JP2566366B2 - Display in aircraft docking guidance system - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a display in an aircraft docking guidance device for accurately guiding a parked aircraft to a stop point (parking spot).

[0002]

2. Description of the Related Art Conventionally, in order to accurately guide a parked aircraft to a stop point, azimuth and distance information is provided by optical information. However, the parallax of a pilot changes due to the weight of the aircraft and the like. Distance information cannot be obtained. Also, it is difficult to support different models at the same parking spot. Therefore, it is used as a supplement, and is substantially guided by a hand signal on the ground. There is also a means for providing distance information by burying a sensor in the basement of an aircraft approach road and detecting the passage of wheels. However, there is a difficulty in hindering the operation of the aircraft during installation and maintenance. In addition, although there is a distance measuring means using a laser, the reflectance of laser light with respect to black is low, the model is limited, and it is difficult to use in all weathers.

Therefore, a collision prevention light (hereinafter referred to as A
(CL) is used as the position reference of the aircraft, and the deviation from the aircraft approach line and the distance to the stop point are calculated, and the information is accurately displayed by the pilot display device as the azimuth information and distance information. Aircraft docking guidance devices that guide the vehicle to a stopping point have been considered.

[0004]

SUMMARY OF THE INVENTION The present invention has been made in view of the above circumstances, and is an aircraft capable of reliably monitoring type information, direction information, distance information, and the like of an aircraft so that a pilot can visually recognize it. An object is to provide a display in a docking guidance device.

[0005]

In order to solve the above-mentioned problems, the present invention takes an image of an aircraft collision prevention light with a plurality of image pickup devices, and uses color extraction means corresponding to each image pickup device to obtain each collision prevention light. In the aircraft docking guidance device that extracts the color signal of the above to obtain the data of the collision prevention light on the imaging screen, and obtains the azimuth information and the distance information by calculating the data of the collision prevention light to be the position reference of the aircraft. A character display lamp for displaying the type information of the aircraft,
A center line lamp and an off-center line lamp for displaying the azimuth information, and a distance step indicator lamp for displaying the distance information are provided.

[0006]

With the above means, the pilot's accustomedness and visibility can be taken into consideration, and the type information, azimuth information, distance information, etc. of the aircraft can be reliably monitored so that the pilot can be reliably visually recognized.

[0007]

Embodiments of the present invention will now be described in detail with reference to the drawings.

FIG. 1 is a front view of a display device according to a first embodiment of the present invention. That is, the collision prevention light of an aircraft is imaged by a plurality of imaging devices, and the color signal of each collision prevention light is extracted by the color extraction means corresponding to each imaging device to obtain the data of the collision prevention light on the imaging screen. , In an aircraft docking guidance device that obtains azimuth information and distance information by arithmetically processing the data of the collision prevention light and uses it as the position reference of the aircraft, the display 1 is installed in front of the stop position on the extension line of the runway center line. A character display lamp 2 for displaying aircraft type information, distance information, stop information, etc. is provided on the upper front of the display 1. A center line lamp 3 for indicating the center position of the aircraft is provided in the center of the front of the display 1 as an azimuth information display, and the left and right sides of the aircraft are displayed substantially parallel to both sides of the center line lamp 3. An off-center line lamp 4 is provided. A plurality of distance step indicator lights 5 for displaying remaining distance information are provided on both front sides of the display 1. This distance step indicator light 5 is 0 m,
0.5m, 1.0m, 1.5m, 2m, 3m, 4m, 5
m, 6m, 7m, 8m, 9m, 10m, 13m, 16
It consists of 18 lights that display m, 19m, 22m, and 25m. The character display lamp 2, the center line lamp 3, the off-center line lamp 4 and the distance step display lamp 5 are configured so that they can be switched between green, orange and red by a light emitting diode (LED), for example.

