Automatic Deployable Flight Recorder Deployment Logic
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Solution Overview
Problem
Current flight recorders face challenges in timely and efficient deployment after a catastrophic aviation event, particularly in extreme crash conditions, leading to potential false-positive deployments and safety risks, and the delay in locating them can hinder investigation and pose risks to other aircraft.
Innovation Solution
An automatic deployable flight recorder system with multiple crash sensors and a recorder release unit that adjusts deployment criteria based on flight conditions, using sensor diversity, redundancy, and voting logic to minimize false deployments while ensuring reliable deployment in catastrophic events.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the flight recorder is designed to deploy at the slightest possibility of a crash, then the deployment reliability is improved, but false-positive deployments increase causing safety risks
Solution Approach 1:
The patent applies dynamics by making the deployment sensitivity adjustable based on flight conditions. The system transitions from a static deployment threshold to a dynamic one that adapts to the current flight state, allowing the recorder to deploy reliably in actual crashes while avoiding false positives during normal operations or minor disturbances.
Solution Approach 2:
The patent changes the parameter of deployment sensitivity based on flight conditions. By monitoring parameters such as altitude, speed, and flight phase, the system adjusts the deployment threshold dynamically, ensuring high reliability in catastrophic events while preventing unintended deployment during routine flight variations.
2Object-affected harmful factors
If multiple crash sensors and voting logic are used, then false-positive deployments are reduced, but device complexity increases
Solution Approach 1:
The patent segments the crash detection function into multiple independent sensors distributed at different locations on the aircraft. Each sensor independently monitors for crash conditions, and the voting logic combines their outputs. This segmentation approach reduces false positives by requiring consensus among multiple sensors while keeping each individual sensor relatively simple.
Solution Approach 2:
The patent makes the sensor system multi-functional by using the same sensor array for both crash detection and false-positive prevention. The voting logic serves dual purposes: confirming actual crashes through multiple sensor agreement and filtering out false alarms when sensors disagree or show inconsistent patterns.
3Object-affected harmful factors
If deployment criteria are adjusted based on flight conditions, then false-positive deployments are minimized, but detection response time may be delayed
Solution Approach 1:
The patent applies preliminary action by pre-establishing deployment criteria for different flight conditions before a crash event occurs. The system continuously monitors flight parameters and pre-loads appropriate deployment thresholds based on the current flight phase, ensuring that when a crash occurs, the system can immediately apply the correct criteria without calculation delays.
Solution Approach 2:
The patent uses feedback by continuously monitoring flight conditions and adjusting deployment criteria in real-time. The system receives feedback from flight sensors, compares current conditions against predefined thresholds, and dynamically adjusts the deployment sensitivity accordingly, maintaining both speed and accuracy in crash detection.
Data Source
AI summary
Embodiments of the invention provides an automatic deployable flight recorder (ADFR) system that includes a deployable fight recorder, a plurality of crash sensors, and a recorder release unit. The recorder release unit is communicatively coupled to the deployable fight recorder and the plurality of crash sensors, and is configured to initiate deployment of the deployable flight data recorder from an aircraft when a deployment criteria that is adjusted based on a flight condition of the aircraft is satisfied.