CN118092035A - Self-adaptive illumination control system and control method for aircraft cockpit - Google Patents
Self-adaptive illumination control system and control method for aircraft cockpit Download PDFInfo
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- CN118092035A CN118092035A CN202410424889.XA CN202410424889A CN118092035A CN 118092035 A CN118092035 A CN 118092035A CN 202410424889 A CN202410424889 A CN 202410424889A CN 118092035 A CN118092035 A CN 118092035A
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- 238000005286 illumination Methods 0.000 title claims abstract description 104
- 238000000034 method Methods 0.000 title claims abstract description 50
- 230000003044 adaptive effect Effects 0.000 claims abstract description 43
- 238000002834 transmittance Methods 0.000 claims abstract description 20
- 238000013459 approach Methods 0.000 claims description 10
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- QGLKJKCYBOYXKC-UHFFFAOYSA-N nonaoxidotritungsten Chemical compound O=[W]1(=O)O[W](=O)(=O)O[W](=O)(=O)O1 QGLKJKCYBOYXKC-UHFFFAOYSA-N 0.000 claims description 2
- 229910001930 tungsten oxide Inorganic materials 0.000 claims description 2
- 230000004313 glare Effects 0.000 abstract description 14
- 230000004438 eyesight Effects 0.000 abstract description 10
- 230000005855 radiation Effects 0.000 description 8
- 230000000694 effects Effects 0.000 description 7
- 238000009413 insulation Methods 0.000 description 7
- 230000037072 sun protection Effects 0.000 description 7
- 230000000903 blocking effect Effects 0.000 description 5
- 230000036541 health Effects 0.000 description 4
- 230000004630 mental health Effects 0.000 description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 230000006750 UV protection Effects 0.000 description 2
- 230000001351 cycling effect Effects 0.000 description 2
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- 230000009286 beneficial effect Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
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- G—PHYSICS
- G02—OPTICS
- G02F—OPTICAL DEVICES OR ARRANGEMENTS FOR THE CONTROL OF LIGHT BY MODIFICATION OF THE OPTICAL PROPERTIES OF THE MEDIA OF THE ELEMENTS INVOLVED THEREIN; NON-LINEAR OPTICS; FREQUENCY-CHANGING OF LIGHT; OPTICAL LOGIC ELEMENTS; OPTICAL ANALOGUE/DIGITAL CONVERTERS
- G02F1/00—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics
- G02F1/01—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour
- G02F1/13—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour based on liquid crystals, e.g. single liquid crystal display cells
- G02F1/1313—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour based on liquid crystals, e.g. single liquid crystal display cells specially adapted for a particular application
-
- G—PHYSICS
- G02—OPTICS
- G02F—OPTICAL DEVICES OR ARRANGEMENTS FOR THE CONTROL OF LIGHT BY MODIFICATION OF THE OPTICAL PROPERTIES OF THE MEDIA OF THE ELEMENTS INVOLVED THEREIN; NON-LINEAR OPTICS; FREQUENCY-CHANGING OF LIGHT; OPTICAL LOGIC ELEMENTS; OPTICAL ANALOGUE/DIGITAL CONVERTERS
- G02F1/00—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics
- G02F1/01—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour
- G02F1/13—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour based on liquid crystals, e.g. single liquid crystal display cells
- G02F1/133—Constructional arrangements; Operation of liquid crystal cells; Circuit arrangements
- G02F1/13306—Circuit arrangements or driving methods for the control of single liquid crystal cells
- G02F1/13318—Circuits comprising a photodetector
-
- G—PHYSICS
- G02—OPTICS
- G02F—OPTICAL DEVICES OR ARRANGEMENTS FOR THE CONTROL OF LIGHT BY MODIFICATION OF THE OPTICAL PROPERTIES OF THE MEDIA OF THE ELEMENTS INVOLVED THEREIN; NON-LINEAR OPTICS; FREQUENCY-CHANGING OF LIGHT; OPTICAL LOGIC ELEMENTS; OPTICAL ANALOGUE/DIGITAL CONVERTERS
- G02F1/00—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics
- G02F1/01—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour
- G02F1/15—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour based on an electrochromic effect
- G02F1/153—Constructional details
- G02F1/1533—Constructional details structural features not otherwise provided for
-
- G—PHYSICS
- G02—OPTICS
- G02F—OPTICAL DEVICES OR ARRANGEMENTS FOR THE CONTROL OF LIGHT BY MODIFICATION OF THE OPTICAL PROPERTIES OF THE MEDIA OF THE ELEMENTS INVOLVED THEREIN; NON-LINEAR OPTICS; FREQUENCY-CHANGING OF LIGHT; OPTICAL LOGIC ELEMENTS; OPTICAL ANALOGUE/DIGITAL CONVERTERS
