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The development of reusable rockets has attracted much attention to save the space mission cost. This study proposes a design method of control system for automatic landing of rockets based on nonlinear model predictive control. The system model considered here consists of the 6° of freedom motion, nonlinearity of dynamics, variation of fuel mass, and manipulation of gimbal angles and aerodynamic coefficients. The objective of this paper is to propose a control system design method based on model predictive control for automatic landing of reusable rockets with considering the variation of fuel mass and the manipulation of gimbal angles and aerodynamic coefficients. The effectiveness of the proposed method is verified by numerical simulations.

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Nonlinear Model Predictive Control for Landing Guidance of Reusable Rocket with Manipulation of Gimbal Angles and Aerodynamic Coefficients

  • 会议论文

  • 发表日期：

    2026年

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  • Taisuke Iwabuchi,
  • Tomoaki Hashimoto

摘要

The development of reusable rockets has attracted much attention to save the space mission cost. This study proposes a design method of control system for automatic landing of rockets based on nonlinear model predictive control. The system model considered here consists of the 6° of freedom motion, nonlinearity of dynamics, variation of fuel mass, and manipulation of gimbal angles and aerodynamic coefficients. The objective of this paper is to propose a control system design method based on model predictive control for automatic landing of reusable rockets with considering the variation of fuel mass and the manipulation of gimbal angles and aerodynamic coefficients. The effectiveness of the proposed method is verified by numerical simulations.