Thrust termination 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: 10.2514/1.26576
  3. Publisher: American Institute of Aeronautics and Astronautics Inc , 2007
  4. Abstract:
  5. Thrust termination dynamics of a solid propellant rocket motor that is crucial to the performance of the rocket has been analyzed. Active thrust termination or reversing of a separating motor facilitate the staging process and enhance the performance of a multistage rocket. This can be achieved by opening a secondary nozzle located on the motor head and causing rapid depressurization of the motor chamber. The strong dependence of the solid propellant burning rate on the chamber pressure causes a transient nonlinear behavior that can result in premature dynamic extinguishments of the motor. It was confirmed that there is a maximum achievable level of equilibrium reverse thrust due to enlargement of the nozzle throat area. It has also been recommended that to avoid undesirable transient reverse thrust, the exit diameter should be decreased or the diverging part of the secondary nozzle should be eliminated
  6. Keywords:
  7. Nozzles ; Rocket engines ; Thrust bearings ; Transient analysis ; Depressurization ; Dynamic extinguishments ; Thrust termination dynamics ; Transient nonlinear behavior ; Solid propellants
  8. Source: Journal of Propulsion and Power ; Volume 23, Issue 5 , 2007 , Pages 1141-1142 ; 07484658 (ISSN)
  9. URL: https://arc.aiaa.org/doi/10.2514/1.26576