Design and use method of aircraft metal beam part deformation compensation dynamic model

Abstract

The invention discloses an aircraft metal beam part deformation compensation dynamic model design and use method, which is characterized by comprising the following steps: step 1, obtaining deformation compensation parameters of an aircraft metal beam part through processing detection; step 2, establishing a reaction in the airplane metal beam part model so as to establish an airplane metal beam part deformation compensation dynamic model; the reaction means that a program is used for achieving deformation response of the aircraft metal beam part deformation compensation dynamic model; and step 3, automatically judging and selecting corresponding deformation compensation parameters for the current month by adopting the established aircraft metal beam part deformation compensation dynamic model so as to establish an aircraft metal beam part deformation compensation model of the current month. According to the method, the problem of out-of-tolerance deformation generated in the length direction after the metal beam is machined under the influence of multiple factors of different plant temperatures is solved, high-quality machining of metal beam parts is achieved, and efficient development and rapid batch production of large aircrafts are guaranteed.

Description

Technical Field

[0001] The present invention relates to, but is not limited to, the field of digital manufacturing, and relates to a design and use method of a dynamic model for deformation compensation of aircraft metal beam parts. Background Art

[0002] Aircraft metal beam parts are the main load-bearing components of the aircraft. During flight, they bear multiple loads such as aerodynamic loads, gravity, and inertial forces, and distribute them throughout the entire aircraft structure. They are subjected to enormous tensile, compressive, bending, and torsional forces, and are an important guarantee for the structural integrity and stability of the aircraft. The high quality and high reliability of aircraft metal beams are key factors in ensuring the safety of passengers, crew members, and aircraft property. Aircraft metal beam parts are assembled with wing ribs and skins to form aircraft wings. The machining accuracy of aircraft metal beam parts directly affects the assembly with wing ribs and skins, resulting in problems such as excessive gaps, out-of-tolerance fit, and out-of-tolerance wing dimensions. This leads to uneven stress distribution at the joints, resulting in local stress concentration and fatigue damage during flight, which directly affects the overall performance and safety of the aircraft. Therefore, very high machining accuracy requirements are imposed on aircraft metal beam parts.

[0003] The conventional processing technology for aircraft metal beams is to use CNC machine tools to mill metal blanks based on the designed digital model, and then shot peening to strengthen the shape. The processing of aircraft metal beams is affected by many factors, especially the influence of factory temperature, which can cause the metal beams to deform excessively along the length direction after processing. During the development of large aircraft, as the size of the beams increases, the deformation becomes more serious, seriously affecting the precise manufacturing of aircraft components. The current method for dealing with metal beam processing deformation is to establish a post-compensation method with a single fixed compensation coefficient based on the forming results. This method cannot meet the production requirements of multiple processing periods and multiple temperatures, resulting in extremely unstable processing quality of aircraft metal beams, seriously affecting the development and batch production quality of aircraft, extending the aircraft production cycle, and increasing the production cost of aircraft. Summary of the Invention

[0004] The purpose of the present invention is: to solve the above-mentioned problems, the embodiment of the present invention provides a design and use method of a dynamic model for deformation compensation of aircraft metal beam parts, so as to solve the problems that the existing post-compensation method for metal beam processing deformation is difficult to meet the production requirements of multiple processing periods and multiple temperatures, resulting in extremely unstable aircraft metal beam processing quality, seriously affecting the development and batch production processing quality of the aircraft, extending the aircraft production cycle, and increasing the production cost of the aircraft.

[0005] The technical solution of the present invention is as follows: The present invention provides a design and use method of a dynamic model for deformation compensation of aircraft metal beam parts, comprising: Step 1: Obtain deformation compensation parameters of aircraft metal beam parts through processing inspection; Step 2: establishing a reaction in the aircraft metal beam part model to establish a deformation compensation dynamic model of the aircraft metal beam part; the reaction refers to: realizing a deformation response of the deformation compensation dynamic model of the aircraft metal beam part using a program; Step 3: Using the established deformation compensation dynamic model of aircraft metal beam parts, automatically determine and select corresponding deformation compensation parameters for the current month to establish the deformation compensation model of aircraft metal beam parts for the current month.

