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Effects of Dual Oxidizers on the Properties of Composite Solid Rocket Propellants

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Chemical Rocket Propulsion

Part of the book series: Springer Aerospace Technology ((SAT))

Abstract

The microstructures and granular distribution of different oxidizers (AP, HMX, CL-20, GUDN, and ADN) were investigated. Several industrial and research types of hydroxyl-terminated polybutadiene (HTPB)-based composite solid rocket propellants containing different dual oxidizers (with a fraction of AP in the reference formulation replaced by HMX, CL-20, GUDN, or ADN), but featuring the same nominal composition, were prepared. The energetic properties and hazardous properties of the corresponding solid propellants were analyzed. The effects of the kind of dual oxidizers on the strand burning rate and pressure exponent of propellants were investigated. Thermal decomposition and the mechanical properties of propellants were also analyzed. It was shown that AP and prilled ADN particles are approximately ball shaped and more uniform than that of the others, while CL-20 is the most irregular one. The application of different oxidizers to composite solid propellants was revealed as feasible, and samples could be cast in vacuum and cured safely. Compositions with ADN or CL-20 filler show higher performance in terms of specific impulse, heat of explosion, burning rate, and density, but are more sensitive to impact and friction. The mechanical properties of mono-oxidizer AP-based composition (reference composition) are superior to those of the others.

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Abbreviations

ADN:

Ammonium dinitramide

AP:

Ammonium perchlorate

cAP:

Coarse ammonium perchlorate

CL-20:

2,4,6,8,10,12-Hexanitro-2,4,6,8,10,12-hexaazaisowurtzitane

CP:

Composite propellant

fAP:

Fine ammonium perchlorate

GFP:

Catocene

GUDN:

N-Guanylurea-dinitramide

HMX:

Cyclotetramethylenetetranitramine

HTPB:

Hydroxyl-terminated polybutadiene

RDX:

Cyclotrimethylenetrinitramine

SEM:

Scanning electron microscopy

TATB:

1,3,5-Triamino-2,4,6-trinitrobenzene

TDI:

2,4-Toluene diisocyanate

\( \overline{M} \) :

Mean molecular mass

a :

Pre-exponential factor of steady burning rate law

d 10 :

Particle diameter corresponding to 10 % of cumulative undersize distribution μm

d 50 :

Mean particle diameter μm

d 90 :

Particle diameter corresponding to 90 % of cumulative undersize distribution μm

E :

Elastic modulus MPa

I s :

Gravimetric specific impulse

n :

Pressure exponent of steady burning rate law

p :

Pressure MPa

Q v :

Heat of explosion

r b :

Steady burning rate mm·s−1

Span:

Extent of particle size distribution defined as (d 90–d 10)/d 50

T c :

Combustion temperature

T p :

Peak temperature

T peak :

Exothermic peak temperature

△ I s :

Specific impulse variation with respect to the reference formulation

ε m :

Elongation at maximum tensile strength %

η :

Viscosity Pa·s

ρ :

Density g·cm−3

σ m :

Maximum tensile strength MPa

τ:

Yield stress MPa

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Acknowledgments

This work is the combined output of several research groups. The authors wish to thank Dr. QiLong Yan, Faculty of Chemical Technology, University of Pardubice, Czech Republic, for useful suggestions in the English statements. Thanks are also due to the colleagues of Science and Technology on Combustion and Explosion Laboratory of Xi’an Modern Chemistry Research Institute for providing many helpful suggestions for the experiments.

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Authors and Affiliations

  1. Xi’an Modern Chemistry Research Institute, Xi’an, 710065, Shaanxi, China

    Wei Qiang Pang, Hui Xiang Xu, Xue Zhong Fan, Feng Qi Zhao & Wu Xi Xie

  2. Space Propulsion Laboratory (SPLab), Department of Aerospace Science and Technology, Politecnico di Milano, 10256, Milan, Italy

    Wei Qiang Pang & Luigi T. DeLuca

Authors
  1. Wei Qiang Pang
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  2. Luigi T. DeLuca
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  4. Xue Zhong Fan
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  5. Feng Qi Zhao
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  6. Wu Xi Xie
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Correspondence to Wei Qiang Pang .

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Editors and Affiliations

  1. Space Propulsion Laboratory (SPLab) Department of Aerospace Science and Technology, Politecnico di Milano, Milan, Italy

    Luigi T. De Luca

  2. Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), Sagamihara, Japan

    Toru Shimada

  3. Department of Chemical Engineering, Mendeleev University of Chemical Technology, Moscow, Russia

    Valery P. Sinditskii

  4. The Inner Arch, Poissy, France

    Max Calabro

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Pang, W.Q., DeLuca, L.T., Xu, H.X., Fan, X.Z., Zhao, F.Q., Xie, W.X. (2017). Effects of Dual Oxidizers on the Properties of Composite Solid Rocket Propellants. In: De Luca, L., Shimada, T., Sinditskii, V., Calabro, M. (eds) Chemical Rocket Propulsion. Springer Aerospace Technology. Springer, Cham. https://doi.org/10.1007/978-3-319-27748-6_17

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  • DOI: https://doi.org/10.1007/978-3-319-27748-6_17

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