二次点火发动机最优增程设计与分析

Optimized research and analysis on range-extend principle for re-ignition solid rocket motors

关键词:  火箭弹  固体推进剂火箭发动机  脉动式火箭发动机  最大射程  最优设计

Key words:  Rocket projectile  Solid propellant rocket engine  Impulse rocket engine  Maximum firing range  Optimum de- sign

摘要:

研究了采用二次点火发动机对火箭弹进行增程的最优设计方法与设计原理,用罚函数法把约束条件构成统一的目标函数,再用直接寻优法进行计算,分析了火箭弹倾角、再点火时间及总冲分配等因素对射程的影响。结果表明,二次点火发动机技术可以实现远程火箭弹增程最大的设计要求,且最优发射角对射程影响极大;总冲分配最佳时,总的阻力消耗最小,增程率越大;再点火时间的影响相对较弱。同时还比较了二次点火发动机工作时的火箭弹弹道与一般弹道的区别,及其对阻力和射程的影响。

Abstract:

Optimization design approach and principle of range extend rocket with re-ignition rocket motors were researched. By which effects of tilt angle of re-ignition motor rocket, re-ignition time and proportion of total impulse on range were analyzed, alteration regularities between re-ignition motors’ parameters and optimized range were derived. The ballistic trajectory, atmospheric resistance and range of rocket projectiles with re-ignition solid rocket motors were compared with that of conventional rocket projectiles. The results may present useful reference for design of similar motors and rocket projectiles.