[0006] Optionally, in the above-mentioned method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts, step 1 includes: selecting an aircraft metal beam part, and establishing deformation compensation parameters of the aircraft metal beam part in different months of the year through processing inspection.

[0007] Optionally, in the above-mentioned method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts, step 1 includes: Step 11, selecting an aircraft metal beam part with the same processing technology as an object for obtaining deformation compensation parameters of the aircraft metal beam part; Step 12, measuring the total length L of the aircraft metal beam part; Step 13, processing the aircraft metal beam parts according to the processing technology every month, and measuring the actual total length RL of the aircraft metal beam parts after processing; Step 14, calculate the deformation compensation parameter Mdi of the aircraft metal beam parts in each month, and complete the establishment of the deformation compensation parameter Mdi of the aircraft metal beam parts throughout the year. The calculation formula is: Mdi=-(RL-L)*t / (L*1000); Where i is a positive integer from 1 to 12; t is the compensation coefficient, and its value range is 0 <t≤1。

[0008] Optionally, in the method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts as described above, step 2 includes: establishing a reaction in the aircraft metal beam part model through a program, and the reaction is used to automatically determine the current month and select the deformation compensation parameters corresponding to the current month by judging the user's operation actions, thereby establishing an aircraft metal beam part deformation compensation model.

[0009] Optionally, in the above-mentioned method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts, step 2 includes the following steps: Step 2-1, select the aircraft metal beam model in the 3D CAD software; Step 2-2, selecting the beam plane of the aircraft metal beam part model in the 3D CAD software as the reference plane for deformation compensation; Step 2-3, selecting in 3D CAD software the intersection of the wing root edge line and the aircraft wing chord plane on the beam plane of the aircraft metal beam part model as a deformation compensation reference point of the aircraft metal beam part model; Steps 2-4: In the 3D CAD software, the deformation compensation reference point of the aircraft metal beam part model is used as the starting point, and the intersection of the deformation compensation reference plane and the aircraft wing chord plane is used as the deformation compensation direction of the aircraft metal beam part model; Step 2-5: Establish a deformation compensation coordinate system with the deformation compensation reference point of the aircraft metal beam part model as the origin of the coordinate system, the deformation compensation direction of the aircraft metal beam part model as the X-axis of the coordinate system, and the deformation compensation reference plane as the Y-axis of the coordinate system; In steps 2-6, select the Radial command in the 3D CAD software, use the deformation compensation reference point of the aircraft metal beam part model as the affine origin, the XY plane in the deformation compensation coordinate system as the affine XY plane, and the X axis in the deformation compensation coordinate system as the affine X axis. Set the initial value of the ratio in the X, Y, and Z directions to 1. Step 2-7, respectively establish deformation compensation parameters PMdi=Mdi of the aircraft metal beam model in the 3D CAD software, where i is a positive integer from 1 to 12; Step 2-8, create the month parameter Month in the 3D CAD software, and set the initial value to 1; Step 2-9: Create the deformation compensation X-axis ratio parameter Xrate in the 3D CAD software, and set the initial value to 1; Step 2-10, in the 3D CAD software, use the formula editor to make the X-ratio in the established radiation command equal to the value of the parameter Xrate; Step 2-11: Set the automatic update of the part module to manual update in the 3D CAD software; In step 2-12, a reaction command is selected in the 3D CAD software knowledge module. In the reaction command, a metal beam deformation compensation entity is selected as the source type. An update is selected as the available event. A program is written in the work instruction to automatically determine the current month and select corresponding deformation compensation parameters. A dynamic model of deformation compensation for aircraft metal beam parts is established.

