某飞机火箭控制盒隔振设计与试验

针对某飞机火箭控制盒过振动问题,设计了一套专用的隔振装置。首先通过隔振理论计算了6组不同固有频率和放大倍数的隔振性能,综合考虑隔振性能和耐久性寿命要求选定隔振参数,并计算隔振器的刚度和阻尼;然后针对隔振装置的核心元件,设计了4种不同硬度胶体配方并分别试制了4只试样;基于电子万能材料试验机,对试样进行了刚度和迟滞回线测试,获得胶体刚度和阻尼随硬度变化规律,再根据理论分析所需隔振器参数,拟合得到所需胶体的硬度,并用样件验证;最后基于电磁振动台,设计了一套隔振系统,进行振动功能和振动耐久性寿命考核。试验结果表明:所设计隔振装置的性能可以满足该火箭控制盒的隔振设计要求。

Design and Test of Vibration Isolation System for an Aircraft Rocket Firing Unit

In order to solve the problem of excessive vibration of an aircraft rocket firing unit, a special vibration isolation system is designed. Firstly, six groups of vibration isolation performance with different natural frequencies and amplification factors are calculated by the vibration isolation theory. Considering the requirements of vibration isolation performance and durability life, the vibration isolation parameters are selected, and the stiffness and damping of the isolator are calculated. Secondly, according to the core components of the vibration isolation system, four rubber formulations with different hardness were designed and four specimens were prepared respectively. Based on a universal testing machine, the stiffness and hysteresis loops of these specimens were tested. The variation of stiffness and damping of rubber damper with hardness was obtained. Then, according to the properties of the vibration isolation system calculated before, the hardness of the required rubber is obtained by fitting and verified. At last, based on the electromagnetic shaking table, a vibration isolation system was designed to verify the vibration isolation performance and vibration durability life. The test results show that the performance of the designed vibration isolation system can meet the requirements of the aircraft rocket firing unit.