2430:
1910:
327:
In order to keep the maximum operating temperatures of the titanium case in the vicinity of 800 °F (427 °C), the ablative liner was designed as a composite material providing the maximum heat sink and minimum weight. The selected configuration consisted of a high density, erosion-resistant
314:
ablative liner is retained in the exit cone during transportation, launch and boost. During engine firing, thrust loads force the exit cone liner against the case. The titanium head end assembly which contains the Pintle
Injector and propellant valve subcomponents is attached with 36 A-286 steel
313:
alloy titanium case was accomplished by machining the chamber portion and the exit cone portion from forgings and welding them into one unit at the throat centerline. The ablative liner is fabricated in two segments and installed from either end. The shape of the nozzle extension is such that the
331:
The installed pintle injector, unique to TRW-designed liquid-propulsion systems, provides improved reliability and less costly method of fuel–oxidizer impingement in the thrust chamber than conventional coaxial distributed-element injectors typically used on liquid bipropellant rocket engines.
301:
and was subsequently adopted for the Delta expendable launch vehicle 2nd stage. The engine made 10 flights during the Apollo program and 77 during its Delta career between 1974 and 1988. The TRW TR-201 was re-configured as a fixed-thrust version of the LMDE for Delta's stage 2. Multi-start
302:
operation is adjustable up to 55.6 kN and propellant throughput up to 7,711 kg; and the engine can be adapted to optional expansion ratio nozzles. Development of the innovative thrust chamber and pintle design is credited to TRW Aerospace
Engineer Gerard W. Elverum Jr.
576:
482:
595:
463:
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2527:
2522:
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first invented by Gerard W. Elverum Jr. and developed by TRW in the late 1950s and received US Patent in 1972. This injector technology and design is also used on SpaceX
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launches between 1972 and 1988. The engine had a 100% reliability record during this 15 year operational period.
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79:
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1918:
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851:
574:, Elverum Jr., Gerard W., "Liquid propellant rocket engine coaxial injector", issued 1968-01-08
480:, Elverum Jr., Gerard W., "Liquid propellant rocket engine coaxial injector", issued 1968-01-08
2002:
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silica cloth/phenolic material surrounded by a lightweight needle-felted silica mat/phenolic insulation.
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593:, Elverum Jr., Gerard W., "Variable thrust bipropellant rocket engine", issued 1963-02-25
461:, Elverum Jr., Gerard W., "Variable thrust bipropellant rocket engine", issued 1963-02-25
256:
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1987:
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1982:
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519:. 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Redondo Beach, CA: TRW Inc.
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Length: 51 inches – gimbal attachment to nozzle tip (minus nozzle extension)
398:
Expansion ratio: 16:1 without nozzle extension; 43:1 with nozzle extension
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2077:
2072:
1992:
1977:
1962:
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1370:
749:
662:
279:
160:
46:
2207:* Different versions of the engine use different propellant combinations
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Maximum diameter: 34 inches (860 mm) (minus nozzle extension)
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REMEMBERING THE GIANTS - Apollo Rocket
Propulsion Development
631:
513:
TRW Pintle Engine
Heritage and Performance Characteristics
404:
Cooling, lower thrust chamber: ablative quartz phenolic;
437:
The TR-201 engine was used as the second stage for 77
305:
The combustion chamber consists of an ablative-lined
278:
as oxidizer. It was developed in the early 1970s by
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510:Dressler, Gordon A.; Bauer, J. Martin (July 2000).
344:
Dry mass: 300 pounds (140 kg) with columbium (
297:The thrust chamber was initially developed for the
209:
201:
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185:
180:
169:
158:
148:
136:
131:
123:
118:
108:
85:
78:
70:
60:
52:
42:
34:
24:
309:case to the 16:1 area ratio. Fabrication of the
382:Oxidizer: dinitrogen tetroxide at 5.62 kg/s
428:s for total of 5 starts; 10 × 350-s single burn
364:Engine cycle: pressure fed (15.5 atm reservoir)
2239:
859:
647:
421:V electrical signal to on/off solenoid valves
8:
19:
2528:Rocket engines using the pressure-fed cycle
612:. Encyclopedia Astronautica. Archived from
548:. Encyclopedia Astronautica. Archived from
341:Number flown: 77 (Delta 2000 configuration)
2523:Rocket engines using hypergolic propellant
2246:
2232:
2224:
1540:
1264:
922:
913:
866:
852:
844:
729:High Energy Astronomy Observatory Program
654:
640:
632:
361:Mounting: gimbal attachment above injector
96:
92:
450:
239:used to propel the upper stage of the
18:
7:
897:Comparison of orbital rocket engines
738:High Energy Astronomy Observatory 2
407:Cooling, nozzle extension: radiative
2533:Rocket engines of the United States
743:High Energy Astronomy Observatory 3
733:High Energy Astronomy Observatory 1
534:from the original on 31 March 2022.
