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RADIATIVE EFFECTS ON ROCKET STABILITY WITH OZONE-CONTAINING OXIDIZER.
Quarterly rept. no. 1, 1 Sep-30 Nov 66,
DEFENSE RESEARCH CORP SANTA BARBARA CA
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In the first part of this report, the basic equations as well as the computing program that we have devised previously for calculating the explosion trajectory of the ozone system under constant pressure is revised for similar calculations under constant-volume conditions. Time histories of temperature, pressure, and intermediate concentrations are calculated and presented for comparisons under both the constant-pressure and constant-volume conditions. A new model is also formulated to simulate more realistic engine environments for predicting the stability of ozone-containing propellants in a rocket. The radiation intensity is taken to be the blackbody spectrum at appropriate engine temperatures. The assumption that the absorbing medium is optically thin is not longer invoked. Author
APPROVED FOR PUBLIC RELEASE