基于EMD及闭环测试的飞机直接升力控制系统设计  

Design of Aircraft Direct Lift Control System Based on EMD and Closed-Loop Testing

作　　者：陈宣文[1] 孟强 黄晖[1] CHEN Xuanwen;MENG Qiang;HUANG Hui(Xi'an Astronautics Computing Technique Research Institute,AVIC,Xi'an 710068,china)

机构地区：[1]航空工业西安航空计算技术研究所,西安710068

出　　处：《计算机测量与控制》2024年第9期157-162,169,共7页Computer Measurement &Control

基　　金：航空科学基金项目(20182C31553)。

摘　　要：飞机直接升力水平不均会造成飞机飞行偏航问题,为实现对飞机飞行能力的有效控制,设计基于EMD及闭环测试的飞机直接升力控制系统;在FSEU架构中,设置ARINC429总线闭环机制,联合伺服控制模块与实时机载终端,实现飞机直接升力控制系统应用模式的搭建;根据隐藏EMD信息定义条件,求解质心动力学方程,再按照气动特性原则,计算航向偏离度的具体数值,完成基于EMD的飞机升力控制;以内存网交联环境为基础,配置模型机组织,实现对闭环测试功能的完善;实验结果表明,应用所设计系统可以改善直接升力水平不均的问题,将飞机飞行偏航角控制在0°~20°的数值范围之内,能够实现对飞机飞行能力的有效控制。The uneven direct lift of aircraft could cause the issue of flight yawing,in order to effectively control the aircraft s flight capabilities,a direct lift control system based on empirical mode decomposition(EMD)and closed-loop testing was designed.In the FSEU architecture,the ARINC429 bus closed-loop mechanism was set up.The servo control module and real-time onboard terminal were integrated to build the application mode of the aircraft s direct lift control system.The centroid dynamics equation was solved through defining the conditions for the hidden EMD information.Based on aerodynamic principles,the specific value of heading deviation was calculated to achieve the EMD-based lift control.Based on memory network crosslinking environment,the model organization was configured to improve the closed-loop testing functionality.Experimental results show that the designed system can improve the uneven lift and control the aircraft s yaw angle within the range of 0°~20°,effectively controlling aircraft s flight capabilities.

关 键 词：EMD分解方法 闭环测试 飞机直接升力 动力学方程 气动特性 

分 类 号：TP311[自动化与计算机技术—计算机软件与理论]