Aircraft navigation component course ground revision method and device

Abstract

The invention belongs to the technical field of aeronautical manufacturing aircraft debugging, and relates to an aircraft navigation component course ground revision method and device. Comprising the following steps: selecting a measurement datum line on the ground, and determining an included angle between the measurement datum line and a true north direction; measuring the course of the aircraft, and determining an included angle between the course of the aircraft and the measurement datum line; according to the included angle between the measurement datum line and the true north direction and the included angle between the course of the aircraft and the measurement datum line, obtaining a true course angle of the aircraft; acquiring an aircraft course angle value output by a navigation component on the aircraft; determining a revised angle value of the navigation component; and compensating the revised angle value into the airborne navigation component, so that the course of the navigation component is consistent with the course of the airplane.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft debugging in aviation manufacturing, and relates to a method and a device for ground correction of the heading of an aircraft navigation component. Background Art

[0002] During the ground assembly and debugging process of aircraft manufacturing, the consistency between the heading of the aircraft's internal navigation components and the aircraft's heading often troubles aircraft debugging personnel. The aircraft's navigation components are installed inside the aircraft (such as the aircraft's inertial navigation components, which are generally located at or near the center of gravity of the aircraft). During debugging, it is required that the heading measured and calculated by the navigation components coincide with the aircraft's heading to ensure the accuracy of navigation and positioning.

[0003] During debugging at the current stage, the heading arrow on the surface of the navigation component is used, and a ruler is used to measure and calculate the parallelism between the center line of the arrow and the reference heading inside the aircraft. Based on the results, the software compensation angle in the navigation component is revised to meet the requirements. Due to errors in the measurement of the center line of the arrow, the reference heading, and the ruler, the heading of the navigation component is not consistent with the heading of the aircraft, and the efficiency is low. Summary of the invention

[0004] Technical problem solved by the present invention: In order to solve the problem of low accuracy and low efficiency in ground correction of heading of aircraft navigation components, the technical solution of the present invention proposes a method for ground correction of heading of aircraft navigation components.

[0005] The technical solution of the present invention:

[0006] In a first aspect, the present invention provides a method for ground correction of a heading of an aircraft navigation component, the method comprising:

[0007] Step 1: Select a measurement reference line on the ground and determine the angle between the measurement reference line and the true north direction;

[0008] Step 2: Measure the heading of the aircraft and determine the angle between the heading of the aircraft and the measurement reference line;

[0009] Step 3: Obtaining the true heading angle of the aircraft according to the angle between the measurement reference line and the true north direction, and the angle between the heading of the aircraft and the measurement reference line;

[0010] Step 4: Obtain the aircraft heading angle value output by the navigation component on the aircraft;

[0011] Step 5: Determine a revised angle value of the navigation component according to the true heading angle of the aircraft and the aircraft heading angle value output by the navigation component;

[0012] Step 6: Compensate the revised angle value into the onboard navigation component so that the heading of the navigation component is consistent with the heading of the aircraft.

[0013] Furthermore, step one is specifically as follows:

[0014] Select a measurement reference point on the ground, select a point within the visible range of the aircraft as the measurement azimuth point, and measure the angle α between the measurement reference point and the measurement reference line connecting the measurement reference point and the measurement azimuth point and the true north direction.

[0015] Furthermore, step 2 is specifically as follows:

[0016] According to the aircraft design requirements, the specified measurement points are selected on the outside of the aircraft, and the straight line where the aircraft's heading is located is measured using a laser tracker. The aircraft's heading L is determined with the nose as the positive direction, and the angle β between the aircraft's heading L and the measurement reference line is measured using a laser tracker.

[0017] Furthermore, step three is specifically as follows:

[0018] The actual heading angle of the aircraft γ = β-α.

[0019] Furthermore, step five is specifically as follows:

[0020] According to the actual heading angle γ of the aircraft and the heading angle value δ of the aircraft output by the navigation component, a revised angle value Δ=γ-δ of the navigation component is determined.

