A-004

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A-004
Little Joe II A-004.jpg
Little Joe II A-004, White Sands, New Mexico
Mission type Abort test
Operator NASA
Mission duration 6 minutes, 50 seconds
Distance travelled 34.63 kilometers (21.52 mi)
Apogee 23.83 kilometers (14.81 mi)
Spacecraft properties
Spacecraft Apollo CM-002
Start of mission
Launch date January 20, 1966, 15:17:01 (1966-01-20UTC15:17:01Z) UTC
Rocket Little Joe II
Launch site White Sands LC-36
End of mission
Landing date January 20, 1966, 15:23:51 (1966-01-20UTC15:23:52Z) UTC

Apollo program insignia.png


Project Apollo
Abort Tests
← Pad Abort Test 2

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.

Objectives[edit]

Mission A-004 was unmanned and was conducted to demonstrate that

  1. The launch escape vehicle would satisfactorily orient and stabilize itself in the proper attitude after being subjected to a high rate of tumbling during the powered phase of an abort
  2. The escape vehicle would maintain its structural integrity under test conditions in which the command module structure was loaded to the design limit.

The launch vehicle was the fifth and final Little Joe II flown. The propulsion system consisted of four Algol and five Recruit rocket motors. The attitude control system was similar to the one used on mission A-003 except that the reaction control system was deleted and the vehicle was provided with the capability of responding to a radio-transmitted pitch up command. The pitch up maneuver was required to help initiate tumbling of the launch vehicle. The spacecraft for this mission consisted of a modified Block I command and service module boilerplate, BP-2, and a modified Block I launch escape system (airframe 002). The center of gravity and thrust vector were changed to assure that power-on tumbling would be attained after abort initiation. The earth landing system was essentially the same as that used during Pad Abort Test 2.

Flight[edit]

The vehicle was launched on January 20, 1966, at 08:17:01 a.m. MST (15:17:01 UTC) after several postponements due to technical difficulties and adverse weather conditions. The pitchup maneuver was commanded from the ground when telemetry showed that the desired altitude and velocity conditions had been reached. The planned abort was automatically initiated 2.9 seconds later. The launch escape vehicle tumbled immediately after abort initiation. Pitch and yaw rates reached peak values of 160 degrees per second, and roll rates reached a peak of minus 70 degrees per second. The launch escape system canard surfaces deployed at the proper time and stabilized the command module with the aft heat shield forward after the escape vehicle had tumbled about four times. Tower jettison and operation of the earth landing systems were normal, and the command module landed about 113,620 feet (34.6 km) from the launch pad after having reached a maximum altitude of 78,180 feet (23.8 km) above mean sea level.

All systems performed satisfactorily, and the dynamic loads and structural response values were within the design limits and predicted values. Although a structural loading value of primary interest was not achieved (local differential pressure between the interior and exterior of the command module wall), all test objectives were satisfied.

Boilerplate location[edit]

The boilerplate spacecraft is currently on display at the Cradle of Aviation.[1]

References[edit]

  1. ^ http://www.cradleofaviation.org/history/permanent_exhibits/exploring_space/rockwell_command_module_002.html

External links[edit]

 This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.