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30m/s提高至40m/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。 Near space vehicles have received widespread attention and research in recent years. In order to overcome the shortcomings of traditional airship and solar aircraft, such as large size and poor wind resistance ability, this paper presents a conceptual scheme of an ascending and floating integrated aircraft, and studies its overall parameter design method. Taking the energy balance analysis as the core, the mathematical models of solar energy system, fuel cell system, propulsion system and other subsystems are established. The overall parameters design method is given and the overall design parameters are studied. The results show that compared with the conventional airship, the LIFU has a 53% reduction in volume, a 22% decrease in length, and a 4% drop in takeoff weight. Relative to the fixed-wing solar aircraft, wingspan decreased by 52%, wing area decreased by 56%, take-off weight decreased by 3.5%. The overall parameters of the aircraft are very sensitive to the flight speed. When the flight speed is increased from 30m / s to 40m / s, the take-off weight is increased by about 1 time and the hull volume is increased by 77%. Increasing the efficiency of solar cells, fuel cells and propellers effectively reduces the take-off weight, and the LIFO is more sensitive to these parameters than conventional airships.