A clamping and rotating device for manufacturing of aircraft engine acoustic liner structures and method of use thereof

Abstract

The application discloses a clamping and rotating device for manufacturing an aircraft engine sound insulation structure and a use method thereof, and the device comprises a rotating main shaft, a plurality of sets of clamping plate mechanisms sleeved on the rotating main shaft and a separately arranged rotating support seat; the composite forming male die and the engine sound insulation structure are clamped by the clamping plate mechanisms and are supported to have certain rigidity, so that the panel and the back plate can be laid and pasted; the composite forming male die and the engine sound insulation structure are kept in a certain posture by the rotating support seat, so that the honeycomb filling and the hole making operation can be facilitated. The device realizes the functions of laying, pasting, filling and sealing and hole making of the composite material product, embodies the advantages of cost reduction and site saving, and has universality and good practical value.

Description

TECHNICAL FIELD

[0001] The present application relates to a clamping and rotating device for manufacturing an aircraft engine acoustic liner structure and a method for using the same. BACKGROUND

[0002] The noise of an aircraft mainly comes from the engine, so the noise reduction of the engine becomes a key point. As long as the noise of the aircraft engine can be effectively reduced, the problem of the large noise of the aircraft can be solved. At present, the main technologies for reducing the noise of the engine include increasing the bypass ratio, using an acoustic liner, and a long fairing, etc. Among them, the acoustic liner is the most potential technology for improving the noise of the engine.

[0003] The acoustic liner structure is made of composite materials, which can not only reduce the weight of the engine but also achieve the noise reduction effect. The acoustic liner structure is a large-curvature cylindrical structure, which includes a panel, a honeycomb, a back plate, etc. as shown in the structure diagram. Figure 1 The forming process of the acoustic liner structure generally includes laying the panel on the forming mold, pouring the honeycomb, laying the back plate, and drilling holes. The forming mold of the acoustic liner structure is generally also a cylindrical carbon fiber composite mold, which includes a male mold and a female mold. Because the diameter of the acoustic liner structure is large, the overall stiffness of the forming mold is weak, so how to fix the profile of the carbon fiber composite mold becomes a key technology for manufacturing the acoustic liner structure. At the same time, the honeycomb inside the acoustic liner structure needs to be poured at a certain attitude to ensure that it meets the design requirements and avoid the risk of honeycomb collapse, so how to ensure the attitude of the honeycomb during pouring is also an important part of the manufacturing process of the acoustic liner structure. In addition, due to the special cylindrical structure of the acoustic liner structure, the drilling of the holes is also very difficult, so how to quickly and accurately drill holes is also a problem to be solved in the manufacturing process of the acoustic liner structure. SUMMARY

[0004] In order to solve the above problems and achieve the above purposes, the present application provides a clamping and rotating device for manufacturing an aircraft engine acoustic liner structure and a method for using the same. The device is designed with a rotating function and can be fixed based on the inner profile of the male mold of the acoustic liner structure forming mold (hereinafter referred to as the composite forming male mold), which ensures the profile stiffness of the composite forming male mold during the manufacturing process of the acoustic liner structure, and facilitates the laying of the panel, the pouring of the honeycomb, and the subsequent assembly and drilling of the holes. The specific technical scheme is as follows:

[0005] Firstly, the present application provides a clamping and rotating device for manufacturing an aircraft engine acoustic liner structure, which comprises a rotating main shaft, a plurality of sets of clamping plate mechanisms sleeved on the rotating main shaft, and a separately arranged rotating support seat.

[0006] The rotating main shaft is arranged along the central axis of the engine acoustic liner structure, and the length of the rotating main shaft is greater than the height of the engine acoustic liner structure.

