LISA orbit selection and stability

Details LISA orbit selection and stability LISA orbit selection and stability

Oct 2001

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2001cqgra..18.4053f&link_type=abstract

Classical and Quantum Gravity, Volume 18, Issue 19, pp. 4053-4057 (2001).

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Scientific paper

The LISA mission involves three spacecraft separated by 5×106 km. Each spacecraft needs to be able to point at the other spacecraft in order to transmit and receive laser signals to each other. The initial beam acquisition process is dependent on the pointing accuracy of the spacecraft, the laser beam width and the knowledge of the directions to the other spacecraft. The directions from one spacecraft to another will be determined by tracking radio signals from each spacecraft independently by Earth tracking stations. An analysis of the position determination estimation is described here. Using conventional Doppler and range information, the relative angular positions of each spacecraft can be determined to better than 1 µrad (0.2 arcsec), which is less than the laser beamwidth.

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