Cyclone family
Cyclone family
Cyclone-1
lightweight
CLASS OF LAUNCH-VEHICLE
1.5 t
PL (Hcirc=200km, i=51,6˚)
| 30 m HEIGHT | 2.25 m DIAMETER |
65 t
MASS
Cyclone-1
lightweight
CLASS OF LAUNCH-VEHICLE
1.5 t
PL (Hcirc=200km, i=51,6˚)
30 m
HEIGHT
2.25 m
DIAMETER
65 t
MASS
DESCRIPTION
Cyclone-1 launch vehicle is a lightweight liquid-propellant rocket, designed to place payloads into the low near-earth orbits, including sun-synchronous one.
ILV Stage 1 is equipped with Yuzhnoye-developed RD870 engine, which burns liquid oxygen and kerosene as propellants. PA Yuzhmash has already developed production capabilities for the basic components of this engine and they have been manufactured for installation in other engines.
Stage 2 is equipped with RD809K engine, which is also Yuzhnoye-developed and burns liquid oxygen and kerosene as propellants.
Upper stage is equipped with RD840 engine, powered by storable propellants NT+UDMH.
Basis of this ILV development is the use of composite materials for manufacturing of the Stages’ basic core elements, including tanks for cryogenic propellants, as well as maximization of additive technologies in manufacturing of main engines to be installed on the Stage.
DESCRIPTION
Cyclone-1 launch vehicle is a lightweight liquid-propellant rocket, designed to place payloads into the low near-earth orbits, including sun-synchronous one.
ILV Stage 1 is equipped with Yuzhnoye-developed RD870 engine, which burns liquid oxygen and kerosene as propellants. PA Yuzhmash has already developed production capabilities for the basic components of this engine and they have been manufactured for installation in other engines.
Stage 2 is equipped with RD809K engine, which is also Yuzhnoye-developed and burns liquid oxygen and kerosene as propellants.
Upper stage is equipped with RD840 engine, powered by storable propellants NT+UDMH.
Basis of this ILV development is the use of composite materials for manufacturing of the Stages’ basic core elements, including tanks for cryogenic propellants, as well as maximization of additive technologies in manufacturing of main engines to be installed on the Stage.
FEATURES
| Cyclone-1 | |
| Stages | 3 |
| Dimensions, mm | |
| Height | 30000 |
| Body diameter | 2250 |
| Fairing diameter | 2250 |
| Launching mass (without payload), t | 65 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | LOX + kerosene |
| Upper stage | NT + UDMH |
| Engines: | |
| Stage 1 | RD870 |
| Stage 2 | RD809К |
| Upper stage | RD840 |
| Engine thrust, tonf | |
| Stage 1 (sea level) | 79,75 |
| Stage 2 (vacuum) | 10 |
| Upper stage (vacuum) | 0,04 |
| Maximum payload mass to orbit, t | |
| Circular orbit (Нcirc=200 km, i=51,6°) | 1,5 |
| Sun-synchronous orbit (Нcirc=700 km, i=98,16°) | 1,05 |
FEATURES
| Cyclone-1 | |
| Stages | 3 |
| Dimensions, mm | |
| Height | 30000 |
| Body diameter | 2250 |
| Fairing diameter | 2250 |
| Gross mass (without payload), t | 65 |
| Propellants | |
| Stage 1 | LOX + kerosene |
| Stage 2 | LOX + kerosene |
| Upper stage | NT + UDMH |
| Engines: | |
| Stage 1 | RD870 |
| Stage 2 | RD809К |
| Upper stage | RD840 |
| Engine thrust, tonf | |
| Stage 1 (sea level) | 79,75 |
| Stage 2 (vacuum) | 10 |
| Upper stage (vacuum) | 0,04 |
| Maximum payload mass to orbit, t | |
| Circular orbit (Нcirc=200 km, i=51,6°) | 1,5 |
| Sun-synchronous orbit (Нcirc=700 km, i=98,16°) | 1,05 |