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Transient Burning of nAl-Loaded Solid Rocket Propellants

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Innovative Energetic Materials: Properties, Combustion Performance and Application

Abstract

The introduction of nano-sized energetic ingredients first occurred in Russia about 60 years ago and produced great expectations in the rocket propulsion community. While steady combustion regimes of solid rocket propellants loaded with nanometals are discussed in a companion paper, several instances of unsteady combustion regimes are examined in this paper. Ignition, extinction by fast depressurization, self-sustained oscillatory burning, pressure deflagration limit, and other transient burning processes are considered. Both steady and unsteady combustion papers describe the main features in terms of solid propellant performance and intend to emphasize the unique properties or operating conditions made possible by the addition of nano-sized energetic ingredients. Attention is mainly focused on nAl addition to AP/HTPB formulations, the workhorse of solid space launcher motors.

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Abbreviations

ADN:

Ammonium DiNitramide

AFM:

Atomic Force Microscopy

Alex :

ALuminum Electro-eXploded

ALICE:

ALuminum-ICE

AN:

Ammonium Nitrate

AP:

Ammonium Perchlorate

APT:

Advanced Powder Technologies, Tomsk, Russia

ARM:

Arrested Reactive Milling

ASD-4, -6:

Conventional μAl powders (used in Russia)

BET:

Brunauer–Emmett–Teller

BR or BKL:

Butyl rubber (used as inert binder in Russia)

CCP:

Condensed Combustion Products

C/F:

Coarse/Fine

CL-20:

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

CMDB:

Composite Modified Double-Base

DB:

Double-Base

DOA:

DiOctyl Adipate (plasticizer)

DOS:

Di(2-ehtylhexyl) Sebacate, also known as Dioctyl Sebacate (plasticizer)

EB:

Energetic Binder

EDX (EDS):

Energy Dispersive X-ray analysis

EEW:

Electrical Explosion of Wires

EM:

Energetic Materials

EMCDB:

Elastomer Modified Cast Double-Base

EnC:

Energetic NanoComposites

ESD:

ElectroStatic Discharge

FGL:

First Gasification Line (ignitability threshold)

GNG:

Ignition boundary determined by Go/No-Go testing (flame retention threshold)

HEM:

High-Energy Material

HMX:

Cyclotetramethylenetetranitramine

HTPB:

Hydroxyl-terminated polybutadiene (plasticized by transformer oil in Russia)

H-Alex:

ALuminum EXploded, coated by HTPB

ICKC:

Institute of Chemical Kinetics and Combustion, Novosibirsk, Russia

ICP:

Institute of Chemical Physics, Moscow, Russia

IPDI:

IsoPhorone DiIsocyanate (curing agent)

IR:

InfraRed

LEF:

Leading Edge Flame

MIC:

Metastable Intermolecular Composites

MPVT-LD:

Tetrazole copolymer plasticized by mixed nitroester (used as EB in Russia)

nAl:

Nano-sized Al particles

nAl@NA:

Nano-sized Al particles coated with nickel acetylacetonate

nAl@OA:

Nano-sized Al particles coated with oleic acid

nAl@PA:

Nano-sized Al particles coated with perfluorotetradecanoic acid

nAlloy:

Alloy of nano-sized particles

nBiMe:

Nano-sized BiMetallic particles

nEM:

Nano-sized Energetic Materials

nFe2O3:

Nano-sized Fe2O3

nMe:

Nano-sized Metal particles

nonAl:

NonAluminized formulations

NC:

NitroCellulose

NG:

NitroGlycerine

PB:

PolyButadiene

PBAN:

PolyButadiene AcryloNitrile

PCP:

PolyCaprolactone triols

PDL:

Pressure Deflagration Limit

PEI:

PolyEthyleneImine

PS:

PolySulfide

QE:

Quinol Ether

RDX:

Cyclotrimethylenetrinitramine

SKD, SKDM:

Butadiene rubber plasticized by transformer oil (used as inert binder in Russia)

SPLab:

Space Propulsion Laboratory, Politecnico di Milano, Milan, Italy

SRM:

Solid Rocket Motor

TDI:

