Mayak family
Mayak family
| Mayak |
Mayak
|
DESCRIPTION Mayak rocket family design is based on installation of Yuzhnoye-developed RD815 engine on the first stages and technologies, derived from Zenit, Cyclone and Antares rockets. RD872 or RD835 engines are installed on the upper stages. ILV main stages use liquid oxygen and kerosene as propellants. The family consists of ILV of lightweight to superheavy capabilities, placing payloads into all kinds of near-Earth orbits, including GTO and GEO, as well as escape trajectories. Mayak family has both monoblock and modular configurations and features 3,9 m diameter Stage 1 with three RD815 engines. As an option, ILV can be upgraded to include the upper stage, as well as the fairing of the required size depending on the payload. Upper stage has a capability of multiple burns in flight. Yuzhnoye-developed RD809K, RD861K engines are considered for installation on the upper stages. |
DESCRIPTION
Mayak rocket family design is based on installation of Yuzhnoye-developed RD815 engine on the first stages and technologies, derived from Zenit, Cyclone and Antares rockets. RD872 or RD835 engines are installed on the upper stages. ILV main stages use liquid oxygen and kerosene as propellants.
The family consists of ILV of lightweight to superheavy capabilities, placing payloads into all kinds of near-Earth orbits, including GTO and GEO, as well as escape trajectories. Mayak family has both monoblock and modular configurations and features 3,9 m diameter Stage 1 with three RD815 engines.
As an option, ILV can be upgraded to include the upper stage, as well as the fairing of the required size depending on the payload. Upper stage has a capability of multiple burns in flight. Yuzhnoye-developed RD809K, RD861K engines are considered for installation on the upper stages.
Mayak-M3.9
Mayak-M3.9
heavy-lift
CLASS OF LAUNCH-VEHICLE
18.2 t
PL (Hcirc=200km, i=51,6˚)
| 65 m HEIGHT | 3.9 m DIAMETER |
526 t
MASS
Mayak-S3.9 ILV is a two-stage monoblock rocket 65 m long with 3.9 m body diameter. It is designed to orbit spacecraft into all kinds of near-earth orbits, including GTO.
Existing technologies and procedures, applied in development of Zenit, Cyclone and Antares rockets are involved as much as possible for development of this ILV and its complex, providing high level of reliability and manufacturing readiness, minimum development terms and reasonable expenses both for complex development and for its operation.
ILV development is based on the available or already developed engines, installations and units. Such approach permits to considerably reduce the expenses and ILV development time.
ILV structure is based on tanks and basic components of Zenit and Antares rockets and has diameter of 3900 mm, applied in batch production of Antares and Zenit family.
Stage 1 features three Yuzhnoye-developed RD815 engines, which burn liquid oxygen and kerosene as propellants.
Stage 2 features RD872 engine, which also uses liquid oxygen and kerosene as propellants. The engine is based on RD870 engine, which basic components manufacture has already been mastered by the PA Yuzhmash and is being manufactured for other engines.
