Effect of mixing section configurations on combustion efficiency of Mg-CO_(2)Martian ramjet  

作　　者：Xu WANG Yanpeng BU Xu XU Qingchun YANG 

机构地区：[1]School of Astronautics,Beihang University,Beijing 100191,China [2]Shenyuan Honors College,Beihang University,Beijing 100191,China

出　　处：《Chinese Journal of Aeronautics》2023年第4期165-173,共9页中国航空学报（英文版）

基　　金：supported by the Fund of Advance Research Projects of Manned Spaceflight,China(No.050303).

摘　　要：Experiments were conducted to determine the effects of the mixing section configurations on the Mg-CO_(2)Martian ramjet combustion efficiency.It was carried out at a mainstream mass flow rate of 110 g/s and a temperature of 810 K.The chamber pressure was measured under different configurations and Oxidizer to Fuel(O/F)ratios.Results showed that the engine achieved self-sustaining combustion and worked stably during experiments.The pre-combustion chamber is needed to increase the combustion efficiency and promote the full combustion of the powder.After the configuration of the pre-combustion chamber,the best combustion efficiency reached 80%when radial powder injection and lateral carbon dioxide intake were used.In addition,the O/F ratio in the pre-combustion chamber decreased from 0.67 to 0.31,resulting in an 8%increase in the combustion efficiency.It was speculated that different mixing section configurations and the variations in an O/F ratio within the pre-combustion chamber impacted the combustion efficiency and in essence,all affected the flow velocity and residence time of the two-phase flow in the com-bustion chamber.

关 键 词：Combustion efficiency Magnesium-base fuel Martian ramjet Mars exploration Structural configurations 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]