417:Ignition: hypergolic, started by 28
401:Cooling, upper thrust chamber: film
284:lunar module descent engine (LMDE)
14:
197:1.38 m (4 ft 6 in)
189:2.27 m (7 ft 5 in)
2428:
1908:
388:Thrust, vacuum: 42.923 kN
1:
2254:Spacecraft engines and motors
1693:RD-0202 to 0206, 0208 to 0213
723:Functional flow block diagram
713:Compton Gamma Ray Observatory
391:Specific impulse, vacuum: 303
176:301 s (2.95 km/s)
165:700 kPa (100 psi)
140:41.9 kN (9,400 lb
2549:
324:inch (6.4 mm) bolts.
2426:
2203:
1906:
892:
823:The Aerospace Corporation
781:TRW Low Maintenance Rifle
718:Descent propulsion system
708:Chandra X-ray Observatory
385:Oxidizer:fuel ratio: 1.60
247:, from 1972 to 1988. The
214:
205:113 kg (249 lb)
2438:Solid propellant motors
1738:RD-250 to 252, 261, 262
499:. NASA. pp. 73–86.
282:as a derivative of the
286:. This engine used a
150:Thrust-to-weight ratio
2482:Spacecraft propulsion
2214:are under development
1602:YF-20, 21, 22, 24, 25
1381:RD-107, 108, 117, 118
410:Chamber pressure: 7.1
220:Delta (rocket family)
2502:Liquid apogee engine
828:Goodrich Corporation
1703:RD-0216, 0217, 0235
1366:RD-0107, 0108, 0110
591:US Patent 3,205,656
572:US Patent 3,699,772
525:10.2514/6.2000-3871
478:US Patent 3,699,772
459:US Patent 3,205,656
379:) at 8.92 kg/s
299:Apollo Lunar Module
113:Pressure-fed engine
21:
527:. AIAA 2000-3871.
218:, second stage of
80:Liquid-fuel engine
2510:
2509:
2497:Apogee kick motor
2221:
2220:
2163:Space Shuttle SRB
1904:
1903:
1842:
1841:
1532:
1531:
1254:
1253:
841:
840:
243:, referred to as
225:
224:
25:Country of origin
2540:
2475:Related articles
2432:
2431:
2248:
2241:
2234:
2225:
1912:
1911:
1748:RD-263, 268, 273
1679:along other LREs
1541:
1401:RD-191, 151, 181
1265:
923:
914:
868:
861:
854:
845:
833:Northrop Grumman
811:Related articles
677:Lucas Industries
656:
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427:
420:
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394:
350:nozzle extension
323:
322:
318:
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275:
274:
266:
265:
171:Specific impulse
100:
22:
2548:
2547:
2543:
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2539:
2538:
2537:
2513:
2512:
2511:
2506:
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2429:
2424:
2255:
2252:
2222:
2217:
2199:
1920:
1913:
1909:
1900:
1838:
1728:RD-0255 to 0257
1723:RD-0243 to 0245
1585:
1574:
1570:
1564:
1552:
1528:
1269:
1260:
1250:
1114:
1108:
1102:
933:
927:
908:
901:
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886:launch vehicles
872:
842:
837:
806:
802:Dean Wooldridge
785:
696:
665:
660:
630:
629:
619:
617:
616:on 17 June 2012
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320:
316:
315:
288:pintle injector
273:
270:
269:
268:
264:
261:
260:
259:
257:
229:TR-201 or TR201
143:
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89:
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2124:United States
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1878:United States
1876:
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1874:
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1840:
1839:
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1823:
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1801:United States
1799:
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1527:
1526:
1525:
1524:
1519:
1514:
1509:
1504:
1499:
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1489:
1487:LR70-NA , S-3D
1484:
1479:
1474:
1469:
1464:
1459:
1453:United States
1451:
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1194:
1189:
1183:United States
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1093:
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1078:
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1063:United States
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1039:
1038:
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1017:
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911:
903:
902:
900:
899:
893:
890:
889:
875:Rocket engines
873:
871:
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863:
