Systems's mains characteristics
Characteristic | Orbiter Value | Buran Value |
Mass of the system at the beginning, t | 2046 | 2350 |
Thrust at launch, tf | 3076 | 3568 |
Specification of the Orbiter | ||
Mass at launch, t | 109 | 105 |
Maximum mass at landing, t | 96 | 87 |
Payload mass, t | 20 | 30 |
Volume of the crew cabine, m³ | 71 | 73 |
Dimensional specifications | ||
Length, m | 34.24 | 36.37 |
Wingspan, m | 23.79 | 23.92 |
Height, m | 17.25 | 16.35 |
Length of the payload bay, m | 18.3 | 18.55 |
Diameter of the payload bay, m | 4.6 | 4.7? |
Quantity of flight | 100 | 100 |
Mass of the structure, t | 68.586 | 62 |
Heat shield tiles, number | 24000 | 38600 |
Circular work orbit, km | 185 to 1000 | 250 to 500 |
Crew | 7 | 10 |
Total mass of the 1st stage, t | 1180 | 1490.4 |
Mass of oxygen, t | X | 886.8 |
Mass of kerosene (РГ-1), t | X | 341.2 |
Mass of solid fuel, t | 950 | X |
Pulverulent aluminium powder (combustible), % | 16 | X |
Perchlorate of ammonium (combustive), % | 69.6 | X |
Iron oxyde powder (catalyst), % | 0.4 | X |
Polybutadiene Acrylonitrile or Hydroxyl-terminated polybutadiene (polymer), % | 12 | X |
Epoxy curring agent (catalyst), % | 2 | X |
Engine of the 1st stage | ||
Thrust on the sea level (100% thrust), tf | X | 740 |
Thrust in vacuum (100% thrust), tf | X | 806 |
Total mass of the 2nd stage, t | 757 | 776.2 |
Mass of oxygen, t | ~600 | 602.775 |
Mass of hydrogen, t | ~100 | 100.868 |
Engine of the 2nd stage | ||
Thrust on the sea level (100% thrust), tf | 170 | 147.6 |
Thrust in vacuum (100% thrust), tf | 213 | 190 |
Dimensional specifications of the system | ||
Height, m | 56.14 | 58.765 |
Width, m | 23.79 | 23.92 |
Dimensional specifications of the 1st stage | ||
Height, m | 45.6 | 39.46 |
Diameter, m | 3.71 | 3.92 |
Dimensional specifications of the external tank | ||
Height, m | 46.9 | 58.576 |
Diameter, m | 8.4 | 7.75 |
Uses | ||
1st stage, flight | 20 | 10 |
2nd stage (external tank), flight | 100 (1) | 1 |
Azimuth of launch, ° | 35-120 | 51-83, 97, 101-104, 110 |
Minimal duration between 2 consecutive flights, days | 25 | 20 |
In sum, the Soviets' design of the Energiya a modular ELV was in keeping with traditional emphasis on functionality, versatility, and simplicity. fact that they designed a new rocket with cryogenic liquid fuel no less, for Energiya instead of adapting a previous Soviet speaks to Glushko's political influence at the as well as a Soviet political system could give one individual so much power. Buran's configuration as a winged, reusable spacecraft largely attributable to two factors: the long history of spaceplane concepts and the Soviets' to match the U.S. Shuttle's capabilities by its design.
First, politics inevitably shapes and often dominates the of science and technology. The U.S. Shuttle built and designed the way it was a variety of mostly domestic political reasons. the Buran was also heavily affected by politics, its development is one more Cold story of the Soviets competing with the States. During the 1970s, the Apollo-Soyuz Test was the exception that proves the rule superpower competition and the stories of the Shuttles conform closely to this rule.