[0007] The clamping plate mechanism comprises a ring-shaped fixing seat sleeved on the rotating main shaft and a plurality of clamping plate units distributed on the outer edge of the ring-shaped fixing seat;

[0008] The clamping plate unit comprises a clamping plate body and a clamping plate adjusting assembly;

[0009] The clamping plate body is in contact with the inner profile of the composite forming male mold or the engine acoustic lining structural member, and is used for supporting the profile of the composite forming male mold or the engine acoustic lining structural member;

[0010] The clamping plate adjusting assembly is used for adjusting the clamping plate body, facilitating the assembly and clamping of the composite forming male mold and the engine acoustic lining structural member, and making the profile of the composite forming male mold and the engine acoustic lining structural member meet the design requirements;

[0011] The rotating support seat is used for supporting the two ends of the rotating main shaft, and the rotating main shaft can rotate on the rotating support seat, and the composite forming male mold and the engine acoustic lining structural member can maintain the required posture during the manufacturing process.

[0012] The clamping and rotating device for manufacturing the engine acoustic lining structural member of the aircraft,

[0013] The plurality of clamping plate units are evenly distributed on the outer edge of the ring-shaped fixing seat in a radial manner around the rotating main shaft;

[0014] The clamping plate body is L-shaped or T-shaped, and comprises a contact part directly in contact with the inner profile of the composite forming male mold or the engine acoustic lining structural member and a connecting part used for connecting with the clamping plate adjusting assembly;

[0015] The clamping plate adjusting assembly comprises an adjusting seat fixed on the ring-shaped fixing seat, an adjusting screw and an adjusting handle;

[0016] The adjusting screw is connected with the connecting part of the clamping plate body through the adjusting seat;

[0017] The adjusting handle is used for adjusting the normal movement of the clamping plate body along the adjusting screw perpendicular to the rotating main shaft, clamping or loosening the composite forming male mold and the engine acoustic lining structural member, or keeping the profile of the composite forming male mold and the engine acoustic lining structural member in the design state.

[0018] Preferably, the clamping plate body is provided with an OPT point for detecting the matching precision of the clamping plate body and the inner profile of the composite forming male mold or the engine acoustic lining structural member.

[0019] Preferably, the adjusting screw and the adjusting seat are further provided with a clamping plate positioning pin hole, and the clamping plate body is positioned at a certain position by the clamping plate positioning pin, so as to keep the profile state of the composite forming male mold and the engine acoustic lining structural member.

[0020] The clamping and rotating device for manufacturing the engine acoustic lining structural member of the aircraft,

[0021] The clamping plate mechanism is two groups, which are arranged in the middle of the rotating main shaft; the edge of the annular fixing seat is also provided with a composite forming male die or an assembly supporting seat of the engine sound insulation structural member, which is used for installing the assembly supporting plate;

[0022] The assembly supporting seat is arranged at intervals with the clamping plate body, and the assembly supporting plate is used for positioning and supporting the horn of the composite forming male die or the engine sound insulation structural member;

[0023] The shaped arc of the assembly supporting plate is consistent with the everted arc of the horn of the composite forming male die and the engine sound insulation structural member.

[0024] The aforementioned clamping and rotating device for manufacturing the engine sound insulation structural member of the aircraft further comprises a laying supporting seat, which is a prism type frame structure welded by square steel;

[0025] The center of the table surface of the laying supporting seat is provided with a rotating shaft hole for vertically installing the rotating main shaft, so as to facilitate the laying of the panel and the back plate of the engine sound insulation structural member.

[0026] The aforementioned clamping and rotating device for manufacturing the engine sound insulation structural member of the aircraft, the rotating supporting seat is provided with a bearing sleeve at the fulcrum of the two ends of the rotating main shaft, and the bearing sleeve and the rotating main shaft are provided with rotating positioning pin holes at the corresponding positions, and the rotating main shaft is fixed by the rotating positioning pin to position the composite forming male die or the engine sound insulation structural member in the required posture.

[0027] Preferably, the rotating positioning pin holes on the rotating main shaft are multiple, so as to position the composite forming male die and the engine sound insulation structural member in different postures.

[0028] Preferably, the end of the rotating main shaft is provided with a rotating handle for rotating operation.

