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<p>This paper presents a novel nonlinear method for the theoretical prediction of Pogo dynamic loads on a multi-stage launch vehicle, with emphasis on the structural response of complex upper-stage configuration. The methodology is based on nonlinear mathematical modeling of the dynamic interaction between the liquid-propulsion system and the rocket structure. The model accounts for the non-stationarity of dynamic processes in vehicle systems, nonlinearities arising from cavitation phenomena in the main engine pumps, and the amplitude-dependent damping of rocket structure vibrations. A detailed finite element approach is employed to capture the specific features of the upper stage’s spatial layout. The proposed method was applied to predict Pogo dynamic loads for a three-stage liquid launch vehicle equipped with a new sphero-conical upper stage under flight conditions. The results indicate that the predicted Pogo acceleration amplitudes at the upper-stage mounting interface exceed the flight oscillations of a two-stage prototype: reaching 0.4&#xa0;<i>g</i> during the first interval of Pogo instability and 0.5&#xa0;<i>g</i> during the second.</p>

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Theoretical prediction of dynamic loads on the upper stage structure during the longitudinal instability of a multi-stage launch vehicle

  • 期刊论文

  • 发表日期：

    2026年6月29日

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  • Olexiy Nikolayev,
  • Inna Bashlii,
  • Sergey Dolgopolov,
  • Nataliia Khoriak

摘要

This paper presents a novel nonlinear method for the theoretical prediction of Pogo dynamic loads on a multi-stage launch vehicle, with emphasis on the structural response of complex upper-stage configuration. The methodology is based on nonlinear mathematical modeling of the dynamic interaction between the liquid-propulsion system and the rocket structure. The model accounts for the non-stationarity of dynamic processes in vehicle systems, nonlinearities arising from cavitation phenomena in the main engine pumps, and the amplitude-dependent damping of rocket structure vibrations. A detailed finite element approach is employed to capture the specific features of the upper stage’s spatial layout. The proposed method was applied to predict Pogo dynamic loads for a three-stage liquid launch vehicle equipped with a new sphero-conical upper stage under flight conditions. The results indicate that the predicted Pogo acceleration amplitudes at the upper-stage mounting interface exceed the flight oscillations of a two-stage prototype: reaching 0.4 g during the first interval of Pogo instability and 0.5 g during the second.