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Journal of Projectiles, Rockets, Missiles and Guidance >

2017 , Vol. 37 >Issue 4: 84 - 87

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2017.04.020

ROCKETS TECHNOLOGY

Analysis of Combustion Characteristics of Solid Rocket Scramjet

  • LIU Zai ,
  • CHEN Linquan ,
  • WU Qiu
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  • The 41st Institute of the Fourth Academy, CASC, Xi'an 710025, China

Received date: 2016-09-18

  Online published: 2025-05-28

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Abstract

In this paper, the combustion characteristics of solid rocket scramjet under different inflow conditions were studied by numerical simulation. The internal flow field of engine was simulated by using the two order upwind format based on density, and the turbulence model and combustion model adopted SST k-ω model and eddy dissipation model respectively. The results indicated that the flame temperature and the maximum chemical reaction rate both increased with the increase of inflow Mach number. The combustion efficiency decreased with the increase of inflow Mach number, and the combustion efficiency was lower than 50%. The decrease of combustion efficiency led to the decrease of thrust and specific impulse of secondary combustion chamber. With the change of inflow Mach number, the fuel rich gas consumption should be adjust appropriately to ensure the combustion performance of engine.

Key words： numerical simulation; solid rocket scramjet; secondary combustion chamber; combustion efficiency

Cite this article

LIU Zai , CHEN Linquan , WU Qiu . Analysis of Combustion Characteristics of Solid Rocket Scramjet[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2017 , 37(4) : 84 -87 . DOI: 10.15892/j.cnki.djzdxb.2017.04.020

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