[0029] The use method of the aforementioned clamping and rotating device for manufacturing the engine sound insulation structural member of the aircraft comprises the following steps:

[0030] 1) Assembling the composite forming male die: rotating the adjusting handle of the clamping plate mechanism to move the clamping plate body inward along the axis of the rotating main shaft, so as to set the composite forming male die on the clamping plate mechanism on the rotating main shaft; then reversely rotating the adjusting handle of the clamping plate mechanism to move the clamping plate body outward along the normal direction of the rotating main shaft, so as to clamp the composite forming male die; and vertically inserting the rotating main shaft into the rotating shaft hole of the laying supporting seat, so as to make the composite forming male die in a vertical state;

[0031] 2) Adjusting the model surface of the composite forming male die: adjusting the position of the clamping plate according to the measurement results, adjusting the moving distance of the clamping plate body, until the model surface of the composite forming male die meets the design tolerance requirements, and locking the model surface state of the composite forming male die by the clamping positioning pin;

[0032] 3) Panel laying: lay the panel material of the prepared engine sound insulation structure on the locked composite forming male mold surface according to requirements;

[0033] 4) Honeycomb filling: after the panel laying of the engine sound insulation structure is completed, remove the laying support seat; then install the entire device horizontally or at an angle on the rotating support seat; rotate the rotating main shaft, and position the composite forming male mold at a certain posture through the rotating positioning pin to fill the honeycomb;

[0034] 5) Backboard laying: after the honeycomb filling is completed, remove the entire device from the rotating support seat, again vertically insert the rotating main shaft into the rotating shaft hole of the laying support seat, so that it is in an upright state; then lay the prepared backboard material of the engine sound insulation structure on the filled honeycomb according to requirements;

[0035] 6) Forming and hole making: after the backboard laying is completed, solidify and form according to requirements; after solidification and forming, remove the forming mold, then set the engine sound insulation structure obtained by solidification and forming on the clamping plate mechanism in the manner of step 1), and adjust the profile of the engine sound insulation structure to meet the design requirements in the manner of step 2); then install the entire device on the rotating support seat, rotate the rotating main shaft, and position the engine sound insulation structure at a certain posture through the rotating positioning pin to perform hole making operation.

[0036] Preferably, the assembling of the composite forming male mold in step 1) is: first, assemble the assembling base plate on the assembling base plate seat, then assemble after vertically inserting the rotating main shaft into the rotating shaft hole of the laying support seat, and the trumpet mouth of the composite forming male mold is placed downward; or first vertically insert the rotating main shaft into the rotating shaft hole of the laying support seat, then assemble the composite forming male mold, and finally install the assembling base plate, and the trumpet mouth of the composite forming male mold can be placed upward or downward.

[0037] The application has the following beneficial effects:

[0038] The clamping and rotating device for the engine sound insulation structure of the aircraft provided by the application can fix the profile of the composite forming mold of the engine sound insulation structure of the aircraft or the profile of the engine sound insulation structure itself at the profile position required by the design, and keep a certain rigidity, which is convenient for panel and backboard laying, honeycomb filling, and hole making.

[0039] The application realizes the concentration of multiple requirements such as composite material part laying, filling, and hole making in one set of device, and has the advantages of reducing cost and saving occupied space.

[0040] The application has universality, and is applicable to the profile support requirements of large-curvature whole-tube composite material parts or large-curvature composite material parts, and has good practical value. BRIEF DESCRIPTION OF DRAWINGS

[0041] Figure 1 Structure diagram of engine sound insulation structure of the present application;

[0042] Figure 2 Structure diagram of composite forming male die of the present application;

[0043] Figure 3 Structure diagram of several sets of clamping plate mechanisms and paving and supporting seat structures sleeved on the rotating main shaft of the present application;

[0044] Figure 4 Structure diagram of several sets of clamping plate mechanisms and rotating supporting seat structures sleeved on the rotating main shaft of the present application;

[0045] Figure 5 Structure diagram of clamping plate assembly of the present application;

[0046] Figure 6 Structure diagram of bearing sleeve, rotating positioning pin hole and rotating positioning pin of the present application;

[0047] Figure 7 Assembling diagram of composite forming male die of the present application;

[0048] Figure 8 Diagram of engine sound insulation structure rotating hole operation using the device of the present application.

