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

Xiao-Yu Zhang,Yu-Xin Zhao,Kun-Peng He,De-Xin Xu

doi:10.1155/2013/284869

Xiao-Yu Zhang, Yu-Xin Zhao + Show 2 more

Open Access

https://doi.org/10.1155/2013/284869

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Abstract

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.

Highlights

Some of the earliest flight vehicles are controlled by moving the body of the pilot to affect the center of mass (c. m.) of the vehicle
Considering the above-mentioned issues, in this paper, we investigate the control of Moment Aerospace Vehicles (MMAV) using FSMC based on dynamic inversion approach
In order to demonstrate the performance of the proposed flight control system, simulations are presented

Summary

Introduction

Some of the earliest flight vehicles are controlled by moving the body of the pilot to affect the center of mass (c. m.) of the vehicle. This approach yields continuous control and chattering elimination It constrains the sliding system’s trajectories not to the sliding surface but to its vicinity losing the robustness to the disturbances. (b) Using the higher-order sliding mode control techniques [18,19,20,21,22,23,24] This approach allows driving the sliding variable to zero and its consecutive derivatives in the presence of the disturbances/uncertainties increasing the accuracy of the sliding variable stabilization, and has still been successfully applied for the control of electropneumatic actuators [25, 26].

Mass Moment Aerospace Vehicles Model

Sliding Mode Control System Design

Simulation Results and Discussions

Conclusions