大口径火箭增程炮弹发动机结构的受热分析

Thermal Analysis of the Engine Structure of Large Caliber Rocket Extended Range Projectile

火箭增程炮弹的火箭发动机装药燃烧较快,一般在2s左右,导致燃烧室短时间内的压强和温度较高。为此,本文基于有限元法和热分析方法对火箭增程炮弹发动机燃烧室壳体进行了受热分析。首先,主要分析了火箭弹的结构;其次,选用固体火箭发动机分别进行了以合金钢、铝合金、铜合金为材料的3种瞬态热分析,改进了火箭增程炮弹发动机燃烧室并进行了瞬态热分析对比。结果表明,合金钢的隔热性能最佳,其次是铝合金,并且燃烧室的容积越大,温度上升速率越小。

The rocket motor charge of the rocket extended range projectile burns faster,generally about 2 s,resulting in higher pressure and temperature in the combustion chamber within a short period of time.For this reason,this paper is based on the finite element method and thermal analysis method for the conducts thermal analysis on the combustion chamber shell of the rocket extended range projectile motor.Firstly,mainly analyzes the rocket structure.Secondly,selects the solid rocket motor,conducts three kinds of transient thermal analysis using alloy steel,aluminum alloy and copper alloy as materials,improves the combustion chamber of the rocket extended range projectile motor,and conducts a comparison of transient thermal analysis.The results show that the thermal insulation performance of alloy steel is the best,followed by aluminum alloy,and the larger the combustion chamber volume,the smaller the rate of temperature rise.