[0049] In the drawings: 1, engine sound insulation structure; 11, face plate; 12, back plate; 13, honeycomb; 2, composite forming male die; 3, rotating main shaft; 31, rotating handle; 4, annular fixing seat; 5, clamping plate assembly; 51, clamping plate body; 511, contact part; 512, connecting part; 52, clamping plate adjusting assembly; 521, adjusting seat; 522, adjusting screw; 523, adjusting handle; 524, clamping plate positioning pin hole; 6, paving and supporting seat; 61, rotating shaft hole; 7, rotating supporting seat; 71, bearing sleeve; 72, rotating positioning pin hole; 73, rotating positioning pin; 8, clamping plate positioning pin; 91, assembling supporting plate seat; 92, assembling supporting plate; DETAILED DESCRIPTION

[0050] The technical solutions of the present application will be described clearly and completely below in combination with embodiments and drawings. Obviously, the described embodiments are only the preferred embodiments of the present application, rather than all the embodiments, nor are they other forms of limitations of the present application. Any skilled person in the art can make changes or modifications, etc. by using the disclosed technical content. However, any simple modification, equivalent change and modification made according to the technical essence of the present application without departing from the technical solution content of the present application still belongs to the protection scope of the technical solution of the present application. The specific embodiments are as follows:

[0051] This embodiment is a clamping and rotating device for manufacturing aircraft engine acoustic lining structural parts, such as Figures 3 to 6 As shown, it includes a rotating main shaft 3, several groups of clamping mechanisms sleeved on the rotating main shaft 3 and a separately arranged rotating support seat 7; the rotating main shaft 3 is arranged along the central axis of the engine sound lining structure 1, and its length is greater than the height of the engine sound lining structure 1; the clamping mechanism includes an annular fixing seat 4 sleeved on the rotating main shaft 3 and several clamping units 5 distributed on the outer edge of the annular fixing seat 4; the clamping unit 5 includes a clamping body 51 and a clamping adjustment assembly 52; the clamping body 51 contacts the inner surface of the composite molding male mold 2 or the engine sound lining structure 1, and is used to support the surface of the composite molding male mold 2 or the engine sound lining structure 1; the clamping adjustment assembly 52 is used to adjust the clamping body 51 to facilitate the assembly and clamping of the composite molding male mold 2 and the engine sound lining structure 1, and to make the surfaces of the composite molding male mold 2 and the engine sound lining structure 1 meet the design requirements and ensure the rigidity of the composite molding male mold 2, so as to facilitate the laying of the panel and back panel of the engine sound lining structure 1. The rotating support 7 supports both ends of the rotating spindle 3, which can rotate on the rotating support 7, maintaining the composite forming male mold 2 and the engine acoustic lining structural component 1 in the desired posture during the manufacturing process, facilitating honeycomb filling and subsequent hole-making operations of the engine acoustic lining structural component 1. This allows multiple required functions, such as composite component laying, potting, and hole-making, to be integrated into a single device, resulting in cost reduction and space conservation.

