Aircraft Lighting System With Segmented Laser Generator
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Solution Overview
Problem
Aircraft rotorcraft headlights lack the ability to generate an orientable light beam with adjustable geometry and power, resulting in significant aerodynamic drag, weight, and electromagnetic interference due to bulky projectors and large electrical installations.
Innovation Solution
A lighting system featuring a centralized light generator with multiple laser diodes emitting beams of different wavelengths, combined and processed to produce a high-power, adjustable light beam transmitted to a compact optical head outside the fuselage, which uses a photovoltaic system to generate electricity for a motor, allowing for geometric adjustment and reduced aerodynamic drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Illumination intensity
If a bulky projector is used to generate high-power light beam, then the light output is improved, but the aerodynamic drag and weight increase significantly
Solution Approach 1:
The system divides the light generation function into two separate components: a centralized light generator containing the bulky laser diodes and optical components, and a compact optical head containing only the necessary optical elements. This segmentation allows the heavy and bulky components to be located in the fuselage where they do not affect aerodynamic performance, while the compact optical head mounted on the aircraft skin maintains low drag.
Solution Approach 2:
The invention extracts the light-generating components (laser diodes, optical components) from the optical head and relocates them to a centralized light generator in the fuselage. Only the optical elements are retained in the compact optical head, significantly reducing its size and weight, thereby minimizing aerodynamic drag while maintaining high light output capability.
2Illumination intensity
If a bulky projector is used to generate high-power light beam, then the light output is improved, but the weight increases significantly
Solution Approach 1:
The system divides the light generation function into two separate components: a centralized light generator containing the bulky laser diodes and optical components, and a compact optical head containing only the necessary optical elements. This segmentation allows the heavy and bulky components to be located in the fuselage where they do not affect aerodynamic performance, while the compact optical head mounted on the aircraft skin maintains low drag.
Solution Approach 2:
The invention extracts the light-generating components (laser diodes, optical components) from the optical head and relocates them to a centralized light generator in the fuselage. Only the optical elements are retained in the compact optical head, significantly reducing its size and weight, thereby minimizing aerodynamic drag while maintaining high light output capability.
3Illumination intensity
If large electrical installations are used to power the searchlight, then the light output is improved, but electromagnetic interference increases
Solution Approach 1:
The invention extracts the electrical power supply and associated wiring from the optical head and relocates them to the centralized light generator in the fuselage. This separation minimizes the amount of electrical wiring in the aircraft structure, thereby reducing electromagnetic interference with other aircraft equipment while maintaining the ability to deliver high power to the light-generating components.
4Device complexity
If a fixed geometry light beam is used, then the device complexity is reduced, but the adaptability to different illumination requirements is worsened
Solution Approach 1:
The system incorporates dynamic optical elements in the compact optical head, such as movable mirrors or adjustable optical components, that allow the light beam geometry to be dynamically adjusted according to different illumination requirements. This dynamic capability provides versatility for various search and signaling operations without requiring multiple fixed optical 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
The system achieves a high-power, adjustable light beam with reduced aerodynamic drag and weight, eliminating the need for bulky projectors and large electrical installations, while minimizing electromagnetic interference.
Implementation Method 1
a light generator (30) arranged inside the fuselage, the light generator comprising a plurality of light sources which includes at least two laser diodes (35) each emitting a light beam called 'initial beam'
Implementation Method 2
the main optical head including a photovoltaic system illuminated by the reflected beam to generate an electric current supplying a battery of the main projector
Data Source
Figure 1~4
Figure 3
AI summary
The present invention relates to an aircraft (1) equipped with a lighting system (10) comprising a main projector (20) (21) located outside (EXT) a fuselage (2). The lighting system (10) includes, within the fuselage, at least one light generator (30) comprising a plurality of laser diodes (35), at least two laser diodes emitting two beams of different wavelengths, and an internal light combiner (41) generating, from said initial beams (100), a light beam (101) directed towards the main projector (21). A modulation system (150) modulates the emission frequency of said light beam (101). The main projector (21) comprises a main optical head including a mirror (155), a photovoltaic system (160), a battery (195), and an optical processing system.A motor (86) is connected to said optical head, said motor (86) being powered and controlled according to the electric current generated by the photovoltaic system.