A method for measuring machining parameters of propeller blades

Abstract

The present invention provides a method for measuring propeller blade machining parameters, comprising establishing a three-dimensional propeller model, obtaining a top view of the three-dimensional model, reconstructing a two-dimensional top view based on the top view data at a 1:1 ratio, determining a reference baseline, determining a reference angle, obtaining the angle and radius values ​​required for machining, restoring the obtained angles to the three-dimensional model, obtaining the height values ​​required for machining, and ultimately obtaining the machining parameters for all blades. By converting the three-dimensional model and the two-dimensional top view, the present invention can accurately obtain the radius, angle, and height required for machining, provided only rectangular coordinate data is provided on a drawing. Furthermore, a given propeller rectangular coordinate design can be converted into a propeller manufacturing process method that matches cylindrical coordinates, simplifying the process and utilizing existing equipment resources for measurement and machining, thereby enabling smooth propeller manufacturing.

Description

Technical Field

[0001] The present invention relates to the technical field of propeller manufacturing, and in particular to a method for measuring processing parameters of propeller blades. Background Art

[0002] Propellers are rotating bodies with irregular, complex curved blades, requiring extremely high manufacturing precision. Typically, based on the design data in the drawings, the propeller is cast, measured, machined, polished, and inspected for flaws in the blank. Conventional design drawings list key parameters such as cross-sectional radius, pitch angle, and blade thickness in cylindrical coordinate format. With the advancement of propeller design technology and the evolution of design concepts, more and more design firms are providing propeller manufacturers with design parameters directly in rectangular coordinates, making it difficult for manufacturers to intuitively obtain the processing parameters. Summary of the Invention

[0003] In order to overcome the technical problem in the prior art that propeller processing parameters cannot be obtained based on rectangular coordinate system data, the present invention provides a method for measuring propeller blade processing parameters.

[0004] The technical solution adopted by the present invention to achieve the above-mentioned object is: a method for measuring the processing parameters of a propeller blade, comprising the following steps:

[0005] S1: Build a three-dimensional propeller model based on the hub, blade position data and pitch in the rectangular coordinate system of the design drawing;

[0006] S2: Obtain a bottom view of the 3D model;

[0007] S3: Obtain position data in the bottom view of the 3D model and use 2D software to draw a 2D bottom view in a 1:1 ratio.

[0008] S4: Determine the reference baseline;

[0009] S5: Determine the reference angle;

[0010] S6: Obtain the angle and radius values ​​required for processing;

[0011] S7: restoring the obtained angle value and radius value to the three-dimensional model;

[0012] S8: Obtain the height value required for processing;

[0013] S9: Repeat the above steps S1-S8 to obtain the processing parameters of each blade on the propeller;

[0014] Preferably, the step S3 is specifically: selecting a bottom view mode of the three-dimensional model in the three-dimensional drawing software, projecting the propeller blade pressure surface into a plane figure, using the measurement tool provided by the software to obtain the position data of the blade tip, the propeller tip circle, the propeller hub small end face, the center point of the hub small end face, the center line of the blade pressure surface, the blade pressure surface following edge line, and the blade pressure surface leading edge line, the position of the blade tip is the coordinate position of the blade reference point (0, 0), and according to the position data obtained in S2, using the two-dimensional drawing software to restore and draw the two-dimensional graph of the propeller blade pressure surface in a 1:1 ratio;

[0015] Preferably, the method for obtaining the reference reference line in step S4 is specifically as follows: in the two-dimensional diagram of the propeller blade pressure surface obtained in S3, the small end surface of the hub is used as the reference surface, the blade tip position is determined, that is, the coordinate position of the blade reference point (0, 0), and the center point of the small end surface of the hub and the blade tip are connected to form a reference reference line;

[0016] Preferably, the reference angle in step S5 is determined by: taking the center point of the small end face as the starting point, drawing a straight line tangent to the center line of the thickness of the blade pressure surface to obtain a positioning reference line, and the angle between the positioning reference line and the reference reference line is the reference angle;

[0017] Preferably, the step S6 specifically includes the following steps:

[0018] S6.1: In the two-dimensional drawing, using the small end face of the hub as the reference plane, mark the rectangular coordinate section position line of the blade according to the rectangular coordinate system data on the design drawing. Obtain the first intersection point of the section position line with the blade pressure surface trailing edge line, the second intersection point of the section position line with the blade pressure surface centerline, and the third intersection point of the section position line with the blade pressure surface leading edge line.

