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Engineering Review : International journal for publishing of original researches from the aspect of structural analysis, materials and new technologies in the field of mechanical engineering, shipbuilding, fundamental engineering sciences, computer sciences, electrical engin, Vol. 37 No. 3, 2017.

Original scientific paper

Stability region of closed-loop pilot-vehicle system for fly-by-wire aircraft with limited actuator rate

Li Ying-hui ; School of Aeronautics and Astronautics Engineering, Air Force Engineering University, Xi' an
Qu Liang ; School of Aeronautics and Astronautics Engineering, Air Force Engineering University, Xi' an
Xu Hao-jun ; School of Aeronautics and Astronautics Engineering, Air Force Engineering University, Xi' an
Cao Qi-meng ; School of Aeronautics and Astronautics Engineering, Air Force Engineering University, Xi' an

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Abstract

The category-II PIO (Pilot Induced Oscillations) caused by actuator rate limitation of fly-by-wire airplanes will badly threaten the flight safety. The stability regions of closed-loop pilot-vehicle (CLPV) system with rate limited actuator were studied in this paper to assess stability of such CLPV system. The augmented state  variables were introduced to segregate the rate limited element from the primary  system in order to build the saturation nonlinear model of CLPV system. To get the maximal stability region, firstly, the estimation of the stability region of CLPV system is transformed into convex optimization problem; secondly, the Schur  complement lemma is applied to transform the convex optimization problem into
linear matrix inequalities(LMIs) formulations; finally, the ellipsoidal stability region estimation algorithm is obtained. The time-domain simulation results show that the estimated stability region is slightly conservative and within the real  stability region of CLPV system. The category II PIO of static unstable fly-by-wire airplanes is a kind of much rapid divergent oscillation instead of limit cycle oscillation. Moreover, the stability region is distinctly influenced by the pilot  controlling gains and the actuator rate limitation value, the proposed stability  region method exhibits clear physical concept and intuitionistic results.

Keywords

pilot induced oscillation; rate limited actuator; closed-loop pilot-vehicle system; stability regions; linear matrix inequality

Hrčak ID:

184815

URI

https://hrcak.srce.hr/184815

Publication date:

18.7.2017.

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