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titanium fuel turbopump uses a two-stage pump with inducer and is actuated by a two-stage axial turbine. It rotates at 35,000 rpm and supplies a discharge pressure of 16.5 MPa (2,390 psi). The oxidizer turbopump uses a single-stage centrifugal pump with a helical inducer driven by a two-stage turbine. It rotates at 18,000 rpm and supplies a discharge pressure of 14 MPa (2,000 psi).
27:
328:
In May 2013 the formal qualification testing campaign began. By the end of 2013 more than 70 tests and 24,000 seconds of firing at steady state conditions had been performed by 12 engines. The concept review confirmed that the performance goal and launcher requirements were met, and the engine was
369:
All subsystems are attached to the combustion chamber and gimbal is achieved by rotating the whole engine on two orthogonal planes with two independent actuators. The injector plate uses coaxial injectors, some of which are extended to create baffles that prevent high frequency instabilities. The
345:
The requirements for an inexpensive, highly reliable, disposable engine are met by using dual 510 kN (110,000 lbf) (sea level) gas generator engines on a single mounting frame. Each engine has dual turbopumps with separate gas exhaust. Both turbines are fed by a single fuel rich gas
321:. The preliminary design was accomplished by mid-2002 and the first set of components was manufactured by early 2003. The same year saw the initial component and subsystem tests, with the gas generator successfully performing its first test on July 30. By December 2003 the whole
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in two planes. Although the YF-77 is ignited prior to liftoff, the LM-5's four strap-on boosters provide most of the initial thrust in an arrangement similar to the
European
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and a propellant utilization valve on ground tests. The engine also has dual heat exchanger to supply hot gaseous hydrogen and oxygen for tank pressurization.
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successfully passed its first integrated test, and on
September 17, 2004 a successful 50-second firing of a complete prototype engine was achieved.
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354:. The turbopumps use solid propellant cartridges for start-up, while the gas generator and combustion chamber use
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317:. The development responsibility was assigned to the Beijing Aerospace Propulsion Institute, a division of the
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398:"Development Status of the Cryogenic Oxygen/Hydrogen YF-77 Engine for Long-March 5"
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337:(CNSA) commencing in 2005. The engine has been successfully tested by mid-2007.
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In
January 2002, the development of a new cryogenic engines was approved by the
531:] (in Chinese). Shanghai: Shanghai Science Technology and Education Press.
359:
546:
529:
Divine Arrow
Crosses the Sky: Development History of Long March Rocket Series
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rocket. Engine development began in the 2000s, with testing directed by the
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1932:* Different versions of the engine use different propellant combinations
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Commission for
Science, Technology and Industry for National Defense
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Wang, Weibin; Zheng, Dayong; Qiaot, Guiyu (2013-09-23).
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346:generator. The combustion chambers and throat are
329:ready for integration for the first launch of the
319:Academy of Aerospace Liquid Propulsion Technology
57:Academy of Aerospace Liquid Propulsion Technology
358:. The valves and prevalves are helium-actuated
584:
269:developed for booster applications. It burns
8:
483:: CS1 maint: multiple names: authors list (
431:"The Development of LOX/LH2 Engine in China"
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285:core stage. Each engine can independently
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281:cycle. A pair of these engines powers the
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1961:Rocket engines using hydrogen propellant
466:(in Simplified Chinese). 《火箭推进》2022年02期
379:
222:2,600 mm (100 in) (with rack)
476:
442:International Astronautical Federation
409:International Astronautical Federation
72:
18:
7:
622:Comparison of orbital rocket engines
335:China National Space Administration
523:Chen, Minkang; Ru, Jiaxin (2007).
14:
1633:
201:316.7 seconds (3.106 km/s)
190:428.0 seconds (4.197 km/s)
499:"Chang Zheng-5 (Long March-5)"
462:孙纪国,郑孟伟,龚杰峰,陶瑞峰 (2022-01-15).
