JPH05294292A - Monitoring device for aircraft - Google Patents

Abstract

PURPOSE:To recognize an abnormal place from the inside of a control room by installing a means which is equipped with at least one TV camera device on the outer wall of the airframe of an aircraft and displays the output image of the TV camera in the control room and a means for remote operating the image pick-up angle of the TV camera device from the inside of the control room. CONSTITUTION:An upper part camera device 10 is equipped with an upper part left camera 16 and an upper part right camera 17, and a lower part camera device 11 is equipped with a lower part camera 18. The image pick-up angle of each camera is displayed in a digital display device 14 and an analogue display device 15. When the TV camera is correctly set to an abnormal place, the abnormal place is monitored by a monitor TV 9 and the breakage level is judged, and an airframe is steered and the communication to a control tower is carried out on the basis of the data. The upper part camera device 10 is equipped with the left and right cameras on a turning base, and the side surfaces of a vertical tail can be recognized from the left and right sides.

Description

Detailed Description of the Invention

[0001]

FIELD OF THE INVENTION The present invention is used in aircraft. In particular, it relates to a technique for visually recognizing obstacles outside the aircraft during navigation.

[0002]

2. Description of the Related Art A conventional example will be described with reference to FIG. FIG. 11 is an overall configuration diagram of a conventional example. A command signal from the control command unit 1 to each unit is transmitted to the actuator unit 3 or directly to the substance unit 5 via the I / O unit 2. The operation of the actuator unit 3 is monitored by the detection unit 4, and the I / O is restarted.
It is fed back to the abnormality monitoring display unit 6 via the unit 2. The operation at a position not via the actuator unit 3 is directly I
It is fed back to the abnormality monitoring display unit 6 via the / O unit 2.

The abnormality notification panel 7 of the abnormality monitoring display unit 6 displays an abnormality of each function, and when an abnormality occurs, an alarm indicating the abnormal portion is displayed, and regarding the level of the abnormality, the signal of the abnormal portion is electrically displayed. Abnormality, and the abnormality monitoring display unit 6 is selected by a current signal, a voltage signal, or a digital signal.
Be transmitted to. Then, these signals are displayed on the abnormality notification panel 7 by an ammeter, a voltmeter, or a digital display, respectively. The type of these signals depends on the physical properties of the anomaly.

For example, looking at the flow of abnormality monitoring of the pull-in and pull-out control of the wheel legs, from the control command unit 1 to the I / O.
The signal transmitted to the actuator unit 3 via the unit 2 moves the actuator, and the operation state is monitored by the detection unit 4. The result is fed back to the I / O unit 2 again,
From here, a signal is transmitted to the abnormality monitoring display unit 6. This flow is the same even when there is an abnormality in another actuator.
Each engine, which is an operating mechanism without an actuator,
In the fuel system and the like, a signal from the substance unit 5 is directly transmitted to the abnormality monitoring display unit 6 via the I / O unit 2.

[0005]

As described above, when the detection unit detects an abnormality in the pulling-in or pulling-out of the wheel legs, an alarm is displayed in the portion displaying the "wheel condition" of the abnormality monitoring display unit. However, regarding the level of the anomaly, it is only an indication of whether or not the leg has come out, and in order to know exactly how much it has gone out, the controller of the ground control tower tests this aircraft over the control tower. There is no choice but to fly and visually check it with binoculars, and to notify the result to the pilot wirelessly. In an emergency, it takes a considerable amount of time and the psychological burden on the pilot is very large. Also, when the flaps on the vertical stabilizer and behind the rudder that controls the direction of navigation are damaged, only the extent to which they are damaged can be determined, and the pilot must guide the aircraft by trial and error. Under such circumstances, the guidance error of the aircraft will be caused, and the risk of causing a serious accident will increase. Further, although it is extremely rare, an abnormality alarm may be displayed due to a failure of the abnormality detection means although no abnormality is detected anywhere. Even in such a case, since the location cannot be visually recognized, it takes time to realize that the abnormality detecting means has a failure.

