摘要
为延长导弹压缩空气弹射的有效推力行程,提出一种新型两级提拉式单侧冷弹射方案。采用Peng-Robinson真实气体方程,建立了弹射内弹道模型;在Simulink中搭建内弹道求解模块、在ADAMS中建立了冷弹射方案的虚拟样机,以气缸输出力、气缸位移和速度为状态变量,实现联合仿真,获得了内弹道参量的变化规律,并基于小型原理样机试验对仿真结果进行了验证。验证结果表明:第1级低压室压强先升后降;气缸换级过程中,低压室温度、压强与导弹加速度发生突变,但对导弹速度、位移影响较小。以气源容积最小为目标函数,选定约束条件和设计变量,应用遗传算法进行优化设计。优化后的气源容积降低了64.5%,优化结果大大提高了发射装置的机动性。研究结果验证了新型两级提拉式单侧冷弹射方案的可行性。
A kind of one-side ejection device with two-step cylinder is proposed to increase the effective thrust travel of missile pneumatic launching system. The real gas state equation,Peng-Robinson equation,is used as theoretical basis. The mathematical expressions of pneumatic interior ballistics model are deduced on the basis of ＇P-R＇ state equation for the two-step cylinder. The interior ballistics equation is solved by using Simulink software,and the one-side launching ejection is built by means of ADAMS. The co-simulation model of device is achieved. The results show that the pressure of first-order lower-chamber rises first and then falls. It can be seen from the calculated result that both the thermodynamic parameters and the missile acceleration obviously fluctuate in the process of cylinder changing,but their influences on missile speed and displacement are very small. To reduce the equipment volume,the air source volume is selected as the objective function. The air source volume optimized by genetic algorithm is de-creased by 64. 5%,thus improving greatly the mobility of launcher.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2017年第3期466-475,共10页
Acta Armamentarii
基金
国家国防科技工业局技术基础科研项目(B2620116005)
江苏省普通高校研究生科研创新(实践)计划项目(KYLX15_0328)
