scholarly journals Aircraft pitch control tracking with sliding mode control

2018 ◽  
Vol 7 (4.13) ◽  
pp. 62
Author(s):  
Nurhana M. Rouyan ◽  
Renuganth Varatharajoo ◽  
Samira Eshghi ◽  
Ermira Junita Abdullah ◽  
Shinji Suzuki
Keyword(s):  
Sliding Mode Control ◽  
Flight Control ◽  
Sliding Mode ◽  
Aerodynamic Characteristics ◽  
Control Methods ◽  
Fighter Aircraft ◽  
Pitch Control ◽  
Mode Control ◽  
Numerical Treatments ◽  
High Angles Of Attack

Sliding mode control (SMC) is one of the robust and nonlinear control methods. An aircraft flying at high angles of attack is considered nonlinear due to flow separations, which cause aerodynamic characteristics in the region to be nonlinear. This paper presents the comparative assessment for the flight control based on linear SMC and integral SMC implemented on the nonlinear longitudinal model of a fighter aircraft. The controller objective is to track the pitch angle and the pitch rate throughout the high angles of attack envelope. Numerical treatments are carried out on selected conditions and the controller performances are studied based on their transient responses. Obtained results show that both SMCs are applicable for high angles of attack.  

scholarly journals Sliding Mode Control for Mass Moment Aerospace Vehicles Using Dynamic Inversion Approach

2013 ◽  
Vol 2013 ◽  
pp. 1-11 ◽  
Author(s):  
Xiao-Yu Zhang ◽  
Yu-Xin Zhao ◽  
De-Xin Xu ◽  
Kun-Peng He
Keyword(s):  
Sliding Mode Control ◽  
Flight Control ◽  
Sliding Mode ◽  
Moving Mass ◽  
Aerodynamic Parameter ◽  
Aerospace Vehicles ◽  
Variable Structure Systems ◽  
Control Approach ◽  
Mode Control ◽  
Mass Moment

The moving mass actuation technique offers significant advantages over conventional aerodynamic control surfaces and reaction control systems, because the actuators are contained entirely within the airframe geometrical envelope. Modeling, control, and simulation of Mass Moment Aerospace Vehicles (MMAV) utilizing moving mass actuators are discussed. Dynamics of the MMAV are separated into two parts on the basis of the two time-scale separation theory: the dynamics of fast state and the dynamics of slow state. And then, in order to restrain the system chattering and keep the track performance of the system by considering aerodynamic parameter perturbation, the flight control system is designed for the two subsystems, respectively, utilizing fuzzy sliding mode control approach. The simulation results describe the effectiveness of the proposed autopilot design approach. Meanwhile, the chattering phenomenon that frequently appears in the conventional variable structure systems is also eliminated without deteriorating the system robustness.

scholarly journals Fuzzy adaptive sliding-mode control for hypersonic vehicles

Filomat ◽  
2018 ◽  
Vol 32 (5) ◽  
pp. 1789-1796
Author(s):  
Qian Gao ◽  
Naibao He ◽  
Fengxue Cao
Keyword(s):  
Sliding Mode Control ◽  
Flight Control ◽  
Sliding Mode ◽  
External Disturbance ◽  
Control Technique ◽  
Adaptive Sliding Mode Control ◽  
Observation System ◽  
Terminal Sliding Mode ◽  
Mode Control ◽  
Near Space

This study focuses on a novel anti-disturbance flight control scheme for the near space hypersonic vehicle (NHV) based on the fuzzy sliding-mode control technique and disturbance observer. First, a fuzzy system is employed to approximate the uncertainty nonlinear dynamics; furthermore, an auxiliary fast dynamic observation system is introduced to tackle the system uncertainty and the time-varying unknown external disturbance of the NHV. Second, the dynamic adaptive terminal sliding-mode control strategy is raised to alleviate the chattering phenomenon. Third, the Lyapunov method is used to prove that the adaptive control system can be guaranteed to be stable and the tracking errors are converged in finite time. Finally, the effectiveness of the proposed method is verified with simulation.

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