Fly-By-Wire Control Router Redundancy for Small Aircraft
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Solution Overview
Problem
Small general aviation aircraft lack the space, power, and cost efficiency to implement redundancy systems for fly-by-wire systems, which are essential for ensuring safe operation in case of power loss or component failure, as they do not have the resources to support full fly-by-wire systems like larger commercial aircraft.
Innovation Solution
A universal vehicle control router system with multiple flight control computers, each with a fully analyzable and testable voter, and backup batteries, is designed to provide redundant control pathways and power, allowing for self-assessment and validation of actuator instructions, ensuring continued operation even in case of primary power disruption or component failure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If redundancy systems are implemented in small GA aircraft, then safety and reliability are improved, but weight, space, and cost increase
Solution Approach 1:
Multiple flight control computers are integrated into a single rack-mounted unit, combining redundant components in a compact configuration that provides full redundancy while minimizing weight and space compared to distributed arrangements
Solution Approach 2:
The flight control computer system is designed with universal interfaces and a unified control architecture that allows a single integrated unit to perform multiple functions previously requiring separate systems, reducing overall system weight while maintaining safety
2Reliability
If redundancy systems are implemented in small GA aircraft, then safety and reliability are improved, but device complexity increases
Solution Approach 1:
The patent integrates multiple flight control computers into a single rack-mounted unit with unified power distribution and control logic, reducing the number of separate systems and interfaces that pilots must manage, thereby decreasing operational complexity while maintaining full redundancy
3Reliability
If redundancy systems are implemented in small GA aircraft, then safety and reliability are improved, but cost increases
Solution Approach 1:
By consolidating redundant flight control computers into a single integrated rack-mounted unit, the patent reduces manufacturing costs through simplified assembly, reduced wiring harness requirements, and lower installation complexity compared to distributed redundant systems
Solution Approach 2:
The integrated flight control computer system uses universal components and standardized interfaces that can be manufactured and maintained more economically than specialized redundant systems, reducing overall cost while providing full safety redundancy
4Extent of automation
If full fly-by-wire systems are implemented without mechanical manual reversion, then automation is improved, but loss of information and control capability worsens during power failure
Solution Approach 1:
The system includes a backup battery that is pre-charged and automatically activates upon detection of primary power failure, ensuring continuous operation of the fly-by-wire system without requiring mechanical reversion or loss of control capability
Solution Approach 2:
The backup battery serves as an intermediary power source between the primary power system and the flight control computers, maintaining electrical power to the fly-by-wire system during primary power failures and preventing loss of control capability
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
This solution enhances vehicle safety by enabling autonomous or augmented control modes without relying on direct human intervention, reduces training requirements for pilots, and decreases the overall mass and cost of the system by integrating redundant components within a single housing, allowing for persistent operation during power failures.
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 small 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.