This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Numerical and Experimental Measures of the Unmanned Aerial System UAS-S4 of Hydra Technologies
Technical Paper
2014-01-2145
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
This article presents a structural analysis of the Unmanned Aerial System UAS-S4 ETHECATL. Mass, center of gravity position and mass moment of inertia are numerically determined and experimentally attested using the pendulum method.
To determine the mass moment of inertia, a bifilar torsion-type pendulum is used for the Z-axis and a simple pendulum for the X and Y axes [14]. A nonlinear dynamic model is developed for the rotational motion about the center of gravity (Gs) of the tested system, including the effects of large-angle oscillations, aerodynamic drag, viscous damping and additional mass effects.
MATLAB genetic algorithms are then used to obtain the values of mass moment of inertia that would validate the experimental data with the numerical results.
The experiment used data gathered by three sensors: an accelerometer, a gyroscope and a magnetometer. Therefore, a method is used to calibrate these three sensors.
For determining the accuracy of the method, the experimental results for an object of uniform density for which the moment of inertia is computed numerically from geometrical data, are presented. The experimental results obtained for the UAS-S4 ETHECATL are also presented and compared to the analytical predictions [13]. The experimental method gives, with respect to the numerical results, an error of 4.4% for the moment of inertia around the Z-axis and of 9.5% for the moment of inertia around the X and Y axes. In addition, the experimental results of UAS-S4 inertia validate the analytical predictions [13] with a relative error of 6.52% on average.
Authors
Citation
Tondji Chendjou, Y. and Botez, R., "Numerical and Experimental Measures of the Unmanned Aerial System UAS-S4 of Hydra Technologies," SAE Technical Paper 2014-01-2145, 2014, https://doi.org/10.4271/2014-01-2145.Also In
References
- Raymer , D. Aircraft Design: A Conceptual Approach 2012 ISBN-13: 978-1600869112 5
- Williams , John E. , Vukelich , Steven R. The USAF Stability and Control Digital DATCOM. Volume I. Users Manual AFFDL-TR-79-3032 I Nov. 1979
- Williams , John E. , Vukelich , Steven R. The USAF Stability and Control Digital DATCOM. Volume II. Implementation of Datcom Methods AFFDL-TR-79-3032 II Nov. 1979
- Williams , John E. , Vukelich , Steven R. The USAF Stability and Control Digital DATCOM. Volume III. Plot Module AFFDL-TR-79-3032 III Nov. 1979
- Anton , N. , Botez , R. M. , Popescu , D. 2011 Stability derivatives for X-31 delta-wing aircraft validated using wind tunnel test data Proceedings of the Institution of Mechanical Engineers 225 Journal of Aerospace Engineering 403 416
- Anton , N. , Popescu , D. , Botez , R.M. 2010 New methods and code for stability derivatives calculations from Hawker 800 XP aircraft geometrical data knowledge The Aeronautical Journal 114 1156
- Anton , N. , Botez , R. M. 2011 A new type of the stability derivatives for X-31 model aircraft validated using wind tunnel test data Applied Vehicle Technology Panel Specialists Meeting AVT-189, Assessment of Stability and Control Prediction Methods for NATO Air and Sea Vehicles Dstl Portsdown West, Fareham, Hampshire, Grande Bretagne 12 14 octobre
- Anton , N. , Botez , R.M. , Popescu , D. 2009 New methods and code for aircraft stability derivatives calculations from its geometrical data CASI Aircraft Design and Development Symposium Kanata, Ont. 5 7 may
- Sugar Gabor , O. , Koreanschi , A. , and Botez , R. Optimization of an Unmanned Aerial System' Wing Using a Flexible Skin Morphing Wing SAE Int. J. Aerosp. 6 1 115 121 2013 10.4271/2013-01-2095
- Gabor Sugar , O. , Koreanschi , A. , Botez , R. M. 2013 An efficient numerical lifting line method for practical wing optimization through morphing on the Hydra Technologies UAS-S4 CASI AÉRO 2013 conference Toronto, Canada April 30 th May 2 nd
- Şugar Gabor , O. , Koreanschi , A. , Botez , R. M. 2013 Unmanned Aerial System Hydra Technologies Éhecatl wing optimization using a morphing approach AIAA Guidance, Navigation, and Control Conference Boston, USA 19 22 August
- Soulé H.A. , and Miller , M.P. The Experimental Determination of the Moments of inertia of Airplanes NACA Rept. 467 1933
- Fabien Dubois internship report Modélisation structurelle et optimisation numérique d'un drone à voilure fixe 02 07 2012
- Augier David and More Christophe Physique MP MP*-PTPT* 2 eme année Collection Méth
- Jardin Matt R. and Muller Eric R Optimized Measurements of Unmanned-Aircraft-Vehicle Mass Moment of Inertia with a Bifilar Pendulum
- http://magnetic-declination.com
- Talat Ozyagcilar Applications Engineer Calibrating and eCompass in the present of Hard and Soft-Iron Interference 3 04 2013