Modular SmallSat C&DH Architecture for Radiation Tolerance

Solution Overview

Problem

Current commercial off-the-shelf (COTS) components for spacecraft Command and Data Handling (C&DH) systems face challenges in handling single event effects (SEE) and total ion dose (TID) radiation, requiring a radiation-tolerant and flexible design to ensure reliability and performance beyond existing capabilities.

Innovation Solution

A modular architecture for SmallSat C&DH hardware using a combination of robust radiation-tolerant and COTS components, featuring a reprogrammable field programmable gate array (FPGA) with a soft-core processor, error correction capabilities, and modular design to accommodate various configurations within a 1U CubeSat form factor, including a C&DH processor card and auxiliary card with analog circuitry and miniaturized components.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of manufacture

If commercial off-the-shelf (COTS) components are used for C&DH systems, then cost is reduced, but radiation tolerance and reliability deteriorate

Engineering Contradiction:

ImprovecostVSAvoidradiation tolerance

Core Design Contradiction:

Ease of manufactureVSReliability

Solution Approach 1:

The system is divided into two distinct segments: radiation-tolerant components (FPGA, processor) for critical functions requiring high reliability, and COTS components for non-critical functions where cost is prioritized. This segmentation allows each segment to be optimized for its specific requirements while working together in an integrated system.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Different quality levels are applied to different parts of the system based on their functional requirements. Critical subsystems (command processing, data handling, flight software execution) use radiation-tolerant components with higher reliability, while less critical subsystems use cost-effective COTS components, creating a heterogeneous system with locally optimized quality.

Inventive Principle:

Principle #3Local quality

2Reliability

If radiation tolerant components are used, then reliability is improved, but cost increases

Engineering Contradiction:

Improveradiation toleranceVSAvoidcost

Core Design Contradiction:

ReliabilityVSEase of manufacture

Solution Approach 1:

The system is divided into two distinct segments: radiation-tolerant components (FPGA, processor) for critical functions requiring high reliability, and COTS components for non-critical functions where cost is prioritized. This segmentation allows each segment to be optimized for its specific requirements while working together in an integrated system.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Different quality levels are applied to different parts of the system based on their functional requirements. Critical subsystems (command processing, data handling, flight software execution) use radiation-tolerant components with higher reliability, while less critical subsystems use cost-effective COTS components, creating a heterogeneous system with locally optimized quality.

Inventive Principle:

Principle #3Local quality

3Loss of time

If a fixed C&DH design is used, then development time is reduced, but adaptability to different mission configurations deteriorates

Engineering Contradiction:

Improvedevelopment timeVSAvoidconfiguration flexibility

Core Design Contradiction:

Loss of timeVSAdaptability or versatility

Solution Approach 1:

The C&DH system incorporates dynamic reconfigurability through the FPGA, which can be programmed with different flight software and configuration settings depending on the specific mission requirements. This allows the hardware platform to adapt its functionality dynamically without requiring physical redesign, achieving both rapid development and high adaptability.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The modular C&DH architecture with standardized interfaces and the reprogrammable FPGA creates a universal platform that can serve multiple mission types and configurations. The same hardware base can be adapted for different satellite bus types, mission durations, and operational requirements through software configuration rather than hardware redesign.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Data Source

PatentUS11618592B1Modular architecture for an extensible SmallSat (MARES) command and data handling hardware

Publication Date: 2023.04.04 UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR NAT AERONAUTICS & SPACE ADMINISTRATION

AI summary

The present invention relates to a modular architecture for a resilient extensible SmallSat (MARES) command and data handling (C&DH) device used in a spacecraft, the modular architecture which conforms to a 1U CubeSat board area form factor, including: a C&DH processor card disposed on a backplane of the form factor; a C&DH processor card disposed on a backplane of the form factor; a fault tolerant field programmable gate array (FPGA) disposed on the C&DH processor card, the FPGA including an embedded fault tolerant memory controller, and a soft-core processor which runs core flight software on a real-time executive for a multiprocessor operating system; and a C&DH auxiliary card disposed on the backplane and used in conjunction with the C&DH processor card, to provide processing capability for the spacecraft, the auxiliary card which contains peripheral interface drivers and read electronics for monitoring a health and safety of the spacecraft.