Output performance analyses of solar array on stratospheric airship with thermal effect

2016 ◽  
Vol 104 ◽  
pp. 743-750 ◽  
Author(s):  
Jun Li ◽  
Mingyun Lv ◽  
Dongjie Tan ◽  
Weiyu Zhu ◽  
Kangwen Sun ◽  
...  
2017 ◽  
Vol 147 ◽  
pp. 135-144 ◽  
Author(s):  
Huafei Du ◽  
Weiyu Zhu ◽  
Yifei Wu ◽  
Lanchuan Zhang ◽  
Jun Li ◽  
...  

2016 ◽  
Vol 17 (3) ◽  
pp. 432-441 ◽  
Author(s):  
Yuanyuan Zhang ◽  
Jun Li ◽  
Mingyun Lv ◽  
Dongjie Tan ◽  
Weiyu Zhu ◽  
...  

2020 ◽  
Vol 26 (4) ◽  
pp. 21-32
Author(s):  
Nibras Mahmood Obaid ◽  
Emad T. Hashim ◽  
Naseer K. Kasim

The performance analyses of 15 kWp (kW peak) Grid -Tied solar PV system (that considered first of its type) implemented at the Training and Energy Research Center Subsidiary of Iraqi Ministry of Electricity in Baghdad city has been achieved. The system consists of 72 modules arranged in 6 strings were each string contains 12 modules connected in series to increase the voltage output while these strings connected in parallel to increase the current output. According to the observed duration, the reference daily yields, array daily yields and final daily yields of this system were (5.9, 4.56, 4.4) kWh/kWp/day respectively. The energy yield was 1585 kWh/kWp/year while the annual total solar irradiation received by solar array system was 1986.4kWh/m2. The average power losses per day of array, system losses and overall losses were (1.38, 0.15, 1.53) kWh/kWp/day respectively. The average capacity factor and performance ratio per year were 18.4% and 75.5% respectively. These results highlighted the performance analyses of this PV solar system located in Baghdad city. The performance can be considered as good and significant comparing with other world PV solar stations.  


2017 ◽  
Vol 124 ◽  
pp. 22-33 ◽  
Author(s):  
Mingyun Lv ◽  
Zhongbing Yao ◽  
Lanchuan Zhang ◽  
Huafei Du ◽  
Junhui Meng ◽  
...  

2013 ◽  
Vol 772 ◽  
pp. 608-614
Author(s):  
Kang Wen Sun ◽  
Gao Ming Liang ◽  
Ke Li ◽  
Ming Zhu

As one of the key technic of achieving high-altitude and long-time flight, the stratospheric airship energy system in stratosphere is always the important point but also very difficult. In this paper, the stratospheric airship geometry analysis as a starting point, through a series analysis as follow: the stratospheric airship surface mesh model, the sun vector, the relationship between the sun vector and the body coordinate system, and the solar radiation model, we have accomplished the characteristics analysis of the radiation receiving on stratospheric airship. The analysis result show that: Although different flight direction corresponding to different distribution of light intensity, the light changes from sunrise to sunset is symmetrical when the stratospheric airship on the condition of level flight. Airship for east heading of region resides, the maximum energy can be obtained when the solar array laying in the installation of 0 β π / 4. With the changing of heading angle and pitch angle, the radiation receiving of the solar array can also transform, but the influence of pitch angle greater than heading angle.


Energies ◽  
2021 ◽  
Vol 14 (14) ◽  
pp. 4204
Author(s):  
Qiumin Dai ◽  
Daoming Xing ◽  
Xiande Fang ◽  
Yingjie Zhao

High altitude airships possess tremendous potential for long-endurance spot hovering platforms for both commercial and strategic applications. The energy system, which is mainly made up of solar array and regenerative fuel cell, is the key component of a high altitude airship. The thermal effect is a major factor that affects the performance of the energy system of long endurance stratospheric vehicles. In this paper, a conceptual design method focusing on the thermal and power characteristics of an energy system for stratospheric airships is proposed. The effect of thermal behavior of solar array on the energy system is analyzed. An optimized case is obtained on the consideration of power supply, thermal behaviors of helium and solar array. Results show that the maximum temperature difference of the solar array may be reduced by about 20 K and the mass of payload can be improved by up to 5%.


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