Antares
Antares
Antares
medium-lift
CLASS OF LAUNCH-VEHICLE
8,1 t
PL (Нp=200km, Нa=300km, i=51.6˚)
| 42,5 m HEIGHT | 3.9 m DIAMETER |
330 t
MASS
Antares
medium-lift
CLASS OF LAUNCH-VEHICLE
8.1 t
PL (Нp=200km, Нa=300km, i=51.6˚)
42.5 m
HEIGHT
3.9 m
DIAMETER
330 t
MASS
DESCRIPTION
Orbital Sciences Corporation and Yuzhnoye have developed the Antares medium-lift launch vehicle to deliver payloads to the International Space Station. The Antares launch vehicle comprises two tandem stages 3.9 m in diameter.
Antares is a two-stage rocket. Core structure of the Antares’ Stage 1 was developed and produced by Ukraine’s Yuzhnoye State Design Office and Yuzhmash Machine Building plant in cooperation with Ukraine’s Hartron-Arkos (Kharkiv), Hartron-Ucom (Zaporizhzhya), Chezara, Rapid (Chernihiv) and Kievprylad (Kyiv) etc. as ordered by the US corporation Northrop Grumman.
Antares pre-launch processing, testing and launch were supported by the specialists from Yuzhnoye State Design Office, Yuzhmash Machine Building plant and Hartron-Arkos. Real-time launch technical support, acquisition and processing of the telemetry information were provided and as a result, Ukrainian specialists have provided full scope of services in the area of their responsibility.
DESCRIPTION
Orbital Sciences Corporation and Yuzhnoye have developed the Antares medium-lift launch vehicle to deliver payloads to the International Space Station. The Antares launch vehicle comprises two tandem stages 3.9 m in diameter.
Antares is a two-stage rocket. Core structure of the Antares’ Stage 1 was developed and produced by Ukraine’s Yuzhnoye State Design Office and Yuzhmash Machine Building plant in cooperation with Ukraine’s Hartron-Arkos (Kharkiv), Hartron-Ucom (Zaporizhzhya), Chezara, Rapid (Chernihiv) and Kievprylad (Kyiv) etc. as ordered by the US corporation Northrop Grumman.
Antares pre-launch processing, testing and launch were supported by the specialists from Yuzhnoye State Design Office, Yuzhmash Machine Building plant and Hartron-Arkos. Real-time launch technical support, acquisition and processing of the telemetry information were provided and as a result, Ukrainian specialists have provided full scope of services in the area of their responsibility.
FEATURES
| Antares | |
| Stages | 2 |
| Dimensions, mm | |
| Height | 42500 |
| Body diameter | 3900 |
| Fairing diameter | 3900 |
| Gross mass (without payload), t | 330 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | HTPB |
| Engines: | |
| Stage 1 | 2×RD-181 |
| Stage 2 | Castor-30XL |
| Engine thrust, tf | |
| Stage 1 (sea level) | 392 |
| Stage 2 (vacuum) | 48.7 |
| Maximum payload mass to orbit, t | |
| Нp=200 км, Нa=300 km, i=51.6° | 8.1 |
FEATURES
| Antares | |
| Stages | 2 |
| Dimensions, mm | |
| Height | 42500 |
| Body diameter | 3900 |
| Fairing diameter | 3900 |
| Gross mass (without payload), t | 330 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | HTPB |
| Engines: | |
| Stage 1 | 2×RD-181 |
| Stage 2 | Castor-30XL |
| Engine thrust, tf | |
| Stage 1 (sea level) | 392 |
| Stage 2 (vacuum) | 48.7 |
| Maximum payload mass to orbit, t | |
| Нp=200 км, Нa=300 km, i=51.6° | 8.1 |