 |
| Basic flight parameters of “Aerial Launch” ARC SP
| | Maximal take-off mass, t
| 392
| | Launching mass of CR, t
| 102
| | Flight radius to launch area, km
| 4000
| | Flight speed at moment of separation, km/h
| 650
| | Flight attitude at moment of separation, m
| 9000... 10000
| | Length of the RW for the system’s launch. m
| 3000
| | Weight of artificial satellite
|
| | At H=200 km, i=90º
| 3000
| | At H=200 km, i=51º
| 3400
| | At H=200 km, i=0º
| 4000
| | CR fuel components
|
| | Oxidizing agent
| liquid oxygen
| | Fuel
| kerosene
|
|
|
