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important. Initial attempts did not work well: there were bonding issues and air pockets. Initially, the stage was insulated with a honeycomb material. These panels had grooves milled in the back which were purged with helium during filling. The final method was to spray insulation on by hand and trim the excess. This change saved both weight and time and avoided the issues with air pockets entirely. The LH2 tank volume was 260,000 US gallons (980 m) for storing 153,000 pounds (69 t) of liquid hydrogen.
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511:. It insulated a 126 °F (70 °C) temperature differential between the two tanks. The use of a common bulkhead saved 3.6 tonnes in weight, both by eliminating one bulkhead and by reducing the overall length of the stage. The S-II's common bulkhead design was tested in 1965 on the subscale Common Bulkhead Test Tank (CBTT), made of only 2 LH2 tank cylinders.
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began the process to find the contractor to build the stage. Out of the 30 aerospace companies invited to a conference where the initial requirements were laid out, only seven submitted proposals a month later. Three of these were eliminated after their proposals had been investigated. However it was
537:
tank was constructed of six cylinders: five were 2.4 meters high and the sixth was 0.69 meters high. The biggest challenge was the insulation. Liquid hydrogen must be kept colder than about 20 °C above absolute zero (−423 °F or 20.4 K or −252.8 °C) so good insulation is very
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Modified to act as the terminal stage. The only S-II to enter earth orbit, made an uncontrolled reentry into the
Atlantic on January 11, 1975. Interstage failed to separate due to payload damage during launch.
448:
Plans were also developed to build 10 follow-on stages, S-II-16 through -25, but funding to assemble them never materialized. These stages would have supported later Apollo missions, including those of the
422:
then decided that the initial specifications for the entire rocket were too small and so it was decided to increase the size of the stages used. This raised difficulties for the four remaining companies as
414:. At the same time the S-II stage design began to take shape. Initially it was to have four J-2 engines and be 74 feet (23 m) in length and 260 inches (6.6 m) in diameter.
469:
When fully loaded with propellant, the S-II had a mass of about 480 t (1,060,000 lb). The hardware was only 7.6% of this—92.4% was liquid hydrogen and liquid oxygen.
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container of 10 meters diameter and 6.7 meters high holding up to 83,000 US gallons (310 m) or 789,000 pounds (358 t) of oxidizer. It was formed by welding 12
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Subscale S-II tank assembly composed of two LH2 tank cylinders, a standard forward bulkhead, common dome, and aft skirt with a modified aft bulkhead. Tested in 1965.
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Assembly canceled in 1965 to prioritize work on the first flight stage, S-II-1. Testing requirements transferred to S-II-S, which was renamed S-II-S/D.
526:(large triangular sections) and two circular pieces for the top and bottom. The gores were shaped by positioning in a 211,000-liter tank of water with
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pattern. The second stage accelerated the Saturn V through the upper atmosphere with 1,000,000 pounds-force (4.4 MN) of thrust.
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First all-up S-II stage, assembled between 1963 and 1965. Completed several engine tests at the
Mississippi Test Facility (now the
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20:
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had still not yet decided on various aspects of the stage including size, and the upper stages that would be placed on top.
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The beginning of the S-II came in
December 1959 when a committee recommended the design and construction of a high-thrust,
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Carried cameras to record first stage separation, similar to Apollo 4. Two engines failed during ascent due to
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Carried "Camera
Targets" spaced around the forward skirt and carried cameras to record first stage separation
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The S-II was constructed vertically to aid welding and keep the large circular sections in the correct shape.
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Completed facilities checkouts and propellant load tests at
Kennedy Space Center in 1966 as part of the
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1800 kg lighter allowing 600 kg more payload, more powerful engines and carried more LOX
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stages) that included both the top of the LOX tank and bottom of the LH2 tank. It consisted of two
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From SA-515 the Skylab backup vehicle which NASA did not use. Also earmarked for Apollo 19.
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666:). Destroyed by accidental LH2 tank overpressurization during pressure testing May 28, 1966
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Used as
Dynamic Test Stage replacement after destruction of S-II-S/D and S-II-T
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1645:
Stages to Saturn: A Technological
History of the Apollo/Saturn Launch Vehicles
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1596:"Saturn Illustrated Chronology - Part 7: January 1966 through December 1966"
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1454:"Saturn Illustrated Chronology - Part 2: January 1961 through December 1961"
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At the bottom was the thrust structure supporting five J-2 engines in a
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arrangement. The center engine was fixed, while the other four were
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Second stage of the Saturn V, built by North
American Aviation
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Inboard engine failed during ascent due to pogo oscillation.
