Physics
Scientific paper
Jul 1992
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992jpnt.confv....j&link_type=abstract
AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 28th, Nashville, TN, July 6-8, 1992. 8 p.
Physics
Engine Design, Gas Flow, Propellant Grains, Solid Propellant Rocket Engines, Structural Analysis, Titan Launch Vehicles, Engine Failure, Pressure Distribution
Scientific paper
The redesigned development test motor of the Titan IV SRMU (called the PQM-1) is analyzed with a method that couples flow and structural characteristics. The numerical model incorporates both the flow physics of the combustion gases and the structural response of the solid propellant grain. The Hercules Incorporates Axisymmetric Loading code for finite element analysis is utilized in conjunction with the Hercules Solid Propellant Ignition Transient Evaluation. Steady-state calculations are conducted that yield surface-pressure distributions and propellant deformations for the case of small changes in pressure/deformation. Experimental data from hot-gas tests are used for comparison with the analytical results which indicate that the PQM-1 configuration eliminates the failures related to deformation of propellant grains. The PQM-1 motor configuration is shown to offer good margins of safety for the grains and stability for an effective ignition modulus of at least 250 psi.
Johnson David H.
Lauterbach Daniel D.
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