H-IIA

H-IIA (H2A) is an  launch system operated by Mitsubishi Heavy Industries (MHI) for the Japan Aerospace Exploration Agency. H-IIA rockets have been used to launch satellites into geostationary orbit, to launch a lunar orbiting spacecraft, and to launch an interplanetary space probe to Venus. All
Launches occur at the Tanegashima Space Center . It first flew in 2001 and has been launched 28 times. Current Launches are operated by MHI only as JAXA handed the Launch System over in 2007.

 

 The H-IIA is a derivative of  , rocket,  redesigned to improve reliability and minimize costs. The Launcher can fly in different versions with different numbers Solid and Liquid Fueled  Strap-On Boosters.  Flight proven components of the H-IIA series are also being used on the H-IIB Heavy Lift Launch Vehicle that is being used for International Space Station Resupply Mission using the H-II Transfer Vehicle

First and second stage use liquid Hydrogen and liquid Oxygen as propellants. The Launcher can lift payloads of up to 11,000 kilograms to Low Earth Orbit. Sun Synchronous orbit and GTO Capabilities are about 4,000 Kilograms. First stage is powered by One LE-7A Engine with a total thrust of 1,078 Kilonewtons.After engine ignition, the main engine is monitored for several seconds and good  performance is verified before the vehicle is released and lifts off. The H-IIA Launcher has two or four  Solid Rocket Boosters that are ignited on the Ground and provide an additional amount of thrust for the first portion of the ascent.  SRB-A Boosters burn for the first 100 seconds of the flight and are jettisoned 10 seconds after burnout. One,engine powers the vehicle during second stage flight. The Engine is 2.79 meters in Diameter and has a nozzle diameter of 2.49 meters. LE-5B provides 137 Kilonewtons of thrust. It has a nominal burn time of 530 seconds, but is certified to burn for up to 40 minutes. The engine can support up to 16 re-starts.