Development of Total and Radiative Heat Flux Measurement Systems for Rocket Nozzle Applications
AEROTHERM CORP MOUNTAIN VIEW CA
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Total heat flux and radiative heat flux measurement systems were developed for use in ablative solid rocket nozzles. The ablative materials considered under the program were MX4926 carbon cloth phenolic and MX2600-96 silica cloth phenolic. Detailed accuracy, design, fabrication, and installation studies were performed to define the system configurations. A PRELIMINARY EVALUATION PROGRAM WAS PERFORMED IN WHICH THE MEASUREMENT SYSTEMS WERE INSTALLED IN TWO-DIMENSIONAL NOZZLES AND SUCCESSFULLY TESTED IN SIMULATED ROCKET ENVIRONMENTS USING AN ARC PLASMA GENERATOR. Final systems evaluation and demonstration was performed through two nozzle firings on the AFRPL 40-inch char motor. A high flame temperature aluminized propellant, APG 112D, was used and peak pressures in both firings were approximately 1000 psia with firing durations of approximately 60 seconds. Successful performance of the two measurement systems was demonstrated.
- Solid Propellant Rocket Engines