固体火箭技术2026，Vol.49Issue(4)：520-528,9.DOI:10.7673/j.issn.1006-2793.2026.04.004
基于压强反馈的固体姿轨控发动机工作模式转换过程研究
Working mode conversion process of solid divert and attitude control motor based on pressure feedback
段鑫 1陈晓丽 1潘元岳 1牛禄 1陈晓龙1
作者信息
- 1. 上海航天动力技术研究所,上海 201109
- 折叠
摘要
Abstract
To investigate the dynamic response of chamber pressure during mode-switching of divert and attitude control motors,a pressure-feedback control scheme was adopted.Combined with zero-dimensional internal ballistic and valve servo modeling,the open-loop pressure response was simplified as a first-order inertial element,which was further reduced to a standard second-order system upon the application of closed-loop control.Analytical formulas were derived to describe the dynamic effects of motor characteristic parameters on the mode-switching process,as well as disturbance control errors,and steady-state errors under constant,linear and sinusoidal disturbances were analyzed.A pressure feedback control test was designed,where multiple types of disturbances were generated by adjusting the opening of the attitude control valve,and two groups of mode-switching verification tests were implemented.Test results reveal that proportional control can eliminate errors induced by constant disturbances,but constant offsets persist under linear disturbances and identical-frequency errors occur under sinusoidal disturbances.The dynamic response exhibits obvious time-varying characteristics when mode-switching is triggered at different operating moments.With the target pressure of the high-pressure mode set to 9 MPa,the open-loop gain is increased via control parameters tuning.The control error is limited to 0.2 MPa across all stages without disturbance injection.After introducing various disturbances,the maximum control error reaches 0.5 MPa and the maximum mode-switching time is 0.8 s,which proves that the system possesses strong disturbance rejection capability.关键词
固体姿轨控发动机/变推力/压强反馈控制/扰动/动态响应Key words
SDACM/variable thrust/pressure feedback control/disturbance/dynamic response分类
航空航天引用本文复制引用
段鑫,陈晓丽,潘元岳,牛禄,陈晓龙..基于压强反馈的固体姿轨控发动机工作模式转换过程研究[J].固体火箭技术,2026,49(4):520-528,9.