[0052] In this embodiment, the plurality of cardboard units 5 are radially and evenly distributed on the outer edge of the annular fixing seat 4 around the rotating main shaft 3; the cardboard body 51 is L-shaped or T-shaped, and includes a contact portion 511 that directly contacts the inner surface of the composite molding male mold 2 or the engine acoustic lining structural component 1 and a connecting portion 512 for connecting to the cardboard adjustment assembly 52; the cardboard adjustment assembly 52 includes an adjustment seat 521 fixed on the annular fixing seat 4, an adjustment screw 522 and an adjustment handle 523; the adjustment screw 522 passes through the adjustment seat 521 and is connected to the connecting portion 512 of the cardboard body 51; the adjustment handle 523 is used to adjust the adjustment screw 522 to drive the cardboard body 51 to move in a normal direction perpendicular to the rotating main shaft 3, clamping or releasing the composite molding male mold 2 and the engine acoustic lining structural component 1, or keeping its surface in the design requirement state. The card plate body 51 is also provided with a plurality of OPT points for cooperating with the digital detection method to detect the surface accuracy of the composite molding male mold 2 or the engine sound lining structural component 1 supported by the card plate body 51; the adjusting screw 522 and the adjusting seat 521 are also provided with a card plate positioning pin hole 524, and the card plate positioning pin 8 is used to position the card plate body 51 at a certain position to maintain the surface state of the composite molding male mold 2 and the engine sound lining structural component 1.

[0053] As a preferred embodiment, the clamping plate mechanism is two groups, which are arranged at the middle part of the rotating main shaft 3; the edge of the annular fixing seat 4 is further provided with a composite forming male die 2 or an assembly supporting plate seat 91 of the engine sound insulation structural member 1, which is used for installing an assembly supporting plate 92; the assembly supporting plate seat 91 is arranged at intervals with the clamping plate body 51, the assembly supporting plate 92 is used for positioning and supporting the horn mouth of the composite forming male die 2 or the engine sound insulation structural member 1; the shaped curvature of the assembly supporting plate 92 is consistent with the everted curvature of the horn mouth of the composite forming male die 2 and the engine sound insulation structural member 1. When the composite forming male die 2 or the engine sound insulation structural member 1 is assembled, the assembly supporting plate 92 is clamped with the horn mouth to facilitate positioning and installation, and it is judged whether the assembly is in place, and at the same time, the horn mouth can be installed downward to support the composite forming male die 2 or the engine sound insulation structural member 1.

[0054] The clamping and rotating device for manufacturing the engine sound insulation structural member of the aircraft of the embodiment further comprises a paving and pasting supporting seat 6, which is a prism type frame structure welded by square steel; the center of the table surface of the paving and pasting supporting seat 6 is provided with a rotating shaft hole 61, which is used for inserting and vertically installing the rotating main shaft 3, so as to facilitate the paving and pasting of the panel 11 and the back plate 12 of the engine sound insulation structural member 1.

[0055] The clamping and rotating device for manufacturing the engine sound insulation structural member of the aircraft of the embodiment further comprises a paving and pasting supporting seat 6, which is a prism type frame structure welded by square steel; the center of the table surface of the paving and pasting supporting seat 6 is provided with a rotating shaft hole 61, which is used for inserting and vertically installing the rotating main shaft 3, so as to facilitate the paving and pasting of the panel 11 and the back plate 12 of the engine sound insulation structural member 1.

[0056] The method for using the clamping and rotating device for manufacturing the engine sound insulation structural member of the aircraft of the embodiment comprises the following steps: Figure 7 and Figure 8 The method for using the clamping and rotating device for manufacturing the engine sound insulation structural member of the aircraft of the embodiment comprises the following steps:

[0057] 1) Assembling the composite forming male mold 2: adjust the handle 523 of the rotating clamping plate mechanism, move the clamping plate body 51 inward along the axis of the rotating main shaft 3, i.e. move the clamping plate body 51 towards the axis, so as to fit the composite forming male mold 2 on the clamping plate mechanism of the rotating main shaft 3; then rotate the handle 523 of the clamping plate mechanism in the opposite direction, move the clamping plate body 51 outward along the normal direction of the rotating main shaft 3, clamp the composite forming male mold 2; and insert the rotating main shaft 3 vertically into the rotating shaft hole 61 of the laying support seat 6, so that the composite forming male mold 2 is in a vertical state. It is emphasized that when assembling the composite forming male mold, the assembly support plate 92 can be assembled on the assembly support plate seat 91 first, then the rotating main shaft 3 is inserted vertically into the rotating shaft hole 61 of the laying support seat 6, and the composite forming male mold 2 is assembled, with the trumpet mouth of the composite forming male mold 2 placed downward; or the rotating main shaft 3 is inserted vertically into the rotating shaft hole 61 of the laying support seat 6 first, then the composite forming male mold 2 is fitted, and finally the assembly support plate 92 is installed, with the trumpet mouth of the composite forming male mold 2 placed upward or downward. It is preferred that the trumpet mouth is placed downward, which is convenient for assembly and positioning.

