Glue joint surface gap detection method of aircraft composite material assembly

Abstract

The invention discloses a glue joint surface gap detection method for an aircraft composite material assembly, and the method comprises the steps: fixing an assembly composite material on a shape maintaining frame, and enabling a rigid composite material to be stably placed; and a three-dimensional shape measuring instrument is used for respectively measuring space coordinate point clouds of the molded surface of the cementing contact surface and the molded surface of the to-be-cemented surface. And making glue joint area mark points in the matching areas of the to-be-glue-jointed surface molded surface and the glue joint contact surface molded surface by using the data identification, and obtaining the glue joint area mark points. And data registration and iterative alignment from the to-be-glued surface molded surface to the glued contact surface molded surface are completed based on the glued area mark points of the to-be-glued surface molded surface and the glued contact surface molded surface, and a registered to-be-glued surface molded surface space coordinate point cloud is obtained. And finally, selecting the molded surface of the cementing contact surface as a reference surface and the registered molded surface to be cemented as a detection surface, calculating a normal distance D between a space point on the reference surface and a space point on the detection surface, and further obtaining a gap value and a gap area between the reference surface and the detection surface. According to the invention, measurement and simulation calculation are carried out on the composite material assembly in an unassembled state, so that the defect of filler gauge measurement after assembly of parts in the past is overcome, gap detection of any spatial position of the bonding surface of the composite material part can be realized, and relatively good practicability is achieved.

Description

Technical Field

[0001] This invention belongs to the technical field of aircraft manufacturing, and specifically relates to a method for detecting the gap at the adhesive surface of aircraft composite components. Background Technology

[0002] Composite components are made by bonding composite parts together. The geometric accuracy of the bonding joints directly affects the overall quality, performance, and function of the component, and is a key indicator affecting the aircraft's maneuverability and lifespan. Based on engineering experience, composite parts with a thickness of 1mm to 4mm typically suffer from poor rigidity and are prone to deformation. During the bonding process, inadequate bonding at the joints between two parts frequently leads to component detachment and cracking, rendering the component unusable. Therefore, it is necessary to inspect the bonding gaps to effectively develop solutions.

[0003] For inspecting the gaps in composite component adhesive joints, the visible area is typically measured manually with a feeler gauge or by visual inspection. This method is highly subjective, prone to human and random errors, and cannot accurately determine the specific location and detailed morphology of the gap area. For areas outside the visible area and inaccessible to a feeler gauge, there is currently no accurate measurement method; judgment must be based on experience, which introduces uncertainties in assessing the bonding accuracy and affects the adhesive quality of composite components. Summary of the Invention

[0004] The purpose of this invention is to provide a method for detecting gaps at the adhesive surfaces of aircraft composite components, aiming to solve the aforementioned problems. This invention can detect gaps at the adhesive surfaces of composite components, quantify gaps in non-visible areas, and determine gap values ​​and gap region morphology.

[0005] This invention is mainly achieved through the following technical solutions:

[0006] A method for detecting the gap at the adhesive surface of an aircraft composite component, the composite component comprising a rigid composite and an assembled composite, wherein the rigid composite has a rigidity greater than or equal to the rigidity of the assembled composite, and the rigid composite and the assembled composite are respectively provided with an adhesive contact surface and a surface to be adhesively bonded; the method includes the following steps:

[0007] Step S1: Fix the assembled composite material onto the shape-conforming frame, use a 3D topography measuring instrument to measure the surface to be bonded, and obtain the spatial coordinate point cloud T of the surface to be bonded in the coordinate system of the 3D topography measuring instrument. Y (Y = 1, 2, 3…);

[0008] Step S2: Place the rigid composite material stably, measure the shape of the adhesive contact surface using a 3D topography measuring instrument, and obtain the spatial coordinate point cloud S of the adhesive contact surface shape in the coordinate system of the 3D topography measuring instrument. Y (Y = 1, 2, 3...);

[0009] Step S3: Based on the spatial coordinate point cloud T Y (Y = 1, 2, 3...) and spatial coordinate point cloud S Y (Y=1,2,3...), using the data marking method, mark the bonding area points (7)Q in the mating area of ​​the surface to be bonded (5) and the bonding contact surface (6). n(n＝1,2,3...) ;

[0010] Step S4: Based on the bonding area markers of the surface to be bonded and the contact surface to be bonded, complete the data registration and iterative alignment from the surface to be bonded to the contact surface to obtain the registered spatial coordinate point cloud T′ of the surface to be bonded. Y(Y＝1，2，3...) :

[0011] T′ Y(Y＝1,2,3...) =AQ n (n = 1, 2, 3...) + (1 - A)S Y(Y＝1,2,3... )

[0012] Where A is the weight;

[0013] Step S5: Select the bonding contact surface as the reference surface, and the registered bonding surface as the test surface. Calculate the spatial points (S) on the reference surface. Yx S Yy S Yz ) and spatial points (T) on the detection surface Yx T Yy T Yz The normal distance D between the reference surface and the detection surface is obtained, and the gap value and gap area between the reference surface and the detection surface are obtained.

