摘要
针对航空武器装备特种冲击波形加载需求,基于小孔节流阻尼原理设计了一款具有30×45个可调节小孔的冲击波形发生器,建立了该波形发生器动力学方程,采用四阶龙格库塔法对加载波形进行了仿真,并进行试验验证。结果表明,该波形发生器性能达到了模拟12g/200ms标准半正弦波指标要求,并在某舰载外挂物弹射拦阻冲击试验和直升机座椅垂向冲击试验中进行了应用,为航空武器装备的特种冲击试验提供了一种验证装置和试验方法。
According to the requirements of special shock test for aviation weapon equipment, a shock wave generator with 30 × 45 adjustable small holes was designed based on the principle of orifice throttling and damping.The dynamic equation of the waveform generator was established. The loading waveform was simulated by the fourthorder Runge Kutta method, and the experimental verification was carried out. The results show that the performance of the waveform generator can meet the requirements of simulating 12 g/200 ms standard half sine waveform, and has been applied in the shock test of an aircraft external store and the vertical impact test of helicopter seat, which provides a verification device and test method for the special impact test of aviation weapon equipment.
作者
杨强
白春玉
刘小川
常选仓
刘冲冲
Yang Qiang;Bai Chunyu;Liu Xiaochuan;Chang Xuancang;Liu Chongchong(Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics,AVIC Aircraft Strength Research Institute,Xi’an 710065,China;The 29th Research Institute CETC,Chengdu 610036,China)
出处
《航空科学技术》
2020年第12期48-54,共7页
Aeronautical Science & Technology
