Conceptual design for a mercury relativity satellite

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Conceptual design for a mercury relativity satellite

Bender, P.L. / Ashby, N. / Vincent, M.A. / Wahr, J.M.

Abstract It was shown earlier that 1 × 10⁻¹⁴ Doppler data and 3 cm accuracy range measurements to a small Mercury Relativity Satellite in a polar orbit with 4-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% 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 4 in linear dimensions. The cylindrical surface of the spin-stabilized spacecraft is highly reflecting to minimize thermal input from the sun. 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.