A design method of an aero test process model

Abstract

The application discloses a design method of an aeronautical test process model. Firstly, an aircraft design datum is extracted in a three-dimensional design software CATIA; then, a marking design datum is established according to the extracted aircraft design datum; then, a test center point in a two-dimensional marking drawing is obtained through the offset of a standard size in the two-dimensional marking drawing and a required datum line of marking in the marking design datum; then, the test center point in the two-dimensional marking drawing is projected to establish a three-dimensional test center point; three-dimensional datum lines are sequentially established; then, the three-dimensional datum lines are discretized; finally, three-dimensional datum line discrete point coordinates are output according to the obtained discrete points, and three-dimensional test center point coordinates are obtained. The application can be directly used for aircraft static test marking, effectively solves the problems of long manual marking period and low precision, and greatly shortens the aircraft static test period.

Description

Technical Field

[0001] This invention relates to the field of aircraft manufacturing technology, and in particular to a design method for an aviation test process model. Background Technology

[0002] The location for static testing of aircraft typically requires technicians to mark lines on the aircraft surface using measuring tools. This process begins by locating visible markers such as rivets or regular holes on the aircraft surface as baselines. Then, the intersection points of these lines are obtained by parallel line transfer. Finally, specialized tools are used to mark the outline of the test location from the drawings onto the aircraft surface. Due to the large dimensions of aircraft and the cumbersome marking process, dozens of people are usually required to work together, and the entire marking cycle can take several days. This demanding task is difficult to meet the rapid and precise requirements of modern aircraft static testing. Summary of the Invention

[0003] The technical problem solved by this invention is to provide a design method for an aviation test process model, so as to solve the problems in the background art mentioned above.

[0004] The technical problem solved by this invention is achieved by the following technical solution: A design method for an aerospace test process model, the specific steps of which are as follows: Step 1) Extract aircraft design baselines In the 3D design software CATIA, the theoretical outer surface of the 3D aircraft component, the 3D reference surface, and the outline of the corresponding component on the scribing design reference surface are extracted. The theoretical outer surface of the 3D aircraft component includes the theoretical outer surface of large components such as fuselage, wings, and tail. The 3D reference surface includes the aircraft horizontal reference surface, symmetry reference surface, reference surfaces of each frame, beam reference surface, and rib reference surface. Step 2) Establish the design benchmark for line marking In the 3D design software CATIA, the outline of the corresponding component is obtained based on the aircraft design datum extracted in step one). Then, the datum line required for scribing is obtained by intersecting the scribing design datum plane with the aircraft design datum plane in step one. Step 3) Establish the two-dimensional experimental center point In the scribing design reference plane established in step two), the test center point in the two-dimensional scribing drawing is obtained on the scribing design reference plane by using the standard dimensions in the two-dimensional scribing drawing and the offset of the scribing reference line obtained in step two). Step 4) Establish the three-dimensional test center point In the 3D design software CATIA, the test center point in the 2D scribing diagram obtained in step 3) is perpendicular to the scribing design reference plane and projected onto the required 3D aircraft component theoretical shape surface to obtain the test center point of the theoretical position on the surface of the aircraft component. Step 5) Establish a three-dimensional baseline In the scribing design datum plane established in step 2), the design datum line is perpendicularly passed through the scribing design datum plane to obtain the datum plane, and the datum plane intersects with the theoretical outer surface to obtain the three-dimensional datum line on the theoretical outer surface of each major component, and the three-dimensional datum line on the theoretical outer surface of the major component is used as the verification reference line. Step 6) Discretize the three-dimensional baseline Establish a reference plane perpendicular to the scribing design reference plane using the reference line obtained in step 2), and then find the intersection line with the theoretical outer surface of the three-dimensional aircraft component to obtain the reference line required for three-dimensional scribing. Then divide the reference line required for three-dimensional scribing into multiple discrete points. Step 7) Output the coordinates of the three-dimensional test center point Based on the discrete points obtained in step six, the coordinates of the discrete points of the three-dimensional baseline are output according to the three-dimensional point coordinate format that the auxiliary marking device can recognize, thereby obtaining the coordinates of the three-dimensional test center point.

[0005] In this invention, in step four), the test center points in the two-dimensional line drawing include test center points with size markings and points whose test center point positions are not directly marked. The specific steps for establishing three-dimensional test center points for test center points with size markings are as follows: The test center point with size markings is projected perpendicularly to the established scribing design reference plane onto the theoretical outer surface of the three-dimensional aircraft component to obtain the test center point of the theoretical position on the surface of the aircraft component. The specific steps for establishing the center point of a three-dimensional experiment for points whose center point positions are not directly marked are as follows: First, select three points where the center point is not directly marked. Then, project these three points perpendicular to the scribing design reference plane onto the theoretical outer surface of the three-dimensional aircraft component. Next, using the projection points of these three points as reference points on the theoretical outer surface of the three-dimensional aircraft component, translate the theoretical three-dimensional test center point of the points where the center point is not directly marked according to the arc length based on the actual dimensions of the test profile of the points where the center point is not directly marked.

