In-Situ Solid-Propellant Burn-Rate Measurements Using Flash Cineradiography
Final rept. 1 Oct 1983-30 Sep 1984
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Flash radiography has been applied to the measurement of solid- propellant burn rates during a series of solid-propellant rocket motor tests at AEDC. This technique offers the advantage of realistic operating conditions and higher data rates than other measurement techniques. The propellant grains were cylindrically perforated and had action times ranging from 2.2 to 3 sec. Four of the six motors were designed to exhibit varying degrees of erosive burning. Chamber pressure and axial thrust were measured on each of the tests. Approximately 25 radiographs at a rate of 6 per second were recorded during the tests. These radiographs were subjected to three different methods of image processing. In addition to the quantitative data obtained, many interesting burn anomalies were revealed in the radiographs.
- Combustion and Ignition
- Solid Propellant Rocket Engines
- Solid Rocket Propellants