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 Test

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。

Abstract:

The uneven direct lift level of an aircraft can cause flight yaw issues. To achieve effective control of the aircraft's flight capability, an aircraft direct lift control system based on EMD and closed-loop testing is designed. In the FSEU architecture, the ARINC429 bus closed-loop mechanism is set up, combined with the servo control module and real-time onboard terminal, to achieve the establishment of the application mode of the aircraft direct lift control system. Define the conditions based on the hidden EMD information, solve the mass cardiac mechanics equation, and then calculate the specific value of heading deviation according to the principles of aerodynamic characteristics to complete the aircraft lift control based on EMD. Based on the memory network cross-linking environment, configure the model machine organization to improve the closed-loop testing function. The experimental results show that the application of the designed system can improve the problem of uneven direct lift levels, control the aircraft's flight yaw angle within the numerical range of 0 ° -20 °, and achieve effective control of the aircraft's flight capability.