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Yaw Departure and Recovery of a Tailless Aircraft Configuration
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.ORCID iD: 0000-0003-2391-641X
2013 (English)In: Journal of Aircraft, ISSN 0021-8669, Vol. 50, no 1, 311-315 p.Article in journal (Refereed) Published
Abstract [en]

The ability to recover an aircraft from an out-of-control condition is essential both from a safety and from an economical point of view. Investigations show that a significant amount of fatal accidents occur due to loss of control outside the tested flight envelope. For passenger aircraft, safety is of greatest importance; for military aircraft, a pilot's life can be saved by an ejection seat and the remaining loss after an accident is the cost of the aircraft. The purpose of this study was to investigate departure and recovery in the yaw degree of freedom for a tailless aircraft model. In previous studies, stability and control investigations have shown that the model is not stable in yaw for low angles of attack (AOA), and a simple control model has been implemented to handle the instability at moderate sideslip angles. An increase in yaw damping due to deflected flaps is, however, observed. To accurately simulate the departure motion for the current experimental setup by using the preceding equations, a better understanding of the friction is needed.

Place, publisher, year, edition, pages
2013. Vol. 50, no 1, 311-315 p.
National Category
Aerospace Engineering
URN: urn:nbn:se:kth:diva-119130DOI: 10.2514/1.C031868ISI: 000314667100032ScopusID: 2-s2.0-84874539347OAI: diva2:610390

QC 20130311

Available from: 2013-03-11 Created: 2013-03-07 Last updated: 2013-03-11Bibliographically approved

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