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 and evaluation of a damage-tolerant flight control system
Entwurf und Bewertung eines beschädigungstoleranten Flugsteuerungssystems
2005
19 Seiten, 11 Quellen
Aufsatz (Zeitschrift)
Englisch
Design and evaluation of a damage-tolerant flight control system
Online Contents | 2005
|Design and Evaluation of a Damage-Tolerant Flight Control System
SAGE Publications | 2005
|AIAA-2004-4872 Design and Evaluation of a Damage-Tolerant Flight Control System
British Library Conference Proceedings | 2004
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