Deformation detection method in maintenance operation of light aircraft wing

Abstract

The invention discloses a deformation detection method in light aircraft wing maintenance operation, and relates to the technical field of wing maintenance, and the detection method comprises the following process steps: building a three-dimensional reference coordinate system for normal wings of the same specification; in a three-dimensional reference coordinate system of a normal wing, key points capable of representing important structure positions of the wing are determined, and coordinate values of the key points in the three-dimensional reference coordinate system are obtained; establishing a three-dimensional reference coordinate system for the maintained wing by taking a normal wing as a benchmark; the method comprises the following steps: determining key points capable of representing important structure positions of a wing in a three-dimensional reference coordinate system of a maintained wing by taking a normal wing as a benchmark, and obtaining coordinate values of the key points in the three-dimensional reference coordinate system; and by taking a normal wing as a reference, comparing the coordinate values of the key points on the maintained wing with the coordinate values of the key points on the normal wing in a one-to-one correspondence manner, so as to obtain a deformation result of the maintained wing. According to the invention, wing deformation can be objectively detected, and the accuracy and precision are high.

Description

Technical Field

[0001] The invention relates to the technical field of wing maintenance, and in particular to a deformation detection method in a light aircraft wing maintenance operation. Background Art

[0002] Light aircraft have a fuselage length of about 6 to 8 meters, a height of about 2.3 to 2.8 meters, a wingspan of about 8 to 11 meters, an empty weight of about 350 to 500 kg, and about 2 to 6 seats, such as the Cessna 172 or PA-44-180 aircraft. These aircraft are the main primary trainer aircraft for civil aviation pilot training around the world.

[0003] During the pilot training process, due to improper operation of the pilot, emergencies such as over-limit flight, hard landing, and runway overrun are prone to occur, resulting in damage and deformation of the wings of light aircraft. As the key component of the aircraft, the wing damage repair work is particularly important.

[0004] The main structure of the wing is as follows Figure 1 As shown, it includes components such as wing spars, wing ribs 4, stringers 5, skins and mounting joints. The wing is connected to the fuselage through the mounting joints. The wing spars serve as the main load-bearing structure of the wing, including the front wing spars 1, the rear wing spars 2 and the tail wing spars 3. The wing ribs 4 are connected to the wing spars and the skins to maintain the aerodynamic shape of the skins and ensure the aerodynamic force transmission between the skins, stringers 4 and wing spars. The stringers 5 are located above the wing ribs 4 and support the skins together with the wing ribs 4 to ensure the aerodynamic shape of the skins. The skins cover the wing ribs 4 and stringers 5 to form the surface of the wing.

[0005] At present, in the process of repairing light aircraft wing damage, visual judgment or the use of tools such as spirit levels and rulers to measure the distortion of the wing are usually adopted. The damage and deformation are assessed only by the experience of the maintenance personnel. This subjective judgment makes it difficult to accurately identify and control the damage and deformation, and is only suitable for repairing minor damage such as local deformation of the wing structure. For major damage such as overall deformation of the wing, it is impossible to accurately detect it and it cannot be repaired, so the whole wing can only be replaced. Summary of the invention

[0006] The technical purpose of the present invention is to provide a deformation detection method for light aircraft wing maintenance operations with high wing deformation detection accuracy in view of the particularity of the above-mentioned light aircraft and the shortcomings of the prior art.

[0007] The technical solution adopted by the present invention is as follows: A method for detecting deformation during maintenance of a wing of a light aircraft, the method comprising the following process steps: Step 1. Establish a three-dimensional reference coordinate system for a normal wing of the same specification; Step 2. In the three-dimensional reference coordinate system of a normal wing, determine the key points that can characterize the important structural positions of the wing, and obtain the coordinate values ​​of each key point in the three-dimensional reference coordinate system; Step 3. Using the normal wing as a reference, establish a three-dimensional reference coordinate system for the repaired wing; Step 4. Taking the normal wing as a reference, determine the key points that can characterize the important structural positions of the wing in the three-dimensional reference coordinate system of the repaired wing, and obtain the coordinate values ​​of each key point in the three-dimensional reference coordinate system; Step 5. Taking the normal wing as the reference, compare the coordinate values ​​of each key point on the repair wing with those of each key point on the normal wing one by one to obtain the deformation result of the repair wing.

[0008] The above technical measures establish a three-dimensional reference coordinate system for the normal wing and determine the key points and the coordinate values ​​of the key points. Taking the normal wing as a reference, a three-dimensional reference coordinate system is established for the maintenance wing, and the key points and the coordinate values ​​of the key points are determined. This can ensure that the key points on the normal wing and the maintenance wing are comparable, which is beneficial to improving the accuracy and reliability of detection. By comparing the coordinate values ​​of the key points on the maintenance wing with those of the key points on the normal wing one by one, the deformation result of the maintenance wing is obtained, and the deformation of the maintenance wing can be accurately evaluated, which is beneficial to improving the accuracy and precision of detection.

