12U Nanosatellite Bus M12P

12U nanosatellite bus M12P / M12P-R

Download M12P/M12P-R bus brochure here

NanoAvionics’ flight-proven 12U satellite bus is based on a modular and highly integral design. It delivers extended, up to 11U, payload volume and saves development costs for customers.

M12P 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 and Earth Observation (EO) missions.

NanoAvionics also offers a single fault tolerant 12U satellite bus design option – M12P-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.

M12P and M12P-R buses include 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.

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12U nanosatellite bus M12P / M12P-R

Download M12P/M12P-R bus brochure here

NanoAvionics’ flight-proven 12U satellite bus is based on a modular and highly integral design. It delivers extended, up to 11U, payload volume and saves development costs for customers.

M12P 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 and Earth Observation (EO) missions.

NanoAvionics also offers a single fault tolerant 12U satellite bus design option – M12P-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.

M12P and M12P-R buses include 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.

  • Bus Features:
    • Empty bus mass (with propulsion): 6500 g (M12P) / 8000 g (M12P-R – single fault tolerant design)
    • Max payload mass: 17 500 g (M12P) / 16 000 g (M12P-R – single fault tolerant design)
    • Payload volume: up to 11U (M12P) / up to 8U (M12P-R – single fault tolerant design)
    • Contains high-performance propulsion system EPSS C2.
    • M12P 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:

    • 8 cells, 7.4 V, 12800 mAh, 92 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
    • Star Tracker

    Attitude control type: 3-axis stabilization

    Attitude pointing accuracy: up to 0.1°

    Attitude pointing knowledge: up to 0.05°

    Stability accuracy (Jitter): ±0.004°/s (at f>4Hz)

    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
Highlighted Missions
NanoAvionics
ACS3

Client name

NASA

Launch date

2022

NanoAvionics was selected to build a 12U nanosatellite bus for an in-orbit demonstration of NASA’s Advanced Composite Solar Sail System (ACS3). The aim of the ACS3 mission is to replace conventional rocket propellants by developing and testing solar sails using sunlight beams to thrust the nanosatellite. These solar sail propulsion systems are designed for future small interplanetary spacecraft destined for low-cost deep-space and science missions requiring long-duration, low-thrust propulsion.
As part of this project, NanoAvionics also supplied a mechanical testbed model and a FlatSat model. In addition, a team of NanoAvionics engineers have been providing the support required for testing, integration, and operations of the nanosatellite.

Read the press release

NanoAvionics
2x12U satellite buses for Omnispace

Client name

Thales Alenia Space for Omnispace

Launch date

TBA

NanoAvionics was contracted by Thales Alenia Space to build the initial two satellite buses for Omnispace’s satellite-based Internet of Things (IoT) infrastructure. Omnispace is reinventing mobile communications by delivering the world’s first global hybrid 5G non-terrestrial network based on 3GPP standards. These initial satellites, for operation in non-geostationary orbit (NGSO), will support the development and implementation of Omnispace’s global hybrid network.

Read the press release

  • Bus Features:
    • Empty bus mass (with propulsion): 6500 g (M12P) / 8000 g (M12P-R – single fault tolerant design)
    • Max payload mass: 17 500 g (M12P) / 16 000 g (M12P-R – single fault tolerant design)
    • Payload volume: up to 11U (M12P) / up to 8U (M12P-R – single fault tolerant design)
    • Contains high-performance propulsion system EPSS C2.
    • M12P 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:

    • 8 cells, 7.4 V, 12800 mAh, 92 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
    • Star Tracker

    Attitude control type: 3-axis stabilization

    Attitude pointing accuracy: up to 0.1°

    Attitude pointing knowledge: up to 0.05°

    Stability accuracy (Jitter): ±0.004°/s (at f>4Hz)

    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