A description of the main existing active control technologies is given, i.e. artificial stability load alleviation, ride quality and flutter suppression, and their application to fighter and transport aircraft.
The precondition and preparations necessary to apply CCV techniques to an aircraft in the design stage or to an existing aircraft are mentioned. Load and weight reductions arising from CCV techniques are estimated, and its possible influence on fatigue reduction is discussed.
A description of the work presently done in Germany is given. It comprises extensive theoretical and experimental work on the problem of flutter suppression. The experimental work consists of testing such systems in the wind tunnel as well as in flight. Furthermore theoretical and experimental work is being done on active control techniques such as maneuver load control, gust load alleviation and ride quality. Last but not least the modification of a F104 fighter to give it relaxed stability is reported.
That the application of CCV techniques may give rise to problems of its own is indicated by the example of the CSAS coupling with the elastic motion of the structure. It is furthermore pointed out that the various active control techniques interact, and that their application is an interdisciplinary problem.