16U nanosatellite bus M16P / M16P-R

Download M16P/M16P-R bus brochure here

NanoAvionics’ flight-proven 16U satellite bus is based on a modular and highly integral design. It delivers extended payload volume and saves development costs for customers.

M16P satellite bus enables customers to concentrate on the most important mission goals and deal with high-level mission implementation tasks only, such as payload development, integration, and support during the mission in orbit.

The standard configuration of the bus is optimized for IoT, M2M, ADS-B, AIS and other commercial and emergency communication applications as well as scientific missions. Also, as an option – M16P configuration for Earth Observation (EO) missions are available.

M16P bus includes propulsion system capable to perform high-impulse maneuvers such as: orbital deployment, orbit maintenance, precision flight in formations, orbit synchronization and atmospheric drag compensation. It results in extended satellite orbital lifetime uncovered new opportunities for the unique customer missions and significant savings on constellation maintenance costs.

NanoAvionics also offers a single fault tolerant 16U satellite bus design option – M16P-R. By doubling the critical satellite subsystems, single point failures are removed from the system, hence adding mission reliability and redundancy. Such satellite system is designed to have a mission lifetime of 10 years in LEO.

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16U nanosatellite bus M16P / M16P-R

Download M16P/M16P-R bus brochure here

NanoAvionics’ flight-proven 16U satellite bus is based on a modular and highly integral design. It delivers extended payload volume and saves development costs for customers.

Bus Features:
- Empty bus mass (with propulsion): 7500 g (M16P) / 9000 g (M16P-R – single fault tolerant design)
- Max payload mass: 16 500 g (M16P) / 15 000 g (M16P-R – single fault tolerant design)
- Payload volume: up to 15U (M16P) and up to 12U (M16P-R)
- Contains high-performance propulsion system EPSS C2.
- M16P bus is already pre-integrated (mechanically, electrically and functionally tested) and pre-qualified to be straight ready for the payload integration. Therefore, final flight acceptance and flight readiness procedures are minimized for the customer.
- Sample mission code is pre-installed for the customer to be able to run system diagnostics upon delivery of the bus and quick payload integration.
- Sophisticated mission code can be prepared by NanoAvionics team according to separately agreed terms and conditions.
- Payload integration service can be performed by NanoAvionics team according to separately agreed terms and conditions.
Payload Controler:
- Cortex™ M7 core, Clock speed up to 400 MHz (configurable)
- 1 MB of internal RAM
- 2 MB of internal FLASH memory
- 512 kB of FMC-connected FRAM memory
- 4 MB FMC-connected SRAM
- 256 MB of external NOR-FLASH for data storage (2 x two die (64 MB each) chips, QSPI)
- 2×512 kB of FRAM (SPI) for frequently changing data storage
- Integrated TRC
- microSD NAND Memory support (up to 2 x 32 GB)
- Three On-Board PWM Controlled H-Bridges
- PWM Outputs
- FreeRTOS
- In-Orbit firmware update
- Firmware Power-on-check and Restore
- RFS – Redundant Record-based File System
- A number of Payload dedicated interfaces:
  - 100BASE-TX Ethernet port
  - CAN Interface
  - 2 x RS422 (on request interchangeable with 2 x RS485)
  - 3 x buffered SPI
  - 2 x USART/UART
  - 2 x I2C
- CSP Support
- Self-Diagnostics
- Dynamic CPU Frequency Control
- User-friendly Console
Power System:
- Input, output converter efficiency: up to 96 %
- Battery cells balancing
- Configurable thermal control system
- Supported data interfaces: CAN, with CSP protocol support, UART for configuration
- Fail-safe design: in case of total microcontroller malfunction EPS will go to emergency mode and selected emergency channels will keep satellite operational
Outputs (over-current protected):
- 4 regulated voltage rails: 3.3 V; 5 V; (3 V – 18V configurable)
- Up to 18 regulated configurable – 3.3 V / 5 V / 3V – 18 V
- Unregulated battery voltage (switchable): 6.0 V – 8.4 V
- Typical Output Channel Current: 3.13 A
- Consistent 3.3 V Output converter power: 20 W
- Consistent 5 V Output converter power: 20 W
- Consistent 3-18 V Output converter power: 20 W
- Min unregulated output power with on-board battery back (2S1P configuration): 25 W
- Min unregulated output power with external battery pack (2S7P configuration): 175 W
Inputs:
- 4 MPPT converters (8 channels) with integrated ideal blocking diodes
- Voltage: 2.6 – 18 V
- Max input power per converter: 25 W
- Max charging power with on-board battery back (2S1P configuration): 10 W
- Max charging power with extended battery pack (2S7P configuration): 70 W
Batteries:
- 14 cells, 7.4 V, 23800 mAh, 161 Wh
Flight Computer (Including ADCS Functionality):
- ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHz (configurable)
- Double-Precision FPU
- FreeRTOS
- In-orbit firmware update and Self-Diagnostics
- CSP support
- Mission planner with time-scheduled script/task execution support
- Telemetry logging
ADCS Sensors and Actuators:
- High precision Inertial Measurement Unit (IMU)
- Reaction Wheels System NanoAvionics “SatBus 4RW0”
- Integrated NanoAvionics Magnetorquers
- Attitude control type: 3-axis stabilization
- Star Tracker
Attitude pointing accuracy: up to 0.1°

