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Flight mechanics of a free-wing tilt-body aircraft

Published online by Cambridge University Press:  03 February 2016

K. Ro ,
J. W. Kamman  and
J. B. Barlow
K. Ro
Affiliation:
Western Michigan University, Kalamazoo, Michigan, USA
J. W. Kamman
Affiliation:
Western Michigan University, Kalamazoo, Michigan, USA
J. B. Barlow
Affiliation:
University of Maryland, College Park, Maryland, USA
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Abstract

The free-wing tilt-body aircraft refers to a vehicle configuration in which the wing, fuselage, and empennage are in a longitudinally articulated connection. This allows the main wing to freely rotate relative to the body, while the empennage, which is in the form of a long twin boom connected to the rear of the body, changes its incidence angle relative to the body in response to external commands. The principal advantages claimed for the configuration are short takeoff and landing capability, and reduced gust sensitivity. The aerodynamics of the free-wing tilt-body configuration has been previously studied, but analysis of its flight mechanics is limited. In this paper we present derivations of the flight dynamic equations of motion using multi-body dynamic modelling techniques, and combine the resulting equations of motion with experimental aerodynamic data to achieve a nonlinear mathematical model for flight simulation of a generic free-wing tilt-body vehicle. The mathematical model is suitable for the study of detailed dynamic characteristics as well as for model based control law synthesis. Key flight performance, and stability and control characteristics of a generic configuration are obtained from the mathematical model.

Type
Research Article
Information
The Aeronautical Journal , Volume 112 , Issue 1137 , November 2008 , pp. 625 - 640
Copyright
Copyright © Royal Aeronautical Society 2008

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