Study of a Rotating Detonation Engine (RDE) has been carried out in many research institutions. The RDE has the advantage of high efficiency, simple structure and only once ignition. Toward the practical use for rocket engine, the evaluation of thrust efficiency and the knowledge of combustion under high acceleration or multiple degrees of freedom are essential. In this study, C_2H_4 + O_2 mixture was used as propellant. A Slide mechanism for thrust measyrement was developed, and the mechanism reduced noise and exhausted burned gas. So, the thrust history was acquired and the thrust performance was assessed.
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