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 the Energiya as a ELV was in keeping their traditional emphasis on versatility, and simplicity. The that they designed a rocket engine, with cryogenic fuel no less, for Energiya instead of adapting previous Soviet rocket speaks Glushko's political influence at time, as well as Soviet political system that give one individual so power. The Buran's configuration a winged, reusable spacecraft largely attributable to two the long Soviet history spaceplane concepts and the desire to match the Shuttle's capabilities by matching design.
First, politics inevitably shapes and dominates the conduct of and technology. The U.S. was built and designed way it was for variety of mostly domestic reasons. While the Buran also heavily affected by politics, its development is more Cold War story the Soviets competing with United States. During the the Apollo-Soyuz Test Project the exception that proves rule of superpower competition the stories of the Shuttles conform closely to rule.