KR100654606B1 - Altitude calibration method for aircraft - Google Patents

Abstract

The present invention uses a center position display rod vertically installed at a predetermined position on a runway center line, and four position display rods positioned at right angles to each other at a predetermined distance from the center position display rod. In the aircraft altitude correction method using a first altitude measuring device and a second altitude measuring device provided on the ground at a predetermined distance at a right angle, and an external central processing unit wirelessly connected to the altitude measuring device, the first and second altitudes A first step of photographing an aircraft at a time passing through the center position display rod through a measuring device; A second step of transmitting image information photographed through the first and second altitude measuring devices to the central processing unit; The central processing unit reads the angle θ ₁ formed between the central position indicating rod and the aircraft centering on the first altitude measuring device using the image information of the first altitude measuring device, and the second altitude measuring device. A third step of reading a projection angle (θ ₂ ) formed by the second altitude measuring device and the aircraft about the center position indicating rod using the image information of the center; A fourth step of the central processing unit calculating the altitude value of the aircraft using the angle of angle (θ ₁ ) and the projection angle (θ ₂ ) using a triangulation method; A fifth step of the central processing unit determining whether the calculated altitude value of the aircraft and the numerical value of the altimeter received from the aircraft coincide; A sixth step of sending, by the central processing unit, a signal to the aircraft to correct the numerical value of the aircraft altimeter to the altitude value when the altitude value and the numerical value of the altimeter do not match; And the seventh step of modifying the numerical value of the altimeter to the altitude value according to the correction signal.

Aircraft, altitude correction, altitude measuring device

Description

Altitude calibration method for aircraft

1 is a perspective view showing an altitude measurement system according to the present invention.

Figure 2 is an exemplary view for explaining the altitude measurement according to the present invention.

3 is an exemplary view showing an example of using the altitude measuring device according to the present invention.

Figure 4 is an illustration showing another example using the altitude measuring device according to the present invention.

5 is a perspective view showing an example of the altitude measurement using the altitude measurement system according to the present invention.

Figure 6a is an exemplary view for explaining a method for measuring the altitude using the altitude measuring apparatus according to the present invention.

Figure 6b is another exemplary view for explaining a method for measuring the altitude using the altitude measuring apparatus according to the present invention.

7 is a flowchart illustrating an altitude correction method according to the present invention.

*** Explanation of main parts of drawing ***

10, 20: Altitude measurement device 11: side level

12, 22: rear level indicator 13-1, 13-2, 23-1, 23-2: right angle adjustment indicator

14, 24: leveling plate 15, 25: base of the altitude measuring device

16, 26: altitude angle display portion 30: center position indicator rod

40, 50: longitudinal position indicating rod 60, 70: transverse position indicating rod

80: runway centerline

The present invention relates to an aircraft altitude calibration method for calibrating an aircraft altimeter, and more particularly, to an aircraft altitude calibration method for calibrating an altimeter of an aircraft by easily measuring the altitude of an aircraft using two or more altitude measuring devices on the ground.

The altimeter mounted on the aircraft uses a pressure altimeter, such as an anroid altimeter, which measures altitude when measuring the strength of the pressure using the property that atmospheric pressure decreases as the height rises above sea level. It is an altimeter. However, since this altitude is only the height from sea level, not the height from the ground, a radio altimeter is used with a pressure altimeter to indicate the height from the ground, which reflects radio waves emitted from the aircraft to the ground. Measure altitude by measuring the time to come.

Among these altimeters, the pressure altimeter simply displays the atmospheric pressure as a highly converted value, and does not indicate altitude or absolute altitude depending on the terrain, nor does it display changes in altitude due to changes in temperature, humidity, and barometric pressure. Do not.

Therefore, since the altitude value displayed by the aircraft altimeter shows a lot of difference from the actual altitude, most aircraft correct the altitude value of the altimeter through flight test.

Conventionally, a method used to measure a static pressure in a place where the trailing cone or bomb is dragged 50 meters behind the aircraft and there is no influence on the flight of the aircraft, but it is quite cumbersome and is difficult to run on the runway or the aircraft. The situation was often uncomfortable and very uncomfortable.

