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Pegasus 2

American satellite

Field	Value
name	Pegasus 2
image	Pegasus satellite.jpg
image_caption	A Pegasus satellite in orbit
operator	NASA
COSPAR_ID	1965-039A
mission_duration	1 year (design)
years (achieved)
spacecraft_type	Pegasus
manufacturer	Fairchild Hiller
launch_mass	9058 kg
payload_mass	1450 kg
launch_date	UTC
launch_rocket	Saturn I SA-8
launch_site	Cape Canaveral LC-37B
disposal_type	Decommissioned
deactivated
decay_date	3 November 1979
orbit_epoch	3 July 1965
orbit_reference	Geocentric
orbit_regime	Low Earth
orbit_periapsis	508 km
orbit_apoapsis	737 km
orbit_inclination	31.7 degrees
orbit_period	97.15 minutes
apsis	gee
programme	Apollo micrometeoroid investigation
previous_mission	Pegasus 1
next_mission	Pegasus 3

years (achieved)

Pegasus 2 or Pegasus II, known before launch as Pegasus B was an American satellite which was launched in 1965 to study micrometeoroid impacts in Low Earth orbit. It was the second of three Pegasus satellites to be launched, following the launch of Pegasus 1 three months earlier. The Pegasus spacecraft were manufactured by Fairchild Hiller, and operated by NASA.

Spacecraft

Pegasus 2 was a Pegasus spacecraft, consisting of 1450 kg of instruments, attached to the S-IV upper stage of the carrier rocket which had placed it into orbit. It had a total mass of 9058 kg, and was equipped with two sets of micrometeoroid detection panels, and a radio for tracking and returning data. The panels were 29 m long, and equipped with 116 individual detectors.

Launch

Pegasus 2 was launched atop a Saturn I rocket, serial number SA-8, flying from Launch Complex 37B at the Cape Kennedy Air Force Station. The launch occurred at 07:35:01 UTC on 25 May 1965. Following launch, Pegasus 2 was given the COSPAR designation 1965-039A, whilst NORAD assigned it the Satellite Catalog Number 01381.

Pegasus 2 was a secondary payload on the carrier rocket, which was carrying a boilerplate Apollo spacecraft, Apollo 104 or BP-26, as part of a series of configuration tests for the Apollo program. The Apollo boilerplate acted as a payload fairing for the Pegasus spacecraft, which was stored inside what would have been the Service Module of a functional spacecraft. Upon reaching orbit, the boilerplate Command and Service modules were jettisoned. Boilerplate separation occurred 806 seconds after liftoff, with Pegasus 2's detectors being deployed one minute later. The predicted orbital lifetime of Pegasus 2 was 1220 days.

Operations

Pegasus 2 was operated in a low Earth orbit. On 3 July 1965 it was catalogued as being in an orbit with a perigee of 508 km and an apogee of 737 km, inclined at 31.7 degrees to the equator and with a period of 97.15 minutes. Once in orbit, the panels were deployed to detect micrometeoroid impacts. Experiment results were returned to Earth by radio. The spacecraft operated until 29 August 1968, and subsequently remained in orbit until it decayed and reentered the atmosphere on 3 November 1979.

References

Krebs, Gunter. "Pegasus 1, 2, 3". Gunter's Space Page.
"World Civil Satellites 1957-2006". Space Security Index.
Wade, Mark. "Pegasus".
McDowell, Jonathan. "Launch List". Jonathan's Space Page.
McDowell, Jonathan. "Launch Log". Jonathan's Space Page.
"Pegasus 2". US National Space Science Data Center.
McDowell, Jonathan. "Satellite Catalog". Jonathan's Space Page.

Info: Wikipedia Source

This article was imported from Wikipedia and is available under the Creative Commons Attribution-ShareAlike 4.0 License. Content has been adapted to SurfDoc format. Original contributors can be found on the article history page.

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