[0014] To better realize the present invention, in step S3, the data identification is marked by symmetrically pasting measurement identification blocks or marking points.

[0015] To better realize the present invention, further, in step S5, the formula for calculating the normal distance D is as follows:

[0016]

[0017] To better realize the present invention, the composite components are further divided into rigid composites and assembled composites according to their rigidity.

[0018] To better realize the present invention, the composite component is placed independently and its shape is measured multiple times. If the absolute value of the accuracy error of the repeated measurement is greater than 1 mm, the composite component is identified as an assembled composite; otherwise, it is a rigid composite.

[0019] To better realize the present invention, the rigid composite material is further defined as a composite skeleton, and the assembled composite material is defined as a composite skin.

[0020] The beneficial effects of this invention are as follows:

[0021] (1) This invention can detect the gap in the spatial position of the adhesive surface of composite components, eliminating the blind spot problem that occurs in conventional testing, and does not rely on the theoretical model of the parts. This invention avoids human error and random error caused by manual measurement, and can accurately obtain the specific location of the gap and the detailed morphology of the gap area, and digitally store the gap data for easy subsequent quality inspection and review. This invention is simple to operate, has strong technical versatility, is easy to promote and apply, and has good practicality;

[0022] (2) This invention can be applied to different types of composite components, selecting the measurement state of the adhesive surface of the bonded parts according to their rigidity, calculating the normal distance between the reference plane and the detection surface, and obtaining the gap value and area morphology, etc., thus achieving strong versatility. This invention solves the shortcomings of previous feeler gauge measurements after parts assembly by measuring and simulating composite components in an unassembled state, enabling gap detection at any spatial position on the adhesive surface of composite parts, and has good practicality. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of the aircraft composite component of the present invention;

[0024] Figure 2 A schematic diagram of the connection structure between the composite skin and the composite skeleton;

[0025] Figure 3 A schematic diagram of the surface to be bonded on a composite skin;

[0026] Figure 4 A schematic diagram of the adhesive contact surface on a composite material skeleton;

[0027] Figure 5 A schematic diagram of the structure of the marking points for the bonding area on the surface to be bonded;

[0028] Figure 6 A schematic diagram of the structure of the marking points of the adhesive bonding area on the adhesive contact surface;

[0029] Figure 7 This is a schematic diagram showing the alignment of the surface to be bonded with the surface to be bonded.

[0030] Wherein: 1-Composite component, 2-Composite skin, 3-Composite skeleton, 4-Shape conformer, 5-Surface to be glued, 6-Surface to be glued, 7-Marking point of the glued area. Detailed Implementation

[0031] Example 1:

[0032] A method for detecting the gap at the adhesive surfaces of aircraft composite components, such as... Figure 1 and Figure 2 As shown, composite component 1 includes composite skin 2 and composite skeleton 3, which need to be glued together. Composite skin 2 is a part with poor rigidity and is easily deformed, while composite skeleton 3 has relatively good rigidity and better shape retention. The specific steps include:

[0033] ①For example Figure 3 As shown, the composite skin 2 with poor rigidity is fixed on the shape conformer 4, and its adhesive surface 5 is measured using a three-dimensional topography measuring instrument to obtain the spatial coordinate point cloud T of the surface under the coordinate system of the three-dimensional topography measuring instrument. Y(Y＝1，2，3...) .

[0034] ②For example Figure 4 As shown, the rigid composite skeleton 3 is placed directly on a stable platform, and the spatial coordinates S of the adhesive contact surface 6 in the coordinate system of the three-dimensional topography measuring instrument are obtained. Y(Y＝1,2,3...) .

[0035] ③ For example Figure 5 and Figure 6 As shown, during the data processing, data markers are used to mark the bonding area points 7Q in the key mating areas of the two surfaces. n(n＝1，2，3...) Furthermore, the marking method can take the form of symmetrically pasting measurement marker blocks, marking points, etc.

