The Earth 2.0 (ET) mission is a Chinese next-generation space mission to detect thousands of Earth-sized terrestrial planets, including habitable Earth-like planets orbiting solar type stars (Earth 2.0s), cold low-mass planets, and freefloating planets. To meet the scientific goals, the ET spacecraft will carry six 30 cm diameter transit telescopes with each field of view of 500 square degrees, and one 35 cm diameter microlensing telescope with a field of view of 4 square degrees, monitor ~1.2M FGKM dwarfs in the original Kepler field and its neighboring fields continuously while monitoring over 30M stars in the Galactic bulge direction. The high precision transit observations require high photometry precision and pointing stability, which is the key drive for the ET spacecraft design. In this paper, details of the overall mission modeling and analysis will be presented. The spacecraft orbit, pointing strategy, stability requirements are presented, as well as the space-ground communication analysis. The ET spacecraft adopts an ultra-high photometry precision & high stable platform, largely inherited from other space science missions. The preliminary design of spacecraft which meets mission requirements is introduced, including the spacecraft overall configuration, observation modes, avionics architecture and development plan, which pays great attention to the pointing stability and huge volume science telemetry download.
The enhanced X-ray Timing and Polarimetry (eXTP) is an international cooperation flagship mission, equipped with four kinds of instruments, including 9 SFA (Spectroscopic Focusing Array) telescopes, 4 PFA (Polarimetry Focusing Array) telescopes, 6 WFM (Wide Field Monitor) cameras, and 40 LAD (Large Area Detector) modules. These payloads overall require about 11.5m2 for mounting on the same side of the satellite, with high alignment requirement between lines of sight of each instrument to guarantee the effective area and response performance of scientific payload, which is the most important driver for the satellite mechanical design. At the same time, the mirror assemblies and cameras of SFA and PFA telescopes are installed separately on the satellite, relying on the satellite structure to ensure the relative position accuracy. There are also factors such as payload field-of-view, sun shield, antenna accommodation, mechanical property to be taken care of in the satellite configuration design. According to the characteristics of payloads, an integrated configuration and structure design of eXTP satellite is proposed, with a high-rigid optical module providing large area for payload optics accommodation, a central cylinder as the primary force-taking structure of the satellite, a service module for platform equipment accommodation, and a detector module equipped with cameras of SFA and PFA. This paper introduces the mechanical design and analysis of eXTP satellite. The feasibility and performance of configuration and structure design are verified by simulation analysis.
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