摘要
为了对着陆缓冲火箭发动机进行优化设计，提出了优化准则、目标函数及设计变量的约束条件；研究了着陆缓冲发动机总冲量及在阻力伞存在的条件下发动机点火高度优化方法；在多元回归基础上建立了发动机的能量方程，并提出分部件建立质量方程。优化设计实例计算结果达到了预期目标。
n order to optimize the design of landing buffer solid rocket motors, the optimization criteria, objective functions, constraint conditions for the design are suggested. The optboization method of the total impulse and firing altitude of the motor with a resistance parachute is studlied. The energy equations of the motor based on the polynary element regression and the mass equations of the components are established. The calculation results of the optimized design sample come to expected target.
出处
《固体火箭技术》
EI
CAS
CSCD
1995年第4期8-12,共5页
Journal of Solid Rocket Technology
基金
航天基金
关键词
软着陆
固体推进剂
火箭发动机
拦阻装置
Terms Soft landing
Optimum design
Solid propellant rocket engine
Arreting gear.
