【摘要】 以阀控低速大扭矩液压马达驱动多管火箭发射系统的回转机构为研究对象,建立了扭转振动响应与液压马达参数的关系。通过对马达参数和扭转冲击响应的计算分析,表明增大油腔工作压力和减少不溶气体的渗入量可以提高系统的动态扭转刚度,回转机构的冲击角速度随着旁路节流阻尼孔的增大而减小;另外,增加合适的节流孔基本上不改变系统的动态扭转刚度。说明在发射系统其它参数不变的情况下,可通过调整液压马达的旁路节流孔实现对回转结构抗燃气射流冲击振动的控制。更多还原

【Abstract】 Swing mechanism of multiple launch rocket system driven by low speed and high torque hydraulic motor was taken as research object.The relationship between torsion vibration response of swing mechanism and the parameters of hydraulic motor was(established).From calculation and analysis of torsion vibration response of swing mechanism and the parameters of hydraulic motor,it is found that the symmetric dynamic torsion rigidity can be enhanced by increasing working liquid pressure or decreasing inleakage of insoluble gas,the impact angle velocity of swing mechanism reduces along with the opening area of by-pass throttle added.The systematic dynamic torsion rigidity isn’t changed by adding proper throttle.Therefore,when other parameters of launching system are unchangeable,adjusting the opening area of by-pass throttle can control of impact vibration of swing mechanism caused by rocket exhaust.更多还原