8U nanosatellite bus M8P - NanoAvionics
8U nanosatellite bus M8P

8U nanosatellite bus M8P

Download the M8P bus brochure here

The NanoAvionics M8P small satellite allows customers to focus on their most important objectives by providing a pre-configured 8U CubeSat bus, designed to maximize payload volume and functionality. The standardized setup enables engineers to spend more development time and resources on high-level tasks, such as payload development and its support during operations.

Modern 8U CubeSats can provide significant levels of performance and data resolution with the advanced subsystems on today’s market. Our M8P is a powerful, pre-configured platform to support such technologies and has been specifically designed for optimum performance in demanding commercial settings.

For engineers assessing 6U options, note that this 8U is a viable alternative. The M8P can provide very similar average orbit power to a 16U nanosatellite, and improve mission capabilities and redundancy at only marginally increased production and launch costs compared to the M6P.

The bus has a modular design, making it simple to adapt and extend, depending on the mission requirements, and the system can be used for a diverse array of applications, as a solo satellite or in a constellation, including:

  • Commercial and emergency communication services,
  • Internet of Things (IoT) and Machine-to-Machine (M2M) applications,
  • Earth Observation (EO) services, scientific and research missions,
  • Automatic Dependent Surveillance–Broadcast (ADS-B) aviation traffic monitoring and control, and
  • Automatic Identification Systems (AIS) maritime traffic monitoring and control.

Beyond such primary mission objectives, an optional propulsion system can enable greater versatility and extended operational lifetimes. This includes high-impulse maneuvers for collision avoidance, re-positioning, orbital changes, de-orbiting, precision flight formations, and atmospheric drag compensation.

Payload volume of up to 7U is provided due to the optimized hardware layout and the proven architecture has been engineered to support sensitive payloads. All onboard systems also utilize radiation-tolerant components and have been carefully designed to enable both precise thermal control and robust, consistent power delivery.

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Download the M8P bus brochure here

The NanoAvionics M8P small satellite allows customers to focus on their most important objectives by providing a pre-configured 8U CubeSat bus, designed to maximize payload volume and functionality. The standardized setup enables engineers to spend more development time and resources on high-level tasks, such as payload development and its support during operations.

Modern 8U CubeSats can provide significant levels of performance and data resolution with the advanced subsystems on today’s market. Our M8P is a powerful, pre-configured platform to support such technologies and has been specifically designed for optimum performance in demanding commercial settings.

For engineers assessing 6U options, note that this 8U is a viable alternative. The M8P can provide very similar average orbit power to a 16U nanosatellite, and improve mission capabilities and redundancy at only marginally increased production and launch costs compared to the M6P.

The bus has a modular design, making it simple to adapt and extend, depending on the mission requirements, and the system can be used for a diverse array of applications, as a solo satellite or in a constellation, including:

  • Commercial and emergency communication services,
  • Internet of Things (IoT) and Machine-to-Machine (M2M) applications,
  • Earth Observation (EO) services, scientific and research missions,
  • Automatic Dependent Surveillance–Broadcast (ADS-B) aviation traffic monitoring and control, and
  • Automatic Identification Systems (AIS) maritime traffic monitoring and control.

Beyond such primary mission objectives, an optional propulsion system can enable greater versatility and extended operational lifetimes. This includes high-impulse maneuvers for collision avoidance, re-positioning, orbital changes, de-orbiting, precision flight formations, and atmospheric drag compensation.

Payload volume of up to 7U is provided due to the optimized hardware layout and the proven architecture has been engineered to support sensitive payloads. All onboard systems also utilize radiation-tolerant components and have been carefully designed to enable both precise thermal control and robust, consistent power delivery.

  • Bus Features:
    • Empty bus mass: 5000 g / 6500 g
    • Payload volume: up to 7U
    • M8P bus is already pre-integrated (mechanically, electrically, and functionally tested) and pre-qualified to be immediately ready for payload integration, which minimizes, final flight acceptance and flight readiness procedures 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 the NanoAvionics team according to separately agreed terms and conditions.
    • Payload integration service can be performed by the NanoAvionics team according to separately agreed terms and conditions.
  • Payload Controller:
    • 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: > 96 %
    • Battery cells balancing
    • Configurable thermal control system
    • Supported data interfaces: CAN, with CSP protocol support, UART
    • 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 – 12V configurable)
    • Up tp 18 regulated configurable – 3.3 V / 5 V / 3 – 12 V
    • Unregulated with switch: battery voltage 6.0 – 8.4 V
    • Typical output channel current: 3.13 A (configurable)
    • 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: 25W
    • 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, 13600 mAh, 92 Wh
  • Flight Computer (Including ADCS Functionality):
    • ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHz (configurable)
    • FreeRTOS
    • In-orbit firmware update and Self-Diagnostics
    • CSP, KISS support
    • Mission planner with time scheduled script/task execution support
    • Telemetry logging

    ADCS sensors and actuators:

    • NanoAvionics Sun Sensors
    • Integrated magnetic and inertial sensors
    • Reaction Wheels System NanoAvionics “SatBus 4RW0”
    • Integrated NanoAvionics Magnetorquers
    • Start 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
  • Bus Features:
    • Empty bus mass: 5000 g / 6500 g
    • Payload volume: up to 7U
    • M8P bus is already pre-integrated (mechanically, electrically, and functionally tested) and pre-qualified to be immediately ready for payload integration, which minimizes, final flight acceptance and flight readiness procedures 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 the NanoAvionics team according to separately agreed terms and conditions.
    • Payload integration service can be performed by the NanoAvionics team according to separately agreed terms and conditions.
  • Payload Controller:
    • 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: > 96 %
    • Battery cells balancing
    • Configurable thermal control system
    • Supported data interfaces: CAN, with CSP protocol support, UART
    • 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 – 12V configurable)
    • Up tp 18 regulated configurable – 3.3 V / 5 V / 3 – 12 V
    • Unregulated with switch: battery voltage 6.0 – 8.4 V
    • Typical output channel current: 3.13 A (configurable)
    • 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: 25W
    • 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, 13600 mAh, 92 Wh
  • Flight Computer (Including ADCS Functionality):
    • ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHz (configurable)
    • FreeRTOS
    • In-orbit firmware update and Self-Diagnostics
    • CSP, KISS support
    • Mission planner with time scheduled script/task execution support
    • Telemetry logging

    ADCS sensors and actuators:

    • NanoAvionics Sun Sensors
    • Integrated magnetic and inertial sensors
    • Reaction Wheels System NanoAvionics “SatBus 4RW0”
    • Integrated NanoAvionics Magnetorquers
    • Start 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