[0019] S6.2: Connect the center point of the small end face of the hub and the first intersection point to obtain the edge intersection line;

[0020] S6.3: Connect the center point of the hub small end face and the second intersection point to obtain the center intersection line;

[0021] S6.4: Connect the center point of the hub small end face and the third intersection point to obtain the guide edge intersection line;

[0022] S6.5: Obtain the trailing edge angle between the positioning reference line and the trailing edge intersection line, the center angle between the positioning reference line and the center intersection line, and the leading edge angle between the positioning reference line and the leading edge intersection line. Measure and record the trailing edge angle, center angle, and leading edge angle.

[0023] S6.6: Construct a circle with the center point of the hub small end face as the center, and intersect the blade pressure surface trailing edge line at the first intersection point. The radius of this circle is the blade pressure surface trailing edge position radius.

[0024] S6.7: Construct a circle with the center point of the hub small end face as the center, and intersect the blade centerline at the second intersection point. The radius of this circle is the radius of the measuring point on the blade pressure surface centerline.

[0025] S6.8: Construct a circle with the center point of the hub small end face as the center, and intersect the blade pressure side leading edge line at the third intersection point. The radius of this circle is the blade pressure side leading edge position radius.

[0026] Preferably, step S8 includes the following steps:

[0027] S8.1: Select the rear view mode for the 3D model obtained in S7. With the first intersection of the blade pressure surface edge line and the circle in S6.6 as the vertex, draw a vertical line to the small end face of the hub to obtain the height of the blade pressure surface edge position.

[0028] S8.2: Using the second intersection of the blade pressure surface centerline and the circle in S6.7 as the vertex, draw a perpendicular line to the small end face of the hub to obtain the blade centerline height.

[0029] S8.3: Using the third intersection of the leading edge line of the blade pressure surface and the center circle of S6.8 as the vertex, draw a perpendicular line to the small end face of the hub to obtain the height of the leading edge of the blade pressure surface.

[0030] Compared with the existing technology, the present invention has the advantage that, through the conversion of a three-dimensional model and a two-dimensional bottom view, the radius, angle and height required for processing can be accurately obtained under the condition that only rectangular coordinate data is given in the drawing; a given propeller rectangular coordinate design scheme can be converted into a propeller manufacturing process method that matches the cylindrical coordinates, thus simplifying the process and utilizing existing equipment resources for measurement and processing to achieve smooth manufacturing of the propeller. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is a flow chart of the method of the present invention.

[0032] Figure 2 It is a two-dimensional bottom view of the propeller measured by the present invention.

[0033] Figure 3 It is a rear view of the three-dimensional model of the propeller measured by the present invention.

[0034] In the figure: 1: propeller blade pressure surface; 2: blade tip; 3: propeller tip circle; 4: propeller hub small end surface; 5: center point of hub small end surface; 6: blade pressure surface centerline; 7: blade pressure surface trailing edge line; 8: blade pressure surface leading edge line; 9: reference datum line; 10: positioning datum line; 11: reference angle; 12: cross-section position line; 13: first intersection point; 14: second intersection point; 15: third intersection point; 16: trailing edge intersection line; 17: center intersection line; 18: leading edge intersection line; 19: trailing edge angle; 20: center angle; 21: leading edge angle; 22: blade pressure surface trailing edge position radius; 23: blade pressure surface centerline measuring point position radius; 24: blade pressure surface leading edge position radius; 25: blade pressure surface trailing edge position height; 26: blade centerline position height; 27: blade pressure surface leading edge position height. DETAILED DESCRIPTION

[0035] A method for measuring propeller blade processing parameters of the present invention, in a specific embodiment, comprises the following steps:

[0036] S1: Create a three-dimensional propeller model in UG software based on the hub, blade position data and pitch provided by the rectangular coordinate system of the design drawing;

[0037] S2: Obtain a bottom view of the 3D model;

[0038] S3: Obtain position data in the bottom view of the three-dimensional model, and use CAD drawing software to restore and draw a two-dimensional bottom view at a 1:1 ratio; specifically: select the bottom view mode of the three-dimensional model in the UG software, project the propeller blade pressure surface 1 into a plane figure, and use the measurement tool provided by the software to obtain the position data of the blade tip 2, propeller tip circle 3, propeller hub small end face 4, hub small end face center point 5, blade pressure surface center line 6, blade pressure surface following edge line 7, and blade pressure surface leading edge line 8. The position of the blade tip 2 is the coordinate position of the blade reference point (0, 0). According to the position data obtained in S2, use CAD drawing software to restore and draw a two-dimensional diagram of the propeller blade pressure surface 1 at a 1:1 ratio;

