Operation of a Rotary-valved Pulse Detonation Rocket Engine Utilizing Liquid-kerosene and Oxygen

作     者：WANG Ke FAN Wei YAN Yu ZHU Xudong YAN Chuanjun 

作者机构：School of Power and Energy Northwestern Polytechnical University Xi ＇an 710072 China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2011年第24卷第6期

页      面：726-733页

核心收录：

学科分类：081702[工学-化学工艺] 082502[工学-航空宇航推进理论与工程] 08[工学] 0817[工学-化学工程与技术] 0825[工学-航空宇航科学与技术] 

基　　金：National Natural Science Foundation of China (50976094) Doctoral Program Foundation of Education Ministry of China (20096102110022) Doctorate Foundation of Northwestern Polytechnical University (CX201112) Graduate Innovation Lab Center of Northwestern Polytechnical University (10006,10013) 

主　　题：pulse detonation rocket engines rotary valve velocity deficit kerosene oxygen 

摘      要：The pulse detonation rocket engine （PDRE） requires periodic supply of oxidizer, fuel and purge gas. A rotary-valve assembly is fabricated to control the periodic supply in this research. Oxygen and liquid aviation kerosene are used as oxidizer and fuel respectively. An ordinary automobile spark plug, with ignition energy as low as 50 mJ, is used to initiate combustion. Steady operation of the PDRE is achieved with operating frequency ranging from 1 Hz to 10 Hz. Experimentally measured pressure is lower than theoretical value by 13% at 1 Hz and 37% at 10 Hz, and there also exists a velocity deficit at different operating frequencies. Both of these two phenomena are believed mainly due to droplet size which depends on atomization and vaporiza-tion of liquid fuel.