Fly-By-Wire Control Router With FAT Voting and Backup Power
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Solution Overview
Problem
Small general aviation (GA) aircraft lack the space and power to implement redundancy systems for fly-by-wire systems, which are essential for ensuring the integrity of flight control instructions and providing reliable operation in case of processor failure or power loss.
Innovation Solution
A universal vehicle control router is introduced, which includes multiple flight control computers with fully analyzable and testable voters (FAT voters) and backup batteries. This system is designed to be compact and self-contained, allowing it to be mounted in a single rack, and it performs self-assessments and cross-assessments to validate actuator instructions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional redundancy systems are implemented in small GA aircraft, then reliability of fly-by-wire system is improved, but weight and space requirements increase beyond available capacity
Solution Approach 1:
The patent combines multiple flight control computers and their power supplies into a single integrated rack-mounted system. The controllers are physically combined in one location rather than distributed separately, and the power supplies are consolidated into shared units that can support multiple controllers simultaneously. This merging reduces total weight and space compared to traditional redundant systems where each controller has its own dedicated power supply.
Solution Approach 2:
The patent implements universal power supplies that can serve multiple flight control computers simultaneously. Instead of dedicated power supplies for each controller, a single power supply unit can provide power to multiple controllers, making the power system multi-functional. This universality reduces the total number of power supplies needed, thereby reducing weight and space while maintaining redundancy.
2Reliability
If traditional redundancy systems are implemented in small GA aircraft, then reliability of fly-by-wire system is improved, but device complexity increases beyond manageable levels
Solution Approach 1:
The patent combines multiple flight control computers and their power supplies into a single integrated rack-mounted system. The controllers are physically combined in one location rather than distributed separately, and the power supplies are consolidated into shared units that can support multiple controllers simultaneously. This merging reduces total weight and space compared to traditional redundant systems where each controller has its own dedicated power supply.
Solution Approach 2:
The patent implements universal power supplies that can serve multiple flight control computers simultaneously. Instead of dedicated power supplies for each controller, a single power supply unit can provide power to multiple controllers, making the power system multi-functional. This universality reduces the total number of power supplies needed, thereby reducing weight and space while maintaining redundancy.
3Reliability
If traditional redundancy systems are implemented in small GA aircraft, then reliability of fly-by-wire system is improved, but cost increases beyond budget constraints
Solution Approach 1:
The patent combines multiple flight control computers and their power supplies into a single integrated rack-mounted system. The controllers are physically combined in one location rather than distributed separately, and the power supplies are consolidated into shared units that can support multiple controllers simultaneously. This merging reduces total weight and space compared to traditional redundant systems where each controller has its own dedicated power supply.
Solution Approach 2:
The patent implements universal power supplies that can serve multiple flight control computers simultaneously. Instead of dedicated power supplies for each controller, a single power supply unit can provide power to multiple controllers, making the power system multi-functional. This universality reduces the total number of power supplies needed, thereby reducing weight and space while maintaining redundancy.
4Reliability
If power is interrupted to the single power bus in GA aircraft, then electrical components may not function, but adding redundant power sources increases weight and complexity
Solution Approach 1:
The patent implements universal power supplies that can serve multiple flight control computers simultaneously. Instead of dedicated power supplies for each controller, a single power supply unit can provide power to multiple controllers, making the power system multi-functional. This universality reduces the total number of power supplies needed, thereby reducing weight and space while maintaining redundancy.
Solution Approach 2:
The patent incorporates monitoring systems that detect power bus interruptions and automatically switch between power sources. The system continuously monitors the status of the primary power bus and, upon detecting a failure, automatically transitions to alternative power sources such as backup batteries or ground power units. This feedback mechanism ensures continuous operation without requiring complex manual intervention or over-engineered static redundancy.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution provides a reliable and redundant fly-by-wire system for small GA aircraft, ensuring continued operation even in case of power disruptions or processor failures, while also reducing weight, cost, and complexity compared to traditional redundancy systems.
Implementation Method 1
Each flight control computer may comprise a backup battery. In the event of a power disruption from the primary power source, such as a generator and primary battery, the backup battery may power the flight control computer and all actuators.
Data Source
AI summary
A universal vehicle control router for fly-by-wire aircraft may include multiple vehicle control computers, such as flight control computers. Each flight control computer may be part of an independent channel that provides instructions to multiple actuators to control multiple vehicle components. Each channel is a distinct pathway capable of delivering a system function, such as moving an actuator. Each flight control computer may include a fully analyzable and testable voter (FAT voter). In the event of a failure to one of the flight control computers, the FAT voters may cause the failing flight control computer to be ignored or shut off power. Each flight control computer may comprise a backup battery. In the event of a power disruption from the primary power source, such as a generator and primary battery, the backup battery may power the flight control computer and all actuators.