Russian

Land Launch Project

Main Characteristics


Factor name Value
Mass of spacecraft injected into, kg
  • geostationary orbit
  • geo-transfer orbit
    (perigee = 4100 km, apogee= 35786 km, i=23.2,
    shortage of velocity to GEO - 1500 m/s)
  • mid-circular
    (cir = 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
(63 EL and 46N. 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) ) cir= 10000 , i=51,4;
  2) a= 4000 , p= 35786 km, i=23°

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