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

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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.

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E-mail：hkxb@buaa.edu.cn

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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

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