JPH05162695A - Pilot assisting device - Google Patents

Abstract

PURPOSE:To facilitate recovery from vertigo so as to improve safety by displaying a horizontal plane on an HUD display panel at the time of a pilot falling into vertigo. CONSTITUTION:An HUD control panel 4 is provided with a display mode change-over switch 5 for switching a normal display mode and an emergency display mode. When a pilot falls into vertigo, the display mode change-over switch 5 is operated to switch the normal display mode into the emergency display mode. With this change-over of the display mode, a digital computer 3 takes in information on the speed, altitude and attitude and the like of an airframe inputted through an A/D converter 1 to generate three-dimensional horizontal plane information, and outputs this information to a display processor 2 to display it on a CRT 6. The display image plane is reflected by a mirror 7, focused by a lens system 8 and projected to an HUD display panel 9. With the horizontal plane displayed on the display panel 9, the pilot can recognize the attitude of his own aircraft intuitively so as to recover from vertigo easily.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a pilot assisting device for assisting recovery from Vertigo in the event of a pilot or Vertigo (spatial disorientation).

[0002]

2. Description of the Related Art A HUD (Head Up Display) is a device mounted on an aircraft to assist a pilot in maneuvering. In this HUD, a transparent panel is placed immediately after the windshield at the position where the pilot can see through the front field of view, and necessary data and indicators, such as the altitude, speed, and attitude of the aircraft, are displayed to fix the gaze ahead. At the same time, the flight specifications can be read at the same time.

[0003]

The conventional HUD is designed to independently display information such as the altitude, speed, and attitude of the aircraft. Therefore, the pilot reads them and makes a comprehensive judgment, You have to know the status of the aircraft. There is no particular problem if the visibility is good and the actual horizon or topography such as mountains is visible, but if the ground surface object such as the horizon is not visible in the clouds or at night, the pilot will be unable to see ) May fall into. It is known that this Vertigo does not fall when the actual horizon or topography such as a mountain is visible, but falls when the ground surface object such as the horizon cannot be seen in the clouds or at night. When the pilot falls into a kind of panic state at the time of Vertigo, etc., it is extremely difficult to read the above various information from the HUD and comprehensively judge them.

The present invention has been made in view of the above circumstances, and it is an object of the present invention to provide a pilot assisting device capable of facilitating recovery from Vertigo and improving safety when the pilot falls into Vertigo. To do.

[0005]

A pilot assist device according to the present invention determines a display mode changeover switch for switching between a normal HUD display mode and an emergency display mode, and a display mode selected by this display mode changeover switch. Mode determining means, and means for displaying the speed information, altitude information, attitude information and the like of the machine body on the HUD display panel by reading the symbol, when the normal display mode is designated by the display mode changeover switch. When the emergency display mode is designated by the display mode changeover switch, horizontal plane display information is obtained based on the speed information, altitude information, attitude information, etc. of the aircraft, and coordinate conversion to the pilot viewpoint is performed to the HUD display panel. And a means for displaying a horizontal plane.

[0006]

When the normal display mode is selected by the display mode changeover switch, speed information, altitude information, attitude information and the like of the machine are symbolized and displayed on the HUD display panel. And when the pilot fell into Vertigo,
Operate the display mode selector switch to switch to the emergency display mode. In this emergency display mode, horizontal plane display information is obtained based on aircraft speed information, altitude information, attitude information, etc.
Further, coordinate conversion to the pilot viewpoint is performed to display a horizontal plane on the HUD display panel, for example, three-dimensionally. The pilot can intuitively understand the flight status of the aircraft from the horizontal plane displayed on the HUD display panel, and can easily recover from Vertigo.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described below with reference to the drawings. FIG. 1 is a block diagram of a HUD according to the present invention.

In FIG. 1, reference numeral 1 denotes an A / D converter, which inputs measurement information such as the speed, altitude, and attitude of an aircraft required by a pilot. The A / D converter 1 converts the measurement information into digital information, and inputs the digital information to the HUD digital computer 3 via the display processor 2.
A control panel 4 is connected to the digital computer 3. This control panel 4 has a display mode selector switch 5 together with various operation switches.
Is equipped with. The display mode changeover switch 5 is a switch for switching and designating the normal HUD display mode and the emergency display mode at the time of Vertigo.

The digital computer 3 is a normal HU.
In the D display mode, information such as the speed, altitude, and attitude (pitch attitude angle, roll attitude angle) of the aircraft input via the A / D converter 1 is captured and output to the display processor 2 for emergency display mode. Then, horizontal plane information is generated on the basis of the information such as the speed, altitude, and attitude of the body, and is output to the display processor 2. Display processor 2
In the normal display mode, information such as speed, altitude, and attitude sent from the digital computer 3 is symbolized and displayed on the CRT 6, and in the emergency display mode, the horizontal surface is sent by the horizontal surface information sent from the digital computer 3. Is displayed on the CRT 6.

The display screen of the CRT 6 is reflected by a mirror 7 arranged in front of the CRT 6, focused by a lens system 8 and projected on a HUD display panel 9. The HUD display panel 9 is configured by using, for example, a half mirror, is arranged inside the driver's seat window (front part) 10, and has a pilot 11
The panel projected image (symbol) can be viewed while being superimposed on the external view from the cockpit window 10.

