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Stability analysis for inverse simulation of aircraft

Published online by Cambridge University Press:  04 July 2016

K. M. Yip  and
G. Leng
K. M. Yip
Affiliation:
Aerospace Engineering GroupDepartment of Mechanical EngineeringNational University of Singapore, Singapore
G. Leng
Affiliation:
Aerospace Engineering GroupDepartment of Mechanical EngineeringNational University of Singapore, Singapore
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Abstract

The integration inverse method has been extensively investigated in the past decade; however, none of the researches fully addresses the stability analysis of the method that is crucial to successful implementation. This paper presents a stability test to analyse the global stability of the integration inverse method for linear time-invariant systems. A stable solution may be obtained from careful selection of the discretisation interval using the proposed stability test. A discrete model is derived to approximate the Newton's scheme in the inverse method. With this approximate model, the stability of the inverse method can be examined. The stability test is exact for linear systems and can be extended to the inverse method for non-linear aircraft simulations by considering an equivalent linear model for each point of the flight envelopes. Guidelines for selection of appropriate reference points in the inverse simulation are given.

Type
Research Article
Information
The Aeronautical Journal , Volume 102 , Issue 1016 , July 1998 , pp. 345 - 351
Copyright
Copyright © Royal Aeronautical Society 1998 

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