Roscosmos

Roscosmos is the national space agency of Russia. It was restructured in 2015 but it has basically been designing and building rockets, satellites and other crafts related with space exploration. The agency is part of the development of the ISS, and during the 1950s and 1960s it had some of the most important achievements in space exploration (such as first satellite launched into orbit or first spacewalk).

Headquarters: Moscow, Russia

Launch Sites: Baikonour Cosmodrome Kazahstan, Vostochny Cosmodrome Russia (in construction).

Rockets

A-1 Sputnik

Overview (Sputnik)

This is a rocket designed by Sergei Korolev which was based on the R-7 semyorka balistic missile. It launched the first satellite into orbit (sputnik satellite).

Data (Sputnik)

Height: 30 m

Diameter: 3 m

Stages: 2

Mass: 267,000 kg

LEO: 500 kg

First Flight: 4 October 2957

Last Flight: 15 May 1958

Launches: 4

Successes: 3

Failures: 1

Success Rate: 75%

Reusability: None

Boosters

Engine: RD-107

Number: 4

Thrust: 970 kN

Specific Impulse: 306 s

Burn Time: 120 s

Fuel: RP-1 (Kerosene) LOX (liquid oxygen)

First Stage

Engine: RD-108

Engine Number: 1

Thrust (Sea Level): 912 kN (sea level)

Burn Time: 330 s

Specific Impulse: 308 s (sea level)

Fuel: RP-1 (Kerosene) LOX (liquid oxygen)

Soyuz Fregat

Overview (Soyuz)

The Soyuz Fregat is a retired rocket developed mainly by Roscosmos with the help of ESA. It launched for the first time in 2001. It was used to launch both cargo and humans to orbit or the ISS.

Data (Soyuz)

Height: 49.5 m

Diameter: 2.95 m

Stages: 2 or 3

Mass: 305,000 kg

LEO: 7,800 kg

SSO: 4,500 kg

First Flight: 20 May 2001

Last Flight: 25 September 2019

Launches: 70

Successes: 69

Failures: 1

Success Rate: 98.5%

Reusability: None

Boosters

Engine: RD-107A

Number: 4

Thrust: 838 kN

Specific Impulse: 263 s

Burn Time: 118 s

Fuel: RP-1 (Kerosene) LOX (liquid oxygen)

Height: 19,6 m

Diameter: 2,68 m

First Stage

Engine: RD-108A

Engine Number: 1

Thrust (Sea Level): 792 kN (sea level)

Burn Time: 280 s

Specific Impulse: 257 s (sea level)

Fuel: RP-1 (Kerosene) LOX (liquid oxygen)

Height: 27,1 m

Diameter: 2,95 m

Mass: 99,500 kg

Second Stage

Engine: RD-0110

Engine Number: 1

Thrust (Sea Level): 297 kN (vacuum)

Burn Time: 230 s

Specific Impulse: 326 s (sea level)

Fuel: RP-1 (Kerosene) LOX (liquid oxygen)

Height: 6,7 m

Diameter: 2,66 m

Mass: 25,300 kg

Third Stage

Engine: S5.92 (optional stage, only on Fregat version)

Engine Number: 1

Thrust (Sea Level): 20 kN (vacuum)

Burn Time: 1100 s

Specific Impulse: 333 s (sea level)

Fuel: RP-1 (Kerosene) LOX (liquid oxygen)

Height: 1,5 m

Diameter: 3,35 m

Mass: 5,250 kg

Fuel: N₂O₄/UDMH

Proton-M

Overview (Proton)

The Proton Rocket is built by Krunichev and belongs to the Proton rocket family. It is launched from theh Baikonur Cosmodrome in Kazakhstan. It has been a controversial rocket due to its high pollution when it comes to launching and due to its launch success rate.

Data (Proton)

Height: 58.2 m

Diameter: 7.4 m

Stages: 3 or 4

Mass: 705,000 kg

LEO: 23,000 kg

SSO: 6,920 kg

First Flight: 7 April 2001

Launches: 109

Successes: 98

Partial Failures: 2

Failures: 9

Success Rate: 89.9%

Reusability: None

First Stage

Engine: RD-275M

Engine Number: 6

Thrust (Sea Level): 10,532 kN (sea level)

Burn Time: 108 s

Specific Impulse: 285 s (sea level)

Fuel: N₂O₄/UDMH

Height: 21.18 m

Diameter: 7.4 m

Propellant Mass: 428,300 kg

Empty Mass: 30,600 kg

Second Stage

Engine: RD-0210 (3 engines) RD-0211 (1 engine)

Engine Number: 4 total

Thrust (Sea Level): 2,399 kN (vacuum)

Burn Time: 206 s

Specific Impulse: 327 s (sea level)

Fuel: N₂O₄/UDMH

Height: 17.05 m

Diameter: 4,1 m

Propellant Mass: 157,300 kg

Empty Mass: 11,000 kg

Third Stage

Engine: RD-0212

Engine Number: 1

Thrust (Sea Level): 613 kN (vacuum)

Burn Time: 238 s

Specific Impulse: 325 s (sea level)

Fuel: N₂O₄/UDMH

Height: 4.11 m

Diameter: 4.1 m

Propellant Mass: 46,562 kg

Empty Mass: 3,500 kg

Fourth Stage

Engine: S5.98 (optional stage)

Engine Number: 1

Thrust (Sea Level): 19,62 kN (vacuum)

Burn Time: 3000 s

Specific Impulse: 3256s (sea level)

Fuel: N₂O₄/UDMH

Height: 2.61 m

Diameter: 4 m

Propellant Mass: 19,800 kg

Empty Mass: 2,370 kg

Fuel: N₂O₄/UDMH

Launch Cost: $65 Million

Angara A5

Overview (Angara)

This is a rocket designed and manufactured by Krunichev that belongs to the Angara rocket family. They are heavy satellite launchers.

Data (Angara)

Height: 42.7 m

Diameter: 8.86 m

Stages: 2 or 3

Mass: 790,000 kg

LEO: 24,500 kg

GTO: 7,500 kg

First Flight: 23 December 2014

Launches: 1

Successes: 1

Partial Failures: 0

Failures: 0

Success Rate: 100%

Reusability: None

Boosters

Engine: RD-191

Number: 4

Thrust: 7,680 kN

Specific Impulse: 310 s

Burn Time: 214 s

Fuel: RP-1 (Kerosene) LOX (liquid oxygen)

First Stage

Engine: RD-191

Engine Number: 1

Thrust (Sea Level): 294 kN (sea level)

Burn Time: 325 s

Specific Impulse: 310 s (sea level)

Fuel: RP-1 (Kerosene) LOX (liquid oxygen)

Second Stage

Engine: RD-0124A

Engine Number: 1

Thrust (Sea Level): 294 kN (vacuum)

Burn Time: 424 s

Specific Impulse: 359 s (sea level)

Fuel: RP-1 (Kerosene) LOX (liquid oxygen)

Third Stage

Engine: S5.98M (optional)

Engine Number: 1

Thrust (Sea Level): 19,6 kN (vacuum)

Burn Time: 3000 s

Specific Impulse: 326 s (sea level)

Fuel: N₂O₄/UDMH

Launch Cost: $90-105 Million

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