Method for compensating thermal expansion of a large-size measuring field component attitude

Abstract

This application belongs to the field of thermal expansion compensation technology for large aircraft manufacturing equipment, and specifically relates to a method for compensating the attitude thermal expansion of large-size measurement field components. This method utilizes an expansion plate structure, combined with sensor ranging, to unify the assembly structure of the ranging sensor and the attitude adjustment positioner. By unifying the expansion change data of the expansion plate and attitude adjustment positioner under two different thermal expansion coefficient states through the measurement field coordinate system, the expansion amount of the expansion plate with the same thermal expansion coefficient as the product to be assembled is used as the axial movement of the attitude adjustment positioner along the compensation direction, which is then transmitted to the segmented assembly components to achieve thermal expansion compensation. This application is applicable to the high-precision assembly of various large-size aircraft products and is suitable for unidirectional or multidirectional combined temperature compensation of tooling measurement fields and component attitude adjustment and positioning structures during the assembly process.

Description

Technical Field

[0001] This application belongs to the field of thermal expansion compensation technology for large aircraft process equipment, and specifically relates to a method for compensating the attitude thermal expansion of large-size measurement field components. Background Technology

[0002] Aircraft manufacturing products and their process equipment are large in size, with the largest aircraft process equipment reaching approximately 80 meters in length. Aircraft products often utilize composite materials and aluminum alloys, while process equipment is predominantly steel-structured, and the foundations supporting the process equipment are typically reinforced concrete. Therefore, due to factors such as uniformity and material variations, wing structures often employ longitudinal expansion plates to compensate for the wing box during assembly. While fuselage structures, due to their better symmetry, generally do not use expansion plates, their use is a common structural design practice in the assembly of large, precision fuselages.

[0003] Current expansion plates typically consist of a long strip or beam structure along the entire expansion direction, used to support the positioning and measurement references of the aircraft. The material of the strip or beam structure is the same as the skin material of the main expansion structure of the aircraft. The strip or beam structure is generally fixed at the main positioning reference location, with parallel guide rails along its length at other locations. The strip or beam structure expands freely in the longitudinal direction with temperature changes, using the fixed structure as a reference.

[0004] Existing expansion plates used in aircraft manufacturing processes, both domestically and internationally, are mainly suitable for integral tooling structures where materials can be easily altered. However, for discrete structure assembly tooling such as horizontal wing box assembly and three-section fuselage docking, it is actually difficult to set up or completely install expansion plates. Therefore, it is necessary to explore a thermal expansion compensation method applicable to discrete structure assembly tooling.

[0005] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention

[0006] The purpose of this application is to provide a method for compensating for the attitude thermal expansion of large-size measurement field components, in order to solve at least one problem existing in the prior art.

[0007] The technical solution of this application is:

[0008] A method for compensating for the attitude thermal expansion of a large-size measurement field component includes:

[0009] Step 1: Obtain multiple modular assembly components of the product to be assembled and docked, install process ball heads on each modular assembly component, and connect each process ball head to the corresponding attitude adjustment positioner through a hinge.

[0010] Step 2: Set expansion plates of the same material parallel to the compensation direction of the products to be assembled and docked, and set multiple measurement reference points on the upper surface of the expansion plates. Construct a measurement field coordinate system based on the measurement reference points.

[0011] Step 3: Select one of the modular assembly components as the compensation direction expansion reference, and set the attitude adjustment positioner connected to the compensation direction expansion reference to the longitudinal compensation zero position;

[0012] Step 4: Set a fixing pin at the position of the expansion plate corresponding to the longitudinal compensation zero position, and connect the expansion plate to the tooling structure;

[0013] Step 5: Taking the expansion reference in the compensation direction as the starting point, set a slide rail parallel to the compensation direction at the interface between the expansion plate and the tooling structure;

[0014] Step 6: Obtain a perpendicular line to the compensation direction at the hinge point between each of the process ball heads and the attitude adjustment positioner.

[0015] Step 7: Set a limiting member at the position of the expansion plate that intersects with each of the vertical lines. The limiting member has a limiting member measuring section that is parallel to the compensation direction. Set a distance measuring sensor at the position corresponding to each of the limiting member measuring sections.

[0016] Step 8: In the coordinate system of the measurement field, calibrate the distance relationship between the hinge point of the process ball head and the attitude adjustment positioner and the vertical line along the compensation direction;

[0017] Step 9: Measure the distance information of the limiting component along the compensation direction caused by temperature changes in real time using the distance sensor;

[0018] Step 10: Adjust the axial movement of the attitude adjustment positioner along the compensation direction according to the ranging information to perform thermal expansion compensation.

[0019] In at least one embodiment of this application, in step 1, the attitude adjustment locator is disposed on the upper surface of the foundation.

