Design and Experimental Investigation on Uniform Distributed Injector in HAN-Based Monopropellant Thruster

被引：0

作者：

Liu C. ^{[1
,2
]}

Liu J. ^{[1
,2
]}

Yao T.-L. ^{[1
,2
]}

Lin Q.-G. ^{[1
,2
]}

Sun D.-C. ^{[3
]}

机构：

[1] Shanghai Institute of Space Propulsion, Shanghai

[2] Shanghai Engineering Research Center of Space Engine, Shanghai

[3] School of Aeronautics and Astronautics, Dalian University of Technology, Dalian

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2021年 / 42卷 / 07期

关键词：

Atomization characteristics; Combustion performance; HAN-based thruster; Hot fire test; Numerical simulation; Uniform distributed injector;

D O I：

10.13675/j.cnki.tjjs.200658

中图分类号：

学科分类号：

摘要：

Compared to hydrazine, Hydroxyl ammonium Nitrate (HAN) is more stable and takes longer to be completely decomposed. In order to improve the initial contact area between the propellant and the catalyst to make the propellant evenly distributed in the catalytic bed, the uniform distributed method of the injector is studied. The numerical simulation research on the injection process and atomization effect of the new injector structure has been carried out by using the Volume of Fluid (VOF) model, it provided theoretical support for the optimization of the injector structure. At the same time, the comparison of the density distribution, diameter and axial velocity of the atomized droplet in space of the two injector structures are detected by the three-dimensional phase Doppler Anemometry (PDA). Finally, through the hot fire test on the ground, the performance of the thruster with two types of injector structure under warm start pulse test, steady-state test and combustion reactivities have been compared, and it has concluded that the structure with injection core is better under starting response characteristics and combustion performance. © 2021 Editorial Department of Journal of Propulsion Technology. All right reserved.

引用

页码：1606 / 1614

页数：8

共 16 条

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