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848:
839:
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836:
835:
830:
825:
820:
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799:
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745:
740:
735:
726:
725:
720:
715:
710:
704:
702:
698:
697:
695:
694:
689:
687:TRW Automotive
684:
679:
673:
671:
667:
666:
661:
659:
658:
651:
644:
636:
628:
627:
601:
582:
563:
552:on 6 July 2008
537:
502:
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469:
449:
448:
446:
443:
434:
431:
430:
429:
424:Burn time: 500
422:
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396:
389:
386:
383:
380:
372:
368:
365:
362:
359:
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353:
342:
337:
336:Specifications
334:
307:titanium alloy
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137:Thrust, vacuum
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2:
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2226:
2213:
2209:
2206:
2205:
2202:
2194:
2191:
2189:
2186:
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2181:
2179:
2176:
2174:
2171:
2169:
2166:
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2161:
2159:
2156:
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2151:
2149:
2146:
2144:
2141:
2139:
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2134:
2131:
2129:
2126:
2125:
2123:
2119:
2116:
2114:
2111:
2109:
2106:
2104:
2101:
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2036:
2034:
2031:
2029:
2026:
2025:
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2019:
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1862:RD-211 to 214
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1708:RD-0233, 0234
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1698:RD-0207, 0214
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1677:Paektusan LRE
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1045:KVD-1 (RD-56)
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367:Fuel: 50:50 N
366:
363:
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343:
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335:
333:
329:
325:
312:
308:
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295:
293:
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255:as fuel, and
254:
250:
249:rocket engine
246:
242:
238:
237:rocket engine
235:pressure-fed
234:
230:
221:
217:
213:
208:
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196:
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119:Configuration
117:
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111:
107:
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88:
84:
81:
77:
73:
69:
66:
63:
59:
55:
51:
48:
45:
41:
37:
33:
30:
29:United States
27:
23:
16:Rocket engine
2414:
2211:
1825:
1752:
1673:North Korea
1444:
1437:
1405:
1333:
1321:
1314:
1292:
1241:
1234:
1222:
1210:
1203:
1196:
1174:
1167:
1160:
1143:
1136:
1129:
1073:
1066:
1054:
1032:
975:
968:
879:solid motors
775:
768:
761:
754:
670:Subsidiaries
618:. Retrieved
614:the original
604:
585:
566:
554:. Retrieved
550:the original
540:
512:
505:
496:
491:
472:
453:
436:
330:
326:
304:
296:
241:Delta rocket
228:
226:
43:Manufacturer
2261:Liquid fuel
2210:Engines in
1857:RD-109, 119
1795:RD-864, 869
1780:RD-854, 861
1743:RD-253, 275
1391:RD-170, 171
682:LucasVarity
433:Delta usage
377:Aerozine 50
253:Aerozine 50
132:Performance
103:Aerozine 50
61:Predecessor
56:Upper stage
53:Application
2517:Categories
2487:Spacecraft
2410:SuperDraco
1597:YF-1, 2, 3
1545:Hypergolic
1517:Rutherford
1236:Prometheus
1198:Archimedes
797:Simon Ramo
770:Pioneer 11
763:Pioneer 10
445:References
233:hypergolic
181:Dimensions
86:Propellant
2492:Satellite
2467:SpaB-140C
2138:Castor 30
2018:Zefiro 40
2013:Zefiro 23
1954:SpaB-140C
1351:NK-33, 44
1261:cryogenic
1107:Methalox
926:Hydrolox
918:Cryogenic
818:Astrolink
756:Pioneer 1
692:TRW Vidar
610:"Delta P"
352:installed
294:engines.
38:1972–1988
2355:KTDU-425
2153:Orbus-21
2008:Zefiro 9
1771:Ukraine
1549:Aerozine
1537:Storable
1429:Ukraine
1371:RD-0110R
1268:Kerolox
750:N2 chart
701:Products
663:TRW Inc.
