A subscale solid propellant rocket motor experimental program to validate the performance and gasdynamic analysis of the Titan IV SRMU

Details A subscale solid propellant rocket motor experimental program to validate the performance and gasdynamic analysis of the Titan IV SRMU A subscale solid propellant rocket motor experimental program to validate the performance and gasdynamic analysis of the Titan IV SRMU

Jul 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992jpnt.confqt...a&link_type=abstract

AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 28th, Nashville, TN, July 6-8, 1992. 12 p. Research supporte

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Computation

Combustion Chambers, Ground Tests, Piezoelectric Transducers, Solid Propellant Rocket Engines, Test Firing, Titan Launch Vehicles, Computational Fluid Dynamics, Failure Modes, Pressure Gradients, Propellant Grains

Scientific paper

Experiments were conducted to support Hercules Aerospace investigations into the failure of the Titan IV Solid Rocket Motor Upgrade (SRMU) during its first ground test firing and to demonstrate the effectiveness of a remedial grain configuration. Motor internal flow processes for several propellant comfigurations were examined using a 7 percent scale reusable solid propellant combustor in short duration tests. Propellant surface pressure distributions in the combustor were determined by rapid response piezoelectric pressure tranducers. Results of the PQM-1 and PQM-1 one second propellant grain configurations indicated that a high pressure gradient across the joint of the aft and central motor segments led to deformation of the aft grain segment which caused a partial blockage of flow in the central bore of the motor, overpressurization of the forward case and subsequent failure. Tests with the June 5th Baseline redesigned grain configuration showed that chamfering the sharp edges of the forward face of the aft segment leads to a significant reduction in loads across the center-to-aft interface. Test results are discussed and provide a basis to proceed with the remedial design and second ground firing test of the Titan IV SRMU.

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