[0010] Optionally, in the above-mentioned method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts, steps 2-12 include: Step 2-12-1, use the month(now()) function to read the month in the current system time, and assign the month to the month parameter Month established in the 3D CAD software; Step 2-12-2, select the aircraft metal beam part deformation compensation parameter PMdi corresponding to the month according to the value of the month parameter Month, where the value of i is the month value of Month; Step 2-12-3, by writing a program, calculate the value of the deformation compensation X-axis ratio parameter Xrate based on the selected aircraft metal beam part deformation compensation parameter PMdi. The calculation formula is: Xrate=(1-PMdi).

[0011] Optionally, in the method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts as described above, step 3 includes: opening the established dynamic model for deformation compensation of aircraft metal beam parts, activating the program in the reaction command by updating, so as to establish the deformation compensation model of aircraft metal beam parts for the current month.

[0012] Optionally, in the above-mentioned method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts, step 3 specifically includes the following steps: Step 31, opening the established deformation compensation dynamic model of the aircraft metal beam part in 3D CAD software; In step 32, select the update command in the 3D CAD software to activate the program in the response command, automatically determine the current month, select the corresponding deformation compensation parameter PMdi, and calculate the deformation compensation X-axis ratio parameter Xrate value, thereby establishing a deformation compensation model for aircraft metal beam parts based on the current month.

[0013] The beneficial effects of the present invention are as follows: the present invention provides a design and use method for a deformation compensation dynamic model of an aircraft metal beam part, which first obtains the deformation compensation parameters of the aircraft metal beam part, then uses three-dimensional CAD software to establish a reaction in the deformation compensation model of the aircraft metal beam part, and in the reaction, the program automatically reads the current month and selects the deformation compensation parameters corresponding to the current month, thereby establishing a deformation compensation model for the aircraft metal beam part; based on the established deformation compensation model of the aircraft metal beam part, the process personnel can open the established deformation compensation dynamic model of the aircraft metal beam part, execute an update operation to activate the logic program in the reaction, and automatically complete the automatic modeling of a deformation compensation model of the aircraft metal beam part for the current month. The technical solution provided by the embodiment of the present invention has the following beneficial effects: (1) The design and use method of the deformation compensation dynamic model of aircraft metal beam parts provided by the present invention is used to realize the software packaging of the deformation compensation dynamic model of aircraft metal beam parts in different months of the year. Based on the preparation of the reaction program under the knowledge module in the model, the process personnel realize the automatic construction and automatic dynamic precise compensation of the deformation compensation model of aircraft metal beam parts in different months by updating the reaction program of the activation model. This solves the problem of excessive deformation of the metal beam along the length direction after processing under the influence of multiple factors such as different factory temperatures, realizes high-quality processing of metal beam parts, and ensures the efficient development and rapid batch production of large aircraft.

[0014] (2) The design and use method of the dynamic model for deformation compensation of aircraft metal beam parts provided by the present invention changes the traditional thinking of single results of the model, practices the automatic acquisition and change of the multi-state of the model, and provides a new solution for the multi-state deformation compensation of large aircraft long stringers, beams, and wall panels. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0016] Figure 1 A flowchart of a method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts provided by an embodiment of the present invention; Figure 2 Schematic diagram of an aircraft metal beam part according to an embodiment of the present invention; Figure 3 Schematic diagram of a deformation compensation dynamic model for aircraft metal beam parts according to an embodiment of the present invention.

[0017] Description of reference numerals: 1- Aircraft metal beam parts, 2- Aircraft metal beam parts deformation compensation dynamic model, 3- Compensation reference point, 4- Compensation coordinate system. DETAILED DESCRIPTION

[0018] To make the purpose, technical solutions and advantages of the present invention more clearly understood, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless there is a conflict, the embodiments and features in the embodiments of the present application can be combined with each other in any manner.

