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研究了基于Flowmaster软件的直升机压力加油冲击压力仿真建模,将仿真结果与试验结果比较,采用地面压力加油泵进行建模,仿真计算冲击压力值远较试验值大;据此,提出采用恒压源代替地面压力加油泵的建模方法,仿真计算冲击压力值与试验值相差10%左右,满足了直升机压力加油冲击压力的工程计算需要。
Based on the software Flowmaster, simulation modeling of helicopter pressure refueling impact pressure was carried out. The simulation results were compared with the experimental results. The ground pressure pump was used for modeling. The simulation results show that the impact pressure is much larger than the experimental value. Source instead of ground pressure pump modeling method, the simulation calculation of the impact pressure value and the test value difference of about 10%, to meet the helicopter pressure fuel injection pressure engineering needs.