 Launch of SA-10 carrying AS-105 | |
| Mission type | Spacecraft aerodynamics; micrometeoroid investigation |
|---|---|
| Operator | NASA |
| COSPAR ID | 1965-060B |
| SATCATno. | 1468 |
| Distance travelled | 912,064,090 kilometers (566,730,350 mi) |
| Orbits completed | ~22,152 |
| Spacecraft properties | |
| Spacecraft | Apollo BP-9 Pegasus 3 |
| Launch mass | 1,451 kilograms (3,199 lb) |
| Start of mission | |
| Launch date | July 30, 1965, 13:00:00 (1965-07-30UTC13Z) UTC |
| Rocket | Saturn I SA-10 |
| Launch site | Cape KennedyLC-37B |
| End of mission | |
| Decay date | November 22, 1975 (1975-11-23)[1] |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Low Earth orbit |
| Perigee altitude | 521 kilometers (324 mi) |
| Apogee altitude | 536 kilometers (333 mi) |
| Inclination | 28.8 degrees |
| Period | 95.2 minutes |
| Epoch | 3 September 1965[1] |
AS-105 was the fifth and finalorbital flight of aboilerplateApollo spacecraft, and the third and final launch of aPegasus micrometeoroid detection satellite. It was launched bySA-10, the tenth and finalSaturn I rocket, in 1965.
AS-105 was anApolloboilerplate spacecraft; boilerplate BP-9A was used for the flight. The spacecraft reentered on November 22, 1975.[2] The Saturn launch vehicle (SA-10) was similar to those of missions AS-103 and AS-104. As on the previous mission, the boilerplateservice module was equipped with a test installation of a reaction control engine package.
The primary flight objective was to continue demonstration of the launch vehicle's iterative guidance mode and evaluation of system accuracy.
AS-105 was launched fromCape Kennedy Launch Complex 37B at 08:00EST (13:00GMT) on July 30, 1965, on the last Saturn I rocket, SA-10. A planned thirty-minute hold ensured that launch time coincided with the opening of thePegasus launch window. The launch was normal and the payload was inserted into orbit approximately 10.7 minutes after lift-off. The total mass placed in orbit, including the spacecraft, Pegasus spacecraft, adapter, instrument unit, andS-IV stage, was 34,438 pounds (15,621 kg).
The spacecraft was separated 812 seconds after lift-off and the separation and ejection system operated as planned. ThePegasus 3 spacecraft, which was attached to the S-IV stage of the Saturn I and stowed inside the boilerplate service module, was deployed 40 seconds after command initiation at 872 seconds. Pegasus 3 was a 1423.6 kilogram (3138.6 pound) micrometeoroid detection satellite, which was bolted to the S-IV.
This article incorporatespublic domain material from websites or documents of theNational Aeronautics and Space Administration.
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