Aircraft Warning Lamp Aerodynamic Cooling
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Solution Overview
Problem
Existing aircraft warning lamps with LED technology face challenges in achieving optimal aerodynamic shape while maintaining light emission requirements and heat management, leading to increased weight and size due to the need for large cooling systems and suboptimal aerodynamic properties.
Innovation Solution
A warning lamp design featuring a two-part light permeable cover with a cooling body integrated between the cover elements, allowing for aerodynamic shaping and efficient heat dissipation through airflow exposure, with the cooling body's surface forming part of the external contours and being thermally linked to the mounting element for enhanced heat removal.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a cooling body is integrated into the warning lamp housing, then heat management of LEDs is improved, but aerodynamic performance deteriorates due to increased drag
Solution Approach 1:
The cover is divided into a frontal cover element and a rear cover element with the cooling body positioned between them. This segmentation allows the cooling body to be integrated into the aerodynamic shape without compromising light emission areas, while the frontal and rear elements maintain streamlined profiles to reduce drag.
Solution Approach 2:
Different regions of the cover are assigned different functions: the frontal and rear cover elements are optimized for aerodynamic flow, while the cooling body is positioned in a region where it can dissipate heat effectively without interfering with light emission paths. The cooling body's surface forms part of the external contours, allowing localized heat dissipation while maintaining overall aerodynamic shape.
2Reliability
If LED lights are used instead of Xenon lamps, then service life and reliability are improved, but heat sensitivity and size requirements worsen
Solution Approach 1:
The cooling body is merged with the housing structure and integrated between the frontal and rear cover elements. This integration eliminates the need for separate, bulky cooling systems, as the cooling function is built into the existing housing architecture, thereby reducing overall size while maintaining effective heat management for the LEDs.
3Object-affected harmful factors
If the cover is made as a single aerodynamic shape, then aerodynamic performance is improved, but light emission requirements worsen
Solution Approach 1:
The cover is segmented into distinct functional zones: a frontal cover element for aerodynamic flow, a rear cover element for light emission, and a cooling body positioned between them. This segmentation allows each zone to be optimized for its specific function while maintaining overall aerodynamic integrity.
Solution Approach 2:
The cover elements are positioned asymmetrically relative to the cooling body, with the frontal cover element pointing in the direction of flight and the rear cover element pointing opposite to the direction of flight. This asymmetric arrangement allows the cooling body to be integrated into the aerodynamic shape while maintaining proper light emission directions required by aviation regulations.
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 design reduces weight and size compared to Xenon strobe lights, maintains compliance with light emission regulations, and enhances aerodynamic performance by allowing for the use of different materials for the cover elements and integrating light control features, while ensuring effective heat management and reduced likelihood of failures.
Implementation Method 1
a cooling body for the (at least one) LED, wherein the cooling body possesses a cooling surface that is exposed to the surrounding air when the housing is mounted on the aircraft
Implementation Method 2
the cooling body, with separation of the frontal cover element from the rear cover element, is arranged between the two, wherein its cooling surface is a part of the external contours of the housing cover
Implementation Method 3
the frontal cover area is formed by a frontal cover element which is made from a light permeable first material, the rear cover area is formed by a rear cover element which is made from a light permeable second material
Data Source
Figure 1
Figure 2
AI summary
The warning lamp for an aircraft is provided with a housing (10) which possesses a light permeable cover (12) that is exposed to the surrounding air when the housing is mounted on the aircraft, with a frontal cover area and a rear cover area, a mounting element (44) to fasten the cover to a lower part (14) of the housing (10), wherein one edge (41) of the cover (12) is covered by an edge of the mounting element (44) and protrudes from it, a lamp with at least one LED (42,46,58,60), which is arranged within an area that is covered by the cover (12), and a cooling body (18) for the at least one LED (42,46,58,60), wherein the cooling body (18) possesses a cooling surface (32) that is exposed to the surrounding air when the housing (10) is mounted on the aircraft. The frontal cover area is formed by a frontal cover element (22) which is made from a light permeable first materia!. The rear cover area is formed by a rear cover element (28), which is made from a light permeable second material. The cooling body (18), while separating the frontal cover element (22) from the rear cover element (28), is arranged between them, wherein its cooling surface (32) is a part of the external contours of the cover (12) of the housing (10) that is given by the frontal and rear cover elements (22,28) and possesses an upper region (38) as well as adjacent, opposing side areas (40).