SOWA

Current available payload slot options:

• 12x of 0,25U slots
• 6x of 0,5U slots
• 3x 1U slots
• 2x 2U slots
• 2x tuna-can external slot

Space-proven NanoBus structure:

Power management system is based on complex of Energy Harvesting System; Battery Management System; Auxiliary Power System (payload power supply). 

• Peak power 75 W
• System redundancy, autonomous fault handling and recovery
• Battery supervisory circuit
• Hardware protection from excessive discharge
• Hardware MPPT implementation
• User programable up to 6 A maximum battery pack load current
• Available power supply: 1.8 V, 3.3 V, 5 V, 12 V and unregulated battery voltage
• Up to 36V available on request
• Battery pack capacity: 54,6 Wh

Space-proven command and data handling module with following capabilities:

• Main processor: up to 216 MHz, 2 MB FLASH
• Storage memory: from 1 GB up to 16 GB NAND FLASH
• External program memory: up to 3 MB with hardware Forward Error Correction
• Payload interfaces: I2C, SPI, UART, RS485, RS422, CAN, USB, Ethernet, DAC/ADC
• Multiple temperature sensors
• Working temperatures: -30^oC to 65^oC
• Power supply: independent DC/DC converter
• Over-The-Air update capability

Redundant low frequency communication module

S-band communication module

Platform is equipped with following attitude determination and control subsystems:

• Space-proven advance flight computer
• 3x magnetorquers
• 3x reaction wheels
• 1x coarse sun-sensor
• 1x fine sun-sensor
• 1x magnetometer 3-axis
• 1x gyroscope 3-axis
• 1x GPS receiver

Platform accuracy: <1 degree of positioning accuracy; <0,01 degree of pointing accuracy

Platform is carrying 2 x SatRevolution Vision 300 optical payloads with additional processing capabilities.

• Sensors: 2 (Bayer; NIR)
• Bands: 4 (B; G; R; NIR)
• Ground Sample Distance (GSD): 5.8 m @500 km
• Field of View (FoV) for a single sensor: 14.2 x 11.8 km @500 km
• Angle of view (AoV) for a single sensor: 1.62° x 1.35°
• Maximum image area per orbit: 7 600 km2
• Daily coverage: 122 800 km2
• On-board memory: 128 GB Flash
• Single image resolution – 2456 x 2054 px
• Focal length – 300 mm; Aperture – f/5.6
• 8, 10, 12 bit processing

• September-December 2020 – external payload design and readiness review
• January-March 2021 – external payload design finalization
• April 2021 – provision of payload engineering models
• May 2021 – provision of payload flight models
• June-July 2021 – payload integration
• August-September 2021 – satellite integration and testing campaign
• October 2021 – delivery for launch
• December 2021 – launch
• January 2022-December 2024 – in-orbit service provision

Payload Services:

• Payload design review
• Platform provision
• Assembly, integration and testing
• Campaign management
• Launch event
• Platform and payload commissioning
• Payload in-orbit operations and service provision

Data Services:

• Imaging
• Image processing
• Data analysis
• Custom tasking