A wing-rudder nose cone and hanging point integrated structure and its manufacturing method

Abstract

The present invention relates to a wing-rudder type structure and a manufacturing method thereof, and specifically to a wing-rudder head cone and hanging point integrated structure and a manufacturing method thereof, in order to solve the shortcomings in the prior art that when the cross-sectional area of the head cone changes greatly, the continuity of the composite material is difficult to ensure, and at the same time, it is difficult for the solidified material to enter the middle position of the cross-section with a larger thickness, resulting in uneven distribution of the solidified material in the middle position, which has a great impact on the bearing performance of the head cone. The wing-rudder head cone and hanging point integrated structure of the present invention includes a head cone formed by splicing a first semi-cone and a second semi-cone, an inner and outer wrapping rings arranged on the bottom surface of the head cone, and a rudder body fixed to the side of the head cone; the bottom surface of the head cone is coaxially provided with an annular boss, an inner and outer wrapping rings, and the rudder body is fixedly connected to the outer wrapping ring through the first and second hanging points; the manufacturing method of the present invention effectively improves the uniformity of the material density of the integrated structure and reduces the manufacturing cycle.

Description

Technical Field

[0001] The present invention relates to a wing-rudder structure and a manufacturing method thereof, and in particular to a wing-rudder nose cone and hanging point integrated structure and a manufacturing method thereof. Background Art

[0002] At present, the preparation process of composite materials at home and abroad mainly includes two parts: composite material molding and composite material curing. When curing composite materials, chemical vapor deposition (CVI), precursor impregnation and pyrolysis (PIP), reactive melt infiltration (RMI), slurry impregnation and hot pressing and other preparation methods are usually used. All of them require the curing material to enter the interior of the composite material. Therefore, the above methods have high requirements on the cross-sectional thickness of the product preform and the continuity of the preform fiber during the preparation process. The cross-sectional thickness of the top angle and bottom surface of the conical structure of the rudder nose cone varies greatly. When the cross-sectional area changes greatly, the continuity of the composite material is difficult to ensure. At the same time, it is difficult for the curing material to enter the middle position of the thicker cross-section, resulting in uneven distribution of the curing material in the middle position, making the density uniformity of the nose cone poor, which has a great impact on the bearing performance of the nose cone. Summary of the Invention

[0003] The purpose of the present invention is to solve the shortcomings in the prior art that when the cross-sectional area of the nose cone changes greatly, the continuity of the composite material is difficult to ensure, and at the same time, it is difficult for the solidified material to enter the middle position of the cross-section with a larger thickness, resulting in uneven distribution of the solidified material in the middle position, which has a great impact on the bearing performance of the nose cone. A method for manufacturing the same is provided.

[0004] To achieve the above objectives, the present invention provides the following technical solutions:

[0005] A wing rudder nose cone and hanging point integrated structure, which is special in that: it includes a nose cone formed by splicing a first semi-cone and a second semi-cone, an inner ring and an outer ring arranged on the bottom surface of the nose cone, and a rudder body fixed to the side surface of the nose cone; long notches are provided at corresponding positions along the axial direction at the junction of the first semi-cone and the second semi-cone, and the two long notches are spliced to form a first groove; an annular boss is provided coaxially with the bottom surface of the nose cone; the inner ring is sleeved on the annular boss; the outer ring is sleeved on the outside of the inner ring, and a through groove is provided on the side wall of the outer ring along the axial direction, the center lines of the through groove and the first groove are located in the same radial plane, and the two side walls of the through groove extend outward to form a first hanging point and a second hanging point respectively. ; The rudder body includes an airfoil-shaped rudder and a connecting structure thereof. The cross-section of the airfoil-shaped rudder is a trapezoid. The waist of the trapezoidal cross-section continuously decreases along the axial direction, and the heights of the two waists near the top angle of the nose cone approach zero. The surface where the lower base of the trapezoid is located corresponds to the first groove on the side surface of the nose cone and the through groove of the outer ring. A connecting structure is provided at a position corresponding to the first groove on the side surface of the nose cone on the bottom surface of the airfoil-shaped rudder. The connecting structure is connected to the first groove. The two side surfaces of the airfoil-shaped rudder are respectively provided with second grooves that match the first hanging point and the second hanging point. The first hanging point and the second hanging point are respectively installed in the two second grooves, and the outer surfaces of the first hanging point and the second hanging point are flush with the two side surfaces of the airfoil-shaped rudder.

