INTERNATIONAL SPACE STATION

	INTERNATIONAL SPACE STATION SOYUZ TMA
SOYUZ TMA SPACECRAFT MAIN CHARACTERISTICS

Name of characteristic, dimensions	up to 7220	Remarks
1. Spacecraft mass, kg	до 7220
2. Descent module mass, kg	~ 2900
3. Crew, persons	2:3
4. Orbit parameters inclination, deg altitude, km of insertion during spacecraft docking during spacecraft descent	51.6 202/238* up to 425 up to 460	*) Perigee/apogee
5. Geometrical characteristics of the spacecraft, mm body length maximal diameter diameter of living compartments solar array span	6980 2720 2200 10700
6. Calculated mass of payload, kg delivered returned	up to 100 up to 50	With a 3-person crew
7. Flying life*, days	200	*) including the autonomous flight time
8. Touchdown speed, m/s with the main parachute system maximum / nominal with the reserve parachute system maximum / nominal	2.6 / 1.4 4.0 / 2.4	3.6 / 2.6 (via Soyuz ТМ) 6.1 / 4.3 (via Soyuz TM)
9. Launch Vehicle	Soyuz FG	Developed for the Soyuz TMA spacecraft, has passed flight testing during the Progress spacecraft launches in the years 2001-2002.

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