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<p>This paper describes the realization of a reconfigurable command distribution Application-Specific Integrated Circuit (ASIC) using inhouse 180&#xa0;nm Radiation Hardened By Design (RHBD) bulk Complementary Metal Oxide Semiconductor (CMOS) technology library. Spacecraft operations are controlled from ground stations through its telecommand subsystem. Command distribution is a critical building block of the telecommand system that distributes the discrete commands to other subsystems after the validation and decoding of command codes uplinked from the ground station. For every spacecraft, the mission objective decides the&#xa0;configuration and various types of commands, which have their own interfaces. Hence, the associated hardware modules for command generation and distribution vary from spacecraft to spacecraft. Traditionally, a discrete component-based design with one-time programmable Field Programmable Gate Arrays (FPGAs) and fixed ASIC design done with external foundry was followed in our spacecraft avionics, which required different hardware modules to be realized, that had high Turn&#xa0;Around Time (TAT). The monolithic reconfigurable command distribution ASIC design realized with in-house foundry presented in this paper simplifies the overall command distribution system. Multiple ASICs can be used in the same Command Distribution Module (CDM) to achieve higher capacity at the spacecraft level as additional board space becomes available due to a minimal number of discrete components. Another advantage is that the reconfigurable nature of the ASIC meets quantitative requirements for different types of commands across many spacecraft missions with the same CDM reducing TAT significantly. The challenges and approach for achieving defect testability in ASIC design with redundant fail-safe logics are presented. The ASIC is validated for radiation reliability in space for SEE up to 67&#xa0;MeV-cm<sup>2</sup>/mg and up to 200kRads for Total Ionization Dose (TID). Subsequently, these ASICs have also been inducted into our spacecraft Avionics.</p>

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Reconfigurable Command Distribution ASIC for Spacecraft Avionics

  • 期刊论文

  • 发表日期：

    2025年8月21日

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  • A. Rajendra Kumar,
  • K. Padmapriya,
  • J. K. Kishore,
  • Debjyoti Mallik,
  • Suvashish Tiwari

摘要

This paper describes the realization of a reconfigurable command distribution Application-Specific Integrated Circuit (ASIC) using inhouse 180 nm Radiation Hardened By Design (RHBD) bulk Complementary Metal Oxide Semiconductor (CMOS) technology library. Spacecraft operations are controlled from ground stations through its telecommand subsystem. Command distribution is a critical building block of the telecommand system that distributes the discrete commands to other subsystems after the validation and decoding of command codes uplinked from the ground station. For every spacecraft, the mission objective decides the configuration and various types of commands, which have their own interfaces. Hence, the associated hardware modules for command generation and distribution vary from spacecraft to spacecraft. Traditionally, a discrete component-based design with one-time programmable Field Programmable Gate Arrays (FPGAs) and fixed ASIC design done with external foundry was followed in our spacecraft avionics, which required different hardware modules to be realized, that had high Turn Around Time (TAT). The monolithic reconfigurable command distribution ASIC design realized with in-house foundry presented in this paper simplifies the overall command distribution system. Multiple ASICs can be used in the same Command Distribution Module (CDM) to achieve higher capacity at the spacecraft level as additional board space becomes available due to a minimal number of discrete components. Another advantage is that the reconfigurable nature of the ASIC meets quantitative requirements for different types of commands across many spacecraft missions with the same CDM reducing TAT significantly. The challenges and approach for achieving defect testability in ASIC design with redundant fail-safe logics are presented. The ASIC is validated for radiation reliability in space for SEE up to 67 MeV-cm2/mg and up to 200kRads for Total Ionization Dose (TID). Subsequently, these ASICs have also been inducted into our spacecraft Avionics.