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OA
Pressure control method of pintle solid rocket motor based on adaptive super-twisting sliding mode controller
喉栓式固体火箭发动机压强控制系统具有很强的时变性及非线性,在运行过程中存在的多种干扰易对系统性能调节产生消极影响.为解决上述问题,首先,根据零维内弹道方程推导出压强与喉栓位移之间的数学关系,并结合电机模型推导出系统的传递函数;其次,结合自适应控制和滑模控制设计了一种自适应超螺旋滑模控制器(ASTSMC)以减小系统误差、提高其抗干扰性能,并通过李雅普诺夫函数证明了其稳定性;最后,对ASTSMC进行了多方面的仿真研究.结果表明:ASTSMC的响应速度相较于PID控制器和超螺旋滑模控制器(STSMC)分别提高了 464.6%和 146.2%,并且无超调量;在抗干扰性方面,其控制误差相对于PID控制器和STSMC控制器分别减小 82.4%和 66.7%.
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.
边政;朱铭;王文泽;袁泽建;薛海峰;李映坤;陈雄
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西北工业集团有限公司,西安 710043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
航空航天
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
pintlesolid rocket motorpressure controlnonlinear controladaptive super-twisting sliding mode controller
《固体火箭技术》 2026 (1)
65-73,9
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