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AS-104

AS-104

Launch of Saturn AS-104
Mission type	Spacecraft aerodynamics; micrometeoroid investigation
Operator	NASA
COSPAR ID	1965-039B
SATCAT no.	1385
Mission duration	8,810 days[1]
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 (1965-05-25UTC07:35:01Z) UTC
Rocket	Saturn I SA-8
Launch site	Cape Kennedy LC-37B
End of mission
Decay date	July 8, 1989 (1989-07-09)[1]
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[2]
Apollo program ← AS-103 AS-105 →

AS-104 was the fourth orbital test of a boilerplate Apollo spacecraft, and the second flight of the Pegasus micrometeoroid detection satellite. It was launched by SA-8, the ninth Saturn I carrier rocket.

Objectives[edit]

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[edit]

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 2:35:01 a.m. EST (07:35:01 GMT) on May 25, 1965.^[3] 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.^[4][5]

Wikimedia Commons has media related to Saturn-Apollo 8.

References[edit]

External links[edit]

• NSSDC: SA-8
• Manned space flight network performance analysis for the SA-8 mission

 This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.