Kosmos 23
| Mission type | Technology |
|---|---|
| COSPAR ID | 1963-050A |
| Spacecraft properties | |
| Spacecraft type | Omega |
| Manufacturer | Yuzhnoye |
| Launch mass | 200 kilograms (440 lb)[1] |
| Start of mission | |
| Launch date | 13 December 1963, 14:15:00 UTC |
| Rocket | Kosmos-2I 63S1 |
| Launch site | Kapustin Yar Mayak-2 |
| End of mission | |
| Decay date | 27 March 1964 |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Low Earth |
| Perigee | 237 kilometres (147 mi) |
| Apogee | 528 kilometres (328 mi) |
| Inclination | 48.9 degrees |
| Period | 92.2 minutes |
Kosmos 23 (Russian: Космос 23 meaning Cosmos 23), also known as Omega No.2, was a satellite which was launched by the Soviet Union in 1963. It was an Omega satellite, derived from the Dnepropetrovsk Sputnik series. It was a 200-kilogram (440 lb) spacecraft,[1] which was built by the Yuzhnoye Design Bureau, and was used to conduct experiments with the use of gyroscopes to control spacecraft, for VNIIEM.[2]
Kosmos 23 was launched from pad 2 of the Mayak Launch Complex at Kapustin Yar, aboard a Kosmos-2I 63S1 carrier rocket.[3] The launch occurred at 14:15:00 UTC on 13 December 1963, and resulted in the successful insertion of the satellite into a low Earth orbit.[4] Upon reaching orbit, the satellite was assigned its Kosmos designation, and received the International Designator 1963-050A.[5] The North American Aerospace Defense Command assigned it the catalogue number 00707.
Kosmos 23 was the second of two Omega satellites to be launched,[2] after Kosmos 14.[6] It was operated in an orbit with a perigee of 237 kilometres (147 mi), an apogee of 528 kilometres (328 mi), 48.9 degrees of inclination, and an orbital period of 92.2 minutes.[7] It remained in orbit until it decayed and reentered the atmosphere on 27 March 1964.[7]
See also
References
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