Toluene Di-Isocyanate (curing agent)

ZN:

Zeldovich–Novozhilov

μAl:

Micron-sized Al particles

μEM:

Micron-sized Energetic Materials

µscale:

Micron-sized scale

2P:

Two-phase flow

bif :

Bifurcation

c…, c c , c g :

Specific heat, in the condensed-phase, in the gas-phase, J/(g K)

c-phase:

Condensed-phase

d 43 :

Mass average diameter, cm

d AN :

Average diameter AN particles

d AP :

Average diameter AP particles

g-phase:

Gas-phase

k :

ZN sensitivity parameter of steady mass burning rate to initial temperature

k…, k c , k g :

Thermal conductivity, in the condensed-phase, in the gas-phase, W/(cm K)

n :

Pressure exponent in the Vieille steady burning rate law

n q :

Slope of the FGL ignition boundary in logarithmic plot

p, p i , p f :

Pressure, initial pressure, final pressure, MPa

q :

Radiant flux intensity, W/cm2

q c,s :

Conductive heat flux to the condensed-phase from burning surface, W/cm2

q g,s :

Conductive heat flux to burning surface from the gas-phase, W/cm2

r :

ZN sensitivity parameter of steady surface temperature to initial temperature

r b :

Steady burning rate, cm/s

s :

Burning surface

S sp :

Specific surface area, m2/g

u g :

Steady average gas-phase velocity in the flame zone, m/s

t, t ign :

Time, ignition delay time, s

\(t_{th,c}^{*}\), \(t_{th,g}^{*}\):

Characteristic time thermal wave in the condensed-phase, in the gas-phase, s

\(\it t_{{ext}}^{*}\) :

Characteristic time external disturbance, s

T :

Temperature, K

α…, α c , α g :

Thermal diffusivity, in the condensed-phase, in the gas-phase, cm2/s

ρ…, ρ c , ρ g :

Density, in the condensed-phase, in the gas-phase, g/cm3

σ p :

Steady burning rate temperature sensitivity, 1/K

Ω :

\(= 2\pi \cdot {\text{frequency}} \cdot \alpha_{c} /\left( {r_{b} } \right)^{2}\), nondimensional circular frequency

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Acknowledgments

Useful and clarifying discussions are gratefully acknowledged with:

• Mr. Giovanni Colombo, Politecnico di Milano, Milan, Italy;

• Prof. Alexander B. Vorozhtsov and Dr. Marat I. Lerner, Tomsk State University, Tomsk, Russia;

• Dr. Alexander A. Gromov and Dr. Alexander G. Korotkikh, Tomsk Polytechnic University, Tomsk, Russia.

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Authors and Affiliations

  1. Space Propulsion Laboratory (SPLab), Politecnico di Milano, 20156, Milan, Italy

    Luigi T. DeLuca

  2. Nanjing University of Science and Technology, Nanjing, China

    Luigi T. DeLuca

  3. Science and Technology on Combustion and Explosion Laboratory, Xi’an Modern Chemistry Research Institute, Xi’an, 710065, Shaanxi, China

    WeiQiang Pang

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  1. Luigi T. DeLuca
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  2. WeiQiang Pang
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Correspondence to Luigi T. DeLuca .

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Editors and Affiliations

  1. Science and Technology on Combustion and Explosion Laboratory, Xi’an Modern Chemistry Research Institute, Xi’an, China

    WeiQiang Pang

  2. Space Propulsion Laboratory (RET), Politecnico di Milano, Milan, Italy

    Luigi T. DeLuca

  3. Department of Non-Ferrous Metal and Gold, National University of Science and Technology “MISiS”, Moscow, Russia

    Alexander A. Gromov

  4. School of Chemistry, University of Edinburgh, Edinburgh, UK

    Adam S. Cumming

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DeLuca, L.T., Pang, W. (2020). Transient Burning of nAl-Loaded Solid Rocket Propellants. In: Pang, W., DeLuca, L., Gromov, A., Cumming, A. (eds) Innovative Energetic Materials: Properties, Combustion Performance and Application. Springer, Singapore. https://doi.org/10.1007/978-981-15-4831-4_5

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