The present invention has been made against such a background, and an object thereof is to provide an aircraft monitoring device capable of visually recognizing an abnormal portion from the inside of a cockpit.

[0007]

SUMMARY OF THE INVENTION The present invention is an aircraft provided with means for monitoring the operation of each part of the aircraft to detect an abnormality, and means for notifying the cockpit of an abnormal location by a signal from this detecting means. In the monitoring device for aircraft, one or more television camera devices are provided on the outer wall of the aircraft body, means for displaying the output image of the television camera in the cockpit, and the angle of view of the television camera device are remotely controlled from the cockpit. And means for doing so.

It is desirable that the television camera device includes an infrared irradiating means in consideration of use at night. Also,
The device of the present invention can also be configured to include means for automatically starting by the output of the means for detecting the abnormality.

The remote control means may be configured to include a control means which is controlled by a CPU and directs the angle of view to an abnormal portion by the output of the abnormality detecting means to assist the operation of the operation staff. .. Further, the means for displaying the video may be configured to include a display means for displaying outputs of a plurality of television cameras, respectively.

[0010]

In the cockpit of an aircraft, television camera devices are provided on the upper and lower portions of the outer wall of the fuselage in order to grasp the situation outside the fuselage using the television camera. It is desirable that these can be remotely operated ± 360 ° in the horizontal direction and ± 90 ° in the vertical direction. Since the outer shape of the television camera device is provided outside the machine body, it is formed in a shape in consideration of air resistance. In addition, an infrared irradiator can be incorporated in consideration of use at night.

The remote control method of each television camera is as follows: a horizontal motor and a vertical motor, which are servo motors, are switched for each television camera to manually adjust the vertical and horizontal directions, and a CPU is connected to the servo motor. The optimum positions for visually recognizing each part of the aircraft are stored in advance in this CPU, and only the command signal indicating the location to be visually recognized is input from the cockpit, and the data required to visually recognize that location is read from the CPU and automatically There are other ways to point the camera to that location. These methods can realize an operation of automatically starting at the same time as displaying the abnormality and displaying the abnormal portion on the monitor television by interlocking with the abnormality alarm display section.

[0012]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS The configuration of the first embodiment of the present invention will be described with reference to FIGS. FIG. 1 is an overall configuration diagram of the first embodiment of the present invention. FIG. 2 is a block diagram of the first embodiment device of the present invention. FIG. 3 is a view showing a mounting state of the first embodiment device of the present invention.

According to the present invention, the detecting section 4 as means for monitoring the operation of each part of the aircraft 20 to detect an abnormality, and a signal from the detecting section 4 which is the means for detecting this, informs the cockpit of the abnormal portion. In an aircraft monitoring device including an abnormality monitoring display unit 6 as a means, an upper camera device 10 and a lower camera device 11, which are two TV camera devices, are provided on an outer wall of an aircraft body of the aircraft 20. A monitor TV 9 as a means for displaying the output image of the above in the cockpit, and a TV camera as a means for remotely controlling the angle of view of these two TV camera devices, the upper camera device 10 and the lower camera device 11, from the cockpit. The operation unit 8 is provided.

Further, in consideration of use at night, the upper camera device 10 and the lower camera device 11 have an infrared irradiator 19 as an infrared irradiating means. The monitor television 9 is of a cathode ray tube type or a liquid crystal type.

Next, the operation of the first embodiment device of the present invention will be described with reference to FIG. FIG. 4 is a flow chart showing the operation of the first embodiment of the present invention. When an abnormality occurs in the machine body, the detection unit 4 which is an abnormality detection unit detects the abnormality (S
1), an alarm is displayed on the abnormality notification panel 7 of the abnormality monitoring display unit 6 (S2). An upper camera device 10 and a lower camera device 11, which are external TV camera devices, and a TV camera operation unit 8 and a monitor TV 9 for remotely operating these devices.
Is automatically started, and the operator remotely operates the angle of view by the TV camera operating unit 8 (S3). Monitor tv 9
Displays an out-of-machine image (S4). Here, the operator in the cockpit determines whether the angle of view of the upper camera device 10 or the lower camera device 11 is correct, and if adjustment is necessary, readjusts it (S5).

