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Pressurization system in tanks ensures maintenance of desired pressure in the propellant tank of launch vehicles. Tank pressure during the transient operation of the engine over shoots, if the outflow of propellant to the engine is low due to the early start of pressurization system, and dips, if there is delay in the start of pressurization system. Start sequence of pressurization system is dependent on ullage volume, tank pre-pressurization requirements, regulation pressure and engine propellant consumption. The start transient characteristics of the system can be validated only during the developmental hot test of stage. Deviation, if any, observed in the system performance may result in re-design of the pressurization system. Thus, to understand and predict the propellant tank ullage pressure build-up during start transient, a non-conventional experiment was carried out simulating the pressurization system, different ullage volumes of propellant tanks and propellant expulsion rate as expected in flight. An available mathematical model to capture the start transient characteristics was validated with the experimental results. With the validated mathematical model, pressurization system start sequence and tank pressure evolution prediction for various input conditions can be estimated which is required for launch vehicle mission planning.

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A Novel Approach for Capturing Pressurization System Start Transients and Sensitivity of Ullage Volume in a Propellant Tank

  • 会议论文

  • 发表日期：

    2026年

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  • V. Unnikrishnan,
  • Akash Kasina,
  • Sourabh Karmarkar,
  • B. Suresh Babu,
  • Reji Joseph,
  • P. R. Ajayalal,
  • K. Senthil Vel

摘要

Pressurization system in tanks ensures maintenance of desired pressure in the propellant tank of launch vehicles. Tank pressure during the transient operation of the engine over shoots, if the outflow of propellant to the engine is low due to the early start of pressurization system, and dips, if there is delay in the start of pressurization system. Start sequence of pressurization system is dependent on ullage volume, tank pre-pressurization requirements, regulation pressure and engine propellant consumption. The start transient characteristics of the system can be validated only during the developmental hot test of stage. Deviation, if any, observed in the system performance may result in re-design of the pressurization system. Thus, to understand and predict the propellant tank ullage pressure build-up during start transient, a non-conventional experiment was carried out simulating the pressurization system, different ullage volumes of propellant tanks and propellant expulsion rate as expected in flight. An available mathematical model to capture the start transient characteristics was validated with the experimental results. With the validated mathematical model, pressurization system start sequence and tank pressure evolution prediction for various input conditions can be estimated which is required for launch vehicle mission planning.