CN116522482B - Method for improving modeling efficiency of control surface angle piece of wind tunnel test model - Google Patents
Method for improving modeling efficiency of control surface angle piece of wind tunnel test model Download PDFInfo
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Abstract
The invention discloses a method for improving modeling efficiency of a control surface angle piece of a wind tunnel test model, which comprises the following steps: s1, cutting to obtain a stabilizer connecting part and a control surface connecting part; s2, enabling the rotation deflection angle to be the minimum deflection angle; s3, extracting first characteristic points and determining first proportional parameters; extracting corner points; s4, enabling the rotation deflection angle to be the maximum deflection angle; extracting second characteristic points and determining second proportion parameters; s5, obtaining a relation between the proportional parameter and the steering surface angle sheet deflection angle through data fitting; s6, extracting a third characteristic point according to the deflection angle of the control surface angle piece; creating a three-dimensional configuration of the intermediate connecting part; and S7, carrying out Boolean addition operation on the middle connecting part, the stabilizer connecting part and the control surface connecting part to obtain a control surface angle sheet, and repeating the steps S6-S7 to generate the control surface angle sheets with different deflection angles. The method can generate different control surface angle pieces only by rotating the control surface angle pieces around the control surface rotating shaft by corresponding angles, thereby greatly saving design time and improving design work efficiency.
Description
Technical Field
The invention relates to the technical field of wind tunnel tests, in particular to a method for improving modeling efficiency of a control surface angle piece of a wind tunnel test model.
Background
When the aircraft flies in the sky, the main components supporting the aircraft to fly in the sky are an airfoil main body (comprising wings, horizontal tails, vertical tails and the like) and a controllable control surface attached to the airfoil main body, the attitude control of the aircraft mainly depends on the aerodynamic force change caused by the control surface deflection to generate moment for the whole aircraft, the control surface deflection of the real aircraft is mainly performed by a steering engine, and the control surface angle can be adjusted steplessly. The wind tunnel test is mainly used for exploring and researching mechanical properties and the like corresponding to the aircraft in different states, and the important one of the different states is to change the angle of an attached controllable control surface behind the airfoil main body. Different from the control surface deflection of a real aircraft, the control surface deflection of the wind tunnel test is not required to be adjusted steplessly, the control surface deflection of the wind tunnel test is mainly realized by replacing a control surface angle sheet, the control surface deflection of the real aircraft can cause larger air flow disturbance by a steering engine and a rotating shaft, and the control surface deflection of the wind tunnel test is very small disturbance caused to air flow when an airfoil main body and the control surface are connected by the control surface angle sheet.
Patent document CN112926138a provides a modeling method of a control surface angle piece applied to a wind tunnel test model, comprising the following steps: leading in a three-dimensional configuration of a wind tunnel test model to form a mounting groove; obtaining a three-dimensional configuration of the stabilizer connecting part and a three-dimensional configuration of the control surface connecting part; rotating the three-dimensional configuration of the control surface connecting part to enable the included angle between the top surface of the three-dimensional configuration of the control surface connecting part and the top surface of the three-dimensional configuration of the stabilizer connecting part to be equal to the control surface angle required by the wind tunnel test; creating a three-dimensional configuration of the intermediate connecting part; the three-dimensional configuration of the middle connecting part, the three-dimensional configuration of the stabilizer connecting part and the three-dimensional configuration of the control surface connecting part are subjected to Boolean addition to obtain the three-dimensional configuration of the control surface angle sheet, wherein in the creation process, the three-dimensional configuration of the middle connecting part is mainly created, the three-dimensional configuration of the control surface connecting part needs to be rotated for many times to different angle requirements, the corner points and the characteristic points are selected according to the designed angle, the characteristic points need to be selected in consideration of whether the built middle connecting part can meet the requirements of wind tunnel tests, the characteristic points need to be selected again for different angle requirements, a complex process is adopted, a series of angle sheets with different deflection angles, such as 10 DEG, 15 DEG, 10 DEG and the like, are generally required to be designed and manufactured in the practical application process, and the different control surface deflection angles are realized through the replacement of the angle sheets. And the feature points are selected again according to different angle requirements, so that the modeling workflow is long, and the modeling speed is greatly reduced.