Next, the operation of the display 1 will be described. That is, the display device 1 provides the aircraft pilot with information about the lateral shift (azimuth information) with respect to the approach center line of the aircraft at the parking location and the distance to the stop position from 25 m before. This device can be used by both the pilot (left seat) and the co-pilot (right seat). First, before entering an aircraft, a ground worker inputs a model name into the operation unit. The entered model name is, as shown in FIG.
It is displayed in green on the character display lamp 2. When the ground worker inputs the model name, the distance step indicator lights 5 are all displayed in green. When the aircraft docking guidance device catches an approaching aircraft, the distance step indicator light 5 changes as follows, as shown in FIG. 2B. 25m ～ 2m ……………………………… Green 1.5m, 1.0m, 0.5m ………… Orange 0m (stop position) …………………… Red

In accordance with the approach of the aircraft, the distance step indicator light 5 is, as shown in FIG. 2 (c), 25m to 10m.
The lights are turned off one by one every 3 m, every 10 m from 2 m every 1 m, and every 2 m to 0 m every 0.5 m. As shown in FIG. 3 (a), when the aircraft comes to a position 10 m before the stop position, the model display disappears on the character display lamp 2 and SLOW is displayed in orange. When the aircraft arrives at a position 10 m before the stop position, as shown in FIG. 3B, the SLOW display disappears on the character display lamp 2 and the remaining distance is displayed in orange in units of 0.1 m. When the aircraft reaches the stop position (0 m), as shown in FIG. 3 (c), the numerical value display of the distance disappears on the character display lamp 2 and STOP is displayed in red.
Is displayed. When the aircraft overruns 1 m or more from the stop position, the STOP display disappears on the character display lamp 2 and OVER is displayed in red, as shown in FIG. 4A. After the aircraft has stopped at the stop position and the choke man has stopped the wheels, by operating the operation unit, as shown in Fig. 4 (b),
CHCK (abbreviation of CHOCK) is displayed in green on the character display lamp 2. In case of emergency, a ground worker can perform an emergency stop operation from the operation unit. In this case, as shown in FIG. 4C, STOP is displayed in red on the character display lamp 2 and all the display lamps are changed to red display.

Next, the azimuth information will be explained. When the aircraft is within a range of 20 cm to the left and right from the center of the approach line, the center line lamp 3 lights up in green as shown in FIG. 3 (b). The position reference of the aircraft is the position of the upper ACL. 20cm to the left and right with the aircraft centering on the approach line
When entering the range of 1.0 m, the off-center line lamp 4 in the deviated direction lights in orange together with the green center line lamp 3.
Further, when the aircraft deviates from the center line and deviates from the approach line by 1 m or more, the off-center line lamp 4 changes from orange to red.

FIG. 5 is a front view of a display device according to the second embodiment of the present invention. That is, the center line lamp 3 for displaying the center position of the aircraft is displayed at the center of the front of the display 1 as the direction information display.
Below the center line lamp 3, a machine shadow display lamp 6 for displaying a machine shadow of the aircraft is provided. This image light 6
Is always lit to indicate the approach direction of the aircraft. 5, those parts which are the same as those corresponding parts in FIG. 1 are designated by the same reference numerals, and a description thereof will be omitted.

FIG. 6 is a front view of a display device according to a third embodiment of the present invention. That is, as shown in FIG. 7, an image of the nose gear 8 of the aircraft 7 is picked up by an image pickup device 9 such as a CCD television (TV) camera, and the image data of the nose gear 8 obtained by the image pickup device 9 is displayed below the display 1. The image is displayed on the image display unit (monitor) 10 of, for example, a liquid crystal television receiver. 6, those parts that are the same as those corresponding parts in FIG. 1 are designated by the same reference numerals, and a description thereof will be omitted.

FIG. 8 is a structural explanatory view showing an aircraft docking guidance device according to a third embodiment of the present invention. That is, this embodiment is divided into an image system and a display system. The image system performs ACL extraction, center of gravity calculation, three-dimensional measurement, calculation of azimuth distance information, and the display system displays azimuth distance information, operation switch display, history reproduction, abnormality detection, data communication with the central control unit. I do. The camera unit A is composed of CCD cameras 11R and 11L installed on the left and right sides of the ACL.

