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diaphragm that would burst when the helium pressure reached a certain level and allow the gas to vent harmlessly into space. Once the helium was gone however, the DPS would no longer be operable. This was not seen as an issue since normally, the helium release would not occur until after the lunar module was on the Moon, by which time the DPS had completed its operational life and would never be fired again.
554:
The design and development of the innovative thrust chamber and pintle design is credited to TRW Aerospace
Engineer Gerard W. Elverum Jr. The engine could throttle between 1,050 pounds-force (4.7 kN) and 10,125 pounds-force (45.04 kN) but operation between 65% and 92.5% thrust was avoided
485:, "The lunar module descent engine probably was the biggest challenge and the most outstanding technical development of Apollo." A requirement for a throttleable engine was new for crewed spacecraft. Very little advanced research had been done in variable-thrust rocket engines up to that point.
519:
The first full-throttle firing of Space
Technology Laboratories' LM descent engine was carried out in early 1964. NASA planners expected one of the two drastically different designs would emerge the clear winner, but this did not happen throughout 1964. Apollo Spacecraft Program Office manager
550:
helium was loaded and stored at 3,500 psi (24 MPa). The helium was pressure regulated down to 246 psi (1.70 MPa) for the propellant tanks. Pressure from the helium would gradually rise as it warmed and would eventually be vented. The system was also equipped with a rubber
866:
759:
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885:
456:
of 50,000 feet (15,000 m), then provide a powered descent to the lunar surface, with hover time above the lunar surface to select the exact landing site. To accomplish these maneuvers, a propulsion system was developed that used
451:
The propulsion system for the descent stage of the lunar module was designed to transfer the vehicle, containing two crewmen, from a 60-nautical-mile (110 km) circular lunar parking orbit to an elliptical descent orbit with a
512:, and Space Technology Laboratories, Inc. (STL). In May, STL was selected as the competitor to Rocketdyne's concept. STL proposed an engine that was gimbaled as well as throttleable, using flow control valves and a variable-area
607:
to the engine to increase thrust. The nozzle exhaust bell, like the original, was designed to crush if it hit the surface. It never had on the first three landings, but did buckle on the first
Extended landing,
1476:
493:(MSC) judged this approach to be plausible, it represented a considerable advance in the state of the art. (In fact, accidental ingestion of helium pressurant proved to be a problem on
1985:
1970:
489:
proposed a pressure-fed engine using the injection of inert helium gas into the propellant flow to achieve thrust reduction at a constant propellant flow rate. While NASA's
497:, the first flight of the Apollo Service Module engine in February 1966.) Therefore, MSC directed Grumman to conduct a parallel development program of competing designs.
1002:
1469:
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to prevent excessive nozzle erosion. It weighed 394 pounds (179 kg), with a length of 90.5 inches (230 cm) and diameter of 59.0 inches (150 cm).
528:, in November 1964 to recommend a choice, but their results were inconclusive. Grumman chose Rocketdyne on January 5, 1965. Still not satisfied, MSC Director
516:, in much the same manner as does a shower head, to regulate pressure, rate of propellant flow, and the pattern of fuel mixture in the combustion chamber.
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convened his own five-member board, also chaired by Faget, which reversed
Grumman's decision on January 18 and awarded the contract to STL.
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formed a committee of NASA, Grumman and Air Force propulsion experts, chaired by
American spacecraft designer
1965:
1290:
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1100:
964:
849:
658:
300:
296:
864:, Elverum Jr., Gerard W., "Liquid propellant rocket engine coaxial injector", issued 1968-01-08
757:, Elverum Jr., Gerard W., "Liquid propellant rocket engine coaxial injector", issued 1968-01-08
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221:
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To keep the DPS as simple, lightweight, and reliable as possible, the propellants were pressure-fed with
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10,500 lbf (47 kN) maximum, throttleable between 1,050 and 6,825 lbf (4.67–30.36 kN)
1939:
1849:
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1417:
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883:, Elverum Jr., Gerard W., "Variable thrust bipropellant rocket engine", issued 1963-02-25
738:, Elverum Jr., Gerard W., "Variable thrust bipropellant rocket engine", issued 1963-02-25
473:
was designed to crush without damaging the LM if it struck the surface, which happened on Apollo 15.
