1977-012A
Tansei-3 (MS-T3) was the test payload for the Mu-3H prototype flight. Mass was 128 kg plus 56 kg kick motor. Size is 0.93m dia 0.80m high; 1.38m long with kick motor, KM-A thrust is 7.0 kN , Isp 283s. Launch was 71 deg elevation and 152 deg azimuth. The Mu-3H had a larger first stage than the earlier models.
The payload included a 0.38m dia kick motor which raised the orbit at first apogee. The kick motor was installed `upside-down' on top of the satellite at launch. Tansei 3 had a spin rate of 2.1 rev per second in parking orbit, maintaining its attitude for half a revolution. Kick motor fired half an orbit after insertion above S America increasing speed by about 750 m/s into a 136 minute orbit.
On the first rev visibile from Kagoshima, the first yo-yo system is fired to decrease spin rate from 120 to 40 rpm. A cold gas jet propulsion test was tried but a valve malfunction caused problems. Then, a second yo-yo system was used to further despin the satellite and activate the magnetic spabilization.
Stage 3+4 was 1436 kg full 351 empty, 67 kN., 53 s burn time. Without St 4, 1249f 164em. Isp 284s. Stage 4 was 187 kg full 141 kg empty including satellite, 20s burn time, 6.8 kN, KM-A is 59f 13? em., Isp 281s.
|
| Tansei 3 |
| |
|
| Date | Time | Event | Orbit |
|---|
|
| 1977 Feb 19 | 0515:00 | Launch by Mu 3H-1 | KASC |
| | | T+0:08 SOB burnout |
| | | T+0:09 SOB sep |
| | 0516? | T+1:24 St 1 burnout | -6228 x 95 x 58.3 |
| | | T+1:26 B2 ig |
| | 0517? | St 2 burnout |
| | 0517? | Fairing top off |
| | 0517? | Fairing lower part off |
| | 0520? | T+6:00Spinup St 3 | -5366 x 331 x 62.5 (p344) |
| | 0521 | T+6:02 St 2 sep | -4451 x 328 x 65.5 |
| | 0521:05 | St 2 apo |
| | 0521 | T+6:07 St 3 burn, 54s |
| | 0522 | St 3 burnout |
| | 0522:57 | T+7:57 St 3 sep | 95.9 329 x 793 x 65.5 |
| | | T+7:57 Yo ig |
| | | | 327 x 825 x 65.64 (ISASB) |
| | 0607:58 | Activate damping? |
| | 0609:39 | T+54:40 KM Kick motor burn, 20s |
| | 0610:00 | KM burnout |
| | 0611:20 | T+56:20 KM sep | 134.3 796 x 3821 x 65.8 |
| | | T+56:20 Yo-yo despin |
| | | Boom deploy |
| | | T+1 week? Second yo-yo despin |
Payload:
- MAG Magnetic attitude control system (test for EXOS-A)
- JET Cold-gas jet for spin axis control
- MAG-EXT Mag stabilization booms, 2m long
- Yo-yo system
- UVP Auroral UV photometer test