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Transient conduction prediction in nozzle assembly of solid rocket motors

Ebrahimi, M ; Sharif University of Technology | 2007

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  1. Type of Document: Article
  2. DOI: 10.2514/6.2007-202
  3. Publisher: 2007
  4. Abstract:
  5. Transient heat-up of a solid propellant rocket structure during motor burning time is studied, numerically. The solid phase energy equation coupled with unsteady compressible flow equations are used in this simulation. The flow-field equations are discretized and solved using upwind Roe's scheme. The results show that heat transfer from the gas phase boundaries has negligible effect on internal ballistics behavior. On the other hand, the results are suitable for a thermal stresses analysis in the chamber case and are consequently valuable from structural design viewpoints
  6. Keywords:
  7. Solid phase energy equation ; Solid rocket motors ; Transient conduction prediction ; Computer simulation ; Flow measurement ; Heat conduction ; Nozzles ; Solid propellants ; Thermal stress ; Rocket engines
  8. Source: 45th AIAA Aerospace Sciences Meeting 2007, Reno, NV, 8 January 2007 through 11 January 2007 ; Volume 4 , 2007 , Pages 2333-2337 ; 1563478900 (ISBN); 9781563478901 (ISBN)
  9. URL: https://arc.aiaa.org/doi/abs/10.2514/6.2007-202