About: S5.142

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The S5.142 (AKA DST-25) 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 was used in KTDU-80 propulsion module from the Soyuz-TM to the Soyuz-TMA-M, as the low thrust thruster (DPO-M). As of the Soyuz MS, KTDU-80 does not use DPO-M anymore.

Attributes	Values
rdfs:label	S5.142 (ja) S5.142 (en) S5.142 (pt)
rdfs:comment	S5.142 (別名 DST-25)はN2O4/UDMHをO/F1.85で燃焼する液体加圧供給式ロケットエンジンである。有人宇宙船の推進器として使用される。現在は宇宙船の推進モジュールであるの低推力推進器(DPO-M)として装備される。S5.142は25 N (5.6 lbf)の推力を燃焼室圧力0.88 MPa (128 psi)で生み出し、ノズル膨張比が45で到達比推力は285秒 (2.79 km/s)である。 300,000回の始動と累計燃焼時間25,000秒が可能で1回の燃焼は0.03秒から4,000秒までである。それぞれのユニットの重量は0.9 kg (2.0 lb)である。 (ja) O S5.142 (também conhecido como DST-25), é um motor de foguete a combustível líquido queimando N2O4/UDMH. Ele é usado para efetuar manobras em espaçonaves tripuladas, fazendo parte do módulo de propulsão das espaçonaves: Soyuz-TMA-M, Soyuz TM e Soyuz MS. (pt) The S5.142 (AKA DST-25) 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 was used in KTDU-80 propulsion module from the Soyuz-TM to the Soyuz-TMA-M, as the low thrust thruster (DPO-M). As of the Soyuz MS, KTDU-80 does not use DPO-M anymore. (en)
foaf:homepage	http://kbhmisaeva.ru/main.php%3Fid=53
name	S5.142 (en)
dcterms:subject	KB KhimMash rocket engines Rocket engines of Russia Rocket engines using hypergolic propellant Rocket engines using the pressure-fed cycle
Wikipage page ID	47398222 (xsd:integer)
Wikipage revision ID	1107633104 (xsd:integer)
Link from a Wikipage to another Wikipage	Human spaceflight Unsymmetrical dimethylhydrazine Attitude control system KB KhIMMASH Pressure-fed engine KB KhimMash rocket engines Rocket engines of Russia Rocket engines using hypergolic propellant Rocket engines using the pressure-fed cycle Russia Angara (rocket family) Soyuz-TMA Liquid-propellant rocket KTDU-80 Spacecraft propulsion Soyuz-TM KVTK (rocket stage) Dinitrogen tetroxide Soyuz MS Soyuz TM-23 Specific impulse Rocket propellant Rocket engine Russian space program Soyuz-TMA-M
Link from a Wikipage to an external page	http://kbhmisaeva.ru/main.php%3Fid=53
sameAs	S5.142 S5.142 S5.142 S5.142 S5.142
dbp:wikiPageUsesTemplate	dbt:Convert dbt:Infobox_rocket_engine dbt:Orbital_spacecraft_rocket_engines dbt:Reflist dbt:Rocket-stub
combustion chamber	1 (xsd:integer)
country of origin	Russia
cycle	Pressure-fed engine
date	1990 (xsd:integer)
designer	KB KhIMMASH
first date	1996-02-21 (xsd:date)
fuel	Unsymmetrical dimethylhydrazine
mixture ratio	1.850000 (xsd:double)
oxidiser	Dinitrogen tetroxide
predecessor	11 (xsd:integer)
purpose	attitude control thruster (en)
restarts	300000 (xsd:integer)
status	Retired (en)
type	liquid (en)
used in	KTDU-80
has abstract	The S5.142 (AKA DST-25) 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 was used in KTDU-80 propulsion module from the Soyuz-TM to the Soyuz-TMA-M, as the low thrust thruster (DPO-M). As of the Soyuz MS, KTDU-80 does not use DPO-M anymore. The S5.142 generates 25 N (5.6 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 45 that enables it to achieve a specific impulse of 285 s (2.79 km/s). It is rated for 300,000 starts with a total firing time of 25,000 seconds and can do single burns from 0.03 seconds to 4,000 seconds. Each unit weights 0.9 kg (2.0 lb). (en) S5.142 (別名 DST-25)はN2O4/UDMHをO/F1.85で燃焼する液体加圧供給式ロケットエンジンである。有人宇宙船の推進器として使用される。現在は宇宙船の推進モジュールであるの低推力推進器(DPO-M)として装備される。S5.142は25 N (5.6 lbf)の推力を燃焼室圧力0.88 MPa (128 psi)で生み出し、ノズル膨張比が45で到達比推力は285秒 (2.79 km/s)である。 300,000回の始動と累計燃焼時間25,000秒が可能で1回の燃焼は0.03秒から4,000秒までである。それぞれのユニットの重量は0.9 kg (2.0 lb)である。 (ja) O S5.142 (também conhecido como DST-25), é um motor de foguete a combustível líquido queimando N2O4/UDMH. Ele é usado para efetuar manobras em espaçonaves tripuladas, fazendo parte do módulo de propulsão das espaçonaves: Soyuz-TMA-M, Soyuz TM e Soyuz MS. (pt)
burn time	25000.0 (second)
nozzle ratio	45 (xsd:integer)
gold:hypernym	UDMH
prov:wasDerivedFrom	wikipedia-en:S5.142?oldid=1107633104&ns=0
page length (characters) of wiki page	5601 (xsd:nonNegativeInteger)
foaf:isPrimaryTopicOf	wikipedia-en:S5.142
is Link from a Wikipage to another Wikipage of	A.M. Isayev Chemical Engineering Design Bureau KTDU-80
is foaf:primaryTopic of	wikipedia-en:S5.142

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