Ishikawajima-Harima Heavy Ind. / ISAS |
L - 4S | M - 4S | M - 3C | M - 3H | ||||||
Overall Vehicle |
Operational | from | 26.09.1966 | 25.09.1970 | 16.02.1974 | 19.02.1977 | ||||
|
to | 11.02.1970 | 19.08.1972 | 21.02.1979 | 16.09.1978 | |||||
Orbital flights | 5 | 4 | 4 | 3 | ||||||
Payload weight | t | L-4S-5 | 0.038 | M-4S-1 | 0.056 | M-3C-1 | 0.064 | M-3H-1 | 0.316 | |
Gross liftoff weight | t | 9.10 | 43.75 | 41.30 | 49.30 | |||||
Gross propellant weight | t | 6.99 | 32.72 | 31.40 | 38.11 | |||||
Total length | m | 16.52 | 23.56 | 20.24 | 23.80 | |||||
Max. diameter (span) | m | 2.89 | 3.20 | 3.20 | 3.75 | |||||
Total liftoff thrust (s.l.) | kN | 485.1 | 1,486.7 | 1,519.1 | 1,725.6 | |||||
Total impulse (vac) | MN*s | 16.7 | 81.4 | 79.4 | 99.9 | |||||
Fairing |
Total length | m | 2.00 | 3.00 | 3.50 | 4.00 | ||||
Diameter | m | 0.48 | 0.86 | 1.41 | 1.41 | |||||
Total weight | t | 0.05 | 0.10 | 0.25 | 0.30 | |||||
Stage 4 | Name | L-40 | M-40 | |||||||
Length | m | 1.06 | ||||||||
Diameter | m | 0.55 (0.48) | 0.86 (0.79) | |||||||
Liftoff weight | t | 0.111 | 0.509 | |||||||
Propellant weight | t | 0.088 | 0.369 | |||||||
Engines | ||||||||||
Propellant | solid | solid | ||||||||
Total thrust (vac) | kN | 7.8 | 26.5 | |||||||
Specific impulse (vac) | N*s/kg | 2491 | 2648 | |||||||
Burn time | s | 27.5 | 37 | |||||||
Total impulse (vac) | MN*s | 0.2 | 1.0 | |||||||
Stage 3 |
Name |
L-30 | M-30 | M-3A | M-3A | |||||
Length | m | 2.07 | 4.02 | 1.33 | 1.65 | |||||
Diameter | m | 0.55 | 0.86 | 1.41 (1.14) | 1.41 (1.14) | |||||
Liftoff weight | t | 0.943 | 3.273 | 1.311 | 1.436 | |||||
Propellant weight | t | 0.547 | 1.986 | 1.075 | 1.084 | |||||
Engines | ||||||||||
Propellant | solid | solid | solid | solid | ||||||
Total thrust (vac) | kN | 64.7 | 129.4 | 56.9 | 56.9 | |||||
Specific impulse (vac) | N*s/kg | 2445 | 2599 | 2775 | 2785 | |||||
Burn time | s | 20.6 | 39.9 | 52.5 | 53.1 | |||||
Total impulse (vac) | MN*s | 1.3 | 5.2 | 3.0 | 3.0 | |||||
Stage 2 |
Name | L-20 | M-20 | M-21 | M-22 | |||||
Length | m | 4.07 | 4.69 | 4.89 | 4.89 | |||||
Diameter | m | 0.77 | 1.41 | 1.41 | 1.41 | |||||
Liftoff weight | t | 2.408 | 11.144 | 11.144 | 11.307 | |||||
Propellant weight | t | 1.845 | 7.146 | 7.174 | 7.195 | |||||
Engines | ||||||||||
Propellant | solid | solid | solid | solid | ||||||
Total thrust (vac) | kN | 115.7 | 284.4 | 278.5 | 324.6 | |||||
Specific impulse (vac) | N*s/kg | 2382 | 2560 | 2677 | 2716 | |||||
Burn time | s | 38 | 64.3 | 68.7 | 60.2 | |||||
Total impulse (vac) | MN*s | 4.4 | 18.3 | 19.1 | 19.6 | |||||
Stage 1 |
Name | L-10 | M-10 | M-11 | M-12 | |||||
Length | m | 8.38 | 11.85 | 11.85 | 14.91 | |||||
Diameter | m | 0.77 | 1.41 | 1.41 | 1.41 | |||||
Liftoff weight | t | 4.507 | 24.592 | 24.5 | 31.6 | |||||
Propellant weight | t | 3.887 | 20.522 | 20.453 | 27.098 | |||||
Engines | ||||||||||
Propellant | solid | solid | solid | solid | ||||||
Total thrust (s.l.) | kN | 295.1 | 730.1 | 762.5 | 969.0 | |||||
Specific impulse (s.l.) | N*s/kg | 2108 | 2148 | 2185 | 2344 | |||||
Burn time | s | 27.8 | 60.4 | 58.6 | 65.5 | |||||
Total impulse (vac) | MN*s | 9.3 | 50.3 | 50.7 | 70.6 | |||||
Booster |
Name | 2 SB-310 | 8 SB-310 | 8 SB-310 | 8 SB-310 | |||||
Length | m | 5.77 | 5.79 | 5.79 | 5.79 | |||||
Diameter | m | 0.31 | 0.31 | 0.31 | 0.31 | |||||
Liftoff weight | t | 1.005 | 4.166 | 4.063 | 4.120 | |||||
Propellant weight | t | 0.624 | 2.696 | 2.699 | 2.737 | |||||
Engines | ||||||||||
Propellant | solid | solid | solid | solid | ||||||
Total thrust (s.l.) | kN | 190.0 | 756.6 | 756.6 | 756.6 | |||||
Specific impulse (s.l.) | N*s/kg | 2157 | 2148 | 2148 | 2148 | |||||
Burn time | s | 7.1 | 7.7 | 7.7 | 7.8 | |||||
Total impulse (vac) | MN*s | 1.5 | 6.6 | 6.6 | 6.7 |