A-003
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| Mission Insignia | |
|---|---|
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| Mission Statistics | |
| Mission Name: | A-003 |
| Call Sign: | A-003 |
| Launch: | May 19, 1965 13:01:04 UTC White Sands Missile Range Launch Complex 36 |
| Landing: | May 19, 1965 13:06:07 UTC |
| Duration: | 5 min 2.8 s |
| Number of Orbits: |
Suborbital |
| Apogee: | 3.75 mi (6.04 km) |
| Distance Traveled: |
3.45 mi (5.55 km) |
| A-003 | |
A-003 was the fourth abort test of the Apollo spacecraft.
[edit] Objectives
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 unmanned 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.
[edit] Flight
The test vehicle was launched on May 19, 1965, at 06:01:04 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 resulting roll rate caused the launch vehicle to break up before second-stage ignition, and a low-altitude spacecraft 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. The command module forward heat shield was protected by the hard portion of the boost protective cover and was jettisoned satisfactorily in an apex-forward attitude at low altitude. The soft portion of the boost protective cover remained intact until tower jettison. At tower jettison, part of the cover stayed with the command module for a short time although the rest of the cover moved away with the tower. The hard portion of the boost protective cover remained intact until ground impact. Both drogue parachutes inflated, even under the severe conditions that existed; that is, command module apex forward and rolling. The command module was effectively stabilized and oriented for deployment of the main parachutes.
Because of the early launch vehicle breakup, the desired altitude of 120,000 feet (36.6 km) was not achieved. However, the spacecraft did demonstrate a successful low-altitude abort at 12,400 ft (3.8 km) from a rapidly rolling (approximately 335 degrees per second) launch vehicle. The Mach number, dynamic pressure, and altitude at the time of abort were similar to Saturn IB or Saturn V launch trajectory conditions.
[edit] External links
- The Apollo Spacecraft: A Chronology
- Apollo Program Summary Report
- Little Joe II Qualification Test Flight Report - September 1963 (PDF)
- Little Joe II Progress Report - December 1964 (PDF)
- Little Joe II Mission A-003 - April 1965 (PDF)
- Project Apollo flight-test report, boilerplate 22 - August 1965 (PDF)
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