 Little Joe II launch with A-001 | |
| Mission type | Abort test |
|---|---|
| Operator | NASA |
| Mission duration | 5 minutes, 50.3 seconds |
| Distance travelled | 6.82 kilometers (4.24 mi) |
| Apogee | 9.08 kilometers (5.64 mi) |
| Spacecraft properties | |
| Spacecraft | Apollo BP-12 |
| Start of mission | |
| Launch date | May 13, 1964, 12:59:59 UTC |
| Rocket | Little Joe II |
| Launch site | White Sands LC-36 |
| End of mission | |
| Landing date | May 13, 1964, 13:05:51 UTC |
 Project Apollo Abort Tests | |
A-001 was the second abort test of the Apollo spacecraft.
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).
Unacceptable wind conditions had forced a 24-hour postponement of the launch, but the vehicle was successfully launched on May 13, 1964, at 12:59:59.7 UTC (05:59 am MST). 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 9.1 to 7.9 metres per second (30 to 26 ft/s) instead of the predicted 7.3 metres per second (24 ft/s) with three parachutes. The command module landed 6.8 kilometres (22,400 ft) downrange at 350.2 seconds after attaining an altitude of 9.075 kilometres (29,772 ft) above mean sea level. Except for the parachute failure, all test objectives were satisfied.
The boilerplate is currently located at the Columbia Memorial Space Center in Downey, California.
This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration .
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AS-201, flown February 26, 1966, was the first uncrewed test flight of an entire production Block I Apollo command and service module and the Saturn IB launch vehicle. The spacecraft consisted of the second Block I command module and the first Block I service module. The suborbital flight was a partially successful demonstration of the service propulsion system and the reaction control systems of both modules, and successfully demonstrated the capability of the command module's heat shield to survive re-entry from low Earth orbit.
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The Apollo command and service module (CSM) was one of two principal components of the United States Apollo spacecraft, used for the Apollo program, which landed astronauts on the Moon between 1969 and 1972. The CSM functioned as a mother ship, which carried a crew of three astronauts and the second Apollo spacecraft, the Apollo Lunar Module, to lunar orbit, and brought the astronauts back to Earth. It consisted of two parts: the conical command module, a cabin that housed the crew and carried equipment needed for atmospheric reentry and splashdown; and the cylindrical service module which provided propulsion, electrical power and storage for various consumables required during a mission. An umbilical connection transferred power and consumables between the two modules. Just before reentry of the command module on the return home, the umbilical connection was severed and the service module was cast off and allowed to burn up in the atmosphere.
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A-002 was the third abort test of the Apollo spacecraft.
A-003 was the fourth abort test of the Apollo spacecraft. This particular flight is notable because during the abort test flight, an actual abort situation occurred, and further proved the Apollo launch escape system (LES). The CM was successfully pulled away from the malfunctioning Little Joe booster and it landed safely under parachutes.
A-004 was the sixth and final test of the Apollo launch escape vehicle and the first flight of a Block I production-type Apollo Command/Service Module.
QTV was the first test flight of the Apollo Little Joe II rocket. It was launched in August 1963.
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