About: LE-7

Facets (new session)
Description
Metadata
Settings
- Rule:
- Inverse Functional Properties:
- "Same As":

About: LE-7 Goto Sponge NotDistinct Permalink

An Entity of Type : yago:Whole100003553, within Data Space : dbpedia.demo.openlinksw.com associated with source document(s)
QRcode icon

http://dbpedia.demo.openlinksw.com/describe/?url=http%3A%2F%2Fdbpedia.org%2Fresource%2FLE-7&invfp=IFP_OFF&sas=SAME_AS_OFF

The LE-7 and its succeeding upgrade model the LE-7A are staged combustion cycle LH2/LOX liquid rocket engines produced in Japan for the H-II series of launch vehicles. Design and production work was all done domestically in Japan, the first major (main/first-stage) liquid rocket engine with that claim, in a collaborative effort from the National Space Development Agency (NASDA), Aerospace Engineering Laboratory (NAL), Mitsubishi Heavy Industries, and Ishikawajima-Harima. NASDA and NAL have since been integrated into JAXA. However, a large part of the work was contracted to Mitsubishi, with Ishikawajima-Harima providing turbomachinery, and the engine is often referred to as the Mitsubishi LE-7(A).

Attributes	Values
rdf:type	yago:WikicatRocketEngines yago:WikicatRocketEnginesUsingHydrogenPropellant yago:Artifact100021939 yago:Device103183080 yago:Engine103287733 yago:Instrumentality103575240 yago:JetEngine103596285 yago:Machine103699975 yago:Motor103789946 yago:Object100002684 yago:PhysicalEntity100001930 yago:Reaction-propulsionEngine104057435 yago:Rocket104099175 yago:Whole100003553
rdfs:label	LE-7 (in) LE-7 (fr) LE-7 (en) LE-7 (ja) 미쓰비시 LE-7 (ko) LE-7火箭发动机 (zh)
rdfs:comment	Le LE-7 est un moteur-fusée à ergols liquides japonais brûlant le mélange cryogénique hydrogène/oxygène développé pour propulser le premier étage des lanceurs H-IIA et H-IIB. Il s'agit du premier moteur de cette puissance développé par l'industrie spatiale japonaise. Sa poussée dans le vide est de 1078 kN et il est de type à combustion étagée. (fr) LE-7 dan LE-7A adalah sebuah mesin roket cair, menggunakan pembakaran siklus LH2/LOX yang diproduksi di Jepang untuk seri kendaraan peluncuran H-II. Desain kerja dan produksi semua dilakukan di dalam negeri di Jepang, merupakan mesin roket cair tahap pertama, dalam upaya kolaborasi dari National Space Development Agency (NASDA), Aerospace Engineering Laboratory (NAL), Mitsubishi Heavy Industries, dan Ishikawajima-Harima. NASDA dan NAL telah lama sejak diintegrasikan ke JAXA. (in) LE-7エンジンは、宇宙開発事業団（NASDA）が航空宇宙技術研究所（NAL）、三菱重工業、石川島播磨重工業と共に開発したH-IIロケットの第1段用液体ロケットエンジン。日本初の第1段用液体ロケットエンジンである。現在は、LE-7の設計を元にコストダウンと信頼性向上を図ったLE-7AエンジンがH-IIAロケットおよびH-IIBロケットの一段目に使用されている。 (ja) 미쓰비시 LE-7은 1994년에 일본 미쓰비시 중공업과 IHI와 JAXA의 이전의 조직 와 가 개발한 진공추력 110톤, 비추력 446초의 액체연료 로켓엔진이다. 2000년에 LE-7을 개량한 LE-7A가 개발되었다. (ko) LE-7火箭发动机及其改进型LE-7A是日本为H2火箭系列制造的液態氢氧发动机。是第一种第一级主引擎。设计研发工作都在日本国内进行，由日本國家太空開發機構(NASDA)，航空宇宙技術研究所(NAL)，三菱重工和合力完成。NASDA和NAL已经合并为JAXA。设计主要由三菱重工完成，石川岛播磨提供涡轮泵。因为该发动机也称为“三菱重工 LE-7(A)”。 LE-7的设计初衷是为H2火箭研制一个不可重用的高效中等尺寸发动机。 (zh) The LE-7 and its succeeding upgrade model the LE-7A are staged combustion cycle LH2/LOX liquid rocket engines produced in Japan for the H-II series of launch vehicles. Design and production work was all done domestically in Japan, the first major (main/first-stage) liquid rocket engine with that claim, in a collaborative effort from the National Space Development Agency (NASDA), Aerospace Engineering Laboratory (NAL), Mitsubishi Heavy Industries, and Ishikawajima-Harima. NASDA and NAL have since been integrated into JAXA. However, a large part of the work was contracted to Mitsubishi, with Ishikawajima-Harima providing turbomachinery, and the engine is often referred to as the Mitsubishi LE-7(A). (en)
name	LE-7 (en)
foaf:depiction
dcterms:subject	Rocket engines of Japan Rocket engines using the staged combustion cycle Rocket engines using hydrogen propellant
Wikipage page ID	15496163 (xsd:integer)
Wikipage revision ID	1082384756 (xsd:integer)
Link from a Wikipage to another Wikipage	Multistage rocket LE-5 Nozzle Vibration LH2 Comparison of orbital rocket engines Mitsubishi Heavy Industries Computational fluid dynamics Fatigue (material) Welding Rocket engines of Japan Gimbal Liquid-propellant rocket Cavitation H-II H-IIA H-IIB Actuators JAXA Japan Propellant Rocket engines using the staged combustion cycle Rocket engines using hydrogen propellant LE-9 Staged combustion cycle (rocket) Booster (rocketry) IHI Corporation Casting Regenerative cooling (rocket) Expendable launch system LOX Turbomachinery Turbopump Axial flow pump Liquid rocket Machined Turbopumps
Link from a Wikipage to an external page	https://web.archive.org/web/20020626171141/http:/www.astronautix.com/engines/le7.htm https://web.archive.org/web/20021018023043/http:/www.astronautix.com/engines/le7a.htm http://www.jaxa.jp/projects/rockets/h2a/f8/img/h-2af8.pdf http://www.mhi.co.jp/tech/pdf/e392/e392051.pdf
sameAs	LE-7 LE-7 LE-7 LE-7 LE-7 LE-7 LE-7 LE-7 LE-7 LE-7
thrust to weight	64.130000 (xsd:double)
dbp:wikiPageUsesTemplate	dbt:Commons_category dbt:Convert dbt:Dead_link dbt:Infobox_rocket_engine dbt:Reflist dbt:Rocket_engines dbt:Short_description dbt:Sub
thumbnail	wiki-commons:Special:FilePath/LE-7_rocket_engine.jpg?width=300
bot	InternetArchiveBot (en)
caption	LE-7, Nagoya City Science Museum, 2006 (en)
combustion chamber	1 (xsd:integer)
country of origin	Japan

Faceted Search & Find service v1.17_git139 as of Feb 29 2024

Alternative Linked Data Documents: ODE Content Formats:

RDF

ODATA

Microdata

About

OpenLink Virtuoso version 08.03.3330 as of Mar 19 2024, on Linux (x86_64-generic-linux-glibc212), Single-Server Edition (378 GB total memory, 58 GB memory in use)
Data on this page belongs to its respective rights holders.
Virtuoso Faceted Browser Copyright © 2009-2024 OpenLink Software