FEATURES
| Mayak-M3.9 | |
| Stages | 2 |
| Dimensions, mm | |
| Height | 65000 |
| Body diameter | 3900 |
| Fairing diameter | 4200 |
| Gross mass (without payload), t | 526 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | LOX + kerosene |
| Engines: | |
| Stage 1 | 3×RD815 |
| Stage 2 | RD872 |
| Engine thrust, tf | |
| Stage 1 (sea level) | 753.96 |
| Stage 2 (vacuum) | 93 |
| Maximum payload mass to orbit, t | |
| Circular orbit (Нcirc = 200 km, i=51.6°) | 18.2 |
| Geostationary transfer orbit (Нp=190 km, Нa=35786 km, i=16.3) | 4.52 |
| Trajectory to the Moon | 6.3* |
Mayak-SH-3
Mayak-SH-3
super heavy-lift
CLASS OF LAUNCH-VEHICLE
59.3 t
PL (Hcirc=200km, i=51,6˚)
| 75 m HEIGHT | 3.9 m DIAMETER |
1387 t
MASS
FEATURES
| Mayak-SH-3 | |
| Stages | 2 |
| Dimensions, mm | |
| Height | 75000 |
| Body diameter | 3900 |
| Fairing diameter | 5100 |
| Gross mass (without payload), t | 1387 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | LOX + kerosene |
| Engines: | |
| Boosters | 6×RD815 |
| Stage 1 | 3×RD815 |
| Stage 2 | RD872 |
| Engine thrust, tf | |
| Stage 1 (sea level) | 2261.88 |
| Stage 2 (vacuum) | 93 |
| Maximum mass of payload to orbit, t | |
| Circular orbit (Нcirc=200 km, i=51.6°) | 59.3 |
| Trajectory to the Moon | 18.7* |
Mayak-SH-5
Mayak-SH-5
super heavy-lift
CLASS OF LAUNCH-VEHICLE
93.2 t
PL (Hcirc=200km, i=51,6˚)
| 80 m HEIGHT | 3.9 m DIAMETER |
2246 t
MASS
FEATURES
| Mayak-SH-5 | |
| Stages | 2 |
| Dimensions, mm | |
| Height | 80000 |
| Body diameter | 3900 |
| Fairing diameter | 6200 |
| Gross mass (without payload), t | 2246 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | LOX + kerosene |
| Engines: | |
| Boosters | 12×RD815 |
| Stage 1 | 3×RD815 |
| Stage 2 | RD872 |
| Engine thrust, tf | |
| Stage 1 (sea level) | 3769.8 |
| Stage 2 (vacuum) | 93 |
| Maximum payload mass to orbit, t | |
| Circular orbit (Нcirc=200 km, i=51.6°) | 93.2 |
| Trajectory to the Moon | 30.5* |
Mayak-SH-7
Mayak-SH-7
super heavy-lift
CLASS OF LAUNCH-VEHICLE
133 t
PL (Hcirc=200km, i=51,6˚)
| 79.9 m HEIGHT | 3.9 m DIAMETER |
3001 t
MASS
FEATURES
| Mayak-SH-7 | |
| Stages | 2 |
| Dimensions, mm | |
| Height | 79900 |
| Body diameter | 3900 |
| Fairing diameter | 6200 |
| Gross mass (without payload), t | 3001 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | LOX + kerosene |
| Engines: | |
| Boosters | 18×RD815 |
| Stage 1 | 3×RD815 |
| Stage 2 | RD872 |
| Engine thrust, tf | |
| Stage 1 (sea level) | 5277.72 |
| Stage 2 (vacuum) | 93 |
| Maximum payload mass to orbit, t | |
| Circular orbit (Нcirc=200 km, i=51.6°) | 133 |
| Trajectory to the Moon | 40* |
Mayak-M3.9
Mayak-M3.9
| heavy-lift CLASS OF LAUNCH-VEHICLE | 18.2 t PL (Hcirc=200km, i=51,6˚) |
| 65 m HEIGHT | 3.9 m DIAMETER | 526 t MASS |
DESCRIPTION
Mayak-S3.9 ILV is a two-stage monoblock rocket 65 m long with 3.9 m body diameter. It is designed to orbit spacecraft into all kinds of near-earth orbits, including GTO.
Existing technologies and procedures, applied in development of Zenit, Cyclone and Antares rockets are involved as much as possible for development of this ILV and its complex, providing high level of reliability and manufacturing readiness, minimum development terms and reasonable expenses both for complex development and for its operation.
ILV development is based on the available or already developed engines, installations and units. Such approach permits to considerably reduce the expenses and ILV development time.
ILV structure is based on tanks and basic components of Zenit and Antares rockets and has diameter of 3900 mm, applied in batch production of Antares and Zenit family.
Stage 1 features three Yuzhnoye-developed RD815 engines, which burn liquid oxygen and kerosene as propellants.
