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for the 7A. The oxidizer inducer was also redesigned, but this was primarily due to poor performance at low inlet pressures as opposed to reliability concerns. The fuel turbopump itself was also the subject of various durability enhancements. Additionally the combustion chamber/injector assembly underwent a number of small changes, like decreasing the number of injector elements, to reduce machining complexity (and thus cost) and improve reliability. While these changes overall resulted in a drop in maximum specific impulse to 440 seconds (4.3 km/s) (basically making the engine less fuel efficient), the trade off for lower cost and enhanced reliability was considered acceptable.
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extension was designed that could be added to the base of the new standard “short” nozzle when extra performance was required. But when the engine was fitted with the nozzle extension, the 7A encountered a new problem with unprecedented side-loads and irregular heating on the nozzle strong enough to
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work was able to sufficiently replicate and trace the dangerous transient loading and a new one-piece “long” nozzle with full regenerative cooling (as opposed to the original short nozzle with a separate film-cooled extension) was designed to mitigate the problem. Before this new nozzle was ready,
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components, and to simplify as many of the remaining welds as possible. This resulted in a substantial rework of the pipe routing (which makes the outward appearance of the two models considerably different). To combat the fuel inducer complications described above, the fuel inducer was redesigned
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The LE-7A is an upgraded model from the LE-7 rocket engine. Basic design is unchanged from the original model. The 7A had additional engineering effort placed on cost cutting, reliability, and performance developments. The renovation was undertaken to mate it with the likewise improved
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303:) liquid rocket engine with that claim, in a collaborative effort from the National Space Development Agency (NASDA), Aerospace Engineering Laboratory (NAL),
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some H-IIA's were launched using only the short nozzle. The 7A no longer uses a separate nozzle extension in any configuration.
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launch vehicle, with the common goal being a more reliable, more powerful and flexible, and more cost effective launch system.
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series of launch vehicles. Design and production work was all done domestically in Japan, the first major (
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595:"LE-7A Engine Separation Phenomenon Differences of the Two Nozzle Configurations"
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2057:* Different versions of the engine use different propellant combinations
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due to this vibration was the cause of premature engine failure.
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Yasuhide
Watanabe; Norio Sakazume; Masanori Tsuboi (July 2003).
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39th AIAA/ASME/SAE/ASEE Joint
Propulsion Conference and Exhibit
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Combustion chamber pressure: 12.0 MPa (1,740 psi)
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launch vehicles uses two LE-7A engines in its first stage.
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Specific impulse (sea level): 338 seconds (3.31 km/s)
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Rated thrust (sea level): 870 kN (200,000 lbf)
465:
Rated thrust (sea level): 843 kN (190,000 lbf)
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Rated thrust (vacuum): 1,098 kN (247,000 lbf)
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Specific impulse (vacuum): 429 seconds (4.21 km/s)
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Rated thrust (vacuum): 1,074 kN (241,000 lbf)
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Specific impulse (vacuum): 440 seconds (4.3 km/s)
