探空火箭动力系统优化设计  

DESIGN OPTIMIZATION OF PROPULSION SYSTEM OF SOUNDING ROCKET

作　　者：袁书生[1] 方丁酉[2] 代绪恒 

机构地区：[1]海军航空工程学院,烟台264001 [2]国防科技大学,湖南长沙410073

出　　处：《固体火箭技术》1992年第4期1-8,共8页Journal of Solid Rocket Technology

摘　　要：提出了探空火箭动力系统设计参数优化计算方法.综合考虑了动力系统与火箭外弹道之间的关系.在给定有效载荷、最高射高的条件下,选取动力系统的设计参数使火箭的起飞质量最小.选用了增广拉格朗日法约束优化技术和牛顿迭代法求解数学模型.计算结果表明,该计算方法是合理的.An calculating method for design parameter optimization of the propulsion system of the sounding rocket is given. The relation between the propulsion system and the exterior ballistics of the rocket is taken into account. Under the conditions of the given payload and the highest launching height, the design parameters of the propulsion system are selected to minimize takeoff mass of the rocket. The extended Lagrangian method is used for restraining the optimization technique and Newton iterative method for solving the mathematical model. The results have shown that the calculating method is rational.

关 键 词：探空火箭 最优 设计 参数 最佳化 

分 类 号：V421.4[航空宇航科学与技术—飞行器设计]