|Mission type||Abort test|
|Mission duration||6 minutes, 50 seconds|
|Distance travelled||34.63 kilometers (21.52 mi)|
|Apogee||23.83 kilometers (14.81 mi)|
|Start of mission|
|Launch date||January 20, 1966, 15:17:01UTC|
|Rocket||Little Joe II|
|Launch site||White Sands LC-36|
|End of mission|
|Landing date||January 20, 1966, 15:23:51UTC|
Mission A-004 was uncrewed and was conducted to demonstrate that
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 (Block I production model 002), 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.
The vehicle was launched on January 20, 1966, at 8:17:01 a.m. MST (15:17:01 UTC) after several postponements due to technical difficulties and adverse weather conditions. The pitch up 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.
This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.