This chapter deals with automatic flight control systems. It describes the effect of flight conditions on the aircraft modes, presents some background in handling qualities and control design criteria, and describes the purpose and design requirements of a large number of commonly used control systems. Stability augmentation systems are conventionally designed separately for the longitudinal dynamics and the lateral‐directional dynamics, and this is made possible by the decoupling of the aircraft dynamics in most flight conditions. In the case of high‐performance military aircraft, where the pilot may have to maneuver the aircraft to its performance limits and perform tasks such as precision tracking of targets, specialized control augmentation systems are needed. The chapter shows how algebraic expressions for the rigid‐body modes can be derived so that their dependence on the stability derivatives and on the flight conditions can be examined, and conditions for stability can be deduced.
Aircraft Dynamics and Classical Control Design
2015-11-02
127 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Aircraft Control Based on Flexible Aircraft Dynamics
Online Contents | 2016
|Aircraft Control Based on Flexible Aircraft Dynamics
AIAA | 2016
|