Folding Wing Latch Pin Actuator Failure Detection
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Solution Overview
Problem
Conventional folding wing tip designs face challenges in detecting primary lock failures in branched driveline systems, leading to undetectable failure modes and increased maintenance downtime, which affects the operational efficiency and flexibility of aircraft in fitting within existing airport infrastructure.
Innovation Solution
A folding wing system with a sensor system that includes a wing tip position sensor, angle gearbox position sensor, secondary lock drive line position sensor, and secondary lock actuator sensor to indirectly detect primary lock failures, combined with a secondary lock crank arm assembly featuring a quick release mechanism and spring bias for enhanced operation and maintenance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional folding wing tip designs are used, then the wing can be folded to fit within airport infrastructure, but primary lock failures cannot be detected leading to increased maintenance downtime
Solution Approach 1:
The patent implements a feedback mechanism by installing sensors (position sensors, load sensors, temperature sensors) that continuously monitor the state of latch pin actuators and wing tip position, providing real-time feedback to the flight management system to detect failures immediately
Solution Approach 2:
The patent introduces intermediary sensing components (position sensors, load sensors, temperature sensors) that mediate between the mechanical locking system and the flight management system, enabling indirect detection of primary lock failures through monitoring secondary parameters
2Adaptability or versatility
If folding wing tips are used to reduce span for airport infrastructure, then aircraft can operate at more airports, but the system complexity increases with branched driveline systems
Solution Approach 1:
The patent segments the driveline system into multiple independent latch pin actuators, each with its own sensing system, allowing individual monitoring and failure isolation without affecting the entire wing folding system
Solution Approach 2:
The patent implements a dynamic monitoring system that adapts its sensing and detection capabilities based on the operational state of the wing folding mechanism, enabling real-time adjustment to system conditions
3Reliability
If multiple sensors are added to detect primary lock failures, then detection capability improves, but device complexity increases
Solution Approach 1:
The patent designs multi-functional sensors that simultaneously monitor multiple parameters (position, load, temperature) using single sensor units, reducing the overall number of components while maintaining comprehensive monitoring capability
Solution Approach 2:
The patent combines multiple sensing functions into integrated sensor assemblies that monitor latch pin actuator status, wing tip position, and environmental conditions simultaneously, consolidating what would otherwise require separate sensing systems
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 system effectively detects primary lock failures and reduces maintenance downtime by allowing for quicker fault isolation and operation within various airport infrastructure constraints, enhancing aircraft flexibility and fuel efficiency.
Implementation Method 1
The spring is biased to lock the primary lock
Implementation Method 2
The piston is configured to unlock the primary lock
Data Source
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AI summary
A latch pin actuator (600) comprises a primary lock (702) having a curvature (712) configured to allow a latch pin (602) into a housing (604) when the primary lock (702) is in an unlocked position, and wherein the primary lock (702) is configured to prevent the latch pin (602) from entering a housing (604) in a locked position, by facing the curvature (712) in a different direction in the locked position, a spring (706) and a piston (710). The primary lock (702) is attached to a primary lock cam (608) and has a notch (716) as a fracture evident geometry. The spring (706) is biased to lock the primary lock (702). The piston (710) is configured to unlock the primary lock (702).