[0006] In this invention, in step seven), the auxiliary marking device includes a laser device.

[0007] Beneficial effects: This invention can be directly used for scribing in aircraft static tests, effectively solving the problems of long cycle and low accuracy of manual scribing, and greatly shortening the cycle of aircraft static tests. Attached Figure Description

[0008] Figure 1 This is a two-dimensional scribing diagram of an aircraft component in a preferred embodiment of the present invention.

[0009] Figure 2 This is a schematic diagram of the three-dimensional test center point of an aircraft component in a preferred embodiment of the present invention.

[0010] Figure 3 This is a schematic diagram of the discrete points of the baseline in a preferred embodiment of the present invention. Detailed Implementation

[0011] To make the technical means, creative features, objectives and effects of this invention easier to understand, the invention will be further described below with reference to specific illustrations.

[0012] A design method for an aerospace test process model, the specific steps of which are as follows: Step 1) Extract aircraft design baselines according to Figure 1 The aircraft heading shown is extracted in the 3D design software CATIA. Figure 1 The three-dimensional theoretical shape surface of the aircraft component shown in the figure, the three-dimensional reference surface and the outline of the corresponding component on the scribing design reference surface; the three-dimensional theoretical shape surface of the aircraft component includes the theoretical shape surface of large components such as fuselage, wings, and tail; the three-dimensional reference surface includes the aircraft horizontal reference surface, symmetry reference surface, reference surfaces of each frame, beam reference surface, and rib reference surface. Figure 1 The aircraft component shown has 19 test points, namely 1, 2, 3-1, 3-2, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14-1, 14-2, 15-1, 15-2, 15-3, and 15-4, which are 20 test positions. The static test positions have four different external contours, numbered 6#, 7#, 9#, and 14# respectively. Step 2) Establish the design benchmark for line marking In the 3D design software CATIA, the aircraft design datum extracted in step one is obtained... Figure 1 The outline of the component shown is obtained by... Figure 1 The scribing design reference plane intersects with the aircraft design reference plane to obtain the scribing design reference, namely reference line 1 and reference line 2; Step 3) Establish the two-dimensional experimental center point according to Figure 1 The horizontal dimensions X1, X2, X3, X4, X5, X6, X7, X8, X9, X10, X11, X12, the vertical dimensions Z1, Z2, Z3, Z4, the diagonal dimensions Y1, Y2, Y3, Y4, the baseline 1, the baseline 2, and the 19 test center points 1, 2, 3-1, 3-2, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14-1, 14-2, 15-1, 15-2, 15-3, 15-4 are marked on the scribing design reference plane. Step 4) Establish the three-dimensional test center point like Figure 2 As shown, Figure 1Twelve test center points with size markings, numbered 1, 2, 4, 5, 6, 7, 8, 9, 10, 11, 12, and 13, are perpendicular to the established scribing design reference plane and projected onto the theoretical outer surface of the three-dimensional aircraft component to obtain the test center points of the theoretical position on the surface of the aircraft component. like Figure 2 As shown, for Figure 1 For the eight points (3-1, 3-2, 14-1, 14-2, 15-1, 5-2, 15-3, and 15-4) where the test center point is not directly marked, the location of the test center point needs to be... Figure 1 Points A, B, and C are projected perpendicularly to the design reference plane onto the theoretical outer surface of the three-dimensional aircraft component. Then, using the projection points of points A, B, and C as reference points on the theoretical outer surface of the three-dimensional aircraft component, the theoretical three-dimensional test center points of these eight points (3-1, 3-2, 14-1, 14-2, 15-1, 5-2, 15-3, and 15-4) are translated according to the arc length to obtain the actual dimensions of the 14# test profile. Step 5) Establish a three-dimensional baseline In the scribing design datum plane established in step 2), the design datum line is perpendicularly passed through the scribing design datum plane to obtain the datum plane, and the datum plane intersects with the theoretical outer surface to obtain the three-dimensional datum line on the theoretical outer surface of each major component, and the three-dimensional datum line on the theoretical outer surface of the major component is used as the verification reference line. Step 6) Discretize the three-dimensional baseline like Figure 3 As shown, through Figure 1 The reference lines 1 and 2 are established to form reference planes perpendicular to the scribing design reference plane. Then, the intersection lines with the theoretical outer surface of the three-dimensional aircraft component are obtained to obtain the three-dimensional reference lines 1 and 2. The three-dimensional reference lines 1 and 2 are then divided into multiple discrete points. Step 7) Output the coordinates of the three-dimensional test center point Based on the discrete points obtained in step six), and following the format of the three-dimensional points shown in Table 1, output the X, Y, and Z coordinates of the baseline discrete points obtained in step six and the three-dimensional test center point obtained in step four to the table. Use laser or other equipment to assist in rapid line drawing. The X, Y, and Z columns are entered as numbers without punctuation marks to obtain the coordinates of the three-dimensional test center point.