437:), with the manufacturing plant built by the government at
528:
three carefully orchestrated sets of underwater explosions
495:, the S-II used a common bulkhead (similar to that of the
406:
fueled engine. The contract for this engine was given to
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Demonstrated S-II's common bulkhead on a subscale tank
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56:. Unsourced material may be challenged and removed.
1469:"Manufacturing plan for Saturn S-II, Stages 16-25"
507:sheets separated by a honeycomb structure made of
362:(pronounced "S-two") was the second stage of the
1457:. NASA-Marshall Space Flight Center. p. 28.
465:Cutaway illustration of the S-II (second) stage
19:For the functionally-defined brain region, see
655:"All-systems" test vehicle for engine firings
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1310:Apollo 19, later Skylab 1 backup (not flown)
144:S-II stage during stacking operations in the
8:
1618:"Skylab rocket debris falls in Indian Ocean"
433:(who were also awarded the contract for the
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696:Destroyed in test stand September 29, 1965
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491:(empty container between tanks) like the
116:Learn how and when to remove this message
445:. 15 flight stages were to be produced.
398:S-II assembly building in Seal Beach, CA
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1302:From the cancelled Apollo 18 mission.
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775:and incorrect engine control wiring.
7:
1492:Apollo 18-19 Ground Ignition Weights
689:Structural and Dynamic Test Vehicle
54:adding citations to reliable sources
1598:. NASA-Marshall Space Flight Center
1512:"The Tortoise Steps of Saturn S-II"
205:480,000 kg (1,058,000 lb)
313:4,400 kN (1,000,000 lbf)
14:
569:Common Bulkhead Test Tank (CBTT)
410:and it would be later called the
213:443,000 kg (977,000 lb)
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480:, similar to the engines on the
30:
1648:. NASA History Series SP-4206.
221:36,200 kg (79,700 lb)
41:needs additional citations for
595:U.S. Space & Rocket Center
21:Secondary somatosensory cortex
1:
435:Apollo Command/Service Module
1657:Apollo Saturn Reference Page
419:Marshall Space Flight Center
323:421 seconds (4.13 km/s)
1642:Bilstein, Roger E. (1980).
1400:GPX (secondary coordinates)
451:Apollo Applications Program
1906:
272:November 9, 1967 (AS-501)
18:
1728:
1532:"Second Stage Fact Sheet"
1395:GPX (primary coordinates)
1370:Map all coordinates using
352:
290:
133:
1573:"Saturn Vehicle History"
1378:Download coordinates as:
366:rocket. It was built by
189:24.9 m (82 ft)
1339:29.554051°N 95.094266°W
621:34.710544°N 86.657185°W
431:North American Aviation
368:North American Aviation
181:General characteristics
1254:Apollo-Saturn V Center
1247:Apollo 18 (cancelled)
466:
399:
283:May 14, 1973 (AS-513)
197:10 m (33 ft)
1577:spacelaunchreport.com
1390:GPX (all coordinates)
1344:29.554051; -95.094266
1280:28.52385°N 80.68345°W
674:Dynamic test vehicle
626:34.710544; -86.657185
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1317:Johnson Space Center
1258:Kennedy Space Center
664:Stennis Space Center
530:to shape each gore.
487:Instead of using an
50:improve this article
1752:Gas-generator cycle
1427:Apollo (spacecraft)
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1285:28.52385; -80.68345
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599:Huntsville, Alabama
552:Serial number
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1831:Other LOX & LH
1624:. January 11, 1975
1583:on March 21, 2022.