[0020] In at least one embodiment of this application, in step 7, the ranging sensor is disposed on the upper surface of the foundation.

[0021] In at least one embodiment of this application, in step 1, the attitude adjustment locator is mounted on a column on the upper surface of the foundation.

[0022] In at least one embodiment of this application, in step 7, the ranging sensor is mounted on a column on the upper surface of the foundation.

[0023] In at least one embodiment of this application, in step 8, the distance relationship is: the change in the amount of expansion along the compensation direction at the reference temperature, with the compensation direction expansion reference as the starting point, between the hinge point of the process ball head and the attitude adjustment positioner and the vertical line.

[0024] In at least one embodiment of this application, in step 10, thermal expansion compensation is performed at fixed time intervals, the fixed time intervals being no less than 30 minutes and no more than 2 hours.

[0025] In at least one embodiment of this application, in step 10, the amount of axis movement is:

[0026] ;

[0027] ;

[0028] Where, p n Let λ be the axis displacement in the nth compensation cycle, λ be the thermal response coefficient, and d be the axis displacement in the nth compensation cycle. n For the ranging information of the nth compensation period, p n-1 The axial displacement is the amount of the (n-1)th compensation cycle, ε is the temperature change rate compensation coefficient, and T n Let T be the temperature during the nth compensation cycle. n-1 Let t be the temperature of the (n-1)th compensation cycle, Δt be the fixed time interval, and τ be the thermal time constant.

[0029] In at least one embodiment of this application, in step 10, when the ranging information is ≤ α mm, thermal expansion compensation is not performed, where α is the ranging information threshold.

[0030] The invention has at least the following beneficial technical effects:

[0031] The large-size measurement field component attitude thermal expansion compensation method of this application transfers the expansion amount of the expansion plate with the same thermal expansion coefficient as the product to be assembled to the segmented assembly component, thereby realizing thermal expansion compensation for the assembly of large aircraft components and improving assembly accuracy. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of a measurement field according to one embodiment of this application.

[0033] in:

[0034] 1-Expansion plate; 2-Fixing pin; 3-Limiting component; 4-Distance sensor; 5-Long-range compensation zero point; 6-Attitude adjustment positioner; 7-Segmented assembly component; 8-Measurement reference point; 9-Foundation. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0036] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0037] The following is in conjunction with the appendix Figure 1 This application will be described in further detail.

[0038] This application provides a method for compensating for the attitude thermal expansion of a large-size measurement field component, including the following steps:

[0039] Step 1: Obtain multiple modular assembly parts 7 of the product to be assembled and docked, install process ball heads on each modular assembly part 7, and connect each process ball head to the corresponding attitude adjustment positioner 6 through a hinge.

[0040] In step 1, each modular assembly component 7 is connected to an attitude adjustment positioner 6 that includes at least one axis for automatic and precise control of motion in the compensation direction. During the assembly of aircraft components, the modular assembly component 7 can be attitude adjusted using an attitude adjustment positioner 6 with XYZ three-axis compensation attitude adjustment function, or it can be attitude adjusted using an attitude adjustment positioner 6 with only longitudinal compensation attitude adjustment function. In this embodiment, the attitude adjustment positioner 6 can be installed on the upper surface of the foundation 9, or a column can be arranged vertically upward on the upper surface of the foundation 9, and the attitude adjustment positioner 6 can be installed on the column. In addition, the attitude adjustment positioner 6 can also be installed on the overall tooling structure, and when installed on the tooling structure, a compensation direction sliding structure needs to be provided.

[0041] Step 2: Set expansion plates 1 of the same material parallel to the compensation direction of the products to be assembled and docked, and set multiple measurement reference points 8 on the upper surface of expansion plates 1. Construct a measurement field coordinate system based on the measurement reference points 8.

[0042] In step 2, an expansion plate 1 of the same material is set parallel to the compensation direction of the product to be assembled and docked. Multiple measurement reference points 8 are set on the upper surface of the expansion plate 1, which has the same thermal expansion coefficient as the product to be assembled and docked. A measurement field coordinate system is constructed based on the measurement reference points 8, and the measurement field coordinate system is used as the basis for the attitude adjustment and positioning of each segment assembly component 7.

[0043] Step 3: Select a segmented assembly component 7 as the compensation direction expansion reference, and set the attitude adjustment positioner 6 connected to the compensation direction expansion reference as the longitudinal compensation zero position 5.

[0044] In step 3, the expansion reference of the compensation direction is selected, and the attitude adjustment positioner 6 connected to the expansion reference of the compensation direction is set as the longitudinal compensation zero position 5. The attitude adjustment positioner 6 at the longitudinal compensation zero position 5 does not perform thermal expansion compensation.

