KOUNOTORI5 successfully launched by H-IIB F5!
The KOUNOTORI5, a regular cargo transporter to space, was launched by the H-IIB Launch Vehicle No.5 (H-IIB F5) at 8:50:49 p.m. on August 19 (Wed.) 2015 (Japan Standard Time, JST) from the Tanegashima Space Center. The launch vehicle flew smoothly, and, at about 14 minutes and 54 seconds after liftoff, the separation of the KOUNOTORI5 was confirmed. The KOUNOTORI5 will fly near the International Space Station, and Astronaut Yui will maneuver the robotic arm to capture it. We plan to broadcast h...
- Aug. 19, 2015 (22:30) [release]
- Launch Success of H-II Transfer Vehicle "KOUNOTORI5" (HTV5) by H-IIB Launch Vehicle No. 5
- Aug. 17, 2015 (14:00) [release]
- Launch Date and Time of H-II Transfer Vehicle "KOUNOTORI5" (HTV5) by H-IIB Launch Vehicle No. 5
About H-IIB Launch Vehicle
Opening the Door to Future Space Mission
Japan has been developing its own launch vehicles, based upon various researches and experiments. Among launch vehicles, the H-IIA launch vehicle has been supporting satellite launch missions as a major large-scale launch vehicle with high reliability.
Characteristics of H-IIB Launch Vehicle
1.Key Capacity Improvement: Clustering
The H-IIB launch vehicle is a two-stage rocket using liquid oxygen and liquid hydrogen as propellant and has four strap-on solid rocket boosters (SRB-A) powered by polibutadiene.
2.For Effective Development
At the time of launching HTV, the H-IIB will use a special fairing for HTV. However, in other parts, it will take over most of the specifications and structures of on-board equipments and ground systems already used for the H-IIA. These efforts are designed to reduce development risk and cost. Moreover, it will share the launch facility with the H-IIA and be launched from Yoshinobu Launch Pad of the Tanegashima Space Center.
Major Characteristics (H-IIB Test Flight)
|Mass (t)||531 (without payload mass)|
|Guidance Method||Inertial Guidance Method|
|First Stage||Solid Rocket
|Second Stage||Payload Fairing(5S-H)|
|Outside diameter (m)||5.2||2.5||4.0||5.1|
|Mass (t)||202||306 (for four SRB-As in total)||20||3.2|
|Propellant mass (t)||177.8||263.8 (for four SRB-As in total)||16.6||-|
|Combustion time (s)||352||114||499||-|
|Propellant type||Liquid oxygen/hydrogen||Polybutadiene composite solid propellant||Liquid oxygen/hydrogen||-|
|Propellant supply system||Turbo pump||-||Turbo pump||-|
|Impulse to weight ratio (s)*1||440||283.6||448||-|
|Attitude control method||Gimbal||Movable nozzle||Gimbal gas jet system||-|
|Major onboard avionics||Guidance control equipment
|-||Guidance control equipment
Command destruct system
|*1||In vacuum. Solid rocket booster's thrust is set to the maximum value.|
H-IIB Launch Vehicle Launch Capacity
|F5||8/19/2015||H-II Transfer Vehicle "KOUNOTORI5" (HTV5)|
|F4||8/4/2013||H-II Transfer Vehicle "KOUNOTORI4" (HTV4)|
|F3||7/21/2012||H-II Transfer Vehicle "KOUNOTORI3" (HTV3)|
|F2||1/22/2011||H-II Transfer Vehicle "KOUNOTORI2" (HTV2)|
|TF1||9/11/2009||H-II Transfer Vehicle "KOUNOTORI" (HTV Demonstration Flight)|