arXivDaily arXiv每日学术速递 周一至周五更新
arXiv 2006.03111astro-ph.IM
收藏

高倾角太阳任务

The High Inclination Solar Mission

K. Kobayashi, L. Johnson, H. Thomas, S. McIntosh, D. McKenzie, J. Newmark, A. Heaton, J. Carr, M. Baysinger, Q. Bean, L. Fabisinski, P. Capizzo, K. Clements, S.… 展开作者

K. Kobayashi, L. Johnson, H. Thomas, S. McIntosh, D. McKenzie, J. Newmark, A. Heaton, J. Carr, M. Baysinger, Q. Bean, L. Fabisinski, P. Capizzo, K. Clements, S. Sutherlin, J. Garcia, K. Medina, D. Turse

阅读 PDF
arXiv 页面 ↗HTML 原文 ↗

摘要：

高倾角太阳飞行任务（HISM）是一个观测太阳和日光层的黄道外飞行任务概念。任务剖面主要基于太阳极地成像仪的概念：最初螺旋进入0.48天文单位的黄道轨道，然后以每年$\sim 10$度的速度增加轨道倾角，最终达到$>$ 75度的日面倾角。轨道剖面是利用目前正在为太阳巡洋舰飞行任务开发的技术所产生的太阳帆来实现的。HISM遥感仪器包括一个成像分光偏振计（多普勒成像仪/磁力仪）和一个可见光日冕仪。现场仪器包括法拉第杯、离子组成光谱仪和磁力计。等离子体波的测量是用电天线和高速磁强计进行的。任务评估中使用的$7,000\,\mathrm{m}^2$帆是4象限$1,666\,\mathrm{m}^2$太阳巡洋舰设计的直接延伸，并采用了相同类型的高强度复合材料吊杆、展开机构和膜技术。模拟的帆系统旋转（约1 rpm），以确保所需的吊杆特性和裕度。航天器总线具有精确指向的三轴稳定仪器平台，一旦航天器到达0.48 AU的太阳距离，就可以进行全面的科学观测。

英文摘要：

The High Inclination Solar Mission (HISM) is a concept for an out-of-the-ecliptic mission for observing the Sun and the heliosphere. The mission profile is largely based on the Solar Polar Imager concept: initially spiraling in to a 0.48 AU ecliptic orbit, then increasing the orbital inclination at a rate of $\sim 10$ degrees per year, ultimately reaching a heliographic inclination of $>$75 degrees. The orbital profile is achieved using solar sails derived from the technology currently being developed for the Solar Cruiser mission, currently under development. HISM remote sensing instruments comprise an imaging spectropolarimeter (Doppler imager / magnetograph) and a visible light coronagraph. The in-situ instruments include a Faraday cup, an ion composition spectrometer, and magnetometers. Plasma wave measurements are made with electrical antennas and high speed magnetometers. The $7,000\,\mathrm{m}^2$ sail used in the mission assessment is a direct extension of the 4-quadrant $1,666\,\mathrm{m}^2$ Solar Cruiser design and employs the same type of high strength composite boom, deployment mechanism, and membrane technology. The sail system modelled is spun (~1 rpm) to assure required boom characteristics with margin. The spacecraft bus features a fine-pointing 3-axis stabilized instrument platform that allows full science observations as soon as the spacecraft reaches a solar distance of 0.48 AU.

机构、总结、中文摘要均由AI分析而来，可能存在错误，请以论文正文为准。

↑