Vertical Flight Simulation Performance Analysis Based on Power Function Control Command

doi:10.16182/j.issn1004731x.joss.19-0057

Abstract

Abstract: Based on the fly height control method of modal direct switching, after the input of the control command, the control output may be oscillated or even diverged. The power function conforms to the variation law of the flight altitude command, and is used as the prototype function to derive the relationship between the given height, the current height and the vertical velocity. Using this transformation relationship as the input command of the vertical velocity control loop, a smooth control system is designed. The system does not require control modal switching and can achieve the flight altitude maintenance andflight altitude change. The performance analysis of the designed smooth control system is carried out by the A320 flight simulation platform. The results show that the system can achieve a high degree of smooth control and the steady-state error is well suppressed.

Key words: vertical speed control, altitude control, power prototype function, A320 flight simulation

CLC Number:

V249.1

Qu Zhongjun, Kang Zeyu, Cheng Yongmei. Vertical Flight Simulation Performance Analysis Based on Power Function Control Command[J]. Journal of System Simulation, 2020, 32(9): 1780-1786.

References

[1] 吴森堂. 飞行控制系统[M]. 北京: 北京航空航天大学出版社, 2013.
Wu Sentang.Flight control system[M]. Beijing: Beijing University of Aeronautics and Astronautics Press, 2013.
[2] 徐军, 欧阳绍修. 运输类飞机自动飞行控制系统[M]. 北京: 国防工业出版社, 2013.
Xu Jun, Ouyang Shaoxiu.Automatic flight control system for transport aircraft[M]. Beijing: National Defense Industry Press, 2013.
[3] 张湑蕊, 赵宏涛, 亓迎川. LQR与PID结合的无人机高度控制[J]. 空军预警学院学报, 2017, 31(4): 280-283.
Zhang Jianrui, Zhao Hongtao, Qi Yingchuan.UAV's altitude control by using LQR and PID[J]. Journal of Air Force Early Warning Academy, 2017, 31(4): 280-283.
[4] 江琼, 陈怀民, 吴佳楠. H∞鲁棒控制与PID控制相结合的无人机飞行控制研究[J]. 宇航学报, 2006, 27(2): 192-195.
Jiang Qiong, Chen Huaimin, Wu Jianan.Research On UAV Flight Control Based On PID Control and H∞ Robust Control[J]. Journal of Astronautics, 2006, 27(2): 192-195
[5] 陈静杰, 张明卉. 基于H_∞/PID混合控制的飞机高度控制器设计[J]. 控制工程, 2009(增3): 160-162, 165.
Chen Jingjie, Zhang Minghui.Airplane Altitude Controller Design Based on Combining Control of H_∞ and PID[J]. Control Engineering of China, 2009 (S3): 160-162, 165.
[6] Li Y Q, Lei C.Adaptive Fuzzy Controller Design Based on Aircraft Model[J]. Applied Mechanics and Materials (S1662-7482), 2014: 2470-2473.
[7] Singh S, Murthy T V R. Neural Network-Based Sensor Fault Accommodation in Flight Control System[J]. Journal of Intelligent Systems (S2191-026X), 2013, 22(3): 317-333.
[8] 李欣. 大型客机自动飞行控制律研究[D]. 南京: 南京航空航天大学, 2013.
Li Xin.Research on automatic flight control law for large passenger aircraft[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2013.
[9] 康泽禹, 程咏梅, 崔小丹, 等. 发动机推力档位缺失下一种自动推力计算方法[J]. 西北工业大学学报, 2018, 36(6): 1116-1120.
Kang Zeyu, Cheng Yongmei, Cui Xiaodan, et al.An Automatic Thrust Calculation Method in Case of Engine Gear Missing in Flight Control Simulation System[J]. Journal of Northwestern Polytechnical University, 2018, 36(6): 1116-1120.
[10] Wright S.Model-based development of MAV altitude control via ground-based equipment[J]. International Journal of Modelling Identification and Control (S1746-6172), 2017, 28(4): 361.
[11] Li H Y, Li C W, Li H Y, et al.An Integrated Altitude Control Design for a Tail-Sitter UAV Equipped with Turbine Engines[J]. IEEE Access (S2169-3536), 2017(99): 1.
[12] 史忠科. 高性能飞机发展对控制理论的挑战[J]. 航空学报, 2015, 36(8): 2717-2734.
Shi Zhongke.Challenge of control theory in the presence of high performance aircraft development[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(8): 2717-2734.