Factor name |
Value
|
Mass of spacecraft injected into, kg
- geostationary orbit
- geo-transfer orbit
(Нperigee = 4100 km, Нapogee= 35786 km, i=23.2њ,
shortage of velocity to GEO - 1500 m/s)
- mid-circular
(Нcir = 10000 km, i = 51.4 deg.)
|
up to 1600
up to 3600
up to 4830
|
Maximum rate, number of launches per year |
up to 7
|
Time from the contract conclusion with SC Customer to the launch performed, months |
12 - 18
|
Time for ILV processing and launch, days (with one-shift operation) |
41
|
Time of ILV prepared launch (from the time of ILV roll-out of the assembly & testing facilities), days
|
up to 3
|
Time of prelaunch after the launch cancellation of ILV filled, days |
not less than in 3
|
Duration of the unloaded Integrated Launch Vehicle staying on LD, days |
4
|
Duration of the launch timeline, hr |
5
|
Continuity of AU thermostatting since ILV roll-out of the assembly & testing facilities prior to launch or before the ILV return to the assembly & testing facilities (in case of launch cancellation) |
provided
|
Probability of prelaunch processing and launch at the given time (interval) |
not less than 0.97
|
Probability of failure-free operation of ILV during SC injection |
not less than 0,96
|
Maximum reserve of the propellant components and compressed gases |
for 2 launches
|
Periodicity of maintenance |
once a year
|
Clean room for SC (AU) preparation and their mating with LV |
Avalable
|
Cosmodrome |
Baikonur (63њ EL and 46њN. Lat.)
|
Accuracy of SC Injection (3 s ) into Typical Orbits
Block DM-SLB provides injection into the given orbit with high accuracy.
Parameter name |
Orbit |
Circular 1) |
GTO 2) |
GEO |
Orbit altitude, km |
±25
|
-
|
±200
|
Perigee altitude, km |
-
|
±40
|
-
|
Apogee altitude, km |
-
|
±100
|
-
|
Inclination, deg |
±0,06
|
±0,1
|
±0,2
|
Longitude of the ascending node, deg |
±0,2
|
±0,3
|
-
|
Argument of perigee, deg
|
-
|
±0,2
|
-
|
Period of revolution, s
|
±45
|
|
±450
|
Notes:
1) ) Нcir= 10000 км, i=51,4њ;
2) Нa= 4000 км,
Нp= 35786
km, i=23° |
|