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Numerical and experimental investigation on the effects of aft mixing chamber diaphragm in hybrid rocket motor

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Abstract

This paper focuses on the investigation of an aft mixing chamber diaphragm in a hybrid rocket motor. Both numerical and experimental researches are carried out to study its effects on the motor performances. The hybrid rocket motor with star fuel grain is utilized. The 90% hydrogen peroxide (HP) oxidizer and hydroxyl terminated polybutadiene (HTPB) based fuel are adopted as propellants. The diaphragm configuration settled in the aft mixing chamber includes four circular-holes with a uniform circumferential distribution. For both motors with and without the diaphragm, three-dimensional numerical simulations with gaseous combustions considered are carried out to study the flow field characteristics and motor performances. The comparison results show that the diaphragm can improve the mixing of the oxidizer and fuel. It has evident effect on increasing the motor efficiencies. Two firing experiments are conducted with full scale motors to investigate the effects of the diaphragm. The diaphragm used in the test is composed of a central steel framework and a closed thermal insulation layer. With the diaphragm employed, the combustion efficiency increases from 93.9% to 97.34% and the specific impulse efficiency increases from 80.77% to 87.28%, which verifies the positive effect of the diaphragm. Both numerical and experimental studies indicate that the scheme of the aft mixing chamber diaphragm proposed in the paper can improve the efficiencies of the hybrid rocket motor obviously.

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Abbreviations

A :

Arrhenius pre-exponential constant

c :

molar concentration

c*:

characteristic velocity

E :

activation energy

H :

enthalpy

I s :

specific impulse

k :

kinetic energy of turbulent fluctuation

M :

molecular weight

\(\dot m\) :

mass flow rate

n :

normal direction

OF :

oxidizer to fuel ratio

P :

pressure

R :

universal gas constant

r :

fuel regression rate

T :

temperature

t :

time

V :

volume

X,Y,Z :

coordinate system

Y :

mass fraction

ɛ :

turbulence dissipation rate

ρ :

density

λ :

thermal conductivity

η :

efficiency

c:

combustion chamber

cg:

combustion chamber gases

est:

estimated

exp:

experimental

f:

fuel

g:

combustion gas

o:

oxidizer

ref:

reference

s:

fuel surface, resident

theo:

theoretical

References

  1. Chiaverini M J, Kuo K K. eds. Fundamentals of hybrid rocket combustion and propulsion. Vol 28: Progress in Astronautics and Aeronautics. Reston, Virginia: AIAA, 2006

    Google Scholar 

  2. Dyer J, Doran E, Dunn Z, et al. Design and development of a 100 km nitrous oxide/paraffin hybrid rocket vehicle. AIAA Paper 2007-5362, 2007

    Google Scholar 

  3. Larsen C R. Development of guide to commercial space transportation reusable launch vehicle operations & maintenance. AIAA Paper 2005-6795, 2005

    Google Scholar 

  4. Taylor F W, Howard R. Dream chaser for space transportation: tourism, NASA and military integrated on a Atlas V. AIAA Paper 2008-7837, 2008

    Google Scholar 

  5. Rao D L, Cai G B, Zhu H, et al. Design and optimization of variable thrust hybrid rocket motors for sounding rockets. Sci China Tech Sci, 2012, 55(1): 125–135

    Article  Google Scholar 

  6. Li J H, Yu N J, Zeng P, et al. Design and integrated simulation of a pressurized feed system of the dual-thrust hybrid rocket motor. Sci China Tech Sci, 2013, 56(4): 989–1000

    Article  Google Scholar 

  7. Li X T, Tian H, Cai G B. Numerical analysis of fuel regression rate distribution characteristics in hybrid rocket motors with different fuel types. Sci China Tech Sci, 2013, 56(7): 1807–1817

    Article  Google Scholar 

  8. Farbar E, Louwers J, Kaya T. Investigation of metallized and nonmetallized hydroxyl terminated polybutadiene/hydrogen peroxide hybrid rockets. J Propul Power, 2007, 23(2): 476–486

