AS-201
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| AS-201 | |
|---|---|
| Name | AS-201 |
| Mission type | Uncrewed suborbital test flight |
| Operator | NASA |
| Mission duration | 37 minutes, 19.7 seconds |
| Distance travelled | 8,472 km (5,264 mi) |
| Apogee | 488 km (303 mi) |
| Spacecraft | Apollo CSM-009 |
| Manufacturer | North American Aviation |
| Launch mass | 20,820 kg (45,900 lb) |
| Rocket | Saturn IB SA-201 |
| Launch site | Cape Canaveral LC-34 |
| Launch date | February 26, 1966, 16:12:01 UTC |
| Landing date | February 26, 1966, 16:49:21 UTC |
| Recovery by | USS ''Boxer'' |
| Orbit regime | Suborbital |
| Programme | Apollo program |
| Previous mission | Apollo-Saturn 204 |
| Next mission | AS-203 |
AS-201. It was the first uncrewed test flight of the Saturn IB launch vehicle and the Block I version of the Apollo command and service module. Launched on February 26, 1966, the mission successfully demonstrated the Saturn IB's performance and the command module's basic spaceworthiness, though several spacecraft systems experienced significant problems. The flight was a critical step in the Apollo program, validating hardware essential for future crewed missions to the Moon.
Mission overview
The primary objectives of the mission were to verify the structural integrity and compatibility of the Saturn IB rocket and the Apollo spacecraft during launch. Engineers from NASA and contractors like North American Aviation sought to test the S-IB and S-IVB rocket stages under flight conditions. A key goal was to evaluate the command module's heat shield during a high-energy reentry, simulating the conditions of a return from lunar orbit. The flight plan called for a suborbital trajectory, with the spacecraft splashing down in the South Atlantic Ocean near Ascension Island.
Spacecraft and launch vehicle
The flight utilized the Saturn IB designated SA-201, which was more powerful than the earlier Saturn I and capable of launching a fully fueled Apollo command and service module into low Earth orbit. The spacecraft was CSM-009, a Block I model not designed for docking with a Lunar Module. It was equipped with functional reaction control system thrusters and a Service Propulsion System engine for in-space maneuvers. The command module lacked crew couches and many life support systems, as it was an engineering test article built by North American Aviation under the supervision of NASA's Manned Spacecraft Center.
Flight
Liftoff from Launch Complex 34 at Cape Canaveral occurred successfully at 16:12 UTC. The S-IB first stage and S-IVB second stage performed nominally, injecting the spacecraft onto its planned ballistic arc. After separation, the Service Propulsion System engine fired twice to increase reentry velocity. However, electrical power failures caused a premature shutdown of the first burn and affected other systems. The spacecraft achieved an apogee of 488 kilometers before reentering the atmosphere at approximately 8,300 meters per second, subjecting the heat shield to severe thermal loads. It splashed down as planned and was recovered by the aircraft carrier USS ''Boxer''.
Aftermath and significance
Post-flight analysis by teams at the Manned Spacecraft Center and Marshall Space Flight Center confirmed the Saturn IB's design was sound, a major milestone for the Apollo program. The problems with the spacecraft's electrical system and a pressure loss in the Service Propulsion System were thoroughly investigated, leading to design modifications for subsequent missions like AS-202 and Apollo 4. While the mission was only partially successful, it provided invaluable data that directly contributed to the success of the first crewed Apollo mission, Apollo 7. The flight proved the fundamental capability of the Saturn IB and Apollo spacecraft stack, paving the way for orbital tests and eventual lunar voyages.