飞机全电刹车系统设计与分析  

Design and Analysis on Aircraft Electric Brake System

作　　者：张秋红[1] 李玉忍[1] 

机构地区：[1]西北工业大学自动控制系,陕西西安710072

出　　处：《航空计算技术》2003年第3期97-100,共4页Aeronautical Computing Technique

摘　　要：飞机全电刹车与传统液压刹车的主要不同在于机电作动机构代替了原来的液压活塞机构,且具有带刹车力矩反馈的特点。论文分析了全电刹车系统机电作动器的结构和工作原理,建立系统整体数学模型;对机轮速度和刹车力矩两个反馈信号,分别采用PBM(压力偏调)和PID控制,仿真结果基本符合要求,体现了全电刹车系统的优越性。The main difference between Aircraft electric brake system and the traditional hydraulic brake system is primary hydraulic piston acutator replaced by EMA actuator. The structure and working principle of the electric- mechanical acutator in aircraft electric brake system, which has the characteristic with brake torque feedback, is analyzed in the thesis, and the whole system mathematical model is built. The PBM is applied in wheel-speed control, and the PID is applied in brake-torque control. The result of simulation is satisfying, which shows the superiority of electric brake system.

关 键 词：飞机 全电刹车系统 设计 机电作动器 控制律 

分 类 号：V227.8[航空宇航科学与技术—飞行器设计]