KOUNOTORI6 completed its mission with re-entry!
The KOUNOTORI6 (HTV6, a cargo transporter to the International Space Station) left the ISS on Jan. 28 and re-entered the atmosphere at around 0:06 a.m. on Feb. 6 (Japan Standard Time.) Reentry of KOUNOTORI6 was confirmed ...
- Dec. 10, 2016 (00:10) [release]
- Launch success of the H-IIB Launch Vehicle No. 6 (H-IIB F6) with the H-II Transfer Vehicle "KOUNOTORI6” on board
- Dec. 7, 2016 (14:00) [release]
- Launch of the H-IIB Launch Vehicle No. 6 with the H-II Transfer Vehicle "KOUNOTORI6” on Board
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
|F6||12/9/2016||H-II Transfer Vehicle "KOUNOTORI6" (HTV6)|
|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)|