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Integrated Guidance and Control Using Model Predictive Control with Flight Path Angle Prediction against Pull-Up

Jongho Park1, Youngil Kim2, Jong-Han Kim3

  • 1Department of Military Digital Convergence, Ajou University, Suwon 16499, Korea.

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Summary

This study introduces an integrated guidance and control system using model predictive control for missile interception of maneuvering targets. The algorithm effectively estimates target motion and predicts future positions for enhanced interception capabilities.

Keywords:
convex optimizationintegrated guidance and controlmodel predictive controlterminal homing

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Area of Science:

  • Aerospace Engineering
  • Control Systems Engineering
  • Robotics

Background:

  • Missile guidance systems require advanced control strategies to effectively engage maneuvering targets.
  • Model predictive control (MPC) offers a robust framework for handling complex dynamics and constraints in guidance applications.
  • Accurate target state estimation is crucial for successful interception, especially against dynamic threats.

Purpose of the Study:

  • To develop and validate an integrated guidance and control algorithm for terminal homing missiles targeting maneuvering adversaries.
  • To implement a model predictive control (MPC) strategy that incorporates missile dynamics and operational constraints.
  • To enhance target state estimation and prediction using an extended Kalman filter (EKF) and polynomial fitting.

Main Methods:

  • Development of missile equations of motion, including short-period and actuator dynamics.
  • Formulation and solution of a convex optimization problem for guidance commands, subject to acceleration and look angle constraints.
  • Utilizing a discrete-time extended Kalman filter (EKF) for target position estimation based on look angle measurements.
  • Employing polynomial fitting for predicting the target's future flight-path angle.

Main Results:

  • The proposed integrated guidance and control algorithm demonstrated effective performance in simulations against maneuvering targets.
  • The EKF successfully estimated target states, providing crucial data for the MPC controller.
  • Numerical simulations, including Monte Carlo analysis, confirmed the robustness and accuracy of the developed algorithm.

Conclusions:

  • The integrated guidance and control approach using MPC provides a viable solution for missile interception of maneuvering targets.
  • The combination of EKF for estimation and MPC for control offers a powerful strategy for terminal homing applications.
  • The algorithm's ability to handle constraints and predict target motion ensures improved interception success rates.