燃气发生器弹射特性数值仿真与试验研究

Numerical Simulation and Experimental Study on Ejection Characteristics of Gas Generator

为了研究燃气发生器弹射特性,基于改性双基固体推进剂装药结构和燃气发生器参数,建立了燃气底推弹射形式的数学模型,利用四阶龙格库塔法对数学模型进行求解,获得了燃气发生器弹射参数变化特性,结果表明:在常温条件下,载荷出简时的行程为7.7m,需要时间为0.53s,载荷出筒速度为31.1m/s,最大加速为81.7m/s^(2),满足弹射要求;同时,发现环境温度对燃气发生器弹射参数较大影响,随着环境温度增加,低压室压力峰值增加,载荷出筒时间缩短,出筒速度和最大过载增加;与常温弹射试验结果对比,低压力的压力峰值最大误差为5.2%,导弹载荷出筒速度最大误差为5.4%,表明所建立的燃气发生器弹射模型能够准确描述导弹载荷弹射参数特性。

In order to study the ejection characteristics of the gas generator,based on the charge structure of the modified double-base solid propellant and the parameters of the gas generator,a mathematical model of the ejection form of the gas bottom push was established.The fourth-order Runge-Kutta method was used to solve the mathematical model,and the variation characteristics of the ejection parameters of the gas generator were obtained.The results show that at normal temperature conditions,the missile load moved 7.7m in 0.53s,with a launching velocity of 31.1m/s,and the maximum acceleration is 81.7 m/s^(2),which meet the ejection requirements.In addition,the ambient temperature has a great influence on the ejection parameters of the gas generator.With the increase of the ambient temperature,the peak pressure of the low-pressure chamber of the launcher canister increases,the ejecting time of the missile load decreases,and the ejecting speed and the maximum overload increase.Compared with the normal temperature ejection experimental results,the maximum error of low-pressure peak pressure is 5.2%,and the maximum error of missile load velocity is 5.4%.It indicates that the established gas generator ejection model can describe the ejection parameter characteristics of missile load accurately.