固体火箭技术2026，Vol.49Issue(1)：65-73,9.DOI:10.7673/j.issn.1006-2793.2026.01.008
基于自适应超螺旋滑模控制器的喉栓式固体火箭发动机压强控制方法
Pressure control method of pintle solid rocket motor based on adaptive super-twisting sliding mode controller
边政 1朱铭 1王文泽 1袁泽建 2薛海峰 1李映坤 1陈雄1
作者信息
- 1. 南京理工大学机械工程学院,特种动力技术教育部重点实验室,南京 210094
- 2. 西北工业集团有限公司,西安 710043
- 折叠
摘要
Abstract
The pressure control system of a pintle solid rocket motor exhibits significant time-varying and nonlinear characteristics,along with multiple disturbances during operation,which adversely affect its regulation performance.To address these issues,first,the mathematical relationship between pressure and pintle displacement was derived based on the zero-dimensional interior ballistic equation,and the transfer function of the system was derived based on the motor model.Second,an adaptive super-twisting sliding mode controller(ASTSMC)was designed by combining adaptive control and sliding mode control to reduce the system error and improve its anti-interference performance,and its stability was proved by the Lyapunov function.Finally,the ASTSMC was simulated in many aspects.The results show that the response speed of ASTSMC is 464.6%and 146.2%higher than that of the PID controller and super-twisting sliding mode controller(STSMC),respectively,and with no overshoot.In terms of anti-interference,the control error of ASTSMC is reduced by 82.4%and 66.7%,respectively,compared with the PID and STSMC controller.关键词
喉栓/固体火箭发动机/压强控制/非线性控制/自适应超螺旋滑模控制器Key words
pintle/solid rocket motor/pressure control/nonlinear control/adaptive super-twisting sliding mode controller分类
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边政,朱铭,王文泽,袁泽建,薛海峰,李映坤,陈雄..基于自适应超螺旋滑模控制器的喉栓式固体火箭发动机压强控制方法[J].固体火箭技术,2026,49(1):65-73,9.
