阅读说明：本技术 用于跑道照明的动态照明系统和飞行器部件 (Dynamic lighting system for runway lighting and aircraft component ) 是由 加布里埃尔·约瑟芬·克里斯蒂亚娜·德布鲁韦 于 2020-04-10 设计创作，主要内容包括：本发明涉及一种用于跑道照明的动态照明系统(1)和飞行器部件,所述动态照明系统包括光源,所述光源具有可寻址光束方向<Image he="78" wi="112" file="DDA0002446161460000011.GIF" imgContent="drawing" imgFormat="GIF" orientation="portrait" inline="no"></Image>以及控制单元,所述控制单元配置成：接收飞行器的姿态信息以及选择用于起飞或着陆<Image he="76" wi="98" file="DDA0002446161460000012.GIF" imgContent="drawing" imgFormat="GIF" orientation="portrait" inline="no"></Image>的跑道的取向；获取水平轴线<Image he="68" wi="89" file="DDA0002446161460000013.GIF" imgContent="drawing" imgFormat="GIF" orientation="portrait" inline="no"></Image>和竖直轴线<Image he="74" wi="114" file="DDA0002446161460000014.GIF" imgContent="drawing" imgFormat="GIF" orientation="portrait" inline="no"></Image>所述水平轴线<Image he="60" wi="32" file="DDA0002446161460000015.GIF" imgContent="drawing" imgFormat="GIF" orientation="portrait" inline="no"></Image>与<Image he="70" wi="45" file="DDA0002446161460000016.GIF" imgContent="drawing" imgFormat="GIF" orientation="portrait" inline="no"></Image>的纵向方向共线；确定实际飞行器轨迹<Image he="78" wi="99" file="DDA0002446161460000017.GIF" imgContent="drawing" imgFormat="GIF" orientation="portrait" inline="no"></Image>和参考飞行器轨迹<Image he="77" wi="150" file="DDA0002446161460000018.GIF" imgContent="drawing" imgFormat="GIF" orientation="portrait" inline="no"></Image>获取实际竖直进场角度(β)、参考竖直进场角度(β<Sub>0</Sub>)、以及实际水平进场角度(γ)；并且致动光源,以使所述光束方向<Image he="77" wi="86" file="DDA0002446161460000019.GIF" imgContent="drawing" imgFormat="GIF" orientation="portrait" inline="no"></Image>进行绕所述竖直轴线<Image he="77" wi="96" file="DDA00024461614600000110.GIF" imgContent="drawing" imgFormat="GIF" orientation="portrait" inline="no"></Image>的值为|β|-|β<Sub>0</Sub>|的角运动,并且进行绕所述水平轴线<Image he="65" wi="96" file="DDA00024461614600000111.GIF" imgContent="drawing" imgFormat="GIF" orientation="portrait" inline="no"></Image>的值为|γ|的角运动,以将所述光源的束朝向所述跑道方向竖直地和水平地对齐。(The invention relates to a dynamic lighting system (1) for runway lighting, comprising a light source with addressable beam directions, and an aircraft component And a control unit configured to: receiving attitude information of an aircraft and selecting for takeoff or landing The orientation of the runway of (a); obtaining horizontal axes And a vertical axis The horizontal axis And are collinear; determining an actual aircraft trajectory And reference aircraft trajectory Obtaining an actual vertical approach angle (beta), a reference vertical approach angle (beta) 0 ) And an actual horizontal approach angle (γ); and actuating the light source to direct the light beam About said vertical axis Has a value of | beta | - | beta 0 And performs an angular movement about the horizontal axis Is an angular movement of | γ | to align the beam of light sources vertically and horizontally towards the runway direction.)

1. A dynamic lighting system for runway lighting, the dynamic lighting system comprising:

-a light source having an addressable beam direction

-a control unit configured to:

-receiving aircraft attitude information, selecting a runway (R) for takeoff or landing, and orientation of said runway

-acquiring a horizontal axisAnd a vertical axisThe horizontal axis

-determining from the aircraft attitude information on the horizontal axisAnd the vertical axis

-acquiring the actual aircraft trajectoryProjection on XY plane with the horizontal axisAn actual vertical approach angle (β) formed therebetween, and a trajectory at said reference aircraft

-acquiring the aircraft trajectoryProjection on the X-Z plane and theHorizontal axisThe actual horizontal approach angle (y) formed therebetween,

-actuating the light source to direct the light beamAbout said vertical axis

-and, actuating the light source to direct the light beamAbout said horizontal axisIs of value | γ |, said angular movement following a movement from said actual horizontal approach angle (γ) towards said horizontal axis

2. -a dynamic lighting system for runway lighting according to claim 1, wherein the light source is mechanically movable and configured to move according to received servo commands.

3. -a dynamic lighting system for runway lighting according to claim 1 wherein the light source has a directable output beam, preferably consisting of an array of electrically controlled LEDs or laser diodes, a projection by LCD, or electrically controlled micro mirrors.

