FIELD: space engineering; designing and development of artificial satellites injected into elliptical orbits at altitudes of 200 to 700 km. SUBSTANCE: overall dimensions, mass and aerodynamic characteristics of satellite are selected depending on perigee altitude and initial eccentricity of working orbit more than 0.02 and preset satellite existence time. These characteristics ensure ballistic coefficient of satellite whose upper bound is found from special relationship. Relative maximum permissible random deviations of drag coefficient and mass of satellite which take place due to technological errors are introduced into this relationship. EFFECT: extended operational capabilities due to avoidance of premature recovery from working orbit because of atmospheric braking. 1 dwg, 2 tbl
