Study on Valve Systems for Pulse Detonation Engines

Abstract

We proposed a novel rotary valve system for a pulse detonation rocket engine (PDRE). Since this valve can supply three gases (oxidizer, fuel, purge gas) into a PDE tube (combustor) by using a rotary disk, the weight of this valve is light. We carried out the thrust measurement by using the PDRE system with the rotary valve and ethylene-oxygen propellant in order to confirm the thrust performance of the system. As a result, we confirmed the stable operation of the system over a wide range of operation frequency and measured the time-averaged thrust. We succeeded reducing the size and the weight of a valve for a PDRE. In addition, the maximum time-averaged thrust of 31.7 was achieved at operation frequency of 33.3 Hz and propellant supply pressure of 1.0 MPa. Moreover, the maximum specific impulse of 249.5 sec was achieved at operation frequency of 33.0 Hz and propellant supply pressure of 0.7 MPa.