舰载导弹发射舱内燃气流热效应研究

连续发射导弹后,舰载导弹发射舱内的温度会因发射筒的持续散热而明显升高。当舱内温度升幅超过安全温度后,将造成安全隐患。建立了发射筒散热的数学模型,选取了几种典型的导弹发射模式,对发射舱内时间-温度变化过程进行了模拟计算。计算结果表明,在某些饱和发射模式下,发射舱内温度升速较快、升幅较大,甚至超过规定的安全温度。该方法可以在发射舱工程设计前,为发射筒的隔热设计提供理论依据,同时为导弹发射舱内温度监控方案设计提供技术支持。

Numerical simulations of temperature field in shipboard launch compartment

When a missile was launched out,the launch canister walls will adsorb heat from rocket jet flow.After missile taking off,the hot canister will release heat into launch-compartment.In saturation launch conditions,canister can make temperature in launch compartment much higher to exceed the safety temperature in it.Where,the heat transfer equilibrium model in launch compartment is established and,time-temperature process of canisters releasing heat in launch compartment is numerically simulated.Calculation results show that,in several saturation launch situations,temperature in launch compartment is higher than the required safe temperature to make potential danger.Furthermore,this simulation results are able to provide theoretical supports for canister thermal-insulation designs and for the temperature monitor and control designs in launch compartment practically.