Robust nonlinear control of a hypersonic aircraft

Qian Wang, Robert F. Stengel

    Research output: Contribution to journalArticle

    479 Citations (Scopus)

    Abstract

    For the longitudinal motion of a hypersonic aircraft containing 28 inertial and aerodynamic uncertain parameters, robust flight control systems with nonlinear dynamic inversion structure are synthesized. The system robustness is characterized by the probability of instability and probabilities of violations of 38 performance criteria, subject to the variations of the uncertain system parameters. The design cost function is defined as a weighted quadratic sum of these probabilities. The control system is designed using a genetic algorithm to search a design parameter space of the nonlinear-dynamic-inversion structure. During the search iteration, Monte Carlo evaluation is used to estimate the system robustness and cost function. This approach explicitly takes into account the design requirements and makes full use of engineering knowledge in the design process to produce practical and efficient control systems.

    Original languageEnglish (US)
    Pages (from-to)577-585
    Number of pages9
    JournalJournal of Guidance, Control, and Dynamics
    Volume23
    Issue number4
    DOIs
    StatePublished - Jan 1 2000

    Fingerprint

    hypersonic aircraft
    Hypersonic vehicles
    Nonlinear Control
    Robust Control
    Aircraft
    aircraft
    control system
    Nonlinear Dynamics
    Cost Function
    Inversion
    Control System
    Cost functions
    Robustness
    Flight Control System
    Knowledge Engineering
    Uncertain Parameters
    uncertain systems
    inversions
    Uncertain Systems
    costs

    All Science Journal Classification (ASJC) codes

    • Control and Systems Engineering
    • Aerospace Engineering
    • Space and Planetary Science
    • Electrical and Electronic Engineering
    • Applied Mathematics

    Cite this

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    abstract = "For the longitudinal motion of a hypersonic aircraft containing 28 inertial and aerodynamic uncertain parameters, robust flight control systems with nonlinear dynamic inversion structure are synthesized. The system robustness is characterized by the probability of instability and probabilities of violations of 38 performance criteria, subject to the variations of the uncertain system parameters. The design cost function is defined as a weighted quadratic sum of these probabilities. The control system is designed using a genetic algorithm to search a design parameter space of the nonlinear-dynamic-inversion structure. During the search iteration, Monte Carlo evaluation is used to estimate the system robustness and cost function. This approach explicitly takes into account the design requirements and makes full use of engineering knowledge in the design process to produce practical and efficient control systems.",
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    Robust nonlinear control of a hypersonic aircraft. / Wang, Qian; Stengel, Robert F.

    In: Journal of Guidance, Control, and Dynamics, Vol. 23, No. 4, 01.01.2000, p. 577-585.

    Research output: Contribution to journalArticle

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