[0009] Furthermore, in step 1 and step 3, the process of establishing the three-dimensional reference coordinate system is: S1. At the rear spar mounting joint of the wing, take the center of the front end surface of the mounting hole as the first reference point, named point O; At the front spar mounting joint of the wing, the center of the front end surface of the mounting hole is used as the second reference point, named point O1; On the upper surface of the intersection of the wing rib and the rear spar at position 23.65WS of the wing, the center of the rivet head is used as the third reference point, named point A; On the upper surface of the intersection of the wing rib and the rear spar at position 71.125WS of the wing, the center of the rivet head is used as the fourth reference point, named point B; S2. Take point O as the origin of the coordinate system; The line connecting point O and point O1 is the X-axis, and the positive direction is the leading edge of the wing; Translate the line connecting point A and point B until point A coincides with point O, so that point B becomes point Bˊ, with the line connecting point 0 and point Bˊ as the Y axis, the positive direction being the direction of the wing tip, and the line connecting point 0 and point Bˊ being perpendicular to the line connecting point O and point O1; The XOY plane is established by the line connecting point O and point O1 and the line connecting point 0 and point Bˊ; S3. Establish the Z axis on the XOY plane using the right-hand screw rule to create a three-dimensional reference coordinate system.

[0010] The above-mentioned technical measures take into account the structural characteristics and stress conditions of the wing by establishing a three-dimensional reference coordinate system based on four reference points, which is conducive to improving the accuracy of the three-dimensional reference coordinate system; by establishing a three-dimensional reference coordinate system, accurate measurement of the coordinate values ​​of each key point can be achieved, which is conducive to improving the accuracy of detection.

[0011] Furthermore, in step 2 and step 4, the key points that can characterize the important structural positions of the wing are determined according to the following rules: 23 rivets were selected on the upper and lower surfaces of the wing, with their centers as key points; The 23 rivets on the upper surface of the wing are named as follows: The rivet on the upper surface of the intersection of the 85.875WS rib and the front wing spar is named K1; The rivet on the upper surface of the intersection of the 85.875WS rib and the rear spar of the wing is named C1; The rivet on the upper surface of the intersection of the 100.50WS rib and the front spar of the wing is named L1; The rivet on the upper surface of the intersection of the 100.50WS rib and the rear spar of the wing is named D1; The rivet on the upper surface of the intersection of the 100.50WS rib and the wing tail beam is named T1; The rivet on the upper surface of the intersection of the 118.00WS rib and the front spar of the wing is named M1; The rivet on the upper surface of the intersection of the 118.00WS rib and the rear spar of the wing is named E1; The rivet on the upper surface of the intersection of the 118.00WS wing rib and the wing tail spar is named U1; The rivet on the upper surface of the intersection of the 136.00WS rib and the front spar of the wing is named N1; The rivet on the upper surface of the intersection of the 136.00WS wing rib and the rear wing spar is named F1; The rivet on the upper surface of the intersection of the 136.00WS wing rib and the wing tail spar is named V1; The rivet on the upper surface of the intersection of the 154.00WS rib and the front spar of the wing is named P1; The rivet on the upper surface of the intersection of the 154.00WS wing rib and the rear wing spar is named G1; The rivet on the upper surface of the intersection of the 154.00WS wing rib and the wing tail spar is named W1; The rivet on the upper surface of the intersection of the 172.00WS rib and the front spar of the wing is named Q1; The rivet on the upper surface of the intersection of the 172.00WS wing rib and the rear wing spar is named H1; The rivet on the upper surface of the intersection of the 172.00WS wing rib and the wing tail beam is named X1; The rivet on the upper surface of the intersection of the 190.00WS rib and the front spar of the wing is named R1; The rivet on the upper surface of the intersection of the 190.00WS rib and the rear spar of the wing is named I1; The rivet on the upper surface of the intersection of the 190.00WS rib and the wing tail beam is named Y1; The rivet on the upper surface of the intersection of the 208.00WS rib and the front spar of the wing is named S1; The rivet on the upper surface of the intersection of the 208.00WS wing rib and the rear wing spar is named J1; The rivet on the upper surface of the intersection of the 208.00WS rib and the wing tail beam is named Z1; The 23 rivets on the lower surface of the wing and their names are determined as follows: The rivet on the lower surface of the intersection of the 85.875WS rib and the front wing spar is named K2; The rivet on the lower surface of the 85.875WS rib and the rear spar of the wing is named C2; The rivet on the lower surface of the intersection of the 100.50WS rib and the front spar of the wing is named L2; The rivet on the lower surface of the intersection of the 100.50WS wing rib and the rear wing spar is named D2; The rivet on the lower surface of the intersection of the 100.50WS rib and the wing tail beam is named T2; The rivet on the lower surface of the intersection of the 118.00WS rib and the front spar of the wing is named M2; The rivet on the lower surface of the 118.00WS rib and the rear spar of the wing is named E2 position; The rivet on the lower surface of the intersection of the 118.00WS rib and the wing tail beam is named U2; The rivet on the lower surface of the intersection of the 136.00WS rib and the front spar of the wing is named N2; The rivet on the lower surface of the intersection of the 136.00WS wing rib and the rear wing spar is named F2; The rivet on the lower surface of the intersection of the 136.00WS rib and the wing tail spar is named V2; The rivet on the lower surface of the intersection of the 154.00WS rib and the front spar of the wing is named P2; The rivet on the lower surface of the intersection of the 154.00WS wing rib and the rear wing spar is named G2 position; The rivet on the lower surface of the intersection of the 154.00WS wing rib and the wing tail spar is named W2 position; The rivet on the lower surface of the intersection of the 172.00WS rib and the front spar of the wing is named Q2; The rivet on the lower surface of the intersection of the 172.00WS rib and the rear spar of the wing is named H2; The rivet on the lower surface of the intersection of the 172.00WS wing rib and the wing tail beam is named X2; The rivet on the lower surface of the intersection of the 190.00WS rib and the front spar of the wing is named R2; The rivet on the lower surface of the intersection of the 190.00WS rib and the rear spar of the wing is named I2; The rivet on the lower surface of the intersection of the 190.00WS rib and the wing tail spar is named Y2; The rivet on the lower surface of the intersection of the 208.00WS rib and the front spar of the wing is named S2; The rivet on the lower surface of the intersection of the 208.00WS wing rib and the rear wing spar is named J2; The rivet on the lower surface of the intersection of the 208.00WS rib and the wing tail beam is named Z2.

