Propeller blade section integrated adjustment method based on UG software

Abstract

The present application relates to the technical field of marine propeller, a propeller blade section integrated adjustment method based on UG software. First, the pitch value and thickness value of the propeller blade blank are measured and compared with the standard value marked on the construction drawing, and it is judged whether adjustment is needed. If adjustment is needed, the propeller model is constructed based on the UG NX modeling module, the propeller radius value r is input, the UG NX OPEN GRIP secondary development technology is used to automatically obtain the radius of each section of the propeller blade and make corresponding marking, the propeller blade section curve group to be adjusted is selected, the adjustment value of each section curve group of the blade is input, and the Z value of each section curve of the blade is adjusted and subsequent Z value adjustment calculation is performed at one time. Through the present application, the section curve group on the blade can be selected, and the section curve group can be adjusted integrally, so that the final propeller meets the standard requirements, and the method is simple and easy to operate.

Description

Technical Field

[0001] This invention relates to the field of marine propulsion technology. Background Technology

[0002] After the propeller is cast, it still needs to be ground and cut. Since there is an error between the blank after the propeller is cast and the standard value marked on the actual drawing, if the cast blank is ground and cut directly, the final propeller product will not meet the standard requirements. Summary of the Invention

[0003] To address the problem in existing technologies where discrepancies exist between the cast propeller blank and the standard values ​​on the drawings, resulting in the blank failing to meet standard requirements after grinding and cutting, this invention provides an integrated adjustment method for propeller blade cross-sections based on UG software.

[0004] The technical solution adopted by the present invention to achieve the above objectives is as follows:

[0005] A method for integrated adjustment of propeller blade cross-section based on UG software includes the following steps:

[0006] S1. Measure the pitch value of the propeller blade blank and the thickness value of the pitch point of the propeller blade blank.

[0007] S2. Compare the measured pitch and thickness values ​​of the propeller blade blank with the standard pitch and thickness values ​​of the propeller blade marked on the propeller blade construction drawings to determine whether the cross-sectional curve of the propeller blade needs to be adjusted.

[0008] S3. Propeller model built based on UG NX modeling module;

[0009] S4. Input the propeller radius value r, and use UG NX OPEN GRIP secondary development technology to automatically obtain the radius of each section of the propeller blade and make corresponding annotations;

[0010] S5. Select the propeller blade section curve group that needs to be adjusted, input the adjustment value of each section curve group, and adjust the Z value of each section curve of the blade in one go;

[0011] S6. Verify the adjusted blade cross-section curve to determine if the adjustment is incorrect;

[0012] S7. Use UG's sheet body inheritance curve feature function to display the adjusted blade section curve group as a sheet body.

[0013] Step S3, which involves constructing the propeller model based on the UG NX modeling module, includes the following steps:

[0014] S3-1. Obtain the two-dimensional coordinates of the blade section curve points and the propeller blade pitch value P from the propeller blade construction drawings, and input the two-dimensional coordinates of the blade section curve points into the UG NX modeling module;

[0015] S3-2. Connect the points of the blade section curve to form a spline curve;

[0016] S3-3. Calculate the helix angle θ of each radial section line of the propeller blade. The calculation formula is as follows:

[0017]

[0018] In the formula: P is the pitch value of each radius, and r is the radius value;

[0019] Based on the helix angle θ, rotate the spline curve;

[0020] S3-4. Calculate the back slope value L of each radius section line of the propeller blade. The calculation formula is as follows:

[0021] L=r·tanα

[0022] In the formula: r represents each radius value, and α represents the backslope angle;

[0023] Move the spline curve to the backsloping position based on the L value;

[0024] S3-5. Use UG's warp function to project the rotated and translated spline curve onto the cylindrical surface constructed with the corresponding r radius;

[0025] S3-6. Use UG's sheet construction function to connect the spline curves of each radius to obtain the propeller blade model.

