全飞行剖面下的航空液压泵热载荷分析与温度预测

Thermal Load Analysis and Temperature Prediction of Aviation Hydraulic Pump Under Full Flight Profile

基于理论分析和仿真实验,研究了影响航空液压泵温度变化的因素。首先,对航空液压泵的基本情况进行了简述,通过数学建模建立了航空液压泵的效率模型,对泵的功率损失进行了详细分析;然后,利用控制体方法建立了描述泵的各部分温度变化的热力学模型,通过理论计算分析了泵在不同工况下的温度变化;在此基础上,利用MATLAB对航空液压泵在飞行剖面下的温度变化进行了仿真计算。研究结果对泵的温度预测和控制具有指导意义。

Based on theoretical analyses and simulation experiments,the factors that affect the temperature change of aviation hydraulic pumps are studied.First,the basic situation of aviation hydraulic pump is briefly described.The efficiency model of aviation hydraulic pump is established through mathematical modeling,and the power loss of the pump is analyzed in detail.Then,the thermodynamic model describing the temperature change of each part of the pump is established by the control body method,and the temperature change of the pump under different working conditions is analyzed by theoretical calculation.On the basis of the above works,MATLAB is used to simulate the temperature change of the aviation hydraulic pump under the flight profile.The main research results have the important guiding significances for the prediction and control of the pump temperature.