Abstract
Aiming at the actuation system force fight problem resulted from active-active operational mode of fly-by-wire aircraft, and considering the technical maturity and reliability from safety aspect, the inertial integration algorithm and PI control law are established. After tradeoff study on these two methods, the PI control law is selected lastly.By physical model equivalent transformation, mechanical kinetics analysis, position closed-loop servo control modeling and AMEsim modeling and simulation analysis of the actuation system, the results show that using PI control can make the static force fight almost decrease to zero, make the dynamic force fight decrease to 1.288 9×106 Pa, 62.58% lower than requirement.It demonstrates the feasibility of the designed PI control law, and can be taken as the theoretic evidence of the forthcoming force fight equalization test on test rig.
Highlights
根据 作动器位置闭环伺服控制模型, 通 过 AMEsim 仿真软件搭建的作动器闭环伺服控制及力 纷争均衡模型如图 4 所示。
Fractional Order Modeling and Control of Dissimilar Redundant Actuating Sys⁃ tem Used in Large Passenger Aircraft[ J]
Aiming at the actuation system force fight problem resulted from active⁃active operational mode of fly⁃by⁃ wire aircraft, and considering the technical maturity and reliability from safety aspect, the inertial integration algo⁃ rithm and PI control law are established
Summary
根据 作动器位置闭环伺服控制模型, 通 过 AMEsim 仿真软件搭建的作动器闭环伺服控制及力 纷争均衡模型如图 4 所示。 模拟飞机在地面,无气动载荷,输入阶跃信号, 研究系统响应。 仿真时间设置为 5 s,仿真步长为 0.05 s。 仿真开始时 2 个系统的外部输入指令均为 0 V,0.5 s 时作动系统 1 外部输入指令变为 4 V,作 动系统 2 外部输入指令变为 1 V,分别对 2 种情形 进行仿真,未启用 PI 控制仿真结果如图 5 至 6 所 示,启用 PI 控制仿真结果如图 7 至 8 所示。 模拟飞机 在 空 中, 输入正弦信号, 研究系统响应。 仿真时间设置为 3 s,仿真步长为 0.05 s。 仿真 开始时作动器 1 外部输入指令为 0.1 V,0.5 Hz 正弦 波;作动器 2 外部输入指令为 0.4 V,0.5 Hz 正弦波; 1.5 s 时施加 1t 的气动载荷。 分别对 2 种情形进行 仿真,未启用 PI 控制仿真结果如图 9 至 所示,启 用 PI 控制仿真结果如图 至 所示。
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
