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Design thermal modeling of solar panel module with embedded reconfigurable Air-Coil for micro-satellites

机译：嵌入式微卫星嵌入式空气线圈的太阳能电池板模块的设计和热建模

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Spacecrafts need to maneuver their solar panels towards the sun and antennas towards the ground station for maximum solar power harvesting and communication with the ground station. For tracking purpose, usually magnetorquer rods, reaction wheels and permanent magnets are used, but they are heavier, expensive, and occupy extra space on the spacecraft. Keeping in mind the dimension, budget and mass constraints of small satellites, a system compatible with small satellite is worth consideration. Consequently, this paper focuses on designing and analyzing a solar panel module with embedded Air-Coil. Such an Air-Coil is an innovative idea for the replacement of heavier, bulky and expensive attitude control systems. The proposed Air-Coil is integrated in the internal layers of an eight layers solar panel PCB module. Complete degradation analyses of the solar panel have been done to ensure that it will meet the satellite power requirements at BOL (beginning of life) and EOL (end of life). The proposed embedded Air-Coil has been analyzed for the generated magnetic moment, resultant torque, power consumption and temperature increase of the complete solar panel unit. A steady state thermal model is proposed to measure the thermal resistance between top and bottom layers of the solar panel module, which gives an idea about the heat trapped inside the solar panel module. The designed embedded Air-Coil is fully reconfigurable where coil in each layer can be operated as a separate coil. The four coils in different layers can be attached or detached through switches in different configurations i.e. single coil, four in series, four in parallel, and their hybrid combinations. The analyses of power consumption, heat dissipation, temperature rise, magnetic moment and torque generation by different configurations of the designed Air-Coil have been performed. The generated magnetic moment is very high i.e. around 12Am2, which is enough to rotate a microsatellite by 90° in 200s. The efficacy of the proposed module is significantly higher than the already available systems with respect to mass, price, power dissipation, heat generation, and dimension.
机译：航天器需要操纵其太阳能电池板朝向太阳，天线对准地面站，以最大程度地收集太阳能并与地面站通信。为了进行跟踪，通常使用磁矩棒，反作用轮和永磁体，但它们较重，昂贵且在航天器上占据额外空间。考虑到小型卫星的尺寸，预算和质量限制，与小型卫星兼容的系统值得考虑。因此，本文着重于设计和分析带有嵌入式Air-Coil的太阳能电池板模块。这样的气圈是一种创新的想法，可以代替较重，笨重和昂贵的姿态控制系统。拟议的Air-Coil集成在一个八层太阳能电池板PCB模块的内部层中。已经对太阳能电池板进行了完整的退化分析，以确保其满足BOL（寿命开始）和EOL（寿命终止）时的卫星功率要求。已对拟议的嵌入式Air-Coil进行了分析，以分析整个太阳能电池板单元的产生的磁矩，合成转矩，功耗和温度升高。提出了一种稳态热模型来测量太阳能电池板模块顶层和底层之间的热阻，从而给出了热量在太阳能电池板模块内部滞留的想法。设计的嵌入式Air-Coil可以完全重新配置，其中每一层的线圈都可以作为单独的线圈运行。可以通过不同配置的开关连接或分离不同层中的四个线圈，即单个线圈，四个串联，四个并联以及它们的混合组合。通过设计的气圈的不同配置对功耗，散热，温升，磁矩和转矩产生进行了分析。产生的磁矩非常高，即大约12Am 2 ，足以在200 s内使微卫星旋转90°。就质量，价格，功率耗散，热量产生和尺寸而言，所提出模块的功效明显高于现有系统。

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