航天推进技术研究院主办
[1]柳长安,李宏君,吴书山.某型靶标液体火箭动力参数优化[J].火箭推进,2018,44(05):32-36.
LIU Changan,LI Hongjun,WU Shushan.Parameter optimization of a liquid rocket propulsion system for a target drone[J].Journal of Rocket Propulsion,2018,44(05):32-36.
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LIU Changan,LI Hongjun,WU Shushan.Parameter optimization of a liquid rocket propulsion system for a target drone[J].Journal of Rocket Propulsion,2018,44(05):32-36.
某型靶标液体火箭动力参数优化
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
44
期数:
2018年05期
页码:
32-36
栏目:
研究与设计
出版日期:
2018-10-31
- Title:
- Parameter optimization of a liquid rocket propulsion system for a target drone
- 文章编号:
- 1672-9374(2018)05-0032-05
- Keywords:
- target drone; high maneuvering; operating envelope; optimization
- 分类号:
- V430-34
- 文献标志码:
- A
- 摘要:
- 随着高速大机动航空技术的发展,为武器鉴定及日常训练提供目标特性的靶标也应具备高速大机动能力。但是高速大机动能力就要求动力系统不仅在高速和大过载飞行工况下具有较大推力,而且应具有较大变推范围以适应靶标较宽的飞行包线。由于国内航发动力目前性能较低而无法满足该类型靶标需求,因此采用火箭动力就成为一种选择。已有采用火箭动力系统的飞行器大多采用推力室变推技术结合多推力室方案来实现大范围变推,但是这无疑就增加了设计参数和设计维度,导致设计分析工作会大大增加。针对这一要求,结合某型靶标的动力系统设计要求进行了动力系统设计参数分析,确定采用最小比冲及包线范围内主要工况点推力偏差的范数来进行设计方案的优劣对比,并借助粒子群优化算法进行了设计方案的优化选择,从而得到了较好的动力系统设计方案及参数。
- 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.
参考文献/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;
备注/Memo
收稿日期:2017-04-18
基金项目: 科技集团公司科技创新研发项目(2014QJ.HTYQ-1Tm)
作者简介: 柳长安(1974—),男,博士,高级工程师,研究领域为动力系统/飞行器总体技术
更新日期/Last Update:
1900-01-01