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<p>The objective of the proposed study is to evaluate the burn rate of boron-based propellant formulations, providing detailed insights into their combustion properties. Burn rate tests are vital for understanding burning duration and ensuring composition uniformity. The methodology combines experimental analysis with NASA’s Chemical Equilibrium with Applications (CEA) simulations to model the combustion behavior of the propellant compositions. Burn rate tests are conducted under varying pressure conditions using a Window Bomb setup, ensuring precise and reliable measurements. This formulation aims to improve the burn rate by 3–5%, optimizing performance for ducted ramjet applications. The novelty of the proposed work is to develop a binary composite mixture of boron and Viton A, enhanced with a suitable burn rate modifier. Viton plays a dual role by providing additional oxygen and aiding in the vaporization of the oxide layer on boron particles, which enhances combustion efficiency. The proposed method can be used for solid propellant based rocket engine as well as few high speed applications vehicles.</p>

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Burn rate characteristics of boron based solid propellant for ducted rocket applications

  • 期刊论文

  • 发表日期：

    2025年8月13日

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  • P. N. Kadiresh,
  • T. Selvakumaran,
  • K. Balaji

摘要

The objective of the proposed study is to evaluate the burn rate of boron-based propellant formulations, providing detailed insights into their combustion properties. Burn rate tests are vital for understanding burning duration and ensuring composition uniformity. The methodology combines experimental analysis with NASA’s Chemical Equilibrium with Applications (CEA) simulations to model the combustion behavior of the propellant compositions. Burn rate tests are conducted under varying pressure conditions using a Window Bomb setup, ensuring precise and reliable measurements. This formulation aims to improve the burn rate by 3–5%, optimizing performance for ducted ramjet applications. The novelty of the proposed work is to develop a binary composite mixture of boron and Viton A, enhanced with a suitable burn rate modifier. Viton plays a dual role by providing additional oxygen and aiding in the vaporization of the oxide layer on boron particles, which enhances combustion efficiency. The proposed method can be used for solid propellant based rocket engine as well as few high speed applications vehicles.