Effects of liner properties on the stress and strain along liner/propellant interface in solid rocket motor

Guo, Xiang Hui; Zhang, Jiangtao; Zhang, Mei; Liu, Lisheng; Zhai, Pengcheng; Zhang, Qingjie

doi:10.1016/j.ast.2016.09.020

Cited by 24 publications

(7 citation statements)

References 19 publications

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“…Guo et al. observed the liner/thermal insulation layer of NEPE propellant by using MCT and found that its thickness less than 10 μm diffusion layer of serrated mosaic structure [58].…”

Section: Meso Scale Dewetting Experiments and Analysis Methodsmentioning

confidence: 99%

See 1 more Smart Citation

Review on the Dewetting of the Particle‐Matrix Interface in Composite Solid Propellants

Zou

LI³

et al. 2023

Propellants Explo Pyrotec

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Dewetting is the main damage mode of composite solid propellants, and the research on the initiation mechanism and evolution process of dewetting damage is an important way to predict the mechanical properties and evaluate the life of propellants. In this paper, the experimental research and analytical methods of dewettingare reviewed at domestic and foreign from three dimensions: macro, meso and micro. On this basis, the reference solutions to the existing research problems are proposed, and the key research directions of interface dewetting in the future are pointed out. The analysis shows that the dewetting behavior of composite solid propellant is affected by multiple factors such as internal factors (par-ticles, matrix, bonding agent) and external factors (temperature and humidity, aging, strain rate, confining pressure). At present, the mechanism of dewetting is not clear, so it is urgent to conduct experimental analysis and numerical simulation research on the interface at the micro level to analyze the physical and chemical properties of the interface. On the meso scale, it is necessary to increase research in the dewetting theoretical model considering multi factor coupling, the mechanical property experiment of particlematrix interface, and the fine construction of meso scale simulation model. On the macro scale, the dynamic analysis method of propellant dewetting under multiple complex loading conditions will be the focus of future research.

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“…Guo et al. observed the liner/thermal insulation layer of NEPE propellant by using MCT and found that its thickness less than 10 μm diffusion layer of serrated mosaic structure [58].…”

Section: Meso Scale Dewetting Experiments and Analysis Methodsmentioning

confidence: 99%

“…When analyzing the experimental results, he also found that the existence of initial damage would make AP particles easier to dewetting, and defects near large-sized AP particles were easier to develop into holes [27]. Yang MCT and found that its thickness less than 10 μm diffusion layer of serrated mosaic structure [58].…”

Section: Micro Ct Methodsmentioning

confidence: 99%

Review on the Dewetting of the Particle‐Matrix Interface in Composite Solid Propellants

Zou

LI³

et al. 2023

Propellants Explo Pyrotec

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“…E N is the For the other material parameters, they are listed in Table 3. In addition, the binder of liner usually has been based on the same polymer system as the propellant [17] , thus the properties of liner are same to the solid propellant in table.…”

Section: Materials Modelsmentioning

confidence: 99%

Structural analysis of solid rocket motor with effects of viscoelastic Poisson's ratio

Wang

Bao

Cui

2022

J. Phys.: Conf. Ser.

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The new measured viscoelastic Poisson's ratio (VPR) is introduced to investigate the effect of its variation on structure integrity analysis of solid rocket motor. A developed relaxation constitutive model considering VPR is utilized to implement in the finite element code MSC.Marc. Cooling analysis and ignition pressure loading case are designed to analyze the effects along the inner surface of propellant grains. Results show that the little change of the VPR including equilibrium Poisson's ratio (ePR) and reference temperature will affect the output of simulation, and the same up variation of the VPR has relatively less effect on the analysis than the elastic one. Furthermore, the up variation of viscoelastic Poisson ratio will disturb the distribution of strain and stress along the inner surface of propellant grains seriously while the elastic one won’t.

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“…It was found that thermal expansion and contraction during the curing and cooling down processes was the most significant factor in the generation of residual stresses [ 6 ]. This involves the first three aforementioned factors, which have been extensively investigated using the finite element method (FEM) due to its significant economy, efficiency and accuracy [ 7 , 8 , 9 ]. However, chemical shrinkage cannot be neglected; the research shows that the residual stresses due to chemical shrinkage may contribute up to 30% of the total residual stresses in composites [ 10 ].…”

Section: Introductionmentioning

confidence: 99%

Numerical Analysis of Curing Residual Stress and Strain in NEPE Propellant Grain

Xie

Zhou

et al. 2023

Polymers

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In order to investigate the formation mechanism of the residual stress and residual strain in a nitrate ester plasticized polyether (NEPE) propellant grain during the curing and cooling process, the temperature, curing degree and stress/strain of the NEPE propellant grain during the curing and cooling process were analyzed via ABAQUS finite element software. The results indicate that there is a temperature gradient in the NEPE propellant grain during curing at 50 °C. The maximum temperature difference is about 5 °C and the maximum temperature is located on the center of propellant grain. At the end of curing, the temperature in the interior of the grain tends to be uniform. The curing degree in the NEPE propellant grain during the curing process has the same trend as temperature. The residual stress/strain of the NEPE propellant grain during the curing and cooling down processes are mainly composed of curing shrinkage stress/strain in the curing process and thermal stress/strain in the cooling down process. The curing shrinkage stress and strain in the curing process account for 19% and 31% of the whole process, respectively. The thermal stress and thermal strain in cooling down process account for 75% and 69% of the whole process, respectively. The thermal stress and thermal strain in the curing process can nearly be ignored. The residual stress and residual strain calculated by the traditional method is larger than that obtained in this paper. The maximum deviation of the residual stress and residual strain are about 8% and 17%, respectively.

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Effects of liner properties on the stress and strain along liner/propellant interface in solid rocket motor

Cited by 24 publications

References 19 publications

Review on the Dewetting of the Particle‐Matrix Interface in Composite Solid Propellants

Review on the Dewetting of the Particle‐Matrix Interface in Composite Solid Propellants

Structural analysis of solid rocket motor with effects of viscoelastic Poisson's ratio

Numerical Analysis of Curing Residual Stress and Strain in NEPE Propellant Grain

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