[0013] Table 1 1 X1 Y1 Z1 2 X2 Y2 Z2 3 X3 Y3 Z3 4 X4 Y4 Z4 5 X5 Y5 Z5 … … … … The specific embodiments described herein are merely illustrative examples of the present invention. Those skilled in the art to which this invention pertains may make various modifications or additions to the described specific embodiments or adopt similar methods to replace them, but without departing from the spirit of the present invention or exceeding the scope defined by the appended claims.

Claims

1. A design method for an aerospace test process model, characterized in that, First, extract the aircraft design datum in the 3D design software CATIA. Then, establish a scribing design datum based on the extracted aircraft design datum. Next, by comparing the standard dimensions in the 2D scribing drawing with the offsets of the required datum lines obtained from the scribing design datum, obtain the test center point in the 2D scribing drawing on the scribing design datum plane. Then, project the test center point in the 2D scribing drawing to establish the 3D test center point. Establish 3D datum lines sequentially, then discretize the 3D datum lines. Finally, based on the obtained discrete points, output the coordinates of the discrete points of the 3D datum lines, thereby obtaining the coordinates of the 3D test center point. The specific steps are as follows: Step 1) Extract aircraft design baselines In the 3D design software CATIA, the theoretical outer surface, 3D reference surface, and the outline of the corresponding component on the scribing design reference surface of the 3D aircraft component are extracted. The theoretical outer surface of the 3D aircraft component includes the theoretical outer surface of the fuselage, wing, and tail. The 3D reference surface includes the horizontal reference surface, symmetry reference surface, reference surfaces of each frame, beam reference surface, and rib reference surface of the aircraft. Step 2) Establish the design benchmark for line marking In the 3D design software CATIA, the outline of the corresponding component is obtained based on the aircraft design datum extracted in step one). Then, the datum line required for scribing is obtained by intersecting the scribing design datum plane with the aircraft design datum plane in step one. Step 3) Establish the two-dimensional experimental center point In the scribing design reference plane established in step two), the test center point in the two-dimensional scribing drawing is obtained on the scribing design reference plane by using the standard dimensions in the two-dimensional scribing drawing and the offset of the scribing reference line obtained in step two). Step 4) Establish the three-dimensional test center point In the 3D design software CATIA, the test center point in the 2D scribing diagram obtained in step 3) is perpendicular to the scribing design reference plane and projected onto the required 3D aircraft component theoretical shape surface to obtain the test center point of the theoretical position on the surface of the aircraft component. Step 5) Establish a three-dimensional baseline In the scribing design datum plane established in step 2), the design datum line is perpendicularly passed through the scribing design datum plane to obtain the datum plane, and the datum plane intersects with the theoretical outer surface to obtain the three-dimensional datum line on the theoretical outer surface of each major component, and the three-dimensional datum line on the theoretical outer surface of the major component is used as the verification reference line. Step 6) Discretize the three-dimensional baseline Establish a reference plane perpendicular to the scribing design reference plane using the reference line obtained in step 2), and then find the intersection line with the theoretical outer surface of the three-dimensional aircraft component to obtain the reference line required for three-dimensional scribing. Then divide the reference line required for three-dimensional scribing into multiple discrete points. Step 7) Output the coordinates of the three-dimensional test center point Based on the discrete points obtained in step six, the coordinates of the discrete points of the three-dimensional baseline are output according to the three-dimensional point coordinate format that the auxiliary marking device can recognize, thereby obtaining the coordinates of the three-dimensional test center point.

2. The design method for an aviation test process model according to claim 1, characterized in that, In step four), the test center point in the two-dimensional line drawing includes test center points with size markings and points whose test center point positions are not directly marked.

3. The design method for an aerospace test process model according to claim 2, characterized in that, The specific steps for establishing a three-dimensional test center point for test center points with dimension markings are as follows: The test center point with size markings is projected perpendicularly to the established scribing design reference plane onto the theoretical outer surface of the three-dimensional aircraft component to obtain the test center point of the theoretical position on the surface of the aircraft component.

4. The design method for an aerospace test process model according to claim 2, characterized in that, The specific steps for establishing the center point of a three-dimensional experiment for points whose center point positions are not directly marked are as follows: First, select three points where the center point is not directly marked. Then, project these three points perpendicular to the scribing design reference plane onto the theoretical outer surface of the three-dimensional aircraft component. Next, using the projection points of these three points as reference points on the theoretical outer surface of the three-dimensional aircraft component, translate the theoretical three-dimensional test center point of the points where the center point is not directly marked according to the arc length based on the actual dimensions of the test profile of the points where the center point is not directly marked.

5. The design method for an aerospace test process model according to claim 1, characterized in that, In step seven), the auxiliary marking equipment includes laser equipment.

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