Disclosure of Invention
The invention aims to solve the problem of low modeling efficiency caused by re-selecting characteristic points according to different angle requirements in the existing modeling method of the control surface angle piece, and provides a method for improving the modeling efficiency of the control surface angle piece of a wind tunnel test model.
In order to achieve the above object, the present invention provides the following technical solutions:
The method for improving the modeling efficiency of the control surface angle sheet of the wind tunnel test model comprises a stabilizer connecting part, a control surface connecting part and an intermediate connecting part, wherein the stabilizer connecting part and the control surface connecting part are connected by the intermediate connecting part, and the method comprises the following steps of:
s1, importing the three-dimensional configuration of the wing stabilizer and the three-dimensional configuration of the control surface of the wind tunnel test model, and cutting the three-dimensional configuration of the wing stabilizer and the three-dimensional configuration of the control surface to obtain the stabilizer connecting part and the control surface connecting part respectively;
S2, rotating the control surface connecting part to enable a rotation deflection angle to be the minimum deflection angle of the control surface angle piece, wherein the rotation deflection angle is an included angle between the top surface of the control surface connecting part and the top surface of the stabilizer connecting part;
S3, extracting a curved surface, close to the stabilizer connecting part, of the control surface connecting part as a first surface, wherein the side edge of the first surface is a first line segment and a second line segment respectively; extracting the end face, close to the control surface connecting part, of the stabilizer connecting part as a second surface, wherein the side edge of the second surface is respectively a third line segment and a fourth line segment; respectively extracting two first characteristic points on the first line segment and the second line segment, wherein the proportion of each first characteristic point to the length of the line segment is a first proportion parameter; respectively extracting two corner points on the third line segment and the fourth line segment;
S4, rotating the control surface connecting part again to enable the rotation deflection angle to be the maximum deflection angle of the control surface angle piece; re-extracting two second characteristic points on the first line segment and the second line segment respectively, wherein the proportion of each second characteristic point to the length of the line segment is a second proportion parameter;
S5, according to the first proportion parameter and the minimum deflection angle, the second proportion parameter and the maximum deflection angle data, obtaining a relation between the proportion parameter and the deflection angle of the control surface angle sheet through data fitting;
s6, according to the deflection angle of the control surface angle piece, obtaining a proportion parameter of a third characteristic point according to a relation between the proportion parameter and the deflection angle of the control surface angle piece, and then extracting two third characteristic points on the first line segment and the second line segment in a self-adaptive manner respectively; creating a line segment according to the four corner points and the four third characteristic points to create a three-dimensional configuration of the middle connecting part, wherein the deflection angle of the control surface angle sheet refers to the deflection angle of the designed control surface angle sheet;
And S7, carrying out Boolean addition operation on the middle connecting part, the stabilizer connecting part and the control surface connecting part to obtain the control surface angle sheet, and repeating the steps S6-S7 to generate the control surface angle sheets with different deflection angles.
Further, step S1 further includes providing a first mounting hole on the stabilizer connecting portion, and providing a second mounting hole on the control surface connecting portion, where the first mounting hole and the second mounting hole are used when the control surface angle piece is assembled.
Further, the standard of the first feature point is selected as that the thickness of the middle connecting portion determined by the first feature point and the corner point can meet the strength requirement of the wind tunnel test model, and the smaller the thickness of the middle connecting portion is, the better the strength requirement is met. According to the standard, a first characteristic point can be selected according to the deflection angle of the control surface angle piece, so that a first proportion parameter is determined.
Further, the relation between the proportional parameter and the deflection angle of the control surface angle piece is a linear relation.
