考虑油液黏压特性的高压航空液压泵柱塞副泄漏模型研究

 提高机载液压系统压力可以提高液压系统功率密度，但是随着航空液压泵转速增大和压力增高，关键摩擦副之一的柱塞副磨损加剧，泄漏量增大。提出了一种考虑油液黏压特性的高压航空液压泵柱塞副泄漏量模型。结合Barus液压油液黏压公式，在经典泄漏量公式的基础上进行一定程度的补充和修正，以便更精确的计算高压航空液压泵柱塞副各种磨损程度下的泄漏量。仿真结果表明，系统压力达到35 MPa，黏度变化导致的泄漏量变化不可忽略。

Leakage Model Considering Viscosity pressure Properties of Oil for Piston cylinder Pair of High Pressure Aviation Hydraulic Pump

Increasing the pressure of the hydraulic system can improve the power density of the hydraulic system. However, with the increase of the speed of the hydraulic pump and the increase of pressure, the wear of the piston cylinder pair, one of the key friction pairs, is aggravated and the leakage is increased. A leakage model of piston cylinder pair in a high pressure aviation hydraulic pump is presented in this paper, considering the pressure viscosity properties of oil. Combined with the Barus pressure viscosity properties formula, this model is supplemented and modified to a certain extent on the basis of the classical leakage formula, so as to more accurately calculate the leakage of the high pressure aviation hydraulic pumps piston cylinder pair in various wear degrees. The simulation results show that the pressure of the system reaches 35 MPa, and the change of leakage caused by viscosity change can not be ignored.