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Bartlett, W.; Kirkland, Z. D.; Polifka, R. W.; Smithson, J. C.; Spencer, G. L. (7 February 1966).
1119:
693:
976:
Rocket
Propulsion – The Apollo Mission, Don Harvey. Mr. Harvey worked at STL designing the LMDE
1980:
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1727:
529:
694:"U.S. Manned Rocket Propulsion Evolution - Part 9.42: TRW Lunar Module Descent Engine (LMDE)"
1944:
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909:
850:
Apollo
Experience Report – Descent Propulsion System – NASA Technical Note: March 1973
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Decreased clearance led to buckling of the extended descent engine nozzle on the landing of
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mission, serving as the primary propulsion engine after the oxygen tank explosion in the
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In order to extend landing payload weight and lunar surface stay times, the last three
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NASA Technical Note: Apollo
Experience Report – Descent Propulsion System. March 1973
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469:. A lightweight cryogenic helium pressurization system was also used. The exhaust
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719:"REMEMBERING THE GIANTS - Apollo Rocket Propulsion Development - NASA"
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620:
After the Apollo program, the DPS was further developed into the TRW
536:
494:
89:
908:. 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.
666:. Houston, TX: NASA, Lyndon B. Johnson Space Center. pp. 8–9.
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Grumman held a bidders' conference on March 14, 1963, attended by
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engine. This engine was used in the second stage, referred to as
1630:
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807:
443:, which paved the way for other engines to use similar designs.
1747:
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could no longer be operated safely, leaving the DPS engine in
465:
pressure-fed ablative cooled engine that was capable of being
571:. After this event, the ground controllers decided that the
1743:
539:
gas instead of using heavy, complicated, and failure-prone
902:
TRW Pintle Engine
Heritage and Performance Characteristics
803:
Chariots for Apollo: A History of Manned Lunar
Spacecraft
967:
31 pages, much detail on both designs, and the testing.
777:"Mechanical Design of the Lunar Module Descent Engine"
640:
series) for 77 successful launches between 1972–1988.
971:
Apollo Lunar Module Propulsion Systems Overview, NASA
402:
invented by Gerard W. Elverum Jr. and developed by
798:"Chapter 6. Lunar Module – Engines, Large and Small"
792:
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282:
Designed for 2 restarts, tested up to four times on
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Apollo spacecraft liquid primary propulsion systems
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335:59.0 in (1.50 m) (Apollo 14 and earlier)
318:85.0 in (2.16 m) (Apollo 14 and earlier)
321:100.0 in (2.54 m) (Apollo 15 and later)
1163:Primary guidance, navigation, and control system
338:63.0 in (1.60 m) (Apollo 15 and later)
603:were upgraded by adding a 10-inch (25 cm)
899:Dressler, Gordon A.; Bauer, J. Martin (2000).
1759:
1470:
1281:Charged Particle Lunar Environment Experiment
996:
8:
771:
769:
579:as the only means of maneuvering Apollo 13.
260:311 s (3.05 km/s) (at full thrust)
30:
1986:Rocket engines using the pressure-fed cycle
1971:Rocket engines using hypergolic propellant
1841:High Energy Astronomy Observatory Program
1766:
1752:
1744:
1477:
1463:
1455:
1003:
989:
981:
845:
843:
692:McCutcheon, Kimble D. (28 December 2021).
563:The LMDE achieved a prominent role in the
826:"LM Descent Propulsion Development Diary"
240:110 psi (760 kPa) (100% thrust)
1261:Apollo Lunar Surface Experiments Package
263:285 s (2.79 km/s) (10% thrust)
649:
508:, United Technology Center Division of
1286:Lunar Ejecta and Meteorites Experiment
583:Modification for Extended Lunar Module
481:According to NASA history publication
243:11 psi (76 kPa) (10% thrust)
29:
938:. Space Launch Report. Archived from
814:from the original on 11 October 2023.
7:
1850:High Energy Astronomy Observatory 2
1333:Suprathermal Ion Detector Experiment
1276:Apollo 14 Passive Seismic Experiment
1271:Apollo 12 Passive Seismic Experiment
1855:High Energy Astronomy Observatory 3
1845:High Energy Astronomy Observatory 1
673:from the original on 23 August 2022
1303:Lunar Seismic Profiling Experiment
1291:Solar Wind Spectrometer Experiment
25:
1256:Solar Wind Composition Experiment
810:History Program Office. SP-4205.
