固体火箭发动机稳态燃速二维模型参数最优化辨识

Optimization identification for steady burning rate 2-D model of solid rocket motor

关键词:  固体火箭发动机  稳态燃速~~+  驼峰效应~~+  侵蚀燃烧  最优化辨识~~+  混合优化方法~~+

Key words:  Solid rocket motor  Steady burning rate~+  Hump effect~+  Erosive burning  Optimization identification~+  Hybrid optimization method~+

摘要:

为提高固体火箭发动机内弹道性能预示精度,综合考虑侵蚀燃烧和驼峰效应对复合推进剂稳态燃速的影响,建立了稳态燃速二维模型,将燃速模型参数辨识问题转化为非线性规划问题求解,采用Powell方法和并行遗传算法组成的混合优化方法提高了非线性规划问题求解的效率和质量,得到了稳态燃速模型参数的全局最优化辨识值,最优化辨识过程和结果不受待辨识参数初值的影响。计算和实验结果的对比表明,实验发动机采用高体积装填分数、大长径比翼柱形装药和低燃速复合推进剂,侵蚀燃烧和驼峰效应显著,稳态燃速二维模型合理。

Abstract:

To predict the internal ballistic property of the solid rocket motor more accurately,the steady burning rate(2-D) model of the composite propellant was set up by taking into account the affect of the hump effect and erosive burning,the burning rate model parameter identification can be converted into nonlinear programming problem which can been solved by hybrid optimization method composed of Powell optimization method and genetic algorithms.The solution efficiency of the optimization problem can been improved by the distributed parallel performance of the genetic algorithms.The global optimum solution of the steady burning rate 2-D model parameter was gained.The optimization identification process and result are more robust with the model parameter initial value.Results show that the effect of the hump and erosive burning must been taking into account for experimental motor because of the high volumetric loading fraction,high length to diameter ratio,and low burning rate composite propellant.It also shows that steady burning rate 2-D model is feasible.