AS-104
AS-104 was the fourth orbital test of a boilerplate Apollo spacecraft, and the second flight of the Pegasus micrometeroid detection satellite. It was launched by SA-8, the ninth Saturn I carrier rocket.
![]() Launch of Saturn AS-104 | |
Mission type | Spacecraft aerodynamics; micrometeroid investigation |
---|---|
Operator | NASA |
COSPAR ID | 1965-039B |
SATCAT no. | 1385 |
Mission duration | 5,275 days |
Distance travelled | 3,282,050,195 kilometers (2.039371443×109 mi) |
Orbits completed | ~79,790 |
Spacecraft properties | |
Spacecraft | Apollo BP-26 Pegasus 2 |
Launch mass | 1,451.5 kilograms (3,200 lb) |
Start of mission | |
Launch date | May 25, 1965, 07:35:01 UTC |
Rocket | Saturn I SA-8 |
Launch site | Cape Kennedy LC-37B |
End of mission | |
Decay date | July 8, 1989 |
Orbital parameters | |
Reference system | Geocentric |
Regime | Low Earth orbit |
Perigee altitude | 511 kilometers (318 mi) |
Apogee altitude | 739 kilometers (459 mi) |
Inclination | 31.7 degrees |
Period | 97.2 minutes |
Epoch | 4 July 1965[1] |
Objectives
The primary mission objective was to demonstrate the launch vehicle's iterative guidance mode and to evaluate system accuracy. The launch trajectory was similar to that of mission AS-103.
The Saturn launch vehicle SA-8 and payload were similar to those of mission AS-103, except that a single reaction control engine assembly was mounted on the boilerplate service module (BP-26). The assembly was instrumented to acquire additional data on launch environment temperatures. This assembly also differed from the one on the AS-101 mission in that two of the four engines were of a prototype configuration instead of all engines being simulated.
Launch
This was the first nighttime launch in the Saturn I series. A built-in 35 minute hold was used to ensure that launch time coincided with the opening of the launch window.
AS-104 was launched from Cape Kennedy Launch Complex 37B at 02:35:01 a.m. EST (07:35:01 GMT) on May 25. 1965, The launch was normal and the payload was inserted into orbit approximately 10.6 minutes after lift-off. The total mass placed in orbit, including the spacecraft, Pegasus B, adapter, instrument unit, and S-IV stage, was 34,113 pounds (15,473 kg). The perigee and apogee were 314.0 and 464.1 miles (505 and 747 km), respectively; the orbital inclination was 31.78'. The 1397 kilogram (3080-pound) Pegasus 2 satellite was also carried to orbit by SA-8, being stowed inside the boilerplate's service module, and remaining attached to the S-IV stage.
The actual trajectory was close to the one predicted, and the spacecraft was separated 806 seconds after lift-off. Several minor malfunctions occurred in the S-I stage propulsion system; however, all mission objectives were achieved.
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References
- McDowell, Jonathan. "Satellite Catalog". Jonathan's Space Page. Retrieved 31 October 2013.
External links
- NSSDC: SA-8
- SA-8 Operational Trajectory
- Manned space flight network performance analysis for the SA-8 mission
- SA-8 flight test data report
This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.