[0058] 2) Adjusting the surface of the composite forming male mold: adjust the position of the clamping plate according to the measurement results, adjust the moving distance of the clamping plate body 51, until the surface of the composite forming male mold 2 meets the design tolerance requirements, and lock the surface state of the composite forming male mold 2 through the clamping plate positioning pin 8;

[0059] 3) Panel laying: lay the panel 11 material of the prepared engine sound insulation structural part 1 on the locked surface of the composite forming male mold 2 according to the requirements;

[0060] 4) Honeycomb filling: after the panel 11 of the engine sound insulation structural part 1 is laid, remove the laying support seat 6; then place the entire device horizontally or at an angle, install it on the rotating support seat 7; rotate the rotating main shaft 3, and position the composite forming male mold 2 at a certain posture through the rotating positioning pin 73 for honeycomb 13 filling;

[0061] 5) Laying back plate: after the honeycomb 13 is filled, remove the entire device from the rotating support seat 7, insert the rotating main shaft 3 vertically into the rotating shaft hole 61 of the laying support seat 6 again, so that it is in a vertical state; then lay the back plate 12 material of the prepared engine sound insulation structural part 1 on the filled honeycomb 13 according to the requirements;

[0062] 6) forming and drilling: after the back plate 12 is laid, it is cured and formed according to the requirements; after the curing and forming, the forming mold is removed, the engine sound insulation structure 1 obtained by curing and forming is sleeved on the clamping plate mechanism in the manner of step 1, and the profile of the engine sound insulation structure 1 is adjusted to meet the design requirements in the manner of step 2; then the whole device is installed on the rotating support seat 7, the rotating main shaft 3 is rotated, and the engine sound insulation structure 1 is positioned in a certain posture by the rotating positioning pin 73 for drilling operation.

[0063] The clamping and rotating device for the aircraft engine sound insulation structure provided by the application can fix the profile of the composite forming mold of the aircraft engine sound insulation structure or the profile of the aircraft engine sound insulation structure itself at the profile position required by the design, and keep a certain rigidity, so as to facilitate the laying of the panel and the back plate and the filling of the honeycomb, and facilitate the drilling operation. The functions of laying, filling and drilling of the composite parts are concentrated in one device, which reduces the cost and saves the occupied space.

[0064] In addition, the device and method of the application also have universality, and can be used for large-curvature whole-cylinder composite parts or the profile support of large-curvature composite parts, and have good practical value.

[0065] It is apparent to those skilled in the art that the application is not limited to the details of the above-described exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or essential characteristics of the application. Therefore, the embodiments should be regarded as exemplary and non-limiting, and the scope of the application is defined by the appended claims rather than the above description, and all changes falling within the meaning and range of the essential elements of the claims are intended to be included in the application. Any reference signs in the claims should not be regarded as limiting the claims involved.

