Press Release


Launch Result of H-IIB Launch Vehicle No. 2
with KOUNOTORI2 (HTV2) Onboard

January 22, 2011 (JST)

Japan Aerospace Exploration Agency
Mitsubishi Heavy Industries, Ltd.

The Japan Aerospace Exploration Agency (JAXA) launched the H-IIB Launch Vehicle No.2 (H-IIB F2) with the KOUNOTORI2 (HTV2, a cargo transfer vehicle to the International Space Station) onboard at 2:37:57 p.m. on January 22 (Sat.,) 2011 (Japan Standard Time, JST) from the Tanegashima Space Center.
The launch vehicle flew smoothly, and, at about 15 minutes and 13 seconds after liftoff, the separation of the KOUNOTORI2 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 F2.
At the time of the launch, the weather was clear, a wind speed was 8.3 meters/second from the north-west and the temperature was 10.6 degrees Celsius.

H-IIB Launch Vehicle No. 2 (H-IIB F2)
Launch Sequence (Quick Review)

EventActual 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) pair burnout *3 1 min. 52 seconds 1 min. 57 sec.
3. Solid rocket booster (SRB-A) 1st pair jettison *4 2 min. 6 sec. 2 min. 7 sec.
4. Solid rocket booster (SRB-A) 2nd Pair jettison *4 2 min. 9 sec. 2 min. 10 sec.
5. Payload fairing jettison 3 min. 45 sec. 3 min. 40 sec.
6. Main engine cutoff (MECO) 5 min. 50 sec. 5 min. 46 sec.
7. 1st and 2nd stages separation 5 min. 58 sec. 5 min. 54 sec.
8. Second stage engine lock in (SELI) 6 min. 9sec. 6 min. 5 sec. (*5)
9. Second stage engine cutoff (SECO) 14 min. 23 sec. 14 min. 15 sec.
10. HTV separation 15 min. 13 sec 15 min. 5 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 F2 engines. Therefore, they are slightly different from the values in the Launch Plan
(*3) The definition of SRBA burnout is when the combustion chamber presser becomes 2% against the largest combustion pressure.
(*4) The definition of SRBA jettison is to cut the thrust struts.
(*5) There was a mistake (typo) in the scheduled value column released on Jan. 22. The mistake was duly corrected. Sorry for the mistake.