固体姿轨控发动机变工况过程推力不确定性分析
2025,47(1):94-104
高经纬
国防科技大学 空天科学学院, 湖南 长沙 410073
贾军凯
国防科技大学 空天科学学院, 湖南 长沙 410073 ;
河北工业大学 机械工程学院, 天津 300401
武泽平
国防科技大学 空天科学学院, 湖南 长沙 410073
张德权
国防科技大学 空天科学学院, 湖南 长沙 410073 ;
河北工业大学 机械工程学院, 天津 300401
张杰
国防科技大学 空天科学学院, 湖南 长沙 410073
张为华
国防科技大学 空天科学学院, 湖南 长沙 410073
国防科技大学 空天科学学院, 湖南 长沙 410073
贾军凯
国防科技大学 空天科学学院, 湖南 长沙 410073 ;
河北工业大学 机械工程学院, 天津 300401
武泽平
国防科技大学 空天科学学院, 湖南 长沙 410073
张德权
国防科技大学 空天科学学院, 湖南 长沙 410073 ;
河北工业大学 机械工程学院, 天津 300401
张杰
国防科技大学 空天科学学院, 湖南 长沙 410073
张为华
国防科技大学 空天科学学院, 湖南 长沙 410073
摘要：
为探究喉栓式固体姿轨控发动机推力动态性能可靠性，考虑燃气阀几何参数不确定性对固体姿轨控发动机变工况过程推力性能不确定性开展研究。结合固体姿轨控发动机工作原理、推力数学模型和零维内弹道方程构建发动机变工况过程推力计算模型。在此基础上，根据固体姿轨控发动机阀门几何参数不确定性模型，采用蒙特卡罗模拟法进行不确定性传递，获取喉栓瞬时运动后推力不确定性随时间的变化规律，实现变工况过程推力不确定性分析，并对不确定性变量进行重要度排序。量化评估固体姿轨控发动机实时调节过程中的推力不确定性，可以为固体姿轨控发动机控制系统提供更合理的设计要求，在满足设计需求的同时节省研制成本。
为探究喉栓式固体姿轨控发动机推力动态性能可靠性，考虑燃气阀几何参数不确定性对固体姿轨控发动机变工况过程推力性能不确定性开展研究。结合固体姿轨控发动机工作原理、推力数学模型和零维内弹道方程构建发动机变工况过程推力计算模型。在此基础上，根据固体姿轨控发动机阀门几何参数不确定性模型，采用蒙特卡罗模拟法进行不确定性传递，获取喉栓瞬时运动后推力不确定性随时间的变化规律，实现变工况过程推力不确定性分析，并对不确定性变量进行重要度排序。量化评估固体姿轨控发动机实时调节过程中的推力不确定性，可以为固体姿轨控发动机控制系统提供更合理的设计要求，在满足设计需求的同时节省研制成本。
基金项目：
国家自然科学基金资助项目（52375278，52005502）
国家自然科学基金资助项目（52375278，52005502）
Uncertainty analysis of thrust during variable operating condition process of solid divert and attitude control motor
GAO Jingwei
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
JIA Junkai
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China ;
School of Mechanical Engineering, Hebei University of Technology, Tianjin 300401 , China
WU Zeping
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
ZHANG Dequan
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China ;
School of Mechanical Engineering, Hebei University of Technology, Tianjin 300401 , China
ZHANG Jie
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
ZHANG Weihua
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
JIA Junkai
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China ;
School of Mechanical Engineering, Hebei University of Technology, Tianjin 300401 , China
WU Zeping
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
ZHANG Dequan
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China ;
School of Mechanical Engineering, Hebei University of Technology, Tianjin 300401 , China
ZHANG Jie
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
ZHANG Weihua
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
Abstract：
To investigate the dynamic uncertainty of thrust of the pintle SDACM (solid divert and attitude control motor), the study focuses on the uncertainty of the thrust performance during variable operating conditions of the SDACM was carried out with the consideration of the uncertainties of the geometric parameters of the pintle gas valve. Computation model of the thrust during variable operating condition process of the SDACM was established by combining the working principle of the SDACM, the regular mathematical model of thrust and the zero-dimensional internal ballistic equation. On this basis, the uncertainty propagation was performed by Monte Carlo simulation method according to the uncertainty models of the geometry parameters of the SDACM, and the variation law of the thrust uncertainty over time after the transient motion of the pintle was obtained, thereby the uncertainty analysis of the thrust in the process of variable operating conditions was realized, and the uncertainty variables were weighted in order of importance. Quantification and evaluation of thrust uncertainty in the real-time regulation process of the SDACM can provide more reasonable design requirements for the control system, and save the development cost of the SDACM while meeting the design requirements.
To investigate the dynamic uncertainty of thrust of the pintle SDACM (solid divert and attitude control motor), the study focuses on the uncertainty of the thrust performance during variable operating conditions of the SDACM was carried out with the consideration of the uncertainties of the geometric parameters of the pintle gas valve. Computation model of the thrust during variable operating condition process of the SDACM was established by combining the working principle of the SDACM, the regular mathematical model of thrust and the zero-dimensional internal ballistic equation. On this basis, the uncertainty propagation was performed by Monte Carlo simulation method according to the uncertainty models of the geometry parameters of the SDACM, and the variation law of the thrust uncertainty over time after the transient motion of the pintle was obtained, thereby the uncertainty analysis of the thrust in the process of variable operating conditions was realized, and the uncertainty variables were weighted in order of importance. Quantification and evaluation of thrust uncertainty in the real-time regulation process of the SDACM can provide more reasonable design requirements for the control system, and save the development cost of the SDACM while meeting the design requirements.
收稿日期：
2023-09-28
2023-09-28
