AS-105 (spacecraft)

From Wikipedia, the free encyclopedia
  (Redirected from A-105 (SA-10))
Jump to: navigation, search
AS-105
Saturn SA10 launch.jpg
Launch of SA-10 carrying AS-105
Mission type Spacecraft aerodynamics;
micrometeroid investigation
Operator NASA
COSPAR ID 1965-060B
SATCAT № 1468
Mission duration 1,466 days[citation needed]
Distance travelled 912,064,090 kilometers (566,730,350 mi)
Orbits completed ~22,152
Spacecraft properties
Spacecraft Apollo BP-9A
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 Canaveral LC-37B
End of mission
Decay date August 4, 1969 (1969-08-05)
Orbital parameters
Reference system Geocentric
Regime Low Earth orbit
Perigee 521 kilometers (324 mi)
Apogee 536 kilometers (333 mi)
Inclination 28.8 degrees
Period 95.2 minutes
Epoch 3 September 1965[1]

Apollo program
← AS-104 AS-201

AS-105 was the fifth and final orbital flight of a boilerplate Apollo spacecraft, and the third and final launch of a Pegasus micrometeroid detection satellite. It was launched by SA-10, the tenth and final Saturn I carrier rocket,in 1965.

Overview[edit]

AS-105 was an Apollo boilerplate 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 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[edit]

AS-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[edit]

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

  1. ^ McDowell, Jonathan. "Satellite Catalog". Jonathan's Space Page. Retrieved 31 October 2013. 
  2. ^ "Saturn I". Astronautix. Retrieved February 28, 2011. 

External links[edit]