Launch Result of H-II Transfer Vehicle "KOUNOTORI4" (HTV4) by H-IIB Launch Vehicle No. 4
Japan Aerospace Exploration Agency (JAXA)
Mitsubishi Heavy Industries, Ltd.
Mitsubishi Heavy Industries, Ltd. and the Japan Aerospace Exploration Agency launched the H-IIB Launch Vehicle No.4 (H-IIB F4) with the KOUNOTORI4 (HTV4, a cargo transfer vehicle to the International Space Station) onboard at 4:48:46 a.m. on August 4 (Sun.) 2013 (Japan Standard Time, JST) from the Tanegashima Space Center.
The launch vehicle flew smoothly, and, at about 14 minutes and 59 seconds after liftoff, the separation of the KOUNOTORI4 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-IIB F4.
At the time of the launch, the weather was fine, a wind speed was 3.5 meters/second from the northwest and the temperature was 27.9 degrees Celsius.
H-IIB Launch Vehicle No.4 (H-IIB F4)
Launch Sequence (Quick Review)
| Event | Actual value (Quick review)*1 | Scheduled value*2 (Predicted value based on actual measurement data) |
|---|---|---|
| 1. Liftoff | 0 second | 0 second |
| 2. Solid rocket booster (SRB-A) burnout *3 | 1 min. 50 sec. | 1 min. 54 sec. |
| 3. Solid rocket booster (SRB-A) 1st pair jettison *4 | 2 min. 6 sec. | 2 min. 4 sec. |
| 4. Solid rocket booster (SRB-A) 2nd pair jettison *4 | 2 min. 9 sec. | 2 min. 7 sec. |
| 5. Payload fairing jettison | 3 min. 40 sec. | 3 min. 40 sec. |
| 6. Main engine cutoff (MECO) | 5 min. 46 sec. | 5 min. 45 sec. |
| 7. 1st and 2nd stages separation | 5 min. 54 sec. | 5 min. 54 sec. |
| 8. Second stage engine lock in (SELI) | 6 min. 4 sec. | 6 min. 4 sec. |
| 9. Second stage engine cutoff (SECO) | 14 min. 8 sec. | 14 min. 7 sec. |
| 10. HTV-4 separation *5 | 14 min. 59 sec. | 14 min. 57 sec. |
(*1) The values are based on quick report results without detailed data evaluation.
(*2) The values are updated ones based on actual measurement data such as thrust characteristics which are unique for the H-IIB F4 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 to cut the thrust struts.
(*5) When the launch vehicle sent the separation signal
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