022-04-15

摘要: 针对运载火箭加速度计反馈主动减载实施效果评价,提出一种基于主动减载姿态动力学稳态分析的评价方法,在传统的“载荷侧滑角”评价指标基础上增加了“姿态偏差”、“摆角需求”和“弹道偏离”评价。稳态分析中考虑了结构干扰的偏置效应以及质心运动对风的抵消效应,重点推导了风切变对于火箭姿态动力学特征参数的影响机理。某型号案例分析结果表明,在典型“平稳风+切变风”风场作用下,主动减载技术在4项评价指标上均取得理想实施效果,并且显著缓解风切变导致的姿态参数快变现象。

关键词: 运载火箭, 主动减载, 风切变, 结构干扰, 效果评价

Abstract: For purpose of assessing the performance of load relief on launch vehicle, an assessment method based on steady state analysis is proposed. In addition to the criterion of load angle on of sideslip, the criteria of attitude deviation, engine deflection angle and trajectory deviation are also adopted. The bias effect of structural disturbances and the counteract effect to wind of translational motion are taken into consideration in this method. The influence mechanism of attitude dynamics parameters changes by wind shear is derived. Case study results indicate that, under the effect of typical wind field of steady wind & shear wind, load relief achieves acceptable performance in all the four assessment criteria, and greatly mitigates the problem of attitude parameters excessive change by wind shear.

Key words: Launch vehicle, Load relief, Wind shear, Structural disturbance, Performance assessment

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