Summary

The NanoAvionics Microsatellite Bus MP42 is a microsatellite bus with modular design, and standardized architecture optimized for constellation.

MP42 buses are designed to be highly versatile. The performance capabilities of MP42 are optimized for remote sensing, high data throughput & complex communications missions, emergency communications, and fundamental research missions.

All the subsystems of the MP42 bus are 20krad radiation tolerant. The subsystems of the MP42 are flight-proven as part of different missions.

The satellite bus is designed to be flexible, reliable, time & cost-efficient during integration with wide applicability, repeatability, and manufacturability. The hardware, software, and mission operation infrastructures of the MP42 satellite bus are established on baseline architecture and mission-specific “building blocks”.

Sophisticated mission code preparation service can be offered by NanoAvionics according to separately agreed terms and conditions.

The MP42 bus includes a propulsion system. The subsystem can perform high-impulse manoeuvres such as orbital deployment, orbit maintenance, precision flight in formations, orbit synchronization and atmospheric drag compensation.
The propulsion system is designed to offer new opportunities for unique missions and a significant savings on constellation maintenance costs.

The propulsion unit also provides satellites with decommissioning capability at the end of mission, meeting the space debris mitigation requirements of ESA and NASA.

MP42 FlatSat access will be provided to help accelerate the development process, payload integration and testing cycle as well as enable simulation of the entire satellite mission.

Key features

  • Pre-integrated (mechanically, electrically and functionally tested) and pre-qualified to be ready for the payload integration
  • Minimized final flight acceptance and flight readiness procedures
  • Default operation of MP42 Bus during satellite mission implemented at command level by execution of uploaded scripts 
  • Subsystem available in the MP42 Bus are,
    • Payload controller
      • Payload Controller 1.5 (default)
      • Payload Controller 2.0 (optional)
    • Payload communication
    • Inter-satellite Link
      • Data Link Service via GEO Satellites (Optional)
    • Command, Control and Telemetry / Payload communication NanoAvionics “SatCOM UHF”
    • NanoAvionics Electrical Power Supply “EPS” 2.0
    • GaAs Solar Panels
    • Flight computer (including ADCS functionality) NanoAvionics “SatBus 3C2
    • Reaction Wheels System (SatBus RW)
    • Magnetorquers “SatBus MTQ
    • GPS System receiver
    • Propulsion System
      • NanoAvionics EPSS C2 (Default)
      • Electrical Propulsion system (optional)
      • Other propulsion equipment options are available
    • Surface mountable umbilical connector with main satellite CAN Bus, payload CAN Bus, battery charging, EPS Kill Switch Reset (KSR), EPS Kill Switch and Override (KS)
    • Integrated magnetometers and temperature sensors with the solar panels

Testing & qualification

NanoAvionics follows quality control procedures by ISO 9001. The company is certified since 2018.

Design of each subsystem of the bus is qualified by thermal vacuum cycling, vibration and shock testing following National Aeronautics and Space Administration General Environmental Verification Standard (NASA GEVS GSFC-STD-7000A) levels. Overall design is based on these ECSS standards and handbooks.

Electronic subsystems are assembled and qualified in accordance with the IPC-A-610 class 3 by IPC certified specialists applying the requirements for each individual electronic component containing the systems. Three dimensional Automatic Optical and X-Ray inspection is performed for each of the assembly.

Electromagnetic Compatibility (EMC) testing at the bus level is performed to qualify robustness against adverse effects of electromagnetic interference from external sources, internal subsystems or the electromagnetic environment of space.

Mechanical components are subjected to measurement checks for tolerance control. Incoming and outgoing items inspection is performed at NanoAvionics to minimize the risk of faults and failures due to the discrepancy of the components.

All subsystems of the satellite bus are radiation tested under 20 kRad Total Ionizing Dose (TID). Additionally, mechanically complex subsystems such as reaction wheels are tested by accelerated lifetime tests to qualify proper functionality.

For traceability purposes each system has a unique number indicated, where the serial number refers to a unique item list and the technical documentation of the product. Incoming/outgoing inspection documentation can be released to the customer if required.

After complete assembly satellite bus undergoes functional testing following European Space Agency European Cooperation for Space Standardization (ESA ECSS) guidance. NanoAvionics also follows the documentation list and content suggested by ECSS standard for nano and micro satellites development.

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Last updated: 2022-06-06

MP42 - Microsatellite Bus

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Specs

mass
> 30 kg

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