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<p>This paper details a robust attitude and guidance control framework for the VS-50 suborbital launch vehicle, a Brazilian-German cooperative project. The strategy uses a state feedback architecture with Linear Matrix Inequality (LMI)-synthesized time-varying parameters to ensure stability and performance. A quadratic Lyapunov function addresses parametric variations, ensuring robustness against inherent dynamic uncertainties. This computationally efficient, mathematically grounded approach, unlike conventional gain-scheduling, bridges theoretical synthesis with practical implementation. Hardware-in-the-loop (HIL) simulations validate the controller, showing stable attitude regulation under disturbances and improved trajectory tracking with guidance control. Results confirm VS-50’s viability as a micro-satellite launch vehicle precursor and establish a scalable orbital framework. The integration of Lyapunov stability, LMI optimization, and HIL validation offers a replicable methodology for advanced aerospace systems, distinct from classical ad hoc strategies. Comprehensive supplementary material, including detailed mathematical models, control architectures, and HIL validation results, is available at [<CitationRef CitationID="CR1">1</CitationRef>].</p>

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Robust Attitude and Guidance Control for a Launch Vehicle System: A Lyapunov-LMI Framework with HIL Validation

  • 期刊论文

  • 出版模式：

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  • 发表日期：

    2025年8月27日

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  • Roberto Brusnicki,
  • Cesar Moura Batagini,
  • Josef Ettl,
  • Renan Lima Pereira

摘要

This paper details a robust attitude and guidance control framework for the VS-50 suborbital launch vehicle, a Brazilian-German cooperative project. The strategy uses a state feedback architecture with Linear Matrix Inequality (LMI)-synthesized time-varying parameters to ensure stability and performance. A quadratic Lyapunov function addresses parametric variations, ensuring robustness against inherent dynamic uncertainties. This computationally efficient, mathematically grounded approach, unlike conventional gain-scheduling, bridges theoretical synthesis with practical implementation. Hardware-in-the-loop (HIL) simulations validate the controller, showing stable attitude regulation under disturbances and improved trajectory tracking with guidance control. Results confirm VS-50’s viability as a micro-satellite launch vehicle precursor and establish a scalable orbital framework. The integration of Lyapunov stability, LMI optimization, and HIL validation offers a replicable methodology for advanced aerospace systems, distinct from classical ad hoc strategies. Comprehensive supplementary material, including detailed mathematical models, control architectures, and HIL validation results, is available at [1].