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The first generation of the Mu series was the four-stage M-4S rocket. It utilized a gravity turn for its orbital insertion, and stabilized its attitude with tail fins and spin. It could send a 180 kg satellite into low earth orbit.
Mission by M-4S Launch Vehicle
The vehicle M-4S-1 is described as follows
1st st. | SOB | 2nd st. | 3rd st. | 4th st. | ||
---|---|---|---|---|---|---|
Total length | m | 23.557 | 5.794 | 10.595 | 5.860 | 1.838 |
Maximum diameter | mm | 1410.0 | 310.0 | 1410.0 | 860.0 | 786.0 |
Weight (ig.) | kg | 43710 | 4166 | 13211 | 3273 | 509.4 |
Weight (b.o.) | kg | 19118 | 1482 | 6052 | 1282 | 140.5 |
Propellant weight | kg | 20522 | 2696 | 7146 | 1986 | 368.6 |
Mass ratio | 2.2031 | 2.1808 | 2.5491 | 3.6235 | ||
Specific impulse | sec | 219.0 | 219.0 | 261.0 | 265.0 | 270.0 |
Center of gravity (ig.) | % | 61.98 | 63.74 | 56.74 | 60.60 | |
Center of gravity (b.o.) | % | 46.10 | 52.53 | 43.72 | 45.82 | |
Ix (ig.) | kg.m.sec2 | 1610.1 | 329.82 | 34.89 | 3.445 | |
Ix (b.o.) | kg.m.sec2 | 660.41 | 152.73 | 12.74 | 0.8464 | |
Iy (ig.) | kg.m.sec2 | 134206 | 7181.5 | 563.05 | 7.8630 | |
Iy (b.o.) | kg.m.sec2 | 62307.6 | 4873.3 | 329.85 | 3.9039 | |
Net payload | kg | 49.4 | 62.2(SA) | |||
Gross payload | kg | 148.2 | 68.9 | |||
Nozzle expansion ratio | 5.94 | 3.57 | 20.0 | 17.36 | 19.9 | |
Nozzle exit diameter | m | 0.8626 | 0.0716 | 0.7595 | 0.3758 | 0.0745 |