Robust Flight Control System Design Research Articles

Robust flight control system design of a fixed wing UAV using optimal dynamic programming

Robust flight control system design of a fixed wing UAV using optimal dynamic programming

Robust Flight Control System Design with Cerebellar Model Articulation Controller

This paper presents a robust proportional-derivative (PD) based cerebellar model articulation controller (CMAC) for vertical take-off and landing flight control systems. It is known that PD control is a simple and effective control method. However, it does not ensure the robustness if it is used alone for uncertain systems. CMAC can be used for robust control. However, it requires training patterns for tuning some weighting factors. A novel CMAC incorporating with a PD controller design is proposed in this paper. Successful on-line training and recalling process of CMAC accompanying the PD controller was developed. The advantage of the proposed method is mainly the robust tracking performance against aerodynamic parametric variation and external wind gust. Even when the PD controller is not designed well, the CMAC is capable of doing a robust tracking control through on-line recalling and training procedures.

Robust flight control system design using H∞ loop-shaping and recessive trait crossover genetic algorithm

A proposed approach to robust controller design is introduced. This approach combines the recessive trait crossover genetic algorithm with the loop-shaping design procedure using H∞ synthesis. The requirements, design and simulation of a flight control system for precision tracking task are considered. The proposed method is applied to design a control system for the F-16 fighter aircraft model. The flight simulations reveal that the desired performance objectives are achieved and that the controller provides acceptable performance in spite of modeling errors and plant parameter variations.

Passification-based robust flight control system design

A robust autopilot for attitude control of the flexible aircraft under parametric uncertainty is designed. The high gain controller with forced sliding motions is used to secure adaptability in the wide region of the aircraft model parameters. The shunting method is applied to ensure the closed-loop system stability in the face of the lack of the aircraft state information. The sequential reference model is used to assign the desired closed-loop system performance. An example illustrating a typical design procedure for aircraft attitude control in the horizontal plane for different flight conditions is given. The system robustness with respect to uncertain plant parameters is studied. The simulation results demonstrate efficiency and high robustness of the suggested control method.

Design and Evaluation of a Damage-Tolerant Flight Control System

The performance and stability requirements for a robust flight control system design are presented in the form of a ‘design challenge.’ The challenge includes description of specific vehicle failures that are to be accommodated by the flight control system. The vehicle chosen for the design is the innovative control effector vehicle, and both longitudinal and lateral/directional degrees of freedom are included. Two flight conditions are considered: Mach number 0.3 and altitude 15 000 ft; Mach number 0.9 and altitude 35 000 ft. No scheduling of the flight control law is permitted in the design. After the performance and stability requirements are described, a solution to the design challenge is presented in the form of a sliding-mode control system offered as an alternative to reconfigurable designs. The performance of this system is then evaluated through analysis and computer simulation, including significant failures and damage.

Design of a robust controller for a supersonic aircraft using H ∞ approach

In this paper an H ∞ optimal, robust flight control system design for a supersonic aircraft has been described. Separate controllers are designed for longitudinal and lateral motions. A general two-degrees-of-freedom controller is proposed, where feedback control is designed for robust performance augmentation, while a series compensator is used to ensure that requisite handling qualities. Three alternative methods to achieve performance robustness have been discussed. The results obtained are very encouraging. It is hoped that this will equip the flight control engineers with an alternative to the conventional methods.

特集 新しい飛行制御技術の展望 多数遅れモデル／多数設計点法によるロバスト飛行制御系の設計

特集 新しい飛行制御技術の展望 多数遅れモデル／多数設計点法によるロバスト飛行制御系の設計

Robust flight control system design with multiple model approach

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