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Modular design of electrical power subsystem for a remote sensing satellite

机译：遥感卫星电源子系统的模块化设计

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Power Supply is one of the most important subjects in Remote Sensing satellite. Having an appropriate and adequate power resources, A Remote Sensing satellite may utilize more complex Payloads and also make them more operable in orbit and mission timeline. This paper is deals with a design of electrical power supply subsystem (EPS) of a hypothetical satellite with remote sensing mission in Low Earth Orbits, without any restriction on the type and number of Payloads and only assuming a constraint on the total power consumption of them. EPS design is in a way that can supply the platform consumption to support Mission and Payload(s) requirements beside the power consumption of the payload(s). The design is also modular, as it can be used not only for the hypothetical system, but also for the other systems with similar architecture and even more needs on power and differences in some specifications. Therefore, a modularity scope is assumed in design of this subsystem, in order to support the satellite in the circular orbits with altitude of 500 to 700 km and inclination of 98 degrees, a sun-synchronous orbit, where one can say the design is applicable to a large range of remote sensing satellites. Design process will be started by high level and system requirements analysis, continued by choosing the best approach for design and implementation based on system specification and mission. After EPS sizing, the specifications of elements are defined to get the performance needed during operation phases; the blocks and sub-blocks are introduced and details of their design and performance analysis are presented; and the modularity is verified using calculations for the confined area based on design parameters and evaluated by STK software analysis results. All of the process is coded in MATLAB software and comprehensive graphs are generated to demonstrate the capabilities and performance. The code and graphs are developed in such a way to completely review the design procedure and system efficiency in worst case of power consumption scenario at the beginning and end of satellite life
机译：电源是遥感卫星中最重要的主题之一。遥感卫星具有适当而充足的动力资源，可以利用更复杂的有效载荷，并使它们在轨道和任务时间表上更具可操作性。本文研究的是一个在低地球轨道上具有遥感任务的假设卫星的电源子系统（EPS）的设计，对有效载荷的类型和数量没有任何限制，并且仅假设它们的总功耗受到限制。 EPS设计的方式是，除了提供有效载荷的功耗外，还可以提供平台消耗以支持任务和有效载荷需求。该设计也是模块化的，因为它不仅可以用于假设的系统，而且还可以用于架构相似，甚至在某些规格上对功率和差异有更多需求的其他系统。因此，在该子系统的设计中假定了模块化范围，以便在高度为500至700 km，倾斜度为98度的圆形轨道（太阳同步轨道）中支持卫星，可以说该设计适用广泛的遥感卫星。设计过程将从高层和系统需求分析开始，然后继续根据系统规范和任务选择最佳的设计和实现方法。在确定EPS尺寸之后，定义元素的规格以获得在操作阶段所需的性能。介绍了模块和子模块，并详细介绍了它们的设计和性能分析；并使用基于设计参数的密闭区域计算来验证模块性，并通过STK软件分析结果进行评估。所有过程都在MATLAB软件中进行了编码，并生成了全面的图形来演示其功能和性能。代码和图形的开发方式可以在卫星寿命的开始和结束时在最坏的功耗情况下，全面审查设计程序和系统效率。

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