The UAV control system must fundamentally be of a closed‐loop form, which employs a negative feedback. This chapter presents fundamentals of control systems, control concepts, basic definitions, major elements, and general design techniques. The controller is designed based on a control law. Some typical control laws are: linear; nonlinear; optimal; adaptive; and robust. The real aircraft behavior is nonlinear and has uncertainties. A UAV is basically a nonlinear system. Furthermore, its dynamics and equations of motion are also nonlinear. The chapter presents some common nonlinear systems phenomena. There are primarily three flight control requirements: longitudinal control requirements; lateral/Roll control requirements; and directional control requirements. The chapter presents these requirements. These requirements must be met by the flight control system. Flight control systems should be designed with sufficient redundancy to achieve two orders of magnitude more reliability than some desired levels.
Control System Design
Design of Unmanned Aerial Systems ; 195-253
2020-03-23
59 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Springer Verlag | 2023
|British Library Conference Proceedings | 2006
|Springer Verlag | 2024
|NTRS | 1977
|NTRS | 1987
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