Further, the detailed process of creating the three-dimensional configuration of the intermediate connection is:
step S61, creating line segments according to the four corner points in the step S3 and the four third characteristic points in the step S6, and extracting four line segments on the end face of the stabilizer connecting part facing the control surface connecting part;
Step S62, extracting the end face of the stabilizer connecting part facing the control surface connecting part, and extracting a characteristic curved surface of the control surface connecting part facing the stabilizer connecting part;
step S63, creating a construction surface between the stabilizer connection part and the control surface connection part;
Step S64, creating an intermediate connection portion from the end face in step S62, the feature curved surface, and the configuration surface in step S63.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides a rapid modeling method of a control surface angle sheet applied to a wind tunnel test model, which adopts a method of correspondingly selecting a first characteristic point and a second characteristic point on a control surface connecting part according to the minimum deflection angle and the maximum deflection angle of the control surface angle sheet so as to establish a relation between a proportion parameter and the deflection angle of the control surface angle sheet, and after designing an angle sheet with any angle, determining the proportion parameter of the characteristic point according to the relation between the proportion parameter and the deflection angle of the control surface angle sheet, and can rapidly and adaptively select a third characteristic point on the control surface connecting part in the modeling process so as to establish an intermediate connecting part. By adopting the method, different control surface angle pieces can be generated only by rotating around the control surface rotating shaft by corresponding angles, so that the design time is greatly saved, and the design work efficiency is improved.
Description of the drawings:
FIG. 1 is a flow chart of a method for improving modeling efficiency of a control surface angle piece of a wind tunnel test model;
FIG. 2 is a schematic representation of the three-dimensional configuration of a pilot hole test model in example 1;
FIG. 3 is a schematic view of a three-dimensional configuration of the wing stabilizer and control surface of example 1;
FIG. 4 is a schematic view of a stabilizer link and a control surface link in embodiment 1;
FIG. 5 is a schematic view of a first mounting hole and a second mounting hole in embodiment 1;
FIG. 6 is a schematic diagram showing the intermediate connection creation process in embodiment 2;
fig. 7 is a diagram of an intermediate connection creation process in embodiment 2;
FIG. 8 is a schematic view of the three-dimensional configuration of the control surface angle blade established in example 2;
The marks in the figure: 10-wing stabilizer, 11-first mounting groove, 20-control surface, 21-second mounting groove, 31-stabilizer connecting portion, 311-first mounting hole, 32-intermediate connecting portion, 33-control surface connecting portion, 331-second mounting hole.
Detailed Description
The present invention will be described in further detail with reference to test examples and specific embodiments. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Example 1
As shown in fig. 1, the control surface angle piece comprises a stabilizer connecting part 31, a control surface connecting part 33 and an intermediate connecting part 32, wherein the stabilizer connecting part 31 and the control surface connecting part 33 are connected by the intermediate connecting part 32, and the method comprises the following steps:
s1, importing a three-dimensional configuration of a wing stabilizer 10 and a three-dimensional configuration of a control surface 20 of a wind tunnel test model, and cutting the three-dimensional configuration of the wing stabilizer 10 and the three-dimensional configuration of the control surface 20 to obtain a stabilizer connecting part 31 and a control surface connecting part 33 respectively;
Referring to fig. 2, which is a schematic structural diagram of a wind tunnel test model according to an embodiment of the present invention, the wind tunnel test model includes a wing stabilizer 10 and a control surface 20, fig. 3 shows a structure of a part of the three-dimensional configuration of the wing stabilizer 10 and the three-dimensional configuration of the control surface 20, a first installation groove 11 is disposed on the three-dimensional configuration of the wing stabilizer 10, a second installation groove 21 is disposed on the three-dimensional configuration of the control surface 20, and a gap is formed between an end surface of the second installation groove 21 and a straight line where a front edge of the three-dimensional configuration of the control surface 20 is located; by setting the gap, even when the control surface angle between the airfoil body and the control surface is the maximum value (the maximum value refers to the maximum value required by the wind tunnel test), interference between the airfoil body and the control surface can be avoided. The stabilizer connecting part 31 is matched with the first mounting groove 11, the control surface connecting part 33 is matched with the second mounting groove 21, the three-dimensional configuration of the stabilizer connecting part 31 is the same as that of the first mounting groove 11, and similarly, the three-dimensional configuration of the control surface connecting part 33 is the same as that of the second mounting groove 21; when the control surface angle sheet connects the wing stabilizer 10 and the control surface, the installation and the disassembly are simple and convenient, and when the control surface angle of the wind tunnel test model needs to be adjusted, the control surface angle sheet only needs to be replaced by another control surface angle sheet.