In addition, in case of ground measurement, people measure the height of passage at the point where the aircraft passes by using the measurement tool with the grid pattern in two places, and then use the method to reduce the error compared with the altimeter of the aircraft. .

However, using the naked eye, the accuracy of the measurement of the passing height of the aircraft is inferior, and even if the aircraft passes through the back of the measurement point without passing through the measurement reference point accurately, the same passing height is checked, so that the reliable altitude cannot be measured. .

In addition, the altimeter of the aircraft is a method of measuring the static pressure of the atmosphere, and since the measurement pressure is changed according to the position measured by the aircraft, it is necessary to test the altimeter calibration using a correction device.

The present invention has been made to solve the above problems, and an object of the present invention is to provide a method for safely performing an aircraft altitude correction test without being affected by the condition of the aircraft and the test location.

SUMMARY OF THE INVENTION An object of the present invention is to provide a method for measuring accurate altitude directly from the ground, without having to attach an accessory to the aircraft for altitude correction of the aircraft's altimeter.

Another object of the present invention is to provide a method for automatically measuring the altitude measurement of the aircraft by using an automatic measuring device rather than the naked eye.

The present invention for achieving the above object is the center by using a central position display rod vertically installed at a predetermined position on the runway center line, four position display rods positioned at right angles to each other with respect to the central position display rod. In the aircraft altitude correction method using a first altitude measuring device and a second altitude measuring device provided on the ground at a predetermined distance perpendicular to each other with respect to the position indicating rod, and an external central processing unit wirelessly connected to the altitude measuring device, A first step of photographing an aircraft at a time when it passes over the center position indicating rod through the first and second altitude measuring devices; A second step of transmitting image information photographed through the first and second altitude measuring devices to the central processing unit; The central processing unit reads the angle θ ₁ formed between the central position indicating rod and the aircraft centering on the first altitude measuring device using the image information of the first altitude measuring device, and the second altitude measuring device. A third step of reading a projection angle (θ ₂ ) formed by the second altitude measuring device and the aircraft about the center position indicating rod using the image information of the center; A fourth step of the central processing unit calculating the altitude value of the aircraft using the angle of angle (θ ₁ ) and the projection angle (θ ₂ ) using a triangulation method; A fifth step of the central processing unit determining whether the calculated altitude value of the aircraft and the numerical value of the altimeter received from the aircraft coincide; A sixth step in which the central processing unit sends a signal to the aircraft to correct the numerical value of the aircraft altimeter to the altitude value if the altitude value and the numerical value of the altimeter do not match; And the seventh step of modifying the numerical value of the altimeter to the altitude value according to the correction signal.

Hereinafter, with reference to the accompanying drawings will be described in detail a preferred embodiment of the present invention.

1 is a perspective view of an altitude measurement system installed for altitude correction according to the present invention.

As shown in FIG. 1, the altitude measuring system according to the present invention includes an altitude measuring device 10 and 20, a central position indicating rod 30, a longitudinal position indicating rod 40 and 50, and a transverse position indicating rod. Consists of (60, 70), the central position indicator rod 30 is installed perpendicular to the ground at any position of the center line 80 of the runway, the longitudinal direction of the runway relative to the center position indicator rod 30 The longitudinal position indicator rods 40 and 50 are provided at predetermined distances on both sides thereof. In addition, a central processing unit (not shown), such as a mobile computer wirelessly connected to the altitude measuring apparatuses 10 and 20, is separately provided.

After the longitudinal position indicating rods 40 and 50 are installed at both sides, the transverse position indicating rods 60 and 70 are positioned at both sides in the transverse direction of the runway with respect to the central position indicating rod 30. Each is installed.

After the lateral position indicator rods 60 and 70 are installed, the altitude measuring device 10 is installed at a predetermined distance by the extension lines of the lateral position indicator rods 60 and 70, and the longitudinal position indicator rods 40 and 50 are provided. The altitude measuring device 20 is installed at a predetermined distance on an extension line of the. Here, the altitude measuring device 10, 20 is installed vertically and horizontally with respect to the ground, respectively.