[0045] Step 4: Set a fixing pin 2 at the position of the expansion plate 1 corresponding to the longitudinal compensation zero position 5, and connect the expansion plate 1 to the tooling structure.

[0046] Step 5: Starting from the expansion reference in the compensation direction, set a slide rail parallel to the compensation direction at the interface between the expansion plate 1 and the tooling structure.

[0047] In step 5, the expansion plate 1 is slidably connected to the tooling structure via a slide rail, so that the expansion plate 1 and the tooling structure can move relative to each other.

[0048] Step 6: Obtain a perpendicular line to the compensation direction at the hinge point between each process ball head and the attitude adjustment positioner 6.

[0049] Step 7: Set a limiting member 3 at the position of the expansion plate 1 that intersects with each vertical line. The limiting member 3 has a limiting member measuring section parallel to the compensation direction. Set a distance sensor 4 at the position corresponding to each limiting member measuring section.

[0050] In step 7, the ranging sensor 4 is used to sense the displacement difference of the expansion plate 1 caused by temperature changes. The ranging sensor 4 adopts the same installation method as the attitude adjustment positioner 6. The ranging sensor 4 can be set on the upper surface of the foundation 9, or a column can be arranged vertically upward on the upper surface of the foundation 9 and the ranging sensor 4 can be set on the column.

[0051] Step 8: In the coordinate system of the measurement field, calibrate the distance relationship between the hinge point of the process ball head and the attitude adjustment positioner 6 and the vertical line along the compensation direction.

[0052] In step 8, when calculating the expansion distance, a detection reference needs to be selected. Since the attitude adjustment hinge point position of the aircraft component is digitally controlled, for the sake of calculation convenience, the product position with strong structural stability is generally selected as the zero point, that is, the vertical position coincides with the hinge point position.

[0053] In this embodiment, the distance relationship is: taking the expansion reference in the compensation direction as the starting point, the data on the change in expansion along the compensation direction between the hinge point of the process ball head and the attitude adjustment positioner 6 and the vertical line when the reference temperature is zero. Preferably, the reference temperature is 20°C. The difference in the thermal expansion coefficients of the foundation material 9 and the expansion plate 1 material is converted into data on the change in expansion in the compensation direction with 20°C as the zero point, preferably by linear comparison of measurement data from at least 3 measurements.

[0054] Step 9: The distance information of the limiting component 3 along the compensation direction caused by temperature change is measured in real time by the distance sensor 4.

[0055] In step 9, the ranging information is the expansion change data of the limiting member 3 along the compensation direction, which is linearly compared with multiple real-time measurement data from the ranging sensor 4.

[0056] Step 10: Adjust the axial movement of the attitude adjuster 6 along the compensation direction according to the ranging information to perform thermal expansion compensation.

[0057] In step 10, thermal expansion compensation is performed at fixed time intervals, which are no less than 30 minutes and no more than 2 hours.

[0058] In the nth compensation cycle, the axis movement of the attitude adjuster 6 is:

[0059] ;

[0060] ;

[0061] Where, p n Let λ be the axis displacement in the nth compensation cycle, λ be the thermal response coefficient, and d be the axis displacement in the nth compensation cycle. n For the ranging information of the nth compensation period, p n-1 The axial displacement is the amount of the (n-1)th compensation cycle, ε is the temperature change rate compensation coefficient, and T n Let T be the temperature during the nth compensation cycle. n-1 Let t be the temperature of the (n-1)th compensation cycle, Δt be the fixed time interval, and τ be the thermal time constant.

[0062] When the ranging information is ≤ α mm, it is defaulted to zero, and no thermal expansion compensation is performed. In this embodiment, the ranging information threshold α is 0.2.

[0063] In this embodiment, the directly measured expansion amount is used as the adjustment benchmark. Based on the expansion amount change data acquired in real time by the ranging sensor 4, it reflects the actual expansion amount caused by temperature changes in the current compensation cycle. The historical compensation expansion amount is used as a thermal inertia correction term. By introducing the axial displacement of the previous cycle, it characterizes the continuation effect of the previous deformation caused by the thermal time constant in the current cycle, so that the compensation process matches the inertial characteristics of the physical system. The temperature change rate compensation expansion amount is used as a dynamic feedforward term. It predicts the expansion amount deviation caused by thermal conduction lag through the temperature change rate, and compensates for the phase lag between the measurement point and the compensation point caused by spatial position differences and thermal conduction delay.

