 A Pegasus satellite in orbit | |
| Operator | NASA |
|---|---|
| COSPAR ID | 1965-039A |
| SATCAT no. | 01381 |
| Mission duration | 1 year (design) 3+1⁄4 years (achieved) |
| Spacecraft properties | |
| Spacecraft type | Pegasus |
| Manufacturer | Fairchild Hiller |
| Launch mass | 9,058 kilograms (19,969 lb) |
| Payload mass | 1,450 kilograms (3,200 lb) |
| Start of mission | |
| Launch date | 25 May 1965, 07:35:01 UTC |
| Rocket | Saturn I SA-8 |
| Launch site | Cape Canaveral LC-37B |
| End of mission | |
| Disposal | Decommissioned |
| Deactivated | 29 August 1968 |
| Decay date | 3 November 1979 |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Low Earth |
| Perigee altitude | 508 kilometers (316 mi) |
| Apogee altitude | 737 kilometers (458 mi) |
| Inclination | 31.7 degrees |
| Period | 97.15 minutes |
| Epoch | 3 July 1965 |
Apollo micrometeoroid investigation | |
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.