The altitude measuring device 10, 20 is provided with respect to the side level (11, 21), the back level (12, 22), the right angle indicator (13-1, 13-2, 23-1, 23-2) and the ground, respectively. It is provided with horizontal control plates 14 and 24 for accurately installing the altitude measuring devices 10 and 20 horizontally, pedestals 15 and 25 of the altitude measuring device, and altitude angle display parts 16 and 26, as in a camcorder. Equipped with a function of recording time-synchronized image during measurement, recording image information related to the altitude measurement displayed through the elevation display unit 16 or 26 to an internally mounted recording device, or recording the image information into a wireless communication method. To the central processing unit.

With the altitude measuring system installed, the longitudinal position indicating rods 40 and 50 and the lateral position indicating rods 60 and 70 are used to determine whether the altitude measuring apparatuses 10 and 20 are located on the runway at right angles to each other. Check if the altitude measuring device 10, 20 is perpendicular to each other.

A method of checking whether the altitude measuring apparatuses 10 and 20 are perpendicular to each other will be described with reference to FIG. 3.

3 is an exemplary view showing an example of using the altitude measuring device according to the present invention, as shown in FIG. 3, through the right angle adjustment indicators 13-1 and 13-2 of the altitude measuring device 10. In order that the directional position indicator rods 40 and 50 can be observed, that is, through the right angle adjustment indicator 13-1, the longitudinal position indicator rod 50 is observed coinciding with the center scale and the right angle adjustment indicator 13-2 is observed. Through the altitude measuring device 10 is installed on the ground so that the longitudinal position indicator 40 is observed in accordance with the center scale.

When the altitude measuring device 10 is installed on the ground, the altitude measuring device 10 is installed horizontally with respect to the ground by using the horizontal control plate 14 installed on the lower side with respect to the levels 12 and 14.

In the same manner as in the altitude measuring apparatus 10 shown in FIG. 3, the altitude measuring apparatus 20 on the runway is positioned in the lateral position indicating rod 70 through the right angle adjustment indicator 23-1 as shown in FIG. 4. The altitude measuring device 20 is installed on the ground so that the horizontal position indicator rod 60 is observed in accordance with the center scale through the right angle adjustment indicator 23-2. Here, the altitude measuring device 20 is horizontal to the ground using the horizontal leveling plate 24 installed on the lower side with respect to the level 21 (not shown) and the level 22 as in the altitude measuring device 10. Is installed.

As such, when the altitude measuring apparatuses 10 and 20 are installed, the altitude measuring apparatuses 10 and 20 mean that the altitude measuring apparatuses 10 and 20 are positioned at right angles with respect to the center position indicating rod 30. Therefore, the altitude measuring device (10, 20) is located at right angles to each other, so the altitude angle of the aircraft can be easily known through the altitude measuring device (10, 20), the center position display of the aircraft installed at a specific point of the runway The altitude of the aircraft is measured by flying the air above the rod 30, and the altitude of the aircraft is measured by the altitude.

Hereinafter, a method of measuring and correcting an altitude of an aircraft using the altitude measuring apparatuses 10 and 20 will be described with reference to FIGS. 5 to 7.

5 is a perspective view showing an example of the altitude measurement using the altitude measurement system according to the present invention, the altitude measuring apparatus 10, 20 respectively photographed the aircraft at the time passing through the center position bar 30, the aircraft Record the image to measure altitude.

As shown in FIG. 5, when the aircraft passes over the center position bar 30, a specific portion of the aircraft as shown in FIG. 6A through the elevation angle display unit 16 of the altitude measuring device 10, For example, when the part where the positive pressure hole of the aircraft is positioned passes over the center position bar 30 is photographed at the same time through the altitude angle display unit 26 of the altitude measuring device 20 as shown in Figure 6b Is photographed.

When the aircraft passes the point E above the center position bar 30 and passes the point E, the projection point D of the aircraft and the position E of the aircraft are based on the position A of the altitude measuring device 10. The angle θ ₁ is measured in the included right triangle using the altitude measuring device 10, and the right triangle including the C and D points at which the central position indicating rod 30 is positioned based on the altitude measuring device 20, which is the B point. Measure the angle θ ₂ by using the altitude measuring device (20).