1013:November 14, 1969
788:December 21, 1968
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378:(LOX) it had five
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1810:Canceled Vehicles
1774:Historic Vehicles
1693:J-2 rocket engine
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1216:34.000°N 19.000°W
1177:December 7, 1972
1126:January 31, 1971
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923:31.517°N 34.517°W
866:31.467°N 34.033°W
810:31.833°N 38.000°W
731:32.200°N 39.667°W
709:November 9, 1967
561:Current location
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260:Partial failure (
163:Country of origin
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1579:. Archived from
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61:Find sources:
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39:This article
37:
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27:
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1794:
1747:Bipropellant
1740:Technologies
1644:
1626:. Retrieved
1621:
1612:
1602:February 17,
1600:. Retrieved
1589:
1581:the original
1576:
1546:. Retrieved
1539:the original
1526:
1515:. Retrieved
1487:
1476:. Retrieved
1472:
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558:Launch date
545:Stages built
540:
532:
518:tank was an
513:
488:
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471:
468:
447:
428:
417:In 1961 the
416:
401:
359:
357:
269:First flight
249:(stage only)
153:Manufacturer
112:
103:
93:
86:
79:
72:
60:
48:Please help
43:verification
40:
1628:October 22,
1342: /
1283: /
1219: /
1094: /
1038: /
982: /
926: /
869: /
813: /
734: /
624: /
520:ellipsoidal
380:J-2 engines
280:Last flight
1872:Categories
1571:Kyle, Ed.
1548:2014-09-23
1517:2023-03-20
1478:2023-03-18
1438:References
1348: (
1329:95°05′39″W
1326:29°33′15″N
1289: (
1270:80°41′00″W
1267:28°31′26″N
1225: (
1100: (
1044: (
988: (
932: (
875: (
819: (
740: (
630: (
611:86°39′26″W
608:34°42′38″N
443:California
439:Seal Beach
408:Rocketdyne
374:(LH2) and
336:Propellant
302:Powered by
218:Empty mass
202:Gross mass
76:newspapers
1781:Saturn IB
1173:Apollo 17
1156:Apollo 16
1139:Apollo 15
1122:Apollo 14
1065:Apollo 13
1009:Apollo 12
953:Apollo 11
897:Apollo 10
686:S-II-S/D
489:intertank
478:gimballed
328:Burn time
247:Successes
106:July 2009
1888:Saturn V
1791:Saturn V
1700:Variants
1411:See also
1307:S-II-15
1244:S-II-14
1190:Skylab 1
1186:S-II-13
1169:S-II-12
1152:S-II-11
1135:S-II-10
840:Apollo 9
784:Apollo 8
762:Apollo 6
705:Apollo 4
577:Unknown
505:aluminum
474:quincunx
384:quincunx
370:. Using
364:Saturn V
285:Skylab 1
274:Apollo 4
262:Apollo 6
194:Diameter
175:Saturn V
142:Apollo 6
1857:Vulcain
1835:Engines
1473:uah.edu
1350:S-II-15
1291:S-II-14
1227:S-II-13
1206:19°00′W
1203:34°00′N
1118:S-II-9
1081:33°17′W
1078:32°19′N
1061:S-II-8
1025:34°13′W
1022:31°28′N
1005:S-II-7
969:34°51′W
966:31°32′N
949:S-II-6
913:34°31′W
910:31°31′N
893:S-II-5
853:31°28′N
836:S-II-4
797:31°50′N
780:S-II-3
758:S-II-2
721:39°40′W
718:32°12′N
701:S-II-1
671:S-II-D
652:S-II-T
647:stack.
645:SA-500F
593:At the
585:S-II-F
390:History
234:Retired
171:Used on
90:scholar
1817:Ares V
1102:S-II-8
1046:S-II-7
990:S-II-6
934:S-II-5
877:S-II-4
856:34°2′W
821:S-II-3
800:38°0′W
742:S-II-1
632:S-II-F
564:Notes
231:Status
186:Height
92:
85:
78:
71:
65:"S-II"
63:
1852:RL-10
1847:RS-68
1842:RS-25
1800:S-IVB
1785:S-IVB
1542:(PDF)
1535:(PDF)
1432:MS-II
1422:S-IVB
524:gores
501:S-IVB
382:in a
331:367 s
257:Other
97:JSTOR
83:books
1795:S-II
1722:J-2X
1717:J-2T
1712:J-2S
1650:NASA
1630:2014
1604:2011
1496:NASA
1417:S-IC
1313:N/A
1250:N/A
555:Use
533:The
514:The
499:and
497:S-IV
493:S-IC
482:S-IC
424:NASA
360:S-II
358:The
140:The
129:S-II
69:news
1821:EDS
1757:LOX
1707:J-2
1385:KML
535:LH2
516:LOX
412:J-2
347:LOX
146:VAB
52:by
1874::
1762:LH
1620:.
1575:.
1557:^
1503:^
1471:.
1256:,
597:,
453:.
441:,
345:/
340:LH
252:12
242:13
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1819:(
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113:(
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94:·
87:·
80:·
73:·
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23:.
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