Sequential H2-optimization procedure for robust flight control law's parametric synthesis

Authors

  • А. А. Tunik Національний авіаційний університет
  • Е. М. Krinetskaya Національний авіаційний університет

DOI:

https://doi.org/10.18372/2306-1472.3.9377

Abstract

Sequential iterative procedure of Flight Control Law (FCL) robust parametric optimization is proposed. The 1st step of this procedure is the application of the convex optimization procedure with quadratic performance index whose coefficients are chosen on the basis of airworthiness require­ments. The steps are made for enlargement of the stability domain in the space of variable parameters applying aforementioned procedure for composite performance index constructed from components, which depend on the influence of parametric disturbances. Practical example illustrates efficiency of this procedure

References

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J.Doyle, K.Glover, P.Khargonekar,B.Francis.State-Space Solution to Standard H2 and Hoo Control Problems.//IEEE Transactions on Automatic Control.Vol.34, No.8, Aug. 1989. P. 831-847.

B.D.Anderson , J. B. Moore. Optimal Control .Linear Quadratic Methods. // Prentice Hall International Inc., 1989. - 380 p.

P.L.D.Peres, J.C.Jeromel. H2 Control for Discrete-Time Systems Optimality and Robustness. Automatika, Vol.29, 1993, No.l,p.p.225 - 228.

F.A.Aliev, V.B.Larin. Optimization of Linear Control Systems. Analytical Methods and Computational Algorithms // Gordon and Breach Science Publishers, 1998. - 272 p.

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How to Cite

Tunik А. А., & Krinetskaya Е. М. (1999). Sequential H2-optimization procedure for robust flight control law’s parametric synthesis. Proceedings of National Aviation University, 3(2), 86–91. https://doi.org/10.18372/2306-1472.3.9377

Issue

Vol. 3 No. 2 (1999)

Section

MODERN AVIATION AND SPACE TEHNOLOGY

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