Contact
Microsatellite Bus MP42

Microsatellite Bus MP42

Download MP42 Bus Brochure Here

The hardware and software of NanoAvionics satellite bus MP42, as well as mission operations infrastructure, are established on baseline architecture and mission-specific “building blocks” for flexible, time- & cost-efficient integration, resulting in wide applicability, reliability, repeatability, and manufacturability.

MP42 buses are highly versatile – their performance capabilities are optimized for remote sensing, high data throughput & complex communications missions, emergency communications, and fundamental research missions – all requiring minimal reconfiguration.

All of the MP42 subsystems have been flight-proven during these different types of missions. The latest technological developments have been implemented to ensure the practical reliability of the platform. Critical systems such as the Flight Computer, Payload Controller, Electric Power System, and all others are 20krad radiation-tolerant and have an expected lifetime of 5 years in LEO. MP42 enables high payload data downlink speed – up to 1 Gbps downlink on the X-Band – while intersatellite link ensures uninterrupted real-time communications (LEO-LEO and LEO-GEO options available).

MP42 buses can include a propulsion system that enables the satellite to perform high-impulse maneuvers such as: orbital deployment, orbit maintenance, precision flight in formations, orbit synchronization, and atmospheric drag compensation. This results in extended satellite orbital lifetime uncovering new opportunities for unique customer missions and significant savings on constellation maintenance costs.

1
2
3
4
5
Drag to sides
Request information

Microsatellite Bus MP42

Download MP42 Bus Brochure Here

The hardware and software of NanoAvionics satellite bus MP42, as well as mission operations infrastructure, are established on baseline architecture and mission-specific “building blocks” for flexible, time- & cost-efficient integration, resulting in wide applicability, reliability, repeatability, and manufacturability.

MP42 buses are highly versatile – their performance capabilities are optimized for remote sensing, high data throughput & complex communications missions, emergency communications, and fundamental research missions – all requiring minimal reconfiguration.

All of the MP42 subsystems have been flight-proven during these different types of missions. The latest technological developments have been implemented to ensure the practical reliability of the platform. Critical systems such as the Flight Computer, Payload Controller, Electric Power System, and all others are 20krad radiation-tolerant and have an expected lifetime of 5 years in LEO. MP42 enables high payload data downlink speed – up to 1 Gbps downlink on the X-Band – while intersatellite link ensures uninterrupted real-time communications (LEO-LEO and LEO-GEO options available).

MP42 buses can include a propulsion system that enables the satellite to perform high-impulse maneuvers such as: orbital deployment, orbit maintenance, precision flight in formations, orbit synchronization, and atmospheric drag compensation. This results in extended satellite orbital lifetime uncovering new opportunities for unique customer missions and significant savings on constellation maintenance costs.

  • Bus Features:
    • Total empty bus mass: from 30 kg
    • Payload volume: 48 x 48 x 32* cm (*payload height is highly adjustable to customers payload requirements)
    • MP42 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 MP42 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:
    • Dual ARM A9 CPU running Linux
    • Artix FPGA for complex data processing
    • 1 GB DDR3L or 512 MB DDR3L ECC protected volatile memory
    • 3 x 4 Mbit FRAM high-reliability storage
    • 2 x 16 MB NAND storage
    • 4 x microSD 32GB to 128 GB interfaces 2 x (1+1)
    • 22 LVDS pairs for flexible high bandwidth IO applications
    • Over 40 GPIO for low-speed IO
    • 4 x RS422 transceivers (up to 1 Mbps + 3x up to 10 Mbps)
    • 2 x I2C lines
    • On-board Temperature sensor
    • On-Board RTC
    • 2 x CAN (1Mbps)
    • 2 x SPI interfaces
    • 2 x 1 Gbps Ethernet
    • USB 2.0 controller (accessible via expander interface)
    • Flexible PCIe, SATA, USB 3.0 SpaceWire interfaces for high bandwidth applications (accessible via expander interface)
    • GPIOS, LVDS pairs and power supplies available at expansion interface
    • 2 Load Switches for external power control
    • Power input: 4.5 V to 15.5 V
    • PC104 form factor
    • Shield option available
    • Trackless PCB design
  • Power System:
    • Input MPPT converters efficiency: up to 97 %
    • Output converter efficiency: up to 97 %
    • Battery Cells Balancing
    • Fail-Safe Design