[0012] The above technical measures can expand the detection range of wing deformation by selecting rivets at specific positions on the upper and lower surfaces of the wing as key points, which is conducive to improving the comprehensiveness and effectiveness of detection.

[0013] Furthermore, in step 2 and step 4, the coordinate values ​​of each key point in the three-dimensional reference coordinate system are obtained as follows: Step ①. Measure the absolute three-dimensional coordinate values ​​of the corresponding key points; Step ②. Convert the absolute three-dimensional coordinate values ​​of the corresponding key points into relative coordinate values ​​in the three-dimensional reference coordinate system.

[0014] The above technical measures convert the absolute three-dimensional coordinate values ​​of the corresponding key points into relative coordinate values ​​in the three-dimensional reference coordinate system, so that the coordinates of all key points are based on the same three-dimensional reference coordinate system, making each key point easy to understand and process, which is conducive to improving convenience.

[0015] Furthermore, in step ①, the absolute three-dimensional coordinate values ​​of the key points are obtained by measuring with a laser tracker.

[0016] The above technical measures measure the absolute three-dimensional coordinate values ​​of key points through a laser tracker, which is conducive to improving accuracy.

[0017] Furthermore, in step ②, the absolute three-dimensional coordinate values ​​of the key points are converted into relative coordinate values ​​in a three-dimensional reference coordinate system by Polyworks software.

[0018] The above technical measures convert the absolute three-dimensional coordinate values ​​of key points into relative coordinate values ​​in a three-dimensional reference coordinate system through Polyworks software, which is conducive to improving convenience and accuracy.

[0019] Furthermore, the light aircraft is a Cessna 172 aircraft or a PA-44-180 aircraft.

[0020] One or more technical solutions provided by the present invention have at least the following technical effects or advantages: The present invention establishes a three-dimensional reference coordinate system for a normal wing, determines key points and coordinate values ​​of the key points, takes the normal wing as a reference, establishes a three-dimensional reference coordinate system for a maintenance wing, and determines key points and coordinate values ​​of the key points, thereby ensuring that key points on the normal wing and the maintenance wing are comparable, which is beneficial to improving detection accuracy and reliability; by comparing the coordinate values ​​of key points on the maintenance wing with those of key points on the normal wing in one-to-one correspondence, the deformation result of the maintenance wing is obtained, the deformation condition of the maintenance wing can be accurately evaluated, and is beneficial to improving detection accuracy and precision. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The drawings described herein are used to provide a further understanding of the embodiments of the present invention, constitute a part of the present invention, and do not constitute a limitation on the embodiments of the present invention; Figure 1 It is a schematic diagram of the structure of a light aircraft wing; Figure 2 It is a schematic flow chart of a deformation detection method in a light aircraft wing maintenance operation in the present invention; Figure 3 It is a schematic diagram of reference point selection in the present invention; Figure 4 is a schematic diagram of establishing a three-dimensional reference coordinate system in the present invention; Figure 5 Schematic diagram of selecting key points on the upper surface of the wing in the present invention; Figure 6 It is a schematic diagram of the key point selection of the lower surface of the wing in the present invention; Among them, 1-front wing beam; 2-rear wing beam; 3-tail wing beam; 4-wing rib; 5-stringer. DETAILED DESCRIPTION

[0022] In order to more clearly understand the above-mentioned purpose, features and advantages of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that the embodiments of the present invention and the features in the embodiments can be combined with each other without conflict.