[0036] ④ In professional software, the data marker points Q can be appropriately increased or decreased according to the actual situation when bonding the surface 5 and the bonding contact surface 6. n(n＝1，2，3...) Weight A is used for principal component analysis, i.e.:

[0037] T′ Y(Y＝1,2,3...) =AQ n(n＝1,2,3...) +(1-A)S Y(Y＝1,2,3...)

[0038] like Figure 7 As shown, data registration and iterative alignment are completed, and the threshold setting of the calculation results must meet the error requirements of the part assembly technology.

[0039] ⑤ Select one of the bonding contact surfaces 6 as the reference surface and the other bonding surface 5 as the test surface, and calculate the normal distance between the spatial point on the reference surface and the spatial point on the test surface:

[0040]

[0041] Obtain the gap value and gap area.

[0042] Preferably, the rigidity evaluation method of composite component 1 is as follows: when the component is placed independently, it is measured by measuring equipment. The measurement is repeated ≥2 times. The part with shape measurement repeatability error greater than ±1mm is judged as a composite component with poor rigidity, and the rest is a composite component with good rigidity.

[0043] This invention can be applied to different types of composite components 1, selecting the measurement state of the adhesive surface of the bonded parts according to their rigidity, calculating the normal distance between the reference plane and the detection surface, and obtaining the gap value and area morphology, etc., thus achieving the detection objectives. It has strong versatility. By measuring and simulating the unassembled state of the composite component 1, this invention solves the shortcomings of previous feeler gauge measurements after component assembly, enabling gap detection at any spatial position on the adhesive surface of composite components, and has good practicality.

[0044] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A method for detecting the gap at the adhesive surface of an aircraft composite component, characterized in that, The composite component (1) includes a rigid composite and an assembled composite, wherein the rigid composite has a rigidity greater than or equal to the rigidity of the assembled composite, and the rigid composite and the assembled composite are respectively provided with an adhesive contact surface (6) and a surface to be adhesive (5); including the following steps: Step S1: Fix the assembled composite material onto the shape conformer (4), measure the surface profile (5) to be bonded using a three-dimensional topography measuring instrument, and obtain the spatial coordinate point cloud of the surface profile (5) to be bonded under the coordinate system of the three-dimensional topography measuring instrument. ; Step S2: Place the rigid composite material stably, measure the shape of the adhesive contact surface (6) using a three-dimensional topography measuring instrument, and obtain the spatial coordinate point cloud of the adhesive contact surface (6) in the coordinate system of the three-dimensional topography measuring instrument. ; Step S3: Based on spatial coordinate point cloud and spatial coordinate point cloud Using data identification methods, adhesive area marking points (7) are made in the mating areas of the surface to be glued (5) and the surface to be glued (6). ; Step S4: Based on the bonding area markers (7) of the surface to be bonded (5) and the bonding contact surface (6), complete the data registration and iterative alignment from the surface to be bonded (5) to the bonding contact surface (6) to obtain the registered spatial coordinate point cloud of the surface to be bonded (5). : Where A is the weight; Step S5: Select the bonding contact surface (6) as the reference surface, and the registered bonding surface (5) as the test surface. Calculate the spatial points on the reference surface. S Yx , S Yy , S Yz ) and spatial points on the detection surface ( T Yx , T Yy , T Yz normal distance D This allows us to obtain the gap value and gap area between the reference surface and the detection surface.

2. The method for detecting the gap at the adhesive surface of an aircraft composite component according to claim 1, characterized in that, In step S3, the data identification is marked by symmetrically pasting measurement identification blocks or marker points.

3. The method for detecting the gap at the adhesive surface of an aircraft composite component according to claim 1, characterized in that, In step S5, the normal distance D The calculation formula is as follows: 。 4. The method for detecting the gap at the adhesive surface of an aircraft composite component according to claim 1, characterized in that, Based on the degree of rigidity, composite components (1) are divided into rigid composites and assembled composites.

5. The method for detecting the gap at the adhesive surface of an aircraft composite component according to claim 4, characterized in that, The composite component (1) is placed independently, and the shape of the composite component (1) is measured multiple times. If the absolute value of the accuracy error of the repeated measurement is greater than 1 mm, the composite component (1) is identified as an assembled composite; otherwise, it is a rigid composite.

6. A method for detecting the gap at the adhesive surface of an aircraft composite component according to any one of claims 1-5, characterized in that, The rigid composite material is a composite skeleton (3), and the assembled composite material is a composite skin (2).

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