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Experimental Investigation of a Solid Propellant Ducted Rocket with a Chin Type Inlet

机译：下巴型入口固体推进剂管火箭的实验研究

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Binbin CHEN; Zhixun XIA; Liya HUANG; Likun MA; Gang LONG;
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1. Characteristics of the combustion chamber of a boron-based solid propellant ducted rocket with a chin-type inlet [J] . Chen Binbin, Xia Zhixun, Huang Liya, Aerospace science and technology . 2018,第NOVa期

机译：带有下巴式进气口的硼基固体推进剂管道火箭的燃烧室特性
2. Experimental Investigation and Numerical Simulation of Secondary Combustor Flow in Boron-Based Propellant Ducted Rocket [J] . Jianxin Hu, Zhixun Xia, Dequan Wang, Transactions of the Japan society for aeronautical and space sciences . 2013,第3期

机译：硼基推进剂火箭管二次燃烧器流动的实验研究与数值模拟
3. Experimental investigation of the factors affecting the burning rate of solid rocket propellants [J] . Hayri Yaman, Veli Celik, Ercan Degirmenci Fuel . 2014,第jana期

机译：影响固体火箭推进剂燃烧速度的因素的实验研究
4. Computing Method Investigation and Verification of Gas-Solid Combustion in Magnesium-Aluminum Based Propellant Ducted Rocket [C] . Wei Wang, Jiang Li, Ke Zhang, International conference on Frontiers of manufacturing science and measuring technology . 2012

机译：镁铝推进剂管火箭弹气固燃烧计算方法研究与验证
5. Experimental study of mixing and combustion processes in a solid propellant ducted rocket motor. [D] . Chuang, Chin-Lung. 1989

机译：固体推进剂管道火箭发动机混合与燃烧过程的实验研究。
6. Investigation of a Low-Toxicity Energetic Binder fora Solid Propellant: Curing Microstructures and Performance [O] . Song Ma, Hongjie Fan, Ning Zhang, 2020

机译：对低毒性能量粘合剂的调查固体推进剂：固化微观结构和性能
7. Experimental Investigation and Numerical Simulation of Secondary Combustor Flow in Boron-Based Propellant Ducted Rocket [O] . Jianxin HU, Zhixun XIA, Dequan WANG, 2013

机译：硼基推进剂管火箭中二次燃烧器流动的实验研究与数值模拟
8. Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area IV : some effects of internal duct shape upon an inlet enclosing 37.2 percent of the forebody circumference [R] . Davis, Wallace F, Edwards, Sherman S, Brajnikoff, George B 1949

机译：同等面积双筒导管入口的超音速实验研究IV：内部导管形状对入口的一些影响包围前体周长的37.2％

Experimental Investigation of a Solid Propellant Ducted Rocket with a Chin Type Inlet

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