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Optimum attitude planning of near-space solar powered airship

机译：近太空太阳能飞艇的最佳姿态规划

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The attitude of Near-space airship including yaw, roll and pitch angle is important to the output performance of airship solar array. The yaw angle of airship can be controlled without affecting airship mission execution in the quasi-zero wind layer of near-space. This paper aims to improve solar energy system of near-space airship by optimizing airship yaw angle. Based on the solar radiation model and solar array energy model, a MATLAB program is established to calculate the output power. For model validation, solar radiation and output power are simulated and compared with experimental results. The optimum yaw angle for a whole year is obtained with optimization model based on genetic algorithm. The effect of airship shape parameters including the slenderness ratio and the ratio of forebody length to total length (L-1/L) is elaborated. The results show that the effect of yaw angle on output power is greater at higher latitude than that at lower latitude and the solar array output energy can be remarkable increased after adjusting yaw angle of airship according to the optimization result. Although the optimal yaw angle is different with the change of working date and latitude, the optimum values mainly lie in 0 degrees and 180 degrees. Moreover, the optimal yaw angle is barely changed, when the slenderness ratio and L-1/L of airship are greater than 0.3 and 0.25, respectively. The result has great valuable engineering reference in attitude planning of near-space airship and other aerospace vehicle for energy improvement. (C) 2018 Elsevier Masson SAS. All rights reserved.
机译：包括偏航角，侧倾角和俯仰角在内的近太空飞艇的姿态对于飞艇太阳能电池阵列的输出性能至关重要。可以控制飞艇的偏航角，而不会影响近空间的准零风层中的飞艇任务执行。本文旨在通过优化飞艇的偏航角来改善近太空飞艇的太阳能系统。基于太阳辐射模型和太阳电池阵列能量模型，建立了MATLAB程序来计算输出功率。为了进行模型验证，模拟了太阳辐射和输出功率，并将其与实验结果进行了比较。通过基于遗传算法的优化模型，得出了全年的最佳偏航角。阐述了飞艇形状参数的影响，包括细长比和前体长度与总长度的比（L-1 / L）。结果表明，偏航角对高纬度输出功率的影响大于低纬度，根据优化结果调整飞艇的偏航角后，太阳能电池阵列的输出能量可以显着增加。尽管最佳偏航角随工作日期和纬度的变化而有所不同，但最佳偏航角主要在0度和180度之间。此外，当飞艇的细长比和L-1 / L分别大于0.3和0.25时，最佳偏航角几乎不变。该结果在近太空飞艇和其他航空航天器的姿态规划中为提高能源效率具有重要的工程参考价值。 （C）2018 Elsevier Masson SAS。版权所有。

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