Optimized Reconfigurable Control Design for Aircraft using Genetic Algorithm

Arsalan H.Khan,Shi Jingping,Zhang Weiguo,Zeashan H.Khan

doi:10.19026/rjaset.6.3481

Arsalan H.Khan, Shi Jingping + Show 2 more

Open Access

https://doi.org/10.19026/rjaset.6.3481

Copy DOI

Abstract

In this study, we propose a Genetic Algorithm (GA) based modular reconfigurable control scheme for an over-actuated non-linear aircraft model. The reconfiguration of the flight controller is achieved for the case of control surface faults/failures using a separate control distribution algorithm without modifying the base-line control law. The baseline Multi-Input Multi-Output (MIMO) Linear Quadratic Regulator (LQR) is optimized using GA to produce desired moment commands. Then, a GA based weighted pseudo-inverse method is used for effective distribution of commands between redundant control surfaces. Control surface effectiveness levels are used to redistribute the control commands to healthy actuators when a fault or failure occurs. Simulation results using ADMIRE aircraft model show the satisfactory performance in accommodating different faults, which confirm the efficiency of optimized reconfigurable design strategy.

Highlights

In advanced safety critical systems, e.g., civil and modern combat aircraft, physical redundancy is ensured in the design by integrating multiple redundant control surfaces with Fly-By-Wire (FBW) technology (Brière and Traverse, 1993; Forssell and Nilson, 2005)
Among the recent popular approaches to manage the actuator redundancy is the modular approach where a separate control allocator is introduced with base-line control strategy for handling actuator faults or failures (Harkegard, 2003; Shertzer et al, 2002)
This study has presented a Genetic Algorithm (GA) based optimized modular control design for reconfigurable flight control

Summary

Introduction

In advanced safety critical systems, e.g., civil and modern combat aircraft, physical redundancy is ensured in the design by integrating multiple redundant control surfaces with Fly-By-Wire (FBW) technology (Brière and Traverse, 1993; Forssell and Nilson, 2005). In essence, these aircrafts have more actuating surfaces to control the same three rotational degrees of freedom (pitch, roll and yaw). None of these studies have discussed a powerful and fast natural evolution based optimization technique for reconfigurable modular flight control design

Objectives

Results

Conclusion