Influence of HTPB prepolymer on achieved properties of composite solid propellant

2019 ◽  
Vol 31 (9-10) ◽  
pp. 1162-1172 ◽  
Author(s):  
I Kingstone Lesley Jabez ◽  
Urmila Das ◽  
R Manivannan ◽  
Sarat Babu Anne
Keyword(s):  
Molecular Weight ◽  
Solid Propellants ◽  
Nmr Studies ◽  
Appreciable Change ◽  
Hydroxyl Value ◽  
Root Cause ◽  
R Ratio ◽  
Composite Solid Propellant ◽  
Composite Solid Propellants ◽  
Composite Solid

Changes/variations during manufacturing and storage of free radical-polymerized hydroxyl-terminated polybutadiene resin/prepolymer (widely used binder for the composite solid propellants) are not reflected in terms of appreciable change in the hydroxyl value. As a result, cured properties of the propellant mixed using the given formulation finalized by keeping R ratio (NCO/OH ratio) within 0.7–0.9 did not yield predicted mechanical properties. Investigations carried out subsequently, by the authors, identified the root cause to be variations in molecular weight and its distribution, which were not indicated in terms of change in hydroxyl value. Authors confirmed their findings by 1H1NMR studies whereby the variation in molecular weight distribution could be explained in terms of variation in spin–spin relaxation time ( T 2) values.

NUMERICAL SIMULATION OF COMBUSTION OF THE COMPOSITE SOLID PROPELLANT CONTAINING BIDISPERSED BORON POWDER

2021 ◽  
pp. 131-139
Author(s):  
V.A. Poryazov ◽  
◽  
K.M. Moiseeva ◽  
A.Yu. Krainov ◽  
◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Burning Rate ◽  
Solid Propellant ◽  
Mathematical Formulation ◽  
Solid Propellants ◽  
Boron Powder ◽  
Composite Solid Propellant ◽  
Composite Solid Propellants ◽  
Composite Solid ◽  
Propellant Surface

A problem of combustion of the composite solid propellants containing various powders of metals and non-metals is relevant in terms of studying the effect of various compositions of powders on the linear rate of propellant combustion. One of the lines of research is to determine the effect of the addition of a boron powder on the burning rate of a composite solid propellant. This work presents the results of numerical simulation of combustion of the composite solid propellant containing bidispersed boron powder. Physical and mathematical formulation of the problem is based on the approaches of the mechanics of two-phase reactive media. To determine the linear burning rate, the Hermance model of combustion of composite solid propellants is used, based on the assumption that the burning rate is determined by mass fluxes of the components outgoing from the propellant surface. The solution is performed numerically using the breakdown of an arbitrary discontinuity algorithm. The dependences of the linear burning rate of the composite solid propellant on the dispersion of the boron particles and gas pressure above the propellant surface are obtained. It is shown that the burning rate of the composite solid propellant with bidispersed boron powder changes in contrast to that of the composite solid propellant with monodispersed powder. This fact proves that the powder dispersion should be taken into account when solving the problems of combustion of the composite solid propellants containing reactive particles.

Selective Radiative Preheating of Aluminum in Composite Solid Propellant Combustion

1987 ◽  
Vol 109 (1) ◽  
pp. 179-184 ◽  
Author(s):  
M. Q. Brewster ◽  
R. Patel
Keyword(s):  
Catalyst Particle ◽  
Radiation Absorption ◽  
Solid Propellants ◽  
Two Phase ◽  
Mass Fractions ◽  
The Matrix ◽  
Composite Solid Propellant ◽  
Composite Solid Propellants ◽  
Burn Rate ◽  
Composite Solid

A two-phase model has been developed to study aluminum (Al) particle preheating through selective radiation absorption in composite solid propellants. The two phases considered are one strongly absorbing particle (Al) phase and another weakly absorbing matrix (ammonium perchlorate (AP), binder and catalyst particle) phase surrounding the Al phase. Separate energy balance equations for the Al and matrix phases are developed. Both the matrix and the Al phase are assumed to be nonemitting, anisotropically scattering, absorbing media. The parameters identified which strongly influence Al preheating and melting are Al size, mass fraction, burn rate, and level of incident radiant flux. It was found that large Al mass fractions and small Al particle sizes promote lower Al temperatures. The effect of adding submicron iron oxide burn rate catalyst particles on aluminum preheating was also investigated. It was found that the addition of small amounts of catalyst can theoretically reduce Al temperatures significantly by dominating the optical properties. These results should prove useful to propellant formulators in trying to reduce the problem of unwanted Al agglomeration.

scholarly journals Cu–Co–O nano-catalysts as a burn rate modifier for composite solid propellants

2016 ◽  
Vol 12 (4) ◽  
pp. 297-304 ◽  
Author(s):  
D. Chaitanya Kumar Rao ◽  
Narendra Yadav ◽  
Puran Chandra Joshi
Keyword(s):  
Solid Propellants ◽  
Composite Solid Propellants ◽  
Burn Rate Modifier ◽  
Nano Catalysts ◽  
Burn Rate ◽  
Composite Solid

scholarly journals DETONATION NANODIAMOND AS PROSPECTIVE COMPONENT OF COMPOSITE SOLID PROPELLANTS

2018 ◽  
Vol 59 (8) ◽  
pp. 96
Author(s):  
Valentin A. Gorbachev ◽  
Evgeniy Yu. Ubey - Volk ◽  
Nikolay V. Shevchenko ◽  
Alexandr A. Golubev
Keyword(s):  
Fuel Composition ◽  
Solid Propellants ◽  
Detonation Nanodiamond ◽  
Metal Free ◽  
Composite Solid Propellants ◽  
Composite Solid

In this articlethe the possibility of application of detonation nanodiamond (DND) as a prospective component of composite solid propellants (CSP) and additive approach to optimization of fuel compositions based on binary fuel compositions is considered. The introduction to the fuel composition of DND allows creating a metal-free CSP with increased energy-to-mass characteristics. Usage of the additive approach for calculations when creating new prospective compositions of CSP allows reducing significantly the volume of work to optimize the fuel compositions and to simplify the process of thermodynamic engineering.

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