Development of a three-dimensional nonlinear viscoelastic constitutive model of solid propellant

Jung, Gyoo-Dong; Youn, Sung‐Kie; Kim, Bong-Kyu

doi:10.1590/s0100-73862000000300007

Cited by 7 publications

(5 citation statements)

References 8 publications

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“…And the stress increases significantly when decreasing temperature and increasing strain rate. Furthermore, the HTPB propellant is capable of large deformation and displays nonlinear material behavior, which is usually associated with the occurrence of the damage in the propellant during the tensile deformation The stress–strain curves exhibit two different shapes at various test temperatures, as shown in Figure .…”

Section: Resultsmentioning

confidence: 99%

Tensile mechanical properties and constitutive model for HTPB propellant at low temperature and high strain rate

Wang¹,

Hu²,

Wang³

et al. 2015

J of Applied Polymer Sci

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To investigate the mechanical properties and fracture mechanisms of hydroxyl-terminated polybutadiene (HTPB) propellant at low temperature and high strain rate, uniaxial tensile tests were conducted over the range of temperatures 233 to 298 K and strain rates 0.4 to 14.14 s 21 using an INSTRON testing machine, and scanning electron microscope (SEM) was employed to observe the tensile fracture surfaces. The experimental results indicate that the deformation properties of HTPB propellant are remarkably influenced by temperature and strain rate. The characteristics of stress-strain curves at low temperatures are different from that at room temperature, and the effects of temperature and strain rate on the mechanical properties are closely related to the changes of properties and the fracture mechanisms of HTPB propellant. The dominating fracture mechanism depends much on the temperature and changes from the dewetting and matrix tearing at room temperature to the particle brittle fracture at low temperature, and the effect of strain rate only alters the mechanism in a quantitative manner. Finally, a nonlinear viscoelastic constitutive model incorporating the damage evolution and the effects of temperature and strain rate was developed to describe the stress responses of this propellant under the test conditions. During this process, the Schapery-type constitutive theories were applied and one damage variable was considered to establish the damage evolution function. The overlap between experimental results and predicted results are generally good, which confirms that the developed constitutive model is valid, however, further researches should be done due to some drawbacks in describing the deformation behaviors at very large strain.

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Section: Resultsmentioning

confidence: 99%

Tensile mechanical properties and constitutive model for HTPB propellant at low temperature and high strain rate

Wang¹,

Hu²,

Wang³

et al. 2015

J of Applied Polymer Sci

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“…Since the relatively bigger particles debond first (Jung et al 2000) and the values of α N converge to the value α N ≈ 2.4 at large particle diameter (see Fig. 11), the interface cohesive strength, σ int max , is calculated from Eq.…”

Section: Experimental Determination Of Interfacial Properties For Thementioning

confidence: 99%

“…It is now observed that the numerical and analytical Lielens predictions are both very close to the experimental data. The omis- sion of the finer particles in the models is not thought to be adversely affecting the accuracy of the predictions for fracture strength as debonding of the larger particles occurs first and therefore limits critically the composite's strength (Jung et al 2000).…”

Section: Elastic Modulus Of the Compositesmentioning

confidence: 99%

Development of an image-based numerical model for predicting the microstructure–property relationship in alumina trihydrate (ATH) filled poly(methyl methacrylate) (PMMA)

2018

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Particulate composites are found in a wide range of applications. Their heterogeneous microstructure affects their bulk behavior and structural performance, however tools for predicting this important structure-property relationship are still lacking. In this study, a numerical method that can provide predictions of the mechanical response of a particulate polymeric matrix composite as a function of volume fraction and particle mean diameter is presented. The work is derived for an alumina trihydrate filled poly(methyl methacrylate) but the methodology is generic and can be used for any particulate composite. Representative Volume elements are determined through images obtained from scanning electron microscopy. The model takes into account the possibility of failure through interface debonding as well as cracks through the matrix. The model predictions for the modulus and fracture strength of the composites are validated through independent experiments on the composite. The numerical results are also used to qualitatively explain the trends measured regarding the fracture toughness of the composites. Compared to other literature on particulate composites, our study is the first to report accurate stress-strain distributions as well as fracture predictions whilst all the necessary model parameters defining the failure criteria are all derived through independent experiments. This paves R. Zhang · J. Y. S. Li-Mayer · M. N. Charalambides (B) Department of Mechanical Engineering, Imperial College London, South Kensington, London SW7 2AZ, UK e-mail: m.charalambides@imperial.ac.uk the way for a relatively simple methodology for determining structure-property relationships in composites design, enabling smarter material utilization and optimal mechanical properties.

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“…This significantly alters the performance of the rocket. Jung G D et-al [35] developed a three dimensional nonlinear viscoelastic constitutive model the validity of which is extended to three-dimensional cases. Large deformation, dewetting and cyclic loading effects are treated as the main sources of nonlinear behavior of the solid propellant.…”

Section: Recent Advancesmentioning

confidence: 99%

Desirability and Assessment of Mechanical Strength Characteristics of Solid Propellant for Use in Multi Barrel Rocket Launcher

Bose¹,

Pandey²

2012

IJCEA

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Solid fuel is the first choice to propel the rockets for the area weapon Multi Barrel Rocket Launcher (MBRL) due to ease of design, manufacturing, handling, packaging, transportability and deployability. It also has the capability of prolonged storage without noticeable degradation of its quality. It is also quite safe and does not pose safety hazards. Tactically it suits the requirement of very fast response time and generates high thrust for small duration. Composite modified double base propellant (CMDB) is preferred in MBRL due to wide range of favorable mechanical properties including superior strain capability. Properties of composite propellant may be tailor made by changing the compositions and compound rate. Various failure modes of this propellant are found to be thermal cycling, handling and transport vibrations, ignition shock and pressure loading, launch and flight acceleration, flight maneuver, high speed maneuver, environmental condition etc. All these causes unsymmetrical stress distribution and may lead to failure. Bond strength within the propellant and between the propellant and inhibitor material is very important parameter to control mechanical failure. For safe design the bond strength should be more than the ultimate tensile strength of the propellant. This criterion is satisfied in the present case for the CMDB propellant of MBRL. Index Terms-Composite modified double base propellant, debonding, load-Elongation plot and MBRL.

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Development of a three-dimensional nonlinear viscoelastic constitutive model of solid propellant

Cited by 7 publications

References 8 publications

Tensile mechanical properties and constitutive model for HTPB propellant at low temperature and high strain rate

Tensile mechanical properties and constitutive model for HTPB propellant at low temperature and high strain rate

Development of an image-based numerical model for predicting the microstructure–property relationship in alumina trihydrate (ATH) filled poly(methyl methacrylate) (PMMA)

Desirability and Assessment of Mechanical Strength Characteristics of Solid Propellant for Use in Multi Barrel Rocket Launcher

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