As an embodiment of the present invention, θ ₁ and θ ₂ are measured through a scale as shown in FIGS. 6A and 6B, and specifically, based on the altitude measuring device 20 as shown in FIG. 2. If the lateral position indicators 60 and 70 are separated by a distance of 1 km, respectively, and the position indicators 60 and 70 are separated from each other by 17.45 m, the angle between them is 1 °.

Therefore, if the position indicating rods 60 and 70 are separated from each other by 17.45 m and the distance measuring rods 60 and 70 are each 1 km away from the altitude measuring device 20, the aircraft photographed in FIG. It is a state which deviates by 0.25 degree from the center position display rod 30 which is phosphorus, and (theta) ₂ is 0.25 degree.

θ ₁ is also the same as θ _2, and the aircraft photographed in FIG. 6A is the seventh scale on the scale, which is the distance DA between the position A of the altitude measuring device 10 and the projected point D of the aircraft. Is located at an angle of between 1.75 ° and, θ ₁ is therefore 1.75 °.

After measuring θ ₁ and θ ₂ in this manner, the length (CD) is calculated by referring to the length BC between the central position indicating rod 30 and the altitude measuring device 20 designated as the predetermined length. Available through

CD = BC tanθ ₂ (1)

Then the distance AD between the altitude measuring device 10 and the D point is

AD = AC-CD (2)

Can be found, the height (DE) from the D point to the aircraft

DE = AD tanθ ₁ (3)

Finally, the absolute altitude (h) of the aircraft is

h = h ₀ + DE (4)

Where h is the absolute altitude of the aircraft, h ₀ is the absolute altitude of the altitude measuring device (10).

In this manner, the altitude of the aircraft is calculated using the altitude measuring apparatus 10 or 20 of the present invention, and the calculated altitude value is compared with the recording value of the altimeter of the aircraft to correct the error to the altimeter.

In the altitude correction method of the present invention, an observer can manually measure the altitude of the aircraft using the altitude measuring apparatus 10 and 20 and compare the altitude calculation with the recorded value of the altimeter of the aircraft to directly correct the altitude of the aircraft altimeter. However, in this embodiment, the altitude measuring device 10 and 20 and a central processing unit (not shown) wirelessly connected to the aircraft may be automatically measured and corrected by the altitude of the aircraft.

As described above, a method of automatically correcting the altitude of the aircraft will be described with reference to FIG. 7.

7 is a flowchart illustrating a method for adjusting the altitude according to the present invention. As shown in FIG. 1, longitudinal position indicating rods 40 and 50 and horizontal position indicating rods (a center position indicating rod 30 are shown in FIG. 1). 60, 70 are installed at right angles to each other, using the display rods 40, 50, 60, 70, the altitude measuring apparatus 10, 20 is installed at right angles with respect to the central position display rod 30, respectively. (S701).

After the altitude measuring devices 10 and 20 are installed at right angles with respect to the center position bar 30, respectively, the aircraft flies over the center position bar 30 as shown in FIG. Using the altitude measuring device (10, 20) photographs the aircraft passing through the point of the central position bar (30) (S702).

At this time, the altitude measuring device (10, 20) is wirelessly connected to an external central processing unit (not shown), respectively, the altitude information of the photographed aircraft, for example, as shown in Figures 6a and 6b 10:20 Simultaneously recorded image information is sent to the central processing unit in 3 minutes, and the central processing unit reads the received image information to determine angles for knowing the altitude of the aircraft, for example, θ ₁ and θ ₂ shown in FIG. It measures (S703).

After reading the image information and measuring the angle to know the altitude of the aircraft, the central processing unit uses the triangulation method to calculate the altitude of the aircraft using the measured angle as in the above-described calculation process of equations (1) to (4). The absolute altitude of the aircraft is calculated (S704).

After calculating the absolute altitude of the aircraft, the central processing unit records the aircraft's altitude recorder, that is, the aircraft altimeter at the time when shooting the aircraft passing the point of the central position indicator 30 using the altitude measuring device (10, 20) The received numerical value is received, and it is determined whether the transmitted altitude value matches the absolute altitude value of the calculation process (S704) (S705).