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678:Japanese Knowledge (XXG) LE-7A page (in Japanese)
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2094:Rocket engines using the staged combustion cycle
673:Japanese Knowledge (XXG) LE-7 page (in Japanese)
668:Encyclopedia Astronautica info page on the LE-7A
311:. NASDA and NAL have since been integrated into
663:Encyclopedia Astronautica info page on the LE-7
274:and its succeeding upgrade model the LE-7A are
262:LE-7A, (Mitsubishi Heavy Industries show-room,
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334:H-II Flight 8, only operational LE-7 failure
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404:New nozzle design (side-loading problem)
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496:Dry mass: 1,800 kg (4,000 lb)
638:"Overview of the H-IIB Launch Vehicle"
459:Mixture ratio (oxidizer to fuel): 5.90
42:LE-7, Nagoya City Science Museum, 2006
29:
522:Liquid hydrogen turbopump: 41,900 rpm
7:
747:Comparison of orbital rocket engines
688:Overview of the H-IIA Launch Vehicle
559:Comparison of orbital rocket engines
450:Operational cycle: staged combustion
525:Liquid oxygen turbopump: 18,300 rpm
690:Includes H-IIA-F6 failure analysis
426:computational fluid dynamics (CFD)
25:
424:tubes during startup. Meticulous
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175:843.5 kN (189,600 lbf)
167:1,078 kN (242,000 lbf)
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683:H-IIA Rocket Engine Development
196:12.7 MPa (1,840 psi)
1:
1543:RD-0202 to 0206, 0208 to 0213
471:Specific impulse (sea level):
239:1,714 kg (3,779 lb)
510:Throttle capability: 72–100%
408:For the new engine model, a
218:349 seconds (3.42 km/s)
207:446 seconds (4.37 km/s)
305:Mitsubishi Heavy Industries
72:Mitsubishi Heavy Industries
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91:Succeeded by LE-7A upgrade
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516:Nozzle area ratio: 51.9:1
326:The original LE-7 was an
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2084:Rocket engines of Japan
1588:RD-250 to 252, 261, 262
569:Staged combustion cycle
456:Oxidizer: liquid oxygen
276:staged combustion cycle
513:Thrust-to-weight: 65.9
383:Changes / improvements
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181:Thrust-to-weight ratio
2064:are under development
1452:YF-20, 21, 22, 24, 25
1231:RD-107, 108, 117, 118
391:by allowing for more
289:liquid rocket engines
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445:LE-7A specifications
422:regenerative cooling
1553:RD-0216, 0217, 0235
1216:RD-0107, 0108, 0110
607:10.2514/6.2003-4763
502:short nozzle: 3.2 m
309:Ishikawajima-Harima
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564:Liquid-fuel rocket
505:long nozzle: 3.7 m
350:ahead of the main
321:Mitsubishi LE-7(A)
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97:Liquid-fuel engine
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48:Country of origin
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1004:
1002:
999:
997:
996:
992:
990:
989:
985:
983:
982:
978:
977:
975:
974:
972:
969:
965:
955:
947:
944:
942:
939:
937:
934:
932:
929:
927:
926:
922:
920:
919:
915:
914:
912:
908:
907:
903:
901:
898:
896:
895:KVD-1 (RD-56)
893:
892:
890:
886:
885:
881:
879:
876:
874:
871:
870:
868:
864:
861:
859:
856:
855:
853:
849:
846:
844:
841:
839:
836:
835:
833:
829:
828:
824:
822:
821:
817:
815:
812:
810:
807:
805:
802:
800:
797:
796:
794:
793:
791:
788:
784:
774:
771:
769:
765:
762:
760:
754:
748:
745:
744:
741:
737:
734:
730:
726:
719:
714:
712:
707:
705:
700:
699:
696:
689:
686:
684:
681:
679:
676:
674:
671:
669:
666:
664:
661:
660:
656:
639:
633:
630:
618:
612:
608:
604:
600:
596:
589:
586:
579:
575:
572:
570:
567:
565:
562:
560:
557:
555:
551:
547:
544:
542:
539:
537:
534:
533:
529:
524:
521:
518:
515:
512:
509:
504:
501:
500:
498:
495:
490:
487:
484:
481:
480:
479:Long nozzle:
478:
473:
470:
467:
464:
463:
461:
458:
455:
452:
449:
448:
444:
442:
440:
432:
430:
427:
423:
419:
416:
411:
403:
401:
398:
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382:
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369:
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365:
361:
357:
353:
349:
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341:
333:
331:
329:
324:
322:
318:
314:
310:
306:
302:
298:
294:
290:
287:
283:
277:
273:
