Experimental test analysis of a 300 N hybrid rocket engine

Q3 Earth and Planetary Sciences
Sachin Srivastava, Amit Kumar Thakur, Lovi Raj Gupta, Rajesh Singh
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引用次数: 0

Abstract

A hybrid rocket engine test bench experiment carried out the thrust 300 N, retaining nitrous gas as an oxidant, and 70 weight percent paraffin and 30 weight percent aluminum as fuel. To enhance the regression rate, new fuels such as paraffin-based fuel have been created, allowing for more compact engine designs with high thrust densities. As a result, the use of hybrid rocket engines in several domains, such as sounding rockets and small satellites for educational purposes and launch vehicle propulsion systems, has become possible. The solid fuel grain diameter is assumed to spread the characterization under different conditions. Estimate the rocket performance in the assumed condition and develop the test bench setup. In this paper, the data are composed of a 165 mm length of grain, external diameter is 79.6 mm and internal/port diameter is 8 mm. The injector plate used in this experiment is three injector holes with 120°. This injector is a showerhead that is simple in design and it is frequently used in hybrid rocket engines. Constraints such as the pressure in the combustion chamber being 50 bar and the SS304 nozzle, thrust were measured. Four separate test series were conducted. In the first test, one hole in the showerhead injector geometry was studied. In the 2nd, 3rd, and 4th tests, injector plates with three injector holes were used. The test bench of a hybrid rocket engine has many components (oxidizer/pressure tank, combustion chamber with the pre-combustion, post-combustion chamber, conical shape nozzle, igniter, injector plate, etc.).

300 N 混合火箭发动机的实验测试分析
混合火箭发动机试验台实验进行了推力 300 N 的试验,保留了氮气作为氧化剂,以及 70 重量百分比的石蜡和 30 重量百分比的铝作为燃料。为了提高回归率,石蜡基燃料等新型燃料应运而生,使发动机设计更加紧凑,推力密度更高。因此,在探空火箭、用于教育目的的小型卫星和运载火箭推进系统等多个领域使用混合火箭发动机成为可能。假定固体燃料颗粒直径会在不同条件下扩散表征。估算假设条件下的火箭性能,并开发试验台设置。本文中的数据由长度为 165 毫米的颗粒组成,外部直径为 79.6 毫米,内部/端口直径为 8 毫米。本实验中使用的喷射板是三个 120° 的喷射孔。该喷射器为喷淋头,设计简单,常用于混合火箭发动机。在燃烧室压力为 50 巴和 SS304 喷嘴等限制条件下,对推力进行了测量。共进行了四次独立的系列测试。在第一次试验中,研究了喷淋头喷射器的一个孔的几何形状。在第 2、第 3 和第 4 次试验中,使用了带有三个喷射器孔的喷射器板。混合火箭发动机的试验台有许多部件(氧化剂/压力罐、带预燃的燃烧室、后燃室、锥形喷嘴、点火器、喷射器板等)。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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来源期刊
Aerospace Systems
Aerospace Systems Social Sciences-Social Sciences (miscellaneous)
CiteScore
1.80
自引率
0.00%
发文量
53
期刊介绍: Aerospace Systems provides an international, peer-reviewed forum which focuses on system-level research and development regarding aeronautics and astronautics. The journal emphasizes the unique role and increasing importance of informatics on aerospace. It fills a gap in current publishing coverage from outer space vehicles to atmospheric vehicles by highlighting interdisciplinary science, technology and engineering. Potential topics include, but are not limited to: Trans-space vehicle systems design and integration Air vehicle systems Space vehicle systems Near-space vehicle systems Aerospace robotics and unmanned system Communication, navigation and surveillance Aerodynamics and aircraft design Dynamics and control Aerospace propulsion Avionics system Opto-electronic system Air traffic management Earth observation Deep space exploration Bionic micro-aircraft/spacecraft Intelligent sensing and Information fusion
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