[0021] In a second aspect, the present invention further provides a device for ground correction of a heading of an aircraft navigation component, the device being used to implement the method described in the first aspect, the device comprising:

[0022] The aircraft true heading angle measurement module is used to select a measurement reference line on the ground and determine the angle between the measurement reference line and the true north direction; measure the heading of the aircraft and determine the angle between the heading of the aircraft and the measurement reference line; obtain the true heading angle of the aircraft according to the angle between the measurement reference line and the true north direction and the angle between the heading of the aircraft and the measurement reference line;

[0023] Acquisition module, used to obtain the aircraft heading angle value output by the navigation component

[0024] A determination module, used to determine a revised angle value of the navigation component according to the true heading angle of the aircraft and the aircraft heading angle value output by the navigation component;

[0025] The compensation module is used to compensate the revised angle value into the onboard navigation component so that the heading of the navigation component is consistent with the heading of the aircraft.

[0026] Furthermore, the determination module is used to determine a revised angle value Δ=γ-δ of the navigation component according to the actual heading angle γ of the aircraft and the aircraft heading angle value δ output by the navigation component.

[0027] This method uses the outside of the aircraft to calculate the heading, which improves the accuracy and precision of the aircraft reference heading compared to the original method, and uses the true north of the earth as the reference benchmark. The benchmark is unified and stable, the calculation principle is simple, and the debugging accuracy and efficiency are greatly improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of ground reference points, azimuth points, and true north measurement;

[0029] Figure 2 It is a debugging and measurement schematic diagram;

[0030] Wherein: 1-aircraft heading or its extension line, 2-measurement reference line, α-angle between measurement reference line and true north, β-angle between measurement reference line and aircraft heading. DETAILED DESCRIPTION

[0031] The technical solution of the present invention is described in detail below with reference to the accompanying drawings.

[0032] The present invention provides a method for ground correction of the heading of an aircraft navigation component, which achieves unification by calculating the true heading angle of the aircraft and feeding it back to the system software. The method comprises the following steps:

[0033] Combined with Figure 1-2 A method for ground revision of the heading of an aircraft navigation component is provided. With the true north as the reference point, points are selected on the ground (one point is located outside the work plant, and the other point is located inside the plant) to measure the angle between the straight line connected to the true north, and the angle between the straight line where the aircraft heading is located and the straight line connected to the ground points is measured. The angle between the aircraft heading and the true north is obtained by calculation, and compared with the aircraft angle given by the inertial navigation, the required compensation amount is calculated, and then the software compensation angle in the navigation component is revised to meet the requirements. The method includes the following steps:

[0034] Step 1: Measure the angle α between the measurement reference line and the true north direction on the ground;

[0035] Step 2: Select a point outside the aircraft to measure the aircraft heading L according to the aircraft heading measurement requirements;

[0036] Step 3: Use a laser tracker (or similar product) to measure and calculate the angle β between 1 and 2;

[0037] Step 4: Figure 2 For example, the true heading angle of the aircraft can be calculated as: "heading angle γ = β-α";

[0038] Step 5: The airborne navigation component system is powered on, and the heading angle value δ of the current position determined by the navigation component is obtained based on the internal calculation of the airborne device;

[0039] Step 6: Compare the actual heading angle γ of the aircraft with the current heading angle δ of the component solved by the navigation component, so the navigation component needs to compensate for the revised angle value Δ=γ-δ;

[0040] Step 7: By compensating the Δ value in the onboard navigation component, the consistency between the navigation component heading and the aircraft heading can be ensured.

[0041] Step 1 is as follows:

[0042] Select a suitable point on the ground as the measurement reference point, select a visible point near the aircraft as the measurement azimuth point, and measure the angle α between the straight line connecting the measurement reference point and the measurement azimuth point and the true north direction.

[0043] Step 2 is as follows:

[0044] According to the aircraft design requirements, the specified measurement points are selected on the outside of the aircraft, and the straight line where the aircraft's heading is located is measured using a laser tracker (or other equivalent equipment), and the aircraft's heading L is determined with the nose as the positive direction.

[0045] Step three is as follows:

[0046] Use a laser tracker (or other equivalent equipment) to measure and calculate the angle β between the aircraft heading L and the measurement reference line.

[0047] Step 4 is as follows:

[0048] The aircraft's heading relative to true north is calculated according to the formula, which is the difference between the angle between the straight line connecting the measurement reference point and the measurement azimuth point and the true north direction and the angle between the aircraft's heading L and the measurement reference line, that is, γ = β-α.

