Cleon I is a modular, scalable smallsat platform from OKB Fifth Generation, configurable from 1U to 16U depending on mission payload and power needs.
Cleon I
Cleon I is a modular, scalable smallsat platform from OKB Fifth Generation, configurable from 1U to 16U depending on mission payload and power needs.
Description
Cleon I is a modular satellite platform developed by OKB Fifth Generation with configuration scalability from 1U to 16U, allowing the form factor to be scaled to efficiently operate the entire system and subsystems depending on mission objective, payload size and required power. The platform has over 4 years of flight heritage. Telemetry, tracking and command meet industry standards, and the company's own 'Grid' software allows users to download and visualize data, book satellite sessions and send control commands to spacecraft. The platform is adapted to the standards of launch operators and satellite deployer manufacturers; before launch the team performs all necessary laboratory tests and integrates the payload at the cosmodrome. Four standard configurations are offered (1U, 3U, 6U, 12U class buses) with scaling weight, power, battery capacity, payload volume and redundancy: weight without payload ranges from 0.5 kg to 12 kg (1.5 kg to 16 kg with payload), average available power from 4-6 W up to 30-50 W, battery capacity from about 10 A·h to 30 A·h, and payload volume from 0.5U up to 10U. Lifetime is not less than 1 year for the smaller configurations and not less than 3 years for the larger ones, with redundancy ranging from partial (EPS) to hot-redundant OBC, EPS and ADCS. On-board voltage/current available for payload is 3.3 V/5A, 5 V/3A and 8.4 V/2A across all configurations. Orientation accuracy is better than 1° with stabilization accuracy better than 0.2°/s, telemetry and control via UHF and S-band, and operating temperature range of -20...60 °C. Satellites built on the Cleon I platform include Norby (NORAD ID 46494) and Norby 2 (NORAD ID 57181).
Specifications
| Configuration scalability | 1U to 16U |
|---|---|
| Flight heritage | Over 4 years |
| Telemetry tracking and command | Meets all industry standards |
| Ground software | Grid — data download/visualization, satellite session booking, control commands |
| Integration and launch support | Adapted to launch operator and deployer standards; laboratory testing and payload integration at the cosmodrome |
| Weight, w/o payload (w/ payload) (1U) | 0,5 kg (1,5 kg) |
| Weight, w/o payload (w/ payload) (3U) | 3 kg (5,5 kg) |
| Weight, w/o payload (w/ payload) (6U) | 6 kg (8,5 kg) |
| Weight, w/o payload (w/ payload) (12U) | 12 kg (16 kg) |
| Design life (1U) | Not less than 1 year |
| Design life (3U) | Not less than 1 year |
| Design life (6U) | Not less than 3 years |
| Design life (12U) | Not less than 3 years |
| Redundancy (1U) | Partial (EPS) |
| Redundancy (3U) | Partial (EPS) |
| Redundancy (6U) | Hot redundant (OBC, EPS, ADCS) |
| Redundancy (12U) | Hot redundant (OBC, EPS, ADCS) |
| Average power available (1U) | 4 – 6 W |
| Average power available (3U) | 10 – 15 W |
| Average power available (6U) | 12 – 20 W |
| Average power available (12U) | 30 – 50 W |
| Average power requirement for on-board systems (1U) | < 3 W |
| Average power requirement for on-board systems (3U) | < 3 W |
| Average power requirement for on-board systems (6U) | < 3 W |
| Average power requirement for on-board systems (12U) | < 5 W |
| Battery capacity (1U) | ≈ 10 A × h |
| Battery capacity (3U) | ≈ 10 A × h |
| Battery capacity (6U) | ≈ 15 A × h |
| Battery capacity (12U) | ≈ 30 A × h |
| Volume available for payload (1U) | 0,5U (50 mm × 100 mm × 100 mm) |
| Volume available for payload (3U) | 2U (100 mm kh 100 mm kh 200 mm) |
| Volume available for payload (6U) | 5U (100 mm x 200 mm x 200 mm + 100 mm x 100 mm x 100 mm) |
| Volume available for payload (12U) | 10U (200 mm × 200 mm × 200 mm + 100 mm x 100 mm × 200 mm) |
| On-board voltage and current load available for payload | 3.3 V/5 A; 5 V/3 A; 8.4 V/2 A |
| Orientation accuracy | < 1° |
| Stabilization accuracy | < 0,2°/s |
| Telemetry and control | UHF, S-band |
| Operating temperature range | -20...60 °C |
| Satellite using platform — norby | NORAD ID 46494; service life 3 years; weight 8.5 kg; orbit altitude 1500 km, inclination 82.5°; dimensions 100 × 226.3 × 340.5 mm; orientation control accuracy roll/pitch/yaw ≥ 1° |
| Satellite using platform — norby 2 | NORAD ID 57181; service life 3 years; weight 8.5 kg; orbit altitude 500-600 km, Sun Synchronous Orbit (SSO); dimensions 100 × 226.3 × 340.5 mm; orientation control accuracy roll/pitch ≥ 1°; no propulsion system; onboard data storage 64 Mb; telemetry/commands VHF 436.7 MHz; payload data S-band 2425 MHz |