- G02F1/00—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics
- G02F1/01—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour
- G02F1/15—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics for the control of the intensity, phase, polarisation or colour based on an electrochromic effect
- G02F1/163—Operation of electrochromic cells, e.g. electrodeposition cells; Circuit arrangements therefor
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- Physics & Mathematics (AREA)
- Nonlinear Science (AREA)
- General Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Chemical & Material Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Mathematical Physics (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Electrochromic Elements, Electrophoresis, Or Variable Reflection Or Absorption Elements (AREA)
Abstract
The invention relates to an adaptive lighting control system for an aircraft cockpit, comprising: a windshield assembly comprising a windshield and an electrochromic film attached to the windshield and adjusting the light transmittance of the windshield assembly based on the magnitude of a voltage supplied to the electrochromic film; an input assembly for providing a desired illumination intensity for the cockpit; and a control assembly connected to the electrochromic film of the windshield assembly and the input assembly and adjusting the magnitude of the voltage supplied to the electrochromic film based on the intensity of illumination required within the cockpit of the aircraft during a full flight phase of the aircraft. The control system can ensure that the aircraft has clear external vision in the cockpit in the full flight stage, and realize that the cockpit external vision has good cockpit vision in various running scenes, so that a pilot can safely operate the aircraft in a scene without glare. In addition, the invention also relates to a self-adaptive illumination control method.
Description
Technical Field
The invention belongs to an external glare prevention self-adaptive control technology for an aircraft cockpit, and relates to a self-adaptive illumination control system for the aircraft cockpit. In addition, the invention also relates to a self-adaptive illumination control method for the aircraft cockpit.
Background
The outside view of a conventional civil aircraft cockpit originates mainly from conventional windshields, which normally only consider light transmission and load bearing functions. However, in some special operating scenarios, for example, in environments such as ambient glare, ambient glare tends to create glare and intense radiation to the pilot's field of view. For example, the view of the cabin of a civil aircraft may be greatly affected in the scenes of take-off, cruising, landing, etc., or in different lighting environments such as daytime, night, etc.
At the same time, civil aircraft often require a sufficiently large windscreen in order to guarantee a wide external view. However, the larger the windshield, the more harmful light may be transmitted. For example, under the high temperature environment experienced during the crew floor preparation phase, external glare can cause overheating within the cockpit. Common methods of insulation may for example use sun protection devices (such as sunshades, sun shades, etc.). The operation or use of these devices is cumbersome, requiring a corresponding storage location to be reserved in the cockpit for storage when not in use, and the storage location also needs to be readily accessible. However, it is difficult to find a reasonable storage location or to occupy valuable space available in an in-flight cabin space environment.
Studies have shown that conventional aircraft windshields do not completely block the ultraviolet radiation emitted by the sun, and pilots are exposed to long wave ultraviolet radiation at a height of 9144 meters (about 30000 feet) corresponding to 20 minutes of sun bed per 1 hour of flight, which can have some impact on the pilot's physical health.
It is therefore particularly important to provide an illumination control apparatus that is capable of providing a sufficiently clear exterior view to the pilot, yet effectively providing thermal insulation, sun protection, and/or ultraviolet protection, and in particular, an adaptive illumination control system for an aircraft cockpit that overcomes one or more of the shortcomings of the prior art.
