固体火箭发动机三维药柱燃面推移仿真技术及燃面通用计算方法  

The General Technique of Emulation and Calculating of Burning Surface of 3-D Grain of Solid Rocket Motors

作　　者：方蜀州[1] 胡克娴[1] 

机构地区：[1]北京理工大学,北京10081

出　　处：《固体火箭技术》1993年第4期10-20,共11页Journal of Solid Rocket Technology

摘　　要：采用实体造型方法进行固体火箭发动机药柱三维复杂内腔推移的仿真和燃面计算,为固体火箭发动机设计提供了前所未有的设计分析手段,减少了计算的繁琐和困难.这种方法能够分析的装药结构形式十分广泛,与现有的燃面计算方法(内弹道计算法、有限元素法、边界拟合坐标法)比较,具有输入简便灵活、几何燃面计算准确、输出信息完备等优点.An emulating modelling method has been applied in emulation of a complex3-D grain of solid rocket motors and calculation of its burning area.The unprecedenteddesign and analysis method,reducing numerous and difficult calculation,has been pres-ented for design of solid rocket motors.It can be used for analysis of various grain.Com-pared with the existing calculation method of burning area(ie:internal ballisticscalculation,finite-element method,boundary fitting coordinate method),this method hasadvantages of easy and flexible inputting,accurate calculating of geometric area of burningand complete output information etc.

关 键 词：火箭发动机 仿真 推进剂药柱 

分 类 号：V435.21[航空宇航科学与技术—航空宇航推进理论与工程]