[0026] The formula for calculating the radius of the blade cross-section curve in step S5 is as follows:

[0027]

[0028] Step S6 calculates the propeller radius position where the blade cross-section curve is located based on the radius value of the cross-section curve. The calculation formula is as follows:

[0029]

[0030] Adjust the Z-value of the blade cross-section curve according to the propeller radius position of the blade cross-section curve, referring to the cross-section adjustment table below:

[0031] Radius position casually Guide edge Adjusting the pitch Adjust height Z 02r Measurement data omitted Measurement data omitted no -8 0.25r Measurement data omitted Measurement data omitted no -7 0.3r Measurement data omitted Measurement data omitted no -5 0.4r Measurement data omitted Measurement data omitted no -5 0.5r Measurement data omitted Measurement data omitted no -3 0.6r Measurement data omitted Measurement data omitted no -2 0.7r Measurement data omitted Measurement data omitted no 0 0.8r Measurement data omitted Measurement data omitted no 0 0.9r Measurement data omitted Measurement data omitted no 3 0.95r Measurement data omitted Measurement data omitted no +5 0.975r Measurement data omitted Measurement data omitted no +6

[0032] After adjusting the Z value of the curve in step S6, the curve is verified to determine whether the adjustment is incorrect, including the following steps:

[0033] S6-1. Select point a on the blade cross-section curve before adjustment and record the coordinates (X, Y, Z) of the point;

[0034] S6-2. Select point a1 on the adjusted blade section curve that corresponds to point a, and record the coordinate values ​​(X1, Y1, Z1) of point a1.

[0035] S6-3. Calculate the difference in the Z direction between point a and point a1 in the coordinate system;

[0036] S6-4. Calculate the propeller radius position where the blade cross-section curve is located, and determine the Z value for adjusting the blade cross-section curve;

[0037] S6-5. Compare the difference in the Z direction between point a and point a1 in the coordinate system with the adjusted Z value of the blade section curve. If the two values ​​are the same, the adjustment is correct. If the two values ​​are different, the adjustment is incorrect. Then return to step S1.

[0038] The advantages of this invention compared to the prior art are:

[0039] First, measure the pitch and thickness of the propeller blade blank and compare them with the standard values ​​marked on the construction drawings to determine if adjustments are needed. If adjustments are needed, based on the propeller model built using the UG NX modeling module, input the propeller radius value r, select the propeller blade cross-section curve group that needs adjustment, calculate the radius value of each curve in each cross-section curve group based on the coordinate values ​​of the points on the blade cross-section curve group, and mark them accordingly. Adjust the Z value of each cross-section curve of the blade in one go. This invention can adjust the cross-section curve group in one go by selecting the cross-section curve group on the blade, so that the final propeller meets the standard requirements. The method is simple and easy to operate. Attached Figure Description

[0040] Figure 1 This is a flowchart of an integrated adjustment method for propeller blade cross-section based on UG software according to the present invention.

[0041] Figure 2 This is a flowchart of the Z-value adjustment method for an integrated adjustment method of propeller blade cross-section based on UG software according to the present invention.

[0042] Figure 3 This is a flowchart of the verification process after Z-value adjustment of an integrated adjustment method for propeller blade cross-section based on UG software according to the present invention. Detailed Implementation

[0043] This invention provides a method for integrated adjustment of propeller blade cross-section based on UG software, such as... Figure 1-2 As shown, it includes the following steps:

[0044] S1. Use a pitch gauge to measure the pitch value of the propeller blade blank, and use calipers to measure the thickness value of the pitch point of the propeller blade blank.

[0045] S2. Compare the measured pitch and thickness values ​​of the propeller blade blank with the standard pitch and thickness values ​​of the propeller blade marked on the propeller blade construction drawings to determine whether the cross-sectional curve of the propeller blade needs to be adjusted.

