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Improved estimation of lateral-directional derivatives of an augmented aircraft using filter error method

Published online by Cambridge University Press:  04 July 2016

J. Singh  and
J. R. Raol
J. Singh
Affiliation:
Scientists, Flight Mechanics and Control Division, National Aerospace Laboratories (NAL), Bangalore, India
J. R. Raol
Affiliation:
Scientists, Flight Mechanics and Control Division, National Aerospace Laboratories (NAL), Bangalore, India
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Abstract

For an augmented aircraft, it is shown that filter error method leads to improved identifiability of aerodynamic parameters from measurements that are affected by the feedback from the flight controller. Simulated lateral-directional data of an advanced fighter aircraft, obtained from a nonlinear six-degree-of-freedom simulator, are used for the purpose of analysis. The aircraft stability and control derivatives are estimated using filter error method and compared to the estimates obtained from output error method to ascertain the degree of improvement achieved in the identified derivatives. Identification results with output error method show that feedback causes a discernible offset in the estimated values of the derivatives relative to the reference parameter values. The filter error method helps to reduce this offset and thereby yield estimates that match better with the reference parameter values.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1035 , May 2000 , pp. 209 - 214
Copyright
Copyright © Royal Aeronautical Society 2000 

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