摘要
为保证导弹平稳出筒,对以燃气-蒸汽为发射动力的发射内弹道计算模型进行了改进,并以某型潜射导弹为例对计算模型进行了仿真计算。结果表明,改进后的模型能够有效降低导弹出筒时刻筒内气体工质的压力,从而实现导弹平稳出筒。这对燃气-蒸汽发射动力系统的设计具有一定的参考价值。
To make the missile leave canister smoothly, launching interior ballistic computation model which adopts gas and steam as launching power was improved. Simulation was done about the computation model by taking one submarine-launched missile for example. Results indicated that the improved model could reduce the gas pressure effectively when missile leaves canister, which made the missile leave canister smoothly. This is of reference value for the design of gas and steam launching power system.
出处
《导弹与航天运载技术》
北大核心
2011年第6期40-42,共3页
Missiles and Space Vehicles
关键词
燃气-蒸汽发射动力系统
潜射导弹
发射内弹道
Gas and steam launching power system
Submarine-launched missile
Launching interior ballistic
