Noninteracting control for helicopter in straight horizontal flight

dc.creator	Koumboulis, F. N.	en
dc.creator	Skarpetis, M. G.	en
dc.creator	Griparis, M. K.	en
dc.date.accessioned	2015-11-23T10:36:12Z
dc.date.available	2015-11-23T10:36:12Z
dc.date.issued	1998
dc.identifier.uri	http://hdl.handle.net/11615/29817
dc.description.abstract	Pitch angle and forward velocity are decoupled via a static state feedback law for the case of helicopter in straight horizontal flight. The set of stability derivatives for which decoupling is satisfied, is explicitly determined. The general analytic expression of the feedback controller, satisfying the decoupling design requirement, is derived. The necessary and sufficient conditions for decoupling and simultaneous stability are explicitly determined in terms of the stability derivatives of the helicopter. Simulation results are presented for vertical translation manoeuvre.	en
dc.source.uri	http://www.scopus.com/inward/record.url?eid=2-s2.0-0032295254&partnerID=40&md5=232242e3da5f4b6343147f3ce8466d8d
dc.subject	Control equipment	en
dc.subject	Design	en
dc.subject	Feedback control	en
dc.subject	Simulation	en
dc.subject	Stability	en
dc.subject	Velocity control	en
dc.subject	Flight control systems	en
dc.subject	Helicopters	en
dc.title	Noninteracting control for helicopter in straight horizontal flight	en
dc.type	conferenceItem	en

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