Demonstration of an Altering-Intensity Swirling-Oxidizer-Flow-Type Hybrid Rocket Function

被引：4
|
作者：
Nakagawa, Ichiro [1 ]
Kishizato, Daiki [2 ]
Koinuma, Yuto [2 ]
Tanaka, Susumu [2 ]
机构：
[1] Tokai Univ, Dept Aeronaut & Astronaut, Hiratsuka, Kanagawa 2591292, Japan
[2] Canon Elect Inc, Chichibu, Saitama 3691892, Japan
来源：
JOURNAL OF PROPULSION AND POWER | 2021年 / 37卷 / 02期
关键词：
Rockets;
D O I：
10.2514/1.B37915
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
In this study, to reduce oxidizer to fuel ratio (O/F) shifts, which are a serious problem for a hybrid rocket used for launching a satellite, an altering-intensity swirling-flow-type hybrid rocket was developed. It can alter the swirl intensity instantaneously during operation by controlling the ratio of the swirling oxidizer flow rate to the axial oxidizer flow rate using ball valves. Eight firing tests were conducted to obtain the relation among oxidizer mass flux, swirl intensity, and regression rate. Then the time scheduling of the valve open ratio was determined to eliminate O/F shift. Finally, a firing test was conducted using this system. From the results, the O/F shift was reduced from 2 to 1, i.e., halved.
引用
收藏
页码：326 / 331
页数：6
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