[0046] Determining whether the cross-sectional profile of a propeller blade needs adjustment includes the following steps:

[0047] S2-1. Calculate the difference between the blank pitch value and the standard pitch value of the propeller blade. The calculation formula is as follows:

[0048] Pitch difference = Raw pitch value - Standard pitch value;

[0049] S2-2. Calculate the difference between the blank thickness of the propeller blade and the standard thickness. The calculation formula is as follows:

[0050] Thickness difference = Blank thickness value - Standard thickness value;

[0051] S2-3. Compare the thickness difference with the pitch difference.

[0052] No adjustment is needed when the thickness difference is greater than the pitch difference;

[0053] When the thickness difference is less than the pitch difference, adjustment is required.

[0054] S3. In UG, call the secondary development-generated grip executable file - blade section adjustment rcy.grx. This file is a secondary development file (with the .grx extension) that can be directly called by UG software. It is generated by the source program segment, i.e., the GripSourceFile file (with the .grs extension), through the NX OPEN GRIP compiler, after being compiled by Compile and Linked. It is based on the propeller model built by the UG NX modeling module, including the following steps:

[0055] S3-1. Obtain the two-dimensional coordinates of the blade section curve points and the propeller blade pitch value P from the propeller blade construction drawings, and input the two-dimensional coordinates of the blade section curve points into the UG NX modeling module;

[0056] S3-2. Connect the points of the blade section curve to form a spline curve;

[0057] S3-3. Calculate the helix angle θ of each radial section line of the propeller blade. The calculation formula is as follows:

[0058]

[0059] In the formula: P is the pitch value of each radius, and r is the radius value;

[0060] Based on the helix angle θ, rotate the spline curve;

[0061] S3-4. Calculate the back slope value L of each radius section line of the propeller blade. The calculation formula is as follows:

[0062] L=r·tanα

[0063] In the formula: r represents each radius value, and α represents the backslope angle;

[0064] Move the spline curve to the backsloping position based on the L value;

[0065] S3-5. Use UG's warp function to project the rotated and translated spline curve onto the cylindrical surface constructed with the corresponding r radius;

[0066] S3-6. Use UG's sheet construction function to connect the spline curves of each radius to obtain the propeller blade model.

[0067] Connecting the cross-sectional curves of the blades yields the propeller model. The propeller and blade models constructed using the UG NX modeling module are conventional models.

[0068] S4. Input the corresponding propeller radius value r, and use UG NX OPEN GRIP secondary development technology to automatically obtain the radius of each section of the propeller blade and make corresponding annotations based on the input propeller radius value through the statement a(1..3)=&spoint(cur(indx));

[0069] S5. Select the propeller blade cross-section curve group that needs adjustment based on the judgment in step S2. If the curve group is not adjusted, machining that area on a CNC machine tool according to the standard curve group will result in insufficient thickness allowance for the propeller blades near that curve group (i.e., excessive cutting depth, because the cutting does not follow the approximate shape of the blank. After casting, the blank propeller cannot perfectly fit the standard 3D model, but the blank is not a scrap. Adjusting the cross-section curve group that needs adjustment according to the propeller manufacturing tolerance can still meet the design requirements). Calculate the radius value of each curve in each blade cross-section curve group based on the coordinate values ​​of the points on the blade cross-section curve group. The formula for calculating the radius value of the blade cross-section curve is as follows:

[0070]

[0071] S6. Adjust the Z value of the blade cross-section curve based on the obtained radius value; shift the cross-section curve group that needs adjustment up or down along the Z axis according to the propeller manufacturing tolerance (a table for adjusting each cross-section will be manually prepared in advance, and the adjustment in UG software will be carried out according to the table). Generally, the manufacturing tolerance of civilian-grade propellers requires that the cross-section curve group be shifted up or down in the Z direction by a distance between +15mm and -15mm. The adjustment data in the table can be within this range to meet the actual blank state for subsequent CNC machine tool processing (without exceeding the allowable tolerance range of propeller manufacturing).