[0066] In addition, it should be understood that although the present specification is described in terms of embodiments, each embodiment does not contain only one independent technical solution, and the description manner of the specification is only for the sake of clarity, and those skilled in the art should regard the specification as a whole, and the technical solutions in the embodiments can also be properly combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A clamping and rotating device for manufacturing aircraft engine acoustic lining structural parts, characterized by: It comprises a rotating main shaft (3), a plurality of groups of clamping plate mechanisms sleeved on the rotating main shaft (3), and a separately arranged rotating support seat (7); The rotating main shaft (3) is arranged along the central axis of the engine sound lining structural member (1), and its length is greater than the height of the engine sound lining structural member (1); The clamping plate mechanism comprises an annular fixing seat (4) sleeved on the rotating main shaft (3) and a plurality of clamping plate units (5) distributed on the outer edge of the annular fixing seat (4); The card board unit (5) comprises a card board body (51) and a card board adjustment assembly (52); The card plate body (51) contacts the inner surface of the composite material forming male mold (2) or the engine sound lining structural component (1), and is used to support the surface of the composite material forming male mold (2) or the engine sound lining structural component (1); The clamping plate adjustment assembly (52) is used to adjust the clamping plate body (51) to facilitate assembly and clamping of the composite forming male mold (2) and the engine acoustic lining structural component (1), and to ensure that the profiles of the composite forming male mold (2) and the engine acoustic lining structural component (1) meet design requirements; The rotating support seat (7) is used to support both ends of the rotating main shaft (3), and the rotating main shaft (3) can rotate on the rotating support seat (7), and enable the composite forming male mold (2) and the engine acoustic lining structural component (1) to maintain a required posture during the manufacturing process; The plurality of clamping plate units (5) are evenly distributed radially around the rotating main shaft (3) on the outer edge of the annular fixing seat (4); The card plate body (51) is L-shaped or T-shaped, and includes a contact portion (511) that directly contacts the inner surface of the composite forming male mold (2) or the engine acoustic lining structural component (1), and a connection portion (512) for connecting to the card plate adjustment assembly (52); The clamping plate adjustment assembly (52) comprises an adjustment seat (521) fixed on the annular fixing seat (4), an adjustment screw (522) and an adjustment handle (523); The adjusting screw (522) passes through the adjusting seat (521) and is connected to the connecting portion (512) of the clamping plate body (51); The adjusting handle (523) is used to adjust the adjusting screw (522) to drive the clamping plate body (51) to move in a normal direction perpendicular to the rotation main axis (3), clamping or releasing the composite forming male mold (2) and the engine acoustic lining structural component (1), or maintaining the molding surface thereof in the state required by the design; The clamping and rotating device also includes a paving support seat (6), which is a prism-shaped frame structure formed by welding square steel; A rotating shaft hole (61) is provided at the center of the table surface of the paving support seat (6) for inserting the rotating main shaft (3) for upright installation, thereby facilitating the paving of the face plate (11) and the back plate (12) of the engine sound lining structure (1).

2. The clamping and rotating device for manufacturing aircraft engine acoustic lining structural parts according to claim 1, characterized in that: The card plate body (51) is provided with an OPT point for detecting the matching accuracy between the card plate body (51) and the inner surface of the composite forming male mold (2) or the engine acoustic lining structural component (1); The adjusting screw (522) and the adjusting seat (521) are also provided with a card plate positioning pin hole (524), and the card plate positioning pin (8) is used to position the card plate body (51) at a certain position to maintain the surface state of the composite molding male mold (2) and the engine sound lining structural component (1).

3. The clamping and rotating device for manufacturing aircraft engine acoustic lining structural parts according to claim 2, characterized in that: The clamping plate mechanism comprises two groups, both of which are arranged in the middle of the rotating main shaft (3); the edge of the annular fixing seat (4) is also provided with an assembly support plate seat (91) of the composite forming male mold (2) or the engine acoustic lining structural member (1), which is used to install the assembly support plate (92); The assembly support plate seat (91) is spaced apart from the card plate body (51), and the assembly support plate (92) is used to position and support the horn of the composite material forming male mold (2) or the engine sound lining structural part (1); The shaping curvature of the assembly support plate (92) is consistent with the bell-mouth outward curvature of the composite forming male mold (2) and the engine sound lining structural component (1).

