L (Lambda)-4S
The L (Lambda)-4S rocket was the first rocket to be used by Japan to send a satellite into earth orbit. The L-4S project was to simulate the procedures and to demonstrate the capabilities for satellite insertion into orbit for the Mu project. The L-4S rocket system was a four-stage, all-solid propellant rocket.
Ohsumi was launched on a Japanese Lambda 4-S booster, making Japan the fourth country to launch a satellite into orbit on its own rocket. Launched 1970-02-11, the Ohsumi satellite was a small observatory carrying five experiments designed to make ionospheric observations of temperature and density, measurements of solar emission, and measurements of energetic particles. A 500-km circular orbit was intended, but an elliptical orbit was achieved. The satellite was a regular 26-sided polygonal prism with a circumscribed radius of 75 cm. The batteries were powered by 5184 solar cells mounted on the satellite body. Average power consumption was 10.3 W.
Institute for Space and Astronautical Sciences, Japan Aerospace Exploration Agency, is devoted to space science, to the collaboration of scientists and engineers to research and develop solid propellant rockets and scientific satellites to meet the needs of science researchers. In 1981, the Institute of Space and Astronautically Science (ISAS) was born as a joint research organization among Japanese universities. Since the launch of OHSUMI in 1970, ISAS and its predecessor have launched 25 scientific satellites and explorers. ISAS is now one of the leading centers of excellence in the world of space science.
In the Space Aeronautics Research and Development Organization (founded in 2003 by the merger of ISAS, NASDA and NAL), space science is defined as one of the main pillars of its activities. It is expected to execute more vigorous research and make further contributions to the progress of science in the world, combining the powers of researchers at universities across the country.
The L-4S-5 launch vehicle is described as follows
| 1st st. | SOB | 2nd st. | 3rd st. | 4th st. | ||
|---|---|---|---|---|---|---|
| Total length | m | 16.522 | 5.772 | 8.141 | 4.067 | 1.104 |
| Weight (ig.) | kg | 9399.0 | 1005.0 | 3417.6 | 943.1 | 111.0 |
| Weight (b.o.) | kg | 4507.0 | 381.0 | 1562.5 | 394.9 | 23.05 |
| Propellant weight | kg | 3887.0 | 624.0 | 1845.0 | 547.5 | 87.95 |
| Mass ratio | 1.982 | 2.187 | 2.388 | 4.816 | ||
| Specific Impulse | sec | 215.0 | 220.0 | 242.9 | 249.3 | 254.0 |
| Center of gravity (ig.) | % | 59.0 | 52.9 | 63.0 | 61.8 | 64.5 |
| Center of gravity (b.o.) | % | 43.2 | 54.3 | 49.6 | 44.8 | 55.7 |
| Ix (ig.) | kg.m.sec2 | 79.89 | 25.48 | 3.52 | 0.259 | |
| Iy (b.o.) | kg.m.sec2 | 16192 | 1259.4 | 99.71 | 0.436 | |
| Net payload | kg | 6.6 | 36.3 | 7.62 | ||
| Gross payload | kg | 7.6 | 96.1 | 8.42 | ||
| Maximum diameter | mm | 767.0 | 310.0 | 767.0 | 548.0 | 483.0 |
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