[0023] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those within the scope of this description. Therefore, the protection scope of the present invention is not limited to the specific embodiments disclosed below.

[0024] Reference Figure 2-6 This embodiment provides a method for detecting deformation in a light aircraft wing maintenance operation, wherein the light aircraft involved refers to a primary training aircraft such as a Cessna 172 aircraft or a PA-44-180 aircraft.

[0025] The detection method includes the following process steps: Step 1. Establish a three-dimensional reference coordinate system for a normal wing of the same specification; The process of establishing a three-dimensional reference coordinate system is: S1. At the rear spar mounting joint of the wing, take the center of the front end surface of the mounting hole as the first reference point, named point O; At the front spar mounting joint of the wing, the center of the front end surface of the mounting hole is used as the second reference point, named point O1; On the upper surface of the intersection of the wing rib and the rear spar at position 23.65WS of the wing, the center of the rivet head is used as the third reference point, named point A; On the upper surface of the intersection of the wing rib and the rear spar at position 71.125WS of the wing, the center of the rivet head is used as the fourth reference point, named point B; S2. Take point O as the origin of the coordinate system; The line connecting point O and point O1 is the X-axis, and the positive direction is the leading edge of the wing; Translate the line connecting point A and point B until point A coincides with point O, so that point B becomes point Bˊ, with the line connecting point 0 and point Bˊ as the Y axis, the positive direction being the direction of the wing tip, and the line connecting point 0 and point Bˊ being perpendicular to the line connecting point O and point O1; The XOY plane is established by the line connecting point O and point O1 and the line connecting point 0 and point Bˊ; S3. Establish the Z axis on the XOY plane using the right-hand screw rule to create a three-dimensional reference coordinate system.

[0026] Among them, the right-hand spiral rule is the right-hand rule in the three-dimensional coordinate system, the leading edge of the wing refers to the edge of the front end of the wing, and the direction of the leading edge of the wing refers to the flight direction of the aircraft.

[0027] Step 2. In the three-dimensional reference coordinate system of a normal wing, determine the key points that can characterize the important structural positions of the wing, and obtain the coordinate values ​​of each key point in the three-dimensional reference coordinate system; The key points that can characterize the important structural positions of the wing are determined according to the following rules: 23 rivets were selected on the upper and lower surfaces of the wing, with their centers as key points; The 23 rivets on the upper surface of the wing are named as follows: The rivet on the upper surface of the intersection of the 85.875WS rib and the front wing spar is named K1; The rivet on the upper surface of the intersection of the 85.875WS rib and the rear spar of the wing is named C1; The rivet on the upper surface of the intersection of the 100.50WS rib and the front spar of the wing is named L1; The rivet on the upper surface of the intersection of the 100.50WS rib and the rear spar of the wing is named D1; The rivet on the upper surface of the intersection of the 100.50WS rib and the wing tail beam is named T1; The rivet on the upper surface of the intersection of the 118.00WS rib and the front spar of the wing is named M1; The rivet on the upper surface of the intersection of the 118.00WS rib and the rear spar of the wing is named E1; The rivet on the upper surface of the intersection of the 118.00WS wing rib and the wing tail spar is named U1; The rivet on the upper surface of the intersection of the 136.00WS rib and the front spar of the wing is named N1; The rivet on the upper surface of the intersection of the 136.00WS wing rib and the rear wing spar is named F1; The rivet on the upper surface of the intersection of the 136.00WS wing rib and the wing tail spar is named V1; The rivet on the upper surface of the intersection of the 154.00WS rib and the front spar of the wing is named P1; The rivet on the upper surface of the intersection of the 154.00WS wing rib and the rear wing spar is named G1; The rivet on the upper surface of the intersection of the 154.00WS wing rib and the wing tail spar is named W1; The rivet on the upper surface of the intersection of the 172.00WS rib and the front spar of the wing is named Q1; The rivet on the upper surface of the intersection of the 172.00WS wing rib and the rear wing spar is named H1; The rivet on the upper surface of the intersection of the 172.00WS wing rib and the wing tail beam is named X1; The rivet on the upper surface of the intersection of the 190.00WS rib and the front spar of the wing is named R1; The rivet on the upper surface of the intersection of the 190.00WS rib and the rear spar of the wing is named I1; The rivet on the upper surface of the intersection of the 190.00WS rib and the wing tail beam is named Y1; The rivet on the upper surface of the intersection of the 208.00WS rib and the front spar of the wing is named S1; The rivet on the upper surface of the intersection of the 208.00WS wing rib and the rear wing spar is named J1; The rivet on the upper surface of the intersection of the 208.00WS rib and the wing tail beam is named Z1; The 23 rivets on the lower surface of the wing and their names are determined as follows: The rivet on the lower surface of the intersection of the 85.875WS rib and the front wing spar is named K2; The rivet on the lower surface of the 85.875WS rib and the rear spar of the wing is named C2; The rivet on the lower surface of the intersection of the 100.50WS rib and the front spar of the wing is named L2; The rivet on the lower surface of the intersection of the 100.50WS wing rib and the rear wing spar is named D2; The rivet on the lower surface of the intersection of the 100.50WS rib and the wing tail beam is named T2; The rivet on the lower surface of the intersection of the 118.00WS rib and the front spar of the wing is named M2; The rivet on the lower surface of the 118.00WS rib and the rear spar of the wing is named E2 position; The rivet on the lower surface of the intersection of the 118.00WS rib and the wing tail beam is named U2; The rivet on the lower surface of the intersection of the 136.00WS rib and the front spar of the wing is named N2; The rivet on the lower surface of the intersection of the 136.00WS wing rib and the rear wing spar is named F2; The rivet on the lower surface of the intersection of the 136.00WS rib and the wing tail spar is named V2; The rivet on the lower surface of the intersection of the 154.00WS rib and the front spar of the wing is named P2; The rivet on the lower surface of the intersection of the 154.00WS wing rib and the rear wing spar is named G2 position; The rivet on the lower surface of the intersection of the 154.00WS wing rib and the wing tail spar is named W2 position; The rivet on the lower surface of the intersection of the 172.00WS rib and the front spar of the wing is named Q2; The rivet on the lower surface of the intersection of the 172.00WS rib and the rear spar of the wing is named H2; The rivet on the lower surface of the intersection of the 172.00WS wing rib and the wing tail spar is named X2; The rivet on the lower surface of the intersection of the 190.00WS rib and the front spar of the wing is named R2; The rivet on the lower surface of the intersection of the 190.00WS rib and the rear spar of the wing is named I2; The rivet on the lower surface of the intersection of the 190.00WS rib and the wing tail beam is named Y2; The rivet on the lower surface of the intersection of the 208.00WS rib and the front spar of the wing is named S2; The rivet on the lower surface of the intersection of the 208.00WS wing rib and the rear wing spar is named J2; The rivet on the lower surface of the 208.00WS rib and the wing tail beam intersection is named Z2 position.

