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Application of the weight function method on a high incidence research aircraft model

Published online by Cambridge University Press:  27 January 2016

N. Anton ,
R. M. Botez  and
D. Popescu
N. Anton
Affiliation:
École de technologie supérieure, Laboratory of Research in Active Controls, Aeroservoelasticity and Avionics, Montréal, Québec, Canada
R. M. Botez*
Affiliation:
École de technologie supérieure, Laboratory of Research in Active Controls, Aeroservoelasticity and Avionics, Montréal, Québec, Canada
D. Popescu
Affiliation:
École de technologie supérieure, Laboratory of Research in Active Controls, Aeroservoelasticity and Avionics, Montréal, Québec, Canada
*
[email protected]
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Abstract

This paper assesses the application of a new method for system stability analysis, the weight functions method, to the longitudinal and lateral motions of a High Incidence Research Aircraft Model. The method consists of finding the number of weight functions that is equal to the number of differential equations required for system modelling. The aircraft’s stability is determined from the sign of the total weight function; which should be negative for a stable model. The Aero-Data Model In Research Environment (ADMIRE) simulation, developed by the Swedish Defence Research Agency, was used for the aerodynamic aircraft modelling, with the following configurations: Mach number = 0·25, altitude = 500m, angle-of-attack [–10 to 30]°, elevon deflection angle [–30 to 30]°, canard deflection [0° and 25°] and rudder deflection angles [–30° and 30°]. These flight configurations were selected because they are among the flight conditions for Cat. II Pilot Induced Oscillation (PIO) criteria validation, performed on the FOI aircraft model presented in the PIO Handbook by the Group for Aeronautical Research and Technology in Europe, Flight Mechanics/Action Group 12. This aircraft model has a known instability for longitudinal and lateral motions and so a control law was introduced to stabilise its flight.

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1195 , September 2013 , pp. 897 - 912
Copyright
Copyright © Royal Aeronautical Society 2013 

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References

1. Yoichi, S. and Yasumi, K. Numerical weight function method for structural analysis formulation for two-dimensional elasticity and plate structures, J Society of Naval Architects of Japan, 2003, 193, pp 33–38, ISSN 0514–8499.Google Scholar
2. Kim, J.H. and Lee, S.B. Calculation of stress intensity factor using weight function method for a patched crack with debonding region, Engineering Fracture Mechanics, 2000, 67, pp 303–310.Google Scholar
3. Paris, P.C., Mcmeeking, R.M. and Tada, H. The weight function method for determining stress intensity factors, cracks and fracture – Proceedings of the Ninth national Symposium on Fracture Mechanics, 1976, 76–1712, pp 471–489.Google Scholar
4. Wu, X.R. and Carlsson, J. The generalised weight function method for crack problems with mixed boundary conditions, J Mechanics and Physics of solids, 1983, 31, (6), pp 485–497.Google Scholar
5. Fett, T. An analysis of the three-point bending bar by use of the weight function method, Engineering Fracture Mechanics, 1991, 40, (3), pp 683–686.Google Scholar
6. Schneider, G.A. and Danzer, R. Calculation of stress intensity factor of an edge crack in a finite elastic disc using the weight function method, Engineering Fracture Mechanics, 1989, 34, (3), pp 547–552.Google Scholar
7. Vainshtok, V.A. and Varfolomeyev, I.V. Application of the weight function method for determining stress intensity factors of semi-elliptical cracks, Int J Fracture, 1987, 35, (3), pp 175–186, DOI: 10.1007/BF00015587.Google Scholar
8. Stroe, I. Weight Functions Method in stability study of vibrations, SISOM 2008 and Session of the Commission of Acoustics, Bucharest, Romania, 29–30 May 2008. online < http://www.imsar.ro/SISOM%20&%20ACOUSTICS_%20Papers_%202008/A14.pdf >, verifed 29 March 2013.,+verifed+29+March+2013.>Google Scholar
9. Stroe, I. and Parvu, P. Weight functions method in stability study of systems, PAMM, Proc Appl Math Mech, 8, 10385 – 10386 (2008) /DOI 10.1002/pamm.200810385.Google Scholar
10. Jiankun, H., Bohn, C. and Wu, H.R. Systematic H∞ weighting function selection and its application to the real–time control of a vertical take–off aircraft, Control Engineering Practice, 2000, 8, pp 241–252.Google Scholar
11. Admirer4p1, http://www.foi.se/en/Our-Knowledge/Aeronautics/Admire/Downloads/, verifed 31 March 2013.Google Scholar
12. GARTEUR FM(AG12), PIO Analysis of a Highly Augmented Aircraft, GARTEUR/TP-120-07, 5 September 2001.Google Scholar
13. Lars, F. and Ulrik, N. ADMIRE The Aero-Data Model In a Research Environment Version 4.0, Model Description, FOI-R-1624-SE, ISSN-1650-1942, December 2005.Google Scholar
14. Terlouw, J.C. et al Robust flight control design challenge. Problem formulation and manual: The high incidence research model (HIRM), GARTEUR/FM/AG-08 TP-088-4, 2 February 1996.Google Scholar
15. GARTEUR FM(AG12), PIO Analysis of a Highly Augmented Aircraft, GARTEUR/TP-120-07, 5 September, 2001.Google Scholar
16. Schmidt, L.V. Introduction to Aircraft Flight Dynamics, AIAA Education Series, 1998.Google Scholar