Summary

The NanoAvionics Multi-Purpose 12U Bus (M12P) is a 12U satellite bus with modular design, and standardized architecture optimized for constellation.

The standard configuration of the M12P bus is for IoT, M2M, ADS-B, AIS, other commercial and emergency communication applications, and scientific missions. M12P configuration for Earth Observation (EO) missions are available as an option.

Maximization of the payload volume is enabled by the hardware layout. It also ensures robust power functionality and thermal control for sensitive payloads, such as measurement and sensing instruments.

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

The system uses the open source FreeRTOS real-time operating system. The FreeRTOS is light weight, reliable, relatively simple and easy to use. The kernel is designed specifically for integral embedded systems and provides a full set of the task scheduler, resource management, and synchronization features.

CubeSat Space Protocol (CSP) enables distributed embedded systems to deploy a service-oriented network topology.

Critical system such as the Flight Computer, Payload Controller, Electric Power System and Communication System are supported by implementing radiation-resistant components and design to ensure reliability.

Data and tasking delay challenges that are critical to the professional service applications, are eliminated through the implementation of intersatellite link system via GEO satellites and integration with KSAT ground station network for constant connectivity.

The M12P 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.

M12P 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.

Launch support is available optimized to M12P satellite bus. NanoAvionics have access to launch providers such as PSLV (India), Rocket Lab Electron (New Zealand), SpaceX Falcon 9, Soyuz, Vega, Long March, Orbital Sciences Antares and Atlas V launch vehicles.

NanoAvionics also has access to launch integration services covering programmatic aspects such as securing the specific launch slot, coordination of logistics, arrangement of mission-specific documents and technical aspects related to flight preparation and integration of the spacecraft with the deployer.

NanoAvionics was selected to build a 12U nanosatellite bus, to be launched in 2022, for an in-orbit demonstration of NASA’s Advanced Composite Solar Sail System (ACS3).

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 M12P Bus during satellite mission implemented at command level by execution of uploaded scripts
Inter-satellite link for regular connectivity
Payload integration service available
Subsystem available in the M12P Bus includes
- Payload controller
  - Payload Controller 1.5 (default)
  - Payload Controller 2.0 (optional):
- Payload communication
  - Satlab S-Band Full-duplex Transceiver SRS-3 (default)
  - Satlab S-Band Full-duplex Transceiver SRS-4 (optional)
  - X-Band Transceiver (Optional)
  - X-Band Transmitter (Optional)
- Inter-satellite Link
  - Data Link Service via GEO Satellites (Optional)
- Command, Control and Telemetry / Payload communication NanoAvionics “SatCOM UHF”
- NanoAvionics Electrical Power Supply “EPS”
- 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 Unit
  - 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.'

NanoAvionics follows the protoflight model philosophy as described in ECSS-E-HB-10-02A to qualify the design.

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.

Design qualification testing reports of satellite bus can be disclosed to the customer if required.

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: 2023-03-08