Modular Avionics Architecture for Low-Mass Failure Recovery
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Solution Overview
Problem
Spacecraft systems face challenges with redundant sub-systems that add cost and mass due to the need for backup components, and existing distributed reconfigurable systems do not efficiently manage failures in extreme space conditions.
Innovation Solution
A distributed computer system with multiple computer nodes, each controlling different aspects of the spacecraft's mission, uses programmable processors that can execute flight software and dynamically take over functions of failing nodes via high-speed data links and backplane communication, eliminating the need for redundant systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If redundant sub-systems are included to handle failures, then reliability is improved, but mass and cost increase
Solution Approach 1:
The patent implements a reconfigurable computer architecture where a single computer system can dynamically assume multiple different sub-system functions through software configuration. When a failure is detected, the system reconfigures to perform the failed sub-system's functions, eliminating the need for physical redundant hardware while maintaining reliability through functional redundancy.
2Reliability
If redundant sub-systems are included to handle failures, then reliability is improved, but cost increases
Solution Approach 1:
The reconfigurable computer system consolidates multiple sub-system functions into a single multi-functional platform, reducing the total number of components required. This consolidation directly reduces manufacturing costs while maintaining the ability to handle failures through software-based reconfiguration rather than requiring expensive physical redundant systems.
Solution Approach 2:
Instead of creating physical copies of redundant hardware systems, the patent uses software virtualization to create functional copies of sub-system capabilities. The reconfigurable computer can replicate the computational and control functions of failed sub-systems through software, providing a cost-effective alternative to physical hardware duplication.
3Productivity
If the spacecraft becomes larger and more complex to maximize revenue, then productivity is improved, but device complexity increases
Solution Approach 1:
The reconfigurable computer system provides a foundation for multi-payload spacecraft by enabling a single computer platform to support multiple different payload functions. This allows the spacecraft to maximize revenue through diverse services while avoiding the complexity of separate dedicated computer systems for each payload, as the reconfigurable system can be software-defined to match mission requirements.
Data Source
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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 sends 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.