升浮一体飞行器总体参数设计方法
收稿日期: 2014-12-09
修回日期: 2015-06-10
网络出版日期: 2015-07-17
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
Received date: 2014-12-09
Revised date: 2015-06-10
Online published: 2015-07-17
Supported by
The Fundamental Research Funds for the Central Universities
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。
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 . DOI: 10.7527/S1000-6893.2015.0178
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.
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