[0039] S4: Determine a reference reference line. Specifically, in the two-dimensional diagram of the propeller blade pressure surface obtained in S3, use the hub small end surface 4 as the reference surface, determine the position of the blade tip 2, that is, the coordinate position of the blade reference point (0, 0), and connect the hub small end surface center point 5 and the blade tip 2 to form a reference reference line 9;

[0040] S5: Determine the reference angle, specifically: starting from the center point 5 of the small end face, draw a straight line tangent to the center line of the blade pressure surface thickness, to obtain a positioning reference line 10, and the angle between the positioning reference line 10 and the reference reference line 9 is the reference angle 11;

[0041] S6: Obtain the angle and radius values ​​required for processing, which specifically includes the following steps:

[0042] S6.1: In the two-dimensional drawing, using the hub small end surface 4 as the reference plane, determine a section at a certain distance from the propeller blade tip 2 according to the rectangular coordinate data in the design drawing. Based on the position data of this section in the rectangular coordinate system, mark the rectangular coordinate section position line 12 of the blade. Determine a first intersection 13 of the section position line 12 with the blade pressure surface trailing edge line 7, a second intersection 14 of the section position line 12 with the blade pressure surface centerline 6, and a third intersection 15 of the section position line 12 with the blade pressure surface leading edge line 8;

[0043] S6.2: Connect the center point 5 of the hub small end face and the first intersection point 13 to obtain the edge intersection line 16;

[0044] S6.3: Connect the center point 5 of the hub small end surface and the second intersection point 14 to obtain the center intersection line 17;

[0045] S6.4: Connect the center point 5 of the hub small end face and the third intersection point 15 to obtain the guide edge intersection line 18;

[0046] S6.5: Obtain trailing edge angle 19 between positioning reference line 10 and trailing edge intersection line 16, center angle 20 between positioning reference line 10 and center intersection line 17, and leading edge angle 21 between positioning reference line 10 and leading edge intersection line 18. Measure and record the angles of trailing edge angle 19, center angle 20, and leading edge angle 21.

[0047] S6.6: Construct a circle with the center point 5 of the hub small end face as the center. The circle intersects the blade pressure surface trailing edge line 7 at the first intersection point 13. The radius of the circle is the blade pressure surface trailing edge radius 22.

[0048] S6.7: Construct a circle with the center point 5 of the hub small end face as the center. The circle intersects the blade centerline 6 at the second intersection point 14. The radius of the circle is the radius of the blade pressure surface centerline measurement point 23.

[0049] S6.8: Construct a circle with the center point 5 of the hub small end face as the center. The circle intersects the blade pressure side leading edge line 8 at the third intersection point 15. The radius of the circle is the blade pressure side leading edge position radius 24.

[0050] S7: restoring the obtained angle value and radius value to the three-dimensional model, that is, restoring the angle value and radius value obtained in the two-dimensional bottom view to the bottom view mode of the three-dimensional model in a 1:1 ratio;

[0051] S8: Obtaining the height value required for processing, specifically including the following steps:

[0052] S8.1: Select the rear view mode in the 3D model obtained in S7. With the first intersection 13 of the blade pressure surface trailing edge line 7 and the circle in S6.6 as the vertex, draw a perpendicular line to the hub small end face 4 to obtain the blade pressure surface trailing edge position height 25;

[0053] S8.2: With the second intersection 14 of the blade pressure surface centerline 6 and the center circle of S6.7 as the vertex, draw a perpendicular line to the hub small end face 4 to obtain the blade centerline position height 26;

[0054] S8.3: With the third intersection 15 of the blade pressure side leading edge line 8 and the center circle of S6.8 as the vertex, draw a perpendicular line to the hub small end face 4 to obtain the blade pressure side leading edge position height 27.

[0055] S9: Repeat the above steps S1-S8 to obtain the processing parameters of each blade on the propeller and apply them to the processing.

[0056] The present invention is described by way of example, and those skilled in the art will appreciate that various changes or equivalent substitutions may be made to these features and embodiments without departing from the spirit and scope of the present invention. Furthermore, under the teachings of the present invention, these features and embodiments may be modified to suit specific circumstances and materials without departing from the spirit and scope of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are intended to be within the scope of the present invention.

