A-105 (spacecraft)

A-105 (Saturn-Apollo 10)
Mission insignia
Mission statistics
Mission name	A-105 (Saturn-Apollo 10)
Spacecraft mass	3199 lb (1451.5 kg)
Call sign	A-105 (SA-10)
Launch pad	Cape Canaveral Complex 37B
Launch date	July 30, 1965 13:00:00 UTC
Landing	August 4, 1969 (Reentry)
Mission duration	1,466 days
Number of orbits	~22,152
Apogee	352 mi (567 km)
Perigee	332 mi (535 km)
Orbital inclination	28.9 deg
Distance traveled	566,730,351 mi (912,064,090 km)
Related missions
Previous Subsequent Pad Abort Test 2 A-004

A-105 was the final boilerplate test of an Apollo spacecraft, launched by the final flight of the Saturn I carrier rocket, SA-10, in 1965.

Overview

A-105 was an Apollo boilerplate spacecraft; boilerplate BP-9A was used for the flight. The spacecraft reentered on November 22, 1975. The Saturn launch vehicle (SA-10) was similar to those of missions A-103 and A-104. As on the previous mission, the boilerplate service 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 interactive guidance mode and evaluation of system accuracy.

Launch

Launch of SA-10 carrying A-105

A-105 was launched from Cape Kennedy Launch Complex 37B at 08:00 EST (13:00 GMT) 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 the Pegasus 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, and S-IV stage, was 34,438 pounds (15,621 kg).

The spacecraft was separated 812 seconds after lift-off. The separation and ejection system operated as planned. The Pegasus 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.

References

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

External links

• NSSDC: SA-10
• Range safety data for Saturn SA-10
• SA-10 flight mechanical summary technical memorandum, Jul. 13, 1965
• Vibration and acoustic analyzes, Saturn SA-10 flight
• Saturn SA-10/Pegasus C postflight trajectory