| Apollo-Saturn 202 | |||||
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| Mission name | Apollo-Saturn 202 | ||||
| Command Module | CM-011 12,061 pounds (5,471 kg) |
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| Service Module | SM-011 32,233 pounds (14,621 kg) |
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| Spacecraft mass | 44,294 pounds (20,091 kg) | ||||
| Launch pad | Cape Canaveral Complex 34 |
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| Launch date | August 25, 1966 17:15:32 UTC |
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| Landing | August 25, 1966 18:48:34 UTC North Pacific Ocean |
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| Mission duration | 1 h 33 min 2 s | ||||
| Apogee | 617.1 nautical miles (1,142.9 km; 710.1 mi) | ||||
| Distance traveled | 13,900 nautical miles (25,700 km; 16,000 mi) | ||||
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AS-202 (also referred to as SA-202) was the second unmanned, suborbital test flight of a production Block I Apollo Command/Service Module launched with the Saturn IB launch vehicle. It launched August 25, 1966 and was the first flight which included the spacecraft Guidance and Navigation Control system and fuel cells. The success of this flight enabled the Apollo program to judge the Block I spacecraft and Saturn IB ready to carry men into orbit.
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AS-202 was the third test flight of the Saturn IB, because a delay in the readiness of the Apollo spacecraft 011 pushed its launch past the July 1966 launch of AS-203. It was designed to test the rocket more than had been done on AS-201 by launching the rocket higher and having the flight lasting twice as long. It would also test the Command and Service Module (CSM-011) by having the engine firing four times during the flight.
The flight was also designed to test out the heat shield by subjecting it to 260 megajoules per square metre. Over the course of the reentry it generated equivalent energy needed to power Los Angeles for over one minute in 1966.
CSM-011 was basically a production model capable of carrying a crew. However it lacked the crew couches and some displays that would be included on later missions for the astronauts. This was the first flight of the guidance and navigation system as well as the fuel cell electrical system.
AS-202 was launched 25 August 1966 from Pad 34. The launch phase was perfectly nominal with the first stage burning for just under two and a half minutes lifting the rocket to 56 km in altitude and 56 km downrange from the launch pad. The second stage burned for a further seven and half minutes putting the spacecraft into a ballistic trajectory with a maximum altitude of 216 km.
The CSM was preprogrammed to make four burns of its Service Propulsion System (SPS). The first occurred a couple of seconds after separation from the S-IVB second stage. It burned for 3 minutes, 35 seconds lifting the spacecraft apogee to 1,128.6 km.
The second burn was 25 minutes later lasting one minute 28 seconds. Two more burns each of three seconds were done ten seconds later to test the rapid restart capabilities of the engine.
As well as testing the SPS, these burns accelerated the spacecraft for an 8900 meters per second reentry. The reentry was a roller coaster like ride, with the spacecraft first dipping down from 122,000 m to 66,000 m. It then lifted back up to 81,000 m. By this time it had shed 1,300 meter/second in speed. It then dipped down for the last time. The main parachutes deployed at 7250 meters in altitude. It splashed down 370 km from the target landing site and it took the USS Hornet 8 hours and 30 minutes to reach the capsule. The Apollo AS-202 command module landed at 16.12° N - 168.9° E.
The capsule is currently on display on the Hornet. The ship is open to the public as a museum in Alameda, California.
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