According to the imported three-dimensional configuration of the wing stabilizer 10 and the imported three-dimensional configuration of the control surface 20, two lines of a center line of the rear edge end surface of the control surface and a rotating shaft of the control surface are defined as reference planes, sketches are made on the reference planes, the wing stabilizer 10 is cut according to the three-dimensional configuration of the wing stabilizer 10 by the first mounting groove 11 arranged on the three-dimensional configuration of the wing stabilizer 10, the rest is the stabilizer connecting part 31, the control surface 20 is cut according to the second mounting groove 21 arranged on the three-dimensional configuration of the control surface 20, the rest is the control surface connecting part 33, and the stabilizer connecting part 31 and the control surface connecting part 33 cut from the wing stabilizer 10 and the control surface respectively are shown in fig. 4. In the case of cutting the three-dimensional configuration of the control surface 20, the front edge portion of the three-dimensional configuration of the control surface 20 is cut to the control surface connection portion 33.
In some embodiments, step S1 further includes providing a first mounting hole 311 on the stabilizer connection portion 31, and providing a second mounting hole 331 on the control surface connection portion 33, where the first mounting hole 311 and the second mounting hole 331 are used when the control surface angle piece is assembled; the first mounting groove 11 is provided with a third mounting hole, the first mounting hole 311 is matched with the third mounting hole, the first mounting hole 311 and the third mounting hole are coaxially arranged and used for assembling the stabilizer connecting part 31 onto the wing stabilizer 10, the second mounting groove 21 is provided with a fourth mounting hole, the second mounting hole 331 is matched with the fourth mounting hole, the first mounting hole 331 and the fourth mounting hole are coaxially arranged and used for assembling the control surface connecting part 33 onto a control surface, and the wing stabilizer 10 and the control surface can be connected through the control surface angle piece by adopting the arrangement. As shown in fig. 4, the first mounting hole 311 and the second mounting hole 331 are schematically provided, and it should be noted that the third mounting hole and the fourth mounting hole are not shown in fig. 3.
Step S2, rotating the control surface connecting part 33 to enable the rotation deflection angle to be the minimum deflection angle of the control surface angle piece, wherein the rotation deflection angle is the included angle between the top surface of the control surface connecting part 33 and the top surface of the stabilizer connecting part 31;
S3, extracting a curved surface of the control surface connecting part 33, which is close to the stabilizer connecting part 31, as a first surface, wherein the side edge of the first surface is a first line segment and a second line segment respectively; the end face of the extracted stabilizer connecting part 31, which is close to the control surface connecting part 33, is a second surface, and the side edges of the second surface are a third line segment and a fourth line segment respectively; respectively extracting two first characteristic points on the first line segment and the second line segment, wherein the proportion of each first characteristic point to the length of the line segment is a first proportion parameter; and respectively extracting two corner points on the third line segment and the fourth line segment.
In this embodiment, the definition form of each feature point is the proportion of the length of the line segment, the first proportion parameter can be determined by selecting the first feature point, the standard of selecting the first feature point is that the thickness of the intermediate connection portion 32 determined by the first feature point and the corner point can meet the strength requirement of the wind tunnel test model, and the smaller the thickness of the intermediate connection portion 32 is, the better the strength requirement is met. According to the standard, a first characteristic point can be selected according to the deflection angle of the control surface angle piece, so that a first proportion parameter is determined.