    Article  Google Scholar 

  9. George P, Krishnan S, Varkey P M, et al. Fuel regression rate in hydroxyl-terminated-polybutadiene/gaseous-oxygen hybrid rocket motors. J Propul Power, 2001, 17(1): 35–42

    Article  Google Scholar 

  10. Risha G A, Ulas A, Boyer E, et al. Combustion of HTPB-Based solid fuels containing nano-sized energetic powder in a hybrid rocket motor. AIAA Paper 2001-3535, 2001

    Google Scholar 

  11. Jansen R, Teegarden E, Gimelshein S. Characterization of a vortex-flow end-burning hybrid rocket motor for nanosatellite applications. AIAA Paper 2012-0125, 2012

    Google Scholar 

  12. Lee C, Na Y, Lee J, et al. Effect of induced swirl flow on regression rate of hybrid rocket fuel by helical grain configuration. Aerosp Sci Technol, 2007, (11): 68–76

    Google Scholar 

  13. Knuth W H, Chiaverini M J, Sauer J A, et al. Solid-fuel regression rate behavior of vortex hybrid rocket engines. J Propul Power, 2002, 18(3): 600–609

    Article  Google Scholar 

  14. Lee C, Na Y, Lee G. The enhancement of regression rate of hybrid rocket fuel by helical grain configuration and swirl flow. AIAA Paper 2005-3906, 2005

    Google Scholar 

  15. Bettella A, Lazzarin M, Bellomo N, et al. Testing and CFD simulation of diaphragm hybrid rocket motors. AIAA Paper 2011-6023, 2011

    Google Scholar 

  16. Grosse M. Effect of a diaphragm on performance and fuel regression of a laboratory scale hybrid rocket motor using nitrous oxide and paraffin. AIAA Paper 2009-5113, 2009

    Google Scholar 

  17. Bellomo N, Lazzarin M, Barato F, et al. Numerical investigation of the effect of a diaphragm on the performance of a hybrid rocket motor. AIAA Paper 2010-7033, 2010

    Google Scholar 

  18. Kim H, Kim S, Woo K, et al. Investigation on the effect of liquefying diaphragm in hybrid rocket motors using paraffin-based fuel. AIAA Paper 2011-5824, 2011

    Google Scholar 

  19. Venkateswaran S, Deshpande M, Merkle C L. The Application of preconditioning to reacting flow cornputations. AIAA Paper 95-1673, 1995

    Google Scholar 

  20. Shih T H, Liou W W, Shabbir A, et al. A new k-ɛ eddy-viscosity model for high reynolds number turbulent flows-model development and validation. Computers Fluids, 1995, 24(3): 227–238, 346

    Article  MATH  Google Scholar 

  21. Chiaverini M J, Harting G C, Lu Y, et al. Pyrolysis behavior of hybrid rocket solid fuels under rapid heating conditions. AIAA Paper 97-3078, 1997

    Google Scholar 

  22. Cohen N S, Fleming R W, Derr R L. Role of binders in solid propellant combustion. AIAA J, 1974, 12(2): 212–218

    Article  Google Scholar 

  23. Venkateswaran S, Merkle C L. Size scale-up in hyrid rocket motors. AIAA Paper 96-0647, 1996

    Google Scholar 

  24. Magnussen B F, Hjertager B H. On mathematical models of turbulent combustion with special emphasis on soot formation and combustion. Symp (Int) Combus, 1977, 16(1): 719–729

    Article  Google Scholar 

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Authors and Affiliations

  1. School of Astronautics, Beihang University, Beijing, 100191, China

    Hui Tian, XinTian Li, NanJia Yu & GuoBiao Cai

Authors
  1. Hui Tian
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  2. XinTian Li
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  3. NanJia Yu
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  4. GuoBiao Cai
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Correspondence to GuoBiao Cai.

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Tian, H., Li, X., Yu, N. et al. Numerical and experimental investigation on the effects of aft mixing chamber diaphragm in hybrid rocket motor. Sci. China Technol. Sci. 56, 2721–2731 (2013). https://doi.org/10.1007/s11431-013-5325-z

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  • DOI: https://doi.org/10.1007/s11431-013-5325-z

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