16U Nanosatellite bus M16P - NanoAvionics
16U Nanosatellite bus M16P

16U nanosatellite bus M16P / M16P-R

Download M16P/M16P-R bus brochure here

A powerful 16U platform can provide high levels of performance, flexibility, and redundancy for advanced payloads. Modern space missions and services require these characteristics in order to create profitable ventures that meet the demanding requirements of today’s clients and end-users.

NanoAvionics’ 16U satellite buses are designed to provide a pre-integrated and pre-qualified platform that is fully tested electrically, functionally, and mechanically for a faster and simpler setup. A single fault-tolerant version, called the M16P-R, is also available and has been developed to eliminate single point failures, increasing reliability and redundancy. 

The M16P has available payload volume of up to 15U, for payloads with a mass of up to 16.5kg, while the M16P-R has 12U of available payload volume and a maximum payload mass of 15kg. Extended payload availability enables mission designers to focus on the most important aspects of their innovation, such as primary payload development and configuration.

Versatility and durability are also very important features of today’s missions. Customer requirements and operational conditions can change rapidly, sometimes requiring satellites to reposition or maneuver to avoid risks or for optimized performance. Such adaptability makes the NanoAvionics M16P platforms suitable for use in both single-satellite missions and constellations.

The standardized M16P configuration, with or without propulsion, makes it adaptable to a variety of both common and specialized applications, including:

  • Earth imaging initiatives such as Earth Observation (EO) and research projects,
  • Tracking and monitoring services such as Automatic Identification Systems (AIS) and Automatic Dependent Surveillance–Broadcast (ADS-B) systems,
  • Satcom and connectivity applications, such as communications and emergency services, and
  • Industrial process monitoring, such as Internet of Things (IoT) and Machine-to-Machine (M2M) services.

The system is fully tested and pre-qualified for rapid flight acceptance and also features sample mission code so that diagnostics can be run upon delivery. NanoAvionics has built every aspect of this 16U system with the industry’s needs firmly in mind at all stages.

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Download M16P/M16P-R bus brochure here

A powerful 16U platform can provide high levels of performance, flexibility, and redundancy for advanced payloads. Modern space missions and services require these characteristics in order to create profitable ventures that meet the demanding requirements of today’s clients and end-users.

NanoAvionics’ 16U satellite buses are designed to provide a pre-integrated and pre-qualified platform that is fully tested electrically, functionally, and mechanically for a faster and simpler setup. A single fault-tolerant version, called the M16P-R, is also available and has been developed to eliminate single point failures, increasing reliability and redundancy. 

The M16P has available payload volume of up to 15U, for payloads with a mass of up to 16.5kg, while the M16P-R has 12U of available payload volume and a maximum payload mass of 15kg. Extended payload availability enables mission designers to focus on the most important aspects of their innovation, such as primary payload development and configuration.

Versatility and durability are also very important features of today’s missions. Customer requirements and operational conditions can change rapidly, sometimes requiring satellites to reposition or maneuver to avoid risks or for optimized performance. Such adaptability makes the NanoAvionics M16P platforms suitable for use in both single-satellite missions and constellations.

The standardized M16P configuration, with or without propulsion, makes it adaptable to a variety of both common and specialized applications, including:

  • Earth imaging initiatives such as Earth Observation (EO) and research projects,
  • Tracking and monitoring services such as Automatic Identification Systems (AIS) and Automatic Dependent Surveillance–Broadcast (ADS-B) systems,
  • Satcom and connectivity applications, such as communications and emergency services, and
  • Industrial process monitoring, such as Internet of Things (IoT) and Machine-to-Machine (M2M) services.

The system is fully tested and pre-qualified for rapid flight acceptance and also features sample mission code so that diagnostics can be run upon delivery. NanoAvionics has built every aspect of this 16U system with the industry’s needs firmly in mind at all stages.

  • 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 – 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:

    • 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
Highlighted Missions
NanoAvionics
ETV-A1

Client name

SEN

Launch date

2022 01 13

ETV-A1 is the first of five satellites, contracted to NanoAvionics by British company Sen, to establish video streaming media to provide real-time Ultra-High Definition (UHD) videos of Earth. Each satellite is equipped with several UHD cameras and will provide multiple perspectives of Earth, from wide-angle imagery down to 1.5M resolution.

Read about Earth-TV

  • 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 – 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:

    • 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