265:
260:
251:
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206:
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199:
195:
193:
188:
184:
182:
178:
174:
170:
166:
162:
157:
153:
149:
145:
141:
138:Configuration
136:
133:
130:
126:
122:
120:Mixture ratio
118:
115:
108:
105:
101:
98:
94:
90:
86:
83:
80:
76:
73:
70:
66:
63:
60:
56:
53:
50:
46:
39:
34:
19:
2061:
1602:
1523:North Korea
1294:
1287:
1255:
1183:
1171:
1164:
1142:
1091:
1084:
1072:
1060:
1053:
1046:
1024:
1017:
1010:
993:
986:
979:
923:
916:
904:
882:
877:
825:
818:
729:solid motors
642:. Retrieved
632:
620:. Retrieved
598:
588:
436:
433:Use on H-IIB
407:
386:
373:
337:
325:
320:
291:produced in
271:
269:
151:Nozzle ratio
68:Manufacturer
2060:Engines in
1707:RD-109, 119
1645:RD-864, 869
1630:RD-854, 861
1593:RD-253, 275
1241:RD-170, 171
413:damage the
354:to prevent
252:first stage
215:, sea-level
159:Performance
78:Application
2078:Categories
1447:YF-1, 2, 3
1395:Hypergolic
1367:Rutherford
1086:Prometheus
1048:Archimedes
580:References
356:cavitation
352:turbopumps
348:propellant
344:axial pump
328:expendable
223:Dimensions
103:Propellant
1988:Castor 30
1868:Zefiro 40
1863:Zefiro 23
1804:SpaB-140C
1201:NK-33, 44
1111:cryogenic
957:Methalox
776:Hydrolox
768:Cryogenic
418:actuators
360:vibration
340:turbopump
338:The fuel
264:Shinagawa
2003:Orbus-21
1858:Zefiro 9
1621:Ukraine
1399:Aerozine
1387:Storable
1279:Ukraine
1221:RD-0110R
1118:Kerolox
552:, &
530:See also
499:Length:
437:The new
393:machined
295:for the
266:, Japan)
236:Dry mass
204:, vacuum
192:pressure
190:Chamber
58:Designer
2062:italics
2023:Star 48
2018:Star 37
1998:Orbus-6
1919:Israel
1853:Waxwing
1809:Europe
1801:SpaB-65
1703:Russia
1568:RD-0237
1563:RD-0236
1534:Russia
1513:Israel
1473:Europe
1317:Kestrel
1263:S1.5400
1226:RD-0124
1192:Russia
1185:SCE-200
1081:Europe
1074:RD-0169
1069:Russia
995:Longyun
988:Lingyun
906:RD-0146
900:RD-0120
891:Russia
848:Vulcain
834:Europe
757:Liquid
733:orbital
389:welding
364:fatigue
244:Used in
143:Chamber
82:Booster
1978:AJ-60A
1943:KM-V2b
1934:Japan
1908:Salman
1874:India
1848:Topaze
1813:Mage 1
1778:China
1769:Solid
1676:TR-201
1640:RD-856
1635:RD-855
1625:RD-843
1615:S5.98M
1604:RD-270
1498:India
1492:Viking
1482:Astris
1477:Aestus
1467:YF-50D
1443:China
1352:RS-27A
1342:Merlin
1332:LR-105
1296:RD-810
1289:RD-801
1273:TEPREL
1269:Spain
1257:RD-193
1246:RD-180
1236:RD-120
1180:India
1173:Welkin
1166:YF-130
1160:YF-115
1155:YF-102
1150:YF-100
1134:China
1062:Aeon R
1055:Aeon 1
1042:Raptor
1026:YF-215
1019:YF-209
1012:TQ-15A
976:China
869:Japan
858:CE-7.5
854:India
809:YF-75D
795:China
644:13 May
640:. JAXA
622:13 May
613:
415:gimbal
410:nozzle
307:, and
228:Length
88:Status
2043:X-254
2038:X-248
2028:UA120
2008:Orion
1983:Algol
1968:SRB-A
1963:M-34c
1938:KM-V1
1928:RSA-3
1904:Iran
1797:FG-47
1792:FG-46
1787:FG-36
1782:FG-02
1743:XLR81
1737:RS-88
1732:Curie
1722:Gamma
1697:Other
1681:XLR81
1670:RS-88
1665:LR-91
1660:LR-87
1610:S5.92
1538:17D61
1507:Vikas
1487:Vexin
1462:YF-40
1457:YF-23
1430:, or
1410:, or
1404:UH 25
1372:XLR50
1357:RS-56
1347:RS-27
1327:LR-89
1322:LR-79
1206:RD-58
1196:NK-15
1144:TH-12
1138:TH-11
1109:Semi-
1006:TQ-12
1001:TQ-11
981:BF-20
946:RS-68
941:RS-25
918:BE-3U
863:CE-20
843:Vinci
827:YF-90
820:YF-79
814:YF-77
804:YF-75
799:YF-73
554:H-IIB
550:H-IIA
439:H-IIB
420:and
377:H-IIA
370:LE-7A
293:Japan
231:3.4 m
185:64.13
128:Cycle
123:5.9:1
52:Japan
18:LE-7A
2033:SRMU
1958:M-34
1953:M-24
1948:M-14
1923:LK-1
1913:Rafe
1898:S200
1893:S139
1843:P230
1838:P120
1771:fuel
1655:AJ10
1517:LK-4
1412:UDMH
1362:S-3D
1283:RD-8
1122:RP-1
1093:M-10
1037:BE-4
936:RL10
925:BE-7
884:LE-9
878:LE-7
873:LE-5
838:HM7B
759:fuel
731:for
727:and
646:2023
624:2023
611:ISBN
574:JAXA
546:H-II
541:LE-9
536:LE-5
397:cast
313:JAXA
297:H-II
272:LE-7
270:The
250:H-II
154:52:1
62:JAXA
31:LE-7
1993:GEM
1888:S12
1833:P80
1828:PAP
1823:P-6
1818:P-4
1718:UK
1502:PS4
1432:HNO
1428:MON
1408:MMH
1312:H-1
1307:F-1
1126:LOX
968:LOX
931:J-2
787:LOX
603:doi
395:or
286:LOX
107:LOX
2080::
1883:S9
1878:S7
1426:,
1415:/
1406:,
1401:,
1124:/
966:/
961:CH
785:/
780:LH
609:.
601:.
597:.
548:,
323:.
279:LH
111:LH
109:/
1745:*
1739:*
1683:*
1672:*
1437:)
1434:3
1423:4
1421:O
1419:2
1417:N
1397:(
1128:)
1120:(
970:)
963:4
959:(
789:)
782:2
778:(
717:e
710:t
703:v
648:.
626:.
605::
284:/
281:2
146:1
113:2
20:)
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