Microsatellite Bus MP42H - NanoAvionics
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Microsatellite Bus MP42H

Microsatellite Bus MP42H

Download MP42 Buses Brochure

Despite decreases in launch costs, the size and weight of a satellite are still very important defining characteristics in the development of a mission or service. The MP42H is NanoAvionics’ smallest and lightest microsatellite bus and uses an 8″ ESPA-class separation ring for deployment on orbit.

The versatile system is pre-installed and pre-qualified for a faster, simpler setup, allowing users to focus more time and effort on high-value tasks such as payload integration and testing. It can accommodate payloads with a total mass of 22kg and a maximum footprint of 280 x 325 mm. The payload’s height is flexible as long as the total satellite height does not exceed 1300 mm.

Despite being only slightly larger and heavier than most higher-end nanosatellites, the MP42H can provide far greater mission capabilities and redundancy opportunities, thanks to the extra avionics volume, better thermal management, and larger payload interface. And these benefits are built-in – achieving such improved performance levels often requires additional non-recurring engineering (NRE) costs, so the readymade MP42H will ultimately provide significantly more capabilities for only a marginal price increase in comparison.

As with all of NanoAvionics’ proven platforms, the MP42H is a highly modular system. Configurable subsystems and operational protocols are included which enable faster setup. The system also has sample mission code pre-installed so that testing can commence immediately upon delivery.

The MP42H bus is equally well-suited for use in single-satellite missions or as the standardized platform for an entire constellation.

The MP42H is highly versatile and is optimized for remote sensing, high data throughput and complex communications missions, emergency communications, and fundamental research missions. In all missions and applications minimal reconfiguration of the existing system setup is needed and a range of standardized data interfaces, components, and protocols add to the reliability and performance of the platform.

The MP42H can also be equipped with a propulsion system, if required, that enables the satellite to carry out high-impulse orbital maneuvers. This adds to the flexibility and reliability of the system as well as extending satellite lifetime.

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Download MP42 Buses Brochure

Despite decreases in launch costs, the size and weight of a satellite are still very important defining characteristics in the development of a mission or service. The MP42H is NanoAvionics’ smallest and lightest microsatellite bus and uses an 8″ ESPA-class separation ring for deployment on orbit.

The versatile system is pre-installed and pre-qualified for a faster, simpler setup, allowing users to focus more time and effort on high-value tasks such as payload integration and testing. It can accommodate payloads with a total mass of 22kg and a maximum footprint of 280 x 325 mm. The payload’s height is flexible as long as the total satellite height does not exceed 1300 mm.

Despite being only slightly larger and heavier than most higher-end nanosatellites, the MP42H can provide far greater mission capabilities and redundancy opportunities, thanks to the extra avionics volume, better thermal management, and larger payload interface. And these benefits are built-in – achieving such improved performance levels often requires additional non-recurring engineering (NRE) costs, so the readymade MP42H will ultimately provide significantly more capabilities for only a marginal price increase in comparison.

As with all of NanoAvionics’ proven platforms, the MP42H is a highly modular system. Configurable subsystems and operational protocols are included which enable faster setup. The system also has sample mission code pre-installed so that testing can commence immediately upon delivery.

The MP42H bus is equally well-suited for use in single-satellite missions or as the standardized platform for an entire constellation.

The MP42H is highly versatile and is optimized for remote sensing, high data throughput and complex communications missions, emergency communications, and fundamental research missions. In all missions and applications minimal reconfiguration of the existing system setup is needed and a range of standardized data interfaces, components, and protocols add to the reliability and performance of the platform.

The MP42H can also be equipped with a propulsion system, if required, that enables the satellite to carry out high-impulse orbital maneuvers. This adds to the flexibility and reliability of the system as well as extending satellite lifetime.

