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Rapid depressurization dynamics of solid propellant rocket motors

Tahsini, A. M ; Sharif University of Technology | 2007

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  1. Type of Document: Article
  2. DOI: 10.2514/6.2007-5802
  3. Publisher: American Institute of Aeronautics and Astronautics Inc , 2007
  4. Abstract:
  5. Transient internal ballistics of a solid propellant rocket motor during rapid depressurization due to opening of an auxiliary nozzle for active thrust termination has been considered in this work. Prediction of thrust termination and reversing dynamics is required for successful stage separation in multi-stage rockets. Quasi one-dimensional unsteady Euler equation with a transient propellant burning model that accounts for the effects of time rate of change of the chamber pressure on the burning rate have been used to simulate the internal ballistics of a rocket motor. The compressible convective flow solver used in this study is based on Roe's scheme. The effects of rapid chamber pressure decrease on the propellant and motor transient behavior have been studied. Prediction of the level of transient thrust reversing, time delay for thrust termination, and the effects of the auxiliary nozzle geometry on thrust reverse and thrust termination have been achieved. It has been shown that there is considerable thrust reversing during an active thrust termination process due to the auxiliary nozzle's gas dynamics
  6. Keywords:
  7. Euler equations ; Gas dynamics ; Nozzles ; Pressure regulation ; Rocket engines ; Auxiliary nozzles ; Depressurization dynamics ; Multi-stage rockets ; Nozzle geometry ; Thrust termination ; Solid propellants
  8. Source: 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Cincinnati, OH, 8 July 2007 through 11 July 2007 ; Volume 8 , 2007 , Pages 7871-7879 ; 1563479036 (ISBN); 9781563479038 (ISBN)
  9. URL: https://arc.aiaa.org/doi/abs/10.2514/6.2007-5802