Characterization of Thermochemical Properties and Combustion Behavior In AP/HTPB Polymer Composite Solid Propellant for Enhanced Performance

Year : 2025 | Volume : 13 | Special Issue 03 | Page : 502 511
    By

    P.N. Kadiresh,

  • K. Raja,

  • S.P. Venkatesan,

  1. Professor and Head, Department of Aerospace Engineering, B.S. Abdur Rahman Crescent Institute of Science and Technology, Vandalur, Chennai, Tamil Nadu, India
  2. Associate Professor, Department of Mechanical Engineering, Vel Tech Rangarajan Dr Sagunthala R&D Institute of Science and Technology, Avadi, Chennai, Tamil Nadu, India
  3. Associate Professor, Department of Mechanical Engineering, Sathyabama Institute of Science and Technology, Chennai, Tamil Nadu, India

Abstract

The thermal decomposition of solid propellants containing hydroxyl-terminated polybutadiene (HTPB) binder is a complex process, driven by multiple interacting chemical and physical factors. Solid propellant combustion characteristics are profoundly influenced by the composition of the propellant, the conditions of pressure, the starting temperature, and a range of aero-thermochemical parameters. The paper explores the influence of polymeric structure in the HTPB binder on thermal decomposition characteristics of the AP/HTPB composite propellants and correlates material properties to superior performance results in composite formulations of relevance to aerospace applications. In this study, the thermal decomposition of AP/HTPB based propellant samples are analyzed through thermo-gravimetric analysis and differential thermal analysis traces were obtained on a simultaneous thermal analyzer. Thermogravimetric analysis facilitates the investigation of decomposition kinetics in solid rocket propellants. Thermogravimetric analysis is executed to assess the thermal decomposition behaviors of propellants samples across a temperature range of 27℃ to 927 ℃ at different heating rates. Propellant samples weighing 2.5 mg to 3 mg have been used for the analysis. The rate at which a solid composite propellant burns is a crucial ballistic characteristic, closely linked to the highest decomposition temperature seen in particular formulations of the propellant. The activation energy, inferred from the slope of the Kissinger plot, was found to be 230.64 kJ/mol.

Keywords: Rocket propellants, hydroxyl-terminated polybutadiene binder, Thermal decomposition, thermo-gravimetric analysis and differential thermal analysis.

[This article belongs to Special Issue under section in Journal of Polymer and Composites (jopc)]

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How to cite this article:
P.N. Kadiresh, K. Raja, S.P. Venkatesan. Characterization of Thermochemical Properties and Combustion Behavior In AP/HTPB Polymer Composite Solid Propellant for Enhanced Performance. Journal of Polymer and Composites. 2025; 13(03):502-511.
How to cite this URL:
P.N. Kadiresh, K. Raja, S.P. Venkatesan. Characterization of Thermochemical Properties and Combustion Behavior In AP/HTPB Polymer Composite Solid Propellant for Enhanced Performance. Journal of Polymer and Composites. 2025; 13(03):502-511. Available from: https://journals.stmjournals.com/jopc/article=2025/view=212660


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Special Issue Subscription Original Research
Volume 13
Special Issue 03
Received 04/11/2024
Accepted 03/12/2024
Published 01/05/2025
Publication Time 178 Days
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