Claims

1. A method for measuring propeller blade processing parameters, characterized in that: The following steps are involved: S1: Build a three-dimensional propeller model based on the hub, blade position data and pitch in the rectangular coordinate system of the design drawing; S2: Obtain a bottom view of the 3D model; S3: Obtain position data in the bottom view of the 3D model and use 2D software to draw a 2D bottom view at a 1:1 ratio: Select the top view mode of the three-dimensional model in the three-dimensional drawing software, project the propeller blade pressure surface (1) into a plane figure, use the measurement tool provided by the software to obtain the position data of the blade tip (2), the propeller tip circle (3), the propeller hub small end face (4), the hub small end face center point (5), the blade pressure surface center line (6), the blade pressure surface following edge line (7), and the blade pressure surface leading edge line (8). The position of the blade tip (2) is the coordinate position of the blade reference point (0, 0). Based on the obtained position data, use the two-dimensional drawing software to restore and draw the propeller blade pressure surface (1) in a 1:1 ratio. S4: Determine the reference baseline; S5: Determine the reference angle; S6: Get the angle and radius values ​​required for processing: S6.1: In the two-dimensional drawing, with the hub small end face (4) as the reference plane, mark the blade rectangular coordinate section position line (12) according to the rectangular coordinate system data of the design drawing, and obtain the first intersection point (13) of the section position line (12) and the blade pressure surface trailing edge line (7), the second intersection point (14) of the section position line (12) and the blade pressure surface center line (6), and the third intersection point (15) of the section position line (12) and the blade pressure surface leading edge line (8); S6.2: Connect the center point (5) of the small end face of the hub and the first intersection point (13) to obtain the edge intersection line (16); S6.3: Connect the center point (5) of the small end face of the hub and the second intersection point (14) to obtain the center intersection line (17); S6.4: Connect the center point (5) of the small end face of the hub and the third intersection point (15) to obtain the guide edge intersection line (18); S6.5: Obtain the trailing edge angle (19) between the positioning reference line (10) and the trailing edge intersection line (16), and the center angle (20) between the positioning reference line (10) and the center intersection line (17), wherein the positioning reference line (10) is obtained by drawing a straight line tangent to the center line of the trailing edge thickness of the blade pressure surface with the center point (5) of the hub small end surface as the starting point, and the leading edge angle (21) between the positioning reference line (10) and the trailing edge intersection line (18), and measure and record the angles of the trailing edge angle (19), the center angle (20), and the trailing edge angle (21); S6.6: Construct a circle with the center point (5) of the hub small end face as the center, and intersect the blade pressure surface trailing edge line (7) at the first intersection point (13). The radius of this circle is the blade pressure surface trailing edge position radius (22); S6.7: Construct a circle with the center point (5) of the hub small end face as the center, and intersect it with the center line (6) of the blade pressure surface at the second intersection point (14). The radius of this circle is the radius of the measuring point position (23) of the blade pressure surface center line. S6.8: Draw a circle with the center point (5) of the small end face of the hub as the center, and intersect it with the edge line of the blade pressure surface guide edge (8) at the third intersection point (15). The radius of this circle is the radius of the blade pressure surface guide edge position (24). S7: restoring the obtained angle value and radius value to the three-dimensional model; S8: Get the height value required for processing: S8.1: Select the rear view mode in the three-dimensional model obtained in S7, take the first intersection point (13) of the blade pressure surface edge line (7) and the circle in S6.6 as the vertex, and draw a vertical line to the small end face (4) of the hub, that is, obtain the blade pressure surface edge position height (25); S8.2: With the second intersection point (14) of the blade pressure surface centerline (6) and the circle in S6.7 as the vertex, draw a vertical line to the small end face (4) of the hub to obtain the blade centerline position height (26); S8.3: With the third intersection point (15) of the blade pressure surface leading edge line (8) and the center circle of S6.8 as the vertex, draw a vertical line to the small end face (4) of the hub to obtain the blade pressure surface leading edge position height (27); S9: Repeat the above steps S1-S8 to obtain the processing parameters of each blade on the propeller.

2. A propeller blade processing parameter measurement method according to claim 1, characterized in that: The method for obtaining the reference reference line in step S4 is specifically as follows: in the two-dimensional diagram of the propeller blade pressure surface obtained in S3, the hub small end surface (4) is used as the reference surface, the position of the blade tip (2) is determined, that is, the coordinate position of the blade reference point (0, 0), and the hub small end surface center point (5) and the blade tip (2) are connected to form a reference reference line (9).

3. The method for measuring propeller blade processing parameters according to claim 2, characterized in that: The determination of the reference angle in step S5 is specifically as follows: starting from the center point (5) of the small end face of the hub, a straight line is drawn that is tangent to the center line of the edge thickness of the pressure surface of the blade to obtain a positioning reference line (10), and the angle between the positioning reference line (10) and the reference reference line (9) is the reference angle (11).

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