Nozzle Flow Computation of Classical Hybrid Rocket Motors

TIAN Hui; CAI Guo-biao; WANG Hui-yu; ZHANG Zhen-peng

Volume 20 Issue 1

Feb. 2005

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TIAN Hui, CAI Guo-biao, WANG Hui-yu, ZHANG Zhen-peng. Nozzle Flow Computation of Classical Hybrid Rocket Motors[J]. Journal of Aerospace Power, 2005, 20(1): 142-146.

Citation:

TIAN Hui, CAI Guo-biao, WANG Hui-yu, ZHANG Zhen-peng. Nozzle Flow Computation of Classical Hybrid Rocket Motors[J]. Journal of Aerospace Power, 2005, 20(1): 142-146.

TIAN Hui, CAI Guo-biao, WANG Hui-yu, ZHANG Zhen-peng. Nozzle Flow Computation of Classical Hybrid Rocket Motors[J]. Journal of Aerospace Power, 2005, 20(1): 142-146.

Citation:

TIAN Hui, CAI Guo-biao, WANG Hui-yu, ZHANG Zhen-peng. Nozzle Flow Computation of Classical Hybrid Rocket Motors[J]. Journal of Aerospace Power, 2005, 20(1): 142-146.

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Nozzle Flow Computation of Classical Hybrid Rocket Motors

School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing100083,China

Received Date: 2004-01-13
Rev Recd Date: 2004-03-23
Publish Date: 2005-02-28

Abstract

Abstract

Numerical solutions of full Navier-Stokes equations with chemical reaction flow were established for the nozzle flow of the LOX/HTPB hybrid rocket motor.Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used.A chemical reaction model with 8 components and 10 elementary reactions was presented.The nozzle entrance condition was obtained by thermodynamic calculation.The nozzle flows under several different oxidizer mass flow rates and grain length were calculated.The relationship between oxidizer mass flow rate and specific impulse was analyzed,which will be useful for the hybrid rocket motor design.
- aerospace propulsion system,
- hybrid propellant rockets,
- nozzle flow,
- rate of combustion,
- thermodynamic calculations,
- performance calculation