[0019] As explained in the aforementioned background technology, aircraft metal beam components, as the primary load-bearing components of aircraft, are crucial for ensuring the structural integrity and stability of aircraft. This means that the machining precision of aircraft metal beam components is highly demanding. Because aircraft metal beams can deform excessively after machining, these deformations require further processing. Existing post-compensation methods struggle to meet the demands of multi-processing and multi-temperature production, resulting in extremely unstable machining quality for aircraft metal beams. This severely impacts aircraft development and mass production, extends aircraft production cycles, and increases production costs.

[0020] In response to the above problems, an embodiment of the present invention provides a design and use method of a dynamic model for deformation compensation of aircraft metal beam parts.

[0021] The present invention provides the following specific embodiments that can be combined with each other. The same or similar concepts or processes may not be described in detail in some embodiments.

[0022] Figure 1 A flowchart of a method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts provided by an embodiment of the present invention; Figure 2 Schematic diagram of an aircraft metal beam part according to an embodiment of the present invention; Figure 3 Schematic diagram of the deformation compensation dynamic model of aircraft metal beam parts in the embodiment of the present invention. Figures 1 to 3 As shown, the design and use method of the deformation compensation dynamic model of aircraft metal beam parts provided by the embodiment of the present invention includes three parts: obtaining deformation compensation parameters of aircraft metal beam parts 1, and establishing and using the deformation compensation dynamic model 2 of aircraft metal beam parts. Figure 1 As shown, based on the deformation compensation dynamic model 2 of aircraft metal beam parts, the corresponding deformation compensation parameter selection is automatically determined for the current month, and the automatic modeling of the deformation compensation model 2 of aircraft metal beam parts for the current month is realized, thereby ensuring the precise processing of aircraft metal beam parts.

[0023] like Figures 1 to 3 As shown, the design and use method of the deformation compensation dynamic model of aircraft metal beam parts provided by the embodiment of the present invention includes the following steps: Step 1: Obtain deformation compensation parameters of aircraft metal beam parts through processing inspection; Step 2: establishing a reaction in the aircraft metal beam part model to establish a deformation compensation dynamic model of the aircraft metal beam part; the reaction refers to: realizing a deformation response of the deformation compensation dynamic model of the aircraft metal beam part using a program; Step 3: Using the established deformation compensation dynamic model of aircraft metal beam parts, automatically determine and select corresponding deformation compensation parameters for the current month to establish the deformation compensation model of aircraft metal beam parts for the current month.

[0024] In one implementation of the present invention, step 1 includes selecting an aircraft metal beam part and establishing deformation compensation parameters for the aircraft metal beam part in different months of the year through processing testing. The specific implementation of step 1 may include the following steps: Step 11, selecting an aircraft metal beam part with the same processing technology as an object for obtaining deformation compensation parameters of the aircraft metal beam part; Step 12, measuring the total length L of the aircraft metal beam part; Step 13, processing the aircraft metal beam parts according to the processing technology every month, and measuring the actual total length RL of the aircraft metal beam parts after processing; Step 14, calculate the deformation compensation parameter Mdi of the aircraft metal beam parts in each month, and complete the establishment of the deformation compensation parameter Mdi of the aircraft metal beam parts throughout the year (as shown in Table 1); the calculation formula is: Mdi=-(RL-L)*t / (L*1000); Where i is a positive integer from 1 to 12; t is the compensation coefficient, and its value range is 0 <t≤1。

