Crack growth behavior in a solid propellant

Liu, C.T.

doi:10.1016/s0013-7944(96)00107-5

Cited by 38 publications

(15 citation statements)

References 3 publications

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“…The results of both analytical and experimental analyses are evaluated and discussed. Investigation of the local behavior near the crack tip and the crack growth behavior in a composite solid propellant containing hard particles in a rubbery matrix, under various loading conditions was done [51]. In the study, three temperatures (347 K, 295 K and 219 K) and two crosshead speeds (2.54 mm/min and 12.7 mm/min) are considered.…”

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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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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“…Furthermore, the crack expansion rate follows a power-law relationship with the stress intensity factor. Similarly, many studies have been carried out by Liu [2][3][4] on the fracture characteristics of propellants. Frederick et al [5] used the RTR (real-time radioscopy) technique to measure and quantify the rate of expansion of the crack tip inside the propellant during combustion for a rocket motor containing a cracked round-hole charge.…”

Section: Introductionmentioning

confidence: 99%

A simulation study of fracture toughness for a solid rocket motor contains a cracked propellant grain: Consideration of gas impingement effect

Wang

Chen

2022

J. Phys.: Conf. Ser.

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It is essential to understand the fracture characteristics of a cracked propellant grain in a solid rocket motor during the motor ignition. In this paper, a finite element model of a solid rocket motor is developed, including the gas impingement flow field and the structural field. A circumferential crack is prefabricated on a round-hole type propellant grain. The gas pressure inside the cracked grain is obtained as a function of time by calculating the flow field. Then applying this pressure to the structural field, and J-integral at the crack tip can be calculated. The J-integral can represent the fracture toughness of the propellant. The results show that the circumferential crack in the propellant grain opens up as the gas pressure gradually increases. The J-integral values at the crack tip show an oscillating trend and are not monotonically increasing. This paper predicts the moment of crack propagation in the rocket motor grain under gas impingement conditions by comparing the JIC of the propellant.

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“…Numerous experimental investigations have been conducted in recent years to explore the micromechanical properties and failure mechanisms of composite solid propellants. D. Bencher [2] and Liu C T [3] analyzed the crack formation through experimental method. Marthinus C J [4] studied the microstructure deformation and fracture behavior of a hydroxyl-terminated polybutadiene (HTPB) propellant by using in-situ uniaxial tensile experiments conducted on a scanning electron microscope (SEM).…”

Section: Introductionmentioning

confidence: 99%

Effect of Microstructure on Micro-Mechanical Properties of Composite Solid Propellant

Han

et al. 2021

Micromachines

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This study was aimed at determining the effect of microstructure on the macro-mechanical behavior of a composite solid propellant. The microstructure model of a composite solid propellant was generated using molecular dynamics algorithm. The correlation of how microstructural mechanical properties and the effect of initial interface defects in propellant act on the macro-mechanics were studied. Results of this study showed that the mechanical properties of propellant rely heavily on its mesoscopic structure. The grain filling volume fraction mainly influences the propellant initial modulus, the higher the volume fraction, the higher initial modulus. Additionally, it was found that the ratio of particles influences the tensile strength and breaking elongation rate of the propellant. The big particles could also improve the initial modulus of a propellant, but decrease its tensile strength and breaking elongation rate. Furthermore, the initial defects lowered the uniaxial tensile modulus, tensile strength, and the relaxation modulus of propellant, but did not affect the relaxation behavior of the propellant.

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Crack growth behavior in a solid propellant

Cited by 38 publications

References 3 publications

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

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

A simulation study of fracture toughness for a solid rocket motor contains a cracked propellant grain: Consideration of gas impingement effect

Effect of Microstructure on Micro-Mechanical Properties of Composite Solid Propellant

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