In the above configuration, when the normal display mode is designated by the display mode changeover switch 5 of the control panel 4, the digital computer 3
Is a display processor 2 that captures information such as the speed, altitude, and attitude of the aircraft input via the A / D converter 1.
Is converted into a symbol by and displayed on the CRT 6. This CRT
The screen displayed at 6 is reflected in a specific direction by the mirror 7, focused by the lens system 8 and projected on the HUD display panel 9.

FIG. 2 shows H in this normal display mode.
9 shows a display example of a UD display panel 9. A speed display scale 21 is displayed on the left side of the display panel 9, an altitude display scale 22 is displayed on the right side, and an azimuth display scale 23 is displayed on the lower side, and the current state is indicated by an instruction mark M on each scale. Further, the own-machine symbol 24 is displayed at the center of the display panel 9 together with the attitude angle display bar 25. In the display example of FIG. 2, a horizontal flight (own aircraft) is performed at a speed of 450 knots (speed display scale 21) and an altitude of 5200 feet (altitude display scale 22) toward an azimuth of 0 degrees (true north, azimuth display scale 23). The symbol 24 and the posture angle display bar 25) are shown.

However, when the pilot falls into Vertigo (spatial disorientation), the pilot operates the display mode changeover switch 5 of the control panel 4 to switch from the normal display mode to the emergency display mode. When switched to the emergency display mode, the digital computer 3 captures information such as the speed, altitude, and attitude of the aircraft input via the A / D converter 1 to generate three-dimensional horizontal plane information. Then, it is output to the display processor 2, displayed on the CRT 6, and projected on the display panel 9. That is, in the emergency display mode,
As shown in FIG. 3, the horizontal plane 31 that would be seen from the position of the pilot at that time is three-dimensionally displayed on the display panel 9,
Help recovery from Vertigo.

The processing operation in the emergency display mode will be described below with reference to the flowchart of FIG. When the emergency display mode is designated, the digital computer 3 inputs the speed, altitude, and altitude of the aircraft input via the A / D converter 1.
Read necessary data such as posture (Step A)
1). Then, the digital computer 3 uses the inclination of the lattice plane, the lattice movement velocity,
The lattice spacing is calculated (step A2), and the coordinates are transformed into the lattice plane seen from the viewpoint of the pilot 11 (step A3). Then, the coordinate-converted information is output to the display processor 2, and the horizontal plane 31 is displayed on the HUD display panel 9 via the CRT 6, the mirror 7 and the lens system 8 (step A4). In this case, the pitch attitude angle,
Information on the roll posture angle is expressed by the inclination of the lattice plane as shown in FIG. In addition, the ground speed is roughly estimated from the aircraft speed and attitude, and the speed is expressed by moving the grid plane based on this, and the altitude is expressed by changing the grid interval from the altitude information.

In this state, the digital computer 3
It is judged whether or not the emergency display mode is switched to the normal display mode by operating the display mode changeover switch 5, and if the display mode is not switched, the above step A1 is performed.
The display control of the horizontal plane 31 is performed by repeating the processing of A4. The cycle of repeating steps A1 to A4 is sufficiently fast, for example, about 30 Hz so that the movement of the displayed horizontal plane (lattice surface) 31 does not make a person feel uncomfortable.
That is all. By displaying the horizontal plane 31 on the HUD display panel 9 in this manner, the pilot can intuitively recognize his / her own attitude and recovery from Vertigo becomes easy.

When the pilot recovers from Vertigo, the pilot operates the display mode changeover switch 5 to switch from the emergency display mode to the normal display mode. When switched to the normal display mode, the digital computer 3 detects the state in step A5, returns to the normal HUD display screen shown in FIG. 2, and terminates the processing in the emergency display mode.

In the above embodiment, the horizontal plane 31 is displayed three-dimensionally by the lattice plane. However, depending on the capability of the on-board computer, the three-dimensional topography can be calculated from the own-machine attitude information, the own-machine position information, and the map information. It is also possible to display.

[0018]

As described above in detail, according to the present invention, when the pilot falls into Vertigo (spatial disorientation), the H
Since the horizontal plane can be displayed on the UD display panel, the pilot can intuitively recognize the attitude of the aircraft, facilitate recovery from Vertigo, and improve safety.

[Brief description of drawings]

FIG. 1 is a diagram of a display example according to a first embodiment of the present invention.

FIG. 2 is a diagram showing a normal display example of a HUD.

FIG. 3 is a diagram of a configuration example of a HUD.

FIG. 4 is an example of a flowchart of this function.

[Explanation of symbols]

1 ... A / D converter, 2 ... Display processor, 3 ...
Digital computer, 4 ... Control panel,
5 ... Display mode changeover switch, 6 ... CRT, 7 ... Mirror, 8 ... Lens system, 9 ... HUD display panel, 10 ... Pilot window, 11 ... Pilot, 21 ... Speed display scale, 2
2 ... Altitude display scale, 23 ... Direction display scale, 24
… Self-opportunity symbol, 25… Attitude angle display bar, 31… Horizontal plane.

Claims (1)

[Claims] 1. A display mode changeover switch for switching between a normal HUD display mode and an emergency display mode, a mode judgment means for judging a display mode selected by the display mode changeover switch, and a normal mode by the display mode changeover switch. In the state in which the display mode is designated, the emergency display mode is designated by means for reading the speed information, altitude information, attitude information, etc. of the body and displaying them on the HUD display panel as symbols, and the display mode changeover switch. In the state, a means is provided for obtaining horizontal plane display information based on speed information, altitude information, attitude information, etc. of the airframe, and performing coordinate conversion to the pilot viewpoint to display the horizontal plane on the HUD display panel. Pilot aid equipment to do.