[0006] Furthermore, the annular boss includes a first half ring and a second half ring, one end of the first half ring is fixedly connected to the first semi-cone, and one end of the second half ring is fixedly connected to the second semi-cone; the inner ring is sleeved outside the first half ring and the second half ring.

[0007] Furthermore, the outer ring includes a third half ring and a fourth half ring, and an installation space is left between one of the corresponding end faces of the third half ring and the fourth half ring. The end faces on both sides of the installation space extend outward to form a first hanging point and a second hanging point respectively, and the first hanging point and the second hanging point are relatively arranged planar structures.

[0008] Furthermore, threaded holes are respectively provided on the connecting structure, the first semi-cone and the second semi-cone on both sides of the first groove, the wing-shaped rudder between the two second grooves, the first hanging point and the second hanging point, as well as the inner ring, the outer ring and the annular boss, and screws are provided in the corresponding threaded holes for fixed connection.

[0009] Furthermore, light holes are correspondingly provided on the connecting structure, the first semi-cone and the second semi-cone on both sides of the first groove, the wing-shaped rudder between the two second grooves, the first hanging point and the second hanging point, as well as the inner ring, the outer ring and the annular boss, and pins are provided in the corresponding light holes for fixed connection.

[0010] Furthermore, the first hanging point and the second hanging point are both right-angled trapezoids.

[0011] At the same time, the present invention also provides a method for manufacturing the above-mentioned integrated structure of the rudder nose cone and the attachment point, which is special in that it includes the following steps:

[0012] S1. Assembling the first semi-cone, the second semi-cone and the annular boss

[0013] The first semi-cone and the second semi-cone form a head cone, a first groove is formed on one side of the junction of the first semi-cone and the second semi-cone, and an annular boss is provided on the bottom surface of the head cone;

[0014] S2. Assemble the inner ring

[0015] The inner ring sleeve is arranged on the annular boss and is coaxial with the annular boss;

[0016] S3. Assemble the rudder body

[0017] Inserting the connecting structure of the rudder body into the corresponding first groove;

[0018] S4. Assemble the outer ring, the first hanging point and the second hanging point

[0019] The outer wrapping ring is sleeved on the outer side of the inner wrapping ring, and the through groove of the outer wrapping ring is arranged to match the bottom surface of the airfoil rudder, so that the first hanging point and the second hanging point are respectively located in the second grooves on the two sides of the airfoil rudder. After the assembly is completed, a formed rudder nose cone and hanging point integrated structure is obtained;

[0020] S5. Solidify the integrated structure in S4 to obtain a stable integrated structure.

[0021] Furthermore, before S1, step S0 is also included:

[0022] Use molds to respectively manufacture a first semi-cone, a second semi-cone, an annular boss, an inner wrapping ring, a rudder body, an outer wrapping ring, a first hanging point, and a second hanging point;

[0023] The annular boss includes a first half ring and a second half ring, and the outer ring includes a third half ring and a fourth half ring;

[0024] The first semi-cone and the first semi-ring, the second semi-cone and the second semi-ring, the third semi-ring and the first hanging point, and the fourth semi-ring and the second hanging point are all integrated structures.

[0025] Furthermore, the materials used for the first semi-cone, the second semi-cone, the annular boss, the inner wrapping ring, the rudder body and the outer wrapping ring are all ceramic-based composite materials;

[0026] In S5, the CVI-SiC method is used to solidify the formed wing-rudder nose cone and the integrated structure of the hanging point.

