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A satellite intended to travel in a constellation of satellites in an area of space in which the dominant disturbing forces and torques are for the most part caused by differential solar pressure between the satellites of the constellation comprises a satellite structure and a sunshield to prevent a

A satellite intended to travel in a constellation of satellites in an area of space in which the dominant disturbing forces and torques are for the most part caused by differential solar pressure between the satellites of the constellation comprises a satellite structure and a sunshield to prevent at least a portion of the satellite structure from being illuminated by solar rays. The reflectivity of the reflective surfaces of the sunshield is adjusted as a function of the angle of incidence of the solar rays.

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There is claimed: 1. A satellite intended to travel in a constellation of satellites in an area of space in which the dominant disturbing forces and torques are for the most part caused by differential solar pressure between said satellites of said constellation, said satellite comprising a satelli

There is claimed: 1. A satellite intended to travel in a constellation of satellites in an area of space in which the dominant disturbing forces and torques are for the most part caused by differential solar pressure between said satellites of said constellation, said satellite comprising a satellite structure, a sunshield having reflective surfaces and adapted to prevent at least a portion of said satellite structure from being illuminated by solar rays, and reflectivity adjustment means for adjusting the reflectivity of said reflective surfaces of said sunshield as a function of the angle of incidence of said solar rays, wherein said reflective surfaces and said reflectivity adjustment means are disposed on the shield symmetrically at four points relative to a center of thrust of the shield. 2. The satellite according to claim 1, wherein said means for adjusting the reflectivity of said reflective surfaces of said sunshield equalize the solar pressure/satellite mass ratio for each satellite. 3. The satellite according to claim 1, wherein said reflective surfaces the reflectivity whereof is adjusted by said adjustment means are arranged symmetrically with respect to a center of thrust of said satellite to enable control about three axes of said satellite. 4. The satellite according to claim 1, wherein said means for adjusting the reflectivity of said reflective surfaces of said sunshield as a function of said angle of incidence of said solar rays comprise variable reflectivity films the variation whereof is controlled electrically. 5. The satellite according to claim 1, wherein said reflectivity adjustment means comprise Maltese cross shaped devices. 6. The satellite according to claim 1, wherein said reflectivity adjustment means are arranged and selected to vary said reflectivity from 0.3 to 0.8.