Solar Orbiter magnetometer - thermal and management, March 2009-April 2010

太阳轨道磁力计 - 热和管理，2009 年 3 月至 2010 年 4 月

• 批准号: ST/H000941/1
• 负责人: Timothy Horbury
• 金额: $ 6.75万
• 依托单位: Imperial College London
• 依托单位国家: 英国
• 项目类别: Research Grant
• 财政年份: 2009
• 资助国家: 英国
• 起止时间: 2009 至 无数据
• 项目状态: 已结题
• 来源: https://gtr.ukri.org/projects?ref=ST%2FH000941%2F1
• 关键词: Solar; Orbiter; magnetometer; thermal; management

Imperial College London leads a consortium which has proposed a magnetometer for the Solar Orbiter mission. The magnetometer is a key instrument to the science goals of the mission and comprises two sensors located on a boom in shadow behind the spacecraft, an electronics box in the spacecraft and associated harnesses. The proposed design measures the magnetic field in the vicinity of the spacecraft with sufficient precision to characterise phenomena from large scale structures to ion kinetic scales, is a mature design and complies with the mass and power requirements of the Payload Definition Document. This proposal is for a limited amount of work to support the Imperial College London team until April 2010. During this time, we will undertake instrument leadership activities, coordinating our activities with the European Space Agency, NASA and other instrument teams. We will also address the most important technical issue of the instrument, which is temperature control. The sensor will sit at the end of a boom, in continual shadow, and hence will get cold. We will undertake detailed modelling work, to determine precisely how cold it is expected to run, and how we can keep the temeprature within allowable limits using heaters: specifying the required heater power is a key goal. We will aos investigate whether we can run our sensors at temperatures lower than that to which they have previously been qualified.

伦敦帝国理工学院领导了一个财团，该财团提出了一种用于太阳轨道飞行器任务的磁力计。磁力计是实现该任务科学目标的关键仪器，由两个传感器组成，传感器位于航天器后面阴影处的吊杆上，航天器内的一个电子箱和相关的线束。所提出的设计测量了航天器附近的磁场，具有足够的精度来表征从大型结构到离子动力学尺度的现象，是一种成熟的设计，符合有效载荷定义文件的质量和功率要求。这项提案是为了支持帝国理工学院团队的有限数量的工作，直到2010年4月。在此期间，我们将进行仪器领导活动，与欧洲航天局、美国宇航局和其他仪器团队协调我们的活动。我们还将讨论该仪器最重要的技术问题，即温度控制。传感器将位于吊杆的末端，处于持续的阴影中，因此会变冷。我们将进行详细的建模工作，以准确确定预期运行的温度，以及如何使用加热器将温度保持在允许的范围内：指定所需的加热器功率是一个关键目标。我们还将研究我们的传感器是否能在比它们之前合格的温度更低的温度下运行。