4. The clamping and rotating device for manufacturing aircraft engine acoustic lining structural parts according to claim 3, characterized in that: The rotating support seat (7) is used to support the fulcrums at both ends of the rotating main shaft (3), and bearing sleeves (71) are provided at corresponding positions of the bearing sleeve (71) and the rotating main shaft (3). The rotating main shaft (3) is fixed by the rotating locating pins (73) to position the composite forming male mold (2) or the engine sound lining structural component (1) in a required posture.

5. The clamping and rotating device for manufacturing aircraft engine acoustic lining structural parts according to claim 4, characterized in that: There are a plurality of rotating positioning pin holes (72) on the rotating main shaft (3) so as to position the composite forming male mold (2) and the engine acoustic lining structural component (1) in different postures.

6. The clamping and rotating device for manufacturing aircraft engine acoustic lining structural parts according to claim 5, characterized in that: A rotating handle (31) is provided at the end of the rotating main shaft (3) for facilitating rotating operation.

7. The method for using the clamping and rotating device for manufacturing an aircraft engine acoustic lining structure according to claim 6, characterized in that: The steps include: 1) Assembling the composite forming male mold (2): rotating the adjusting handle (523) of the clamping mechanism to move the clamping body (51) inwardly toward the axis of the rotating main shaft (3), so that the composite forming male mold (2) is sleeved on the clamping mechanism on the rotating main shaft (3); then rotating the adjusting handle (523) of the clamping mechanism in the opposite direction to move the clamping body (51) outwardly along the normal direction perpendicular to the rotating main shaft (3), thereby clamping the composite forming male mold (2); and vertically inserting the rotating main shaft (3) into the rotating shaft hole (61) of the paving support seat (6), so that the composite forming male mold (2) is in an upright state; 2) Adjusting the composite forming positive mold surface: adjusting the position of the card plate according to the measurement results, adjusting the moving distance of the card plate body (51), until the composite forming positive mold (2) surface meets the design tolerance requirements, and locking the composite forming positive mold (2) surface state through the card plate positioning pin (8); 3) Panel laying: Laying the prepared panel (11) material of the engine acoustic lining structure (1) on the locked composite forming male mold (2) mold surface according to requirements; 4) Honeycomb filling: After the panel (11) of the engine acoustic lining structure (1) is laid, the laying support seat (6) is removed; then the entire device is placed horizontally or tilted at a certain angle and installed on the rotating support seat (7); the rotating main shaft (3) is rotated, and the composite forming male mold (2) is positioned in a certain posture by rotating the positioning pin (73) to perform honeycomb filling (13); 5) Laying the back plate: After the honeycomb (13) is filled, the entire device is removed from the rotating support seat (7), and the rotating main shaft (3) is inserted upright into the rotating shaft hole (61) of the paving support seat (6) again, so that it is in an upright state; then the prepared back plate (12) material of the engine sound lining structure (1) is laid on the filled honeycomb (13) as required; 6) Forming and drilling: After the back plate (12) is laid, it is cured and formed as required; after curing and forming, the forming mold is removed, and the engine sound lining structure (1) obtained by curing and forming is placed on the clamping plate mechanism in the manner of step 1), and the surface of the engine sound lining structure (1) is adjusted to meet the design requirements in the manner of step 2); then the entire device is installed on the rotating support seat (7), the rotating main shaft (3) is rotated, and the engine sound lining structure (1) is positioned in a certain posture by rotating the positioning pin (73) to perform the drilling operation.

8. The method for using the clamping and rotating device for manufacturing aircraft engine acoustic lining structural parts according to claim 7, characterized in that: The assembling of the composite forming male mold in step 1) is as follows: first assembling the assembly support plate (92) on the assembly support plate seat (91), then vertically inserting the rotating spindle (3) into the rotating shaft hole (61) of the paving support seat (6) and then assembling, with the flared mouth of the composite forming male mold (2) placed downward; or first vertically inserting the rotating spindle (3) into the rotating shaft hole (61) of the paving support seat (6), then fitting the composite forming male mold (2), and finally installing the assembly support plate (92), with the flared mouth of the composite forming male mold (2) placed upward or downward.

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