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{{Short description|Uncrewed flight of the Saturn IB rocket, July 5, 1966}} |
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{{Infobox spaceflight |
{{Infobox spaceflight |
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| name = AS-203 |
| name = AS-203 |
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| destroyed = {{end-date|July 5, 1966}} |
| destroyed = {{end-date|July 5, 1966}} |
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| orbit_epoch = July 5, 1966<ref name=satcat>{{cite web|last=McDowell|first=Jonathan|title=SATCAT|url=http://planet4589.org/space/log/satcat.txt|publisher=Jonathan's Space Pages| |
| orbit_epoch = July 5, 1966<ref name=satcat>{{cite web|last=McDowell|first=Jonathan|title=SATCAT|url=http://planet4589.org/space/log/satcat.txt|publisher=Jonathan's Space Pages|accessdate=March 23, 2014}}</ref> |
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| orbit_reference = [[geocentric orbit|Geocentric]] |
| orbit_reference = [[geocentric orbit|Geocentric]] |
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'''AS-203''' ( |
'''AS-203''' (or '''SA-203''') was an uncrewed flight of the [[Saturn IB]] rocket on July 5, 1966. It carried no [[command and service module]], as its purpose was to verify the design of the [[S-IVB]] rocket stage restart capability that would later be used in the [[Apollo program]] to boost astronauts from Earth orbit to a trajectory towards the Moon. It successfully achieved its objectives, but the stage was inadvertently destroyed after four orbits. |
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==Objectives== |
==Objectives== |
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| title = Evaluation of AS-203 Low Gravity Orbital Experiment |
| title = Evaluation of AS-203 Low Gravity Orbital Experiment |
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| date = 13 January 1967 |
| date = 13 January 1967 |
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| pages = |
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| publisher = NASA |
| publisher = NASA |
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| url = https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19680012073_1968012073.pdf |
| url = https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19680012073_1968012073.pdf |
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| doi = |
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}} |
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| id = }} |
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</ref> |
</ref> |
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In the spring of 1966, the decision was made to launch AS-203 before [[AS-202]], as the CSM that was to be flown on AS-202 was delayed. The S-IVB stage arrived at [[Cape Canaveral Air Force Station|Cape Kennedy]] on 6 April 1966; the S-IB first stage arrived six days later, and the Instrument Unit came two days after that. |
In the spring of 1966, the decision was made to launch AS-203 before [[AS-202]], as the CSM that was to be flown on AS-202 was delayed. The S-IVB stage arrived at [[Cape Canaveral Air Force Station|Cape Kennedy]] on 6 April 1966; the S-IB first stage arrived six days later, and the Instrument Unit came two days after that. |
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On April 19, technicians began to erect the booster at Pad 37B. Once again, the testing regimen ran into problems that had plagued AS-201, including cracked solder joints in the printed-circuit boards, requiring over 8,000 |
On April 19, technicians began to erect the booster at Pad 37B. Once again, the testing regimen ran into problems that had plagued AS-201, including cracked solder joints in the printed-circuit boards, requiring over 8,000 to be replaced. |
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In June 1966, three Saturn rockets could be seen set up on various pads across the Cape: at Pad 39A was a full-size mock-up of the Saturn V; AS-202 was at Pad 34; and AS-203 was at 37B. |
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==Flight== |
==Flight== |
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The rocket launched on the first attempt on July 5. The [[S-IVB]] and |
The rocket launched on the first attempt on July 5. The [[S-IVB]] and IU were inserted into a {{convert|100|nmi|km mi|adj=on}} circular orbit. |
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The S-IVB design test objectives were carried out on the first two orbits, and the hydrogen was found to behave mostly as predicted, with sufficient control over its location and of engine temperatures required for restart. The next two orbits were used for extra experiments to obtain information for use in future cryogenic stage designs. These included a free-coast experiment to observe and control the negative acceleration of the fuel caused by the small amount of aerodynamic drag on the vehicle; a rapid fuel tank depressurization test; and a closed fuel tank pressurization test. |
