Preliminary design and optimization of slotted tube grain for solid rocket motor

作     者：K Nisar LIANG Guo-zhu A Kamran 

作者机构：School of AstronauticsBeijing University of Aeronautics and Astronautics Beijing 100191 China 

出 版 物：《航空动力学报》 (Journal of Aerospace Power)

年 卷 期：2008年第23卷第12期

页      码：2332-2340页

摘      要：In this paper,design and optimization technique of slotted tube grain for solid rocket motors has been *** doing so,the design objectives and constraints have been set,geometric parameters identified,performance prediction parameters calculated,thereafter preliminary designs completed and finally optimal design *** model for slotted tube grain configuration has been *** thrust has been taken as the objective function with constraints of burning time,mass of propellant,fixed length and diameter of chamber *** parameter method has been used for calculating the performance prediction parameters.A set of preliminary designs has been completed and an analysis of these results *** all the preliminary results fulfill the design requirements in terms of objective function and constraints,however in order to attain the optimal design,Sequential quadratic programming optimization technique has been *** the slotted tube grain geometry is totally dependent upon various independent variables and each of these variables has a bearing on explicit characteristic of grain designing,hence affects of the independent variables on performance parameters have been examined,thus variation laws have been *** on the variation laws and the analysis of preliminary design results,upper and lower limits have been defined for the independent geometric variables and an initial guess provided for conducting *** attained exhibits that an optimal result has been attained and the value of objective function has been *** the design constraint limits have also been met while ensuring sound values of volumetric loading fraction,web fraction and *** methodology of design and optimization of slotted tube grain for solid rocket motors can be used by engineers as a reference guide for actual design and engineering purposes.

主 题 词：固体火箭 发动机 动力系统 设计方案 

学科分类：08[工学] 080502[080502] 0805[工学-能源动力学] 

核心收录：

D　O　I：10.13224/j.cnki.jasp.2008.12.029

馆 藏 号：203402411...