Disclosure of Invention
The invention aims to enable the civil aircraft to provide comfortable cockpit vision for pilots under different illumination running environments, avoid interference of glare and reflection during flight of the pilots, and ensure flight safety. In addition, in order to promote the cockpit internal comfort under severe weather environments such as summer high temperature, high altitude radiation, provide a cockpit self-adaptation illumination system in the full stage of flight, carry out self-adaptation control to the illumination that gets into the cockpit under the different illumination environment, realize always having clear external view in the cockpit, avoid harmful glare reflection, thermal-insulated sun-proof, anti ultraviolet, provide comfortable illumination environment for the flight unit to guarantee flight safety, promote flight comfort, keep pilot's physical and mental health.
According to one aspect of the present invention, an adaptive lighting control system for an aircraft cockpit is presented, which may include: a windshield assembly comprising a windshield and an electrochromic film attached to the windshield and adjusting the light transmittance of the windshield assembly based on the magnitude of a voltage supplied to the electrochromic film; the input assembly is used for providing illumination intensity required by the cockpit; and a control assembly connected to the electrochromic film of the windshield assembly and the input assembly and adjusting the magnitude of the voltage supplied to the electrochromic film based on the intensity of illumination required within the cockpit of the aircraft during a full flight phase of the aircraft.
The self-adaptive illumination control technology can ensure that the cockpit has clear external vision under the full flight phases of taxiing, taking off, cruising, approaching, descending, landing and the like of the aircraft without increasing extra workload of the pilot, and realizes that the cockpit external vision has good cockpit vision under various running scenes such as daytime, night and the like, so that the pilot can safely operate the aircraft under the scene without glare. Meanwhile, the functions of heat insulation, sun protection and ultraviolet radiation prevention in the cockpit are taken into consideration, and the physical and mental health of pilots is protected. The adaptive lighting control technique is capable of acting on the entire flight envelope of the aircraft, i.e., during the full flight phases of taxiing, takeoff, cycling, approach, descent, landing, etc., of the aircraft.
According to the above aspect of the present invention, preferably, the input assembly may include: the outside-cockpit illumination detection equipment is used for acquiring illumination intensity, temperature and/or ultraviolet intensity of the outside environment of the cockpit; the airborne core network is used for acquiring the current flight phase and the current flight speed; and a cockpit lighting demand table for storing different lighting intensity demands according to different flight phases during the full flight phase.
The self-adaptive illumination control system provided by the invention can balance various external illumination, temperature, ultraviolet rays and other factors through the input assembly, and can provide the optimal illumination intensity requirement for a crew by integrating the current state of the aircraft.
According to the above aspect of the present invention, preferably, the input assembly may further include: the cockpit illumination demand knob is used for increasing and decreasing the cockpit illumination demand which is initially set. By this arrangement, the pilot is allowed to flexibly adjust the intensity of the illumination entering the cockpit through the windshield assembly due to individual perceived differences or physical conditions on the basis of adaptive adjustment.
According to the above aspect of the invention, preferably, in order to more precisely control the intensity of illumination entering the cockpit through the windshield assembly, the off-cockpit illumination detection means may include an illuminance sensor and/or an infrared camera and calculate the value of the current aircraft windshield illumination intensity maximum according to latitude and longitude, weather, environment, and attitude of the aircraft.
According to the above aspect of the present invention, preferably, the windshield may include a first windshield and a second windshield, and the electrochromic film is disposed between the first windshield and the second windshield. This arrangement can better protect the electrochromic film and can block fragments of the outer windshield or electrochromic film from entering the cockpit, thereby avoiding harm to the health of the pilot.
According to the above aspect of the present invention, preferably, the electrochromic film is a tungsten oxide electrochromic film. This arrangement allows a wide range of discolouration of the windshield assembly, easy restoration to a transparent colour, in particular allowing the electrochromic film to become transparent in the event of failure or non-powered, thus enhancing flight safety.
According to another aspect of the present invention, an adaptive illumination control method for an aircraft cockpit is presented, the adaptive illumination control method may include: providing an adaptive illumination control system, the adaptive illumination control system may include: a windshield assembly comprising a windshield and an electrochromic film attached to the windshield and adjusting the light transmittance of the windshield assembly based on the magnitude of a voltage supplied to the electrochromic film; the input assembly is used for providing illumination intensity required by the cockpit; and a control assembly connected to the electrochromic film of the windshield assembly and the input assembly and adjusting a magnitude of a voltage supplied to the electrochromic film based on a desired light intensity within the cockpit of the aircraft during a full flight phase of the aircraft, wherein the control assembly determines the desired light intensity of the cockpit based on the flight phase during the full flight phase.
