Input Excitation Techniques for Aerodynamic Derivatives Estimation of Highly Augmented Fighter Aircraft

  • N. Shantha Kumar National Aerospace Laboratories, Bangalore
DOI: https://doi.org/10.14429/dsj.49.3828
Keywords: SIMULINK based simulation, Fighter aircraft, Lateral directional aerodynamic derivatives

Abstract

This paper presents the results of an investigation related to the estimation of lateral-directional aerodynamic derivatives of highly augmented and advanced fighter aircraft from the flight like response data. Different types of pilot inputs are used to generate aircraft response data in the engineer-in-loop flight simulator to determine which input excitation flight provide the most accurate estimates of aircraft stability and control derivatives. Also, MATILABI SIMULINK-based simulation platform is used to generate aircraft response with single-surface excitation to evaluate the usefulness of the method for stability and control derivatives estimation. The maximum likelihood estimation, based on output error utilisation technique is used to estimate the derivatives from the aircraft simulation response data. The results indicate that accuracy of the estimated derivatives improve with persistence excitation and single-surface excitation.

Author Biography

N. Shantha Kumar, National Aerospace Laboratories, Bangalore
Mr N Shantha Kumar obtained his MTech (Aerospace Engineering) from Indian Institute of Technology(IlT) Bombay, in 1987. Presently, he is working as Scientist at the Flight Mechanics and Control Division ofthe National Aerospace Laboratories (NAL), Bangalore. His areas of work include: modelling and parameteres timation of aerospace vehicles and sensor failure detection and management. He worked as Guest Scientistat the Institute of Flight Mechanics of German Amspace Research Establishment and Institute of FlightMechanics, Braunschweig, Germany, for six months during 1993. He is a member of the Aeronautical Society of India.

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Published
2013-01-01
How to Cite
Kumar, N. (2013). Input Excitation Techniques for Aerodynamic Derivatives Estimation of Highly Augmented Fighter Aircraft. Defence Science Journal, 49(3), 187-196. https://doi.org/10.14429/dsj.49.3828
Issue
Vol 49 No 3
Section
Aeronautical Systems
Copyright (c) 2016 Defence Science Journal

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