A method and apparatus for displaying flight path vectors

Abstract

This invention belongs to the field of avionics design technology in aviation, and relates to a method and device for displaying flight path vectors. By acquiring data such as the aircraft's roll angle, pitch angle, yaw angle, and flight path angle, and using the calculation method described in this patent, the flight path vector is displayed on the attitude indication area of ​​the integrated display. The pilot can intuitively observe the aircraft's expected position in space and the deviation between the expected position and the current position by observing the flight path vector displayed on the attitude indication area of ​​the integrated display.

Description

Technical Field

[0001] This invention belongs to the field of aviation technology and relates to a method and apparatus for displaying flight trajectory vectors. Background Technology

[0002] The flight path vector (FPV) is used to indicate the flight path angle (FPA) of an aircraft relative to the horizon and the deviation angle of the aircraft relative to the center of the pitch scale.

[0003] Pilots can visually observe the aircraft's actual position in space by observing the flight path vector displayed on the attitude indicator area of ​​the integrated display. Summary of the Invention

[0004] This invention provides a method and apparatus for displaying flight path vectors. By acquiring data such as the aircraft's roll angle, pitch angle, yaw angle, and flight path angle, and employing the calculation method described in this invention, the flight path vector is displayed on the attitude indication area of ​​the integrated display. The pilot can intuitively observe the aircraft's expected position in space and the deviation between the expected position and the current position by observing the flight path vector displayed on the attitude indication area of ​​the integrated display.

[0005] The first aspect of this invention provides a method for displaying flight track vectors, comprising:

[0006] Obtain the aircraft's pitch angle (R), roll angle (DA), flight path angle (FPA), and attitude sphere radius (R). ATT ;

[0007] Using formula and Obtain the actual coordinates (X, Y) of the flight path angle symbol in the attitude indication area of ​​the integrated display on the aircraft;

[0008] When the actual coordinates (X, Y) of the flight path angle symbol in the attitude indication area do not exceed the radius R of the attitude sphere ATT At that time, the flight path angle symbol is displayed in the attitude indication area of ​​the integrated display on the aircraft according to (X, Y).

[0009] Optionally, the method further includes:

[0010] When the actual coordinates (X, Y) of the flight path angle symbol in the attitude indication area exceed the radius R of the attitude sphere ATT At that time, the flight path angle symbol is displayed in the attitude indication area of ​​the integrated display on the aircraft according to (X′, Y′);

[0011] in,

[0012] Optional, attitude sphere radius RATT The size is determined based on the attitude indication area of ​​the integrated display on the aircraft.

[0013] Optionally, the aircraft pitch angle, roll angle R, yaw angle DA, and flight path angle FPA are obtained from onboard sensors.

[0014] A second aspect of the present invention provides a display device for flight track vectors, comprising:

[0015] The information acquisition module is used to acquire the aircraft's pitch angle (R), roll angle (R), yaw angle (DA), flight path angle (FPA), and attitude sphere radius (R). ATT ;

[0016] The coordinate acquisition module is used to obtain coordinates using formulas. and Obtain the actual coordinates (X, Y) of the flight path angle symbol in the attitude indication area of ​​the integrated display on the aircraft;

[0017] The display module is used when the actual coordinates (X, Y) of the flight path angle symbol in the attitude indication area do not exceed the radius R of the attitude sphere. ATT At that time, the flight path angle symbol is displayed in the attitude indication area of ​​the integrated display on the aircraft according to (X, Y).

[0018] Optionally, the display module is also used to display information when the actual coordinates (X, Y) of the flight track angle symbol in the attitude indication area exceed the radius R of the attitude sphere. ATT At that time, the flight path angle symbol is displayed in the attitude indication area of ​​the integrated display on the aircraft according to (X′, Y′);

[0019] in,

[0020] Optional, attitude sphere radius R ATT The size is determined based on the attitude indication area of ​​the integrated display on the aircraft.

[0021] Optionally, an information acquisition module is used to acquire the aircraft pitch angle, roll angle R, yaw angle DA, and flight path angle FPA from onboard sensors.

[0022] This invention provides a method and apparatus for displaying flight path vectors. By acquiring data such as the aircraft's roll angle, pitch angle, yaw angle, and flight path angle, and employing the calculation method described in this invention, the flight path vector is displayed on the attitude indication area of ​​the integrated display. The pilot can intuitively observe the aircraft's expected position in space and the deviation between the expected position and the current position by observing the flight path vector displayed on the attitude indication area of ​​the integrated display. Attached Figure Description

[0023] Figure 1This is a schematic diagram illustrating the principle of a flight track vector display method provided by the present invention. Detailed Implementation

[0024] The present invention will now be described in further detail with reference to the accompanying drawings:

[0025] like Figure 1 As shown, the solid line coordinate system is the screen coordinate system used to actually draw the flight path vector, with the horizontal and vertical axes representing pixel or distance offsets on the display screen, respectively. The dashed line coordinate system is the geographic coordinate system, with the horizontal axis representing the horizontal baseline and the vertical axis representing the vertical baseline.

