升浮一体飞行器总体参数设计方法

doi:10.7527/S1000-6893.2015.0178

固体力学与飞行器总体设计

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

升浮一体飞行器总体参数设计方法

杨穆清, 马东立, 李毅波, 乔宇航, 李冠雄

北京航空航天大学航空科学与工程学院, 北京 100191

收稿日期:2014-12-09 修回日期:2015-06-10 出版日期:2015-11-15 发布日期:2015-07-17
通讯作者: 杨穆清,Tel.:010-82339124,E-mail:qingfengrumu@163.com E-mail:qingfengrumu@163.com
作者简介:杨穆清,男,讲师。主要研究方向:飞行器总体设计。Tel:010-82339124,E-mail:qingfengrumu@163.com;马东立,男,博士,教授,博士生导师。主要研究方向:飞行器总体设计、无人机技术。Tel:010-82339561,E-mail:madonglibuaa@126.com
基金资助:
中央高校基本科研业务费专项资金

General parameters design method of buoyancy-lifting aerial vehicle

YANG Muqing, MA Dongli, LI Yibo, QIAO Yuhang, LI Guanxiong

School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China

Received:2014-12-09 Revised:2015-06-10 Online:2015-11-15 Published:2015-07-17
Supported by:
The Fundamental Research Funds for the Central Universities

摘要/Abstract

摘要：

临近空间飞行器近年来得到了广泛的关注和研究。为克服传统飞艇和太阳能飞机尺寸大、抗风能力差的缺点,本文提出了一种升浮一体飞行器概念方案,并对其总体参数设计方法进行研究。以能量平衡分析为核心,建立了太阳能电池系统、燃料电池系统、推进系统等子系统的数学模型,给出了适合于该飞行器的总体参数设计方法,并对总体设计参数进行了研究。结果表明,升浮一体飞行器相对于传统飞艇,体积下降了53%,长度下降了22%,起飞重量下降了4%。相对于固定翼太阳能飞机,翼展下降了52%,机翼面积减小了56%,起飞重量下降了3.5%。该类飞行器总体参数对飞行速度非常敏感,飞行速度从30 m/s提高至40 m/s时,起飞重量增加约1倍,艇体体积增大77%。提高太阳能电池、燃料电池和螺旋桨效率可有效降低起飞重量,且升浮一体飞行器比传统飞艇对上述参数更敏感。

关键词: 升浮一体飞行器, 总体参数, 能量平衡, 设计方法, 敏感性分析

Abstract:

Near-space aerial vehicle has been widely concerned and studied in recent years. Traditional airship and solar plane have some disadvantages, such as huge dimensions and vulnerable structure. In order to overcome these shortcomings, a concept of buoyancy-lifting aerial vehicle is proposed and studied. Energy balance is the key of the design method. Mathematical model of solar cell system, fuel cell system, propulsion system and so on are established, and sensitivity study is performed. Compared with traditional airship, the volume, length and takeoff weight are reduced by 53%, 22% and 4%, respectively. Compared with traditional solar plane, wing span, wing area and takeoff weight are reduced by 52%, 56% and 3.5%, respectively. Buoyancy-lifting aerial vehicle is very sensitive to flight velocity. With velocity increasing from 30m/s to 40 m/s, takeoff weight is doubled and volume of fuselage augments by 77%. Increasing the efficiency of solar cell, fuel cell and propeller could effectively reduce takeoff weight. Buoyancy-lifting aerial vehicle is more sensitive to these efficiencies than airship.

Key words: buoyancy-lifting aerial vehicle, general parameter, energy balance, design methodology, sensitivity analysis

中图分类号:

V221

杨穆清, 马东立, 李毅波, 乔宇航, 李冠雄. 升浮一体飞行器总体参数设计方法[J]. 航空学报, 2015, 36(11): 3567-3577.

YANG Muqing, MA Dongli, LI Yibo, QIAO Yuhang, LI Guanxiong. General parameters design method of buoyancy-lifting aerial vehicle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(11): 3567-3577.

