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

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 si...

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Bibliographic Details
Published in:Aeronautical journal 2000-05, Vol.104 (1035), p.209-214
Main Authors: Singh, J., Raol, J. R.
Format: Article
Language:English
Subjects:
Air transportation and traffic
Applied sciences
Degrees of freedom (mechanics)
Error analysis
Exact sciences and technology
Flight simulators
Ground, air and sea transportation, marine construction
Signal filtering and prediction
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Summary: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.
ISSN:0001-9240
2059-6464
DOI:10.1017/S0001924000091442