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Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile.

Mariusz Jacewicz1, Piotr Lichota1, Dariusz Miedziński1

  • 1Division of Mechanics, Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology, Nowowiejska 24, 00-665 Warsaw, Poland.

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Lateral correction thrusters significantly reduce rocket impact point dispersion. This study analyzed uncertainties using control algorithms and Monte Carlo simulations for improved accuracy.

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Area of Science:

  • Aerospace Engineering
  • Guidance, Navigation, and Control

Background:

  • Accurate projectile and rocket guidance is crucial for mission success.
  • Uncertainties in aerodynamic parameters, thrust, initial conditions, and inertial measurement units (IMU) affect impact point accuracy.

Purpose of the Study:

  • To analyze the effectiveness of lateral correction thrusters in reducing impact point dispersion.
  • To evaluate the performance of two control algorithms under various uncertainty sources.

Main Methods:

  • A generic rocket mathematical and simulation model was developed in MATLAB/Simulink.
  • The Monte Carlo approach was employed for simulations.
  • Circular Error Probable (CEP) was used to quantify dispersion.

Main Results:

  • Both control algorithms demonstrated a significant reduction in impact point dispersion.
  • The simulations quantified the impact of different uncertainty sources on guidance accuracy.

Conclusions:

  • Lateral correction thrusters are effective in mitigating dispersion for guided projectiles.
  • The implemented control algorithms enhance accuracy despite inherent system uncertainties.