27:Apollo Lunar Module rocket engine
1659:
1446:Category:Apollo program hardware
1441:
1440:
1074:Launch Vehicle Digital Computer
628:, of the Delta launch vehicle (
439:) oxidizer. This engine used a
31:Descent propulsion system (DPS)
1364:Lunar Landing Research Vehicle
1244:Lunar Laser Ranging experiment
1214:Thermal Micrometeoroid Garment
504:, Reaction Motors Division of
73:Lunar descent stage propulsion
1:
1835:Functional flow block diagram
1825:Compton Gamma Ray Observatory
1485:Spacecraft engines and motors
1323:Cold Cathode Gauge Experiment
1298:Modular Equipment Transporter
559:Performance in LM "life boat"
404:Space Technology Laboratories
388:(LMDE), internal designation
384:(DPS - pronounced 'dips') or
1423:Rendezvous Docking Simulator
1234:Portable Life Support System
1143:Apollo Abort Guidance System
616:TR-201 in Delta second stage
1402:Apollo 11 goodwill messages
386:lunar module descent engine
189:47.5 (Apollo 14 and before)
2002:
1369:Mobile quarantine facility
1313:Lunar Surface Magnetometer
936:"Extended Long Tank Delta"
192:53.6 (Apollo 15 and later)
1935:The Aerospace Corporation
1893:TRW Low Maintenance Rifle
1830:Descent propulsion system
1820:Chandra X-ray Observatory
1657:
1438:
1318:Lunar Traverse Gravimeter
1266:Active Seismic Experiment
1178:Descent propulsion system
830:Encyclopedia Astronautica
573:Service Propulsion System
382:descent propulsion system
358:
349:394 lb (179 kg)
18:Descent Propulsion System
1308:Lunar Surface Gravimeter
1183:Ascent propulsion system
1158:Lunar Sounder Experiment
1153:Apollo Guidance Computer
1148:Apollo Docking Mechanism
491:Manned Spacecraft Center
1976:Apollo program hardware
1669:Solid propellant motors
1249:list of retroreflectors
1012:Apollo program hardware
410:descent stage. It used
1354:Launch Umbilical Tower
1168:Apollo Telescope Mount
596:
459:hypergolic propellants
226:25.7 (weight on Earth)
222:Thrust-to-weight ratio
1713:Spacecraft propulsion
1109:Apollo service module
1095:Apollo command module
590:
569:Apollo Service Module
406:(TRW) for use in the
55:Gerard W. Elverum Jr.
1940:Goodrich Corporation
1733:Liquid apogee engine
1418:Lunar escape systems
1328:Heat Flow Experiment
1239:Lunar Roving Vehicle
862:US Patent 3,699,772A
601:Apollo Lunar Modules
416:dinitrogen tetroxide
216:10%–60%, full thrust
1390:Lunar Flag Assembly
1359:Crawler-transporter
1114:Apollo Lunar Module
914:10.2514/6.2000-3871
881:US Patent 3,205,656
836:on August 21, 2002.
755:US Patent 3,699,772
736:US Patent 3,205,656
483:Chariots for Apollo
408:Apollo Lunar Module
32:
597:
105:Liquid-fuel engine
1953:
1952:
1741:
1740:
1728:Apogee kick motor
1452:
1451:
1204:Apollo/Skylab A7L
923:on 9 August 2017.
