LE-5B
LE-5B
Designer: Mitsubishi. Developed in: 1995-2001. Propellants: Lox/LH2. Thrust(vac): 137.000 kN (30,798 lbf). Isp: 447 sec. Burn time: 534 sec. Mass Engine: 269 kg (593 lb). Length: 2.78 m (9.13 ft). Chambers: 1. Chamber Pressure: 36.00 bar. Area Ratio: 110.00. Oxidizer to Fuel Ratio: 5.00. Country: Japan. Status: In production. First Flight: 2001. Last Flight: 2006. Flown: 10.

The LE-5B rocket engine, developed for the second stage of the H-II rocket, was an improved model of the LE-5A. It used hydrogen for the cooling of the thrust chamber, then as the gas to drive the turbine. The result was a simplified, lower cost version of the LE-5A using an expander bleed cycle turbopump. The engine could be throttled to 5% idle mode.

LE-5B used on Rocket Stages

Bibliography and Further Reading
  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...
 
 
 
 
 
 
 
 
 
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