飞机空中加油系统压力冲击抑制优化仿真

摘要

硬管式空中加油系统在应急脱开时,由于加油接头快速关闭,燃油流量在短时间内从最大流量减小为零,会在加油接头处产生强烈的压力冲击,可能造成空中加油系统结构破坏,严重时危及加、受油机飞行安全,已成为硬管式空中加油系统设计的关键问题.为了探究某型飞机硬管式空中加油系统的压力冲击抑制特性,首先分析了系统压力冲击产生机理及抑制因素,建立了系统主要附件的数学模型以及系统仿真模型,然后分别对停止加油三种情况冲击压力以及缓冲装置和旁路阀、溢流阀等系统主要附件压力冲击抑制性能进行了仿真研究.仿真结果表明,系统最大冲击压力出现在应急脱开停止加油时,缓冲装置对压力冲击抑制起主要作用,旁通阀和溢流阀也可抑制压力冲击,但作用不明显.%At the emergent moment of disengaging of boom aerial refueling system disengaging,the nozzle closes up fleetly and the flow rate reduces from max to zero abruptly,which cause strong shock of pressure near the nozzle,and may bring on structural breakage of the system,or even endanger the flight safety of airplane while serious status.In order to explore the restraining characteristic of pressure shock of the boom aerial refueling system,firstly we analysised the generating mechanism and the restraining factor,established the mathematical model of main accessory and the simulation model of the system,and then simulated the pressure shock of three conditions of finishing refueling and the restraining characteristic of the main accessory including the boot,the bypass valve and the level control valve.The results show the maximal pressure shock of the system comes into being at the moment of emergent disengaging,the boot plays an important role of restraining pressure shock,and the bypass valve and the level control valve can also reduce pressure shock,but the effect is not obvious.