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The Zenit-3SLB is further development of the Zenit family launch vehicles. It is the modified Zenti-3SL ILV from the Sea Launch project adapted for launch from the Baikonur cosmodrome. ILV has a three-stage configuration with tandem stage arrangement. Ecologically safe components, namely liquid oxygen and kerosene are used as the main propellant components.
The main feature of the Zenit-3SLB ILV relative to the Sea Launch project ILC is the replacement of the encapsulated payload unit developed by the Boeing company by the ascent unit formed during sequential mating in the clean room to Block DM-SLB developed by S.P. Korolev RSC Energia of spacecraft and payload fairing developed by NPO after S.A. Lavochkin.
Main Characteristics of the Zenit-3SLB ILV
| Factor name |
Value
|
| Launching mass of the Integrated Launch Vehicle (when injecting PL of 3.6 t mass), t |
~ 466,25
|
Payload mass (including SC installation and separation facilities), kg:
- during injection into geo-transfer orbit
with shortage of velocity to GEO equal to 1500 m/s
- during injection into geo-stationary orbit
- during injection into circular orbit
(Эcir.=10000 km and i=51,4°)
|
up to 3600
up to 1600
up to 4830
|
Propellant components used:
|
liquid
oxygen
naphthyl
|
| Number of stages |
2 + Block DM-SLB
|
Engines used in ILV:
- LV stage I unit
- LV stage II unit:
- main
- steering
- Upper Stage DM-SLB
|
1 engine
аФ-171
1 engine
аФ-120
1 engine
аФ-8
1 engine
11Ф58Ь
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Integrated launch vehicle length, m
including:
- the Zenit-2S launch vehicle length, m
- the Zenit-2S launch vehicle diameter, m
- ascent unit length, m
- ascent unit diameter, m
|
58
43,3
3,9
15,3
4,1
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