Summary

The Kongsberg NanoAvionics MP42H is a Microsatellite bus designed for space applications.

It uses a 15″ ESPA-class separation ring and can accommodate payloads with a maximum mass of 60 kg and a total footprint of 572(L) x 460(W) x 370(H)* mm. *Payload height is flexible, as long as the total satellite height does not exceed the launch vehicle’s allowable volume. The large payload envelope provides flexibility for deployable antennas, booms, and other structures.

The platform is also loaded with sample mission code (which is easily customized, extended, or replaced) and pre-qualified for fast flight acceptance testing, subject to mission requirements. NanoAvionics offers three standard MP42 microsatellite performance configurations – Light, Mid, and Max – providing options that best match customers’ payload, mission objectives, and budget.

It is a versatile system and has been optimized for high data throughput and complex communications missions and services. It is also suitable for research projects, emergency communications, and remote sensing services, and can be adapted to such applications with minimal reconfiguration.

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: 2024-02-05

MP42 - Microsatellite Bus

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