698:enginehistory.org
530:Robert R. Gilruth
378:
377:
362:as descent engine
36:Country of origin
16:(Redirected from
1993:
1945:Northrop Grumman
1923:Related articles
1789:Lucas Industries
1768:
1761:
1754:
1745:
1706:Related articles
1663:
1662:
1479:
1472:
1465:
1456:
1444:
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1396:Fallen Astronaut
1188:Scimitar antenna
1173:Apollo TV camera
1005:
998:
991:
982:
952:
951:
949:
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942:on 7 August 2010
931:
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916:. Archived from
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832:. Archived from
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471:nozzle extension
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392:, is a variable-
252:Specific impulse
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510:United Aircraft
502:Aerojet General
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1225:Lunar surface
1223:
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1026:Little Joe II
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548:supercritical
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400:rocket engine
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170:Configuration
168:
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144:Mixture ratio
142:
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39:United States
38:
34:
19:
1880:
1873:
1866:
1829:
1782:Subsidiaries
1427:
1394:
1385:Lunar plaque
1177:
1118:
1099:
944:. Retrieved
940:the original
929:
918:the original
901:
894:
875:
856:
834:the original
829:
820:
802:
749:
730:
713:
701:. Retrieved
697:
687:
675:. Retrieved
659:
652:
619:
598:
576:
562:
553:
534:
526:Maxime Faget
518:
499:
482:
480:
454:pericynthion
450:
447:Requirements
389:
385:
381:
379:
360:Lunar module
291:Gimbal range
274:1030 seconds
183:Nozzle ratio
156:Pressure-fed
60:Manufacturer
1794:LucasVarity
1492:Liquid fuel
1429:Moon Museum
1197:Space suits
522:Joseph Shea
477:Development
412:Aerozine 50
200:Performance
138:Aerozine 50
78:Predecessor
70:Application
1960:Categories
1909:Simon Ramo
1882:Pioneer 11
1875:Pioneer 10
1718:Spacecraft
1641:SuperDraco
1378:Ceremonial
1209:Beta cloth
1136:components
1134:Spacecraft
1083:Spacecraft
1064:J-2 engine
1059:F-1 engine
1052:components
644:References
638:Delta 3000
634:Delta 2000
630:Delta 1000
541:turbopumps
487:Rocketdyne
397:hypergolic
372:References
367:References
307:Dimensions
111:Propellant
1930:Astrolink
1868:Pioneer 1
1804:TRW Vidar
1723:Satellite
1698:SpaB-140C
1227:equipment
1036:Saturn IB
934:Ed Kyle.
703:23 August
677:23 August
610:Apollo 15
593:Apollo 15
565:Apollo 13
545:Cryogenic
467:throttled
463:gimballed
414:fuel and
271:Burn time
86:Successor
47:1964–1972
1981:TRW Inc.
1862:N2 chart
1813:Products
1775:TRW Inc.
1586:KTDU-425
1101:Columbia
1041:Saturn V
1031:Saturn I
812:Archived
668:Archived
577:Aquarius
394:throttle
346:Dry mass
329:Diameter
284:Apollo 9
279:Restarts
254:, vacuum
233:pressure
231:Chamber
52:Designer
1695:SpaB-65
1681:Star 48
1676:Star 37
1558:KTDU-80
1539:KTDU-35
1526:KDU-414
1494:engines
1411:Related
1090:Apollo
946:May 11,
626:Delta-P
506:Thiokol
354:Used in
175:Chamber
99:Retired
1902:People
1888:TR-201
1646:TR-201
1579:S5.142
1566:11D428
1562:11D426
1533:S5.114
887:
868:
761:
742:
622:TR-201
537:helium
495:AS-201
461:and a
390:VTR-10
312:Length
96:Status
90:TR-201
1691:FG-36
1686:FG-15
1651:XLR81
1636:S5.92
1621:RS-25
1615:11D58
1611:RD-58
1591:LEROS
1574:S5.80
1570:S5.79
1552:S5-66
1549:S5-60
1546:S5.53
1543:S5-35
1530:S5.19
1521:Draco
1516:Curie
1501:17D61
1120:Eagle
921:(PDF)
906:(PDF)
722:(PDF)
671:(PDF)
664:(PDF)
297:pitch
162:Pumps
152:Cycle
1631:S5.4
1626:S400
1606:R-4D
1601:LMDE
1596:LMAE
1511:BT-4
1506:AJ10
948:2014
808:NASA
705:2022
679:2022
380:The
299:and
165:None
81:None
44:Date
910:doi
301:yaw
295:6°
147:1.6
64:TRW
1962::
842:^
828:.
806:.
800:.
785:^
768:^
696:.
636:,
632:,
612:.
543:.
136:/
1767:e
1760:t
1753:v
1478:e
1471:t
1464:v
1004:e
997:t
990:v
950:.
912::
779:.
724:.
707:.
681:.
434:4
429:O
425:2
420:N
418:(
178:1
130:4
125:O
121:2
116:N
20:)
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