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Combustion performance of hybrid rocket fuels loaded with MgB_(2)and carbon black additives

Propulsion and Power Research 2023年第2期12卷 212-226页

作者： Yash Pal Sasi Kiran Palateerdham Sri Nithya Mahottamananda Subha Sivakumar Antonella Ingenito School of Aeronautical Sciences Hindustan Institute of Technology and ScienceChennai 603103India School of Aerospace Engineering University of Rome“La Sapienza”00138RomeItaly Department of Aerospace Engineering BS Abdur Rahman Crescent Institute of Science&TechnologyChennai 600048India

Paraffin-based fuel has a great potential for several innovative missions,including space tourism,due to its safety,low environmental impact,high performance and low *** the fact that liquefying solid fuels increases the regression rate of hybrid rocket motors,incorporating energetic materials into solid fuel can still improve the *** objective and scope of this study is to increase the performance characteristics of the paraffin-based fuel by using magnesium diboride(MgB_(2))and carbon black(CB)*** cylindricalport fuel grains were manufactured with various additives percentages in mass(wt%:CB-2%and MgB_(2)-10%)and tested using a laboratory-scale ballistic hybrid motor under gaseous *** mechanical performance results revealed that adding CB and MgB_(2) improved the ultimate strength and elastic modulus of paraffin-based *** addition of these fillers increased the hardness of fuel by developing a strong interaction in the paraffin ***(TG)results showed that CB inclusion improved the thermal stability of the paraffin *** average regression rates of fuels loaded with CB and MgB_(2) were 32%and 52%higher than those of unmodified paraffin wax,*** characteristic velocity efficiency was found in the range of 68%e79%at an O/F ratio of *** MgB_(2) oxidation/combustion in the paraffin matrix was described by a four-step oxidation process ranging from 473 K to 1723 ***,a combustion model of MgB_(2) in the paraffin matrix was proposed,and four-step oxidation processes were discussed in detail.

关键词： hybrid rocket Paraffin wax Regression rate Magnesium diboride Mechanical properties

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Multi-disciplinary Conceptual Design Knowledge of Multi-stage hybrid rocket Using Data Mining Technique

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Journal of Mechanics Engineering and Automation 2015年第1期5卷 1-9页

作者： Masahiro Kanazaki Kazuhisa Chiba Koki Kitagawa Toru Shimada Masashi Nakamiya Department of Aerospace Engineering Graduate School of System Design Tokyo Metropolitan University Tokyo 191-0065Japan Graduate School of Engineering Hokkaido University of Science Sapporo 006-8585 Japan Institute of Space and Astronautical Science Japan Aerospace Exploration Agency Sagamihara 252-5210 Japan Research Institute for Sustainable Humanosphere Kyoto University Kyoto 606-8501 Japan

This paper deals with the application of data mining techniques to the conceptual design knowledge for a LV （launch vehicle） with a HRE （hybrid rocket engine）. This LV is a concept of the space transportation, which can deliver micro-satellite to the SSO （sun-synchronous orbit）. To design the higher performance LV with HRE, the optimum size of each component, such as an oxidizer tank containing liquid oxidizer, a combustion chamber containing solid fuel, a pressurizing tank and a nozzle, should be acquired. The Kriging based ANOVA （analysis of variance） and SOM （self-organizing map） are employed as data mining techniques for knowledge discovery. In this study, the paraffin （FT-0070） is used as a propellant of HRE. Then, the relationship among LV performances and design variables are investigated through the analysis and the visualization. To calculate the engine performance, the regression rate is computed based on an empirical expression. The design knowledge is extracted for the design knowledge of the multi-stage LV with HRE by analysis using ANOVA and SOM. As a result, the useful design knowledge on the present design problem is obtained to design HRE for space transportation.

关键词： hybrid rocket data mining techniques multidisciplinary design

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