The extraction section B includes left and right level clamp circuits 12
R, 12L, amplifiers 13R, 13L, upper / lower limit comparison circuit 1
4R, 14L, and a mask & window controller 15. That is, the CCD camera 1 is synchronized with the image clock.
Color difference signals (R-Y), (B-
Y) and (Y) signals are input. Level clamp circuit 12
The color difference signals are superimposed on the reference DC level by R and 12L. In the upper and lower limit comparison circuits 14R and 14L, the AC
The upper and lower limits of the L color difference signal are set, and the CCD camera 1
The color-difference signals from 1R and 11L that are within the range pass, and the signals that all (RY), (BY), and (Y) signals pass are treated as extraction signals. Only the mask data output from the mask generation circuit 16 and the window generation circuit 17 in which the scanning line is addressed for each pixel, and the signal passed by the mask and window controller 15 in which the window data is extracted and the gate circuit are normal. The extraction signal is output from the extraction unit B as an extraction signal.

The center-of-gravity calculating section C includes a mask generation circuit 16, a window generation circuit 17, an address generation circuit 18, a graphic memory 19, multiple center processing circuits 20R, 20L and CP.
It is composed of U21 and VME interface 22. In other words, the address generation circuit 18 outputs a scanning line that is addressed for each pixel by an image clock as an image address. In the graphic memory 19, the mask and window block address data registered in advance are converted into a signal in which the data is synchronized by the mask generation circuit 16 and the window generation circuit 17 according to the image address bus, and the mask data, Output as window data. In the multi-center processing circuits 20R and 20L, the area (pixel) calculation is performed from the extracted signal, and individual centroid points under one screen are calculated. The multiple center points obtained from the extracted signals from the left and right CCD cameras 11R and 11L are subjected to three-dimensional calculation by combining the respective center of gravity and output three-dimensional information.

The arithmetic processing unit D is a VME interface 2
3, CPU 24, arithmetic processor 25, ROM 26, R
AM27, E ² PROM 28, communication control circuits 29, 30
It is composed of That is, based on the two-dimensional information obtained by the center-of-gravity calculation unit C, data is selected by upper and lower limit value determination, left and right pixel number determination, and pixel number upper and lower limit determination, and the passed information is set to ACL 3
Handle as dimensional information. The three-dimensional information is obtained by calculating the distance and azimuth information based on the spatial information obtained by calibration in advance and outputting the information.

The display control unit E includes a CPU 31, a ROM 3
2, RAM 33, logging memory 34, communication control circuit 3
5, 36, remote control circuit 37, I / O circuits 38, 39,
It is composed of a driver 40. That is, the distance and azimuth information input from the arithmetic processing unit D is subjected to correction calculation of the distance and azimuth from the stop position by the offset data for each model. In addition, smoothing processing such as hysteresis processing is performed on azimuth information and trend processing is performed on distance information.
As the data after the above processing, the data corresponding to the model, distance and azimuth indicator 1 is written and displayed. In the logging, the set model data, the distance from the arithmetic processing unit D for every fixed time, the azimuth information, and the display data are stored in the logging memory 34. In the data communication with the central control unit, the data stored in the logging memory 34 is output when the central control unit requests the data. In abnormal processing, program setting,
Failures due to hardware self-diagnosis, etc. are output to the display unit 1 with fail-safe in mind. The operation section F is composed of operation switches 41.

An image pickup device 9 such as a CCD television camera picks up an image of a nose gear of an aircraft, and the image data of the nose gear obtained by the image pickup device 9 is displayed on an image of, for example, a liquid crystal television receiver via a video controller VC. It is displayed on the section (monitor) 10.

