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Swirl effects on spinning solid propellant rocket motor performance

Tahsini, A. M ; Sharif University of Technology | 2006

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  1. Type of Document: Article
  2. DOI: 10.2514/6.2006-4781
  3. Publisher: American Institute of Aeronautics and Astronautics Inc , 2006
  4. Abstract:
  5. Spining is used in some of solid rocket motors to increase the flight trajectory precision or for stability requirements. The angular acceleration due to the spin increases the burning rate of solid propellant and changes the motor performance by increasing the operating pressure and decreasing the burning time. On the other hand, due to the rocket and its grain rotation, the gases injected from propellant surface to the flow field have an initial angular velocity. The angular velocity of each particle increases as it approaches to the center due to the conservation of angular momentum and a reduction in its radial location, although it vanishes close to the central axis due to viscous effect. These events produce a highly swirling flow in the combustion chamber which changes the radial pressure distribution and discharge coefficient of the nozzle and finally changes the pressure-time history of the engine. Here we have a dual balancing effect between increase of pressure caused by higher burning rate and decrease of pressure due to this swirling effect. The 3D simulation is needed to predict the internal ballistics of these motors accurately and observe simultaneously both of these phenomena. It is achieved here by numerical simulation of Navier_Stokes equations using a finite volume scheme applied on a structured grid. For flux computations, Roe's scheme is used
  6. Keywords:
  7. Acceleration ; Angular momentum ; Angular velocity ; Computer simulation ; Rocket engines ; Swirling flow ; Trajectories ; Angular acceleration ; Flight trajectory ; Propellant surface ; Swirl effects ; Solid propellants
  8. Source: AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference, Sacramento, CA, 9 July 2006 through 12 July 2006 ; Volume 6 , 2006 , Pages 4586-4590 ; 1563478188 (ISBN); 9781563478185 (ISBN)
  9. URL: https://arc.aiaa.org/doi/10.2514/6.2006-4781