About: S5.80

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The S5.80 is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the Soyuz-TMA-M spacecraft propulsion module KTDU-80, and its sibling, the S5.79 rocket engine, is still used as the main propulsion of the Zvezda ISS module.The S5.80 generates 2.95 kN (660 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a specific impulse of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds. The engine, without the pressurization system or propellant tanks, weighs 310 kg (680 lb) and is an integrated unit that is 1.2 m (47 in) long with a diameter of 2.1 m (83 in).

Attributes	Values
rdfs:label	S5.80 (en) S5.80 (pt)
rdfs:comment	The S5.80 is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the Soyuz-TMA-M spacecraft propulsion module KTDU-80, and its sibling, the S5.79 rocket engine, is still used as the main propulsion of the Zvezda ISS module.The S5.80 generates 2.95 kN (660 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a specific impulse of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds. The engine, without the pressurization system or propellant tanks, weighs 310 kg (680 lb) and is an integrated unit that is 1.2 m (47 in) long with a diameter of 2.1 m (83 in). (en) O S5.80 é um motor de foguete a combustível líquido queimando N2O4/UDMH. Ele é usado para efetuar manobras em espaçonaves tripuladas. Ele é usado atualmente no módulo de propulsão da espaçonave Soyuz-TMA-M e no módulo Zvezda da ISS. (pt)
foaf:homepage	http://kbhmisaeva.ru/main.php%3Fid=53
name	S5.80 (en)
dcterms:subject	KB KhimMash rocket engines Rocket engines of Russia Rocket engines of the Soviet Union Rocket engines using hypergolic propellant Rocket engines using the pressure-fed cycle
Wikipage page ID	47376249 (xsd:integer)
Wikipage revision ID	1084022776 (xsd:integer)
Link from a Wikipage to another Wikipage	Progress (spacecraft) Progress-M Human spaceflight Unsymmetrical dimethylhydrazine KB KhIMMASH Pressure-fed engine KB KhimMash rocket engines Rocket engines of Russia Rocket engines of the Soviet Union Rocket engines using hypergolic propellant Rocket engines using the pressure-fed cycle Zvezda (ISS module) Soyuz-TMA USSR Liquid-propellant rocket Mir Core Module KTDU-426 KTDU-80 Reaction control system International Space Station Spacecraft propulsion Soyuz-TM KTDU-35 Dinitrogen tetroxide Pirs (ISS module) Poisk (ISS module) Soviet space program Soyuz TM-1 Specific impulse S.P. Korolev Rocket and Space Corporation Energia Rocket propellant Soyuz (spacecraft) Soyuz-T Salyut programme Rocket engine Salyut 6 Salyut-6 Salyut-7 Russian space program Soyuz-TMA-M
Link from a Wikipage to an external page	http://kbhmisaeva.ru/main.php%3Fid=53
sameAs	S5.80 S5.80 S5.80 S5.80 S5.80
dbp:wikiPageUsesTemplate	dbt:Convert dbt:Infobox_rocket_engine dbt:Orbital_spacecraft_rocket_engines dbt:Reflist
combustion chamber	1 (xsd:integer)
country of origin	USSR
cycle	Pressure-fed engine
date	1977 (xsd:integer)
designer	OKB-2, Anton Tavzarachvili (en)
first date	1986-05-21 (xsd:date)
fuel	Unsymmetrical dimethylhydrazine
mixture ratio	1.850000 (xsd:double)
oxidiser	Dinitrogen tetroxide
predecessor	11 (xsd:integer)
purpose	Spacecraft main propulsion (en)
restarts	30 (xsd:integer)
status	In Production (en)
type	liquid (en)
used in	Soyuz since Soyuz-TM and Progress since Progress-M (en)
has abstract	The S5.80 is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the Soyuz-TMA-M spacecraft propulsion module KTDU-80, and its sibling, the S5.79 rocket engine, is still used as the main propulsion of the Zvezda ISS module.The S5.80 generates 2.95 kN (660 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a specific impulse of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds. The engine, without the pressurization system or propellant tanks, weighs 310 kg (680 lb) and is an integrated unit that is 1.2 m (47 in) long with a diameter of 2.1 m (83 in). (en) O S5.80 é um motor de foguete a combustível líquido queimando N2O4/UDMH. Ele é usado para efetuar manobras em espaçonaves tripuladas. Ele é usado atualmente no módulo de propulsão da espaçonave Soyuz-TMA-M e no módulo Zvezda da ISS. (pt)
burn time	890.0 (second)
gimbal	±5° (en)
nozzle ratio	153.800000 (xsd:double)
gold:hypernym	UDMH
prov:wasDerivedFrom	wikipedia-en:S5.80?oldid=1084022776&ns=0
page length (characters) of wiki page	10538 (xsd:nonNegativeInteger)
foaf:isPrimaryTopicOf	wikipedia-en:S5.80
is Link from a Wikipage to another Wikipage of	11D426 A.M. Isayev Chemical Engineering Design Bureau KTDU-80 S5.79 KRD-79
is Wikipage redirect of	11D426 S5.79 KRD-79
is foaf:primaryTopic of	wikipedia-en:S5.80

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