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'''A-101'''<ref>[http://science.ksc.nasa.gov/history/apollo/sa-6/sa-6.html NASA: ''A-101'']</ref> was the first [[Boilerplate (spaceflight)|boilerplate]] test flight of the [[Apollo spacecraft]], which was launched using ''SA-6'',<ref name="NSSDC">[http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1964-025A NSSDC: ''SA-6'']</ref> the sixth [[Saturn I]] rocket to fly. The flight took place in 1964. |
'''A-101'''<ref>[http://science.ksc.nasa.gov/history/apollo/sa-6/sa-6.html NASA: ''A-101'']</ref> was the first [[Boilerplate (spaceflight)|boilerplate]] test flight of the [[Apollo spacecraft]], which was launched using ''SA-6'',<ref name="NSSDC">[http://nssdc.gsfc.nasa.gov/nmc/masterCatalog.do?sc=1964-025A NSSDC: ''SA-6'']</ref> the sixth [[Saturn I]] rocket to fly. The flight took place in 1964. |
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==Boilerplate Apollo == |
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The first five launches of the Saturn I had carried [[Jupiter-C]] |
The first five launches of the Saturn I had carried [[Jupiter-C]] nosecones, a proven design which allowed engineers to focus on development of the rocket. The [[Apollo Command/Service Module]] (CSM) launch aerodynamics had to be verified, therefore A-101 carried BP-13, a [[boilerplate (spacecraft)|boilerplate spacecraft]] which weighed {{convert|17000|lb|kg}} and duplicated the size and shape of the CSM, and a dummy [[Launch Escape System]] (LES) tower. A flight-weight Command Module weighed around {{convert|12000|lb|kg}}.<ref name="NSSDC"/> The boilerplate spacecraft was instrumented with 116 sensors reading strain, pressure, and acceleration. |
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This allowed it to be instrumented with 116 measuring devices so that engineers could see the strain, pressure, and acceleration experienced by the spacecraft, which they hoped would confirm their calculations. |
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== Flight == |
== Flight == |
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This article's lead section may be too short to adequately summarize the key points. Please consider expanding the lead to provide an accessible overview of all important aspects of the article. (December 2010)
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A-101 (SA-6)
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| Mission type | Test flight |
|---|---|
| Operator | NASA |
| COSPAR ID | 1964-025A  |
| SATCAT no. | 800 |
| Mission duration | ~5 hours, 53 minutes |
| Orbits completed | 54 |
| Spacecraft properties | |
| Spacecraft | Apollo BP-13 |
| Launch mass | 7,700 kilograms (17,000 lb) |
| Start of mission | |
| Launch date | May 28, 1964, 17:07:00 (1964-05-28UTC17:07Z) UTC |
| Rocket | Saturn I SA-6 |
| Launch site | Cape Canaveral LC-37B |
| End of mission | |
| Disposal | Uncontrolled reentry |
| Last contact | May 28, 1964 (1964-05-29) after 4 orbits |
| Decay date | June 1, 1964 |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Low Earth |
| Perigee altitude | 178 kilometers (96 nmi) |
| Apogee altitude | 199 kilometers (107 nmi) |
| Inclination | 31.7 degrees |
| Period | 88.26 minutes |
| Epoch | 30 May 1964[1] |
Project Apollo
Unmanned test flights
A-102 → | |
A-101[2] was the first boilerplate test flight of the Apollo spacecraft, which was launched using SA-6,[3] the sixth Saturn I rocket to fly. The flight took place in 1964.
The first five launches of the Saturn I had carried Jupiter-C nosecones, a proven design which allowed engineers to focus on development of the rocket. The Apollo Command/Service Module (CSM) launch aerodynamics had to be verified, therefore A-101 carried BP-13, a boilerplate spacecraft which weighed 17,000 pounds (7,700 kg) and duplicated the size and shape of the CSM, and a dummy Launch Escape System (LES) tower. A flight-weight Command Module weighed around 12,000 pounds (5,400 kg).[3] The boilerplate spacecraft was instrumented with 116 sensors reading strain, pressure, and acceleration.
It took three attempts to launch the rocket from LC-37B. The first attempt was scrubbed after the liquid oxygen damaged a wire mesh screen during a test, causing fuel contamination. The second attempt was scrubbed after the rocket's guidance system overheated due to failure of an air conditioning compressor.
The vehicle finally lifted off on May 28, 1964. There had been several delays during the count as liquid oxygen vapors obscured an optical window in the SA-6's instrument unit, so that a ground-based theodolite could not see it. This theodolite was required by the countdown computer in order for launch to proceed. Engineers deemed it non-critical and reprogrammed the computer, allowing the launch to proceed.
The ascent was normal up to 116.9 seconds after liftoff, at which point engine number eight shut off early. This was not planned, as it had been on SA-4 as a test, but the rocket compensated perfectly by burning the remaining fuel in the other seven engines for 2.7 seconds longer than planned. The first stage separated and the second stage ignited. Ten seconds later, the Launch Escape System was jettisoned as planned. Also jettisoned from the first stage were eight film cameras that observed separation of the stages.
The second stage cut off at 624.5 seconds after launch (1.26 seconds earlier than predicted), with the stage and boilerplate spacecraft in a 182 kilometers (98 nautical miles) by 227 kilometers (123 nautical miles) orbit. It continued to transmit data for four orbits, after which the batteries failed. The vehicle made a total of 54 orbits, re-entering the atmosphere east of Canton Island in the Pacific Ocean on June 1.
Engineers were quick to find the cause of the failure of engine number eight. The teeth on one of the gears in the turbopump were stripped off. This did not cause any delays in the next launches as engineers had already decided that the gear design was inferior and were planning to change it for the next launch. This was the only problem encountered with an H-1 engine during a flight.
This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.
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