| Mission type | Technology (Weather) |
|---|---|
| Operator | VNIIEM |
| COSPAR ID | 1963-050A |
| SATCAT no. | 00707 |
| Mission duration | 105 days |
| Spacecraft properties | |
| Spacecraft type | Omega |
| Manufacturer | Yuzhnoye |
| Launch mass | 347 kg[1] |
| Dimensions | 1.8 m long and 1.2 m in diameter |
| Start of mission | |
| Launch date | 13 December 1963 13:55:00 GMT |
| Rocket | Kosmos-2I 63S1 |
| Launch site | Kapustin Yar, Mayak-2 |
| Contractor | Yuzhnoye |
| End of mission | |
| Decay date | 27 March 1964 |
| Orbital parameters | |
| Reference system | Geocentric[2] |
| Regime | Low Earth |
| Perigee altitude | 241 km |
| Apogee altitude | 540 km |
| Inclination | 48.98° |
| Period | 92.3 minutes |
| Epoch | 13 December 1963 |
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 347 kilograms (765 lb) spacecraft,[1] which was built by the Yuzhnoye Design Office, and was used to conduct experiments with the use of gyroscopes to control spacecraft, for VNIIEM.[3]
- ^ a b "World Civil Satellites 1957-2006". Space Security Index. Archived from the original on 18 July 2011. Retrieved 26 December 2009.
- ^ https://nssdc.gsfc.nasa.gov/nmc/spacecraft/displayTrajectory.action?id=1963-050A - 27 February 2020
- ^ Wade, Mark. "Omega". Encyclopedia Astronautica. Archived from the original on 7 May 2002. Retrieved 26 December 2009.