  • Microsatellite General Features:
    • Total empty bus mass: from 18 kg (depends on configuration)
    • Maximum satellite mass: 40 kg* (depends on configuration and Payload Mass Properties)
    • MP42H Payload Envelope: 280 x 325 x 280* mm (*satellite height is highly adjustable to customers payload requirements, up to 1300 mm)
  • Specifications:
    • MP42H Bus is already pre-integrated (mechanically, electrically and functionally tested) and pre-qualified to be ready for instant payload integration. Therefore, final flight acceptance and flight readiness procedures are minimized for the Customer.
    • Default operation of MP42H Bus during satellite mission is implemented at command level by execution of uploaded scripts.
    • A sophisticated mission code can be prepared by the NanoAvionics team according to separately agreed terms and conditions.
  • Payload Controller 2.0 (Default):
    • Zynq®-7015 SoC family device featuring ARM Cortex™-A9 processor mated with Artix®-7 based programmable logic.
    • Maximum frequency 866 MHz.
    • 74K Programmable Logic Cells.
    • 256 KB on-chip RAM (processor) and 36 Kb block RAM (programmable logic).
    • 32 MB of external NOR-FLASH for Boot (2× 16 MB chips, QSPI).
    • 3× 512KB of FRAM (SPI) for frequently changing data storage.
    • 2 × 512MB of RAM (DDR3).
    • Integrated RTC.
    • microSD NAND Memory support (up to 4× microSD).
    • PetaLinux operating system.
    • In-Orbit firmware update.
    • Firmware Power-on-check and Restore.
    • RFS – Redundant Record-based File System.
    • A number of Payload dedicated interfaces:
      • 1x Ethernet (with integrated magnetics).
      • 2x CAN Interfaces.
      • 4x RS422/UART.
      • 2x SPI.
      • 1x UART (Debug).
      • 2x I2C.
      • 1x USB 2.0.
      • Up to 34 x LVDS, GTP, GPIO.
    • CSP Support.
    • Self-Diagnostics.
    • Dynamic CPU Frequency Control.
    • User-friendly Console.
  • Payload Controller 1.5 (Optional):
    • 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.
    • 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 MPPT converters efficiency: up to 97 %;
    • Output converter efficiency: up to 97 %;
    • External battery pack provides up to 995 Wh battery capacity;
    • Battery Cell Balancing;
    • Fail-Safe Design.

    Outputs:

    • 20 output channels in default, up to 80 output channels in extended output version (configurable voltage rail);
    • Max 5 V Output converter power: 40 W;
    • Max 12 V Output converter power: 60 W;
    • Max 28 V Output converter power: 75 W;
    • Max unregulated output power with on-board battery back (4S1P configuration): 50 W;
    • Max unregulated output power with on-board battery back (12S7P configuration): 1050 W.

    Inputs:

    • Four MPPT converters (12 solar panel input channels) with integrated ideal blocking diodes;
    • Solar panel voltage range: 5 – 72 V;
    • Max input power per MPPT converter: 50 W;
    • Max charging power with 4S1P battery back configuration: 25 W;
    • Max charging power with 12S7P battery back configuration: 525 W.
  • Flight Computer (Including ADCS Functionality):
    • ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHz (configurable).
    • Double-Precision FPU.
    • 1 MB of Internal RAM.
    • MB of Internal FLASH memory.
    • 2×512 KB of FMC-connected FRAM.
    • 256 MB of External NOR-FLASH for data storage.
    • 2×512 KB of FRAM (SPI) for frequently changing data storage.
    • Integrated RTC.
    • microSD NAND memory up to 32 GB.
    • On-board Magnetorquers Drivers.
    • PWM Outputs.
    • In-orbit Firmware Update.
    • Firmware Power-on-check and Restore.
    • RFS – redundant record-based file system.
    • CSP Support.
    • Self-Diagnostics.
    • Dynamic CPU frequency control.
    • User-friendly console.
    • Mission Planner with time-scheduled script/task execution support.
    • Telemetry Logging.

    ADCS Sensors:

    • High precision Inertial Measurement Unit (IMU).
    • Magnetic Sensors System.
    • Albedo-free Fine Sun Sensors.
    • Star Trackers.

    Actuators:

    • Reaction Wheels System.
    • Integrated Magnetorquers.

    Attitude Control type:

    • 3-axis stabilization.

    Attitude pointing accuracy ranges (pointing/knowledge) and attitude maneuver ability (slew rate) depends on the final bus parameters:

    • Up to 0.05° / up to 0.01° / up to 5°/s.

