Studies of poisson's ratio variation for solid propellant grains under ignition pressure loading

Chyuan, Shiang-Woei

doi:10.1016/j.ijpvp.2003.08.008

Cited by 28 publications

(13 citation statements)

References 13 publications

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“…In the past decades, a considerable amount of work has been done to investigate the properties of solid propellant under various loading conditions . However, there is still limited information available on the mechanical properties and fracture mechanisms of solid propellant at low temperatures and high strain rates.…”

Section: Introductionmentioning

confidence: 99%

“…[3][4][5][6] In the past decades, a considerable amount of work has been done to investigate the properties of solid propellant under various loading conditions. [7][8][9] However, there is still limited information available on the mechanical properties and fracture mechanisms of solid propellant at low temperatures and high strain rates. On the one hand, the existing researches regarding the properties of solid propellant at low temperatures are mainly focus on the effects of components on the mechanical properties 10,11 and the varying of glass transition temperature T g with the various influencing factors, 12,13 etc.…”

Section: Introductionmentioning

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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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

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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“…Also,ahollowr ectangular regioni n the compensatings pecimen comprising 18912 discrete points was defined as the ROC. A4 141 pixels subset size and a5pixelsg rid step were chosen as calculation parameters for the DIC analysis, and the displacement fields of ROI and ROC were analyzed using the efficient and accurateI C-GN algorithm with first-order shapef unctions [ 21].A s noted previously,t he displacement components of ROC were first used to estimatet he eleven unknown parameters (i.e., a 0, 1, …,4 , b 0, 1, …,4 ,a nd k 1 )u sing Equation (1). Based on these determinedp arameters, the displacement fields of ROI were corrected point by point according to Equation (2).…”

Section: Methodsmentioning

confidence: 99%

“…During shipment, storagea nd ignition,t he solid propellants inside aS RM generally suffer from diverse loadings [1,2].T od etermine the integrity and service life of the SRM, it is necessary to evaluatet he stress and strain distributionsa sw ell as the aging and damage of the solid propellant grainsb ased on viscoelastic constitutive theory and computational modeling [1][2][3][4].N umerical analyses performed by various researchers clearly demonstrated that the Poisson's ratio variation in solid propellant grains has as ignificant effect on the resulting stress and strain response. Despite the Poisson's ratio is generally treated as ac onstant for simplicity,m odels that assume ac onstantP oisson ratio usually cannot achieve good results, especially for short-duration loading cases.…”

mentioning

confidence: 99%

Determination of Viscoelastic Poisson’s Ratio of Solid Propellants using an Accuracy‐enhanced 2D Digital Image Correlation Technique

Pan

Yuan

et al. 2015

Propellants Explo Pyrotec

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1IntroductionAs ak ey component of as olid rocket motor( SRM), the structural integrity of solid propellantsp lays ac rucial role in its service life evaluation. During shipment, storagea nd ignition,t he solid propellants inside aS RM generally suffer from diverse loadings [1,2].T od etermine the integrity and service life of the SRM, it is necessary to evaluatet he stress and strain distributionsa sw ell as the aging and damage of the solid propellant grainsb ased on viscoelastic constitutive theory and computational modeling [1][2][3][4].N umerical analyses performed by various researchers clearly demonstrated that the Poisson's ratio variation in solid propellant grains has as ignificant effect on the resulting stress and strain response. Despite the Poisson's ratio is generally treated as ac onstant for simplicity,m odels that assume ac onstantP oisson ratio usually cannot achieve good results, especially for short-duration loading cases. In fact, the Poisson'sr atio of solid propellants, known as at ime-temperature dependent viscoelastic property,i sacomplex function dependent on both time and load histories [5]. Thus, to feed the numerical techniques, experimental determination of time-varying Poisson's ratio of the propellant grains is of practical importance. However,s ince solid propellant grains are very flexible and soft in nature, it is extremely challenging to use existing experimental techniques to accurate measure its time-dependent Poisson's ratio, whichi se xpected to vary from compressible (v < 0.5) to incompressible (v % 0.5) and thusd emanding very high accuracyo ns train measurements.To determine the Poisson's ratio of solid propellants, both indirect and direct measurementt echniquesc an be used [6][7][8].T he indirect measurement methods first measure other material parameters, such as tensile/compressive modulus ands hear modulus, Poisson's ratio is then numerically computed based on the transversal relationship among these material parameters. Becauset he indirect techniques involve multiple measurement and fitting of several mechanical parameters, their practical implementation is not only troublesome, but also prone to induce large measuremente rrors due to the error accumulation involved in various steps.I nc ontrast, the direct measurement

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“…Subsequently the ratio found to be less than 0.5. Chyuan SW [27], [28] carried out an investigation on solid propellant grains considering the effect of Poisson's ratio variation under ignition pressurization. In order to simulate the time-temperature-dependent behaviour of viscoelastic polymer materials for a range of Poisson's ratio values, the concepts of a time-temperature shift principle and reduced integration were used.…”

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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Studies of poisson's ratio variation for solid propellant grains under ignition pressure loading

Cited by 28 publications

References 13 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

Determination of Viscoelastic Poisson’s Ratio of Solid Propellants using an Accuracy‐enhanced 2D Digital Image Correlation Technique

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

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