A-001
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A-001 was the second abort test of the Apollo spacecraft.
| Mission Insignia | |
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| Mission Statistics | |
| Mission Name: | A-001 |
| Call Sign: | A-001 |
| Launch: | May 13, 1964 13:00:01 UTC White Sands Missile Range Launch Complex 36 |
| Landing: | May 13, 1964 13:05:51 UTC |
| Duration: | 5 min 50.3 s |
| Number of Orbits: | Suborbital |
| Apogee: | 5.64 mi - 9.08 km |
| Distance Traveled: | 4.24 mi - 6.82 km |
| A-001 | |
Little_Joe_II_launch.jpg
Objectives
Mission A-001 was the second in the series of tests conducted to demonstrate that the launch escape system could safely remove the command module under critical abort conditions. Unlike Pad Abort Test 1, in which the launch escape system was ignited at ground level, this mission was flown to demonstrate the capability of the escape system to propel the command module safely away from a launch vehicle while in the high-dynamic-pressure (transonic) region of the Saturn trajectory.
The launch vehicle was the second in the series of Little Joe II vehicles, which had been developed to accomplish early and economical testing of the launch escape system. The Little Joe II was propelled by seven solid-propellant rocket motors - one Algol sustainer motor, which provided thrust for about 42 seconds, and six Recruit motors, which burned out approximately 1.5 seconds after ignition. The spacecraft consisted of a launch escape system and a boilerplate command and service module (BP-12).
Flight
Unacceptable wind conditions had forced a 24 hour postponement of the launch, but the vehicle was successfully launched on May 13, 1964, at 05:59:59.7 a.m. M.S.T. (12:59:59.7 UTC). A ground commanded abort signal terminated thrust of the launch vehicle (by rupturing the Algol motor casing), ignited the launch escape and pitch control motors, and separated the command module from the service module. Some structural damage was incurred by the command module aft heat shield because of recontact with the booster at thrust termination. At approximately 44 seconds, the tower jettison motor was ignited and satisfactorily separated the launch escape tower from the command module.
The earth landing sequence was normal until a riser for one of the three main parachutes broke as a result of its rubbing against the structure on the command module upper deck. The parachute separated; however, the command module, supported by the two remaining parachutes, descended at rates of 30 to 26 ft/s (9.1 to 7.9 m/s) instead of the predicted 24 ft/s (7.3 m/s) with three parachutes. The command module landed 22,400 feet (6.8 km) down range at 350.2 seconds after attaining an altitude of 29,772 feet (9.1 km) above mean sea level. Except for the parachute failure, all test objectives were satisfied.
External links
- The Apollo Spacecraft: A Chronology (http://www.hq.nasa.gov/office/pao/History/SP-4009/cover.htm)
- Apollo Program Summary Report (http://history.nasa.gov/apsr/apsr.htm)
- Little Joe II Qualification Test Flight Report - September 1963 (PDF) (http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19790076764_1979076764.pdf)
- Little Joe II Progress Report - December 1964 (PDF) (http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19780070078_1978070078.pdf)
- Little Joe II Mission A-003 - April 1965 (PDF) (http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19790078425_1979078425.pdf)