[0027] Furthermore, S4 further includes forming threaded holes or light holes on the integrated structure and setting corresponding screws or pins, specifically: forming threaded holes or light holes on the connecting structure and the first and second semi-cones on both sides of the first groove, on the bottom surface of the second groove and the first and second hanging points, and on the inner and outer rings and the annular boss, and setting screws or pins in the corresponding threaded holes or light holes;

[0028] In S5, the integrated structure provided with the screws or pins is solidified.

[0029] Compared with the prior art, the present invention has the following beneficial effects:

[0030] 1. The head cone of the present invention has a combined structure of a first semi-cone and a second semi-cone. During the manufacturing process, the solidified material can enter at the joint, effectively reducing the problems of uneven material density, unstable quality and long manufacturing cycle caused by the excessive cross-sectional thickness of the head cone.

[0031] 2. The first hanging point and the second hanging point of the present invention are both connected to the outer ring, and the outer ring is sleeved on the inner ring, so that the bearing capacity of the hanging point is effectively improved; at the same time, the outer ring includes a third half ring and a fourth half ring, making the installation process simpler and more convenient.

[0032] 3. The rudder body of the present invention is inserted into the first groove correspondingly arranged on the head cone through the connecting structure and is connected by screws or pins, thereby ensuring the reliability of the connection between the head cone and the rudder body and the subsequent maintainability. In the later stage, mechanical processing methods can be used to realize the in-situ replacement of screws or pins, which is convenient for maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a structural diagram of an embodiment of the present invention;

[0034] Figure 2 1 is an assembly diagram of the nose cone and the annular boss in an embodiment of the present invention; wherein a is an exploded view of the nose cone and the annular boss, and b is a structural diagram of the nose cone and the annular boss after assembly;

[0035] Figure 3 1 is an assembly diagram of the inner wrapping ring in an embodiment of the present invention; a is an assembly schematic diagram of the inner wrapping ring, and b is a structural diagram of the inner wrapping ring after assembly;

[0036] Figure 4 1 is an assembly diagram of the rudder body in an embodiment of the present invention; a is an assembly schematic diagram of the rudder body, and b is a structural diagram of the rudder body after assembly;

[0037] Figure 5 1 is an assembly diagram of an embodiment of the present invention without showing the threaded holes; a is an exploded view of the wing-rudder head cone integrated structure, and b is a structural schematic diagram of the wing-rudder head cone integrated structure;

[0038] Figure 6 1 is an assembly diagram of an embodiment of the present invention; a is an exploded view of the wing-rudder-head-cone integrated structure, and b is a structural schematic diagram of the wing-rudder-head-cone integrated structure;

[0039] Description of reference numerals:

[0040] 1-rudder body, 101-airfoil rudder, 102-connecting structure, 103-second groove, 201-third semi-ring, 202-fourth semi-ring, 301-first hanging point, 302-second hanging point, 401-first semi-cone, 402-second semi-cone, 403-first groove, 501-first semi-ring, 502-second semi-ring, 6-inner ring. DETAILED DESCRIPTION

[0041] The present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments:

[0042] The rudder nose cone and hanging point integrated structure of the present invention is as follows: Figure 1 As shown, it includes a head cone formed by splicing a first semi-cone 401 and a second semi-cone 402, an inner wrapping ring 6 and an outer wrapping ring arranged on the bottom surface of the head cone, and a rudder body 1 fixed to the side surface of the head cone; an annular boss is coaxially provided on the bottom surface of the head cone, and the annular boss includes a first semi-ring 501 and a second semi-ring 502, one end of the first semi-ring 501 is fixedly connected to the first semi-cone 401, and one end of the second semi-ring 502 is fixedly connected to the second semi-cone 402, and the inner wrapping ring 6 is sleeved on the outside of the first semi-ring 501 and the second semi-ring 502; long notches are provided at corresponding positions along the axial direction at the junction of the first semi-cone 401 and the second semi-cone 402, and the two long notches are spliced to form a first groove 403.

