Aircraft Wing Twist Correction via Laser Beam Detection
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Solution Overview
Problem
Aircraft wings experience unwanted drag due to bending and twisting during flight, leading to increased fuel consumption and operational costs, particularly in adverse weather conditions where optical detection methods like cameras are impaired.
Innovation Solution
A system utilizing laser beams and reflective targets on the wing and fuselage to detect and correct wing deflection and twist by emitting laser beams from the fuselage to reflective surfaces on the wing, with sensors and gimbals adjusting the beam alignment to monitor and adjust for optimal wing configuration, reducing drag and fuel consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If optical detection methods (cameras) are used to monitor wing configuration, then real-time observation is achieved, but detection performance deteriorates in adverse weather conditions and poor light
Solution Approach 1:
The patent replaces optical detection systems (cameras) with a laser-based detection system. The laser beam tracks the wing structure directly, and sensors detect the position of the laser spot on the wing to determine wing configuration. This mechanical/optical substitution eliminates dependence on ambient light conditions and weather, providing reliable detection in all environments.
Solution Approach 2:
The patent introduces a laser beam as an intermediary between the detection system and the wing structure. The laser beam serves as a stable reference that reflects off retroreflective targets on the wing, allowing precise measurement of wing position and orientation without being affected by weather or light conditions.
2Object-generated harmful factors
If wing flexibility is maintained for aerodynamic performance, then drag reduction is achieved, but unwanted twisting and bending occur during flight
Solution Approach 1:
The patent implements a feedback control system where sensors continuously monitor the wing configuration by detecting laser spot position. This data is fed back to actuators that apply corrective forces to twist control surfaces, actively counteracting unwanted wing twisting and bending to maintain optimal aerodynamic configuration throughout flight.
Solution Approach 2:
The patent employs dynamic control of wing twist through actuators that adjust control surfaces in real-time based on flight conditions. This allows the wing to adapt its configuration dynamically, maintaining stability and reducing drag during different phases of flight while preserving the necessary flexibility for aerodynamic performance.
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 monitors and corrects wing deflection and twist, reducing drag and fuel consumption, and maintaining optimal operational performance even in adverse weather conditions.
Implementation Method 1
A system utilizing laser beams and reflective targets on the wing and fuselage to detect and correct wing deflection and twist by emitting laser beams from the fuselage to reflective surfaces on the wing
Data Source
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AI summary
A system which includes a first light beam locating sensor associated with a first position to be located on a wing of an aircraft. The first light beam locating sensor senses a first light beam at an identifiable position on the first light beam locating sensor. A processor is configured to receive a first signal from the first light beam locating sensor wherein the first signal includes a first identifiable position on the first light beam locating sensor. The processor is configured to determine a location of the first position on the wing and perform a first comparison of the location of the first position on the wing to a predetermined analyzed location of the first position on the wing.