The S-IVB design test objectives were carried out on the first two orbits, and the hydrogen was found to behave mostly as predicted, with sufficient control over its location and of engine temperatures required for restart. The next two orbits were used for extra experiments to obtain information for use in future cryogenic stage designs. These included a free-coast experiment to observe and control the negative acceleration of the fuel caused by the small amount of aerodynamic drag on the vehicle; a rapid fuel tank depressurization test; and a closed fuel tank pressurization test. |
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The closed fuel tank experiment involved pressurizing the hydrogen tank by closing its vents, while depressurizing the oxygen tank by allowing it to continue venting. It was expected that the pressure difference between the two tanks (measured as high as {{convert|39.4|psi|kPa}} would collapse the common bulkhead separating them, as happened in a ground test. The rupture occurred during the two-minute loss of signal between the [[Lyndon B. Johnson Space Center|Manned Spacecraft Center]] and the [[Trinidad]] [[Missile Test Project#Tracking stations|tracking station]]. The Trinidad radar image indicated the vehicle was in multiple pieces, and telemetry was never re-acquired. NASA concluded that a spark or impact must have ignited the propellants, causing an explosion. |
The closed fuel tank experiment involved pressurizing the hydrogen tank by closing its vents, while depressurizing the oxygen tank by allowing it to continue venting. It was expected that the pressure difference between the two tanks (measured as high as {{convert|39.4|psi|kPa}}) would collapse the common bulkhead separating them, as happened in a ground test. The rupture must have occurred during the two-minute loss of signal between the [[Lyndon B. Johnson Space Center|Manned Spacecraft Center]] and the [[Trinidad]] [[Missile Test Project#Tracking stations|tracking station]]. The Trinidad radar image indicated the vehicle was in multiple pieces, and telemetry was never re-acquired. NASA concluded that a spark or impact must have ignited the propellants, causing an explosion. |
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Despite the destruction of the stage, the mission was classified as a success, having achieved all of its primary objectives and validating the design concept of the restartable S-IVB-500 version. In September [[Douglas Aircraft Company]], which built the S-IVB, declared that the design was ready for use on the Saturn V to send men to the Moon. |
Despite the destruction of the stage, the mission was classified as a success, having achieved all of its primary objectives and validating the design concept of the restartable S-IVB-500 version. In September [[Douglas Aircraft Company]], which built the S-IVB, declared that the design was ready for use on the Saturn V to send men to the Moon. |
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{{Commons category|AS-203}} |
{{Commons category|AS-203}} |
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{{Portal|Spaceflight}} |
{{Portal|Spaceflight}} |
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*[https://www.youtube.com/watch?v=fIwhRSoeZSE AS-203 Launch Video] |
*[https://www.youtube.com/watch?v=fIwhRSoeZSE AS-203 Launch Video] |
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*[https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1966-059A NASA Space Science Data Coordinated Archive] |
*[https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1966-059A NASA Space Science Data Coordinated Archive] |
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*[http://www.hq.nasa.gov/office/pao/History/SP-4204/cover.html Moonport: A History of Apollo Launch Facilities and Operations ] |
*[http://www.hq.nasa.gov/office/pao/History/SP-4204/cover.html Moonport: A History of Apollo Launch Facilities and Operations ] |
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*[http://www.hq.nasa.gov/office/pao/History/SP-4205/cover.html Chariots for Apollo: A History of Manned Lunar Spacecraft ] |
*[http://www.hq.nasa.gov/office/pao/History/SP-4205/cover.html Chariots for Apollo: A History of Manned Lunar Spacecraft ] |
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{{Apollo program| before=[[AS-201]]| after=[[AS-202]]}} |
{{Apollo program| before=[[AS-201]]| after=[[AS-202]]}} |
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[[Category:Test spaceflights]] |
[[Category:Test spaceflights]] |
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[[Category:Spacecraft launched by Saturn rockets]] |
[[Category:Spacecraft launched by Saturn rockets]] |
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[[Category:Saturn IB]] |
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