Step S4, the control surface connecting part 33 is rotated again to enable the rotation deflection angle to be the maximum deflection angle of the control surface angle piece; re-extracting two second characteristic points on the first line segment and the second line segment respectively, wherein the proportion of each second characteristic point to the length of the line segment is a second proportion parameter;
S5, according to the first proportion parameter and the minimum deflection angle, the second proportion parameter and the maximum deflection angle data, obtaining a relation between the proportion parameter and the control surface angle sheet deflection angle through data fitting;
and S2-S5, correspondingly selecting a first characteristic point and a second characteristic point on the control surface connecting part 33 according to the minimum deflection angle and the maximum deflection angle of the control surface angle piece so as to establish a relation between the proportional parameter and the deflection angle of the control surface angle piece. By adopting the method, the proportion parameter of the characteristic point can be determined according to the deflection angle of the control surface angle piece, and the third characteristic point can be quickly selected on the control surface connecting part 33 in the modeling process so as to establish the middle connecting part 32. When the relation between the proportional parameter and the deflection angle of the control surface angle sheet is established, the relation between the minimum deflection angle and the maximum deflection angle for determining the parameter is selected, and the minimum deflection angle and the maximum deflection angle can take all conditions of the control surface angle sheet into consideration, so that the established functional relation is more accurate.
S6, according to the deviation angle of the control surface angle piece, obtaining the proportion parameter of the third characteristic point according to the relation between the proportion parameter and the deviation angle of the control surface angle piece, and then extracting two third characteristic points on the first line segment and the second line segment in a self-adaptive manner respectively; creating a line segment according to the four corner points and the four third characteristic points to create a three-dimensional configuration of the middle connecting part 32;
the detailed process of creating the three-dimensional configuration of intermediate link 32 is:
Step S61, creating line segments according to the four corner points in the step S3 and the four third characteristic points in the step S6, and extracting four line segments on the end face of the stabilizer connecting part 31 facing the control surface connecting part 33;
Step S62, extracting the end surface of the stabilizer connecting part 31 facing the control surface connecting part 33, and extracting the characteristic curved surface of the control surface connecting part 33 facing the stabilizer connecting part 31;
step S63, creating a construction surface between the stabilizer connection part 31 and the control surface connection part 33;
Step S64, creating the intermediate connection portion 32 from the end face in step S72, the feature curved surface, and the configuration surface in step S73.
And S7, performing Boolean addition operation on the middle connecting part 32, the stabilizer connecting part 31 and the control surface connecting part 33 to obtain the control surface angle pieces, and repeating the steps S6-S7 to generate the control surface angle pieces with different deflection angles.
After the three-dimensional configuration of the control surface angle piece of the wind tunnel test model is completed, the corresponding control surface angle piece can be produced through numerical control technology and the like.
Example 2
The embodiment provides a method for improving modeling efficiency of the control surface angle piece of the wind tunnel test model by adopting the embodiment 1. In step S1, the stabilizer link 31 and the control surface link 33 are obtained by cutting.
In the step S2, the minimum deflection angle of the control surface angle piece required to be designed is-30 degrees, and the rotation deflection angle is-30 degrees according to the rotation of the control surface rotating shaft.
In step S3, the curved surface of the control surface connecting portion 33 near the stabilizer connecting portion 31 is named as a first surface, the first line segment and the second line segment are named as curve segments, the first line segment is named as curve AB, the second line segment is named as curve CD, two first characteristic points on the first line segment are P1, P2, the position of P1 is higher than P2, two characteristic points on the second line segment are P3, P4, the position of P3 is higher than P4, the ratio of the first characteristic points to the length of the line segment is named as a first proportional parameter, the first proportional parameter on the curve AB is named as a base of the point B, the first proportional parameter on the curve CD is named as a base of the point D, the thickness of the intermediate connecting portion 32 determined by the first characteristic points and the corner points is named as a standard of the first characteristic points, the strength requirement of the wind tunnel test model can be met, and under the condition that the strength requirement is met, the smaller the first proportional parameter of P1, P2 is 0.04, 0.18, the first proportional parameter of P3 and P4 can be consistent with P1, P2, 0.04, 0.18. The end surface of the extraction stabilizer connecting portion 31 near the control surface connecting portion 33 is named as a second surface, and in this embodiment, the third line segment and the fourth line segment are straight line segments on the side of the second surface, as shown in fig. 6. Fig. 6 is a schematic diagram of four first feature points and four corner points, two corner points on a third line segment are P11 and P12, two corner points on a fourth line segment are P13 and P14, wherein P11 is higher than P12, P13 is higher than P14, P11, P12, P1 and P2 are located on the same side, and P13, P14, P3 and P4 are located on the same side. Connecting P1-P11, P2-P12, P3-P13, P4-P14, forms a curve of the intermediate connection 32.