[0028] Among them, data such as 208.00WS and 172.00WS are all station positions (i.e. data that characterize the position), which are measured perpendicular to the leading edge of the wing.

[0029] The coordinate values ​​of each key point in the three-dimensional reference coordinate system are obtained as follows: Step ①. Measure the absolute three-dimensional coordinate values ​​of the corresponding key points; Step ②. Convert the absolute three-dimensional coordinate values ​​of the corresponding key points into relative coordinate values ​​in the three-dimensional reference coordinate system.

[0030] In step ①, the absolute three-dimensional coordinate values ​​of the key points are obtained by measuring with a laser tracker.

[0031] In step ②, the absolute three-dimensional coordinate values ​​of the key points are converted into relative coordinate values ​​in the three-dimensional reference coordinate system by Polyworks software.

[0032] The relative coordinate value refers to the coordinate value of each key point relative to the three-dimensional reference coordinate system of the normal wing.

[0033] Step 3. Using the normal wing as a reference, establish a three-dimensional reference coordinate system for the repaired wing; The process of establishing a three-dimensional reference coordinate system is: S1. At the rear spar mounting joint of the wing, take the center of the front end surface of the mounting hole as the first reference point, named point O; At the front spar mounting joint of the wing, the center of the front end surface of the mounting hole is used as the second reference point, named point O1; On the upper surface of the intersection of the wing rib and the rear spar at position 23.65WS of the wing, the center of the rivet head is used as the third reference point, named point A; On the upper surface of the intersection of the wing rib and the rear spar at position 71.125WS of the wing, the center of the rivet head is used as the fourth reference point, named point B; S2. Take point O as the origin of the coordinate system; The line connecting point O and point O1 is the X-axis, and the positive direction is the leading edge of the wing; Translate the line connecting point A and point B until point A coincides with point O, so that point B becomes point Bˊ, with the line connecting point 0 and point Bˊ as the Y axis, the positive direction being the direction of the wing tip, and the line connecting point 0 and point Bˊ being perpendicular to the line connecting point O and point O1; The XOY plane is established by the line connecting point O and point O1 and the line connecting point 0 and point Bˊ; S3. Establish the Z axis on the XOY plane using the right-hand screw rule to create a three-dimensional reference coordinate system.

[0034] Among them, the right-hand spiral rule is the right-hand rule in the three-dimensional coordinate system, and the three-dimensional reference coordinate system of the maintenance wing corresponds to the three-dimensional reference coordinate system of the normal wing.

