纳米卫星低成本、中分辨率成像载荷设计与性能评价

S. M. A. Bashir, Ghulam Abbas Mughal, Rehan Mahmood, K. Khurshid
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引用次数: 1

摘要

任何机载成像系统的主要目标都是从太空中远程拍摄感兴趣区域的图像。对于高分辨率图像,使用大口径望远镜,这需要较大的卫星结构。对于小卫星(特别是纳米卫星),采用低分辨率采集系统获取成像数据。本文讨论了一种专门为纳米卫星设计的成像有效载荷设计,其中存在尺寸、重量和功率的限制。本文讨论了光学器件的设计、传感器的选择、通用软件流程图和总体设计拓扑。最后,从功耗、运行环境、空间分辨率和开发成本等方面对设计的有效载荷进行了评估。有效载荷使用工业部件制造,因此工作温度限制在- 25°C至70°C,此温度限制适用于组件的内部温度。待机功耗远低于10mW。项目以9cm × 9cm的PCB形式交付,随软件平台一起完成离线测试。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Design and performance evaluation of low cost, medium resolution imaging payload for nanosatellites
The main objective of any onboard imaging system is to remotely take images of the region of interest from space. For high resolution images, large aperture size telescopes are used which require large satellite structures. In case of small satellites (especially Nanosatellites) low resolution acquisition systems are used to acquire imaging data. This paper discusses an imaging payload design specifically designed for Nanosatellites where there are constraints of size, weight, and power. Design of optics, selection of sensor, generic software flow diagram and overall design topology are discussed in this paper. Finally the designed payload is evaluated based on the power consumption, operational environment, spatial resolution and cost of development. Payload is made using industrial components hence the operational temperature is limited to −25°C to 70°C, this temperature limit is for internal temperature of the components. The standby power consumption is way under 10mW. The project is delivered in the form of a PCB of 9cm × 9cm along with the software platform for complete offline testing.
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