The method comprehensively considers the external environment, the airplane state and the internal illumination requirement of the cockpit of the airplane in different flight stages, automatically adjusts the illumination intensity entering the cockpit of the airplane through the windshield assembly, and realizes that the cockpit external vision has good cockpit vision in various running scenes, so that a pilot can safely operate the airplane in a scene without glare.
According to the above aspect of the present invention, preferably, the flight phase may include: taxiing, takeoff, cruise, approach, descent and/or landing phases. Therefore, the method can ensure that the aircraft has clear external vision in the cockpit in the full flight stage, avoids harmful glare reflection, heat insulation, sun protection and ultraviolet protection, and provides a comfortable illumination environment for the flight unit, thereby ensuring flight safety, improving flight comfort and keeping physical and mental health of pilots.
According to the above aspect of the present invention, preferably, the control module makes the electrochromic film a light transmittance maximum state in any one of the following states: during the takeoff phase, approach phase or landing phase; or the illumination intensity outside the aircraft cockpit is less than or equal to the illumination intensity required by the aircraft cockpit.
The arrangement can ensure that enough illumination enters the cockpit in the key stages of the aircraft such as the take-off stage, the approach stage or the landing stage and the like and when the external illumination is weak, so that the pilot is prevented from being disturbed by glare and reflection, and further the flight safety is ensured.
According to the above aspect of the present invention, preferably, the control module makes the electrochromic film a light transmittance minimum state in any one of the following states: the aircraft is currently on the ground at a high temperature and the wheel speed is less than a predetermined threshold; or the aircraft is in cruise phase.
This arrangement can avoid direct sunlight to pilots, which may be dazzling during ground or cruise phases. In particular, under the ground environment with high temperature in summer, the arrangement can realize the heat insulation and sun protection effects; and under the environment of high altitude strong ultraviolet radiation, the ultraviolet blocking effect is realized.
The invention provides the adaptive illumination control system and the adaptive illumination control method for the full flight stage, which can actively control favorable light to enter the cockpit according to different stages and different external environments of the aircraft, eliminate or at least partially solve the problems in the prior art, increase the operation safety of the aircraft, improve the flight comfort of the pilot and ensure the physical health of the pilot.
In particular, the beneficial technical effects of the adaptive lighting control system according to the present invention may include, but are not limited to:
(1) Through cockpit self-adaptation illumination control system, for example, through control assembly, the outside illumination operational environment of real-time supervision civil aircraft cockpit and the flight phase of aircraft, the automatic illumination intensity that needs in the cockpit of adaptation regulation prevents harmful glare and reflection, promotes the security of aircraft operation. In particular, the heat insulation and sun protection technical effect can be realized in a high-temperature ground environment in summer; the technical effect of ultraviolet blocking can be realized in the environment of high-altitude strong ultraviolet radiation;
(2) In unexpected fault states (such as power failure, etc.), the self-adaptive illumination control system can be automatically switched to the state with the maximum transmittance, so that the minimum safety guarantee required by pilots is ensured;
(3) The self-adaptive illumination control system reserves an interface with pilot autonomous control authority, and can meet the requirement of individual difference of pilots on illumination on the basis of self-adaptive illumination adjustment.
Therefore, the self-adaptive illumination control system can meet the use requirement, overcomes the defects of the prior art and achieves the preset purpose.
Drawings
For a further clear description of the adaptive illumination control system according to the invention, the invention will be described in detail below with reference to the attached drawings and to the detailed description, wherein:
FIG. 1 shows a schematic block diagram of an adaptive lighting control system for an aircraft cockpit according to a non-limiting embodiment of the present invention; and
Fig. 2 shows a schematic flow chart of an adaptive lighting control method for an aircraft cockpit according to a non-limiting embodiment of the invention.
The figures are merely schematic and are not drawn to scale.
