Microsatellite Bus MP42

Download MP42 Buses Brochure Here

Our mid-range microsatellite bus uses a 15″ separation ring and accommodates payloads with a maximum footprint of 490 x 480 mm and a mass of up to 75 kg. Payload height is flexible as long as the total satellite height does not exceed 1300 mm.

MP42 is highly modular – its configurable subsystems and deployable solar panel configurations can meet customer’s precise mission performance, agility, and power demands.

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 bus is 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.

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 an extended satellite orbital lifetime uncovering new opportunities for unique customer missions and significant savings on constellation maintenance costs.

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Download MP42 Buses Brochure Here

MP42 is highly modular – its configurable subsystems and deployable solar panel configurations can meet customer’s precise mission performance, agility, and power demands.

Microsatellite General Features:
MP42:
- Total empty bus mass: from 45 kg (depends on configuration).
- Maximum satellite mass: 120 kg* (depends on configuration and Payload Mass Properties).
- MP42 Payload Envelope: 490 x 480 x 350* mm (*satellite height is highly adjustable to customers payload requirements, up to 1300 mm).
MP42H:
- Total empty bus mass: from 18 kg (depends on configuration).
- Maximum satellite mass: 40 kg* (depends on configuration and Payload Mass Properties).
- MP42 Payload Envelope: 280 x 325 x 280* mm (*satellite height is highly adjustable to customers payload requirements, up to 1300 mm).
MP42D:
- Total empty bus mass: from 70 kg (depends on configuration).
- Maximum satellite mass: 220 kg* (depends on configuration and Payload Mass Properties).
- MP42 Payload Envelope: 740 x 730 x 500* mm (*satellite height is highly adjustable to customers payload requirements, up to 1300 mm).
Specifications of Microsatellite Buses:
- MP42 Buses are 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 Buses 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:
- 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.
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
- 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) 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:
MP42:
- Total empty bus mass: from 45 kg (depends on configuration).
- Maximum satellite mass: 120 kg* (depends on configuration and Payload Mass Properties).
- MP42 Payload Envelope: 490 x 480 x 350* mm (*satellite height is highly adjustable to customers payload requirements, up to 1300 mm).
MP42H:
- Total empty bus mass: from 18 kg (depends on configuration).
- Maximum satellite mass: 40 kg* (depends on configuration and Payload Mass Properties).
- MP42 Payload Envelope: 280 x 325 x 280* mm (*satellite height is highly adjustable to customers payload requirements, up to 1300 mm).
MP42D:
- Total empty bus mass: from 70 kg (depends on configuration).
- Maximum satellite mass: 220 kg* (depends on configuration and Payload Mass Properties).
- MP42 Payload Envelope: 740 x 730 x 500* mm (*satellite height is highly adjustable to customers payload requirements, up to 1300 mm).
Specifications of Microsatellite Buses:
- MP42 Buses are 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 Buses 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:
- 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.
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
- 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) 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