参考文献

[1] Nickol C L, Guynn M D. High altitude long endurance air vehicle analysis of alternatives and technology requirements development, AIAA-2007-1050[R]. Reston:AIAA,2007.
[2] Zhang K S, Han Z H, Song B F. Flight performance analysis of hybrid airship, AIAA-2009-0901[R]. Reston:AIAA,2009.
[3] Mitchell R W. Effectiveness of hybrid airships as cargo airlifters, AIAA-2011-6832[R]. Reston:AIAA, 2011.
[4] Andan A D, Asrar W, Omar A A. Investigation of aerodynamic parameters of a hybrid airship[J]. Journal of Aircraft, 2012, 49(2):658-661.
[5] Haque A U, Asrar W, Omar A A, et al. Conceptual design of a winged hybrid airship, AIAA-2014-2710[R]. Reston:AIAA, 2014.
[6] Verma A R, Sagar K K, Priyadarshi P. Optimum buoyant and aerodynamic lift for a lifting-body hybrid airship[J]. Journal of Aircraft, 2014, 51(5):1345-1350.
[7] Harper M. A hybrid airship concept for naval missions, AIAA-1976-0923[R]. Reston:AIAA, 1976.
[8] Guo Y L. Thoughts from the cognizance of modern transport airships of Russia and America[C]//Proceedings of 2012 Aerostat Conference. Xi'an:Northwestern Polytechnical University Press, 2012:11-17(in Chinese).郭允良.美/俄国家决策高层认知"现代型运输飞艇"给予我们的思考[C]//2012年中国浮空器大会论文集.西安:西北工业大学出版社, 2012:11-17.
[9] Long F, Luo C. Summarization and analysis of development of foreign airships[C]//Proceedings of 2011 Aerostat Conference. Beijing:Aviation Industry Press, 2011:57-66(in Chinese).龙飞,罗臣.国外飞艇最新发展概述与分析[C]//2011年中国浮空器大会论文集.北京:航空工业出版社, 2011:57-66.
[10] Li F, Ye Z Y, He J Z. Study of aerodynamic configuration design for buoyancy-lifting vehicle in near-space[J]. FlightDynamics, 2009, 27(6):22-25(in Chinese).李峰,叶正寅,贺济洲.临近空间浮升一体化飞行器气动布局研究[J].飞行力学, 2009, 27(6):22-25.
[11] Ye J K, Song B F, Li D, et al. Aerodynamic analysis on a superaltitude winged-airship[J]. Aeronautical Computing Technique, 2008, 38(5):8-10(in Chinese).叶军科,宋笔锋,李栋,等.超高空动升力翼飞艇的气动研究[J].航空计算技术, 2008, 38(5):8-10.
[12] Su J M, Song B F, Zhang Y F. Experimental investigation on aerodynamic interference of near space tandem airship[J]. Journal of Experiments in Fluid Mechanics, 2009, 23(3):58-64(in Chinese).苏建民,宋笔锋,张亚锋.临近空间飞艇排翼式艇翼气动干扰实验研究[J].实验流体力学, 2009, 23(3):58-64.
[13] Wang J, Li Z K, Liu J F, et al. Design and validity check of a wing-boathouse aero craft[J]. Flight Dynamics, 2009,27(5):79-81(in Chinese).王进,李占科,刘纪福,等.一种艇翼式飞行器的设计及验证[J].飞行力学, 2009, 27(5):79-81.
[14] Wang H F, Song B F, Zhong X P. Exploring effective configuration design of a winged airship[J]. Journal of Northwestern Polytechnical University, 2011, 29(3):323-328(in Chinese).王海峰,宋笔锋,钟小平.一种翼艇式飞行器方案研究[J].西北工业大学学报, 2011, 29(3):323-328.
[15] Ma D L, Bao W Z, Qiao Y H. Conceptual design of solar buoyancy-lifting aerial vehicle[C]//Proceedings of 2012 Aerostat Conference. Xi'an:Northwestern Polytechnical University Press, 2012:145-149(in Chinese).马东立,包文卓,乔宇航.太阳能升浮一体飞行器初步概念方案研究[C]//2012中国浮空器大会论文集.西安:西北工业大学出版社, 2012:145-149.
[16] Shen H. Solar photovoltaic technology[M]. Beijing:ChemicalIndustry Press, 2008:23-42(in Chinese).沈辉.太阳能光伏发电技术[M].北京:化学工业出版社, 2008:23-42.
[17] John F, Gundlach IV. Unmanned solar-powered hybrid airships for mars exploration, AIAA-1999-0896[R]. Reston:AIAA, 1999.
[18] Craig L N, Mark D G, Lisa L K, et al. High altitude long endurance UAV analysis of alternatives and technology requirements development, NASA/TP-2007-214861[R]. Washington, D.C.:NASA, 2007.
[19] Khoury G A, Gillett J D. Airship technology[M]. London:Cambridge University Press, 1999:32-45.
[20] Raymer D P. Aircraft design:a comceptual approach[M]. 4th ed. Reston, VA:American Institute of Aeronautics and Astronautics, Inc., 2006.
[21] Strganac T W. Wind study for high altitude platform design, NASA-RP-1044[R]. Washington, D. C.:NASA,1979.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

