AAS 204th Meeting, June 2004
Session 11 Instrumentation, Space Missions
Poster, Monday, May 31, 2004, 9:20am-6:30pm, Ballroom

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[11.07] KEPLER Mission Spacecraft Concept Description

W.D. Deininger, D.D. Miller, A.C. Harvey (Ball Aerospace & Technologies Corp.)

The Kepler Discovery Mission has been developed to monitor a large star field for four years and directly detect Earth-like planets through differential photometry. The mission is launched on a Delta II and flies in a heliocentric orbit. The 903-Kg flight segment consists of a CCD-based photometer instrument and a spacecraft bus. The spacecraft bus is at the base of the flight segment and provides structural support to the photometer. The spacecraft is 3-axis-stablized and uses fine guidance sensors to provide accurate pointing throughout the mission to better than 18.4 arcsec. Reaction wheels are used for attitude adjustments with a cold-gas reaction control system for wheel desaturations. Spacecraft thermal control is largely passive with some active heaters. The spacecraft avionics is based on redundant RAD 750 computers with a throughput of 119 MIPS. The power system produces 812 W EOL using a fixed solar array with a direct energy transfer architecture. Primary data downlink is via a Ka-band HGA to the DSN 34-m antennas.

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