546:"TR-201"
529:Archived
202:Dry mass
194:Diameter
173:, vacuum
161:pressure
159:Chamber
2464:SpaB-65
2450:Star 48
2445:Star 37
2327:KTDU-80
2308:KTDU-35
2295:KDU-414
2263:engines
2212:italics
2173:Star 48
2168:Star 37
2148:Orbus-6
2069:Israel
2003:Waxwing
1959:Europe
1951:SpaB-65
1853:Russia
1718:RD-0237
1713:RD-0236
1684:Russia
1663:Israel
1623:Europe
1467:Kestrel
1413:S1.5400
1376:RD-0124
1342:Russia
1335:SCE-200
1231:Europe
1224:RD-0169
1219:Russia
1145:Longyun
1138:Lingyun
1056:RD-0146
1050:RD-0120
1041:Russia
998:Vulcain
984:Europe
907:Liquid
883:orbital
375:/UDMH (
346:niobium
319:⁄
311:Ti6Al4V
245:Delta-P
216:Delta-P
210:Used in
124:Chamber
74:Retired
2415:TR-201
2348:S5.142
2335:11D428
2331:11D426
2302:S5.114
2128:AJ-60A
2093:KM-V2b
2084:Japan
2058:Salman
2024:India
1998:Topaze
1963:Mage 1
1928:China
1919:Solid
1826:TR-201
1790:RD-856
1785:RD-855
1775:RD-843
1765:S5.98M
1754:RD-270
1648:India
1642:Viking
1632:Astris
1627:Aestus
1617:YF-50D
1593:China
1502:RS-27A
1492:Merlin
1482:LR-105
1446:RD-810
1439:RD-801
1423:TEPREL
1419:Spain
1407:RD-193
1396:RD-180
1386:RD-120
1330:India
1323:Welkin
1316:YF-130
1310:YF-115
1305:YF-102
1300:YF-100
1284:China
1212:Aeon R
1205:Aeon 1
1192:Raptor
1176:YF-215
1169:YF-209
1162:TQ-15A
1126:China
1019:Japan
1008:CE-7.5
1004:India
959:YF-75D
945:China
790:People
776:TR-201
620:4 June
597:
578:
556:4 June
484:
465:
426:
419:
412:
393:
292:Merlin
186:Length
71:Status
20:TR-201
2460:FG-36
2455:FG-15
2420:XLR81
2405:S5.92
2390:RS-25
2384:11D58
2380:RD-58
2360:LEROS
2343:S5.80
2339:S5.79
2321:S5-66
2318:S5-60
2315:S5.53
2312:S5-35
2299:S5.19
2290:Draco
2285:Curie
2270:17D61
2193:X-254
2188:X-248
2178:UA120
2158:Orion
2133:Algol
2118:SRB-A
2113:M-34c
2088:KM-V1
2078:RSA-3
2054:Iran
1947:FG-47
1942:FG-46
1937:FG-36
1932:FG-02
1893:XLR81
1887:RS-88
1882:Curie
1872:Gamma
1847:Other
1831:XLR81
1820:RS-88
1815:LR-91
1810:LR-87
1760:S5.92
1688:17D61
1657:Vikas
1637:Vexin
1612:YF-40
1607:YF-23
1580:, or
1560:, or
1554:UH 25
1522:XLR50
1507:RS-56
1497:RS-27
1477:LR-89
1472:LR-79
1356:RD-58
1346:NK-15
1294:TH-12
1288:TH-11
1259:Semi-
1156:TQ-12
1151:TQ-11
1131:BF-20
1096:RS-68
1091:RS-25
1068:BE-3U
1013:CE-20
993:Vinci
977:YF-90
970:YF-79
964:YF-77
954:YF-75
949:YF-73
532:(PDF)
517:(PDF)
439:Delta
251:uses
231:is a
109:Cycle
2400:S5.4
2395:S400
2375:R-4D
2370:LMDE
2365:LMAE
2280:BT-4
2275:AJ10
2183:SRMU
2108:M-34
2103:M-24
2098:M-14
2073:LK-1
2063:Rafe
2048:S200
2043:S139
1993:P230
1988:P120
1921:fuel
1805:AJ10
1667:LK-4
1562:UDMH
1512:S-3D
1433:RD-8
1272:RP-1
1243:M-10
1187:BE-4
1086:RL10
1075:BE-7
1034:LE-9
1028:LE-7
1023:LE-5
988:HM7B
909:fuel
881:for
877:and
622:2012
558:2012
227:The
154:31.4
65:LMDE
35:Date
2143:GEM
2038:S12
1983:P80
1978:PAP
1973:P-6
1968:P-4
1868:UK
1652:PS4
1582:HNO
1578:MON
1558:MMH
1462:H-1
1457:F-1
1276:LOX
1118:LOX
1081:J-2
937:LOX
521:doi
414:atm
280:TRW
47:TRW
2519::
2033:S9
2028:S7
1576:,
1565:/
1556:,
1551:,
1274:/
1116:/
1111:CH
935:/
930:LH
348:)
101:/
2247:e
2240:t
2233:v
1895:*
1889:*
1833:*
1822:*
1587:)
1584:3
1573:4
1571:O
1569:2
1567:N
1547:(
1278:)
1270:(
1120:)
1113:4
1109:(
939:)
932:2
928:(
867:e
860:t
853:v
655:e
648:t
641:v
624:.
560:.
523::
395:s
373:4
371:O
369:2
321:4
317:1
272:4
267:O
263:2
258:N
144:)
142:f
127:1
97:4
95:O
93:2
91:N
Text is available under the Creative Commons Attribution-ShareAlike License. Additional terms may apply.