[0072] The propeller radius position of the blade cross-section curve is calculated based on the radius value of the cross-section curve. The calculation formula is as follows:

[0073]

[0074] Adjust the Z-value of the blade cross-section curve according to the propeller radius position of the blade cross-section curve, referring to the cross-section adjustment table below:

[0075] Radius position casually Guide edge Adjusting the pitch Adjust height Z 0.2r Measurement data omitted Measurement data omitted no -8 0.25r Measurement data omitted Measurement data omitted no -7 0.3r Measurement data omitted Measurement data omitted no -5 0.4r Measurement data omitted Measurement data omitted no -5 0.5r Measurement data omitted Measurement data omitted no -3 0.6r Measurement data omitted Measurement data omitted no -2 0.7r Measurement data omitted Measurement data omitted no 0 0.8r Measurement data omitted Measurement data omitted no 0 0.9r Measurement data omitted Measurement data omitted no 3 0.95r Measurement data omitted Measurement data omitted no +5 0.975r Measurement data omitted Measurement data omitted no +6

[0076] When selecting a blade section curve group, you can individually click on the curves within the group that require adjustment, or you can select the entire curve group (this operation only requires setting the values ​​of the curve groups that do not need adjustment to 0 in the subsequent pop-up table interface). After confirming the selected curve groups, click the middle mouse button to open a pop-up window. The pop-up window will display the corresponding curve group table interface (marking the radius values ​​of the curve groups selected in the previous step, obtained through relevant radius calculation statements in the program). Enter the values ​​to be adjusted in the list. The position of the section curve at the propeller radius corresponds to the value to be adjusted. As shown in the table above, when the section curve is located at the 0.5r position of the propeller, the height Z adjustment value is -3.

[0077] In S7.UG software, the selected curve group section curves are automatically moved according to the height Z adjustment value. With the help of UG's original sheet body inheritance curve feature function, the adjusted blade section curve group is displayed as a sheet body.

[0078] The rcy.grx program code (including the algorithm) and explanations of the program statements:

[0079] $$Entity variable and numeric array declaration.

[0080]

[0081]

[0082]

[0083]

[0084] After adjusting the Z-value of the curve in step S6, the curve is verified to determine if there are any errors in the adjustment. The blade body formed after the blade cross-section adjustment is verified to check if there are any errors in the adjustment of the blade curve group. The grip executable file - blade cross-section numerical difference verification dis.grx file is called. This file is also a secondary development file (with the .grx extension) that can be directly called by UG software, produced by the NX OPEN GRIP compiler through Compile and Link compilation of the source program segment, i.e., the GripSourceFile file (with the .grs extension), and can be directly called by UG software. Input the corresponding propeller radius value of 0.5R, call up the original blade body model (light blue), select the original blade body curve and the adjusted blade body curve respectively, and the results display the adjustment distance and radius values. The following steps are included:

[0085] S6-1. Select point a on the blade cross-section curve before adjustment and record the coordinates (X, Y, Z) of the point;

[0086] S6-2. Select point a1 on the adjusted blade section curve that corresponds to point a, and record the coordinate values ​​(X1, Y1, Z1) of point a1.

[0087] S6-3. Calculate the difference in the Z direction between point a and point a1 in the coordinate system;

[0088] S6-4. Calculate the propeller radius position where the blade cross-section curve is located, and determine the Z value for adjusting the blade cross-section curve;

[0089] S6-5. Compare the difference in the Z direction between point a and point a1 in the coordinate system with the adjusted Z value of the blade section curve. If the two values ​​are the same, the adjustment is correct. If the two values ​​are different, the adjustment is incorrect. Then return to step S1.

[0090] like Figure 3 As shown, the dis.grx program code (including the algorithm) and explanations of the program statements are as follows:

[0091]

[0092]

[0093]

[0094] This solution enables the overall adjustment of the blade section curve group and the corresponding verification of the difference between the blade section values ​​before and after the adjustment. The method is simple, easy to operate, and automates the adjustment and difference calculation. It generates a visual window prompt and a table input interface for all propeller sections. The difference verification is visualized and labeled in one go.

