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The H3 is the world's first rocket to use an expander bleed cycle for the first stage engine. [ 5 ] As of July 2015 [update] , the minimum configuration is to carry a payload of up to 4,000 kg (8,800 lb) into Sun-synchronous orbit (SSO) for about 5 billion yen , and the maximum configuration is to carry more than 6,500 kg (14,300 lb) into ...
The LE-9 is a liquid cryogenic rocket engine burning liquid hydrogen and liquid oxygen in an expander bleed cycle. Two or three will be used to power the core stage of the H3 launch vehicle. [1] [2] [5] The newly developed LE-9 engine is the most important factor in achieving cost reduction, improved safety and increased thrust.
Kakehashi, Faulty brazing in second-stage engine cooling system caused engine burn through and cable damage resulting in shutdown midway through the upper stage's second burn, leaving spacecraft in elliptical LEO instead of GTO. Spacecraft thrusters raised orbit enough to complete some communications experiments. F8 15 November 1999 07:29 H-II
As the successor to Japan’s H-2A and H-2B rockets, the H3 is designed to be more economical by using commercial off-the-shelf products, rather than exclusive aerospace components, according to JAXA.
JAXA's 63 m (297 ft) H3 rocket can carry a 6.5 ton payload into space, more than H-IIA's maximum of 6 tons, and fly more cheaply by adopting simpler structures and automotive-grade electronics.
The SRB-3 used in the H3 and Epsilon S rockets has one ton more propellant than the SRB-A series to increase its launch capability. To improve reliability and reduce cost, the separation mechanism of the SRB-3 has been greatly simplified compared to the SRB-A series, and the nozzle has been changed from a variable type to a fixed type.
TOKYO (Reuters) -Japan successfully launched its new H3 flagship rocket on Saturday, putting its space programme back on track after multiple setbacks including the failure of the rocket's ...
The LE-5 liquid rocket engine and its derivative models were developed in Japan to meet the need for an upper stage propulsion system for the H-I and H-II series of launch vehicles. It is a bipropellant design, using LH 2 and LOX. Primary design and production work was carried out by Mitsubishi Heavy Industries. [1]