[0026] This invention provides a method for displaying flight track vectors, comprising:

[0027] Obtain the aircraft's pitch angle (R), roll angle (DA), flight path angle (FPA), and attitude sphere radius (R). ATT ;

[0028] Using formula and Obtain the actual coordinates (X, Y) of the flight path angle symbol in the attitude indication area of ​​the integrated display on the aircraft;

[0029] When the actual coordinates (X, Y) of the flight path angle symbol in the attitude indication area do not exceed the radius R of the attitude sphere ATT At that time, the flight path angle symbol is displayed in the attitude indication area of ​​the integrated display on the aircraft according to (X, Y).

[0030] Optionally, the method further includes:

[0031] When the actual coordinates (X, Y) of the flight path angle symbol in the attitude indication area exceed the radius R of the attitude sphere ATT At that time, the flight path angle symbol is displayed in the attitude indication area of ​​the integrated display on the aircraft according to (X′, Y′);

[0032] in,

[0033] Optional, attitude sphere radius R ATT The size is determined based on the attitude indication area of ​​the integrated display on the aircraft.

[0034] Optionally, the aircraft pitch angle, roll angle R, yaw angle DA, and flight path angle FPA are obtained from onboard sensors.

[0035] For example, a method for calculating and displaying a flight track vector is as follows:

[0036] Let pitch be the aircraft's pitch angle, representing the current pitch magnitude of the aircraft, such as... Figure 1 As shown in the figure, a pitch scale is drawn, and the pitch of the aircraft in the figure is 10° downward.

[0037] The roll angle, R, represents the current roll magnitude of the aircraft; the yaw angle, DA, represents the angle between the aircraft's trajectory and heading; and the flight path angle, FPA, represents the angle of the aircraft's vertical profile relative to the horizontal plane. Pitch, R, DA, and FPA are all derived from measurements or calculations by the onboard navigation equipment. The radius of the attitude sphere in the integrated display's attitude indication area is R. ATT The actual position of the flight path angle displayed on the screen is Figure 1 Let the green symbol in the center have coordinates (X, Y) in the screen coordinate system. To obtain (X, Y), the following derivation and calculation are performed:

[0038]

[0039]

[0040] The actual coordinates of the flight track angle symbol in the attitude indication area are:

[0041] X R =ρ*cos(π / 2-α-R)+pitch*sin(R) Formula 3)

[0042] Y R =ρsin(π / 2-α-R)+pitch*cos(R) Formula 4)

[0043]

[0044] When the flight path angle symbol is in the actual coordinates (X) of the attitude zone R Y R When the flight path angle is within the range of the attitude sphere, the flight path angle symbol is determined according to (X). R Y R Displayed in the attitude area;

[0045] When the flight path angle symbol is in the actual coordinates (X) of the attitude zone R Y R When the value exceeds the range of the attitude sphere, it will be displayed on the attitude sphere, specifically (X). R ′, Y R The coordinates of ′) are calculated as follows:

[0046]

[0047] Combining formulas 1)-7), the actual coordinates (X, Y) of the flight path angle symbol in the attitude zone should be:

[0048] when but:

[0049]

[0050] when but:

[0051]

[0052]

Claims

1. A method of displaying flight path vectors, characterized by, The method further comprises: obtaining an aircraft pitch angle, a roll angle R, a drift angle DA, a flight path angle FPA and an attitude sphere radius R of the aircraft ATT ; The actual coordinates (X, Y) of the flight track angle symbol on the attitude indication area of the on-board comprehensive display are obtained by using formulas and . When the flight track angle symbol is not beyond the attitude sphere radius R at the actual coordinates (X, Y) of the attitude indication area ATT , the flight track angle symbol is displayed on the comprehensive display attitude indication area on the aircraft according to (X, Y).

2. The method of claim 1, wherein, The method further comprises: When the actual coordinates (X, Y) of the flight path angle symbol in the attitude indication area exceed the attitude sphere radius R ATT , the flight path angle symbol is displayed in the attitude indication area of the on-board integrated display , . wherein , , .

3. The method of claim 1, wherein, Attitude sphere radius R ATT Depends on the size of the attitude indicator on the aircraft.

4. The method of claim 1, wherein, The aircraft pitch, roll R, drift angle DA, flight path angle FPA are obtained from on-board sensors.

5. A display device for flight path vectoring, characterized in that The method further comprises: An information acquisition module is configured to acquire a pitch angle, a roll angle, a drift angle, a flight path angle, and a ball radius of an aircraft attitude of an aircraft ATT ; The coordinate acquisition module is configured to acquire actual coordinates (X, Y) of the attitude indication area of the on-board comprehensive display of the flight track angle symbol by using formulas and ​ A display module is used to display the flight path angle symbol on the attitude indication area on the screen when the actual coordinates (X, Y) of the flight path angle symbol in the attitude indication area do not exceed the attitude sphere radius R ATT .

6. The flight path vector display apparatus according to claim 5, wherein The display module is further configured to display the flight path angle symbol on the attitude indication area of the on-board integrated display when the actual coordinates (X, Y) of the flight path angle symbol in the attitude indication area exceed the attitude sphere radius R ATT . , ) wherein , , .

7. The flight path vector display apparatus according to claim 5, wherein Attitude sphere radius R ATT Depends on the size of the attitude indicator on the aircraft.

8. The flight path vector display apparatus according to claim 5, wherein The information obtaining module is configured to obtain the aircraft pitch, roll R, drift angle DA, flight path angle FPA from on-board sensors.

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