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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
*
ruxandra@gpa.etsmtl.ca
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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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