Engineering topics
Publications and source records attributed to Vincent, M. A..
In December 2000, it was decided to update the solar cycle/ Mars atmosphere model coded in the software used to do the orbit lifetime aspects of Planetary Protection analysis.
The general problem of determining footprint overlap for instruments on different platforms was analyzed by determining the formation flying and pointing requirements needed to satisfy the science requirements of the CloudSat and Picasso-CENA missions.
The Laser Interferometer Space Antenna is a space mission designed to detect gravitational waves in the frequency range from below 0.0001 Hz to 1 Hz by measuring changes in the distance between spacecraft separated by several million kilometers.
Translocation studies of Lageos laser range data from Quincy and Monument Peak in California observed during 1984-1987 suggest that plate tectonic motion across the San Andreas fault system in the direction of the baseline between the two stations is uniform at a rate of -30(+ or - 3) mm/yr. Changes in the components of the baseline vector were inferred from repeat determinations using the solutions from successive 0.5-year intervals. The changes in the vertical and transverse components of the Quincy-Monument Peak baseline are -0.4(+ or - 5) mm/yr and +14(+ or -5) mm/yr, respectively. The vertical component determinations attest to the height stability of the laser ranging method. Lageos measurements made from Quincy and Monument Peak before 1984 are inaccurate enough to limit their usefulness for plate tectonic studies.
It 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.