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<p>This paper presents the development and validation of a Passive Fault-Tolerant Control (PFTC) strategy for a supersonic missile based on the H<sub>∞</sub> robust-control framework. The objective is to ensure stability and performance in the presence of severe nonlinearities, aerodynamic uncertainties, and multiple simultaneous faults that typify high-speed missile environments. The proposed controller is synthesized from a linearized model around a supersonic trim condition and implemented directly on the full nonlinear six-degree-of-freedom (6-DOF) missile dynamics. Fault scenarios include actuator loss of effectiveness (30%), actuator saturation, aerodynamic-parameter uncertainties (± 50%), symmetric inertia degradation (± 80%), and sensor faults with additive bias and noise. The results demonstrate that the <i>H∞</i>-based PFTC maintains full attitude stabilization and aerodynamic equilibrium under all combined degradations, outperforming an LQR benchmark that fails even under single-fault conditions. Simulation outcomes confirm fast convergence of Euler angles and angular rates, bounded control deflections within saturation limits, and stable aerodynamic and energy balance across the flight envelope. Under combined 30% actuator loss, ± 50% aerodynamic uncertainty, and ± 80% inertia degradation, all attitude states settled within 3&#xa0;s and control deflections remained below 0.5&#xa0;rad, confirming quantitative robustness. The study highlights that integrating robustness at the design stage provides inherent tolerance to parametric deviations and physical limitations without requiring fault detection or controller reconfiguration. This work contributes a comprehensive demonstrations of passive fault tolerance for supersonic missiles, bridging the gap between theoretical robustness and realistic fault conditions in nonlinear missile flight dynamics. The contribution of this work lies in the development of a missile-oriented PFTC framework and its systematic nonlinear validation under multiple simultaneous fault conditions, rather than in proposing a new H∞ control law.</p>

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Passive Fault-Tolerant Control For Supersonic Missile

  • 期刊论文

  • 发表日期：

    2026年6月14日

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  • Kutaibah Srour,
  • Sohayb Abdulkerim

摘要

This paper presents the development and validation of a Passive Fault-Tolerant Control (PFTC) strategy for a supersonic missile based on the H∞ robust-control framework. The objective is to ensure stability and performance in the presence of severe nonlinearities, aerodynamic uncertainties, and multiple simultaneous faults that typify high-speed missile environments. The proposed controller is synthesized from a linearized model around a supersonic trim condition and implemented directly on the full nonlinear six-degree-of-freedom (6-DOF) missile dynamics. Fault scenarios include actuator loss of effectiveness (30%), actuator saturation, aerodynamic-parameter uncertainties (± 50%), symmetric inertia degradation (± 80%), and sensor faults with additive bias and noise. The results demonstrate that the H∞-based PFTC maintains full attitude stabilization and aerodynamic equilibrium under all combined degradations, outperforming an LQR benchmark that fails even under single-fault conditions. Simulation outcomes confirm fast convergence of Euler angles and angular rates, bounded control deflections within saturation limits, and stable aerodynamic and energy balance across the flight envelope. Under combined 30% actuator loss, ± 50% aerodynamic uncertainty, and ± 80% inertia degradation, all attitude states settled within 3 s and control deflections remained below 0.5 rad, confirming quantitative robustness. The study highlights that integrating robustness at the design stage provides inherent tolerance to parametric deviations and physical limitations without requiring fault detection or controller reconfiguration. This work contributes a comprehensive demonstrations of passive fault tolerance for supersonic missiles, bridging the gap between theoretical robustness and realistic fault conditions in nonlinear missile flight dynamics. The contribution of this work lies in the development of a missile-oriented PFTC framework and its systematic nonlinear validation under multiple simultaneous fault conditions, rather than in proposing a new H∞ control law.