Lightweight tandem launch vehicle
The Dnepr launch vehicle is used for efficient and highly accurate injection of a single or multiple spacecraft into 300-900 km orbits inclined at 50.5°, 64.5°, 87.3°, 98°.
The launch vehicle burns hypergolic storable liquid propellants. Using multiple burns of the upper stage propulsion, the vehicle can loft satellites into orbits of various altitudes.
The Dnepr is operated from the Baikonur Cosmodrome and the Yasny launch base. The launch system can provide a launch rate of 25 launches per year.
Before payload unit integration, the launch vehicle placed into the launch silo and filled with propellants can remain in the silo for an unlimited time within its service life. Spacecraft (payload unit) replacement does not require launch vehicle detanking or removal from the silo.
The Dnepr launch services provider is International Space Company Kosmotras (Ukraine, Russia).
The Dnepr is based on the most powerful intercontinental ballistic missile in the world, RS-20, or SS-18 (Satan), having a high payload capability and reliability proven by 160 launches. The first Dnepr was launched on April 21, 1999. 22 launches were made, 21 of them successful.
Basic Specifications
|
Number of stages |
3 |
|
Dimensions, mm Length Stage diameter Fairing diameter |
34300 3000 3000 |
|
Launch mass, tons |
211 |
|
Propellants Oxidizer Fuel |
NTO UDMH |
|
Thrust, ton-force Stage 1 Stage 2 Stage 3 |
461,2 77,5 2,0 / 0,8 |
|
Maximum payload capability into circular orbits, tons |
3,2 |
|
Circular orbit injection accuracy (Нc=300 km) Altitude, km Inclination, deg |
±4,0 ±0,4 |
|
Maximum g-load |
7,8 |
|
Payload fairing cleanliness class (FED STD 209E) |
100 000 |
Dnepr Payload Capability into Circular Orbit
Payload Accommodation Area
Maximum payload unit extension ~ 2500 mm
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