[0035] Step 4. Taking the normal wing as a reference, determine the key points that can characterize the important structural positions of the wing in the three-dimensional reference coordinate system of the repaired wing, and obtain the coordinate values ​​of each key point in the three-dimensional reference coordinate system; The key points that can characterize the important structural positions of the wing are determined according to the following rules: 23 rivets were selected on the upper and lower surfaces of the wing, with their centers as key points; The 23 rivets on the upper surface of the wing are named as follows: The rivet on the upper surface of the intersection of the 85.875WS rib and the front wing spar is named K1; The rivet on the upper surface of the intersection of the 85.875WS rib and the rear spar of the wing is named C1; The rivet on the upper surface of the intersection of the 100.50WS rib and the front spar of the wing is named L1; The rivet on the upper surface of the intersection of the 100.50WS rib and the rear spar of the wing is named D1; The rivet on the upper surface of the intersection of the 100.50WS rib and the wing tail beam is named T1; The rivet on the upper surface of the intersection of the 118.00WS rib and the front spar of the wing is named M1; The rivet on the upper surface of the intersection of the 118.00WS rib and the rear spar of the wing is named E1; The rivet on the upper surface of the intersection of the 118.00WS wing rib and the wing tail spar is named U1; The rivet on the upper surface of the intersection of the 136.00WS rib and the front spar of the wing is named N1; The rivet on the upper surface of the intersection of the 136.00WS wing rib and the rear wing spar is named F1; The rivet on the upper surface of the intersection of the 136.00WS wing rib and the wing tail spar is named V1; The rivet on the upper surface of the intersection of the 154.00WS rib and the front spar of the wing is named P1; The rivet on the upper surface of the intersection of the 154.00WS wing rib and the rear wing spar is named G1; The rivet on the upper surface of the intersection of the 154.00WS wing rib and the wing tail spar is named W1; The rivet on the upper surface of the intersection of the 172.00WS rib and the front spar of the wing is named Q1; The rivet on the upper surface of the intersection of the 172.00WS wing rib and the rear wing spar is named H1; The rivet on the upper surface of the intersection of the 172.00WS wing rib and the wing tail beam is named X1; The rivet on the upper surface of the intersection of the 190.00WS rib and the front spar of the wing is named R1; The rivet on the upper surface of the intersection of the 190.00WS rib and the rear spar of the wing is named I1; The rivet on the upper surface of the intersection of the 190.00WS rib and the wing tail beam is named Y1; The rivet on the upper surface of the intersection of the 208.00WS rib and the front spar of the wing is named S1; The rivet on the upper surface of the intersection of the 208.00WS wing rib and the rear wing spar is named J1; The rivet on the upper surface of the intersection of the 208.00WS rib and the wing tail beam is named Z1; The 23 rivets on the lower surface of the wing and their names are determined as follows: The rivet on the lower surface of the intersection of the 85.875WS rib and the front wing spar is named K2; The rivet on the lower surface of the 85.875WS rib and the rear spar of the wing is named C2; The rivet on the lower surface of the intersection of the 100.50WS rib and the front spar of the wing is named L2; The rivet on the lower surface of the intersection of the 100.50WS wing rib and the rear wing spar is named D2; The rivet on the lower surface of the intersection of the 100.50WS rib and the wing tail beam is named T2; The rivet on the lower surface of the intersection of the 118.00WS rib and the front spar of the wing is named M2; The rivet on the lower surface of the 118.00WS rib and the rear spar of the wing is named E2 position; The rivet on the lower surface of the intersection of the 118.00WS rib and the wing tail beam is named U2; The rivet on the lower surface of the intersection of the 136.00WS rib and the front spar of the wing is named N2; The rivet on the lower surface of the intersection of the 136.00WS wing rib and the rear wing spar is named F2; The rivet on the lower surface of the intersection of the 136.00WS rib and the wing tail spar is named V2; The rivet on the lower surface of the intersection of the 154.00WS rib and the front spar of the wing is named P2; The rivet on the lower surface of the intersection of the 154.00WS wing rib and the rear wing spar is named G2 position; The rivet on the lower surface of the intersection of the 154.00WS wing rib and the wing tail spar is named W2 position; The rivet on the lower surface of the intersection of the 172.00WS rib and the front spar of the wing is named Q2; The rivet on the lower surface of the intersection of the 172.00WS rib and the rear spar of the wing is named H2; The rivet on the lower surface of the intersection of the 172.00WS wing rib and the wing tail beam is named X2; The rivet on the lower surface of the intersection of the 190.00WS rib and the front spar of the wing is named R2; The rivet on the lower surface of the intersection of the 190.00WS rib and the rear spar of the wing is named I2; The rivet on the lower surface of the intersection of the 190.00WS rib and the wing tail spar is named Y2; The rivet on the lower surface of the intersection of the 208.00WS rib and the front spar of the wing is named S2; The rivet on the lower surface of the intersection of the 208.00WS wing rib and the rear wing spar is named J2; The rivet on the lower surface of the intersection of the 208.00WS rib and the wing tail beam is named Z2.

[0036] Among them, data such as 208.00WS and 172.00WS are all station positions (i.e. data that characterize the position), which are measured perpendicular to the leading edge of the wing.

