Intermittent Detonation as a Thrust-Producing Mechanism

Abstract

The feasibility of a reaction device operating on intermittent gaseous detonation waves is considered. The results of a simplified theoretical analysis are presented and discussed. Preliminary experiments were conducted to determine the impulse derived from a single detonation wave and to investigate some of the more influential parameters: These tests were effected by suspending the detonation tube as a pendulum. A cyclic detonation tube was designed and operated utilizing hydrogen-air mixtures. Measurements of thrust, fuel flow, air flow, and temperatures were obtained over a range of operating conditions. Specific impulses of over 2100 sec were realized, which was in good agreement with the predicted performance.