Terminal Angle Optimization of Missiles Using Probabilistic Monte Carlo Simulation

Authors

  • Shilfa Nisa Agustin Universitas Pertahanan Republik Indonesia
  • Y. H. Yogaswara Universitas Pertahanan Republik Indonesia
  • Robertus Heru Thirarjanto Organisasi Riset Penerbangan dan Antariksa, BRIN
  • Larasmoyo Nugroho Organisasi Riset Penerbangan dan Antariksa, BRIN

Keywords:

loitering munitions, missiles, Monte Carlo simulation, statistical optimization, terminal angle

Abstract

Modern missiles, loitering munitions, and glide bombs are increasingly utilized due to their high-precision strike capabilities. However, in urban and complex environments where targets are often hidden behind obstacles, these systems frequently fail to achieve optimal terminal impact angles. This study addresses the limitations of conventional GPS/INS systems by optimizing the terminal angle using a numerical statistical approach based on Monte Carlo simulation. The simulation was conducted on an online cloud platform with 10,000 iterations to handle operational uncertainties. The results demonstrated a reduction in vertical angle error of up to 31.6%, an increase in altitude error of 10.7%, and an increase in hit probability to 84.8% compared to conventional methods. This approach enables missiles to achieve a more effective balance between penetration capability and impact accuracy, which is critical in contested and cluttered battlefields. This study concludes that integrating Monte Carlo simulation provides a more robust solution for improving attack effectiveness in complex environments. Future research is recommended to include hardware-in-the-loop testing and artificial intelligence integration.

 

References

Li et al., “Adaptive Terminal Time and Impact Angle Constraint Cooperative Guidance Strategy,” Drones, vol. 8, no. 4, p. 134, 2024. doi: 10.3390/drones8040134.

Li et al., “Terminal Impact Angle Control Guidance Law Considering Target Observability,” Aerospace, vol. 9, no. 4, p. 193, 2022. doi: 10.3390/aerospace9040193.

Song et al., “Impact-Angle-Control Guidance Law with Terminal Constraints on Curvature of Trajectory,” Mathematics, vol. 11, no. 4, p. 974, 2023. doi: 10.3390/math11040974.

Hu et al., “Deep Reinforcement Learning-Based Impact Angle Constrained Guidance Law for Hypersonic Vehicles,” Mathematics, vol. 13, no. 6, p. 987, 2025. doi: 10.3390/math13060987.

Jacewicz et al., “Study of Model Uncertainties Influence on the Impact Point Dispersion,” Sensors, vol. 22, no. 9, p. 3257, 2022. doi: 10.3390/s22093257.

Specht et al., “Testing and Analysis of Selected Navigation Parameters,” Sensors, vol. 24, no. 8, p. 2418, 2024. doi: 10.3390/s24082418.

Li et al., “Optimal Cooperative Guidance Strategies for Aircraft Defense with Impact Angle Constraints,” Aerospace, vol. 9, no. 11, p. 710, 2022. doi: 10.3390/aerospace9110710.

Sun et al., “Simulation and Optimization of Multi-Phase Terminal Trajectory for Three-Dimensional Anti-Ship Missiles Based on Hybrid MOPSO,” Algorithms, vol. 18, no. 5, p. 278, 2025. doi: 10.3390/a18050278.

Z. Hu et al., “Terminal guidance law under multiple constraints of high-order reshaping of relative range profile,” Acta Aeronautica et Astronautica Sinica, vol. 46, no. 6, 2025. doi: 10.7727/S1000-6893.2024.31405.

Shi et al., “Multiple Constraints-Based Adaptive Three-Dimensional Guidance Law,” Aerospace, vol. 9, no. 12, p. 796, 2022. doi: 10.3390/aerospace9120796.

Yang et al., “Dynamic Encircling Cooperative Guidance for Intercepting Superior Targets with Overload, Impact Angle and Simultaneous Time Constraints,” Aerospace, vol. 11, no. 5, p. 377, 2024. doi: 10.3390/aerospace11050377.

Zhang et al., “Impact-Angle and Terminal-Maneuvering-Acceleration Constrained Guidance,” Aerospace, vol. 9, no. 1, p. 22, 2022. doi: 10.3390/aerospace9010022.

Ceotto et al., “RocketPy: Six Degrees-of-Freedom Rocket Trajectory Simulator,” Journal of Aerospace Engineering, vol. 34, no. 6, 2021. doi: 10.1061/(ASCE)AS.1943-5525.0000130.

Hodžić et al., “Missile Guidance using Proportional Navigation and Machine Learning,” Journal of Engineering Research and Sciences, vol. 3, no. 3, 2024. doi: 10.55708/js0303003.

Liu et al., “Minimum-Data-Driven Guidance for Impact Angle Control,” Aerospace, vol. 11, no. 5, p. 376, 2024. doi: 10.3390/aerospace11050376.

Xian et al., “Impact point prediction guidance of ballistic missiles in high maneuver penetration conditions,” Defense Technology, 2023. doi: 10.1016/j.dt.2022.XX.

Bekhiti et al., “A Novel Three-Dimensional Sliding Pursuit Guidance and Control for Missile Interception,” Technologies, vol. 13, no. 5, p. 171, 2025. doi: 10.3390/technologies13050171.

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Published

2026-06-29

Issue

Vol. 6 No. 1 (2026): Fuse-teknik Elektro

Section

Artikel

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This work is licensed under a Creative Commons Attribution-ShareAlike 4.0 International License.

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