[0020]

As described above, according to the present invention, the pilot's familiarity and visibility can be taken into consideration, and the type information, heading information, distance information, etc. of the aircraft can be reliably monitored, and the pilot can be visually confirmed. You can

[Brief description of drawings]

FIG. 1 is a front view of a display device according to a first embodiment of the present invention.

FIG. 2 is an operation explanatory diagram of the display according to the first embodiment of the present invention.

FIG. 3 is an operation explanatory diagram of the display according to the first embodiment of the present invention.

FIG. 4 is an operation explanatory diagram of the display according to the first embodiment of the present invention.

FIG. 5 is a front view of a display device according to a second embodiment of the present invention.

FIG. 6 is a front view of a display device according to a third embodiment of the present invention.

FIG. 7 is a schematic configuration diagram showing an aircraft docking guidance device according to a third embodiment of the present invention.

FIG. 8 is a structural explanatory view showing an aircraft docking guidance device according to a third embodiment of the present invention.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Display device, 2 ... Character display light, 3 ... Center line light, 4 ... Off center line light, 5 ... Distance step display light, 6 ... Machine shadow display light, 10 ... Image display part (monitor), A ... Camera Department,
B ... Extraction unit, C ... Centroid calculation unit, D ... Calculation processing unit, E ... Display control unit, F ... Operation unit.

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Takafumi Takahashi 1 Komukai Toshiba-cho, Kouki-ku, Kawasaki-shi, Kanagawa Toshiba Tesco Co., Ltd. Kawasaki Plant (72) Inventor Shinkichi Kikuchi Komukai-Toshiba, Kawasaki-shi, Kanagawa No. 1 at Toshiba Tesco Corp. Kawasaki Plant (56) Reference JP-A-3-193596 (JP, A) JP-A-64-52597 (JP, A) JP-A-63-156299 (JP, A) Jitsuko Sho 61-17520 (JP, Y2)

Claims (3)

(57) [Claims] 1. An aircraft docking guidance device which obtains azimuth information and distance information of an aircraft and which is used as a position reference of the aircraft , and a character display lamp for displaying model information of the aircraft in green, orange, and red, and the azimuth information. There appears, centerline lamp green lights, 及
From both sides of the center line lamp of
When the deviation is within the specified range, the orange light turns on,
The off-center line lamp that lights red when the deviation from the specified range is larger than the predetermined range, and the distance information is displayed in green, orange, and red.
A display device in an aircraft docking guidance device, characterized in that a distance step indicator light which is sequentially turned off in the order of green, orange, and red according to an approach is arranged in a plane . 2. An aircraft docking guidance device that obtains azimuth information and distance information of an aircraft and uses it as a position reference of the aircraft , and a character display lamp that displays model information of the aircraft in green, orange, and red, and the azimuth information. There appears, centerline lamp green lights, 及
From both sides of the center line lamp of
When the deviation is within the specified range, the orange light turns on,
The off-center line lamp that lights red when the deviation from the specified range is larger than the predetermined range, and the distance information is displayed in green, orange, and red.
A distance step indicator light that turns off sequentially in the order of green, orange, and red according to the approach and a machine shadow indicator light that displays the aircraft's shadow are arranged in a plane.
An indicator for an aircraft docking guidance device, which is characterized in that 3. An aircraft docking guidance device which obtains azimuth information and distance information of an aircraft and which is used as a position reference for the aircraft , and a character display lamp for displaying model information of the aircraft in green, orange, and red, and the azimuth information. There appears, centerline lamp green lights, 及
From both sides of the center line lamp of
Deviation orange lights when the predetermined range, or approach path of an aircraft
The off-center line lamp that lights red when the deviation from the specified range is larger than the predetermined range, and the distance information is displayed in green, orange, and red.
Distance step indicator lights that sequentially turn off in the order of green, orange, and red according to the approach, and the nose gear of the aircraft is imaged by an imaging device, and the image data of the nose gear obtained by this imaging device is displayed. A display device in an aircraft docking guidance device, characterized in that the image display unit is arranged in a plane .