战术火箭/固体火箭发动机一体化优化设计  

INTEGRAL OPTIMIZATION DESIGN FOR TACTICAL ROCKET AND IT’S SRM BY UTILIZING THE SYNTHESIS OF INTERNAL BALLISTICS AND TRAJECTORY

作　　者：杨军 陈汝训 赵锡良 

出　　处：《宇航学报》1999年第1期21-27,共7页Journal of Astronautics

摘　　要：在综合考虑发动机内弹道性能与火箭外弹道关系的情况下，融内外弹道为一体，系统分析了发动机装药参数、燃烧室设计参数、喷管设计参数、尾翼参数对发动机性能及全弹性能的影响，针对远程战术火箭，建立了火箭总体／固体火箭发动机一体化优化设计的数学模型。在所建模型基础上，以火箭弹总体性能最佳为目标，对总体和发动机设计参数以及药柱几何参数同时进行优选，完成了九个变量的寻优计算，取得了满意结果。Considering of SRM internal ballistic property and rocket trajectory,a set of mathematical models about rocket overall performance and solid rocket motor integral optimization design for the long range tactical rocket are developed.Based on these models,a process of searching for the optimum system property is demonstrated by simultaneous optimization of the rocket frame parameters,motor design parameters and grain configuration para meters.With 9 variables,optimizing calculations are finished and the results are satisfactory.This paper integrates the SRM internal ballistic parameters and trajectory parameters together and systematically analyzes the effect of grain configuration parameters,chamber and nozzle design parameters,and empennage parameters on the rocket and motor performance.

关 键 词：战术火箭 固体火箭发动机 一体化设计 优化设计 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] TJ761.1[兵器科学与技术—武器系统与运用工程]