List of reference numerals in the figures and examples:
A 100-adaptive lighting control system, comprising:
A 10-windshield assembly comprising:
11-a windscreen comprising:
11A-a first windscreen;
11B-a second windscreen;
12-electrochromic film;
A 20-input assembly comprising:
21-an out-of-cabin illumination detection device;
22-an on-board core network;
23-a cockpit illumination demand meter;
24-a cockpit illumination demand knob;
30-control assembly.
Detailed Description
It is to be understood that the invention may assume various alternative orientations and step sequences, except where expressly specified to the contrary. It should be further understood that the specific devices illustrated in the accompanying drawings and described in the specification are simply exemplary embodiments of the inventive concepts disclosed and defined herein. Thus, unless explicitly stated otherwise, the particular orientations, directions, or other physical characteristics to which the various embodiments disclosed relate should not be considered limiting.
Fig. 1 shows a schematic block diagram of an adaptive lighting control system 100 for an aircraft cockpit according to a non-limiting embodiment of the invention.
As shown and as a non-limiting example, the adaptive illumination control system 100 may generally include: windshield assembly 10, input assembly 20, control assembly 30, and the like.
Windshield assembly 10 may include a windshield 11 and an electrochromic film 12. As a non-limiting example, windshield 11 may include a first windshield 11A and a second windshield 11B.
For example, the first windscreen 11A may be an outer windscreen and corresponding sensors and detection devices or the like may be provided on its outer surface, as described in more detail below. The second windshield 11B may be an inner layer of a loadable glass and may block fragments of the first windshield 11A from entering the cockpit and injuring the health of the pilot. Preferably, both the first windshield 11A and the second windshield 11B are transparent or colorless. It should be understood that the description "glass" as used herein should be construed in a broad sense, i.e., may include inorganic glass (glass having silica and other oxides as the main components, etc.), organic glass (glass made mainly of various plastics or polymers, etc.), combinations thereof, or the like.
Electrochromic film 12 may be attached to windshield 11 by various means of attachment such as bonding, crimping, or electrostatic adsorption, and the light transmittance of windshield assembly 10 may be adjusted, or the color of windshield assembly 10 may be adjusted, based on the magnitude of the voltage supplied to electrochromic film 12.
As a preferred embodiment, the electrochromic film 12 may be a tungsten oxide (WO 3) electrochromic film. The electrochromic film has wide color changing range, is easy to restore to transparent color, and is especially suitable for use in airplane cockpit. In addition, the electrochromic film can control the transmittance of illumination intensity by voltage, and the non-energized state is the maximum transmittance state, and the transmittance of illumination intensity changes with the change of voltage.
According to a non-limiting embodiment of the invention, electrochromic film 12 is disposed between first windshield 11A and second windshield 11B. In this way, the first windshield 11A and the second windshield 11B can protect the electrochromic film 12 from damage.
The input assembly 20 is used to provide the required illumination intensity for the cockpit. For example, the input assembly 20 may include: an off-cockpit illumination detection apparatus 21, an on-board core network 22, a cockpit illumination demand table 23, and the like.
The off-cabin lighting detection device 21 may be used to obtain the lighting intensity, temperature and/or ultraviolet intensity of the cabin external environment. As an example, the cockpit external light detection means 21 includes illuminance sensors and/or infrared cameras/cameras, etc. to obtain the light intensity, temperature, ultraviolet intensity of the civil aircraft running environment, and calculate the value of the current maximum aircraft windshield light intensity according to longitude and latitude, weather, environment, and attitude of the aircraft.
The on-board core network 22 may be used to obtain the current flight phase and speed, and the on-board core network 22 may be part of or connected to the core network of the aircraft.
The cockpit lighting requirement table 23 may be used to store different lighting intensity requirements according to different flight phases during a full flight phase. Additionally, the input assembly 20 may also include a cockpit lighting requirement knob 24 for increasing or decreasing the initial set cockpit lighting requirement.
The control assembly 30 may be connected to the electrochromic film 12 and the input assembly 20 of the windshield assembly 10 and adjust the magnitude of the voltage supplied to the electrochromic film 12 during the full flight phase of the aircraft based on the intensity of illumination required within the cockpit of the aircraft.
