Tsyklon

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Based on the R36 SS-9 Scarp ICBM, the 2-stage 8K69 was introduced in Sep-1966 as the launcher for the FOBS Fractional Bombardment System and then in 1967 as the Tsyklon 2 11K67 SL-11 as a space launcher (replaced in 1969 by the 11K69). It has operated in recent years exclusively as an ocean surveillance satellite carrier. A third stage was added to create the Tsyklon 3 11K68 SL-14/F-2 in 1977, which took over from Vostok for Meteor and elint launches.


TSYKLON FAMILY RECORD
First launch: 17-Sep-1966
Number launched: 240 to end-1995, 232 reaching orbit
Launch sites: Tyuratam, Plesetsk
Vehicle success rate: 95.42% to end-1995



TSYKLON 2 SL-11/F-1 SPECIFICATIONS

Tsyklon 2 has recently been employed for the ocean surveillance program but initially flew in the Fractional Orbit Bombardment System (FOBS) and satellite interceptor programs. FOBS versions are conventionally referred to as F-1-r vehicles, the 'r' designating the retro-stage that is actually part of the payload. Similarly, the interceptor and ocean reconnaissance programs involve the F-1-m, the 'm' indicating a payload maneuvering capability.
First launch: 17-Sep-1966
Number launched: 126 to end-1995
Launch sites: Tyuratam
Principal uses: radar/elint ocean surveillance satellites
Vehicle success rate: 95.24% to end-1995
Performance: 3,000 kg into 65o LEO
Number of stages: 2 (stage 1: 11S691; stage 2: 11S692)
Overall length: 35.0 m
Launch mass: 179,000 kg + payload
Stage 1/2 propellants: 121,700 kg nitrogen tetroxide + 48,500 kg UDMH
Other specifications as for Tsyklon 3


TSYKLON 3 SL-14/F-2 SPECIFICATIONS

Tsyklon 3 is the 3-stage version and was first offered as the commercial Tsyklon launcher in Oct-1987. It supports a range of medium military and civil missions but its single most numerous payloads are elint spacecraft.
First launch: 24-Sep-1977
Number launched: 114 to end-1995
Launch sites: Plesetsk
Principal uses: elint, Meteor, oceanographic, geodetic, remote sensing
Vehicle success rate: 95.61% to end-1995
Performance: 3,250 kg into 400 x 400 km 82.5o LEO
Cost: $10 million quoted in 1989
Number of stages: 3
Overall length: 39.27 m
Principal diameter: 3.00 m
Launch mass: 185,500 kg + payload
Launch thrust: 2,747 kN sea level
Guidance: inertial

TSYKLON 3 SL-14/F-2 STAGE 1
Engines: six chambers of RD-218 single engine from NPO Energomash and four gimbaled NPO Yuzhnoye verniers for steering
Length: 19.38 m
Diameter: 3.00 m
Dry mass: 6,320 kg
Oxidizer: nitrogen tetroxide
Fuel: UDMH
Propellant mass: 120,700 kg
Thrust: 2,451 kN SL (2,745 kN vac); verniers 296 kN SL (334 kN vac)
Burn time: 120 s

TSYKLON 3 SL-14/F-2 STAGE 2
Conflicting information has been released concerning stage 2. The RD-219 has been quoted as powering stage 2 but performance characteristics are incompatible. Possibly the RD-219 is employed on Tsyklon 2 and a different engine on Tsyklon 3.
Engines: NPO Energomash RD-219 derivative?, with two fixed chambers and four gimbaled NPO Yuzhnoye verniers for steering (the verniers might not be carried on Tysklon 2)
Length: 10.9 m
Diameter: 3.00 m
Dry mass: 3,460 kg
Oxidizer: nitrogen tetroxide
Fuel: UDMH
Propellant mass: 49,800 kg
Thrust: 956 kN vac
Burn time: 158 s

TSYKLON 3 SL-14/F-2 STAGE 3
Designation: S5M
Engines: NPO Yuzhnoye 11D25 single restart
Length: 2.58 m
Diameter: 2.25 m
Dry mass: 1,407 kg
Oxidizer: nitrogen tetroxide
Fuel: UDMH
Propellant mass: 3,200 kg
Thrust: 78.90 kN vac main
Burn time: 125 s in two burns (dual burn used for orbits >250 km)
Attitude control: 3-axis control during burns by eight fixed nozzles (6 x 20 N + 2 x 98 N) fed by main engine gas generator. 3-axis coast control by 10 thrusters of separate system



NPO ENERGOMASH / RD-218
Designation: 11D69
Configuration: three 2-chamber engines + four gimbaled verniers for steering
Application: SL-11/14 stage 1
First flown: 1966
Dry mass: 1,718 kg
Length: 1.76 m
Maximum diameter: 0.74 m
Engine cycle: open
Oxidizer: nitrogen tetroxide
Fuel: UDMH
Mixture ratio: 2.6
Feed method: single turbopump
Thrust: 2,451 kN SL, 2,745 kN vac (2,970 kN vac has also been quoted)
Specific impulse: 309 s
Expansion ratio: 14.7:1
Combustion chamber pressure: 82.2 atm
Burn time: 120 s

NPO ENERGOMASH / RD-219
Designation: 11D26
Configuration: two fixed chambers
Application: SS-9 Scarp stage 2; Tsyklon stage 2?
First orbital launch: Jun 1977?
Dry mass: 665 kg
Engine cycle: open
Oxidizer: nitric acid
Fuel: UDMH
Feed method: single turbopump feeding two fixed chambers
Thrust: 833 kN vac
Specific impulse: 293 s vac
Combustion chamber pressure: 75 atm
Burn time: 125 s

NPO ENERGOMASH / TSYKLON STAGE 2
It had been assumed that RD-219 powered Tsyklon's second stage but it now appears that a derivative is employed
Configuration: two fixed chambers + four gimbaled verniers for steering (the verniers might not be carried on SL-11)
Application: SL-11/14 stage 2
First flown: 1966
Dry mass: 690 kg
Engine cycle: open
Oxidizer: nitrogen tetroxide
Fuel: UDMH
Mixture ratio: 2.6
Feed method: turbopump
Thrust: 956 kN vac (990 kN vac has also been quoted)
Specific impulse: 324 s
Expansion ratio: 46.1:1
Combustion chamber pressure: 88.0 atm
Burn time: 160 s

NPO YUZHNOYE / 11D25
Configuration: fixed main chamber with 6 x 20 N + 2 x 98 N thrusters for steering
Application: SL-14 stage 3
First flown: Jun-1977
Dry mass: 123 kg
Length: 1.555 m
Maximum diameter: 0.795 m
Cycle: open, with pump turbine exhaust routed to steering thrusters
Oxidizer: nitrogen tetroxide
Fuel: UDMH
Thrust: 78.90 kN vac main chamber
Mixture ratio: 2.1 main, 1.6 thrusters
Specific impulse: 317 s vac main; 230 s vac thrusters
Expansion ratio: 111.2:1 main
Combustion chamber pressure: 90.5 atm main
Burn time: 118 s


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