If the determination result of the determination process (S705) does not match each other, the central processing unit transmits a signal to the aircraft to correct the numerical value of the aircraft altimeter to the absolute altitude value passed through the calculation process (S704) (S706). When the correction signal is received by the aircraft, the aircraft corrects the numerical value of the aircraft altimeter in accordance with the correction signal.

If the determination result of the determination process (S705) is consistent with each other, the central processing unit sends a signal to the aircraft to confirm that the altimeter of the aircraft is normal to maintain the function of the aircraft altimeter.

The technical spirit of the present invention has been described in detail according to the preferred embodiment, but the above embodiments are for the purpose of explanation, in addition to the above-described method of measuring the altitude measurement device by two, the central position display rod 30 Note that altitude measurements can be measured more clearly by installing four altitude measuring devices in four directions each. In addition, those skilled in the art will understand that various implementations are possible within the scope of the technical idea of the present invention.

As described above, the present invention can provide a method of calibrating an altimeter of an aircraft by accurately measuring the altitude of the aircraft on the ground without installing an additional device on the aircraft to calibrate the altimeter of the aircraft.

The present invention can be automatically corrected by measuring the altitude of the aircraft clearly without being affected by the environment of the aircraft altitude measurement site.

Claims (6)

delete  The center position bar is installed vertically at a predetermined position on a runway center line, and the four position bars are positioned at right angles to each other at a predetermined distance with respect to the center position bar. In the aircraft altitude correction method using a first altitude measuring device and a second altitude measuring device provided on the ground at a distance, and an external central processing unit wirelessly connected to the altitude measuring device, A first step of photographing an aircraft at a time when it passes over the center position indicating rod through the first and second altitude measuring devices; A second step of transmitting image information photographed through the first and second altitude measuring devices to the central processing unit; The central processing unit reads the angle θ ₁ formed between the central position indicating rod and the aircraft centering on the first altitude measuring device using the image information of the first altitude measuring device, and the second altitude measuring device. A third step of reading a projection angle (θ ₂ ) formed by the second altitude measuring device and the aircraft about the center position indicating rod using the image information of the center; A fourth step of the central processing unit calculating the altitude value of the aircraft using the angle of angle (θ ₁ ) and the projection angle (θ ₂ ) using a triangulation method; A fifth step of the central processing unit determining whether the calculated altitude value of the aircraft and the numerical value of the altimeter received from the aircraft coincide; A sixth step in which the central processing unit sends a signal to the aircraft to correct the numerical value of the aircraft altimeter to the altitude value if the altitude value and the numerical value of the altimeter do not match; And In the aircraft altitude correction method comprising a seventh step of modifying the value of the altimeter to the altitude value in accordance with the correction signal, And the image information includes image information displayed on a screen consisting of unit angle scales capable of measuring the angle of angle (θ ₁ ) and the angle of projection (θ ₂ ). The altimeter of the first altitude measuring device, the second altitude measuring device, and the aircraft is synchronized in time, and transmits the tuned image information and the numerical value of the altimeter to the central processing unit. Aircraft altitude correction method. 4. The method of claim 3, wherein when the altitude value and the altimeter coincide with each other in the sixth step, the central processing unit transmits a signal indicating that the altimeter of the aircraft is normal to the aircraft. Aircraft altitude correction method further comprising. The method of claim 4, wherein the fourth step comprises: the projection angle θ ₂ , the angle θ ₁ , the distance BC between the center position indicating rod C and the second altitude measuring device B, And using the distance AD between the projection point D of the aircraft and the first altitude measuring device A, CD = BC tanθ ₂ (1) The distance CD between the center position bar C and the projection point D of the aircraft is obtained, and the distance AD between the first altitude measuring device A and the D point is AD = AC-CD (2) Height (DE) from point D to an aircraft DE = AD tanθ ₁ (3) Finally, the absolute altitude (h) of the aircraft is h = h ₀ + DE (4) Calculating an absolute altitude h of the aircraft using a triangulation method, and h ₀ is the absolute altitude of the first altitude measuring device A. 6. The apparatus of claim 5, further comprising a third altitude measuring device and a fourth altitude measuring device which are symmetrical to the first and second altitude measuring devices about the center position indicating rod. 6. Aircraft Altitude Correction Method.

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