Attitude pointing knowledge: up to 0.03°

Stability accuracy (Jitter): ± 0.0029°/s (at f > 4 Hz)

Attitude maneuver ability (Slew rate): Up to 5°/s

Operational modes:
- Sun pointing mode
- Nadir pointing mode
- Velocity pointing mode
- Ground geodetic coordinate pointing mode
- Client defined pointing mode

Bus Features:
- Empty bus mass (with propulsion): 7500 g (M16P) / 9000 g (M16P-R – single fault tolerant design)
- Max payload mass: 16 500 g (M16P) / 15 000 g (M16P-R – single fault tolerant design)
- Payload volume: up to 15U (M16P) and up to 12U (M16P-R)
- Contains high-performance propulsion system EPSS C2.
- M16P bus is already pre-integrated (mechanically, electrically and functionally tested) and pre-qualified to be straight ready for the payload integration. Therefore, final flight acceptance and flight readiness procedures are minimized for the customer.
- Sample mission code is pre-installed for the customer to be able to run system diagnostics upon delivery of the bus and quick payload integration.
- Sophisticated mission code can be prepared by NanoAvionics team according to separately agreed terms and conditions.
- Payload integration service can be performed by NanoAvionics team according to separately agreed terms and conditions.
Payload Controler:
- Cortex™ M7 core, Clock speed up to 400 MHz (configurable)
- 1 MB of internal RAM
- 2 MB of internal FLASH memory
- 512 kB of FMC-connected FRAM memory
- 4 MB FMC-connected SRAM
- 256 MB of external NOR-FLASH for data storage (2 x two die (64 MB each) chips, QSPI)
- 2×512 kB of FRAM (SPI) for frequently changing data storage
- Integrated TRC
- microSD NAND Memory support (up to 2 x 32 GB)
- Three On-Board PWM Controlled H-Bridges
- PWM Outputs
- FreeRTOS
- In-Orbit firmware update
- Firmware Power-on-check and Restore
- RFS – Redundant Record-based File System
- A number of Payload dedicated interfaces:
  - 100BASE-TX Ethernet port
  - CAN Interface
  - 2 x RS422 (on request interchangeable with 2 x RS485)
  - 3 x buffered SPI
  - 2 x USART/UART
  - 2 x I2C
- CSP Support
- Self-Diagnostics
- Dynamic CPU Frequency Control
- User-friendly Console
Power System:
- Input, output converter efficiency: up to 96 %
- Battery cells balancing
- Configurable thermal control system
- Supported data interfaces: CAN, with CSP protocol support, UART for configuration
- Fail-safe design: in case of total microcontroller malfunction EPS will go to emergency mode and selected emergency channels will keep satellite operational
Outputs (over-current protected):
- 4 regulated voltage rails: 3.3 V; 5 V; (3 V – 18V configurable)
- Up to 18 regulated configurable – 3.3 V / 5 V / 3V – 18 V
- Unregulated battery voltage (switchable): 6.0 V – 8.4 V
- Typical Output Channel Current: 3.13 A
- Consistent 3.3 V Output converter power: 20 W
- Consistent 5 V Output converter power: 20 W
- Consistent 3-18 V Output converter power: 20 W
- Min unregulated output power with on-board battery back (2S1P configuration): 25 W
- Min unregulated output power with external battery pack (2S7P configuration): 175 W
Inputs:
- 4 MPPT converters (8 channels) with integrated ideal blocking diodes
- Voltage: 2.6 – 18 V
- Max input power per converter: 25 W
- Max charging power with on-board battery back (2S1P configuration): 10 W
- Max charging power with extended battery pack (2S7P configuration): 70 W
Batteries:
- 14 cells, 7.4 V, 23800 mAh, 161 Wh
Flight Computer (Including ADCS Functionality):
- ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHz (configurable)
- Double-Precision FPU
- FreeRTOS
- In-orbit firmware update and Self-Diagnostics
- CSP support
- Mission planner with time-scheduled script/task execution support
- Telemetry logging
ADCS Sensors and Actuators:
- High precision Inertial Measurement Unit (IMU)
- Reaction Wheels System NanoAvionics “SatBus 4RW0”
- Integrated NanoAvionics Magnetorquers
- Attitude control type: 3-axis stabilization
- Star Tracker
Attitude pointing accuracy: up to 0.1°

Attitude pointing knowledge: up to 0.03°

Stability accuracy (Jitter): ± 0.0029°/s (at f > 4 Hz)

Attitude maneuver ability (Slew rate): Up to 5°/s

Operational modes:
- Sun pointing mode
- Nadir pointing mode
- Velocity pointing mode
- Ground geodetic coordinate pointing mode
- Client defined pointing mode