Distributed Spacecraft Avionics for Redundancy Without Extra Hardware
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Solution Overview
Problem
Spacecraft systems face increased complexity and cost due to the need for redundant sub-systems to handle failures under extreme conditions, which add mass and expense without being actively utilized until failure occurs.
Innovation Solution
A distributed computer system with multiple computer nodes, each controlling different aspects of the spacecraft's mission, utilizes a router processor and programmable processors that can execute flight software to control components and dynamically take over functions of failing nodes, eliminating the need for redundant systems by enabling remote control through high-speed data links and backplane communication.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If redundant sub-systems are included to handle failures, then reliability is improved, but device complexity and mass increase
Solution Approach 1:
Each computer node is designed with universal capabilities to perform multiple functions. The programmable processor can execute different flight software to control various spacecraft subsystems, and any node can take over the functions of any other node. This multi-functionality eliminates the need for dedicated redundant subsystems while maintaining reliability.
Solution Approach 2:
The patent merges the control functions of multiple subsystems into a single distributed computer system where all nodes share common resources including power, data links, and processing capabilities. By combining these functions and allowing dynamic task allocation, the system achieves reliability without duplicating hardware components.
2Reliability
If redundant sub-systems are included to handle failures, then reliability is improved, but mass increases
Solution Approach 1:
Each computer node possesses universal control capabilities that allow it to perform multiple subsystem functions. The programmable processor can be configured through flight software to control different spacecraft subsystems, enabling any node to replace any other node in case of failure. This eliminates the need for separate redundant hardware, reducing spacecraft mass.
Solution Approach 2:
Instead of creating physical copies of redundant subsystems, the patent uses software-based function copying. Flight software can be transferred between nodes to replicate control functions, providing redundancy through information rather than physical duplication, thereby reducing mass.
3Reliability
If multiple computer nodes with full redundancy are used, then reliability is improved, but cost increases
Solution Approach 1:
The patent implements universal computer nodes that can perform any subsystem control function through programmable processors executing flight software. This universality allows a single node design to replace multiple specialized redundant subsystems, reducing development, manufacturing, and integration costs while maintaining reliability.
Solution Approach 2:
The system employs dynamic task allocation where control functions can be reassigned between nodes based on operational needs and node status. This dynamic capability allows the system to adapt to failures without requiring static redundant hardware configurations, reducing overall system cost.
Data Source
AI summary
A distributed computer system for a spacecraft is disclosed. The system has multiple computer nodes, each controlling a different aspect of a mission of the spacecraft. Each node includes a control circuit(s) that controls a set of components, a router processor, and a programmable processor. The programmable processor of each respective computer node issue commands to the control circuit(s) of the respective computer node to carry out an aspect of the mission associated with the respective computer node. Upon failure of the programmable processor in a particular computer node, a healthy programmable processor send commands to the router processor in the particular computer node The router processor of the particular computer node routes the commands received from the remote programmable processor to the control circuit(s) in the particular computer node to control the set of components to carry out the aspect of the mission associated with particular computer node.