摘要
为减少飞机液压系统故障,从温度控制层面对飞机液压伺服舵机进行热力学分析。将液压伺服舵机的物理模型简化为伺服阀控制作动筒的形式,建立液压伺服舵机热力学模型。根据热力学第一定律,采用集中参数法建立热力学方程。基于MATLAB平台,采用龙格-库塔法对舵机热力学模型进行编程仿真计算,得出舵机各节点温度分布曲线。将仿真结果与实验数据进行了对比,对比结果验证了飞机液压伺服舵机热力学模型的正确性,该模型可应用于飞机液压系统动态温度计算。
A thermodynamic analysis method was adopted to hydraulic servo steering units in temperature controlling for reducing aircraft hydraulic systems failure.A hydraulic servo steering units can be simplified to a servo valve and an actuator cylinder.Based on the first law of thermodynamics,the thermodynamic model of hydraulic steering units for aircraft was established.And the thermodynamic differential equations set of the model were derived with lumped parameter method,and solved by Runge-Kutta method.Simulations of hydraulic servo steering thermodynamics model were carried out by employing MATLAB software.And the calculation results coincide with the experimental data.The model presented herein can be used to calculate the dynamic temperature of aircraft hydraulic systems.
出处
《中国机械工程》
EI
CAS
CSCD
北大核心
2015年第15期2070-2074,2080,共6页
China Mechanical Engineering
基金
国家自然科学基金资助项目(51275356)
工业和信息化部大型客机专项课题资助项目(MJF201302)
关键词
飞机
液压伺服舵机
热力学模型
仿真
aircraft
hydraulic steering units
thermodynamic model
simulation