[0025] Table 1 Deformation compensation parameters of aircraft metal beam parts

[0026] In one implementation of the present invention, step 2 includes: programming a reaction in the aircraft metal beam component deformation compensation model 2; the reaction is used to automatically determine the current month and select the corresponding deformation compensation parameters by judging the user's operation, thereby establishing the aircraft metal beam component deformation compensation model. The specific implementation process of step 2 may include the following steps: Step 2-1, select the aircraft metal beam model in the 3D CAD software; Step 2-2, selecting the beam plane of the aircraft metal beam part model in the 3D CAD software as the reference plane for deformation compensation; Step 2-3, selecting the intersection point of the wing root edge line and the aircraft wing chord plane on the beam plane of the aircraft metal beam part model in the 3D CAD software as the deformation compensation reference point 3 of the aircraft metal beam part model; Steps 2-4: In the 3D CAD software, the deformation compensation reference point of the aircraft metal beam part model is used as the starting point, and the intersection of the deformation compensation reference plane and the aircraft wing chord plane is used as the deformation compensation direction of the aircraft metal beam part model; Step 2-5: Establish a deformation compensation coordinate system 4 with the deformation compensation reference point of the aircraft metal beam part model as the coordinate system origin, the deformation compensation direction of the aircraft metal beam part model as the coordinate system X-axis, and the deformation compensation reference plane as the coordinate system Y-axis; In steps 2-6, select the Radial command in the 3D CAD software, use the deformation compensation reference point of the aircraft metal beam part model as the affine origin, the XY plane in the deformation compensation coordinate system as the affine XY plane, and the X axis in the deformation compensation coordinate system as the affine X axis. Set the initial value of the ratio in the X, Y, and Z directions to 1. Step 2-7, respectively establish deformation compensation parameters PMdi=Mdi of the aircraft metal beam model in the 3D CAD software, where i is a positive integer from 1 to 12; Step 2-8, create the month parameter Month in the 3D CAD software, and set the initial value to 1; Step 2-9: Create the deformation compensation X-axis ratio parameter Xrate in the 3D CAD software, and set the initial value to 1; Step 2-10, in the 3D CAD software, use the formula editor to make the X-ratio in the established radiation command equal to the value of the parameter Xrate; Step 2-11: Set the automatic update of the part module to manual update in the 3D CAD software; In step 2-12, a reaction command is selected in the 3D CAD software knowledge module. In the reaction command, the source type is selected as the metal beam deformation compensation entity. In the available event, update is selected. A program is written in the work instruction to automatically determine the current month and select corresponding deformation compensation parameters. A deformation compensation dynamic model 2 of the aircraft metal beam part is established.

[0027] In a specific implementation of the embodiment of the present invention, the implementation process of the above steps 2-12 may include the following steps: Step 2-12-1, use the month(now()) function to read the month in the current system time, and assign the month to the month parameter Month established in the 3D CAD software; Step 2-12-2, select the aircraft metal beam part deformation compensation parameter PMdi corresponding to the month according to the value of the month parameter Month, where the value of i is the month value of Month; Step 2-11-3, by writing a program, calculate the value of the deformation compensation X-axis ratio parameter Xrate based on the selected aircraft metal beam part deformation compensation parameter PMdi. The calculation formula is: Xrate=(1-PMdi).

[0028] In one implementation of the present invention, step 3 includes opening the established aircraft metal beam part deformation compensation dynamic model 2 and activating the program in the reaction command by updating to establish the aircraft metal beam part deformation compensation model for the current month. The specific implementation process of step 3 may include the following steps: Step 31, opening the established deformation compensation dynamic model of the aircraft metal beam part in 3D CAD software; In step 32, select the update command in the 3D CAD software to activate the program in the response command, automatically determine the current month, select the corresponding deformation compensation parameter PMdi, and calculate the deformation compensation X-axis ratio parameter Xrate value, thereby establishing a deformation compensation model for aircraft metal beam parts based on the current month.

[0029] For example, in this embodiment, the month in the system time is July. Select the update command to activate the program in the response command, complete the determination of the current month and the deformation compensation parameter PMdi=PMd7=0.2, and automatically calculate the deformation compensation X-axis ratio parameter Xrate; Xrate=(1-P Mdi); Xrate=(1- PMd7)=(1-0.2)=0.8.

[0030] Based on the deformation compensation parameters in July, an automatic model of deformation compensation model of aircraft metal beam parts was realized in July.

