Zenit 3SL

 

 Architecture
 
 First Stage
 
 Designation:
 Manufacturer:
 Length:
 Diameter:
 Gross Mass:
 Structure:
 Propellant Mass:
 Propellant:
 Primary Propulsion:
  Stage Thrust:
 Pitch/Yaw Control:
 Roll Control:
 Nominal Burn Time:
 Stage Shutdown:
 Stage Separation:

Zenit Stage 1
NPO Yuzhnoye
32.9 m
3.9 m
353,870 kg
Aluminium wafer
325,401 kg
LOx/Kerosene
1 x RD-171
3,468 kN (SL)
Gimbal nozzles (+/-5°)
Gimbal nozzles (+/-5°)
143 sec.
Commanded
Solid separation motors
   Propulsion System

 Engine Designation:
 Manufacturer:
 Type:

 Thrust:
 Throttlability:
 Chamber Pressure:
 Specific Impulse:
 Mixture Ratio:
 Restartability:
 Expansion Ratio:

RD-171
NPO EnergoMash
Staged combustion
4 chambers/1 turbopump
3,468 kN (SL)
49%-102%
245 bar
309 sec. (SL)
2.63
No
37:1
 
 Second Stage
 
 Designation:
 Manufacturer:
 Length:
 Diameter:
 Gross Mass:
 Structure:
 Propellant Mass:
 Propellant:
 Primary Propulsion:
 Auxilliary Propulsion:
 Stage Thrust:
 Pitch/Yaw Control:
 Roll Control:
 Nominal Burn Time:
 Stage Shutdown:
 Stage Separation:

Zenit Stage 2
NPO Yuzhnoye
10.4 m
3.9 m
92,473 kg
Aluminium wafer
81,854 kg
LOx/Kerosene
1 x RD-120
RD-8 vernier engine
912 kN + 78 kN (vac)
Vernier engine
Vernier engine
293 sec.
Commanded
Solid separation motors
   Propulsion System
 Engine Designation:
 Manufacturer:
 Type:
 Thrust:
 Throttlability:
 Chamber Pressure:
 Specific Impulse:
 Mixture Ratio:
 Restartability:
 Expansion Ratio:

RD-120
NPO EnergoMash
Staged combustion
912 kN (vac)
85%-100%
163 bar
350 sec. (vac)
2.58
No
106:1
 
 Third Stage
 
 Designation:
 Manufacturer:
 Length:
 Diameter:
 Gross Mass:
 Structure:
 Propellant Mass:
 Propellant:
 Primary Propulsion:
 Stage Thrust:
 Pitch/Yaw Control:
 Roll Control:
 Nominal Burn Time:
 Stage Shutdown:
 Stage Separation:

Block DM-SL
RKK Energiya
5.6 m
3.7 m
18,600 kg
Aluminium skin-stringer
14,600 kg
LOx/Kerosene
11D58M
78 kN (vac)
Attitude control/Ullage motors
Attitude control/Ullage motors
642 sec.
Commanded
Spring ejection
   Propulsion System
 Engine Designation:
 Manufacturer:
 Type:
 Thrust:
 Throttlability:
 Chamber Pressure:
 Specific Impulse:
 Mixture Ratio:
 Restartability:
 Expansion Ratio:

11D58M
RKK Energiya
Staged combustion
78 kN (vac)
No
77.5 bar
361.0 sec. (vac)
2.53
Up to 5 starts
189:1
           
   Avionics
   Digital flight control system and inertial guidance system apparently unmodified from standard Zenit 2 launcher.

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