4. -a dynamic lighting system for runway lighting according to any of the preceding claims, wherein the control unit is connected to flight management system data of the aircraft to determine the runway (R) selected for takeoff or landing and/or its orientation

5. A dynamic lighting system for runway lighting according to claim 4, wherein the control unit is configured to automatically switch on the light sources during approach, landing and takeoff phases based on information received from the flight management system.

6. -a dynamic lighting system for runway lighting according to any of claims 4-5, wherein the control unit is further configured to perform an automatic dimming function to avoid glare to other aircraft in the airport.

7. -an aircraft part (2) comprising a dynamic lighting system (3) for runway lighting according to any of the preceding claims, the dynamic lighting system (3) being embedded in the aircraft part (2).

Technical Field

The invention relates to a dynamic lighting system for runway lighting. More particularly, the present invention relates to an aircraft lighting system for runway lighting for takeoff and landing purposes.

It is an object of the present invention to provide a framework for runway lighting that is more efficient and optimally suited to all aircraft attitudes that take into account the speed vector of the aircraft.

Another object of the invention is to provide a framework for runway lighting that improves the lighting performance in any external environmental conditions (also in low visibility situations).

Background

Currently, there are two main solutions for dynamic lighting of runways, one based on calculations using MEMs (Micro-Electro-Mechanical Systems) and the other based on image recognition. The first solution requires MEMs technology embedded within the lights to estimate the relative position and attitude of the aircraft with respect to the runway in order to adapt the lighting accordingly, while the second solution involves embedding cameras in the lights and identifying the runway by image post-processing to direct the light beam accordingly.

Both solutions require the integration of a complex framework in the lamp.

In addition, these solutions are not robust for all aircraft attitudes due to the low reliability of the technology used. In particular, there are many deviations in MEMs technology, and in video recognition technology, there are many problems of low visibility due to weather conditions.

Furthermore, the lights illuminating the runway are generally designed for a specific reference situation of the attitude of the aircraft during the takeoff and landing phases, and such a reference orientation of the light beam is not always optimally adapted to the actual attitude of the aircraft (given by its velocity vector); examples are a crosswind landing or a landing at a higher speed (different pitching approach compared to the reference situation).

It is therefore desirable to provide a technical means that is simple, effective and able to withstand environmental conditions without being operationally affected in all aircraft attitudes.

Disclosure of Invention

The present invention overcomes the above-mentioned drawbacks by providing a dynamic lighting system for runway lighting that solves the above-mentioned limitations of the prior art.

The invention relates to a dynamic lighting system comprising a light source having an addressable beam direction, and a control unit configured to:

-receiving aircraft attitude information, selecting a runway (R) for takeoff or landing, and orientation of said runway

-acquiring a horizontal axisAnd a vertical axisThe horizontal axisWith said selected runway

Are co-linear in their longitudinal direction,

-determining from the aircraft attitude information on the horizontal axisAnd the vertical axisThe actual aircraft trajectory in (1)And the reference aircraft trajectory

-acquiring the actual aircraft trajectory

Projection on XY plane with the horizontal axisAn actual vertical approach angle (β) formed therebetween, and a trajectory at said reference aircraftTo the horizontal axisA reference vertical approach angle (beta) formed therebetween₀)，

-acquiring the aircraft trajectory

Projection on the X-Z plane and said horizontal axisThe actual horizontal approach angle (y) formed therebetween,

-actuating the light source to direct the light beamAbout said vertical axisHas a value of | beta | - | beta₀(ii) an angular movement of | following a movement from the actual approach angle (β) towards the desired reference approach angle (β)₀) A direction defined by the angular movement performed to align the beam of light sources vertically towards the runway direction,

-and, actuating the light source to direct the light beamAbout said horizontal axisIs of value | γ |, said angular movement following a movement from said actual horizontal approach angle (γ) towards said horizontal axis

The angular movement is performed in opposite directions so as to align the beams of the light sources horizontally towards the runway direction.

Thus, the invention provides a dynamic lighting system adapted to direct a light beam in a direction towards a runway selected for takeoff or landing, at any time taking into account the trajectory of the aircraft.

Furthermore, since the light source of the system is connected to the existing data of the aircraft to know the attitude of the aircraft by means of the QFU code (the magnetic orientation being clockwise compared to the north pole) and to the data of the flight management system to know which runway has been selected and how it is oriented, the invention provides an easier and more reliable way of orienting the light beam towards the current direction and the correct direction of the runway compared to prior art solutions.

Drawings

For a better understanding of the present invention, the following drawings are provided for illustrative and non-limiting purposes, wherein:

FIGS. 1a and 1b show the vectors considered in the first scenario in the horizontal and vertical planes, where the actual aircraft trajectory

Deviation from a reference aircraft trajectory associated with a particular aircraft attitude

Fig. 1a shows the vector in the vertical plane. Fig. 1b shows the vectors in the horizontal plane.

