On theory and methods for advanced detonation-driven hypervelocity shock tunnels  

作　　者：Zonglin Jiang Jinping Li Zongmin Hu Yunfeng Liu Hongru Yu 

机构地区：[1]State Key Laboratory of High Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China [2]Department of Aerospace Engineering Science,School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China

出　　处：《National Science Review》2020年第7期1198-1207,共10页国家科学评论（英文版）

基　　金：the National Natural Science Foundation of China(11727901 and 11532014)。

摘　　要：This study describes theory and methods for developing detonation-driven shock tunnels in hypervelocity test facilities.The primary concept and equations for high-enthalpy shock tunnels are presented first to demonstrate the unique advantage of shock tubes for aerodynamic ground-based testing.Then,the difficulties in simulating flight conditions in hypervelocity shock tunnels are identified,and discussed in detail to address critical issues underlying these difficulties.Theory and methods for developing detonation drivers are proposed,and relevant progress that has advanced the state of the art in large-scale hypersonic test facilities is presented with experimental verifications.Finally,tailored conditions for detonation-driven shock tunnels are described,laying a solid foundation to achieve long test duration.This interface-matching key issue encountered in developing shock tunnels has been investigated for decades,but not solved for detonation drivers in engineering applications.

关 键 词：HYPERVELOCITY shock tunnel detonation driver flight condition tailored condition test facilities 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]