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Tsiklon-4

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Tsyklon 4

AKA: Cyclone 4;F-3. Status: Design 2005. Payload: 4,900 kg (10,800 lb). Gross mass: 198,250 kg (437,060 lb). Height: 39.95 m (131.06 ft). Diameter: 3.00 m (9.80 ft). Apogee: 400 km (240 mi).

The Tsyklon 4 / Cyclone-4 launch vehicle was designed for operational and highly accurate lofting of single or multiple of satellites into earth orbit (including geostationary and sun-synchronous orbits). Cyclone-4 would be the most powerful rocket among the launchers of the Cyclone family. These rockets began operation in 1969 and proved to be the most reliable launchers in the world. The Cyclone-4 LV met all modern requirements for spacecraft launchers. It would be a three-stage rocket derived from the existing Cyclone-3 vehicle. The first two stages were taken from the Cyclone-3 launcher with a minimum level of necessary upgrade, with the proven production technology maintained to the maximum level. Enhancement of the technical and operational characteristics of Cyclone-4 were improved with the following changes:

• application of a new third stage having a higher reserve of propellants and a new engine with multiple ignition capability;
• use of new, modern control system, flight safety system, and telemetry system;
• use of a new and bigger payload fairing;
• separate assembly of the payload in the sealed fairing, allowing maintenance of the required level of cleanliness in the satellite area bellow the nose fairing;
• all stages were fuelled from the base of the first stage on the launch pad;
• capability to provide thermal safing of the interstage fairing space by applying high-pressure air in the event of an aborted launch.

The vehicle could place a payload of 5250 kg into low earth orbit (185 km / 51.5 deg). Vacuum thrust of stages 1, 2, and 3 were 303, 101.5, and 7.8 metric tons respectively. All stages used N2O4/UDMH propellants, with the stage specific impulses being 300.4, 314, and 325. Maximum G-load was 6.8 G's, and injection accuracy into a 500 km circular orbit was within 5 km of altitude and 0.05 degrees of inclination.

LEO Payload: 4,900 kg (10,800 lb) to a 400 km orbit at 51.60 degrees. Payload: 500 kg (1,100 lb) to a GEO.