Aircraft Fuselage Deformation Monitoring for Status Detection
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Solution Overview
Problem
Current methods for distinguishing between an aircraft's in-flight and on-ground status, such as using signals from engines and landing gear, require extensive wiring and are complex, necessitating a more simplified approach.
Innovation Solution
Monitoring the deformation of a fuselage section using resistance strain gauges or optical sensors to generate a status signal indicating whether the aircraft is in flight or on the ground, which can control warning lights and prevent inadvertent door openings or slide deployments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If signals from engines and landing gear are used to determine aircraft status, then the status information can be obtained, but extensive wiring and complex system integration are required
Solution Approach 1:
The patent divides the aircraft fuselage into multiple sections, each equipped with independent deformation sensors. Each door system can independently monitor the status of its adjacent fuselage section, eliminating the need for centralized signal distribution through extensive wiring. This segmentation allows local determination of aircraft status without relying on complex centralised wiring systems.
Solution Approach 2:
The patent introduces fuselage deformation as an intermediary physical phenomenon to indicate aircraft status. Instead of directly using engine and landing gear signals, the system monitors the deformation of the fuselage caused by pressure differential, which serves as a reliable intermediary indicator of whether the aircraft is in flight or on ground, thereby avoiding complex wiring while maintaining signal reliability.
2Measurement precision
If differential pressure switch signals are used to indicate aircraft status, then accurate status information is obtained, but considerable wiring including connectors is required to transmit signals to all doors
Solution Approach 1:
The patent segments the aircraft into multiple independent monitoring zones, with each door system independently monitoring the deformation of its adjacent fuselage section. This eliminates the need for a single centralized pressure switch signal to be distributed through long wiring to all doors, as each door locally determines status from local fuselage deformation.
Solution Approach 2:
Each door system performs self-determination of aircraft status by monitoring the deformation of its own adjacent fuselage section. This self-service approach eliminates the need for centralized signal distribution, as each system independently obtains the status information it needs without relying on wiring from central sources.
3Stability of the object's composition
If centralized status signals are used for door control, then coordinated control is achieved, but the wiring required between fuselage and door systems is extensive
Solution Approach 1:
The patent divides the door control system into independent modular units, each capable of autonomously determining aircraft status from local fuselage deformation. This segmentation maintains system coordination through uniform deformation monitoring while eliminating the need for extensive centralized wiring to distribute status signals to all door 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
This method reduces wiring requirements and allows for localized control of warning lights, enhancing safety by accurately determining the aircraft's status without relying on central signals, thereby minimizing the risk of inadvertent events.
Implementation Method 1
one or more resistance strain gauges mounted on a flexible board spaced from each other, which board is fixed to said fuselage section
Implementation Method 2
one or more resistance strain gauges or by means of at least one optical sensor
Data Source
AI summary
The invention relates to a method of distinguishing between in-flight status and on-ground status of an aircraft, wherein the interior of a fuselage is pressurized in flight status. The deformation of a fuselage section is monitored, and a signal is generated dependent on such deformation.