Launch Success of H-IIA Launch Vehicle No. 25
with "Himawari-8" Onboard
October 7, 2014 (JST)
Mitsubishi Heavy Industries, Ltd.
Japan Aerospace Exploration Agency (JAXA)
Mitsubishi Heavy Industries, Ltd. and the Japan Aerospace Exploration Agency (JAXA) launched the H-IIA Launch Vehicle No. 25 (H-IIA F25) with the Geostationary Meteorological Satellite “Himawari-8” onboard at 2:16:00 p.m. on October 7, 2014 (Japan Standard Time, JST) from the Tanegashima Space Center.
The launch vehicle flew as planned, and, at about 27 minutes and 57 seconds after liftoff, the separation of the Himawari-8 was confirmed.
We would like to express our profound appreciation for the cooperation and support of all related personnel and organizations that helped contribute to the successful launch of the H-IIA F25.
At the time of the launch, the weather was fine, a wind speed was 8.5 meters/second from the northeast and the temperature was 24.6 degrees Celsius.
H-IIA Launch Vehicle No.25 Flight Sequence (Quick Estimation)
| Event | Actual value (Quick review)*1 | Scheduled value *2 |
|---|---|---|
| 1. Liftoff | 0 min. 0 sec. | 0 min. 0 sec. |
| 2. SRB-A burnout *3 | 1 min. 31 sec. | 1 min. 32 sec. |
| 3. SRB-A jettison *4 | 1 min. 45 sec. | 1 min. 46 sec. |
| 4. Payload fairing jettison | 4 min. 7 sec. | 4 min. 5 sec. |
| 5. First stage main engine cutoff (MECO) | 6 min. 37 sec. | 6 min. 35 sec. |
| 6. 1st and 2nd stages separation | 6 min. 45 sec. | 6 min. 43 sec. |
| 7. Second stage engine lock-in (SELI1) | 6 min. 55 sec. | 6 min. 51 sec. |
| 8. Second stage engine cutoff (SECO1) | 12 min. 11 sec. | 12 min. 15 sec. |
| 9. Second stage engine lock-in (SELI2) | 23 min. 52 sec. | 23 min. 53 sec. |
| 10. Second stage engine cutoff (SECO2) | 27 min. 7 sec. | 27 min. 8 sec. |
| 11. Himawari-8 separation | 27 min. 57 sec. | 27 min. 59 sec. |
*1 Quick estimation value prior to the detailed estimation
*2 The values are updated ones based on actual measurement data such as engine performance which are unique for the H-IIA F25 engines. Therefore, they are slightly different from the values in the Launch Plan.
*3 When the combustion chamber presser becomes 10% against the largest combustion pressure.
*4 The definition of SRB-A jettison is the separation of the rear brace.