Thermo-damage-viscoelastic constitutive model of HTPB composite propellant

Xu, Jie; Chen, Xiong; Wang, Hongli; Zheng, Jian; Zhou, Changsheng

doi:10.1016/j.ijsolstr.2014.05.024

Cited by 56 publications

(18 citation statements)

References 15 publications

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“…Therefore, the following expression can be used to model the deformation of these materials at various temperatures and strain rates:

σ = g \cdot f (ε, t, T)

where the function

g

is applied to calculate the damage evolution, the function

f (ε, t, T)

is applied to describe the linear viscoelastic mechanical property, which is usually related to strain

ε

, time t and temperature T . At present, it is generally accepted to use the Prony series to model the function

f (ε, t, T)

, while there are different expressions to describe the other function

g

…”

Section: Constitutive Modelmentioning

confidence: 99%

“…During the different constitutive models with the second method, the ones proposed by Hinterhoelzl and Schapery have been widely used to study the properties of mechanical or fatigue for various materials . Because the stress–strain data is all from one‐dimensional experiment in this investigation, based on the Schapery‐type constitutive theories, the stress responses of HTPB propellant under the test conditions can be described by the following expressions, in which only one damage variable was considered:

ε^{R} (t) = \frac{1}{E_{R}} \int_{0}^{t} E false(ξ - ξ' false) \frac{\partial ε}{\partial τ} d τ

σ (t) = \frac{\partial W^{R}}{\partial ε^{R}} = E_{R} C (S) ε^{R} (t)

W^{R} = \frac{1}{2} C (S) {(ε^{R})}^{2}

\frac{d S}{d t} = {true[- \frac{\partial W^{R}}{\partial S} true]}^{α}

where ξ (t) = \int_{0}^{t} \frac{d t^{'}}{α_{T} false[T false(t^{'} false) false]}

…”

Section: Constitutive Modelmentioning

confidence: 99%

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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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“…Therefore, the following expression can be used to model the deformation of these materials at various temperatures and strain rates:

σ = g \cdot f (ε, t, T)

where the function

g

is applied to calculate the damage evolution, the function

f (ε, t, T)

is applied to describe the linear viscoelastic mechanical property, which is usually related to strain

ε

, time t and temperature T . At present, it is generally accepted to use the Prony series to model the function

f (ε, t, T)

, while there are different expressions to describe the other function

g

…”

Section: Constitutive Modelmentioning

confidence: 99%

ε^{R} (t) = \frac{1}{E_{R}} \int_{0}^{t} E false(ξ - ξ' false) \frac{\partial ε}{\partial τ} d τ

σ (t) = \frac{\partial W^{R}}{\partial ε^{R}} = E_{R} C (S) ε^{R} (t)

W^{R} = \frac{1}{2} C (S) {(ε^{R})}^{2}

\frac{d S}{d t} = {true[- \frac{\partial W^{R}}{\partial S} true]}^{α}

where ξ (t) = \int_{0}^{t} \frac{d t^{'}}{α_{T} false[T false(t^{'} false) false]}

…”

Section: Constitutive Modelmentioning

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

View full text Add to dashboard Cite

show abstract

“…Generally, to express the effect of damage on a material, a multiplier g representing the damage evolution can be applied to the equation above [11]. Thus, the stress is now (4) There are many types of expressions for the function g. Among them, the Schapery model based on irreversible thermodynamics is widely accepted and employed [11,[15][16][17][18][19][20]. Under conditions of constant temperature and uniaxial compression, the Schapery model can be expressed as…”

Section: Constitutive Modelmentioning

confidence: 99%

“…The model has been widely adopted in analyses regarding propellants [11,20] and asphalt concrete [21][22][23][24]. Wang et al [11] successfully applied the Schapery model in description of the tensile properties of HTPB propellant.…”

Section: Introductionmentioning

confidence: 99%

“…Four temperatures and four strain rates were considered and the results met the data well except for the deformation at very large strain. J. Xu et al [20] employed the multi-step tensilerelaxation tests to verify the accuracy of the Schapery model established for HTPB propellant. Lee et al [21] researched the effect of lime on composite hot-mix asphalt mixtures utilizing Schapery model.…”

Section: Introductionmentioning

confidence: 99%

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Thermal Safety of a Gun‐Launched Missile's Solid Rocket Motor Under Conditions of High Environm. Temp. and Overloaded Forces

Wang

Sui

et al. 2018

Propellants Explo Pyrotec

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To verify a hypothetical failure cause of a gunlaunched missile's solid rocket motor (SRM) under conditions of high environmental temperatures and overloaded forces of up to 6000~12000 g, experiments and simulations were conducted and a new criterion variable was proposed. Uniaxial compression tests of the composite modified double base (CMDB) propellant used in the gun-launched missile were carried out at low and intermediate strain rates at 50 8C to characterize the CMDB propellant's dynamic properties. The Schapery nonlinear viscoelastic constitutive model was employed and applied in finite element analy-ses. Contact and an oscillating frictional direction between the grain and the case were observed when the overload curve oscillated with time. Three key variables of the process were researched: the contact pressure, the relative velocity, and the total contact time. Based on these, a new criterion variable q is proposed for judgements regarding the SRM's thermal safety. By comparing the results with those from friction sensitivity tests, it was discovered that the grain had a possibility of self-ignition that cannot be ignored. Meanwhile, the gap width between the case and the grain was determined to be a key influencing factor.Keywords: gun-launched missile · CMDB propellant · high oscillational overload · high temperature · explosion [a] W.

show abstract

Compressive mechanical properties of HTPB propellant at low, intermediate, and high strain rates

Yang

Xie

Pei³

et al. 2016

J of Applied Polymer Sci

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Low, intermediate, and high strain rate compression testing (1.7 3 10 24 to 2500 s 21 ) of the hydroxyl-terminated polybutadiene (HTPB) propellant at room temperature, were performed using a universal testing machine, a hydraulic testing machine, and a split Hopkinson pressure bar (SHPB), respectively. Results show that the stress linearly increases with strain at each condition; the increasing trend of stress at a given strain with the logarithm of strain rate changes from a linear to an exponential form at 1 s 21 . By combining these characteristics, we propose a rate-dependent constitutive model which is a linearly elastic component as a base model, then multiplied by a rate-dependent component. Comparison of model with experimental data shows that it can characterize the compressive mechanical properties of HTPB propellant at strain rates from 1.7 3 10 24 to 2500 s 21 . V C 2016 Wiley Periodicals, Inc. J.Appl. Polym. Sci. 2016, 133, 43512.

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Thermo-damage-viscoelastic constitutive model of HTPB composite propellant

Cited by 56 publications

References 15 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

Thermal Safety of a Gun‐Launched Missile's Solid Rocket Motor Under Conditions of High Environm. Temp. and Overloaded Forces

Compressive mechanical properties of HTPB propellant at low, intermediate, and high strain rates

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