[0031] The present invention provides a design and use method for a dynamic model of deformation compensation for aircraft metal beam parts. The method first obtains deformation compensation parameters for the aircraft metal beam parts. Subsequently, a reaction is established in the aircraft metal beam part deformation compensation model using three-dimensional CAD software. In the reaction, a program automatically reads the current month and selects the deformation compensation parameters corresponding to the current month, thereby establishing a deformation compensation model for the aircraft metal beam parts. Based on the established deformation compensation model for the aircraft metal beam parts, a process operator can open the established dynamic model of deformation compensation for the aircraft metal beam parts, execute an update operation to activate the logic program in the reaction, and automatically complete the modeling of a deformation compensation model for the aircraft metal beam parts for the current month. The technical solution provided by the embodiments of the present invention has the following beneficial effects: (1) The design and use method of the deformation compensation dynamic model of aircraft metal beam parts provided by the present invention is used to realize the software packaging of the deformation compensation dynamic model of aircraft metal beam parts in different months of the year. Based on the preparation of the reaction program under the knowledge module in the model, the process personnel realize the automatic construction and automatic dynamic precise compensation of the deformation compensation model of aircraft metal beam parts in different months by updating the reaction program of the activation model. This solves the problem of excessive deformation of the metal beam along the length direction after processing under the influence of multiple factors such as different factory temperatures, realizes high-quality processing of metal beam parts, and ensures the efficient development and rapid batch production of large aircraft.

[0032] (2) The design and use method of the dynamic model for deformation compensation of aircraft metal beam parts provided by the present invention changes the traditional thinking of single results of the model, practices the automatic acquisition and change of the multi-state of the model, and provides a new solution for the multi-state deformation compensation of large aircraft long stringers, beams, and wall panels.

[0033] Although the embodiments disclosed herein are as described above, the contents are merely provided to facilitate understanding of the present invention and are not intended to limit the present invention. Any person skilled in the art may make any modifications and variations in the form and details of the embodiments without departing from the spirit and scope of the present invention. However, the scope of patent protection of the present invention shall remain subject to the scope defined by the appended claims.

Claims

1. A design and use method of a dynamic model for deformation compensation of aircraft metal beam parts, characterized in that: include: Step 1: Obtain deformation compensation parameters of aircraft metal beam parts through processing inspection; Step 2: establishing a reaction in the aircraft metal beam part model to establish a deformation compensation dynamic model of the aircraft metal beam part; the reaction refers to: realizing a deformation response of the deformation compensation dynamic model of the aircraft metal beam part using a program; Step 3: Using the established deformation compensation dynamic model of aircraft metal beam parts, automatically determine and select corresponding deformation compensation parameters for the current month to establish the deformation compensation model of aircraft metal beam parts for the current month.

2. The method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts according to claim 1, characterized in that: The step 1 includes: selecting an aircraft metal beam part, and establishing deformation compensation parameters of the aircraft metal beam part in different months of a year through processing and testing.

3. The method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts according to claim 2, characterized in that: The step 1 comprises: Step 11, selecting an aircraft metal beam part with the same processing technology as an object for obtaining deformation compensation parameters of the aircraft metal beam part; Step 12, measuring the total length L of the aircraft metal beam part; Step 13, processing the aircraft metal beam parts according to the processing technology every month, and measuring the actual total length RL of the aircraft metal beam parts after processing; Step 14, calculate the deformation compensation parameter Mdi of the aircraft metal beam parts in each month, and complete the establishment of the deformation compensation parameter Mdi of the aircraft metal beam parts throughout the year. The calculation formula is: Mdi=-(RL-L)*t / (L*1000); Where i is a positive integer from 1 to 12; t is the compensation coefficient, and its value range is 0 <t≤1。 4. The method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts according to claim 1, characterized in that: The step 2 includes: establishing a reaction in the aircraft metal beam part model through a program, wherein the reaction is used to automatically determine the current month and select the deformation compensation parameters corresponding to the current month by judging the user's operation action, thereby establishing the aircraft metal beam part deformation compensation model.