Regarding the method of remotely operating the upper camera device 10 and the lower camera device 11, it is considered that the operator in the cockpit first determines whether the abnormal portion is the upper portion or the lower portion of the fuselage, and the abnormal portion is included in the angle of view. The television camera to be displayed is selected by the camera changeover switch 12. The device of the first embodiment of the present invention is configured so that it is automatically started together with an abnormal alarm display.

In the apparatus of the first embodiment of the present invention, the upper camera device 10 is provided with three television cameras, the upper left camera 16 and the upper right camera 17, and the lower camera device 11 is the lower camera 18. The angle of view of each camera is indicated by the digital display 1
4 and the analog display 15 are displayed. If the TV camera is correctly directed to the abnormal portion, the monitor TV 9 monitors the abnormal portion and determines the damage level, and based on the data, the aircraft is appropriately operated and the control tower is contacted.

Next, the television camera outside the machine will be described with reference to FIGS. FIG. 4 is a top view of the upper camera device 10. FIG. 5 is a side view of the upper camera device 10. FIG. 6 is a top view of the lower camera device 11. FIG. 7 is a side view of the lower camera device 11. The upper camera device 10 according to the first embodiment of the present invention, as shown in FIGS.
Two cameras on the left and right are mounted on one rotating pedestal so that the sides of the vertical tail can be seen from the left and right respectively. The movable range is ± 360 ° in the left / right direction and ± 9 in the up / down direction.
It is 0 °. As shown in FIG. 6, it is formed into a smooth protrusion and has a structure in which air resistance is minimized. Further, in consideration of use at night, two infrared irradiators 19 are provided on each of the left and right sides.

As shown in FIGS. 7 and 8, the lower camera device 11 of the first embodiment of the present invention is formed into a smooth projection like the upper camera device 10 and has a structure in which air resistance is minimized. There is only one camera. The reason is that there is no part in the lower part of the fuselage that requires visual recognition from the side like a vertical stabilizer. Like the upper camera device 10, the movable range is ± 360 ° in the left-right direction and ± 360 ° in the up-down direction.
It is 90 °. Further, an infrared irradiator 19 is provided in consideration of use at night.

Next, a second embodiment of the present invention will be described with reference to FIG. FIG. 9 is a block diagram of a second embodiment device of the present invention. A feature of the second embodiment of the present invention is that the switching of the television camera and the direction adjustment are automatically performed. It is the same as the first embodiment of the present invention in that the operator in the cockpit notices the abnormality alarm and visually recognizes the portion to be visually recognized by operating the TV camera operation unit 8, but the camera changeover switch of the first embodiment of the present invention 12
Instead of the up / down / left / right adjustment switch 13, the command input switch 21 is used in the second embodiment of the present invention. Servo motors controlled by a CPU are used for the left-right motor 23 and the up-down motor 24 of the upper camera device 10 and the lower camera device 11, and the CPU is made to store the position data in which a specified location can be visually recognized optimally by a program. Keep it. When the operation staff who notices the abnormal alarm turns on the command input switch 21 at a location corresponding to the abnormal location, the CPU reads the data required to direct the camera to that position, and the servo motor automatically causes the camera to Turn to the direction. After that, some fine adjustment of the camera viewing angle is performed by the up / down / left / right fine adjustment switch 22.

The advantage of the second embodiment of the present invention is that the burden on the operator can be reduced in an emergency in which the display of the abnormality notification panel 7 lights up. It is also possible to connect to the abnormality monitor display unit 6 and automatically display the abnormal portion on the monitor TV 9 at the same time as displaying the abnormality alarm.

