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Optimal Input Design for Aircraft Stability and Control Flight Testing

Author

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  • Eugene A. Morelli

    (NASA Langley Research Center)

Abstract

Flight testing to characterize aircraft stability and control is a complex and expensive task that involves restrictive practical constraints. Methods are examined for optimizing the inputs applied to aircraft controls during flight test maneuvers to produce informative flight data. Theory underpinning optimal input design for stability and control flight testing is explained. The merits and limitations of optimal inputs are discussed, along with optimization approaches and practical considerations involved in applying optimal inputs in a real flight test environment. Simulated and flight test case studies of optimal multiple-input design for aircraft stability and control flight testing are presented and discussed.

Suggested Citation

  • Eugene A. Morelli, 2021. "Optimal Input Design for Aircraft Stability and Control Flight Testing," Journal of Optimization Theory and Applications, Springer, vol. 191(2), pages 415-439, December.
    • Handle: RePEc:spr:joptap:v:191:y:2021:i:2:d:10.1007_s10957-021-01912-0
    DOI: 10.1007/s10957-021-01912-0
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    References listed on IDEAS

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    1. Smith, M.W.A. & Roberts, A.P., 1978. "An exact equivalence between the discrete- and continuous-time formulations of the Kalman filter," Mathematics and Computers in Simulation (MATCOM), Elsevier, vol. 20(2), pages 102-109.
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    1. Smith, M.W.A. & Roberts, A.P., 1978. "A Kalman filter type of extension to a deterministic gradient technique for parameter estimation," Mathematics and Computers in Simulation (MATCOM), Elsevier, vol. 20(4), pages 291-300.
    2. Woolfson, M.S. & Hui, S.Y.R., 1996. "Application of the transmission line method to the solution of the continuous Kalman filter equations of general order," Mathematics and Computers in Simulation (MATCOM), Elsevier, vol. 42(1), pages 15-33.

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