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Parameter optimization of a liquid rocket propulsion system for a target drone(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2018年05期
Page:
32-36
Research Field:
研究与设计
Publishing date:

Info

Title:
Parameter optimization of a liquid rocket propulsion system for a target drone
Author(s):
LIU Changan; LI Hongjun; WU Shushan
Xi'an Aerospace Propultion Institute,Xi'an 710100,China
Keywords:
target drone;  high maneuvering;  operating envelope;  optimization
PACS:
V430-34
DOI:
-
Abstract:
With the development of the aero-weapon with high speed and high maneuvering,the target drones which were used for weapon authentication and daily training must also have the ability of high speed and high maneuvering.However, this requires the propulsion system should have not only big thrust at high speed and high maneuvering, but also large thrust variable range, in order to meet the requiement of wide flight envelope of the target drone.As now the domestic aeroengines are of low performance and can't satisfy what a target drone needs, so liquid rocket engine is an alternative choice.Most flight vehicles using rocket engines applied variable thruster combined with multi-thrusters to achieve large range thrust changing, which result in more designing parameters and more designing dimensions, thus leads to more design and analysis efforts.According to this question, design parameter analysis of a propulsion system was carried out here according to propulsion system designing demands from a target drone, in which the variables are optimized using the multi-objective particle swarm optimization method(MOPSO), and the design objectives are settled as the engine specific impulse and the thrust deviations.Through the optimization,some optimal design parameters are reached,which can help designers understand their design project and make decisions better.

References:

[1] 马兵兵,翟丽婷,孙璐.火箭发动机随机推力调节控制驱动器的研制[J].火箭推进,2012,38(2):79-82.
MA Bingbing,ZHAI Liting,SUN Lu.Research on random thrust adjustable controller of rocket engine [J].Journal of rocket propulsion,2012,38(2):79-82.
[2] 张金容,靳爱国, 汪亮.泵压式液体火箭发动机变推力方案选择[J].航空动力学报, 2008,23(5):921-926;
[3] 王允良,李为吉.基于混合多目标粒子群算法的飞行器气动布局设计[J].航空学报,2008,29(15):1202-1206;
[4] 安伟刚.多目标优化方法研究及其工程应用[D].西安:西北工业大学,2005;
[5] KENNEDY J, EBERHART R C.Particle swarm optimization[C].Proceedings of the 1995 IEEE International Conference on Neural Networks.1995: 194221948;
[6] Ng K Y, TAN C M.Single and multiobjective wing planform and airfoil shape optimization using a swarm algorithm,AIAA2003-20045[R].USA: AIAA, 2003.
[7] 张忠峰,高云峰,宝音贺西.基于粒子群优化的高超声速飞行器航迹规划[J].系统仿真学报, 2009,21(8):2428-2431;
[8] 柳长安,南向军,闫志勇.反折式二元超声速进气道研究[J].火箭推进, 2014,40(1):45-49;
LIU Changan,NAN Xiangjun,YAN Zhiyong.Research of 2-D reflective supersonic inlet [J].Journal of rocket propulsion,2014,40(1):45-49;
[9] 罗世彬,罗文彩,丁猛,等.超燃冲压发动机二维进气道多级多目标优化设计方法[J].国防科技大学学报, 2004,26(3):1-6;
[10] 林锉云,董加礼.多目标优化的方法与理论[M].长春:吉林教育出版社,1992;
[11] 夏露,高正红,苏伟.Pareto遗传算法在气动外形优化中的应用[J].空气动力学学报,2007,25(2):194-198;

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