Experimental research on high energy initiation technology for detonation driver

Abstract

A shock tunnel with gaseous detonation driver is fit for simulating test gas with high total temperature and pressure, since the sound speed of the driving gas is comparatively high. Decreasing the sound speed of the driving gas can lead to initial detonation difficulties and is therefore deficient in low total temperature and high total pressure gas simulations. In this study, a new high-energy detonation initiation method, the closed-type ignition tube, is proposed, in which initial detonation is achieved in high-concentration nitrogen-diluted hydrogen-oxygen mixed gas and a low-sound speed driving gas is successfully obtained. By experiment, the dominant factors of igniter tube initiation energy are defined, and the design principles of closed igniter tube are given. Through experiments and calculation, the influence mechanism of the new method on the flow process of shock tubes/tunnels is clarified, and the principle of using the new initiation tube is identified. Using this new method, low total temperature and high total pressure test gas could be obtained, which provides a feasible method for expanding the ground test capability of hypersonic flight conditions.