[0037] The coordinate values ​​of each key point in the three-dimensional reference coordinate system are obtained as follows: Step ①. Measure the absolute three-dimensional coordinate values ​​of the corresponding key points; Step ②. Convert the absolute three-dimensional coordinate values ​​of the corresponding key points into relative coordinate values ​​in the three-dimensional reference coordinate system.

[0038] In step ①, the absolute three-dimensional coordinate values ​​of the key points are obtained by measuring with a laser tracker.

[0039] In step ②, the absolute three-dimensional coordinate values ​​of the key points are converted into relative coordinate values ​​in the three-dimensional reference coordinate system by Polyworks software.

[0040] Among them, the relative coordinate value refers to the coordinate value of each key point relative to the three-dimensional reference coordinate system of the maintenance wing. The key points that can represent the important structural positions of the maintenance wing correspond one-to-one with the key points that can represent the important structural positions of the normal wing.

[0041] Step 5. Taking the normal wing as the reference, compare the coordinate values ​​of each key point on the repair wing with those of each key point on the normal wing one by one to obtain the deformation result of the repair wing.

[0042] For example, the coordinate value of one of the key points of a normal wing is expressed as [X1, Y1, Z1], and the coordinate value of the corresponding key point of the repair wing is expressed as [X2, Y2, Z2]. By calculating and analyzing the {[X1, Y1, Z1]- [X2, Y2, Z2]} value, the deformation of the repair wing is detected, and an allowable error range is preset. When the {[X1, Y1, Z1]-[X2, Y2, Z2]} value exceeds the allowable error range, replacement and other operations are required during the repair process of the repair wing. Through repeated adjustments and replacements, the repair wing meets the requirements.

[0043] Although the preferred embodiments of the present invention have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0044] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A method for detecting deformation in light aircraft wing maintenance operations, characterized in that: The detection method comprises the following process steps: Step 1. Establish a three-dimensional reference coordinate system for a normal wing of the same specification; Step 2. In the three-dimensional reference coordinate system of a normal wing, determine the key points that can characterize the important structural positions of the wing, and obtain the coordinate values ​​of each key point in the three-dimensional reference coordinate system; Step 3. Using the normal wing as a reference, establish a three-dimensional reference coordinate system for the repaired wing; Step 4. Taking the normal wing as a reference, determine the key points that can characterize the important structural positions of the wing in the three-dimensional reference coordinate system of the repaired wing, and obtain the coordinate values ​​of each key point in the three-dimensional reference coordinate system; Step 5. Taking the normal wing as the reference, compare the coordinate values ​​of each key point on the repair wing with those of each key point on the normal wing one by one to obtain the deformation result of the repair wing.

2. The method for detecting deformation in light aircraft wing maintenance work according to claim 1, characterized in that: In step 1 and step 3, the process of establishing the three-dimensional reference coordinate system is: S1. At the rear spar mounting joint of the wing, take the center of the front end surface of the mounting hole as the first reference point, named point O; At the front spar mounting joint of the wing, the center of the front end surface of the mounting hole is used as the second reference point, named point O1; On the upper surface of the intersection of the wing rib and the rear spar at position 23.65WS of the wing, the center of the rivet head is used as the third reference point, named point A; On the upper surface of the intersection of the wing rib and the rear spar at position 71.125WS of the wing, the center of the rivet head is used as the fourth reference point, named point B; S2. Take point O as the origin of the coordinate system; The line connecting point O and point O1 is the X-axis, and the positive direction is the leading edge of the wing; Translate the line connecting point A and point B until point A coincides with point O, so that point B becomes point Bˊ, with the line connecting point 0 and point Bˊ as the Y axis, the positive direction being the direction of the wing tip, and the line connecting point 0 and point Bˊ being perpendicular to the line connecting point O and point O1; The XOY plane is established by the line connecting point O and point O1 and the line connecting point 0 and point Bˊ; S3. Establish the Z axis on the XOY plane using the right-hand screw rule to create a three-dimensional reference coordinate system.

