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The second generation was the three-stage M-3C. The second and third stages were newly developed and equipped with SITVC (Secondary Injection Thrust Vector Control) and side jet systems, both of which improved the accuracy of orbital injection. It could send a 195 kg satellite into low earth orbit.
Mission by M-3C Launch Vehicle
The vehicle M-3C-1 is described as follows
1st st. | SOB | 2nd st. | 3rd st. | ||
---|---|---|---|---|---|
Total length | m | 20.241 | 5.794 | 8.395(7.279) | 2.326 |
Maximum diameter | m | 1.410 | 0.310 | 1.410 | 1.144 |
Weight (ig.) | kg | 37445 | 4063 | 11144 | 1311 |
Weight (b.o.) | kg | 16983 | 1357 | 3918 | 235.6 |
Propellant weight | kg | 20453 | 2699 | 7174 | 1075 |
Freon | kg | 173 | |||
H2O2 | kg | 55 | |||
Mass ratio | 2.205 | 2.812 | 5.565 | ||
Specific impulse | sec | 222.8 | 219.0 | 273.0 | 283.0 |
Center of gravity (ig.) | % | 58.54 | 61.70 | 57.95 | |
Center of gravity (b.o.) | % | 41.85 | 54.31 | 51.12 | |
Ix (ig.) | kg.m.sec2 | 1585 | 305.3 | 17.87 | |
Ix (b.o.) | kg.m.sec2 | 639.8 | 112.3 | 2.675 | |
Iy (ig.) | kg.m.sec2 | 105717 | 2960 | 23.99 | |
Iy (b.o.) | kg.m.sec2 | 48690 | 1848 | 10.82 | |
Net payload | kg | 104.2 | 65.7(SA 56.2) | ||
Gross payload | kg | 212.6 | 70.39 | ||
Nozzle expansion ratio | 5.94 | 3.56 | 21.80 | 43.11 | |
Nozzle exit diameter | mm | 1048 | 302 | 1074 | 696 |