Viseoelastic Fracture of Solid Propellants in Pressurization Loading Conditions

Francis, E. C.; Carlton, C. H.; LlNDSEY, G. H.

doi:10.2514/3.62157

Cited by 12 publications

(5 citation statements)

References 9 publications

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“…Pressure shows tL same effect as lowering the temperature, namely, increasing the stress intensity factor at a given crack velocity. The same effects are seen in composite propellants (16).…”

Section: Teumperature and Pressure Effectssupporting

confidence: 66%

“…The constant strain ratc data shown in Figure 5 was evaluated by using Schaper"' s th ory (15,16) to predict the crack growth from mcasured material properties and experimental stress values after correcting for finite zeometry etfects.…”

Section: Comparison With Schaperv's T'heorvmentioning

confidence: 99%

“…This is particularly true for the solid rocket motor grain itself, w!hich must undergo a wide range of environments and loading conditions non heretofore studied in the laboratory either experimentally or analvtiiliv Schapery (15,16) has rece.,'ly been working on a more generalized appr',i,,i, which may be able to resolve wore complicated load histories reprseuntative of actual motor conditions.…”

Section: Introductionmentioning

confidence: 99%

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Crack propagation in double-base propellants

Beckwith

Wang

1978

16th Aerospace Sciences Meeting

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Section: Teumperature and Pressure Effectssupporting

confidence: 66%

Section: Comparison With Schaperv's T'heorvmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Crack propagation in double-base propellants

Beckwith

Wang

1978

16th Aerospace Sciences Meeting

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“…A 35% improvement in fracture toughness was reported by Francis et al 24 for a PBAN propellant tested in a 500 psi pressurized environment (Fig. 3).…”

Section: Experimental Methodssupporting

confidence: 51%

Fracture Considerations for Surveillance Programs

Francis¹,

Jacobs

1976

Journal of Spacecraft and Rockets

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The structural capability of solid propellant grains has been defined in terms of grain safety margins. However, many rocket motors with structural flaws (bore cracks, unbonds, etc.) have been fired successfully within ballistic tolerances. This indicates that conventional grain safety margins do not define adequately conditions which limit structural response of a solid propellant gram. Use of fracture mechanics techniques has been included in some motor service life predictions and eventually will become a routine characterization and evaluation requirement for all solid rocket motors. Some of the available fracture mechanics techniques are summarized, and laboratory fracture test methods, which should be considered for motor surveillance programs, are reviewed. Use of these fracture mechanics tools, together with crack combustion analysis recently developed at the University of Utah, provides a realistic assessment of structural defects and motor ballistic performance.

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“…Using a stress intensity approach to fracture of solid propellant grains, Francis et al (16,17) conducted a program on an unfilled polyurethane polymer (Solithane 113), an epoxy, and later, a PBAN composite propellant formulation.…”

Section: Introductionmentioning

confidence: 99%