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Conceptual design for a Mercury relativity satelliteIt was shown earlier that 1 x 10 to the -14th Doppler data and 3 cm accuracy range measurements to a small Mercury Relativity Satellite in a polar orbit with four-hour period can give high-accuracy tests of gravitational theory. A particular conceptual design has been developed for such a satellite, which would take less than 10 percent of the approach mass for a possible future Mercury Orbiter Mission. The spacecraft is similar to the Pioneer Venus Orbiter, but scaled down by about a factor four in linear dimensions. A despun antenna 30 cm in diameter is used for tracking. The transmitted power is roughly 0.2 watts at K-band and 0.5 watts at X-band. The orbit parameters for individual eight-hour arcs and the gravity field of Mercury through degree and order 10 are determined mainly from the Doppler data. A 50 MHz K-band sidetone system provides the basic ranging accuracy. The spacecraft mass is 50 kg or less.
Document ID
19900028360
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Bender, P. L.
(Joint Institute for Laboratory Astrophysics Boulder, CO, United States)
Ashby, N.
(Joint Inst. for Lab. Astrophysics Boulder, CO, United States)
Wahr, J. M.
(Joint Institute for Laboratory Astrophysics; Colorado, University Boulder, United States)
Vincent, M. A.
(JPL, Pasadena, CA; Joint Institute for Laboratory Astrophysics, Boulder CO, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Publication Information
Publication: Advances in Space Research
Volume: 9
Issue: 9 19
ISSN: 0273-1177
Subject Category
Astronautics (General)
Accession Number
90A15415
Funding Number(s)
CONTRACT_GRANT: NAGW-822
CONTRACT_GRANT: NSG-7637
Distribution Limits
Public
Copyright
Other

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