Design of a Thrust Cut-off System for Launch Vehicles with Solid Rocket Motors

Authors

DOI:

https://doi.org/10.20535/2521-1943.2025.9.3(106).337052

Keywords:

thrust termination, post-shutdown impulse, solid propellant motor, reverse nozzle, trajectory accuracy

Abstract

The article investigates a thrust termination system for solid-propellant vehicles motors, aimed at achieving precise shutdown of thrust without separating the vehicle’s payload section. Despite the existence of various thrust termination techniques, the influence of nozzle configuration on post-shutdown impulse and combustion stability remains insufficiently studied. The objective of the research is to minimize the residual impulse through the application of a reverse-thrust system utilizing dedicated termination nozzles mounted on the forward dome of the motor casing. To achieve this, the study analyzes nozzle geometry, flow orientation, chamber pressure before and after shutdown, and thrust coefficients for both main and termination nozzles. It is established that placing the termination nozzles at an angle of 40° relative to the motor axis and selecting an appropriate throat area enables significant reduction of post-shutdown impulse to a level that ensures stable thrust termination without degrading trajectory accuracy. This effect is attributed to the compensation of the main thrust vector by the directed reaction force produced by the termination nozzles. Unlike charge quenching or annular slit opening methods, the proposed solution does not require nozzle block displacement or injection of extinguishing agents, which simplifies the system and improves reliability. The results can be applied in the development of special-purpose vehicle systems, where structural integrity and high trajectory precision after motor burnout are critical.

References

  1. M. Bondarenko and M. Vorobei, “Modern air defense methods and countermeasures for use in operational-tactical missiles”, Challenges and Issues of Modern Science, vol. 2, pp. 175-183, 2024. Available: https://cims.fti.dp.ua/j/article/view/188.
  2. A. H. Abdul Hamid, M. H. Mohamad Aliman, Z. Salleh, M. J. Sujana , O. Ismail, M. A. Muhammad and M. A. Mohd Fazli, "Transient Thermal Analysis of Solid Propellant Rocket Motor", Journal of Applied Engineering Design and Simulation, vol. 2, no. 1, pp. 1-8, 2022. DOI: https://doi.org/10.24191/jaeds.v2i1.44.
  3. J. M. Tizón, “Burnback Analysis of Solid Propellant Rocket Motors”, arXiv, 2023. [Preprint]. DOI: https://doi.org/10.48550/arXiv.2301.04559.
  4. G. Xu, B. Wang, P. Liu and Y. Guan, “Numerical investigation of the velocity-coupled response of propellant burning rate in a solid rocket motor”, Aerospace Science and Technology, vol. 161, p. 110118, 2025. DOI: https://doi.org/10.1016/j.ast.2025.110118.
    |
  5. M. Bondarenko, V. Habrinets and M. Vorobei, “Preliminary Design Evaluation of Solid-Propellant Rocket Engines”, Challenges and Issues of Modern Science, vol. 4, no. 2, p. 279, 2025. DOI: https://doi.org/10.15421/cims.4.279.
  6. R. Wang, J. Li, B. Wang, S. Ai, D. Wang, Q. Li and N. Wang, “Theoretical and experimental study on combustion response of aluminized solid propellant under acceleration effects”, Acta Astronautica, vol. 225, pp. 186-202, 2024. DOI: https://doi.org/10.1016/j.actaastro.2024.08.042.
    |
  7. A. M. Abdelraouf, O. K. Mahmoud and M. A. Al-Sanabawy, “Thrust termination of solid rocket motor”, Journal of Physics: Conference Series, vol. 2299, no. 1, p. 012018, 2022. DOI: https://doi.org/10.1088/1742-6596/2299/1/012018.
    |
  8. V. R. Ghoradel and H. Mahdavy-Moghaddam, “Simulation and Parametric Analysis of Thrust Reverser System in Solid Fuel Engines”, Journal of Space Science and Technology, vol. 16, no. 2, pp. 1-17, 2023. DOI: https://doi.org/10.30699/jsst.2023.1409.
  9. D.-S. Ha and H. J. Kim, “Dynamic characteristic modeling and simulation of an aerospike-shaped pintle nozzle for variable thrust of a solid rocket motor”, Acta Astronautica, vol. 201, pp. 364-375, 2022. DOI: https://doi.org/10.1016/j.actaastro.2022.09.031.
    |
  10. K. Sreejith, S. Prasad, R. Bagavathiappan, C. Prasanth, R. Jeenu, J. P. Murugan et al., “Design, development, static and flight tests of reverse flow multiple nozzle solid rocket motor with high burn rate propellant”, Current Science, vol. 120, no. 1, pp. 116-121, 2021. DOI: https://www.jstor.org/stable/27310146.
    |
  11. B. Bibhorr and C. R. Anand, "Supplemented Thrust Reversal Contraption for Enhanced Flight Termination System (EFTS)", in 2021 2nd International Conference on Range Technology (ICORT), Chandipur, Balasore, India, 2021, pp. 1-5. DOI: https://doi.org/10.1109/ICORT52730.2021.9581587.
    |
  12. M. Bondarenko, V. Habrinets and M. Vorobei, “Open-source analysis of the potential configuration and kinetic performance of the Oreshnik ballistic missile”, Challenges and Issues of Modern Science, vol. 4, no. 1, pp. 36-42, 2025. DOI: https://doi.org/10.15421/cims.4.306.
  13. M. Zhu, Y. Li, X. Chen, C. Zhou, J. Mi, T. Liu and W. Li, “Nonlinear adaptive robust control strategy of thrust regulation for pintle solid-propellant rocket motors”, Energy, vol. 329, p. 136741, 2025. DOI: https://doi.org/10.1016/j.energy.2025.136741.
    |
  14. C. Merkle and M. Summerfield, “Extinguishment of solid propellants by depressurization – Effects of propellant parameters”, in 7th Aerospace Sciences Meeting, New York, NY, USA, 1969. DOI: https://doi.org/10.2514/6.1969-176.
  15. C. A. Chase, Pioneers in Propulsion – A History of CSD Pratt & Whitney’s Solid Rocket Company. Available: https://gobluechase.files.wordpress.com/2014/08/pioneers-in-propulsion-final.pdf.
  16. C. Guo, Z. Wei, K. Xie and N. Wang, “Thrust Control by Fluidic Injection in Solid Rocket Motors”, Journal of Propulsion and Power, vol. 33, no. 4, pp. 815-829, 2017. DOI: https://doi.org/10.2514/1.B36264.
    |
  17. M. Bondarenko and V. Habrinets, “Thrust Vector Control of Solid Propellant Operative-Tactical Rockets”, Challenges and Issues of Modern Science, vol. 1, pp. 68-73, 2023. Available: https://cims.fti.dp.ua/j/article/view/14.
  18. J. Cha and É. J. de Oliveira, “Performance Comparison of Control Strategies for a Variable-Thrust Solid-Propellant Rocket Motor”, Aerospace, vol. 9, no. 6, p. 325, 2022. DOI: https://doi.org/10.3390/aerospace9060325.

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Published

2025-09-29

How to Cite

[1]
M. Bondarenko, “Design of a Thrust Cut-off System for Launch Vehicles with Solid Rocket Motors”, Mech. Adv. Technol., vol. 9, no. 3(106), pp. 386–394, Sep. 2025.

Issue

Vol. 9 No. 3(106) (2025)

Section

Aviation Systems and Technologies

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Copyright (c) 2025 Микола Бондаренко

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