[0043] The outer wrapping ring is cylindrical and is sleeved on the outside of the inner wrapping ring 6, and a through groove is axially provided on the side wall of the outer wrapping ring. The center lines of the through groove and the first groove 403 are located in the same radial plane, and the two side walls of the through groove extend outward to form a first hanging point 301 and a second hanging point 302 respectively, and the first hanging point 301 and the second hanging point 302 are planar structures arranged opposite to each other; in this embodiment, the outer wrapping ring includes a third half ring 201 and a fourth half ring 202, and an installation space is left between one of the corresponding end faces of the third half ring 201 and the fourth half ring 202, and the end faces on both sides of the installation space extend radially outward to form a first hanging point 301 and a second hanging point 302 respectively, and the first hanging point 301 and the second hanging point 302 are right-angled trapezoids, and the waist perpendicular to the bottom edge is respectively connected to the corresponding end faces of the third half ring 201 and the fourth half ring 202.

[0044] The rudder body 1 includes an airfoil rudder 101 and a connecting structure 102 thereof. The cross-section of the airfoil rudder 101 is a trapezoid. The waist of the trapezoidal cross-section gradually decreases along the axial direction. The height of the two waists near the apex angle of the nose cone approaches zero, and the trapezoidal cross-sectional area is reduced. The surface where the lower base of the trapezoid is located corresponds to the first groove 403 on the side of the nose cone and the through groove of the outer ring; the airfoil rudder 101 is provided with a connecting structure 102 at a position corresponding to the first groove 403 on the side of the nose cone, and the connecting structure 102 cooperates with the first groove 403; in this embodiment, the two sides of the airfoil rudder 101 are respectively provided with second grooves 103 that cooperate with the first hanging point 301 and the second hanging point 302. The first hanging point 301 and the second hanging point 302 are respectively installed in the two second grooves 103, and the outer surfaces of the first hanging point 301 and the second hanging point 302 are flush with the two side surfaces of the airfoil rudder 101, meeting the dynamic requirements of the airfoil rudder 101.

[0045] In this embodiment, threaded holes are correspondingly provided on the connecting structure 102 and the first semi-cone 401 and the second semi-cone 402 on both sides of the first groove 403, the wing-shaped rudder 101 between the two second grooves 103 and the first hanging point 301 and the second hanging point 302, as well as the inner ring 6, the outer ring and the annular boss, and screws are provided in the corresponding threaded holes for fixed connection; in other embodiments of the present invention, the threaded holes can also be light holes, and pins are provided in the corresponding light holes for fixed connection.

[0046] The first semi-cone 401, the second semi-cone 402, the annular boss, the inner wrapping ring 6, the rudder body 1, the outer wrapping ring, and the screws or pins are all made of ceramic matrix composite materials. The various parts are first formed using the ceramic matrix composite materials, and then assembled into one body, and then cured using the CVI-SiC method. The manufacturing method includes the following steps:

[0047] S1. Use molds to respectively produce the first semi-cone 401, the second semi-cone 402, the first semi-ring 501, the second semi-ring 502, the inner ring 6, the rudder body 1, the third semi-ring 201, the fourth semi-ring 202, the first hanging point 301 and the second hanging point 302;

[0048] The first semi-cone 401 and the first semi-ring 501, the second semi-cone 402 and the second semi-ring 502, the third semi-ring 201 and the first hanging point 301, and the fourth semi-ring 202 and the second hanging point 302 are all integrated structures.

[0049] S2, assemble the first semi-cone 401, the second semi-cone 402, the first semi-ring 501 and the second semi-ring 502 to form a head cone and an annular boss, and form a first groove 403 on one side of the junction of the first semi-cone 401 and the second semi-cone 402, as shown in FIG. Figure 2 As shown;

[0050] S3, assemble inner ring 6

[0051] The inner wrapping ring 6 is sleeved on the annular boss, and the inner side surface of the inner wrapping ring 6 and the outer side surface of the annular boss are tightly fitted and coaxially arranged, such as Figure 3 As shown;

[0052] S4. Assemble the rudder body 1

[0053] The connecting structure 102 of the rudder body 1 is inserted into the corresponding first groove 403, as shown in FIG. Figure 4 As shown;

[0054] S5. Assemble the third half ring 201, the fourth half ring 202, the first hanging point 301 and the second hanging point 302

