Design of Tiltrotor Flight Control System Using Fuzzy Sliding Mode Control

2010 ◽  
Author(s):  
Xue Ping Zhu ◽  
Yong Hua Fan ◽  
Jun Yang
Keyword(s):  
Control System ◽  
Sliding Mode Control ◽  
Flight Control ◽  
Sliding Mode ◽  
Flight Control System ◽  
Fuzzy Sliding Mode Control ◽  
Mode Control ◽  
Fuzzy Sliding Mode

Fuzzy sliding mode control of servo control system based on variable speeding approach rate

2019 ◽  
Vol 23 (24) ◽  
pp. 13477-13487 ◽  
Author(s):  
Hao Huang ◽  
Md Zakirul Alam Bhuiyan ◽  
Qunzhang Tu ◽  
Chengming Jiang ◽  
Jinhong Xue ◽  
...  
Keyword(s):  
Control System ◽  
Sliding Mode Control ◽  
Sliding Mode ◽  
Servo Control ◽  
Fuzzy Sliding Mode Control ◽  
Mode Control ◽  
Servo Control System ◽  
Fuzzy Sliding Mode

scholarly journals Longitudinal Attitude Control Decoupling Algorithm Based on the Fuzzy Sliding Mode of a Coaxial-Rotor UAV

Electronics ◽  
2019 ◽  
Vol 8 (1) ◽  
pp. 107 ◽  
Author(s):  
Kewei Li ◽  
Yiran Wei ◽  
Chao Wang ◽  
Hongbin Deng
Keyword(s):  
Sliding Mode Control ◽  
Flight Control ◽  
Sliding Mode ◽  
Underactuated System ◽  
External Interference ◽  
Fuzzy Sliding Mode Control ◽  
Mode Control ◽  
Coaxial Rotor ◽  
Fuzzy Sliding Mode ◽  
Decoupling Algorithm

A longitudinal attitude decoupling algorithm based on the fuzzy sliding mode control for a small coaxial rotor unmanned aerial vehicle (UAV) is presented in this paper. The attitude system of a small coaxial rotor UAV is characterized by nonlinearity, strong coupling and uncertainty, which causes difficulties pertaining to its flight control. According to its six-degree-of-freedom model and structural characteristics, the dynamic model was established, and a longitudinal attitude decoupling algorithm was proposed. A fuzzy sliding mode control was used to design the controller to adapt to the underactuated system. Compared with the uncoupled fuzzy sliding mode control, simulation results indicated that the proposed method could improve the stability of the system, presented with a better adapting ability, and could effectively suppress the modeling error and external interference of the coaxial rotor aircraft attitude system. The proposed method also has the advantages of high accuracy, good stability, and the ease of implementation.

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