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An extension of the first stage motor casing of the M-3C increased propellant to achieve a greater payload capability. The M-3H belongs to the same generation as the M-3C. It could send a 300 kg satellite into low earth orbit.
Mission by M-3H Launch Vehicle
The vehicle M-3H-1 is described as follows
1st stage | SOB | 2nd stage | 3rd stage | 4th stage | ||
---|---|---|---|---|---|---|
Total length | m | 23.80 | 5.794 | 8.895 (8.020) |
3.059 | 1.408 |
Maximum diameter | m | 1.410 | 0.310 | 1.410 | 1.136 | 0.932 |
Weight (ig.) | kg | 44714 | 4120 | 11307 | 1436.4 | 187.25 |
Weight (b.o.) | kg | 17597 | 1371 | 3960 | 351.0 | 141.15 |
Propellant weight | kg | 27098 | 2737 | 7195 | 1083.7 | 45.55 |
Freon | kg | 56.0 | ||||
H2O2 | kg | 84.7 | ||||
Mass ratio | 2.540 | 2.996 | 2.817 | 4.087 | 1.323 | |
Specific impulse | sec | 239 | 219 | 277 | 284 | 281 |
Center of gravity (ig.) | % | 60.96 | 62.90 | 63.75 | 58.66 | |
Center of gravity (b.o.) | % | 42.01 | 53.02 | 47.73 | 67.40 | |
Ix (ig.) | kg.m.sec2 | 1839 | 305.8 | 18.60 | 1.281 | |
Ix (b.o.) | kg.m.sec2 | 659.9 | 105.2 | 3.274 | 1.210 | |
Iy (ig.) | kg.m.sec2 | 188107 | 3258 | 46.95 | 2.638 | |
Iy (b.o.) | kg.m.sec2 | 83114 | 1928 | 22.96 | 1.483 | |
Net payload | kg | 149.98 | SA 128.34 | |||
Nozzle expansion ratio | 6.34 | 3.57 | 21.80 | 41.53 | 43.07 | |
Nozzle exit diameter | mm | 1146 | 302.2 | 1078.3 | 696.0 | 229.7 |
*The M-3H-1 was equipped with an optional kick stage to perform its highly elliptical orbit mission.