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The third generation of the Mu series was M-3S rocket. It could send a 300 kg satellite into low earth orbit.
Mission by M-3S Launch Vehicle
The vehicle M-3S-1 is described as follows
| 1st st. | SOB | 2nd st. | 3rd st. | ||
|---|---|---|---|---|---|
| Total length | m | 23.801 | 5.794 | 8.895 | 2.501 |
| Maximum diameter | m | 1.410 | 0.310 | 1.410 | 1.135 |
| Weight (ig.) | kg | 45379.4*1 | 4122.4 | 11076.8*3 | 1416.0 |
| Weight (b.o.) | kg | 18082.3*2 | 1375.7 | 3862.8 | 330.2 |
| Propellant weight | kg | 27144.0 | 2746.7 | 7214.0 | 1085.8 |
| Freon | kg | 306.3 | 42.0 | ||
| Hydrazine | kg | 28.0 | |||
| Mass ratio | 2.744 | 2.874 | 4.170 | ||
| Specific Impulse | sec | 266*5 | 219*4 | 277*5 | 284*5 |
| Center of gravity (ig.) | % | 58.95 | 66.27 | 77.97 | |
| Center of gravity (b.o.) | % | ||||
| Ix (ig.) | kg.m.sec2 | 1839.0 | 305.8 | 18.60 | |
| Ix (b.o.) | kg.m.sec2 | 660.0 | 105.2 | 3.30 | |
| Iy (ig.) | kg.m.sec2 | 188106.0 | 3257.9 | 46.90 | |
| Iy (b.o.) | kg.m.sec2 | 83111.0 | 1927.8 | 23.00 | |
| Net payload | kg | 145.7 | SA 185.0 | ||
| Gross payload | kg | 148.2 | |||
| Nozzle expansion ratio | 7.75 | 3.57 | 21.98 | 41.53 | |
| Nozzle exit diameter | mm | 1267.0 | 302.2 | 1078.3 | 696.0 |
*1:including Freon(306.3kg)
*2:including Freon(153.15kg)
*3:including Freon & H2O2
*4:in atmosphere
*5:in vacuum