[0055] The third half ring 201 and the fourth half ring 202 are arranged on the outside of the inner ring 6. The through groove formed by the third half ring 201 and the fourth half ring 202 is arranged to match the bottom surface of the airfoil rudder 101, so that the first hanging point 301 and the second hanging point 302 are respectively located in the second groove 103 on the two sides of the airfoil rudder 101. Figure 5 As shown, the formed wing-rudder nose cone and hanging point integrated structure is obtained;

[0056] S6. Threaded holes are formed on the connection structure 102 of the integral structure of the rudder nose cone and the hanging point, the first semi-cone 401 and the second semi-cone 402 on both sides of the first groove 403, the bottom surface of the second groove 103, the first hanging point 301 and the second hanging point 302, as well as the inner ring 6, the outer ring and the annular boss; and screws are installed in the corresponding threaded holes, such as Figure 6 As shown;

[0057] S7. Use the CVI-SiC method to solidify the integrated structure provided with screws in S6, so that the SiC material enters the composite material of the integrated structure of the wing-rudder nose cone, forming a stable integrated structure. In other embodiments of the present invention, other solidification methods may also be used for solidification.

Claims

1. A rudder nose cone and attachment point integrated structure, characterized by: It comprises a nose cone formed by splicing a first semi-cone (401) and a second semi-cone (402), an inner wrapping ring (6) and an outer wrapping ring arranged on the bottom surface of the nose cone, and a rudder body (1) fixed on the side surface of the nose cone; Long notches are provided at corresponding positions along the axial direction at the junction of the first semi-cone (401) and the second semi-cone (402), and the two long notches are spliced together to form a first groove (403); an annular boss is provided coaxially with the bottom surface of the head cone; The inner enveloping ring (6) is sleeved on the annular boss; The outer wrapping ring is sleeved outside the inner wrapping ring (6), and a through groove is provided on the side wall of the outer wrapping ring along the axial direction. The center lines of the through groove and the first groove (403) are located in the same radial plane, and the two side walls of the through groove extend outward to form a first hanging point (301) and a second hanging point (302) respectively; The rudder body (1) comprises an airfoil rudder (101) and a connecting structure (102) thereof. The cross section of the airfoil rudder (101) is a trapezoid. The waist of the trapezoidal cross section continuously decreases along the axial direction, and the heights of the two waists near the top angle of the nose cone approach zero. The surface where the lower base of the trapezoid is located corresponds to the first groove (403) on the side surface of the nose cone and the through groove of the outer ring. A connecting structure (102) is provided at a position corresponding to the first groove (403) on the side surface of the nose cone on the bottom surface of the wing-shaped rudder (101); the connecting structure (102) is matched with the first groove (403); the two side surfaces of the wing-shaped rudder (101) are respectively provided with second grooves (103) matched with the first hanging point (301) and the second hanging point (302); the first hanging point (301) and the second hanging point (302) are respectively installed in the two second grooves (103); and the outer surfaces of the first hanging point (301) and the second hanging point (302) are flush with the two side surfaces of the wing-shaped rudder (101).

2. The integrated structure of the rudder nose cone and the attachment point according to claim 1, characterized in that: The annular boss comprises a first half ring (501) and a second half ring (502), one end of the first half ring (501) is fixedly connected to the first semi-cone (401), and one end of the second half ring (502) is fixedly connected to the second semi-cone (402); the inner ring (6) is sleeved on the outside of the first half ring (501) and the second half ring (502).

3. The integrated structure of the rudder nose cone and the attachment point according to claim 2, characterized in that: The outer ring comprises a third half ring (201) and a fourth half ring (202); an installation space is reserved between corresponding end faces of the third half ring (201) and the fourth half ring (202); end faces on both sides of the installation space extend outward to form a first hanging point (301) and a second hanging point (302), respectively; the first hanging point (301) and the second hanging point (302) are planar structures arranged opposite to each other.

