Ukrainian Space Launch Vehicles

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CYCLONE-1M​

The Cyclone-1M is a lightweight liquid-propellant launch vehicle designed to deliver payloads into low Earth orbits, including sun-synchronous orbits.
The Cyclone-1M will be launched both from a space launch center located in Ukraine and from foreign space launch centers.

FEATURES

Number of stages	3
Dimensions, mm
Length	30000
Stage 1	19000
Stage 2	4500
Stage 3	630
Payload fairing diameter, mm	2600
Launch mass (w/o payload), tons
Stage 1	64.2
Stage 2	7.2
Stage 3	0.3
Propellants
Oxidizer
Stage 1	liquid oxygen
Stage 2	liquid oxygen
Stage 3	-
Fuel
Stage 1	kerosene
Stage 2	kerosene
Stage 3	hydroxylammonium nitrate (HAN)
Thrust: sea level/vacuum, ton-force
Stage 1	79.7/89.1
Stage 2	4.84
Stage 3	0.02

 

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CYCLONE-4​

Lightweight tandem launch vehicle

BASIC SPECIFICATIONS​

Number of stages	3
Dimensions, mm Length Stage diameter Fairing diameter	40190 3000 4000
Launch mass, tons	198,25
Propellants Oxidizer Fuel	NTO UDMH
Thrust, ton-force Stage 1 Stage 2 Stage 3	313 102 8
Maximum payload capability, tons 500-km circular orbit Geostationary transfer orbit Sun-synchronous orbit	5,275 1,6 3,7
Injection accuracy: 500-km circular orbit Altitude, km Inclination, deg Geostationary transfer orbit Apogee height, km Perigee height, km Inclination, deg Sun-synchronous orbit Altitude, km Inclination, deg	± 5 ± (0,05…0,08) ± 100 ± 5 ± (0,05…0,08) ± 6-7 ± (0,05…0,08)
Maximum g-load	6,8
Payload fairing cleanliness class (FED STD 209E)	100 000

 

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CYCLONE-4M​

Class of launch-vehicle: medium-lift
Staging: tandem

Cyclone-4M LV is a two-staged monoblock medium-lift LV produced to satisfy the growing demand for commercial launch missions to LEO and SSO (including SC constellations).
The first stage of the Cyclone-4M LV is developed basing on used components and systems of the Zenith launch vehicles and has a great heredity. The first stage is equipped with a liquid oxygen-kerosene engine.
The second stage of the Cyclone-4M LV is equipped with a restartable nitrogen tetroxide-unsymmetrical dimethylhydrazene engine for orbital maneuvers.
Diameter of a standard Cyclone-4M LV payload unit is 4000 mm and length is 9590 mm. Payload accomodations cleanliness class is 100 000 (FED STD 209E).

General parameters

Quantity stage	2
Length, mm
Length	38700
Diameter of 1 stage	3900
Diameter of 2 stage	3980
Diameter of payload fairing	4000
ILV launching mass (without payload), t
1 stage	260,7
2 stage	14
Propellants
oxidizer
1 stage	liquid oxygen
2 stage	nitrogen tetroxide
fuel
1 stage	kerosene
2 stage	unsymmetrical dimethylhydrazene
Thrust of stage: at the ground / in vacuum, tf
1 stage	319 / 356,7
2 stage	- / 7,916

 

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ZENIT-2SLB​

Medium-lift tandem launch vehicle

The Zenit-2SLB launch vehicle delivers medium-weight payloads into low Earth orbits, including sun-synchronous and polar orbits.
The Zenit-2SLB rocket is a part of the Zenit family, which uses environmentally friendly propellants: liquid oxygen and kerosene RG-1.
The launch vehicle is operated from Baikonur Cosmodrome, Kazakhstan. The launch system can provide a launch rate of up to 12 launches per year (including up to 7 launches with a booster stage).
The Zenit-2SLB is a component of the Zenit-M launch system. The Zenit-2SLB commercial launch services are provided by Space International Services (Ukraine, Russia).
The Zenit-2SLB is derived from the Zenit-2 launch vehicle. The first launch was conducted on June 29, 2007. Including the original Zenit-2 launches, 38 launches were conducted in all, 33 of them successful.