    Outputs:

    • 20 output channels in default, up to 80 output channels in extended output version (configurable voltage rail)
    • Typical output channel current: 3A (configurable)
    • Max 3.3 V Output converter power: 40 W
    • Max 5 V Output converter power: 50 W
    • Max 3-18 V Output converter power: 50 W
    • Max unregulated output power with default battery back (4S1P configuration): 50 W
    • Max unregulated output power with extended battery pack (8S7P configuration): 600 W

    Inputs:

    • Eight MPPT converters (16 solar panel input channels) with integrated ideal blocking diodes
    • Max input power per MPPT converter: 50 W
    • Max charging power with 4S1P battery pack configuration: 20 W
    • Max charging power with 8S7P battery pack configuration and extended input converters: 270 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
    • FreeRTOS
    • 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) depends on the final bus parameters:

    • Up to 0.05° / up to 0.01°

    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:
    • Total empty bus mass: from 30 kg
    • Payload volume: 48 x 48 x 32* cm (*payload height is highly adjustable to customers payload requirements)
    • MP42 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 MP42 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:
    • Dual ARM A9 CPU running Linux
    • Artix FPGA for complex data processing
    • 1 GB DDR3L or 512 MB DDR3L ECC protected volatile memory
    • 3 x 4 Mbit FRAM high-reliability storage
    • 2 x 16 MB NAND storage
    • 4 x microSD 32GB to 128 GB interfaces 2 x (1+1)
    • 22 LVDS pairs for flexible high bandwidth IO applications
    • Over 40 GPIO for low-speed IO
    • 4 x RS422 transceivers (up to 1 Mbps + 3x up to 10 Mbps)
    • 2 x I2C lines
    • On-board Temperature sensor
    • On-Board RTC
    • 2 x CAN (1Mbps)
    • 2 x SPI interfaces
    • 2 x 1 Gbps Ethernet
    • USB 2.0 controller (accessible via expander interface)
    • Flexible PCIe, SATA, USB 3.0 SpaceWire interfaces for high bandwidth applications (accessible via expander interface)
    • GPIOS, LVDS pairs and power supplies available at expansion interface
    • 2 Load Switches for external power control
    • Power input: 4.5 V to 15.5 V
    • PC104 form factor
    • Shield option available
    • Trackless PCB design
  • Power System:
    • Input MPPT converters efficiency: up to 97 %
    • Output converter efficiency: up to 97 %
    • Battery Cells Balancing
    • Fail-Safe Design

    Outputs:

    • 20 output channels in default, up to 80 output channels in extended output version (configurable voltage rail)
    • Typical output channel current: 3A (configurable)
    • Max 3.3 V Output converter power: 40 W
    • Max 5 V Output converter power: 50 W
    • Max 3-18 V Output converter power: 50 W
    • Max unregulated output power with default battery back (4S1P configuration): 50 W
    • Max unregulated output power with extended battery pack (8S7P configuration): 600 W

    Inputs:

    • Eight MPPT converters (16 solar panel input channels) with integrated ideal blocking diodes
    • Max input power per MPPT converter: 50 W
    • Max charging power with 4S1P battery pack configuration: 20 W
    • Max charging power with 8S7P battery pack configuration and extended input converters: 270 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
    • FreeRTOS
    • 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) depends on the final bus parameters:

    • Up to 0.05° / up to 0.01°

    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
At NanoAvionics we are always looking for talented people to join our professional team. Sounds like you?
See open positions
ISO 9001:2015