Manned Space History | Little Joe II | May 19 1965 |
Apollo mission A-003 was the fourth mission to demonstrate the abort capability of the Apollo launch escape system. The purpose of this flight was to demonstrate launch escape vehicle performance at an altitude approximating the upper limit for the canard subsystem.
The launch vehicle was similar to the one used for mission A-002 except that the propulsion system consisted of six Algol motors. The uncrewed flight test vehicle consisted of an Apollo boilerplate command and service module (BP-22) and a launch escape system similar to the one used on the previous mission. The command module Earth landing system configuration was refined to be more nearly like that of the planned production system, and a forward heat shield jettisoning system was provided.
The test vehicle was launched on May 19, 1965, at 6:01:04 a.m. M.S.T. (13:01:04 UTC). Within 2.5 seconds after lift-off, a launch malfunction caused the vehicle to go out of control. The launch vehicle entered into a roll which caused it to break up before second-stage ignition, and a low-altitude abort was initiated instead of the planned high-altitude abort. The launch escape system canard surfaces deployed and survived the severe environment. The high roll rates (approximately 260 degrees per second at the time of canard deployment) induced by the launch vehicle malfunction stabilized the launch escape vehicle in a tower-forward attitude, which overcame the destabilizing effect of the canards. Post-flight simulations verified the ineffectiveness of the canards at the high roll rate, but showed that canards would be effective at the 20 degree per second roll rate limit of the Saturn emergency detection system.
All spacecraft systems operated satisfactorily.
FOOTAGE: NASA