Fig. 4
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Sunlight-avoidance area and Sun-vector locus per orbit with respect to the azimuth and elevation. The sunlight-avoidance areas for the two laser axes of each spacecraft are depicted as gray circles. Equation (37) indicates that the Sun-vector locus per orbit has azimuth and elevation amplitudes of nearly π/9 and π/3, respectively. The angle Q drifts by 2π over one year.
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