Conceptual Design of Single-stage Rocket Using Hybrid Rocket by Means of Genetic Algorithm
In this study,a multi-objective genetic algorithm(MOGA)was applied to the multidisciplinary design optimization(MDO)of a hybrid rocket.A swirling-oxidizer-type hybrid rocket engine(HRE)with a single cylindrical grain port was designed.It was considered that this HRE could temporarily stop combustion via oxidizer throttling; this feature is called multi-combustion.The MOGA was applied to solve the multi-objective problem using real-number coding and the Pareto ranking method.In this study,three design problems were considered.First problem was the maximization of the flight altitude and minimization of the gross weight.Second problem was the minimization of the maximum acceleration and minimization of the gross weight.Third problem was the maximization of the duration time over the target flight altitude and minimization of the gross weight.Each objective function was empirically estimated.In addition,this study compared two types of HREs to investigate the effects of the multicombustion: one type was able to carry out the multi-combustion,and the other was not.Many non-dominated solutions were obtained using the MOGA,and a trade-off was observed between the two objective functions.To understand the design problem,the MOGA results were visualized using a parallel coordinate plot(PCP).
Hybrid rocket engine Single-stage launch vehicle Multi-disciplinary design Genetic algorithm
Masahiro Kanazaki Atthaphon Ariyairt Kazuhisa Chiba Koki Kitagawa Toru Shimada
Tokyo Metropolitan University,6-6,Hino,Tokyo 191-0065,Japan Hokkaido University of Science,7-15-4-1,Maeda,Teine,Sapporo 006-8585,Japan Japan Aerospace Exploration Agency,3-1-1 Yoshinodai,Chuo-ku,Sagamihara 001-0010,Japan
国际会议
2014 Asia-Pacific International Symposium on Aerospace Technology(2014亚太航空航天技术学术会议)
上海
英文
1-13
2014-09-24（万方平台首次上网日期，不代表论文的发表时间）