[0095] This invention has been described through embodiments. Those skilled in the art will understand that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of the invention. Furthermore, under the teachings of this invention, these features and embodiments can be modified to adapt to specific situations and materials without departing from the spirit and scope of the invention. Therefore, this invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the protection scope of this invention.

Claims

1. A method for integrated adjustment of propeller blade cross-section based on UG software, characterized in that, Includes the following steps: S1. Measure the pitch value of the propeller blade blank and the thickness value of the pitch point of the propeller blade blank. S2. Compare the measured pitch and thickness values ​​of the propeller blade blank with the standard pitch and thickness values ​​of the propeller blade marked on the propeller blade construction drawings to determine whether the cross-sectional curve of the propeller blade needs to be adjusted. S3. The propeller model built based on the UG NX modeling module includes the following steps: S3-1. Obtain the two-dimensional coordinates of the blade section curve points and the propeller blade pitch value P from the propeller blade construction drawings, and input the two-dimensional coordinates of the blade section curve points into the UG NX modeling module; S3-2. Connect the points of the blade section curve to form a spline curve; S3-3. Calculate the helix angle θ of each radial section line of the propeller blade. The calculation formula is as follows: ； In the formula: P is the pitch value of each radius, and r is the radius value; Based on the helix angle θ, rotate the spline curve; S3-4. Calculate the back slope value L of each radius section line of the propeller blade. The calculation formula is as follows: ； In the formula: r represents each radius value, and α represents the backslope angle; Move the spline curve to the backsloping position based on the L value; S3-5. Use UG's "warp" function to project the rotated and translated spline curve onto the cylindrical surface constructed with the corresponding r radius; S3-6. Use UG's sheet body construction function to connect the spline curves of each radius to obtain the propeller blade model; S4. Input the propeller radius value r, and use UG NX OPEN GRIP secondary development technology to automatically obtain the radius of each section of the propeller blade and make corresponding annotations; S5. Select the propeller blade section curve group that needs to be adjusted, input the adjustment value of each section curve group, and adjust the Z value of each section curve of the blade in one go; S6. Verify the adjusted blade cross-section curve to determine if the adjustment is incorrect; S7. Use UG's sheet body inheritance curve feature function to display the adjusted blade section curve group as a sheet body.

2. The method for integrated adjustment of propeller blade cross-section based on UG software according to claim 1, characterized in that, The formula for calculating the radius of the blade cross-section curve in step S5 is as follows: ； in, This represents the radius of the blade cross-section curve. , These are the two-dimensional abscissa and ordinate of a point on the blade cross-section curve, respectively. Step S6 calculates the propeller radius position where the blade cross-section curve is located based on the radius value of the cross-section curve. The calculation formula is as follows: Radius position = ; in, This is the propeller radius value; Adjust the Z-value of the blade cross-section curve according to the propeller radius position of the blade cross-section curve, referring to the cross-section adjustment table below: 。 3. The method for integrated adjustment of propeller blade cross-section based on UG software according to claim 1, characterized in that, After adjusting the Z value of the curve in step S6, the curve is verified to determine whether the adjustment is incorrect, including the following steps: S6-1. Select point a on the blade cross-section curve before adjustment and record the coordinates (X, Y, Z) of that point. S6-2. Select point a1 on the adjusted blade section curve that corresponds to point a, and record the coordinate values ​​(X1, Y1, Z1) of point a1. S6-3. Calculate the difference in the Z direction between point a and point a1 in the coordinate system; S6-4. Calculate the propeller radius position where the blade cross-section curve is located, and determine the Z value for adjusting the blade cross-section curve; S6-5. Compare the difference in the Z direction between point a and point a1 in the coordinate system with the adjusted Z value of the blade section curve. If the two values ​​are the same, the adjustment is correct. If the two values ​​are different, the adjustment is incorrect. Then return to step S1.

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