Aircraft Navigation Light with Shared Optical Redundancy
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Solution Overview
Problem
Existing aircraft navigation light systems lack redundancy, leading to high failure probabilities and inefficient use of space and resources, as they often require multiple optical systems and power supplies for redundancy, increasing costs and complexity.
Innovation Solution
An aircraft navigation light system with integrated redundancy, featuring two independent light sources and a common optical system, where each light source can compensate for the other's failure, reducing the need for duplicate optical systems and power supplies, and incorporating a near-end-of-life detector to ensure continuous minimum light output.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple optical systems and power supplies are used for redundancy, then reliability is improved, but device complexity and space requirements increase
Solution Approach 1:
The patent merges multiple light sources into a single optical system. Specifically, it uses two independent light sources (LEDs) that share a common optical system including a single lens, reflector, and housing. This consolidation maintains redundancy for reliability while reducing the number of separate optical assemblies, thereby decreasing device complexity and space requirements compared to using multiple complete optical systems.
Solution Approach 2:
The common optical system serves multiple functions: it shapes and directs light from either light source independently, and can accommodate both light sources simultaneously for enhanced redundancy. The single optical system is designed to be universal in handling light from different sources, eliminating the need for duplicate optical components while maintaining reliable operation.
2Reliability
If multiple optical systems are used for redundancy, then reliability is improved, but space requirements increase
Solution Approach 1:
The patent consolidates two light sources into one shared optical system, significantly reducing the space required compared to installing two complete separate optical systems. The common lens, reflector, and housing structure are shared between both light sources, minimizing the overall footprint while maintaining redundancy capabilities.
3Reliability
If multiple complete navigation light systems are used for redundancy, then reliability is improved, but costs increase
Solution Approach 1:
The patent reduces costs by merging two light sources into a single optical system rather than installing two complete navigation light systems. This eliminates the need for duplicate optical components (lenses, reflectors, housings), reducing material costs, manufacturing complexity, and installation expenses while maintaining the redundancy needed for high reliability.
Solution Approach 2:
The common optical system is designed to universally handle light from either source, providing cost-effective redundancy. Instead of purchasing and installing two complete systems, the universal optical design allows one optical assembly to serve both light sources, significantly reducing overall system cost while maintaining reliable operation.
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 design provides a highly reliable navigation light system with reduced failure probability, lower costs, and minimized space requirements while maintaining the necessary redundancy, simplifying ancillary systems like wiring and ensuring compliance with regulatory light output standards.
Implementation Method 1
The light source provides light into the optical diffuser, which light is scattered and reflected internally and emitted only through the integral window
Implementation Method 2
The light source provides light into the optical diffuser, which light is scattered and reflected internally
Data Source
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AI summary
An aircraft navigation light (8; 9) with integrated redundancy having at least a selected minimum light output, comprises a first light source (81; 91); a second light source (82; 92); and a common optical element (84; 94), which is configured for shaping an output light intensity distribution (89; 99) of the aircraft navigation light (8; 9). The light emitted by each of the first light source (81; 91) and the second light source (82; 92) is modified by the common optical element (84; 94). Each of the first and second light sources (82; 92) has an individual light output capacity, wherein the individual light output capacity of each of the first and second light sources (82; 92) alone is sufficient for providing the selected minimum light output (89; 99) of the aircraft navigation light (8; 9).