Aircraft LED Light Control via Reference Aging Sensor
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Solution Overview
Problem
Aircraft LED light intensity decreases over time due to aging, and existing methods struggle to accurately simulate the operational and environmental conditions of LEDs, especially those subjected to maximum thermal stress, making it difficult to compensate for aging degradation without obstructing light emission or using limited space effectively.
Innovation Solution
A reference LED is used to simulate the thermal conditions of the most stressed LEDs, monitored by an optical sensor to control the entire aircraft light system, ensuring consistent light intensity by mimicking the thermal and operational conditions of the critical LEDs through thermal shielding or active heating, allowing for compensation of aging effects without obstructing the primary light path.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If an optical sensor is placed within the housing of the aircraft light to sense light intensity, then aging degradation can be detected, but the optical sensor causes shielding effects and reduced light yield
Solution Approach 1:
The optical sensor is extracted from the housing and relocated to an external position where it can detect light intensity without obstructing the LED light path. This allows the sensor to perform its measurement function while the housing maintains its full light transmission capability.
Solution Approach 2:
A reference LED is introduced as an intermediary element. Instead of directly sensing the aging of the operational LEDs, the system uses the reference LED (which experiences similar thermal conditions) and an external optical sensor to indirectly monitor aging effects, eliminating the need for internal sensors that would block light.
2Area of stationary object
If a reference LED is used to monitor aging, then space is saved, but the reference LED cannot represent the operational conditions of the primary LEDs
Solution Approach 1:
The reference LED is positioned to experience the same local thermal conditions as the operational LEDs, specifically the maximum thermal stress zone. By ensuring the reference LED is subject to identical thermal environments, it accurately replicates the aging conditions of the primary LEDs while being monitorable from external position.
3Measurement precision
If the optical sensor is placed close to the LED for accurate monitoring, then measurement precision improves, but the sensor obstructs the light emission path
Solution Approach 1:
The optical sensor is extracted from the internal housing space and positioned externally. This allows the sensor to maintain close proximity to the reference LED for accurate aging detection while being completely separate from the light emission path of the operational LEDs, eliminating any obstruction.
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 effectively maintains desired light intensity by accurately monitoring and compensating for aging degradation of the most stressed LEDs, ensuring consistent performance throughout the aircraft light's lifetime without obstructing the primary light emission or requiring placement of sensors in limited spaces.
Implementation Method 1
providing a reference LED located within or outside of the aircraft light
Implementation Method 2
observing the reference LED by means of an optical sensor for monitoring the optical aging behavior
Implementation Method 3
providing thermal conditions resulting in a thermal stress for the reference LED similar to the maximum thermal stress, wherein said thermal conditions are a simulation of the thermal conditions of the at least one LED
Data Source
Figure 1~4
AI summary
Described is a method for controlling an aircraft light (10) so as to emit a desired light intensity, wherein the aircraft light (10) comprises a plurality of LEDs (16, 20) and wherein each of the LEDs (16, 20) is subjected to thermal stress due to at least one of environmental conditions and operational conditions, at least one of the LEDs (20) or at least one group of the LEDs (16, 20) being subjected to a maximum thermal stress. The method comprises the steps of providing a reference LED (24) located within or outside of the aircraft light (10), providing thermal conditions resulting in a thermal stress for the reference LED (24) similar to the maximum thermal stress, and observing the reference LED (24) by means of an optical sensor (26) for monitoring the optical aging behavior of the reference LED (24) throughout its lifetime. For emitting a desired light intensity by the aircraft light (10), the plurality of LEDs (16,20) of the aircraft light (10) are controlled in accordance with the monitored aging behavior of the reference LED (24).