5. The method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts according to claim 4, characterized in that: The step 2 comprises the following steps: Step 2-1, select the aircraft metal beam model in the 3D CAD software; Step 2-2, selecting the beam plane of the aircraft metal beam part model in the 3D CAD software as the reference plane for deformation compensation; Step 2-3, selecting in 3D CAD software the intersection of the wing root edge line and the aircraft wing chord plane on the beam plane of the aircraft metal beam part model as a deformation compensation reference point of the aircraft metal beam part model; Steps 2-4: In the 3D CAD software, the deformation compensation reference point of the aircraft metal beam part model is used as the starting point, and the intersection of the deformation compensation reference plane and the aircraft wing chord plane is used as the deformation compensation direction of the aircraft metal beam part model; Step 2-5: Establish a deformation compensation coordinate system with the deformation compensation reference point of the aircraft metal beam part model as the origin of the coordinate system, the deformation compensation direction of the aircraft metal beam part model as the X-axis of the coordinate system, and the deformation compensation reference plane as the Y-axis of the coordinate system; In steps 2-6, select the Radial command in the 3D CAD software, use the deformation compensation reference point of the aircraft metal beam part model as the affine origin, the XY plane in the deformation compensation coordinate system as the affine XY plane, and the X axis in the deformation compensation coordinate system as the affine X axis. Set the initial value of the ratio in the X, Y, and Z directions to 1. Step 2-7, respectively establish deformation compensation parameters PMdi=Mdi of the aircraft metal beam model in the 3D CAD software, where i is a positive integer from 1 to 12; Step 2-8, create the month parameter Month in the 3D CAD software, and set the initial value to 1; Step 2-9: Create the deformation compensation X-axis ratio parameter Xrate in the 3D CAD software, and set the initial value to 1; Step 2-10, in the 3D CAD software, use the formula editor to make the X-ratio in the established radiation command equal to the value of the parameter Xrate; Step 2-11: Set the automatic update of the part module to manual update in the 3D CAD software; Step 2-12: Select a reaction command in the 3D CAD software knowledge module, select Metal Beam Deformation Compensation Entity as the source type in the reaction command, select Update as the available event, and write a program in the work instruction to automatically determine the current month and select the corresponding deformation compensation parameters; A dynamic model of deformation compensation for aircraft metal beam parts is established.

6. The method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts according to claim 5, characterized in that: The steps 2-12 include: Step 2-12-1, use the month(now()) function to read the month in the current system time, and assign the month to the month parameter Month established in the 3D CAD software; Step 2-12-2, select the aircraft metal beam part deformation compensation parameter PMdi corresponding to the month according to the value of the month parameter Month, where the value of i is the month value of Month; Step 2-12-3, by writing a program, calculate the value of the deformation compensation X-axis ratio parameter Xrate based on the selected aircraft metal beam part deformation compensation parameter PMdi. The calculation formula is: Xrate=(1-PMdi).

7. The method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts according to claim 5, characterized in that: The step 3 includes: opening the established aircraft metal beam part deformation compensation dynamic model, activating the program in the reaction command by updating, so as to establish the aircraft metal beam part deformation compensation model of the current month.

8. The method for designing and using a dynamic model for deformation compensation of aircraft metal beam parts according to claim 7, characterized in that: The step 3 specifically includes the following steps: Step 31, opening the established deformation compensation dynamic model of the aircraft metal beam part in 3D CAD software; In step 32, select the update command in the 3D CAD software to activate the program in the response command, automatically determine the current month, select the corresponding deformation compensation parameter PMdi, and calculate the deformation compensation X-axis ratio parameter Xrate value, thereby establishing a deformation compensation model for aircraft metal beam parts based on the current month.

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