BASIC SPECIFICATIONS​

Number of stages	2
Dimensions, mm Length Stage diameter Fairing diameter	57400 3900 3900
Launch mass, tons	460,6
Propellants Oxidizer Fuel	Liquid oxygen Kerosene
Vacuum thrust, tons Stage 1 Stage 2	806,4 101,1
Maximum payload capability, tons Circular orbit: (Нc=200 km, i=51.4°) Sun-synchronous orbit: (Нc=700 km, i=98.8°)	13,92 5,93
Circular orbit injection accuracy (Нc=100 km) Altitude, km Inclination, deg	±8 ±0,04
Maximum g-load	4.0
Payload fairing cleanliness class (FED STD 209E)	100 000

 

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ZENIT-3SL​

Medium-lift tandem launch vehicle

The Zenit-3SL Integrated Launch Vehicle is designed to deliver heavy spacecraft into mean and high circular and elliptical near-earth orbits, geosynchronous transfer and geostationary orbits, as well as escape trajectories with orbit inclination ±180°.
The Zenit-3SL Integrated Launch Vehicle operates on environmentally safe propellant components liquid oxygen and kerosene RG-1.
Horizontal assembly and transportation technology enables to significantly simplify the technological equipment system and prelaunch processing procedures.
Prelaunch processing is fully automatic providing a means for the ILV launch from the sea launch platform according to “unattended launch” scheme and the highest level of personnel safety.
Launch vehicles are launched from the Pacific Ocean. The Zenit-3SL Integrated Launch Vehicle is operated as a part of the Sea Launch Rocket Space Complex.
The Zenit-3SL launch vehicle is developed on the basis of the Zenit-2S two-stage launch vehicle (developed by Yuzhnoye SDO), DM-SL Upper Stage (developed by RSC Energia) and Payload Unit (developed by Boeing). The first launch took place on March 28, 1999. Total 36 missions were fired, 33 of them – successful.

BASIC SPECIFICATIONS​

Number of stages	3
Dimensions, mm Length Stage diameter Fairing diameter	59600 3900 4150
Launch mass, tons	473
Propellants Oxidizer Fuel	Liquid oxygen Kerosene
Thrust, ton-force Stage 1 Stage 2 Stage 3	806,4 101,1 8,1
Maximum payload capability, tons Circular orbit: (Н=1000 km) Geostationary transfer orbit: (Н=200 km)	6,1 6,1
Injection accuracy Circular orbit (Нc=1000 km) Altitude, km Inclination, deg Geostationary transfer orbit Apogee height, km Perigee height, km Inclination, deg	±25 ±0,06 ±40 ±100 ±0,06
Maximum g-load	4,0
Payload fairing cleanliness class (FED STD 209E)	100 000

 

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ZENIT-3SLB​

Medium-lift tandem launch vehicle

The Zenit-3SLB launch vehicle delivers medium-weight payloads into medium and high circular and elliptical orbits, including geostationary transfer and geostationary orbits, and escape trajectories.
The Zenit-3SLB rocket is a part of the Zenit family, which uses environmentally friendly propellants: liquid oxygen and kerosene RG-1.
The launch vehicle was developed for the Land Launch program to launch spacecraft from Baikonur Cosmodrome, Kazakhstan. The launch system can provide a launch rate of up to 12 launches per year (including up to 7 launches with a booster stage).
The Zenit-3SLB launch services are provided by Space International Services (Ukraine, Russia).
The Zenit-3SLB is derived from the Zenit-3SL launch vehicle. The rocket comprises two stages designed by Yuzhnoye, Block DM-SL booster stage developed by RSC Energia, and a payload unit developed by NPO Lavochkin. The first launch was conducted on April 28, 2008. Six launches were conducted in all, all successful.

BASIC SPECIFICATIONS​

Number of stages	3
Dimensions, mm Length Stage diameter Fairing diameter	58700 3900 4100
Launch mass, tons	466.5
Propellants Oxidizer Fuel	Liquid oxygen Kerosene
Thrust, ton-force Stage 1 Stage 2 Stage 3	806,4 101,1 8,1
Maximum payload capability, tons Circular orbit (Нc=1000 km) Geostationary transfer orbit (H=4100?35786 km, i=23.2°)	5 3,6
Injection accuracy Circular orbit (Нc=1000 km) Altitude, km Inclination, deg Geostationary transfer orbit Apogee height, km Perigee height, km Inclination, deg	±25 ± 0,06 ±100 ±40 ±0,1
Maximum g-load	4.0
Payload fairing cleanliness class (FED STD 209E)	100 000

