Fracture Mechanics of Composite Solid Rocket Propellant Grains: Material Testing

Tussiwand, Giuseppe; Saouma, Victor E.; Terzenbach, Robert; Luca, L.T. De

doi:10.2514/1.34227

Cited by 48 publications

(30 citation statements)

References 23 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%

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%

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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“…Upon reaction of the initiator with the coinitiator, an intermediate complex is formed which then goes on to react with the monomer unit. The more of the CuCl2 percentage is the more of cation source and the more of opining the aziridine ring and the lower of aziridine content which illustrated in table (2) and figure (1&2).…”

Section: Results Of the Aziridine Content And The Refractive Indexmentioning

confidence: 97%

Effect of bonding agent production materials on the mechanical properties of composite solid rocket propellant

elall

Guo

2018

MATEC Web Conf.

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Abstract. An effective pathway was explored to design and select proper bonding agents that could effectively improve the interfacial interactions between bonding agents and solid particles, modern types of composite solid propellants focused on increasing the mechanical properties in order to withstand stresses produced due to various loading conditions, changes in environmental condition, transportation and handling. In this work, the study show that the effect of solvent in production of bonding agent has a different impact on the mechanical properties as the polar solvent in formulation S3 has a good strain values corresponding to the stress. Also the changing of the percentage of CuCl2 has a significant effect on mechanical properties as giving high value of strain with the percentage of 4.5 % and returns back the value of strain decrease with increase the percentage of CuCl2 to give the lowest values of the strain corresponding to the stress value with percentage 7.5 %.

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“…The lines at varioust emperatures are approximately parallel. To ughness data can be correlated as conventional failure properties using the temperature reduced strain rate [16].T ests at 482 www.pep.wiley-vch.de different temperatures ands train rates with the same a T ·ė value have producede qualf racture toughness. Am aster curve for the toughness is thus obtained ( Figure 7c).…”

Section: Master Curve For Dynamic Fracture Toughnessmentioning

confidence: 99%

Effects of Temperature and Strain Rate on the Dynamic Fracture Properties of HTPB Propellant

Bing

Chang

et al. 2015

Propellants Explo Pyrotec

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[a] 1IntroductionHydroxyl-terminated polybutadiene (HTPB) propellant is widely used for the propulsion of missile and space launch vehicles. The solid propellant grain mays ubject to loads such as vibration, impact, among others, during shipping, ignition pressurization, and storage, which may cause damage as microcrack and cavity.Acrack propagating in ap ropellant grain creates extra surface area for burning which affectst he ballistic performance of the rocket motor. Especially under the ignitionp ressurization and the high acceleration conditions, the propellant may subject to dynamic loads.T he fracture initiation and propagationp roperties underh igh strain-rate are importanta spects for the structural integrity of solidr ocket motor.A no bvious error may occur if we use the properties under static state to evaluate the security of ag rain underd ynamic state. In service, the rocket motor is often requiredt oo perate over aw ide ranget emperature (in particularl ow temperature) which can cause significant changes in the physical and mechanical properties of the propellant. Therefore, it is necessary to study the temperature and strain-rate effects on the dynamic fracture properties in the propellant.Impact fracture properties of threen itrocellulose/nitroglycerine gun propellants have been measured in at hreepoint bend mode at moderate impact rates with an instrumented drop-weight impact tester [1].T he fracture toughness of plastic deformation zones underp lane stress conditions was approximately twice than that underp lane strain conditions. The impact fracture toughness of an itrocellulose/nitroglycerine gun propellant was foundt ob ev irtually independent of strain rate over the range from 3t o9 0s À1[2].A ne xperiment of fracture surface energy of as olid propellant under impact loads was conducted. The influence of strain rate on fracture toughnessh as beenp ointedo ut and as trong loading rate dependence has been observed [3,4].At present, research of the dynamic properties of HTPB/ AP propellant was focused on the high strain-rate constitutive models [5,6],a nd the dynamic fracture properties was also important for assessment of structure integrity of solid rocket motor. In the presentedw ork, the temperature and strain-rate dependence of the dynamic fracture toughness of HTPB propellant are studied, and the master curve or dynamic initiation fracture toughness was obtained using the temperature reduce strain rate. 2E xperimental Part Materials and Sample ConfigurationThe material investigated was manufactured by the casting methodc omprising of 86 %s olid particles (AP/AL), 10 % HTPB binder, and 4% others. All the particles ize obeys normald istribution,a nd the meanv alue of the big and small AP particles is about 215,1 50 mm, the variance is 19.5, 10.55 mm, respectively.T he mean valuea nd the variance of metallic aluminum particles is about 120 and 8 mm, respectively.Ac rackeds traight-through Brazilian disc Xi'an High-tech Institute Xi'an 710025, Shan'xi, P. R. China *e-mail:longbingfh@126.c...

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Fracture Mechanics of Composite Solid Rocket Propellant Grains: Material Testing

Cited by 48 publications

References 23 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

Effect of bonding agent production materials on the mechanical properties of composite solid rocket propellant

Effects of Temperature and Strain Rate on the Dynamic Fracture Properties of HTPB Propellant

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