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The requirement for Tsiklon, the first prototype Soviet navigation satellite system, was identified in the late 1950's in order to provide Soviet ballistic missile submarines with accurate position fixes so that acceptable submarine-launched ballistic missile accuracy could be achieved. The draft project was approved in 1962, but development was prolonged due to very poor accuracy due to software problems and lack of accurate geodetic data. The system was finally accepted for service as an interim measure in 1972 pending deployment of the improved Tsiklon-B/Parus system. Tsiklon was designed by Reshetnev; the navigation and control system was by NII Radiopribor (Ivanov, Chief Designer, L I Gusev, Director); with communications systems by MNIIRS MPSS (Nesvist). The Kosmos-3M launch vehicle was used. The TTZ specification was completed by the TsYKOS MO (Space Forces) and the VMF (Soviet Navy). In 1962 research institute NII-695 completed the draft project for a Tsiklon experimental satellite. It was to use the Doppler navigation method and be placed in 800 to 1000 km altitude orbits. Development of the satellite was given to Reshetnev and experimental flights began in 1967 in order to develop a system meeting the required tactical and operational characteristics. The shipboard installation consisted of the Tsunami system, composed of the Sirius radio station, the Signal antenna stabilization platform, the Konus-4 omnidirectional antenna, and the Kvant-L antenna. First trial were conducted with a Project 680 vessel of the Black Sea fleet and showed a position error of 3 km, which was intolerable. A large part of the problem was with inaccuracies in the software models available for predicting the spacecraft ephemeredes. Work by the KIK Center resulted in a 10 to 30 times improvement in this accuracy, incorporating new information on the gravitational anomalies and geoid of the earth. Use of the revised software in 1969 showed an average error of 100 m over a five day period. Further improvement required a better mapping of the earth's gravitational anomalies. Testing of Tsiklon would continue through 1972 before an adequate operational system could be designed and the system was accepted for military service. The Parus/Tsiklon-B production system began flight tests in 1974. Tsiklon 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 center). Typical orbit: 965 km x 1009 km at 83 degrees inclination. 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). Electrical System: Solar cells on exterior. Electric System: 0.20 average kW. Associated Launch Vehicle: Kosmos 11K65M. Tsiklon Chronology
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