For example, the control assembly 30 may collect the illumination signal outside the cockpit of the aircraft, the temperature, the ultraviolet light, and the current flight phase of the aircraft and the illumination within the cockpit required by the pilot, then perform logic processing and judgment, and output the result signal of the logic processing and judgment to the electrochromic film 12, thereby performing illumination control to adjust the illumination intensity within the cockpit of the aircraft.
The term "full flight phase of an aircraft" as used herein may refer to the duration of the full flight phase of an aircraft from taxiing, takeoff, cycling, approach, descent, landing, etc., and the adaptive illumination control system 100 of the present invention may act on the entire flight envelope of an aircraft.
The present invention provides an adaptive illumination control system by utilizing a windshield assembly 10 with electrochromic films to monitor the external illumination environment (e.g., infrared and ultraviolet indicators) of the cockpit of a civil aircraft and the flight phase of the aircraft in real time, and automatically calculate the illumination intensity required by the crew in the cockpit.
The self-adaptive illumination control system provides comfortable cockpit external view which is adaptive to different illumination running environments and different flight phases for the flight unit. The self-adaptive illumination control system can avoid interference of glare and reflection on pilots in the flight process, and particularly avoids direct irradiation of dazzling sunlight on pilots in the key stage of take-off and landing. In addition, under the ground environment of high temperature in summer, the self-adaptive illumination control system can realize heat insulation and sun protection; and under the environment of high altitude strong ultraviolet radiation, the self-adaptive illumination control system can realize the effect of ultraviolet blocking.
Fig. 2 shows a schematic flow chart of an adaptive lighting control method 200 for an aircraft cockpit according to a non-limiting embodiment of the invention.
The adaptive illumination control method 200 shown in fig. 2 may be performed by the exemplary adaptive illumination control system 100 shown in fig. 1. Thus, the method may comprise first providing an adaptive illumination control system 100, and the adaptive illumination control system 100 may likewise comprise: windshield assembly 10, input assembly 20, control assembly 30, etc., wherein control assembly 30 may determine the required illumination intensity of the cockpit based on the flight phase during the full flight phase.
As an example, the flight phase may include: taxiing, takeoff, cruise, approach, descent and/or landing phases, etc.
The adaptive illumination control method 200 according to the present invention may be configured such that the control unit 30 makes the electrochromic film 12 a light transmittance maximum state in any one of the following states: during the takeoff phase, approach phase or landing phase; or the illumination intensity outside the aircraft cockpit is less than or equal to the illumination intensity required by the aircraft cockpit.
Alternatively, the adaptive illumination control method 200 according to the present invention may be configured such that the control assembly 30 causes the electrochromic film 12 to be in a light transmittance minimum state in any one of the following states: the aircraft is currently on the ground at a high temperature and the wheel speed is less than a predetermined threshold; or the aircraft is in cruise phase. As an example, the predetermined threshold may be a speed of less than 5 km/hour, and preferably the predetermined threshold may be about 0 value, or just 0 value, i.e. when the aircraft is stationary on the ground.
In the flow chart of the adaptive illumination control method 200 shown in fig. 2, the method operational steps may begin at 201 and at 202 it may be determined whether the adaptive illumination control system 100 is malfunctioning or in a powered-down or powered-down state.
If the answer is "yes," then the method at 203 causes electrochromic film 12 to be in a transmittance-maximum state, i.e., causes electrochromic film 12 to be in a transparent state, and thus the entire windshield assembly 10 to be in a transparent state, thereby ensuring the operational efficiency of the system. If the answer is "NO," the method may continue to 204.
At 204, the method may obtain information about the flight phase and speed, altitude, etc. at which the aircraft is located. For example, it may be acquired through the on-board core network 22, i.e. from the civil aircraft on-board core network.
Next, at 205, the method determines whether the aircraft is in a critical phase of flight. For example, the flight phase may be acquired through the on-board core network 22 to determine whether the current flight phase is in a critical phase of flight. For example, the aircraft is in the take-off, approach, and landing phases, etc.
If the answer is "yes," the method may place electrochromic film 12 in a maximum transmittance state at 203, ensuring minimum safety required by the pilot.
