拓展太阳能飞机在较高纬度地区的跨年驻留性能有助于促成太阳能飞机的广泛实用化。建立了适用于任意高度、任意纬度、任意指向的光伏组件面功率模型,并考虑了光伏组件的温度效应,通过能量仿真得出:在方位角跟踪方式下,滚偏角为90°的主动式光伏组件的日均面功率最优。然后在布局与能源综合设计思想指导下,建立了一套基于机翼-帆尾的太阳能飞机总体参数设计方法,其组成模块包括各部件质量方程、气动效率方程、用于构建气动布局参数与全机光伏组件面功率特性之间映射关系的Kriging代理模型,以及参与总体参数匹配优化设计的量子粒子群优化(QPSO)算法及其多目标评价函数。面向高纬度与跨年驻留的设计指标,开展了机翼-帆尾太阳能飞机的方案实例设计,其中驻留纬度与高度指标分别为45°N和18km。详细分析了此方案在23.5°N~55°N纬度域内的可持续高度包线。研究结果表明:与传统布局形式相比,机翼-帆尾布局形式大幅提升了高纬度地区冬季附近的光伏组件面功率,有效地减小了翼展尺度、机翼面积并提升了巡航速度,具有良好的应用优势。方案设计实例也验证了基于机翼-帆尾的太阳能飞机总体参数设计方法的可行性。 Expanding the New Year’s staying performance of solar powered aircraft at higher latitudes helps to promote the widespread practical application of solar powered aircraft. The power model of PV module suitable for arbitrary height, arbitrary latitude and arbitrary orientation was established and the temperature effect of PV module was considered. Through the energy simulation, the active power The average daily surface power of PV modules is the best. Then under the guidance of layout and energy integrated design idea, a set of wing-tail-based solar aircraft overall parameter design method is established. The module consists of the mass equations of each component, the aerodynamic efficiency equation, Kriging agent model for mapping the power characteristics of PV modules and the Quantum Particle Swarm Optimization (QPSO) algorithm and its multi-objective evaluation function which are involved in the overall parametric matching and optimization design. For the design targets of high latitude and New Year’s residency, the program design of the wing-sail tail-end solar aircraft was carried out. The latitude and altitude indices of stay were 45 ° N and 18 km respectively. In this paper, the sustainable height envelope of this scheme in 23.5 ° N ~ 55 ° N latitude is analyzed in detail. The results show that compared with the traditional layout form, the wing-tail layout significantly improves the PV module surface power in winter at high latitudes, effectively reducing the span size, wing area and cruising speed, Has good application advantages. The design example also verifies the feasibility of designing the overall parameters of the solar-powered aircraft based on the wing-sail tail.