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INSTRUMENT CONTROL UNIT - ( ICU )

Instrument Thermal Control & Payload Data Processor in Single Sub-System

ICU-Datasheet
ICU - STP CAD
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PIONEERING SPACECRAFT COMPUTING

The ICU provides centralized and autonomous management for spacecraft payloads, including OMA and Auxiliary Camera subsystems, and sensor interfaces. The system is built upon a COTS or radiation-tolerant PolarFire FPGA SoC platform, ensuring robust performance, low power consumption, and high reliability.

KEY FEATURES

  • Radiation-tolerant components and TID monitoring.
  • Integrated FPGA co-processing capabilities.
  • Autonomous thermal management.
  • Dedicated power distribution and monitoring circuits.
  • Fault detection, isolation, and recovery (FDIR) capabilities.
  • Redundant communication interfaces ensuring reliable data transfer.

INTERFACES & DATA COMMUNICATION

  • SpaceWire Interfaces: Main and redundant backup interfaces for reliable communication with the OMA subsystem. Main and Redundant communication with the PLHU platform. Main and redundant interfaces for auxiliary camera.
  • CAN Bus Interfaces: Telemetry and telecommand communication with the PLHU subsystem. Additional redundant CAN interfaces for mission expansion and fault tolerance.
  • RS422 Interfaces: Multiple RS422 communication channels provided for robust data transfer, subsystem interfacing, and debugging purposes.
  • Ethernet Interface: Ethernet port dedicated to debugging, software developments, and system diagnostics.
  • Sensor Interfaces: Integrated radiation-tolerant ADC channels for temperature sensor readings and radiation monitoring.
  • Heater Control Interfaces: PWM-controlled heater channels with built-in short-circuit and fault detection mechanisms.
  • Power Interfaces: Dedicated regulated 12V DC power line for the OMA subsystem. Monitored and controlled power rails with independent latch-up protection.
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PROCESSOR

  • Processor Type: The ICU utilizes the PolarFire FPGA SoC for all versions: PFM/QFM/FM versions: Radiation-tolerant version of the PolarFire FPGA SoC. EM version: Standard PolarFire SoC.
  • Core Configuration: The PolarFire SoC features 5 RISC-V processors, which can operate either independently or in a lock-step configuration for fault-tolerant operation. The combined processing power of all cores can reach up to 4000 DMIPS.
  • Operating Systems Supported: The system supports a range of real-time operating systems (RTOS), including: FreeRTOS (lightweight RTOS), Linux (for more complex tasks) and Bare-metal (for low-level control).
  • The processors can run independently or in lock-step mode depending on mission requirements.
  • Open-Source Toolchains: The ICU leverages open-source development and debug toolchains, available for both Windows and Linux hosts. These tools support development and debugging for RISC-V processors and FPGA fabric components.
  • Custom Co-Processing: The FPGA fabric of the PolarFire SoC can implement custom co-processing cores to offload specific computations from the main processors to the fabric side, enabling flexible, high-performance computation with ease of use in user space
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FUNCTIONS

  • Real-time data acquisition and processing from sensors, including temperature and radiation sensors.
  • Autonomous heater control loops based on configurable temperature set points and profiles.
  • Robust power management and latch-up protection.
  • Secure firmware updates, remote image management, and rollback mechanisms.
  • High-precision timing synchronization through onboard RTC.
  • Housekeeping data collection, logging, and telemetry reporting.
  • FPGA-based custom computational offloading and acceleration.

HOUSEKEEPING & DIAGNOSTICS

  • The ICU autonomously manages system health through comprehensive housekeeping routines that monitor:

    • Internal temperatures and sensor health.
    • Voltage and current across multiple domains.
    • Radiation exposure levels (TID).
    • Heater functionality and thermal management effectiveness.
    • Real-time logging of system health metrics, supporting fault detection and preventative maintenance.

MEMORY & STORAGE

  • Radiation-Tolerant MRAM: The ICU utilizes radiation-tolerant MRAM chips to ensure reliable non-volatile memory storage in space environments. This memory is ideal for storing mission-critical data and software. We may also use MRAM as RAM.
  • Radiation-Tolerant Flash Storage: For data storage and program image storage, the ICU integrates radiation-tolerant Flash memory to ensure reliable long-term data retention.
  • Optional Radiation-Tolerant DDR4: Radiation-tolerant LPDDR4 may be included if required for specific high-bandwidth applications. However, this is not required for the current application and can be implemented based on mission-specific needs.

TEMP. SENSOR & HEATER CONTROL

  • Temperature Sensing and Control: The ICU integrates radiation-tolerant ADC circuitry for accurate temperature sensor readings. These temperature readings are transmitted to the PolarFire SoC for processing and thermal control.
  • Heater Control: Heater driver circuitry will be implemented as needed, either on a separate board or integrated into the processor board, depending on the mechanical and enclosure design. The system supports a double-stack configuration, integrating 12V power circuitry for the OMA camera and the heater driver circuitry.
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REDUNDANCY & LATCH-UP DETECTION

  • Redundant power paths will be implemented to ensure system stability in the event of power failure.
  • Latch-up detection and recovery mechanisms will be implemented onboard to protect against transient errors and to ensure the ICU operates reliably in a radiation-prone environment.

RADIATION DETECTION

  • Radiation Monitoring: The ICU will include radiation detection sensors onboard to continuously monitor the Total Ionizing Dose (TID) levels. These sensors will provide real-time data to the system for radiation environment monitoring.
  • This radiation data will be used for system protection and to track any potential radiation-induced degradation.

PRODUCT DOCUMENTS

ICU is flight proven onboard computer for number of satellite projects and we have full ECSS/ NASA documentation documents & test reports.

    • Failure Modes, Effects, and Criticality Analysis (FMECA)
    • Reliability Analysis Report
    • Radiation Analysis Report
    • Safety Assurance Plan
    • Fault Tree Analysis (FTA)
    • Single Point Failure Analysis (SPFA)
    • Worst Case Analysis (WCA)
    • Derating Analysis Report
    • Availability Analysis Report
    • Mechanical Analysis Report
    • Maintainability Analysis Report
    • Fault Detection, Isolation, and Recovery (FDIR)
    • Qualification Test Plan (QTP)
    • Environmental Test Reports, TVAC, Vib.
    • EMC/EMI Test Report
    • Radiation Test Report
    • Operational Risk Assessment (ORA)
    • Critical Items List (CIL)
    • Materials, Processes, and Mechanical Parts List (MPMPL)
    • Product Assurance Plan (PAP)
    • Configuration Item Data List (CIDL)
    • End Item Data Package (EIDP)
    • As-Built Configuration List (ABCL)

BUDGET

  • Dimension: 180*150*50 mm
  • Mass: 1.85 kg
Instrument Control Unit
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