If the answer is "NO," the method proceeds to 206. At 206, the method determines whether the aircraft is on the ground, at a high temperature, and at a wheel speed of 0. For example, the flight phase, wheel speed of the aircraft may be acquired through the on-board core network 22, and based on the cockpit external temperature acquired by the outside light detection device 21, it is calculated whether the aircraft is currently on the ground, at a high temperature, and the wheel speed is less than a predetermined threshold (e.g., the wheel speed is zero). As used herein, the description "high temperature" may refer to a temperature that a human body can sense. For example, it may be specified that the temperature exceeding 35 ℃ is a high temperature.
If the answer is yes, the method proceeds to 207. At 207, the method controls the electrochromic film 22 to a minimum transmittance to achieve the effect of uv blocking. If the answer is "NO," the method proceeds to 208.
At 208, the method determines whether the aircraft is in an altitude cruise phase.
For example, the aircraft flight phase, altitude, may be obtained through the on-board core network 22, and a calculation may be made as to whether the aircraft is currently in the high altitude cruise phase.
If the answer is yes, the method proceeds to 207. At 207, the method controls the electrochromic film 22 to a minimum transmittance to achieve the effect of uv blocking. If the answer is "no," the method proceeds to 209.
At 209, the method obtains cockpit lighting requirements for a current aircraft flight phase.
For example, different lighting intensity requirements may be stored according to different flight phases during a full flight phase. The lighting intensity demand may be stored as a cockpit lighting demand table 23.
Next, at 210, the method determines whether there is a cockpit lighting demand that varies from pilot to pilot. For example, a cockpit lighting demand knob 24 may be provided in the cockpit for use by a pilot or crew member to make on-demand adjustments to the stored lighting intensity demand.
If the answer is yes, the method proceeds to 211. At 211, the method overlays or updates the full stage cockpit lighting demand table 23. For example, the overlay may be made on the basis of the cockpit lighting requirement table 23 according to the lighting intensity requirement input by the cockpit lighting requirement knob 24. If the answer is "no," the method proceeds to 212.
At 212, the method may determine whether the exterior lighting intensity is greater than the cockpit lighting intensity requirement. For example, the cockpit lighting intensity requirements may be compared to the lighting intensity outside the cockpit.
If the outside illumination intensity is less than or equal to the cockpit illumination intensity requirement, i.e., if the answer is "no," the method proceeds to 203 and the electrochromic film 12 is brought to a transmittance maximum state, i.e., the electrochromic film 12 is brought to a transparent state. If the answer is yes, the method proceeds to 213.
At 213, the method compares the difference between the aircraft exterior light intensity and the cockpit light demand and forms an electrochromic film control signal based on the difference. The control signal may be sent to the control assembly 30, and next, at 214, the control assembly 30 may output a control signal to the electrochromic film 12 to control the magnitude of the voltage applied to the electrochromic film 12, and ultimately the intensity of the illumination within the cockpit. The method may end at 215.
It should be understood that the method steps shown in connection with fig. 2 are exemplary, and that a person skilled in the art may adjust the order of the method steps, add corresponding steps or delete related steps without departing from the scope of the invention.
The terms "inner", "outer" and the like used herein to indicate orientation or orientation are merely for better understanding of the inventive concept shown in the form of preferred embodiments by those of ordinary skill in the art, and are not intended to limit the invention. Unless otherwise indicated, all orders, orientations, or orientations are used solely for the purpose of distinguishing one element/component/structure from another element/component/structure, and do not denote any particular order, order of operation, direction, or orientation unless otherwise indicated. For example, in an alternative embodiment, the "first windshield" may be the "second windshield".
As used herein, unless otherwise indicated, the terms "substantially" and "about" are to be construed as meaning plus or minus five percent of the numerical value or numerical range, or as meaning that there is a deviation of plus or minus five percent of the shape and/or location.
In summary, the adaptive illumination control system 100 according to embodiments of the present invention overcomes the shortcomings of the prior art and achieves the intended objects.
While the adaptive illumination control system of the present invention has been described in connection with the preferred embodiments, those of ordinary skill in the art will recognize that the above examples are for illustrative purposes only and are not intended to be limiting. Accordingly, the present invention may be variously modified and changed within the spirit of the claims, and all such modifications and changes are intended to fall within the scope of the claims of the present invention.
