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Key Energiya-Buran specifications
A. l ENERGIYA ROCKET
Overall specifications
Total launch mass Without payload With Buran
Rocket mass prior to orbiter separation Core stage Wet mass
Liquid oxygen mass Liquid hydrogen mass Strap-on booster Wet mass
Liquid oxygen mass Kerosene mass Dimensions
Core stage length Core stage tank diameter Strap-on booster length Strap-on booster tank diameter Total lift-off thrust
Engine specifications Parameter
Propellants
Oxidizer/fuel mixture ratio Combustion cycle Sea-level thrust Vacuum thrust Sea-level specific impulse Vacuum specific impulse Chamber pressure Turbopump power Turbopump rotation Throttle range Nozzle area ratio Gimbal capability Nominal burn time Dry mass Length Diameter
Energiya data collected from: Y. Baturin (ed.), Mirovaya pilotiruemaya kosmonav – tika, Moscow: RTSoft, 2005, p. 443; Fact sheet of Voronezh Machine Building Factory; “The RD-170 and RD-171” (in Russian), on-line at http://www. lpre. de/ energomash/RD-170/index. htm
A.2 BURAN
|
Maximum launch mass |
105 t |
|
Mass on first mission |
79.41 |
|
Landing mass |
|
|
Nominal |
821 |
|
Maximum |
871 |
|
Dry mass |
621 |
|
Maximum payload to orbit |
|
|
For 200 km, 50.7° orbit |
301 |
|
For 200 km, 97° orbit |
16t |
|
Mass of returned payload |
|
|
Nominal |
15t |
|
Maximum |
20 t |
|
Dimensions |
|
|
Length |
36.37 m |
|
Height (on runway) |
16.35m |
|
Maximum width of fuselage |
5.60m |
|
Wingspan |
23.92m |
|
Wing area |
250 m2 |
|
Tail area |
39 m2 |
|
Body flap area |
10.3m2 |
|
Payload bay length |
18.55m |
|
Payload bay diameter |
4.70 m |
|
Crew |
|
|
Minimum (with ejection seats) |
2 |
|
Maximum (without ejection seats) |
10 |
|
Volume of crew compartment |
73 m3 |
|
Flight duration |
|
|
Nominal |
7 days |
|
Maximum (with extra tanks) |
30 days |
|
Range of orbital inclinations |
50.7-110° |
|
Orbital altitude |
|
|
Nominal (circular) |
250-500 km |
|
Maximum (with extra tanks) |
1,000 km |
|
Maximum g-forces |
|
|
Launch (nominal trajectory) |
2.95g |
|
Re-entry (nominal trajectory) |
1.6g |
|
Lift-to-drag ratio |
|
|
At hypersonic speeds |
1.3 |
|
At subsonic speeds |
5.6 |
|
Crossrange capability |
|
|
Maximum |
1,700 km |
|
Demonstrated during 1st flight |
550 km |
|
Landing speed |
|
|
Average (for 82 ton landing mass) |
312 km/h |
|
Maximum |
360 km/h |
|
On first flight |
263 km/h |
|
Landing rollout distance |
|
|
Minimum/maximum |
1,100-2,000 m |
|
On first flight |
1,620 m |
|
Maximum number of flights |
100 |
Buran data taken from: Y. Baturin, op. cit., p. 438.