[0064] This application presents a method for compensating the thermal expansion of large-size measurement field components. Utilizing an expansion plate 1 structure and combining it with sensor ranging, the assembly structure of the ranging sensor 4 and the attitude adjustment positioner 6 is unified. The expansion change data of the expansion plate 1 and the attitude adjustment positioner 6 under two different thermal expansion coefficient states are unified through the measurement field coordinate system. The expansion amount of the expansion plate 1, which has the same thermal expansion coefficient as the product to be assembled, is used as the axial movement of the attitude adjustment positioner 6 along the compensation direction and transmitted to the segmented assembly component 7, thus achieving thermal expansion compensation. This application is applicable to the high-precision assembly of various large-size aircraft products and is suitable for unidirectional or multidirectional combined temperature compensation of the tooling measurement field and component attitude adjustment positioning structure during the assembly process.

[0065] The large-size measurement field component attitude thermal expansion compensation method of this application can change the current situation where the large contour accuracy of the whole aircraft assembly affected by thermal expansion is above 5mm, realize the full-length accuracy control of large-size aircraft at the sub-millimeter level, and greatly improve the consistency of the overall size of large aircraft components. It has a key supporting and guiding role and universal applicability value for ensuring the assembly thermal expansion compensation effect and assembly accuracy of large aircraft components.

[0066] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method of compensating for thermal expansion of components of a large-scale measurement field, characterized by, include: Step 1: Obtain multiple modular assembly parts (7) of the product to be assembled and docked, install process ball heads on each modular assembly part (7), and connect each process ball head to the corresponding attitude adjustment positioner (6) through a hinge. Step 2: Set an expansion plate (1) of the same material parallel to the compensation direction of the product to be assembled and docked, and set multiple measurement reference points (8) on the upper surface of the expansion plate (1). Construct a measurement field coordinate system based on the measurement reference points (8). Step 3: Select one of the segmented assembly components (7) as the compensation direction expansion reference, and set the attitude adjustment positioner (6) connected to the compensation direction expansion reference as the longitudinal compensation zero position (5). Step 4: Set a fixing pin (2) at the position of the expansion plate (1) corresponding to the longitudinal compensation zero position (5) to connect the expansion plate (1) to the tooling structure; Step 5: Taking the expansion reference in the compensation direction as the starting point, set a slide rail parallel to the compensation direction at the interface between the expansion plate (1) and the tooling structure; Step 6: Obtain a perpendicular line to the compensation direction at the hinge point between each of the process ball heads and the attitude adjustment positioner (6); Step 7: Set a limiting member (3) at the position of the expansion plate (1) that intersects with each of the vertical lines. The limiting member (3) has a limiting member measuring section parallel to the compensation direction. Set a distance sensor (4) at the position corresponding to each of the limiting member measuring sections. Step 8: In the coordinate system of the measurement field, calibrate the distance relationship between the hinge point of the process ball head and the attitude adjustment positioner (6) and the vertical line along the compensation direction; Step 9: Measure the distance information of the limiting member (3) along the compensation direction caused by temperature change in real time using the distance sensor (4); Step 10: Adjust the axial movement of the attitude adjustment positioner (6) along the compensation direction according to the ranging information to perform thermal expansion compensation.

2. The method of claim 1, wherein, In step 1, the attitude adjustment positioner (6) is set on the upper surface of the foundation (9).

3. The method of claim 2, wherein, In step 7, the ranging sensor (4) is installed on the upper surface of the foundation (9).

4. The method of claim 1, wherein, In step 1, the attitude adjustment positioner (6) is set on the column on the upper surface of the foundation (9).

5. The method of claim 4, wherein, In step 7, the ranging sensor (4) is installed on a column on the upper surface of the foundation (9).

6. The method for compensating for the attitude thermal expansion of a large-size measurement field component according to claim 3 or 5, characterized in that, In step 8, the distance relationship is: the expansion change data of the process ball head and the hinge point of the attitude adjustment positioner (6) and the vertical line along the compensation direction when the position is zero at the reference temperature, with the compensation direction expansion reference as the starting point.

7. The method of claim 6, wherein, In step 10, thermal expansion compensation is performed at fixed time intervals, the fixed time intervals being no less than 30 minutes and no more than 2 hours.

8. The method of claim 7, wherein, In step 10, the axis displacement is: ； ； Where, p n Let λ be the axis displacement in the nth compensation cycle, λ be the thermal response coefficient, and d be the axis displacement in the nth compensation cycle. n For the ranging information of the nth compensation period, p n-1 The axial displacement is the amount of the (n-1)th compensation cycle, ε is the temperature change rate compensation coefficient, and T n Let T be the temperature during the nth compensation cycle. n-1 Let t be the temperature of the (n-1)th compensation cycle, Δt be the fixed time interval, and τ be the thermal time constant.

9. The method of claim 8, wherein, In step 10, when the ranging information is ≤ α mm, thermal expansion compensation is not performed, where α is the ranging information threshold.

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