Using CubeSat/micro-satellite technology to demonstrate the Autonomous Assembly of a Reconfigurable Space Telescope (AAReST)
Using CubeSat/micro-satellite technology to demonstrate the Autonomous Assembly of a Reconfigurable Space Telescope (AAReST)
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DOI：
10.1016/j.actaastro.2015.04.008
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发表时间：
2015-09-01
影响因子：
3.5
通讯作者：
Baker, John
中科院分区：
文献类型：
--
作者：
Underwood, Craig;Pellegrino, Sergio;Baker, John
未来直径超过20米的空间望远镜将需要新的方法：高精度编队飞行或在轨组装。我们认为，后者有望在短期内以更低的成本和更实用的解决方案提供，前提是大部分组装可以自主进行。为了获得经验并降低风险，我们提出了一个微型/纳米卫星组合示范使命，重点是所需的光学技术（自适应反射镜、相敏探测器）和自主交会对接技术（卫星间链路、相对位置传感、自动对接机制）。该使命将涉及两颗“3U”立方体卫星式纳米卫星（“立方体卫星”），每颗卫星都携带一个电驱动自适应反射镜，并且每颗卫星都能够自主脱离对接和与一个小型中央“15 U”级微型/纳米卫星核心重新对接，该核心装有两个固定反射镜和一个吊杆部署的焦平面组件。所有三个航天器将作为一个类似于40公斤的微型卫星包发射。航天器总线是基于萨里的SNAP-1和STRaND-1任务（分别于2000年和2013年发射）的遗产，而光学，成像传感器和形状调整自适应镜（及其相关的调整机制）由加州理工学院/喷气推进实验室提供。对接系统本身是以萨里空间中心正在开发的电磁对接系统以及为STRaND-2开发的交会传感技术为基础的。在轨道上，使命剖面将首先在脱离对接之前建立复合航天器的成像能力，然后自主重新对接单个Mirror Sat。这将测试对接系统、自主导航和系统识别技术。如果成功的话，下一阶段将看到两个卫星航天器脱离并重新对接到核心航天器的线性编队，以代表一个大（但稀疏）的高分辨率成像孔径。对恒星成像是主要目标，但正在考虑其他天体和地面目标。加州理工学院和SSC的团队目前正在进行空间硬件的使命规划和开发。自主交会和对接系统目前正在航天中心的二维空气轴承台上进行测试，推进和精确姿态控制系统目前正在开发中。计划于2016年推出。本文详细介绍了使命的概念，所涉及的技术和进展，到目前为止，重点是航天器总线。(C)2015年IAA。由爱思唯尔有限公司出版。保留所有权利。
Future space telescopes with diameter over 20 m will require new approaches: either high-precision formation flying or in-orbit assembly. We believe the latter holds promise at a potentially lower cost and more practical solution in the near term, provided much of the assembly can be carried out autonomously. To gain experience, and to provide risk reduction, we propose a combined micro/nano-satellite demonstration mission that will focus on the required optical technology (adaptive mirrors, phase-sensitive detectors) and autonomous rendezvous and docking technology (inter-satellite links, relative position sensing, automated docking mechanisms). The mission will involve two "3U" CubeSat-like nanosatellites ("MirrorSats") each carrying an electrically actuated adaptive mirror, and each capable of autonomous un-docking and re-docking with a small central "15U" class micro/nano-satellite core, which houses two fixed mirrors and a boom-deployed focal plane assembly. All three spacecrafts will be launched as a single similar to 40 kg micro-satellite package. The spacecraft busses are based on heritage from Surrey's SNAP-1 and STRaND-1 missions (launched in 2000 and 2013 respectively), whilst the optics, imaging sensors and shape adjusting adaptive mirrors (with their associated adjustment mechanisms) are provided by CalTech/JPL The spacecraft busses provide precise orbit and attitude control, with inter-satellite links and optical navigation to mediate the docking process. The docking system itself is based on the electromagnetic docking system being developed at the Surrey Space Centre (SSC), together with rendezvous sensing technology developed for STRaND-2. On orbit, the mission profile will firstly establish the imaging capability of the compound spacecraft before undocking, and then autonomously re-docking a single MirrorSat. This will test the docking system, autonomous navigation and system identification technology. If successful, the next stage will see the two MirrorSat spacecraft undock and re-dock to the core spacecraft in a linear formation to represent a large (but sparse) aperture for high resolution imaging. The imaging of stars is the primary objective, but other celestial and terrestrial targets are being considered. Teams at CalTech and SSC are currently working on the mission planning and development of space hardware. The autonomous rendezvous and docking system is currently under test on a 2D air-bearing table at SSC, and the propulsion and precision attitude control system is currently in development. Launch is planned for 2016. This paper details the mission concept; technology involved and progress to date, focussing on the spacecraft buses. (C) 2015 IAA. Published by Elsevier Ltd. All rights reserved.