 The Polar Satellite Launch Vehicle, the model of rocket that launched CICERO-6 | |
| Mission type | Earth observation |
|---|---|
| Operator | GeoOptics Inc. |
| Spacecraft properties | |
| Manufacturer | Orbital Solutions Monaco[1] |
| Launch mass | 10 kg (22 lb)[2] |
| Power | 21 watts |
| Start of mission | |
| Launch date | 23 June 2017, 3:59 UTC[2] |
| Rocket | PSLV-XL |
| Launch site | Sriharikota Launching Range |
| Contractor | ISRO |
| Orbital parameters | |
| Regime | Low Earth orbit[2] |
| Altitude | 505 km (314 mi) |
| Periapsis altitude | 407.8 km (253.4 mi)[3] |
| Apoapsis altitude | 417.1 km (259.2 mi)[3] |
| Inclination | 97.1° |
| Period | 92.7 minutes |
CICERO-6 (Community Initiative for Continuing Earth Radio Occultation) is a CubeSat designed and operated by GeoOptics, Inc.[1] 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.[2][4] The CICERO project aimed to have a lower cost compared to other Earth observation projects.[5]
- ^ a b Kulu, Erik (2023), CICERO, Nanosats Database, retrieved 14 January 2024
- ^ 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