In step S4, in this embodiment, the minimum deflection angle of the angle plate is +45°, and the rotation deflection angle is +45° by rotating the control surface rotation shaft. Respectively extracting two second characteristic points on the first line segment and the second line segment according to the selection standard of the first characteristic points, and adjusting the proportion parameters; the two second characteristic points on the first line segment are P1', P2', the second proportion parameters of the two second characteristic points are 0.4 and 0.6, the two second characteristic points on the second line segment are P3', P4', the second proportion parameters of the two second characteristic points are 0.4 and 0.6, the connection of P1'-P11, P1' -P12, P3'-P13 and P4' -P14 is reasonably feasible, and the reasonable feasibility means that the line segments forming the intermediate connection part 32 cannot be crossed.
In step S5, at the minimum deflection angle of P1-P4 of-30 °, the maximum deflection angle of P1' -P4 ' is +45°, in this embodiment, the ratio parameter and the angle sheet deflection angle are in a linear relationship, and by taking P1 and P1' as examples, the function relation between the first characteristic point P1 and the control surface angle sheet deflection angle is obtained by linear fitting and is k=0.275 δ+0.184, where k is the first ratio parameter of the first characteristic point P1, δ is the control surface deflection angle, the unit is radian, and when δ= -30 °, the function relation between the first characteristic point P1 and the control surface angle sheet deflection angle is k=0.275+0.184
(-0.524 Rad), k=0.04; when δ= -45 ° (0.785 rad), k=0.4; and (5) correlating the coordinate of the P1 point with the deflection angle of the control surface angle piece. And fitting the P2, the P3 and the P4 by adopting the same method to respectively obtain the proportional parameter and the control surface angle piece deflection angle function relation.
In step S6, the control surface rotating shaft is rotated again according to the deflection angle of the control surface angle piece in modeling software, the rotation deflection angle is the deflection angle of the control surface angle piece, such as-15 degrees, and the points P1-P4 are self-adaptively positioned to reasonable positions. Specifically, as shown in fig. 7, the process of creating the three-dimensional configuration of the intermediate connecting portion 32 is: connecting the third feature points P1, P3 with a first spline, positioning the first spline on the first surface, connecting the points P2, P4 with a second spline, positioning the second spline on the first surface; dividing the first surface by the first spline and the second spline to form a third surface composed of third characteristic points P1-P4; selecting curves P1P11 and P2P12 of the connecting part, selecting a side line P1P2 of a third surface, selecting a side line P11P12 of a second surface, and filling to generate a fourth surface; similar operations are taken for points P3, P4, P13, P14 to generate a fifth face; a sixth surface is generated from the curves P1P11, P3P13 and the first spline line and the second spline line P11P13 of the intermediate connecting portion 32 using a multi-section curved surface, and a seventh surface is generated by taking similar operations to the points P2, P12, P4, P14. The second, third, fourth, fifth, sixth, seventh faces are formed into a closed curved surface using a "join" command, followed by the formation of a three-dimensional configuration of the solid, intermediate connecting portion 32.