179:10.1 MPa (1,460 psi)
168:518 kN (116,000 lbf)
160:700 kN (160,000 lbf)
1:
1418:RD-0202 to 0206, 0208 to 0213
501:. SinoDefence. Archived from
46:Long March 5 inaugural flight
209:525 seconds (8.75 min)
1982:
230:1,500 mm (59 in)
1928:
1631:
617:
440:. IAC-13-C4.1 (1x18525).
429:Nan, Zhang (2013-09-23).
407:. IAC-13-C4.1 (2x17679).
239:
24:
1966:Rocket engines of China
1463:RD-250 to 252, 261, 262
525:神箭凌霄 : 长征系列火箭的发展历程
267:cryogenic rocket engine
1939:are under development
1327:YF-20, 21, 22, 24, 25
1106:RD-107, 108, 117, 118
348:regeneratively cooled
341:Technical description
16:Chinese rocket engine
464:"220tf补燃循环氢氧发动机研制进展"
356:pyrotechnic igniters
1428:RD-0216, 0217, 0235
1091:RD-0107, 0108, 0110
564:Space Launch Report
21:
93:Liquid-fuel engine
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34:Country of origin
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185:Specific impulse
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280:
279:gas generator
276:
275:liquid oxygen
272:
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138:
134:
131:Configuration
129:
126:
125:Gas-generator
123:
119:
115:
113:Mixture ratio
111:
108:
104:
103:Liquid oxygen
101:
97:
94:
90:
86:
82:
79:
76:
69:
65:
61:
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47:
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36:
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28:
23:
1948:
1936:
1477:
1398:North Korea
1169:
1162:
1130:
1058:
1046:
1039:
1017:
966:
959:
947:
935:
928:
921:
899:
892:
885:
868:
861:
854:
798:
791:
779:
757:
700:
693:
688:
604:solid motors
528:
524:
518:
507:. Retrieved
503:the original
493:
468:. Retrieved
457:
446:. Retrieved
437:
424:
413:. Retrieved
404:
368:
352:dump cooling
344:
331:Long March 5
327:
312:
262:
260:
241:Long March 5
144:Nozzle ratio
78:Long March 5
48:(2016-11-03)
42:First flight
1935:Engines in
1582:RD-109, 119
1520:RD-864, 869
1505:RD-854, 861
1468:RD-253, 275
1116:RD-170, 171
360:ball valves
309:Development
243:core stage.
198:, sea-level
152:Performance
71:Associated
63:Application
1955:Categories
1322:YF-1, 2, 3
1270:Hypergolic
1242:Rutherford
961:Prometheus
923:Archimedes
509:2015-07-02
470:2022-06-05
448:2015-07-02
415:2015-07-02
374:References
253:References
248:References
214:Dimensions
99:Propellant
87:In service
1863:Castor 30
1743:Zefiro 40
1738:Zefiro 23
1679:SpaB-140C
1076:NK-33, 44
986:cryogenic
832:Methalox
651:Hydrolox
643:Cryogenic
547:223362195
323:powerpack
273:fuel and
206:Burn time
1878:Orbus-21
1733:Zefiro 9
1496:Ukraine
1274:Aerozine
1262:Storable
1154:Ukraine
1096:RD-0110R
993:Kerolox
479:cite web
364:venturis
295:Ariane 5
227:Diameter
187:, vacuum
