scholarly journals Research on Creep Constitutive and Numerical Simulation of Composite Solid Propellant

2021 ◽  
Vol 1786 (1) ◽  
pp. 012002
Author(s):  
S.X. Feng ◽  
H.F. Qiang ◽  
Y.X. Liu ◽  
X.R. Wang ◽  
T.J. Geng ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Solid Propellant ◽  
Composite Solid Propellant ◽  
Composite Solid

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.

Cook-off test and numerical simulation of AP/HTPB composite solid propellant

2016 ◽  
Vol 40 ◽  
pp. 1-9 ◽  
Author(s):  
Hou-Wen Yang ◽  
Yong-Gang Yu ◽  
Rui Ye ◽  
Xiao-Chun Xue ◽  
Wen-Feng Li
Keyword(s):  
Numerical Simulation ◽  
Solid Propellant ◽  
Composite Solid Propellant ◽  
Composite Solid

scholarly journals Numerical simulation study of composite solid propellant small scale gap test

AIP Advances ◽  
2021 ◽  
Vol 11 (1) ◽  
pp. 015051
Author(s):  
Hong-fu Qiang ◽  
Yu-xiang Liu ◽  
Du-dou Wang ◽  
Xue-ren Wang ◽  
Biao Geng ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Simulation Study ◽  
Solid Propellant ◽  
Small Scale ◽  
Composite Solid Propellant ◽  
Gap Test ◽  
Composite Solid

Numerical Simulation of Combustion of a Metallized Composite Solid Propellant with Additives of Nanosized Aluminum Particles

2018 ◽  
Vol 769 ◽  
pp. 346-351 ◽  
Author(s):  
Vasiliy A. Poryazov ◽  
Aleksey Yu. Krainov
Keyword(s):  
Numerical Simulation ◽  
Solid Propellant ◽  
Gas Flow ◽  
Burning Surface ◽  
Combustion Products ◽  
Aluminum Particles ◽  
Composite Solid Propellant ◽  
Exothermic Chemical Reaction ◽  
Composite Solid ◽  
Metallized Composite Solid Propellant

The paper presents a numerical simulation of combustion of a metallized composite solid propellant with additives of micron-and nanosized aluminum particles. The model takes into account the thermal effect of decomposition of the condensed phase, convection, diffusion, the exothermic chemical reaction in the gas phase, heating and combustion of aluminum particles in the gas flow, the flow of combustion products, the particle velocity lag relative to the gas. The effect of the Al particle size and mass fraction, emitted from the burning surface, on the burning rate is also taken into consideration.

A novel route to improve the mechanical and rheological properties of HTPE/AP/Al propellant by adding a modified hyperbranched polyester

2020 ◽  
pp. 095400832098343
Author(s):  
Xiaomu Wen ◽  
Ximing Zhang ◽  
Keke Chen ◽  
Yunjun Luo
Keyword(s):  
Rheological Properties ◽  
Solid Propellant ◽  
Casting Process ◽  
Hyperbranched Polyester ◽  
Low Viscosity ◽  
Composite Solid Propellant ◽  
Static Tensile ◽  
Void Structure ◽  
Composite Solid ◽  
Hyperbranched Structure

Both better mechanical and rheological properties are pursued for composite solid propellant. In this work, varying proportions of a modified hyperbranched polyester (MHBPE) were added to HTPE/AP/Al propellant. The static tensile property as one kind of mechanical properties of MHBPE/HTPE/AP/Al propellant were found to be superior to those of blank HTPE/AP/Al propellant as a result of the entanglement and interpenetration of molecular chains caused by the introduction of the hyperbranched structure. Evaluations on the related improved creep resistance and stress relaxation performance further demonstrated the advantages of introduction of MHBPE to HTPE/AP/Al propellant. Rheological properties of HTPE/AP/Al propellant with and without MHBPE during the casting process were investigated and compared and the results confirmed the improvement benefiting from low viscosity and loose void structure. Thus, modified hyperbranched polyester provided a novel route to potentially meet the requirements for propellant manufacturing and applications.

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