CICERO-6
| Mission type | Earth observation |
|---|---|
| Operator | GeoOptics Inc. |
| Spacecraft properties | |
| Launch mass | 10 kg (22 lb)[1] |
| Power | 21 watts |
| Start of mission | |
| Launch date | 23 June 2017, 3:59 UTC[1] |
| Rocket | Polar Satellite Launch Vehicle |
| Launch site | Sriharikota Launching Range |
| Contractor | ISRO |
| Orbital parameters | |
| Regime | Low Earth orbit[1] |
| Altitude | 505 km (314 mi) |
| Periapsis altitude | 407.8 km (253.4 mi)[2] |
| Apoapsis altitude | 417.1 km (259.2 mi)[2] |
| Inclination | 97.1° |
| Period | 92.7 minutes |
CICERO-6 (Community Initiative for Continuing Earth Radio Occultation) is a micro-satellite designed and operated by GeoOptics, Inc. It is the first launched of the CICERO satellite constellation. Its purpose, as part of the constellation, is to use GPS and Galileo radio occultation (GNSS-RO) and GNSS reflectometry (GNSS-R) to provide data on Earth's atmosphere and climate.[1][3] The CICERO project aimed to have a lower cost compared to other Earth observation projects.[4]
References
- ^ a b c d Kramer, Herbert J. (2022), CICERO (Community Initiative for Continuing Earth Radio Occultation), European Space Agency, retrieved 5 January 2024
- ^ a b CICERO 6 Satellite details 2017-036AE NORAD 42793, n2yo.com, 2017, retrieved 5 January 2024
- ^ Krebs, Gunter D. (2023), CICERO 1, ..., 12 / OSM 1 CICERO, Gunter Space Page, retrieved 9 January 2024
- ^ Yunck, T.P. (2012), CICERO: Community Initiative for Continuing Earth Radio Occultation (PDF), IROWG Annual Meeting, retrieved 9 January 2024