175:pressure
173:Chamber
53:Designer
1937:italics
1898:Star 48
1893:Star 37
1873:Orbus-6
1794:Israel
1728:Waxwing
1684:Europe
1676:SpaB-65
1578:Russia
1443:RD-0237
1438:RD-0236
1409:Russia
1388:Israel
1348:Europe
1192:Kestrel
1138:S1.5400
1101:RD-0124
1067:Russia
1060:SCE-200
956:Europe
949:RD-0169
944:Russia
870:Longyun
863:Lingyun
781:RD-0146
775:RD-0120
766:Russia
723:Vulcain
709:Europe
632:Liquid
608:orbital
301:on the
293:on the
291:Vulcain
235:Used in
136:Chamber
1853:AJ-60A
1818:KM-V2b
1809:Japan
1783:Salman
1749:India
1723:Topaze
1688:Mage 1
1653:China
1644:Solid
1551:TR-201
1515:RD-856
1510:RD-855
1500:RD-843
1490:S5.98M
1479:RD-270
1373:India
1367:Viking
1357:Astris
1352:Aestus
1342:YF-50D
1318:China
1227:RS-27A
1217:Merlin
1207:LR-105
1171:RD-810
1164:RD-801
1148:TEPREL
1144:Spain
1132:RD-193
1121:RD-180
1111:RD-120
1055:India
1048:Welkin
1041:YF-130
1035:YF-115
1030:YF-102
1025:YF-100
1009:China
937:Aeon R
930:Aeon 1
917:Raptor
901:YF-215
894:YF-209
887:TQ-15A
851:China
744:Japan
733:CE-7.5
729:India
684:YF-75D
670:China
545:
535:
287:gimbal
219:Length
84:Status
1918:X-254
1913:X-248
1903:UA120
1883:Orion
1858:Algol
1843:SRB-A
1838:M-34c
1813:KM-V1
1803:RSA-3
1779:Iran
1672:FG-47
1667:FG-46
1662:FG-36
1657:FG-02
1618:XLR81
1612:RS-88
1607:Curie
1597:Gamma
1572:Other
1556:XLR81
1545:RS-88
1540:LR-91
1535:LR-87
1485:S5.92
1413:17D61
1382:Vikas
1362:Vexin
1337:YF-40
1332:YF-23
1305:, or
1285:, or
1279:UH 25
1247:XLR50
1232:RS-56
1222:RS-27
1202:LR-89
1197:LR-79
1081:RD-58
1071:NK-15
1019:TH-12
1013:TH-11
984:Semi-
881:TQ-12
876:TQ-11
856:BF-20
821:RS-68
816:RS-25
793:BE-3U
738:CE-20
718:Vinci
702:YF-90
695:YF-79
689:YF-77
679:YF-75
674:YF-73
527:[
434:(pdf)
401:(pdf)
263:YF-77
121:Cycle
37:China
20:YF-77
1908:SRMU
1833:M-34
1828:M-24
1823:M-14
1798:LK-1
1788:Rafe
1773:S200
1768:S139
1718:P230
1713:P120
1646:fuel
1530:AJ10
1392:LK-4
1287:UDMH
1237:S-3D
1158:RD-8
997:RP-1
968:M-10
912:BE-4
811:RL10
800:BE-7
759:LE-9
753:LE-7
748:LE-5
713:HM7B
634:fuel
606:for
602:and
543:OCLC
533:ISBN
485:link
303:H-II
299:LE-7
283:LM-5
261:The
1868:GEM
1763:S12
1708:P80
1703:PAP
1698:P-6
1693:P-4
1593:UK
1377:PS4
1307:HNO
1303:MON
1283:MMH
1187:H-1
1182:F-1
1001:LOX
843:LOX
806:J-2
662:LOX
444:: 5
411:: 7
1957::
1758:S9
1753:S7
1301:,
1290:/
1281:,
1276:,
999:/
841:/
836:CH
660:/
655:LH
541:.
481:}}
477:{{
436:.
403:.
382:^
305:.
147:49
105:/
73:LV
1620:*
1614:*
1558:*
1547:*
1312:)
1309:3
1298:4
1296:O
1294:2
1292:N
1272:(
1003:)
995:(
845:)
838:4
834:(
664:)
657:2
653:(
592:e
585:t
578:v
549:.
512:.
487:)
473:.
451:.
418:.
139:1
Text is available under the Creative Commons Attribution-ShareAlike License. Additional terms may apply.