FIG. 2 shows all vectors considered in a second scenario, where the actual aircraft trajectory

Deviation from a reference aircraft trajectory associated with a particular aircraft attitude

Fig. 3 shows an aircraft with a dynamic lighting system embedded in one of its components.

Detailed Description

According to the invention, a lighting system comprises a light source and a control unit. The light source having an addressable beam directionThe direction is steerable to provide dynamic lighting that is specific to the actual aircraft attitudeInformation and runway selected for takeoff or landingThe orientation is sensitive.

Fig. 1a and 1b schematically show a first scenario in which the trajectory followed by the aircraft deviates from the desired reference trajectory. Thus, the beam direction also deviates from the desired reference trajectory, taking into account the trajectory of the aircraft.

FIG. 1a shows an actual aircraft trajectoryReference aircraft trajectoryActual beam directionAnd reference beam directionWherein the reference beam directionWith reference aircraft trajectory in the vertical plane XY

And correspondingly. For reference, horizontal axisWith selected runwayAre collinear.

As shown, the actual aircraft trajectory is followed

Aircraft and horizontal axisForm an angle beta, while the reference aircraft trajectory is desired according to the light orientation default design

To the horizontal axisForm an angle beta₀. Thus, the actual aircraft trajectory

From a desired reference aircraft trajectoryDeviation from | β | - | β₀L. Thus, to the beam directionMaking corrections to achieve desired beam directions

Wherein the desired beam direction

About a vertical axisHas a value of | beta | - | beta₀The deviation of l corresponds to the deviation following from the actual approach angle (β) towards the beam directionDesired reference angle of approach (β)₀) The direction defined by the angular movement performed. In this way, the beam direction is vertically aligned towards the runway direction selected for takeoff or landing.

FIG. 1b shows the actual aircraft trajectoryReference aircraft trajectoryActual beam direction

And desired beam directionThe desired beam directionWith reference aircraft trajectory in the horizontal plane XZ

And correspondingly.

As shown, the aircraft follows the actual aircraft trajectoryThe actual aircraft trajectory and horizontal axisForm an angle gamma, and design a desired reference trajectory for the aircraft according to the default orientation of the beamTo the horizontal axis

Form an angle gamma₀. Thus, the actual aircraft trajectoryFrom a desired reference aircraft trajectoryDeviation from gamma₀L. Thus, to the beam directionMaking corrections to achieve desired beam directionsWherein the desired beam direction

About a horizontal axis

Corresponds to a deviation of value | γ | which follows from the actual horizontal approach angle (γ) towards the horizontal axisThe opposite direction defined by the angular movement performed. In this way, the beam direction is horizontally aligned with the direction towards the runway selected for takeoff or landing.

According to a preferred embodiment, the light source is mechanically movable and configured to move in accordance with the received servo commands.

According to another preferred embodiment, the light source has a directable output beam consisting of an array of electrically controlled LEDs (without mechanically movable parts). Alternatively, the light source may be constituted by an electrically controlled laser diode array or projection by LCD, or electrically controlled micro mirrors.

Furthermore, according to another preferred embodiment, the control unit is connected to flight management system data of the aircraft to determine the runway (R) selected for takeoff or landing, and/or its orientation

According to another preferred embodiment, the control unit is configured to automatically turn on the light sources during approach, landing and take-off phases based on information received from the flight management system, in particular from the height and distance to the target runway.

According to another preferred embodiment, the control unit is further configured to perform an automatic dimming function to avoid glare to other aircraft in the airport after landing has been performed or before the acceleration phase of takeoff. These phases are detected by information provided by the flight management system.

FIG. 2 illustrates a second scenario in which the aircraft is not oriented and selected for takeoff or landingAnd for this purpose, wherein the luminous flux needs to be directed in consideration of the relative position of the aircraft oriented towards the runwayRelative to the desired beam directionCorrecting for β (along the pitch axis) and γ (along the yaw axis).

As mentioned before, in order to obtain the desired beam direction

From

Initially, it is the basic direction of the luminous flux defined in the aircraft (which exists today and is the correct direction for the aircraft to be oriented in the runway direction for the selected takeoff or landing), and then corrected with the aircraft attitude, so that,

if the aircraft trajectory (velocity vector,) Inclined upwards so as to form an angle gamma, vector, with respect to a horizontal plane defined by the runwayCorrected to keep the focus down; conversely, if the aircraft trajectory is tilted downward, the focus is maintainedUpward),

and if the aircraft trajectory (velocity vector,

) Moving sideways so that an angle γ is formed compared to a vertical plane perpendicular to the wing and perpendicular to the fuselage reference line, a vector will be formed+/- | γ |, is corrected so that the light is focused accordingly.

Fig. 3 shows an aircraft (1) with components (2) in which a dynamic lighting system (3) for runway lighting as described above can be embedded. The dynamic lighting system (3) may be embedded on a movable or non-movable part (2) of the aircraft (1).