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Design of the thermal control system for the Space Technology 5 Microsatellite

机译:空间技术5微卫星的热控制系统设计

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The New Millennium Program's (NMP) Space Technology 5 (ST-5) Project, currently in Phase B of the design process, is slated to launch three 20-kg class spin stabilized microsatellites in late 2003. The proposed orbit is highly elliptical and could result in an earth shadow eclipse of almost 2 hours. Although ST-5's maximum eclipse is only 2 hours, future missions could involve eclipses as long as 8 hours. As spacecraft size, mass, and available resources decrease and eclipse duration increases, thermal engineers will be challenged to design simple but robust thermal control systems that meet temperature requirements for all phases of the mission. In addition, future similar missions may involve large ""fleets"" of such small spacecraft, which, for cost and I&T reasons, must be almost identical in design. Such spacecraft will require a generic but robust thermal control design that is suitable for a wide variety of thermal environments. This paper presents the results of a study of three design concepts and preliminary analysis of the design selected for ST-5.
机译:新的千年计划的(NMP)空间技术5(ST-5)项目,目前在设计过程的B阶段,是在2003年底推出了三个20公斤级旋转稳定微卫星的。提出的轨道是高度椭圆形的,可以导致地球阴影日食差不多2个小时。虽然ST-5的最高日食仅为2小时,但未来的任务可能涉及eClipses,只需8小时即可。作为航天器大小,质量和可用资源减少和日食持续时间的增加,热工程师将面临挑战以满足任务所有阶段的温度要求,设计简单但坚固的热控制系统。此外,未来类似的任务可能涉及这种小型航天器的大“车队”“,因为成本和I&T的原因,必须在设计中几乎相同。这种航天器需要通用但坚固的热控制设计,适用于各种热环境。本文介绍了对ST-5选择的三种设计概念和初步分析的研究结果。

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