Investigation of large SRM transient launch gas dynamics in a static test by using a consumable test stand

In February 1995, the Rocket Systems Launch Program of the United States Air Force performed a unique static test which investigated the unsteady gas dynamics created during the launch of a large solid rocket motor. An SR-19 rocket motor was horizontally fired 6 feet from a simulated launch stand. The simulator reflected the exhaust plume for 1.5 seconds before passively ablating through and thereby allowing the plume to vent. A simulator survival time of 1.0 to 3.0 seconds was required to examine realistic effects of plume recirculation but not cause rocket motor overheating and failure. The survival time was accurately predicted using a combination of two-dimensional two-phase inviscid real gas computational fluid dynamic calculations coupled with high speed convective heating correlations. The simulator's design allowed a realistic preflight qualification of base components during a launch environment and a thorough post-test inspection. (Author)