 

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ZENIT-3SLBF​

Medium-lift tandem launch vehicle

The Zenit-3SLBF Integrated Launch Vehicle is designed to deliver medium-weight spacecraft into mean and high circular and elliptical near-earth orbits, including geosynchronous transfer and geostationary orbits, as well as escape trajectories.
The Zenit-3SLBF Integrated Launch Vehicle is included into the Zenit rocket family operating on non-toxic propellant components (liquid oxygen and kerosene RG-1). It is developed within the framework of the Land Launch program for spacecraft launches from the Baikonur Cosmodrome (Kazakhstan). The System is capable to provide up to 12 launches per year (including up to 7 launches with the upper stage).
The Zenit-3SLBF Integrated Launch Vehicle is developed on the basis of the Zenit-2SLB Integrated Launch Vehicle (developed by Yuzhnoye SDO), Fregat-SB Upper Stage and fairing (developed by NPO Lavochin). The first launch took place on January 20, 2011. Total 4 missions were fired, all a success.

BASIC SPECIFICATIONS​

Number of stages	3
Dimensions, mm Length Stage diameter Fairing diameter	55 250 3 900 4 100
Launch mass, tons	462
Propellants Oxidizer Fuel	Liquid oxygen Kerosene
Thrust, ton-force Stage 1 Stage 2 Stage 3	806,4 101,1 2,0
Maximum payload capability, tons Circular orbit: (Нc= 1000 km) Geostationary transfer orbit: (H=35786?4100 km, i=23.2°)	5,5 4,0
Injection accuracy Circular orbit (Нc= 10000 km) Altitude, km Inclination, deg Geostationary transfer orbit (H=4000 km) Apogee height, km Perigee height, km Inclination, deg	±25 ±0,06 ±40 ±100 ±0,1
Maximum g-load	4,0
Payload fairing cleanliness class (FED STD 209E)	100 000

 

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DNEPR​

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

 

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MAYAK​

The Mayak launch vehicle family provides spacecraft launches into low and medium orbits, including sun-synchronous.

The launch vehicles use environmentally friendly propellants: liquid oxygen and kerosene.
The Mayak family is derived from the existing Zenit and Cyclone launch vehicles.
The family includes lightweight (Mayak-L1, Mayak-L2), medium-lift (Mayak-M1, Mayak-M2) and heavy-lift (Mayak-H3, Mayak-H5) launch vehicles.

BASIC SPECIFICATIONS​

	Mayak-L1	Mayak-L2	Mayak-M1
Number of stages	2	2	2
Dimensions, mm Length Stage diameter Fairing diameter	27300 2700 2400	36900 3000 4000	47400 3900 4000
Launch mass, tons	95	165	370
Propellants	liquid oxygen + kerosene
Propulsion: Stage 1 Stage 2 Stage 3/Booster stage	RD801 RD809К -	2*RD801 2*RD809К -	2*RD810 4*RD809К -
Thrust, ton-force Stage 1 (sea-level) Stage 2 (vacuum) Booster stage (vacuum)	123 10 -	246 20 -	388 40 -
Maximum payload capability, tons Circular orbit (Hc=200 km, i=51.6°) Geostationary transfer orbit (Hp/Ha =183/35786 km, i=2.3°)	1500	3000	8200 2400

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BASIC SPECIFICATIONS​

	Mayak-M2	Mayak-H3	Mayak-H5
Number of stages	2/3	2/3	2/3
Dimensions, mm Length Stage diameter Fairing diameter	61000 3900 4600	63000 3900 4600	64000 3900 6000
Launch mass, tons	495/515	1218/1236	2010/2015
Propellants	liquid oxygen + kerosene
Propulsion: Stage 1 Stage 2 Stage 3/Booster stage	4*RD810 RD801В -/RD809К	12*RD810 RD801В -/RD809К	20*RD810 RD801В -/RD809К
Thrust, ton-force Stage 1 (sea-level) Stage 2 (vacuum) Booster stage (vacuum)	776 141,7 - / 10	2328 141,7 - / 10	3880 141,7 - / 10
Maximum payload capability, tons Circular orbit (Hc=200 km, i=51.6°) Geostationary transfer orbit (Hp/Ha =183/35786 km, i=2.3°)	15100/ - -/ 6500	45500/ - 16000/ 19000	70100/ - 25000/ 30200

 

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