Next, a third embodiment of the present invention will be described with reference to FIG. FIG. 10 is a block diagram of a third embodiment device of the present invention. A feature of the third embodiment of the present invention is that one monitor television 9, 9 ', 9 "is provided for each of the three cameras. The abnormality notification panel 7 connected to the television camera operation unit 8 is provided. The monitor televisions 9, 9 ′ and 9 ″ of the respective cameras are simultaneously activated when the display of “” is turned on.

An advantage of the third embodiment of the present invention is that up to three locations can be visually recognized on the monitor televisions 9, 9'and 9 "at the same time. Also, in combination with the second embodiment of the present invention, the abnormal location and its relation. It is also possible to have a structure in which three places can be visually recognized automatically at the same time.

In the first to third embodiments of the present invention, two camera devices, the upper and lower camera devices 10 and 11, are used, but the number of camera devices may be increased if necessary. Monitor televisions 9, 9 ', 9 "of the third embodiment of the present invention
The number of can also be increased if necessary. In addition, by making the lens of each camera have a wide angle, it is possible to omit the vertical control. The upper camera device 10 is configured to be used as binocular by switching between right and left. However, like the lower camera device 11, a monocular device may be installed at two positions on the left and right of the upper part of the machine body.

[0025]

Since the location where the abnormality is notified can be visually recognized from the inside of the cockpit, accurate information for emergency determination and flight control can be immediately obtained. In addition, it is possible to give a sense of security to the pilot because the abnormal part can be visually monitored.

[Brief description of drawings]

FIG. 1 is an overall configuration diagram of a first embodiment of the present invention.

FIG. 2 is a block diagram of an apparatus according to the first embodiment of the present invention.

FIG. 3 is a view showing a mounting state of the first embodiment device of the present invention.

FIG. 4 is a flowchart showing the operation of the first embodiment of the present invention.

FIG. 5 is a top view of the upper camera device according to the first embodiment of the present invention.

FIG. 6 is a side view of the upper camera device according to the first embodiment of the present invention.

FIG. 7 is a top view of the lower camera device according to the first embodiment of the present invention.

FIG. 8 is a side view of the lower camera device according to the first embodiment of the present invention.

FIG. 9 is a block diagram of a second embodiment device of the present invention.

FIG. 10 is a block diagram of a third embodiment device of the present invention.

FIG. 11 is an overall configuration diagram of a conventional example.

[Explanation of symbols]

 1 Control Command Section 2 I / O Section 3 Actuator Section 4 Detecting Section 5 Entity Section 6 Abnormality Monitoring Display Section 7 Abnormality Notification Panel 8 Television Camera Operating Section 9, 9 ', 9 "Monitor Television 10 Upper Camera Unit 11 Lower Camera Unit 12 Camera selector switch 13 Vertical / horizontal adjustment switch 14 Digital display 15 Analog display 16 Upper left camera 17 Upper right camera 18 Lower camera 19 Infrared irradiator 20 Aircraft 21 Command input switch 22 Vertical / horizontal fine adjustment switch 23 Horizontal motor 24 Vertical direction motor

Claims (5)

[Claims] 1. An aircraft monitoring device comprising means for monitoring the operation of each part of an aircraft to detect an abnormality, and means for notifying the cockpit of a location of the abnormality by a signal from the means for detecting the abnormality. At least one TV camera device is provided on the outer wall of the fuselage, and means for displaying an output image of the TV camera in the cockpit and means for remotely controlling the angle of view of the TV camera device from the cockpit are provided. Characteristic aircraft monitoring device. 2. The aircraft surveillance device according to claim 1, wherein the television camera device includes an infrared irradiation unit. 3. The aircraft monitoring device according to claim 1, wherein the television camera device includes a unit that is automatically activated by an output of the unit that detects the abnormality. 4. The aircraft monitoring apparatus according to claim 1, wherein the remote control means includes control means controlled by a CPU to direct the angle of view to the abnormal portion by the output of the means for detecting the abnormality. 5. The aircraft monitoring apparatus according to claim 1, wherein the means for displaying the image includes a display means for displaying outputs of a plurality of television cameras.