LE-5

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 LH₂ and LOX. Primary design and production work was carried out by Mitsubishi Heavy Industries. In terms of liquid rockets, it is a fairly small engine, both in size and thrust output, being in the 89 kN (20,000 lbf) and the more recent models the 130 kN (30,000 lbf) thrust class. The motor is capable of multiple restarts, due to a spark ignition system as opposed to the single use pyrotechnic or hypergolic igniters commonly used on some contemporary engines. Though rated for up to 16 starts and 40+ minutes of firing time, on the H-II the engine is considered expendable, being used for one flight and jettisoned. It is sometimes started only once for a nine-minute burn, but in missions to GTO the engine is often fired a second time to inject the payload into the higher orbit after a temporary low Earth orbit has been established.

MainWikipediaGalleryBibliographyTableSearch

Wikimedia, Wikidata
cryogenic rocket engine, 
Ashkenaz, Calvinist Republic of Ghent, Chinland, Democratic Republic of the Congo, Havilah, Kingdom of Martabam-hongsawatoi, Kingdom of Wolaita, Persia, Sikh Confederacy, Sweden, Tarshish, cryogenic rocket engine, Dong Fang Hong 2, Ekran, 

​

Location: KML, Cluster Map, Maps,

Frameless

LE-5

JAXA Jet engine 1

S-160JA-1 Rocket

LE-5 engine

LE-5 engine - National Museum of Nature and Science, Tokyo - DSC07393

Type	Subtype	Date	Description	Notes	Source
commons	image		LE-5		Commons
commons	image		JAXA Jet engine 1		Commons
commons	image		S-160JA-1 Rocket		Commons
commons	image		LE-5 engine		Commons
commons	image		LE-5 engine - National Museum of Nature and Science, Tokyo - DSC07393		Commons