Yaw control of a tailless aircraft configuration
2010 (English)In: Journal of Aircraft, ISSN 0021-8669, Vol. 47, no 5, 1807-1810 p.Article in journal (Refereed) Published
The yaw control of a tailless aircraft configuration is investigated. The four trailing-edge control surfaces are actuated using electrical servos which are controlled using a custom designed Ethernet interface. Measurements of the yaw moment due to sideslip and due to split flap deflections have been performed using a strain gauge balance for both sting configurations in order to estimate the sting interference effects. The mass moment of inertia J is obtained from a yaw ground vibration test using the yaw sting with a torsional spring installed. Dynamic stability is estimated by performing vibration tests in yaw with the torsional spring installed. The required control surface deflections can be large due to the low dynamic pressure when landing. The configuration uses only four flaps for simultaneous control around all three axes and necessary control surface deflections for pitch, roll and yaw need to be superimposed at all times.
Place, publisher, year, edition, pages
2010. Vol. 47, no 5, 1807-1810 p.
IdentifiersURN: urn:nbn:se:kth:diva-91400DOI: 10.2514/1.C031017ISI: 000283206100034ScopusID: 2-s2.0-78049392997OAI: oai:DiVA.org:kth-91400DiVA: diva2:509937
QC 201203152012-03-142012-03-142012-03-15Bibliographically approved