Automatic Display Unit Backup via Control Transfer Components
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Solution Overview
Problem
Flight management systems in aircraft cockpits face disruptions due to failures in display units, requiring manual intervention for backup system switching, which can lead to operational inefficiencies and safety risks during critical flight operations.
Innovation Solution
A system comprising a processor and memory that automatically detects failures in display units and transfers control between redundant display units without manual input, utilizing a control transfer component and failure indication mechanism to ensure seamless operation and data rendering across primary and secondary systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If manual intervention is used for backup system switching, then system complexity is reduced, but operational efficiency and safety are compromised due to delays during critical failures
Solution Approach 1:
The system performs preliminary configuration of backup controllers and failover protocols before failures occur. Controllers are pre-designated as primary or backup, and automatic failover logic is established in advance, enabling immediate response without manual intervention when failures occur
Solution Approach 2:
The failover system operates autonomously by self-detecting controller failures and automatically transferring control to backup controllers without requiring pilot input. The system monitors its own operational status and initiates recovery actions independently, improving response time during critical failures
2Loss of time
If automatic control transfer is implemented, then response time to failures is improved, but system complexity increases due to additional monitoring and transfer mechanisms
Solution Approach 1:
Backup controllers are designed with multi-functionality, capable of operating as standby units during normal conditions and automatically assuming primary functions when failures occur. This universal design reduces the need for separate dedicated backup systems, managing complexity while enabling rapid automatic failover
Solution Approach 2:
The system implements continuous monitoring of controller operational status with automatic feedback loops that detect failures and trigger failover actions. This closed-loop control enables rapid automatic response to failures while using standardized monitoring protocols to manage system complexity
3Reliability
If redundant display units are deployed, then system reliability is improved, but operational complexity increases due to manual switching requirements
Solution Approach 1:
The redundant display system automatically manages failover between primary and backup controllers without requiring pilot intervention. The system self-monitors operational status and autonomously transfers control to redundant units when failures occur, maintaining ease of operation while ensuring high reliability through continuous redundancy
4Reliability
If automatic failover mechanisms are added, then flight safety is enhanced, but device complexity increases due to additional control transfer components
Solution Approach 1:
Controllers are designed with universal capabilities to function as either primary or backup units depending on operational needs. This multi-functionality allows the same hardware to serve multiple roles, enhancing flight safety through redundancy while avoiding the complexity of separate dedicated backup systems
Solution Approach 2:
Failover protocols and controller designations are established in advance before failures occur. The system pre-configures backup controllers and failover logic, enabling immediate automatic activation when needed, thereby enhancing flight safety without requiring complex real-time decision-making mechanisms
Data Source
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AI summary
Automatic display unit backup during failures of one more display units through the utilization of graphic user interface objects defined for control transfer and reversion after resolution of the failures is provided herein. A system 600 can comprise a memory 110 operatively coupled to a processor 112 that executes stored executable components comprising a first controller 602, a second controller 604, and a failure indication component 104 that provides a first notification based on a first detection of a first failure at the second controller 604, and a second notification based on a second detection of a second failure at the first controller 602. Further, the executable components can comprise a control transfer component 108 that automatically transfers control of a second display unit 602 from the second controller 604 to the first controller 602 based on the first notification.