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Ignition transient simulation in solid propellant rocket motors

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

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  1. Type of Document: Article
  2. DOI: 10.2514/6.2007-1419
  3. Publisher: American Institute of Aeronautics and Astronautics Inc , 2007
  4. Abstract:
  5. In this paper, the internal ballistics of a solid propellant rocket motor including a pyrogen type igniter is numerically investigated. The aim of the simulation is to calculate the chamber pressure as a function of time, during flame spreading phase. In addition, effects of the igniter flow on the propellant heat-up and ignition are studied in detail using unsteady quasi one-dimensional conservation equations for a working gas, coupled with the transient conduction within a solid propellant. The convective and radiative heat flux from the igniter flow to the solid surface is considered. The flow-field equations are solved using upwind Roe's scheme. The obtained results can be used to design more appropriate igniters for solid rocket motors
  6. Keywords:
  7. Computer simulation ; Flow fields ; Heat flux ; Ignition systems ; Numerical analysis ; Propellants ; Transient analysis ; Internal ballistics ; Propellant rocket motor ; Roe's scheme ; Solid surface ; Rocket engines
  8. Source: 45th AIAA Aerospace Sciences Meeting 2007, Reno, NV, 8 January 2007 through 11 January 2007 ; Volume 24 , 2007 , Pages 16754-16758 ; 1563478900 (ISBN); 9781563478901 (ISBN)
  9. URL: https://arc.aiaa.org/doi/10.2514/6.2007-1419