| Characteristic |
Value |
| Maximum mass at the start (1st flight), t |
105 (79.4) |
| Stock of oxygen, t |
10.4 |
| Stock of fuel, t |
4.1 |
| Payload mass H=200km |
|
| Slope of 50.7°, t |
30 |
| Slope of 97°, t |
16 |
| Landing mass |
|
| Nominal, t |
82 |
| Maximum, t |
87 |
| Crew |
|
| During flight tests |
2 |
| Maximum (without ejector seats) |
10 |
| Volume of the crew cabine, m³ |
73 |
| Flight duration |
|
| Nominal, days |
7 |
| Maximum (with full tanks), days |
30 |
| Possible slopes of the orbits, in degrees |
50.7 à 110 |
| Orbits altitudes |
|
| Circular work orbit, km |
250 to 500 |
| Maximum (with full tanks), km |
1000 |
| Accelerations |
|
| During re-entry (maximum), g |
2.95 |
| During going down through the atmosphere, g |
1.6 |
| Landing speed |
|
| Average (with a mass of 82 t), km/h |
312 |
| Maximum, km/h |
360 |
| For the first flight, km/h |
263 |
| Dimensional specifications |
|
| Overall length, m |
36.37 |
| Length of the fuselage, m |
30.85 |
| Width of the fuselage, m |
5.5 |
| Wingspan, m |
23.92 |
| Wings surface, m² |
250 |
| Height from the ground, m |
16.35 |
| Length of the payload bay, m |
18.55 |
| Diameter of the payload bay, m |
4.7? |
| Quantity of flight |
100 |
| Mass of the structure, m |
62 |
| Minimal duration between 2 consecutive flights, days |
20 |