升浮一体飞行器总体参数设计方法

General parameters design method of buoyancy-lifting aerial vehicle

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	万冰, 陈军, 白菡尘. 基于等效热力过程的宽域冲压全流道性能设计方法[J]. 航空学报, 2024, 45(4): 128757-128757.
[2]	姜乐, 陈以彪, 李炎军, 李贵林, 刘涛. 航空发动机增压式离心通风器流动与分离特性[J]. 航空学报, 2024, 45(2): 128675-128675.
[3]	张恺玲, 李思怡, 段毅, 阎超. 进气道流动中SST湍流模型参数的不确定度量化[J]. 航空学报, 2023, 44(S2): 729429-729429.
[4]	孙晓哲, 侯东, 杨建忠. 双余度机电作动器力纷争机理及敏感性[J]. 航空学报, 2023, 44(S1): 727661-727661.
[5]	王志凯, 陈盛, 范玮. 神经网络宽度对燃烧室排放预测的影响[J]. 航空学报, 2023, 44(5): 126816-126816.
[6]	张振康, 徐万武, 李智严, 叶伟. 钝锥体辐射平衡温度不确定度量化分析[J]. 航空学报, 2023, 44(15): 528673-528673.
[7]	舒博文, 黄江涛, 高正红, 刘刚, 何成军, 夏露. 二元激波矢量喷管矢量性能敏感性分析[J]. 航空学报, 2023, 44(13): 127831-127831.
[8]	王睿, 周洲, 郭荣化, 黄悦琛. 太阳能无人机伞降着陆多体动力学仿真与试验[J]. 航空学报, 2022, 43(8): 225721-225721.
[9]	张冬辉, 张泰华, 崔燕香, 陈臣, 王生. 平流层系留气球气动参数敏感性分析[J]. 航空学报, 2022, 43(5): 125083-125083.
[10]	曹凡, 张美芳, 胡骁, 唐智礼. 轴对称短舱自然层流优化及转捩敏感性分析[J]. 航空学报, 2022, 43(11): 527330-527330.
[11]	富佳伟, 于佳龙, 刘超, 王木国, 王孜孜. 隐身舰载战斗机气动力设计关键技术[J]. 航空学报, 2021, 42(8): 525804-525804.
[12]	李冠雄, 王靖宇, 王运涛. 低压储能的升浮一体飞行器总体参数研究[J]. 航空学报, 2021, 42(7): 224438-224438.
[13]	范周伟, 余雄庆, 王朝, 钟伯文. 基于深度神经网络的客机总体设计参数敏感性分析[J]. 航空学报, 2021, 42(4): 524353-524353.
[14]	宋欣, 沈华, 陈龙宝, 李天玉. Weibull分布参数估计值对细节疲劳额定强度的影响[J]. 航空学报, 2021, 42(3): 224759-224759.
[15]	吕刚德, 王海峰, 邓伟. 基于模型的装备维修性设计控制技术[J]. 航空学报, 2020, 41(6): 523453-523453.