About: Descent propulsion system

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The descent propulsion system (DPS - pronounced 'dips') or lunar module descent engine (LMDE), internal designation VTR-10, is a variable-throttle hypergolic rocket engine invented by Gerard W. Elverum Jr. and developed by Space Technology Laboratories (TRW) for use in the Apollo Lunar Module descent stage. It used Aerozine 50 fuel and dinitrogen tetroxide (N2O4) oxidizer. This engine used a pintle injector, which paved the way for other engines to use similar designs.

Attributes	Values
rdfs:label	Descent propulsion system (en) Descent Propulsion System (in) 月着陸船用下降エンジン (ja) Descent Propulsion System (pt)
rdfs:comment	The descent propulsion system (DPS - pronounced 'dips') or lunar module descent engine (LMDE), internal designation VTR-10, is a variable-throttle hypergolic rocket engine invented by Gerard W. Elverum Jr. and developed by Space Technology Laboratories (TRW) for use in the Apollo Lunar Module descent stage. It used Aerozine 50 fuel and dinitrogen tetroxide (N2O4) oxidizer. This engine used a pintle injector, which paved the way for other engines to use similar designs. (en) Descent Propulsion System (DPS) atau LMDE (Lunar Modul Descent Mesin) adalah sebuah mesin roket throttle hypergolic variabel yang dikembangkan oleh Laboratorium Teknologi Ruang Angkasa (TRW) untuk digunakan dalam Apollo Lunar Module Descent Stage. Mesin ini menggunakan Aerozine 50 bahan bakar dan N2O4 oksidator. Mesin ini menggunakan injektor pintle, desain juga digunakan kemudian dalam mesin SpaceX Merlin. (in) 月着陸船用下降エンジン（LMDE、Lunar Module Descent Engine）または DPS（Descent Propulsion System）は、（STL）によってアポロ月着陸船向けに開発された、ハイパーゴリック推進剤を用いた推力可変式ロケットエンジンである。 (ja) O Descent Propulsion System (DPS) ou Lunar Module Descent Engine (LMDE) é um motor de foguete hipergólico de empuxo variável, desenvolvido pela Space Technology Laboratories para uso no estágio de descida do Módulo Lunar Apollo. Ele usava Aerozine 50 como combustível, e tetróxido de nitrogênio (N2O4) como oxidante. Esse motor usava um injetor com pino exclusivo, um desenho que mais tarde seria usado também no motor Merlin da SpaceX. (pt)
name	Descent propulsion system (en)
foaf:depiction
dcterms:subject	TRW Inc. Rocket engines Rocket engines using hypergolic propellant Rocket engines using the pressure-fed cycle Apollo program hardware
Wikipage page ID	35997160 (xsd:integer)
Wikipage revision ID	1122187759 (xsd:integer)
Link from a Wikipage to another Wikipage	Robert R. Gilruth Delta-P Delta 2000 TRW Inc. Joseph Francis Shea Nozzle extension Rocket engines Rocket engines using hypergolic propellant Rocket engines using the pressure-fed cycle Cryogenic Maxime Faget Lyndon B. Johnson Space Center Gimballed thrust Pintle injector Apollo 13 Apollo 15 Apollo 9 Apollo Lunar Module Delta 1000 Delta 3000 Supercritical fluid TRW Inc. Apollo program hardware Helium AS-201 Aircraft principal axes Hypergolic propellant United Aircraft Aerojet Aerozine 50 TR-201 Throttle Dinitrogen tetroxide Hypergolic Apollo Service Module Thiokol Lunar module Turbopump Rocketdyne Rocket engine Pressure-fed engine (rocket) Service Propulsion System Pericynthion
Link from a Wikipage to an external page	http://www.cbtsresidents.com/Spectrum/donharvey1.htm https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20090016298.pdf https://ntrs.nasa.gov/api/citations/19730011150/downloads/19730011150.pdf
sameAs	Descent propulsion system Descent propulsion system Descent propulsion system Descent propulsion system Descent propulsion system
specific impulse vacuum	(en)
throttle range	10 (xsd:integer)
thrust to weight	25.700000 (xsd:double)
dbp:wikiPageUsesTemplate	dbt:Chem dbt:Convert dbt:Infobox_rocket_engine dbt:Orbital_spacecraft_rocket_engines dbt:Reflist dbt:Rp dbt:Short_description dbt:Apollo_program_hardware dbt:TRW
thumbnail	wiki-commons:Special:FilePath/Apollo_15_Engine_Bell.jpg?width=300
combustion chamber	1 (xsd:integer)
country of origin	United States (en)
cycle	Pressure-fed engine (rocket)
date	1964 (xsd:integer)
designer	Gerard W. Elverum Jr. (en)
diameter	(en) 63.0 (inch) 59.0 (inch)
fuel	Aerozine 50
length	(en) 100.0 (inch) 85.0 (inch)
manufacturer	TRW Inc.
mixture ratio	1.600000 (xsd:double)
oxidiser	Dinitrogen tetroxide
predecessor	None (en)
purpose	Lunar descent stage propulsion (en)
restarts	Designed for 2 restarts, has been (en)

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