Stage 2 features RD872 engine, which also uses liquid oxygen and kerosene as propellants. The engine is based on RD870 engine, which basic components manufacture has already been mastered by the PA Yuzhmash and is being manufactured for other engines.
FEATURES
| Mayak-M3.9 | |
| Stages | 2 |
| Dimensions, mm | |
| Height | 65000 |
| Body diameter | 3900 |
| Fairing diameter | 4200 |
| Gross mass (without payload), t | 526 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | LOX + kerosene |
| Engines: | |
| Stage 1 | 3×RD815 |
| Stage 2 | RD872 |
| Engine thrust, tf | |
| Stage 1 (sea level) | 753.96 |
| Stage 2 (vacuum) | 93 |
| Maximum payload mass to orbit, t | |
| Circular orbit (Нcirc = 200 km, i=51.6°) | 18.2 |
| Geostationary transfer orbit (Нp=190 km, Нa=35786 km, i=16.3) | 4.52 |
| Trajectory to the Moon | 6.3* |
Mayak-SH-3
Mayak-SH-3
| super heavy-lift CLASS OF LAUNCH-VEHICLE | 59.3 t PL (Hcirc=200km, i=51,6˚) |
| 75 m HEIGHT | 3.9 m DIAMETER | 1387 t MASS |
FEATURES
| Mayak-SH-3 | |
| Stages | 2 |
| Dimensions, mm | |
| Height | 75000 |
| Body diameter | 3900 |
| Fairing diameter | 5100 |
| Gross mass (without payload), t | 1387 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | LOX + kerosene |
| Engines: | |
| Boosters | 6×RD815 |
| Stage 1 | 3×RD815 |
| Stage 2 | RD872 |
| Engine thrust, tf | |
| Stage 1 (sea level) | 2261.88 |
| Stage 2 (vacuum) | 93 |
| Maximum mass of payload to orbit, t | |
| Circular orbit (Нcirc=200 km, i=51.6°) | 59.3 |
| Trajectory to the Moon | 18.7* |
Mayak-SH-5
Mayak-SH-5
| super heavy-lift CLASS OF LAUNCH-VEHICLE | 93.2 t PL (Hcirc=200km, i=51,6˚) |
| 80 m HEIGHT | 3.9 m DIAMETER | 2246 t MASS |
FEATURES
| Mayak-SH-5 | |
| Stages | 2 |
| Dimensions, mm | |
| Height | 80000 |
| Body diameter | 3900 |
| Fairing diameter | 6200 |
| Gross mass (without payload), t | 2246 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | LOX + kerosene |
| Engines: | |
| Boosters | 12×RD815 |
| Stage 1 | 3×RD815 |
| Stage 2 | RD872 |
| Engine thrust, tf | |
| Stage 1 (sea level) | 3769.8 |
| Stage 2 (vacuum) | 93 |
| Maximum payload mass to orbit, t | |
| Circular orbit (Нcirc=200 km, i=51.6°) | 93.2 |
| Trajectory to the Moon | 30.5* |
Mayak-SH-7
Mayak-SH-7
| super heavy-lift CLASS OF LAUNCH-VEHICLE | 133 t PL (Hcirc=200km, i=51,6˚) |
| 79.9 m HEIGHT | 3.9 m DIAMETER | 3001 t MASS |
FEATURES
| Mayak-SH-7 | |
| Stages | 2 |
| Dimensions, mm | |
| Height | 79900 |
| Body diameter | 3900 |
| Fairing diameter | 6200 |
| Gross mass (without payload), t | 3001 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | LOX + kerosene |
| Engines: | |
| Boosters | 18×RD815 |
| Stage 1 | 3×RD815 |
| Stage 2 | RD872 |
| Engine thrust, tf | |
| Stage 1 (sea level) | 5277.72 |
| Stage 2 (vacuum) | 93 |
| Maximum payload mass to orbit, t | |
| Circular orbit (Нcirc=200 km, i=51.6°) | 133 |
| Trajectory to the Moon | 40* |