In step S7, the three-dimensional configuration of the intermediate connection portion 32, the stabilizer connection portion 31, and the control surface connection portion 33 are subjected to boolean-up operation to obtain a control surface angle piece, as shown in fig. 8. The control surface of the aircraft in the embodiment needs to be designed into the control surface angle pieces of-30 degrees to +45 degrees, one control surface angle piece is designed every 5 degrees, 16 angle pieces are needed to be designed, and the steps S6-S7 are repeated, so that the control surface angle pieces with different deflection angles can be adaptively generated.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (5)
1. A method for improving modeling efficiency of a control surface angle sheet of a wind tunnel test model, wherein the control surface angle sheet comprises a stabilizer connecting part (31), a control surface connecting part (33) and an intermediate connecting part (32), and the intermediate connecting part (32) connects the stabilizer connecting part (31) with the control surface connecting part (33), and the method is characterized by comprising the following steps:
s1, importing a three-dimensional configuration of a wing stabilizer (10) and a three-dimensional configuration of a control surface (20) of the wind tunnel test model, and cutting the three-dimensional configuration of the wing stabilizer (10) and the three-dimensional configuration of the control surface (20) to obtain a stabilizer connecting part (31) and a control surface connecting part (33) respectively;
S2, rotating the control surface connecting part (33) to enable a rotation deflection angle to be the minimum deflection angle of the control surface angle piece, wherein the rotation deflection angle is an included angle between the top surface of the control surface connecting part (33) and the top surface of the stabilizer connecting part (31);
S3, extracting a curved surface, close to the stabilizer connecting part (31), of the control surface connecting part (33) as a first surface, wherein the side edge of the first surface is a first line segment and a second line segment respectively; extracting an end face, close to the control surface connecting part (33), of the stabilizer connecting part (31) as a second surface, wherein the side edge of the second surface is a third line segment and a fourth line segment respectively; respectively extracting two first characteristic points on the first line segment and the second line segment, wherein the proportion of each first characteristic point to the length of the line segment is a first proportion parameter; respectively extracting two corner points on the third line segment and the fourth line segment;
s4, rotating the control surface connecting part (33) again to enable the rotation deflection angle to be the maximum deflection angle of the control surface angle piece; re-extracting two second characteristic points on the first line segment and the second line segment respectively, wherein the proportion of each second characteristic point to the length of the line segment is a second proportion parameter;
S5, according to the first proportion parameter and the minimum deflection angle, the second proportion parameter and the maximum deflection angle data, obtaining a relation between the proportion parameter and the deflection angle of the control surface angle sheet through data fitting;
S6, according to the deflection angle of the control surface angle piece, obtaining a proportion parameter of a third characteristic point according to a relation between the proportion parameter and the deflection angle of the control surface angle piece, and then extracting two third characteristic points on the first line segment and the second line segment in a self-adaptive manner respectively; creating a three-dimensional configuration of the intermediate connecting portion (32) according to four corner points and four third feature point creation line segments;
And S7, carrying out Boolean addition operation on the middle connecting part (32), the stabilizer connecting part (31) and the control surface connecting part (33) to obtain the control surface angle piece, and repeating the steps S6-S7 to generate the control surface angle pieces with different deflection angles.
2. The method for improving modeling efficiency of a control surface angle sheet of a wind tunnel test model according to claim 1, wherein the step S1 further comprises providing a first mounting hole (311) on the stabilizer connecting portion (31), and providing a second mounting hole (331) on the control surface connecting portion (33).
3. The method for improving modeling efficiency of a control surface angle piece of a wind tunnel test model according to claim 1, wherein the criteria for selecting the first feature point are as follows: the thickness of the intermediate connection (32) determined by the first feature points and the corner points meets the strength requirement of the wind tunnel test model.
4. A method for improving modeling efficiency of a control surface angle sheet of a wind tunnel test model according to claim 3, wherein the relation between the proportional parameter and the deflection angle of the control surface angle sheet is a linear relation.
5. The method for improving modeling efficiency of a control surface angle sheet of a wind tunnel test model according to claim 1, wherein the detailed process of creating the three-dimensional configuration of the intermediate connection part (32) is as follows:
step S61, creating line segments according to the four corner points in the step S3 and the four third characteristic points in the step S6, and extracting four line segments on the end face of the stabilizer connecting part (31) facing the control surface connecting part (33);
Step S62, extracting an end face of the stabilizer connecting part (31) facing the control surface connecting part (33), and extracting a characteristic curved surface of the control surface connecting part (33) facing the stabilizer connecting part (31);
step S63, creating a construction surface between the stabilizer connection part (31) and the control surface connection part (33);
Step S64, creating the intermediate connection part (32) according to the end surface in step S62, the characteristic curved surface and the construction surface in step S63.
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