12U Nanosatellite Bus M12P - NanoAvionics
12U Nanosatellite Bus M12P

12U nanosatellite bus M12P / M12P-R

Download M12P/M12P-R bus brochure here

NanoAvionics’ 12U satellite bus is characterized by its modular and highly integral design. The M12P system offers an extended payload volume of up to 11U, to allow customers to focus on high-level implementation tasks and primary mission goals.

The proven and robust setup is designed to reduce development time and costs, with an optimized 12U platform that requires minimal flight readiness and flight acceptance in order to finalize for launch.

The company also offers a single fault-tolerant version of the bus, known as the M12P-R, which eliminates single point failures, increasing reliability and redundancy. The M12P-R has a payload volume of up to 8U and can house payloads with a maximum mass of 16kg.

The M12P’s standardized configuration is also provided with sample mission code pre-installed. This enables a faster setup, simpler payload integration, and the ability to run system diagnostics immediately, in order to accelerate mission development. The platforms are suitable for a wide range of applications in areas such as:

  • Earth Observation (EO),
  • Communication,
  • Automatic Dependent Surveillance–Broadcast (ADS-B) systems,
  • Machine-to-Machine (M2M),
  • Automatic Identification Systems (AIS),
  • Internet of Things (IoT),
  • Emergency services, and
  • Science and research.

Both M12P models support a variety of common data interfaces and feature a fail-safe design that can keep the satellite fully operational in the event of hardware malfunction. The systems are equally well-suited for use in single-satellite missions or as the standardized platform for an entire constellation.

Both the M12P and M12P-R buses can be equipped with an optional propulsion system capable of performing high-impulse maneuvers (such as orbit synchronization, orbital deployment and maintenance, or atmospheric drag compensation). Such operational versatility can extend satellite lifetime and open up new mission concepts.

 

Drag to sides
Request information

Download M12P/M12P-R bus brochure here

NanoAvionics’ 12U satellite bus is characterized by its modular and highly integral design. The M12P system offers an extended payload volume of up to 11U, to allow customers to focus on high-level implementation tasks and primary mission goals.

The proven and robust setup is designed to reduce development time and costs, with an optimized 12U platform that requires minimal flight readiness and flight acceptance in order to finalize for launch.

The company also offers a single fault-tolerant version of the bus, known as the M12P-R, which eliminates single point failures, increasing reliability and redundancy. The M12P-R has a payload volume of up to 8U and can house payloads with a maximum mass of 16kg.

The M12P’s standardized configuration is also provided with sample mission code pre-installed. This enables a faster setup, simpler payload integration, and the ability to run system diagnostics immediately, in order to accelerate mission development. The platforms are suitable for a wide range of applications in areas such as:

  • Earth Observation (EO),
  • Communication,
  • Automatic Dependent Surveillance–Broadcast (ADS-B) systems,
  • Machine-to-Machine (M2M),
  • Automatic Identification Systems (AIS),
  • Internet of Things (IoT),
  • Emergency services, and
  • Science and research.

Both M12P models support a variety of common data interfaces and feature a fail-safe design that can keep the satellite fully operational in the event of hardware malfunction. The systems are equally well-suited for use in single-satellite missions or as the standardized platform for an entire constellation.

Both the M12P and M12P-R buses can be equipped with an optional propulsion system capable of performing high-impulse maneuvers (such as orbit synchronization, orbital deployment and maintenance, or atmospheric drag compensation). Such operational versatility can extend satellite lifetime and open up new mission concepts.

 

  • 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 – 12V configurable)
    • Up to 18 regulated configurable – 3.3 V / 5 V / 3V – 12 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 3-12 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
Spark-2

Client name

Omnispace & Thales Alenia Space

Launch date

2022 05 25

The 12U Omnispace and Thales Alenia Space communications satellite named Spark-2 is an addition to their identical Spark-1 satellite that launched aboard the SpaceX Transporter-4 mission in April, 2022.  The satellite was build for Omnispace’s satellite-based Internet of Things (IoT) infrastructure.

Read the press release

NanoAvionics
Spark-1

Client name

Omnispace & Thales Alenia Space

Launch date

2022 04 01

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. Spark-1 is the first satellite built & launched for Omnispace & Thales Alenia Space.

Read the press release

NanoAvionics
ACS3

Client name

NASA

Launch date

2023

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

  • 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 – 12V configurable)
    • Up to 18 regulated configurable – 3.3 V / 5 V / 3V – 12 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 3-12 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