A Technique to Measure the Irradiance of a Burning Solid Propellant Surface.
Technical rept. Oct 68-Oct 70,
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CALIF
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A simple, reliable experimental technique has been developed to measure the irradiance of the burning surface of a solid propellant. It incorporates an optical lightpipe to transmit incident radiant energy to a radiation detector. The detector used for the majority of the development tests was a solid state silicon detector with a time constant of less than 500 microseconds. Tests were conducted mainly on metallized, composite and composite modified double base propellants. The metallic additive was aluminum its percentage by weight varied from 8 percent to 17 percent. The pressure range investigated was 1 to 35 atmospheres with gaseous nitrogen used to pressurize and purge the combustion bomb. Burn rate measurements were made on short propellant samples using electrical timing wires to indicate the time it takes to burn a known length of propellant. Author
- Combustion and Ignition
- Solid Rocket Propellants