    Operational modes:

    • Sun pointing mode.
    • Nadir pointing mode.
    • Velocity pointing mode.
    • Ground geodetic coordinate pointing mode.
    • Client defined pointing mode.
  • Microsatellite General Features:
    • Total empty bus mass: from 18 kg (depends on configuration)
    • Maximum satellite mass: 40 kg* (depends on configuration and Payload Mass Properties)
    • MP42H Payload Envelope: 280 x 325 x 280* mm (*satellite height is highly adjustable to customers payload requirements, up to 1300 mm)
  • Specifications:
    • MP42H Bus is already pre-integrated (mechanically, electrically and functionally tested) and pre-qualified to be ready for instant payload integration. Therefore, final flight acceptance and flight readiness procedures are minimized for the Customer.
    • Default operation of MP42H Bus during satellite mission is implemented at command level by execution of uploaded scripts.
    • A sophisticated mission code can be prepared by the NanoAvionics team according to separately agreed terms and conditions.
  • Payload Controller 2.0 (Default):
    • Zynq®-7015 SoC family device featuring ARM Cortex™-A9 processor mated with Artix®-7 based programmable logic.
    • Maximum frequency 866 MHz.
    • 74K Programmable Logic Cells.
    • 256 KB on-chip RAM (processor) and 36 Kb block RAM (programmable logic).
    • 32 MB of external NOR-FLASH for Boot (2× 16 MB chips, QSPI).
    • 3× 512KB of FRAM (SPI) for frequently changing data storage.
    • 2 × 512MB of RAM (DDR3).
    • Integrated RTC.
    • microSD NAND Memory support (up to 4× microSD).
    • PetaLinux operating system.
    • In-Orbit firmware update.
    • Firmware Power-on-check and Restore.
    • RFS – Redundant Record-based File System.
    • A number of Payload dedicated interfaces:
      • 1x Ethernet (with integrated magnetics).
      • 2x CAN Interfaces.
      • 4x RS422/UART.
      • 2x SPI.
      • 1x UART (Debug).
      • 2x I2C.
      • 1x USB 2.0.
      • Up to 34 x LVDS, GTP, GPIO.
    • CSP Support.
    • Self-Diagnostics.
    • Dynamic CPU Frequency Control.
    • User-friendly Console.
  • Payload Controller 1.5 (Optional):
    • 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.
    • 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 MPPT converters efficiency: up to 97 %;
    • Output converter efficiency: up to 97 %;
    • External battery pack provides up to 995 Wh battery capacity;
    • Battery Cell Balancing;
    • Fail-Safe Design.

    Outputs:

    • 20 output channels in default, up to 80 output channels in extended output version (configurable voltage rail);
    • Max 5 V Output converter power: 40 W;
    • Max 12 V Output converter power: 60 W;
    • Max 28 V Output converter power: 75 W;
    • Max unregulated output power with on-board battery back (4S1P configuration): 50 W;
    • Max unregulated output power with on-board battery back (12S7P configuration): 1050 W.

    Inputs:

    • Four MPPT converters (12 solar panel input channels) with integrated ideal blocking diodes;
    • Solar panel voltage range: 5 – 72 V;
    • Max input power per MPPT converter: 50 W;
    • Max charging power with 4S1P battery back configuration: 25 W;
    • Max charging power with 12S7P battery back configuration: 525 W.
  • Flight Computer (Including ADCS Functionality):
    • ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHz (configurable).
    • Double-Precision FPU.
    • 1 MB of Internal RAM.
    • MB of Internal FLASH memory.
    • 2×512 KB of FMC-connected FRAM.
    • 256 MB of External NOR-FLASH for data storage.
    • 2×512 KB of FRAM (SPI) for frequently changing data storage.
    • Integrated RTC.
    • microSD NAND memory up to 32 GB.
    • On-board Magnetorquers Drivers.
    • PWM Outputs.
    • In-orbit Firmware Update.
    • Firmware Power-on-check and Restore.
    • RFS – redundant record-based file system.
    • CSP Support.
    • Self-Diagnostics.
    • Dynamic CPU frequency control.
    • User-friendly console.
    • Mission Planner with time-scheduled script/task execution support.
    • Telemetry Logging.

    ADCS Sensors:

    • High precision Inertial Measurement Unit (IMU).
    • Magnetic Sensors System.
    • Albedo-free Fine Sun Sensors.
    • Star Trackers.

    Actuators:

    • Reaction Wheels System.
    • Integrated Magnetorquers.

    Attitude Control type:

    • 3-axis stabilization.

    Attitude pointing accuracy ranges (pointing/knowledge) and attitude maneuver ability (slew rate) depends on the final bus parameters:

    • Up to 0.05° / up to 0.01° / up to 5°/s.

    Operational modes:

    • Sun pointing mode.
    • Nadir pointing mode.
    • Velocity pointing mode.
    • Ground geodetic coordinate pointing mode.
    • Client defined pointing mode.
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