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Mathematical modelling, simulation, and estimation of aircraft parameters using five degree-of-freedom dynamic test rig

Mathematical modelling, simulation, and estimation of aircraft parameters using five... This article proposes a scheme to estimate the aerodynamic derivatives of aircraft using a wind tunnel dynamic test rig system. A five-degree-of-freedom (DOF) rig system has been used to simulate near free flight manoeuvres inside the wind tunnel by exciting a scaled down model aircraft through various types of control surface deflections. A mathematical model that incorporates five DOF in aircraft motion has been developed. The five DOF equations of motion of the rig system are formulated using a vector and matrix approach. The simulated flight data, generated from a five DOF mathematical model, has been used to estimate the aerodynamic parameters of the aircraft. The maximum likelihood method has been used to achieve close estimates of the parameters by minimizing the error between simulated and computed response. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering SAGE

Mathematical modelling, simulation, and estimation of aircraft parameters using five degree-of-freedom dynamic test rig

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References (24)

Publisher
SAGE
Copyright
© Authors 2011
ISSN
0954-4100
eISSN
2041-3025
DOI
10.1177/0954410011407265
Publisher site
See Article on Publisher Site

Abstract

This article proposes a scheme to estimate the aerodynamic derivatives of aircraft using a wind tunnel dynamic test rig system. A five-degree-of-freedom (DOF) rig system has been used to simulate near free flight manoeuvres inside the wind tunnel by exciting a scaled down model aircraft through various types of control surface deflections. A mathematical model that incorporates five DOF in aircraft motion has been developed. The five DOF equations of motion of the rig system are formulated using a vector and matrix approach. The simulated flight data, generated from a five DOF mathematical model, has been used to estimate the aerodynamic parameters of the aircraft. The maximum likelihood method has been used to achieve close estimates of the parameters by minimizing the error between simulated and computed response.

Journal

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace EngineeringSAGE

Published: Jan 1, 2012

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