[0049] Step 5 is as follows:

[0050] The onboard navigation component operates and obtains the heading angle value δ of the current position determined by the navigation component through the internal gyroscope (or other equivalent components).

[0051] Step 6 is as follows:

[0052] Compare the actual heading angle γ of the aircraft with the current heading angle δ calculated by the navigation component, so the navigation component needs to compensate for the revised angle value Δ=γ-δ.

[0053] Step 7 is as follows:

[0054] The Δ value compensation is revised into the onboard navigation component to ensure the consistency of the navigation component heading with the aircraft heading.

[0055] The present invention discloses a method for ground revision of the heading of an aircraft navigation component. By adopting the true north of the earth as a reference datum, the heading parallelism inspection work inside the aircraft is reasonably and effectively adjusted to be carried out outside the aircraft, thereby meeting the aircraft debugging accuracy requirements and effectively ensuring the accuracy of the airborne navigation components.

Claims

1. A method for revising the heading of an aircraft navigation component on the ground, characterized in that: The method comprises: Step 1: Select a measurement reference line on the ground and determine the angle between the measurement reference line and the true north direction; Step 2: Measure the heading of the aircraft and determine the angle between the heading of the aircraft and the measurement reference line; Step 3: Obtaining the true heading angle of the aircraft according to the angle between the measurement reference line and the true north direction, and the angle between the heading of the aircraft and the measurement reference line; Step 4: Obtain the aircraft heading angle value output by the navigation component on the aircraft; Step 5: Determine a revised angle value of the navigation component according to the true heading angle of the aircraft and the aircraft heading angle value output by the navigation component; Step 6: Compensate the revised angle value into the onboard navigation component so that the heading of the navigation component is consistent with the heading of the aircraft.

2. A method for ground correction of aircraft navigation component heading according to claim 1, characterized in that: Step 1 is as follows: Select a measurement reference point on the ground, select a point within the visible range of the aircraft as the measurement azimuth point, and measure the angle α between the measurement reference point and the measurement reference line connecting the measurement reference point and the measurement azimuth point and the true north direction.

3. A method for ground correction of aircraft navigation component heading according to claim 2, characterized in that: Step 2 is as follows: According to the aircraft design requirements, the specified measurement points are selected on the outside of the aircraft, and the straight line where the aircraft's heading is located is measured using a laser tracker. The aircraft's heading L is determined with the nose as the positive direction, and the angle β between the aircraft's heading L and the measurement reference line is measured using a laser tracker.

4. A method for ground correction of the heading of an aircraft navigation component according to claim 3, characterized in that: Step three is as follows: The actual heading angle of the aircraft γ = β-α.

5. A method for ground correction of aircraft navigation component heading according to claim 4, characterized in that: Step 5 is as follows: According to the actual heading angle γ of the aircraft and the heading angle value δ of the aircraft output by the navigation component, a revised angle value Δ=γ-δ of the navigation component is determined.

6. A device for revising the heading of an aircraft navigation component on the ground, characterized in that: The device is used to implement the method according to any one of claims 1 to 5, and the device includes: The aircraft true heading angle measurement module is used to select a measurement reference line on the ground and determine the angle between the measurement reference line and the true north direction; measure the heading of the aircraft and determine the angle between the heading of the aircraft and the measurement reference line; obtain the true heading angle of the aircraft according to the angle between the measurement reference line and the true north direction and the angle between the heading of the aircraft and the measurement reference line; Acquisition module, used to obtain the aircraft heading angle value output by the navigation component A determination module, used to determine a revised angle value of the navigation component according to the true heading angle of the aircraft and the aircraft heading angle value output by the navigation component; The compensation module is used to compensate the revised angle value into the onboard navigation component so that the heading of the navigation component is consistent with the heading of the aircraft.

7. The device for correcting the heading of an aircraft navigation component on the ground according to claim 6, characterized in that: The determination module is used to determine the revised angle value Δ=γ-δ of the navigation component according to the actual heading angle γ of the aircraft and the aircraft heading angle value δ output by the navigation component.

8. An aircraft, characterized in that: The aircraft is loaded with a device according to any one of claims 1-7.

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