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Accession Number
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N20120012051
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Title
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Space Shuttle Solid Rocket Motor Plume Pressure and Heat Rate Measurements.
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Publication Date
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Jun 2012
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Media Count
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49p
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Personal Author
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C. Parlier L. Struchen R. Perez S. Nereolich T. Trovillion W. VonEckroth
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Abstract
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The Solid Rocket Booster (SRB) Main Flame Deflector (MFD) at Launch Complex 39A was instrumented with sensors to measure heat rates, pressures, and temperatures on the last three Space Shuttle launches. Because the SRB plume is hot and erosive, a robust Tungsten Piston Calorimeter was developed to compliment the measurements made by off-the-shelf sensors. Witness materials were installed and their melting and erosion response to the Mach 2 / 4500 F / 4-second duration plume was observed. The data show that the specification document used for the design of the MFD thermal protection system over-predicted heat rates by a factor of 3 and under-predicted pressures by a factor of 2. These findings will be used to baseline NASA Computational Fluid Dynamics models and develop innovative MFD designs for the Space Launch System (SLS) before this vehicle becomes operational in 2017.
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Keywords
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Flame calorimeters
Flame deflectors
Flame temperature
Ground support equipment
Launching pads
Liftoff(Launching)
Pressure measurement
Pressure sensors
Refractory coatings
Rocket exhaust
Solid propellant rocket engines
Space shuttle boosters
Supersonic speed
Temperature sensors
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Source Agency
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National Aeronautics and Space Administration
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NTIS Subject Category
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84E - Space Launch Vehicles & Support Equipment
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Corporate Author
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National Aeronautics and Space Administration, Cocoa Beach, FL. John F. Kennedy Space Center.
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Document Type
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Conference proceedings
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Title Note
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N/A
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NTIS Issue Number
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1303
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Contract Number
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NNJ06VA01C
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