热损失对燃气蒸汽式发射动力系统内弹道计算影响  

Influence of heat loss on internal ballistic calculation of the gas-steam launching power system

作　　者：程栋 李鹏永 闫晴霄 强新伟 CHENG Dong;LI Pengyong;YAN Qingxiao;QIANG Xinwei(Zhengzhou Mechano-Electrics Engineering Institute, Zhengzhou 450015, China)

机构地区：[1]郑州机电工程研究所,郑州450015

出　　处：《固体火箭技术》2018年第3期395-402,共8页Journal of Solid Rocket Technology

摘　　要：传统发射动力系统使用定能量系数修正内弹道计算模型,提高了内弹道特征值计算精度,但内弹道参数曲线计算值与测试值存在一定偏差。某型燃气蒸汽式发射动力系统发射筒内压力计算值与测试值存在一定的偏差,经分析内弹道模型中假设能量系数为常数是造成发射筒内压力计算偏差的主要因素。为了获得能量系数随时间的变化规律,通过使用热损失经典算法和试验研究相结合的方法,对发射动力系统工作过程中的热损失进行了计算研究,发射动力系统总的热损失为32 969.6 kJ,能量系数随发射动力系统工作逐渐增加。使用变能量系数修正内弹道计算模型对发射内弹道进行计算,计算结果表明变能量系数可有效提高导弹发射筒内压力的计算精度,同时经过分析燃气发生器和弯管仍具有降低热损失的潜力。The internal ballistic calculation of traditional launching power system is corrected by the constant energy coefficient,which improves the calculation accuracy of the interior ballistic characteristic value,but the deviation of interior ballistic parameter curve between the calculation value and the test one still exists. The deviation of launching cylinder pressure between the calculation value and the test one still exists in the gas-steam launching power system.The energy coefficient is the main factor of the calculation deviation,which is a constant in the previous internal ballistic calculation model,according to the data.The variable energy coefficient with the time is obtained after calculating the thermal loss for the gas-steam launcher,the total heat loss of the launching power system is 32 969.6 kJ by combining the classical algorithm with the experimental study.The internal ballistic model is corrected by replacing the constant energy coefficient with a variable one.The revised calculation results showed that the accuracy was improved effectively by using the variable energy coefficient,At the same time,the gas generator and elbow still have the potential to reduce heat loss.

关 键 词：燃气-蒸汽式发射动力系统 能量系数 发射筒内压力 内弹道 

分 类 号：V553[航空宇航科学与技术—人机与环境工程]