4. The integrated structure of the rudder nose cone and the attachment point according to claim 3, characterized in that: Threaded holes are correspondingly provided on the connecting structure (102), the first semi-cone (401) and the second semi-cone (402) on both sides of the first groove (403), the wing-shaped rudder (101) between the two second grooves (103), the first hanging point (301) and the second hanging point (302), as well as the inner wrapping ring (6), the outer wrapping ring and the annular boss, and screws are provided in the corresponding threaded holes for fixed connection.

5. The integrated structure of the rudder nose cone and the attachment point according to claim 3, characterized in that: Light holes are correspondingly provided on the connecting structure (102), the first semi-cone (401) and the second semi-cone (402) on both sides of the first groove (403), the wing-shaped rudder (101) between the two second grooves (103), the first hanging point (301) and the second hanging point (302), as well as the inner wrapping ring (6), the outer wrapping ring and the annular boss, and pins are provided in the corresponding light holes for fixed connection.

6. The integrated structure of the rudder nose cone and attachment point according to any one of claims 1 to 5, characterized in that: The first hanging point (301) and the second hanging point (302) are both right-angled trapezoids.

7. A method for manufacturing a rudder nose cone and attachment point integrated structure according to any one of claims 1 to 6, characterized in that: The following steps are involved: S1. Assembling the first semi-cone (401), the second semi-cone (402) and the annular boss The first semi-cone (401) and the second semi-cone (402) form a head cone, a first groove (403) is formed on one side of the junction of the first semi-cone (401) and the second semi-cone (402), and an annular boss is provided on the bottom surface of the head cone; S2. Assemble the inner ring (6) The inner enveloping ring (6) is sleeved on the annular boss and is coaxially arranged with the annular boss; S3. Assemble the rudder body (1) Embedding the connection structure (102) of the rudder body (1) into a correspondingly provided first groove (403); S4. Assembling the outer ring, the first hanging point (301) and the second hanging point (302) The outer wrapping ring is sleeved on the outer side of the inner wrapping ring (6), and the through groove of the outer wrapping ring is arranged in conjunction with the bottom surface of the wing-shaped rudder (101), so that the first hanging point (301) and the second hanging point (302) are respectively located in the second grooves (103) on the two sides of the wing-shaped rudder (101), and the rudder head cone and the hanging point integrated structure are obtained after the assembly is completed; S5. Solidify the integrated structure in S4 to obtain a stable integrated structure.

8. The method for manufacturing a rudder nose cone and attachment point integrated structure according to claim 7, characterized in that: S1 also includes step S0 before: Using a mold, respectively manufacture a first semi-cone (401), a second semi-cone (402), an annular boss, an inner wrapping ring (6), a rudder body (1), an outer wrapping ring, a first hanging point (301), and a second hanging point (302); The annular boss includes a first half ring (501) and a second half ring (502), and the outer ring includes a third half ring (201) and a fourth half ring (202); The first semi-cone (401) and the first semi-ring (501), the second semi-cone (402) and the second semi-ring (502), the third semi-ring (201) and the first hanging point (301), and the fourth semi-ring (202) and the second hanging point (302) are all integrated structures.

9. The method for manufacturing a rudder nose cone and attachment point integrated structure according to claim 8, characterized in that: The materials used for the first semi-cone (401), the second semi-cone (402), the annular boss, the inner wrapping ring (6), the rudder body (1) and the outer wrapping ring are all ceramic-based composite materials; In S5, the CVI-SiC method is used to solidify the formed wing-rudder nose cone and the integrated structure of the hanging point.

10. The method for manufacturing a fin-rudder nose cone and attachment point integrated structure according to claim 9, characterized in that: S4 further includes opening threaded holes or light holes on the integrated structure and setting corresponding screws or pins, specifically: opening threaded holes or light holes on the first semi-cone (401) and the second semi-cone (402) on both sides of the connecting structure (102) and the first groove (403), on the bottom surface of the second groove (103) and the first hanging point (301) and the second hanging point (302), and on the inner ring (6), the outer ring and the annular boss, and setting screws or pins in the corresponding threaded holes or light holes; In S5, the integrated structure provided with the screws or pins is solidified.

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