3. The method for detecting deformation in light aircraft wing maintenance work according to claim 1, characterized in that: In step 2 and step 4, the key points that can characterize the important structural positions of the wing are determined according to the following rules: 23 rivets were selected on the upper and lower surfaces of the wing, with their centers as key points; The 23 rivets on the upper surface of the wing are named as follows: The rivet on the upper surface of the intersection of the 85.875WS rib and the front wing spar is named K1; The rivet on the upper surface of the intersection of the 85.875WS rib and the rear spar of the wing is named C1; The rivet on the upper surface of the intersection of the 100.50WS rib and the front spar of the wing is named L1; The rivet on the upper surface of the intersection of the 100.50WS wing rib and the rear wing spar is named D1; The rivet on the upper surface of the intersection of the 100.50WS rib and the wing tail beam is named T1; The rivet on the upper surface of the intersection of the 118.00WS rib and the front spar of the wing is named M1; The rivet on the upper surface of the intersection of the 118.00WS rib and the rear spar of the wing is named E1; The rivet on the upper surface of the intersection of the 118.00WS wing rib and the wing tail spar is named U1; The rivet on the upper surface of the intersection of the 136.00WS rib and the front spar of the wing is named N1; The rivet on the upper surface of the intersection of the 136.00WS wing rib and the rear wing spar is named F1; The rivet on the upper surface of the intersection of the 136.00WS wing rib and the wing tail spar is named V1; The rivet on the upper surface of the intersection of the 154.00WS rib and the front spar of the wing is named P1; The rivet on the upper surface of the intersection of the 154.00WS wing rib and the rear wing spar is named G1; The rivet on the upper surface of the intersection of the 154.00WS wing rib and the wing tail spar is named W1; The rivet on the upper surface of the intersection of the 172.00WS rib and the front spar of the wing is named Q1; The rivet on the upper surface of the intersection of the 172.00WS wing rib and the rear wing spar is named H1; The rivet on the upper surface of the intersection of the 172.00WS wing rib and the wing tail beam is named X1; The rivet on the upper surface of the intersection of the 190.00WS rib and the front spar of the wing is named R1; The rivet on the upper surface of the intersection of the 190.00WS rib and the rear spar of the wing is named I1; The rivet on the upper surface of the intersection of the 190.00WS rib and the wing tail beam is named Y1; The rivet on the upper surface of the intersection of the 208.00WS rib and the front spar of the wing is named S1; The rivet on the upper surface of the intersection of the 208.00WS wing rib and the rear wing spar is named J1; The rivet on the upper surface of the intersection of the 208.00WS rib and the wing tail beam is named Z1; The 23 rivets on the lower surface of the wing and their names are determined as follows: The rivet on the lower surface of the intersection of the 85.875WS rib and the front wing spar is named K2; The rivet on the lower surface of the 85.875WS rib and the rear spar of the wing is named C2; The rivet on the lower surface of the intersection of the 100.50WS rib and the front spar of the wing is named L2; The rivet on the lower surface of the intersection of the 100.50WS wing rib and the rear wing spar is named D2; The rivet on the lower surface of the intersection of the 100.50WS rib and the wing tail beam is named T2; The rivet on the lower surface of the intersection of the 118.00WS rib and the front spar of the wing is named M2; The rivet on the lower surface of the 118.00WS rib and the rear spar of the wing is named E2 position; The rivet on the lower surface of the intersection of the 118.00WS rib and the wing tail beam is named U2; The rivet on the lower surface of the intersection of the 136.00WS rib and the front spar of the wing is named N2; The rivet on the lower surface of the intersection of the 136.00WS wing rib and the rear wing spar is named F2; The rivet on the lower surface of the intersection of the 136.00WS rib and the wing tail spar is named V2; The rivet on the lower surface of the intersection of the 154.00WS rib and the front spar of the wing is named P2; The rivet on the lower surface of the intersection of the 154.00WS wing rib and the rear wing spar is named G2 position; The rivet on the lower surface of the intersection of the 154.00WS wing rib and the wing tail spar is named W2 position; The rivet on the lower surface of the intersection of the 172.00WS rib and the front spar of the wing is named Q2; The rivet on the lower surface of the intersection of the 172.00WS rib and the rear spar of the wing is named H2; The rivet on the lower surface of the intersection of the 172.00WS wing rib and the wing tail spar is named X2; The rivet on the lower surface of the intersection of the 190.00WS rib and the front spar of the wing is named R2; The rivet on the lower surface of the intersection of the 190.00WS rib and the rear spar of the wing is named I2; The rivet on the lower surface of the intersection of the 190.00WS rib and the wing tail beam is named Y2; The rivet on the lower surface of the intersection of the 208.00WS rib and the front spar of the wing is named S2; The rivet on the lower surface of the intersection of the 208.00WS wing rib and the rear wing spar is named J2; The rivet on the lower surface of the 208.00WS rib and the wing tail beam intersection is named Z2 position.

4. The method for detecting deformation in light aircraft wing maintenance work according to claim 1, characterized in that: In step 2 and step 4, the coordinate values ​​of each key point in the three-dimensional reference coordinate system are obtained as follows: Step ①. Measure the absolute three-dimensional coordinate values ​​of the corresponding key points; Step ②. Convert the absolute three-dimensional coordinate values ​​of the corresponding key points into relative coordinate values ​​in the three-dimensional reference coordinate system.

5. The method for detecting deformation in light aircraft wing maintenance work according to claim 4, characterized in that: In step ①, the absolute three-dimensional coordinate values ​​of the key points are obtained by measuring with a laser tracker.

6. The method for detecting deformation in light aircraft wing maintenance work according to claim 4, characterized in that: In step ②, the absolute three-dimensional coordinate values ​​of the key points are converted into relative coordinate values ​​in the three-dimensional reference coordinate system by Polyworks software.

7. The method for detecting deformation during maintenance of a wing of a light aircraft according to claim 1, characterized in that: The light aircraft is a Cessna 172 aircraft or a PA-44-180 aircraft.

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