This chapter introduces the control laws that require the designer to ‘solve’ for the control vector. At one extreme the control ‘law’ could be trivial: simple cables and pulleys connected to the control stick and rudder pedal at one end, to the control surfaces at the other end. In many cases some form of automatic flight control is used. This can range from systems that modify the airplane's dynamic response, to control‐augmentation systems that translate pilot inputs into specific responses, such as making a given longitudinal stick input command a fixed pitch rate, independent of the airplane's state. The amount of pilot compensation required to perform a task is a measure of an airplane's flying qualities. Historically flight control system design has been based on feedback control, typically using transfer functions of control effectors to system outputs to find feedback gains that give desired responses.
Control Laws
Aircraft Control Allocation ; 20-29
2016-12-05
10 pages
Article/Chapter (Book)
Electronic Resource
English
DIGITAC Multimode Control Laws
SAE Technical Papers | 1985
|Control Laws: General Qualities
Springer Verlag | 2017
|Control Laws: Attitude Applications
Springer Verlag | 2017
|X2™ Load Alleviating Control Laws
British Library Conference Proceedings | 2012
|Exponentially Stabilizing Robot Control Laws
NTRS | 1990
|