SOWA
Extended EO-capable platform aimed at shared in-orbit service provision – imagery, data, services for external payloads and solutions – launches December 2021 with SpaceX Falcon 9 rocket.

Up to 4U of Cubesat capacity available

Optical payload with up 1m resolution

Advance Earth-Observation services in-orbit and on the ground
To find out more about services aboard SOWA mission please contact us
Mission details
Business Case
External Payload Capacity
Structure and Interfaces
Power
On-board Computing
Communications
Guidance and Control
Optical Capabilities
Mission Timeline
Payload and Data Services
Business Case
SatRevolution SOWA creates value in following (but not limited to) business cases:
- Image processing, value-added Earth-observation services
- Demonstration of Earth-observation-oriented technologies in real-life scenarios
- Provision of imagery, services and data
- Obtaining flight heritage for your sub-systems and componentry
External Payload Capacity
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
Structure and Interfaces
Space-proven NanoBus structure:
- CNC manufactured of Aluminium 6061, 5083, 6082 alloy
- Hard anodized and oxidized
- Up to 2 safety deployment switches and 1 RBF pin
- Two separation springs
Available interfaces:
Platform can accept both standard PC104 and platform proprietary design mechanical payload interfaces. Proprietary design allows for smooth payload integration process.
Interfaces available: I2C, SPI, UART, RS485, RS422, CAN, USB, Ethernet, DAC/ADC. Other interfaces are available on request.
Power
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
On-board Computing
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: -30oC to 65oC
- Power supply: independent DC/DC converter
- Over-The-Air update capability
Communications
Redundant low frequency communication module
- Two independent radio transceivers
- Frequency range: 400-440 MHz (optionally 120-500 MHz)
- Transmission data rate 9,6 kb/s
- RF output power: 30 dBm (reconfiguration available on request)
- External program memory: up to 1 MB with hardware Forward Error Correction
- Radio Sensitivity: -120 dBm
- Over-The-Air update capability
S-band communication module
- S-band frequency range: 2200 – 2290 MHz or 2400-2450 MHz
- RF output power: 30 dBm
- S-band transmission rate: 3.5 – 10.5 Mb/s
- External program memory: up to 1 MB with hardware Forward Error Correction
- Over-The-Air update capability
X-band communication module with 300 Mb/s transmission rate
Guidance and Control
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
Optical Capabilities
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
Mission Timeline
- 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 and Data Services
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
SOWA mission platform visualization
Interested in our services?
UNITED KINGDOM OFFICE
R71 Rutherford Appleton Laboratory
Harwell Campus
Didcot OPX11 0QX,
Oxfordshire, UK
POLAND OFFICE
Stabłowicka 147
54-066 Wrocław
Poland
U.S.A. OFFICE
388 Market Street (Suite 1300)
San Francisco, CA 94111
United States
+48 533 325 851
contact@satrevolution.com