Claims (10)
1. An adaptive lighting control system (100) for an aircraft cockpit, comprising:
A windshield assembly (10) comprising a windshield glass (11) and an electrochromic film (12), the electrochromic film (12) being attached to the windshield glass (11) and adjusting the light transmittance of the windshield assembly (10) based on the magnitude of a voltage supplied to the electrochromic film (12);
an input assembly (20) for providing a required illumination intensity of the cockpit; and
-A control assembly (30) connected to the electrochromic film (12) of the windshield assembly (10) and to the input assembly (20) and adjusting the magnitude of the voltage supplied to the electrochromic film (12) during the full flight phase of the aircraft based on the required illumination intensity within the aircraft cockpit.
2. The adaptive lighting control system (100) according to claim 1, wherein the input component (20) comprises:
The outside-cockpit illumination detection device (21) is used for acquiring illumination intensity, temperature and/or ultraviolet intensity of the outside environment of the cockpit;
An on-board core network (22) for acquiring a current flight phase and a current flight speed; and
A cockpit lighting demand table (23) for storing different lighting intensity demands according to different flight phases during said full flight phase.
3. The adaptive lighting control system (100) according to claim 2, wherein the input component (20) further comprises: the cockpit illumination demand knob (24) is used for increasing and decreasing the cockpit illumination demand which is initially set.
4. The adaptive lighting control system (100) according to claim 2, characterized in that the cockpit external lighting detection device (21) comprises a lighting sensor and/or an infrared camera and calculates the value of the current aircraft windshield lighting intensity maximum according to longitude and latitude, weather, environment, aircraft attitude.
5. An adaptive lighting control system (100) according to any one of claims 1-4, characterized in that the windscreen (11) comprises a first windscreen (11A) and a second windscreen (11B), and the electrochromic film (12) is arranged between the first windscreen (11A) and the second windscreen (11B).
6. The adaptive illumination control system (100) according to any one of claims 1-4, wherein the electrochromic film (12) is a tungsten oxide electrochromic film.
7. An adaptive lighting control method for an aircraft cockpit, comprising:
an adaptive lighting control system (100) is provided, the adaptive lighting control system (100) comprising:
A windshield assembly (10) comprising a windshield glass (11) and an electrochromic film (12), the electrochromic film (12) being attached to the windshield glass (11) and adjusting the light transmittance of the windshield assembly (10) based on the magnitude of a voltage supplied to the electrochromic film (12);
an input assembly (20) for providing a required illumination intensity of the cockpit; and
A control assembly (30) connected to the electrochromic film (12) of the windshield assembly (10) and to the input assembly (20) and adjusting the magnitude of the voltage supplied to the electrochromic film (12) during a full flight phase of the aircraft based on the intensity of illumination required within the aircraft cockpit,
Wherein the control assembly (30) determines the required illumination intensity of the cockpit based on the flight phase during the full flight phase.
8. The adaptive lighting control method of claim 7, wherein the flight phase comprises: taxiing, takeoff, cruise, approach, descent and/or landing phases.
9. The adaptive illumination control method according to claim 8, wherein the control assembly (30) causes the electrochromic film (12) to be in a light transmittance maximum state in any one of the following states:
During the takeoff phase, the approach phase or the landing phase; or alternatively
The illumination intensity outside the aircraft cockpit is less than or equal to the illumination intensity required by the aircraft cockpit.
10. The adaptive illumination control method according to claim 8, wherein the control assembly (30) causes the electrochromic film (12) to be in a light transmittance minimum state in any one of:
the aircraft is currently on the ground at a high temperature and the wheel speed is less than a predetermined threshold; or alternatively
The aircraft is in the cruise phase.
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| CN202410424889.XA CN118092035A (en) | 2024-04-09 | 2024-04-09 | Self-adaptive illumination control system and control method for aircraft cockpit |
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| CN202410424889.XA CN118092035A (en) | 2024-04-09 | 2024-04-09 | Self-adaptive illumination control system and control method for aircraft cockpit |
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