Hostname: page-component-cd9895bd7-jn8rn Total loading time: 0 Render date: 2024-12-31T15:15:22.388Z Has data issue: false hasContentIssue false
  • English
  • Français

Weight functions method for stability analysis applied as design tool for Hawker 800XP aircraft

Published online by Cambridge University Press:  27 January 2016

N. Anton  and
R. M. Botez
N. Anton
Affiliation:
[email protected], École de technologie supérieure, Laboratory of Research in Active Controls, Aeroservoelasticity and Avionics, Montréal, Canada
R. M. Botez
Affiliation:
[email protected], École de technologie supérieure, Laboratory of Research in Active Controls, Aeroservoelasticity and Avionics, Montréal, Canada
Get access Rights & Permissions [Opens in a new window]

Abstract

A new method for system stability analysis, the weight functions method, is applied to estimate the longitudinal and lateral stability of a Hawker 800XP aircraft. This paper assesses the application of the weight functions method to a real aircraft and a method validation with an eigenvalues stability analysis of the linear small-perturbation equations. The method consists of finding the weight functions that are 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 – the sign should be negative for a stable model. Aerodynamic coefficients and stability derivatives of the mid-size twin-engine corporate aircraft Hawker 800XP are obtained using the in-house FDerivatives code, recently developed at our laboratory of applied research in active controls, avionics and aeroservoelasticity LARCASE. The results are validated with the flight test data supplied by CAE Inc. for all considered flight cases. This aircraft model was chosen because it was part of a research project for FDerivatives code and continued with weight function method for stability analysis in order to develop a design tool, based only on the aircraft geometrical parameters for subsonic regime. The following flight cases are considered: Mach numbers = 0·4 and 0·5, altitudes = 3,000m, 5,000m, 8,000m and 10,000m, and angles-of-attack α = –5° to 20°.

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1218 , August 2015 , pp. 981 - 998
Copyright
Copyright © Royal Aeronautical Society 2015

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1.Yoichi, S. and Yasumi, K.. Numerical weight function method for structural analysis formulation for two–dimensional elasticity and plate structures, J Soc of Naval Architects of Japan, 2003, ISSN 0514–8499, 193, pp 33–38.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.CrossRefGoogle 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.CrossRefGoogle 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.Stroe, I.. Weight Functions Method in stability study of vibrations, SISOM 2008 and Session of the Commission of Acoustics, Bucharest, Hungary, 29-30 May 2008.Google Scholar
8.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
9.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
10.Anton, N.. Analiza miscarii longitudinale a unui avion de mare manevrabilitate prin metoda bifurcatiei, “AEROSPACE 2005” Conference, Bucharest, Hungary, 11-12 October, 2005.Google Scholar
11.Wilde, J., Linear Algebra II: Quadratic Forms and Definiteness, 26 August 2011. http://www.econ.brown. edu/students/Takeshi_Suzuki/Math_Camp_2011/LA2-2011.pdf.Google Scholar
12.Schmidt, L.V., Introduction to Aircraft Flight Dynamics, AIAA Education Series, 1998.Google Scholar
13.Anton, N., Botez, R.M. and Popescu, D.. New methodology and code for Hawker 800XP aircraft stability derivatives calculation from geometrical data, Aeronaut J, 2010, 114, (1156).Google Scholar
14.Anton, N., Botez, R.M. and Popescu, D.. New methods and code for aircraft stability derivatives calculations from its geometrical data, AIAA Atmospheric Flight Mechanics Conference, Chicago, IL, USA, 10-13 August 2009.Google Scholar
15.Anton, N., Botez, R.M. and Popescu, D.. Stability derivatives for X-31 delta-wing aircraft validated using wind tunnel test data, Proceeding of the Institution of Mechanical Engineering, Part G, J Aero Eng, April 2011, pp 403–416.Google Scholar
16.Anton, N. and Botez, R.M.. 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, UK, 12-14 October, 2011Google Scholar
17.Anton, N. and Botez, R.M.. Weight Functions Method Application on a Delta-Wing X-31 configurations, INCAS Bulletin, 2011, 3, (4), pp 3–16, ISSN 2066-8201.Google Scholar
18.Anton, N., Botez, R.M. and Popescu, D.. Application of the weight function method on a high incidence research aircraft model, Aeronaut J, 2013, 117, (1195), pp 1–16.CrossRefGoogle Scholar
19.Etkin, B., and Reid, L., Dynamics of Flight: Stability and Control, J. Wiley & Sons, 1996.Google Scholar
20.Hamel, C., Sassi, A., Botez, R. and Dartigues, C.. Cessna Citation X aircraft global model identification from fght tests, SAE Int J Aerospace, 2013, 6, (1), pp 106–114, doi:10.4271/2013-01-2094.Google Scholar
21.Boely, N. and Botez, R.M.. New approach for the identification and validation of a nonlinear F/A-18 model by use of neural networks, IEEE Transactions on Neural Networks, 2010, 21, (11), pp 1759–1765.Google Scholar
22.Kouba, G., Botez, R.M. and Boely, N.. Fuzzy logic method use in the F/A-18 aircraft model identification, sous presse, AIAA J Aircr, 2009, 47, (1), pp. 1–17.Google Scholar
23.Hodgkinson, J., Aircraft Handling Qualities, AIAA Education Series, 1999.Google Scholar