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<p>Hybrid-rocket propulsion, which combines the benefits of both liquid and solid propulsion, has gained attention for its safety, throttling capability, and cost-effectiveness. This study presents a combined experimental and theoretical investigation of a hybrid rocket engine using PVC/DBP as fuel and gaseous oxygen as the oxidizer. Four successive firings were conducted to analyze thrust, regression rate, chamber pressure, and specific impulse. NASA CEA was used to model the ideal combustion parameters. The PVC-DBP fuel formulation offers advantages such as ease of processing, availability, and controlled burning behavior. A series of experimental static tests were conducted using a hybrid-rocket engine equipped with a showerhead injector and a convergent-divergent nozzle. The findings demonstrate an inverse correlation between the mass flux of the oxidizer and the regression rate, with measurements dropping from 0.94 to 0.70&#xa0;mm/s. over successive firings as port diameter increased from 15 to 28.15 mm. Thrust measurements followed a similar trend, declining from 220 to 50&#xa0;N, reflecting reduced combustion intensity due to oxidizer dilution. Combustion efficiency improved from 52.16 to 59.55%, suggesting enhanced fuel regression dynamics across multiple firings. Additionally, comparative analysis reveals significant deviations from ideal behavior due to combustion inefficiencies and thermal losses, highlighting the need for nozzle and chamber optimization in practical hybrid engine systems.</p>

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Experimental and theoretical investigation of combustion efficiency, regression rate, and thrust characteristics of a hybrid rocket engine using PVC/DBP fuel

  • 期刊论文

  • 发表日期：

    2025年8月4日

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  • Akash Pawar,
  • Aneena Praveen,
  • Harikrishna Chavhan,
  • Amit Kumar Thakur

摘要

Hybrid-rocket propulsion, which combines the benefits of both liquid and solid propulsion, has gained attention for its safety, throttling capability, and cost-effectiveness. This study presents a combined experimental and theoretical investigation of a hybrid rocket engine using PVC/DBP as fuel and gaseous oxygen as the oxidizer. Four successive firings were conducted to analyze thrust, regression rate, chamber pressure, and specific impulse. NASA CEA was used to model the ideal combustion parameters. The PVC-DBP fuel formulation offers advantages such as ease of processing, availability, and controlled burning behavior. A series of experimental static tests were conducted using a hybrid-rocket engine equipped with a showerhead injector and a convergent-divergent nozzle. The findings demonstrate an inverse correlation between the mass flux of the oxidizer and the regression rate, with measurements dropping from 0.94 to 0.70 mm/s. over successive firings as port diameter increased from 15 to 28.15 mm. Thrust measurements followed a similar trend, declining from 220 to 50 N, reflecting reduced combustion intensity due to oxidizer dilution. Combustion efficiency improved from 52.16 to 59.55%, suggesting enhanced fuel regression dynamics across multiple firings. Additionally, comparative analysis reveals significant deviations from ideal behavior due to combustion inefficiencies and thermal losses, highlighting the need for nozzle and chamber optimization in practical hybrid engine systems.