Reusable Solid Rocket Motor (RSRM) pressure perturbation characterization - An overview

Schorr, Andrew A.; Speas, Kyle

doi:10.2514/6.1995-2722

31st Joint Propulsion Conference and Exhibit 1995

DOI: 10.2514/6.1995-2722

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Reusable Solid Rocket Motor (RSRM) pressure perturbation characterization - An overview

Andrew A. Schorr¹,

Kyle Speas²

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Cited by 4 publications

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Design of a subscale propellant slag evaluation motor using two-phase fluid dynamic analysis

Whitesides¹,

Dill²,

Purinton³

et al. 1996

32nd Joint Propulsion Conference and Exhibit

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Small pressure perturbations in the Space Shuttle Reusable Solid Rocket Motor (RSRM) are caused by the periodic expulsion of molten aluminum oxide slag from a pool that collects in the aft end of the motor around the submerged nozzle nose during the last half of motor operation.It is suspected that some motors produce more slag than others due to differences in aluminum oxide agglomerate particle sizes that may relate to subtle differences in propellant ingredient characteristics such as particle size distributions or processing variations. A subscale motor experiment was designed to determine the effect of propellant ingredient characteristics on the propensity for slag production. An existing 5 inch ballistic test motor was selected as the basic test vehicle. The standard converging/diverging nozzle was replaced with a submerged nose nozzle design to provide a positive trap for the slag that would increase the measured slag weights. Two-phase fluid dynamic analyses were performed to develop a nozzle nose design that maintained similitude in major flow field features with the full scale RSRM. The 5 inch motor was spun about its longitudinal axis to further enhance slag collection and retention. Two-phase flow analysis was used to select an appropdate spin rate along with other considerations, such as avoiding bum rate increases due to radial acceleration effects.Aluminum oxide particle distributions used in the flow analyses were measured in a quench bomb for RSRM type propellants with minor variations in ingredient characteristics.

show abstract

Design of a subscale propellant slag evaluation motor using two-phase fluid dynamic analysis

Whitesides¹,

Dill²,

Purinton³

et al. 1996

32nd Joint Propulsion Conference and Exhibit

View full text Add to dashboard Cite

show abstract

Recent combustion bomb testing of RSRM propellant

Brennan¹

1996

32nd Joint Propulsion Conference and Exhibit

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Predicting slag generation in sub-scale test motors using a neural network

Wiesenberg¹

1999

35th Joint Propulsion Conference and Exhibit

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Reusable Solid Rocket Motor (RSRM) pressure perturbation characterization - An overview

Cited by 4 publications

References 2 publications

Design of a subscale propellant slag evaluation motor using two-phase fluid dynamic analysis

Design of a subscale propellant slag evaluation motor using two-phase fluid dynamic analysis

Recent combustion bomb testing of RSRM propellant

Predicting slag generation in sub-scale test motors using a neural network

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