| Sfera | ||
The Sfera geodetic system covered a broad development for solving problems in geodetics, continental drift, and precise location of cartographic points. The spacecraft was equipped with measurement and signaling apparatus, providing assistance in measuring astronomical-geodetic points of military topographical research for the Red Army General Staff. The satellite allowed improved accuracy for long range weapons. Reshetnev was the Chief Designer. Flight tests were from 1968 to 1972, and the system was accepted for military service in 1973. Series flights were from 1973 to 1980. The Kosmos 3M launcher was used. Colonel Ye S Shchapov was in charge of Sfera development. Sfera used the basic KAUR-1 bus, consisting of a 2.035 m diameter cylindrical spacecraft body, with solar cells and radiators of the thermostatic temperature regulating system mounted on the exterior. Orientation was by a single-axis magneto-gravitational (gravity gradient boom) passive system. The hermetically sealed compartment had the equipment mounted in cruciform bays, with the chemical batteries protecting the radio and guidance equipment mounted at the centre. Typical orbit: 980 km or 1200 km, 74 deg; also 69 deg, 83 deg. Length: 3.00 m (9.80 ft). Maximum Diameter: 2.04 m (6.68 ft). Span: 2.04 m (6.68 ft). Mass: 800 kg (1,760 lb). Associated Launch Vehicle: Kosmos 11K65M. Sfera Chronology
Bibliography and Further Reading
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