Multi-material composite clamping device

Abstract

The utility model discloses a multi-material composite clamping device, which relates to the technical field of aircrafts and comprises a driving plate, a main clamping component is fixedly mounted on the inner wall of the driving plate, a top fitting component is fixedly mounted at the end part of the main clamping component and comprises a pressing plate fixedly mounted at the end part of the main clamping component, and the pressing plate is fixedly mounted at the end part of the main clamping component. A fixing rod is fixedly mounted on the side wall of the pressing plate, a fixing frame is slidably mounted on the outer wall of the fixing rod, and a rack is slidably mounted on the inner wall of the fixing frame; according to the device, in the top attaching assembly and the bottom attaching assembly, the positions of the two abutting columns can be automatically and synchronously adjusted according to the radian and the curved surface form of the surface of the wing, the two abutting columns finally abut against the surface of the wing tightly, and through the meshing transmission design of a gear rod, the two abutting columns are driven by the same gear rod in a coordinated mode; the clamping force is uniformly distributed on a contact area on the surface of the wing, so that the condition that the local stress is too large or too small is effectively avoided.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft, concretely is a multi -material composite clamping device. BACKGROUND

[0002] In the field of aviation manufacturing and maintenance, the clamping operation of the wing of the small manned aircraft is the key step in many process links, the wing of the aircraft is one of the core components of the flight performance and safety of the aircraft, and the manufacturing and maintenance process has extremely strict requirements on precision and quality, different materials are increasingly widely used in the manufacture of the wing of the aircraft, for example, aluminum alloy, carbon fiber composite material and the like, these materials have unique physical and mechanical properties, which bring many advantages such as light weight and high strength to the wing, but at the same time, they also bring unprecedented challenges to the clamping operation of the wing.

[0003] The surface of the wing of the small manned aircraft is not a plane structure in the traditional sense, but has a specific curvature and a complex curved surface form, and this non-planar surface feature is an important consideration factor for the aerodynamic design of the aircraft, aiming to optimize the aerodynamic performance in the flight process, reduce the flight resistance and improve the flight efficiency.

[0004] The clamping plate and the clamping arm of most ordinary clamping devices adopt a rotary connection mode, the original intention is to enable the clamping plate to flexibly adapt to the curvature of the wing surface, and the clamping plate is tightly attached to the wing surface through rotation.

[0005] However, in the actual operation process, especially in the complex environment of aircraft manufacturing and maintenance, the clamping device will inevitably be affected by various vibration sources, the clamping plate with rotary connection is prone to swing due to the lack of effective constraint mechanism, which causes additional and irregular force to be applied to the wing surface during clamping and attachment, and the surface hardness and damage resistance of different materials used for the wing of the aircraft are different, the carbon fiber composite material has high strength characteristics, but its surface is relatively fragile, and the local concentrated force is limited; when the aluminum alloy material is subjected to uneven force, surface scratches, deformation and even internal structure damage may occur, the damage caused by the swing of the clamping plate will reduce the flight performance, and even pose a potential threat to flight safety.

[0006] Therefore, the present application is proposed. UTILITY MODEL CONTENTS

[0007] The utility model aims at providing a multi -material composite clamping device to solve the problems in the above background art.

[0008] The utility model provides a kind of multi-material composite clamping device to solve the above technical problems, including drive plate, the main clamping component is fixedly installed in the drive plate inner wall, the top bonding assembly is fixedly installed in the main clamping component end, the top bonding assembly includes the pressing plate fixedly installed in the main clamping component end, the fixed rod is fixedly installed in the pressing plate side wall, the fixed frame is slidably installed in the fixed rod outer wall, the rack is slidably installed in the fixed frame inner wall, the abutment post is fixedly installed in the rack end, the gear lever is engagedly connected with the rack outer wall, another rack is engagedly connected with the gear lever side away from the rack, the gear lever center is rotatably connected with the fixed rod end inner wall.

[0009] Further, the main clamping component includes a pull rod threadedly installed on the outer wall of the screw rod, a first connecting rod rotatably installed at the end of the pull rod, a second connecting rod rotatably installed at the end of the first connecting rod, a clamping arm rotatably installed at the end of the second connecting rod, a support rod rotatably installed in the inner wall of the fixed plate, and the end of the support rod is rotatably connected with the inner wall of the end of the clamping arm away from the third connecting rod.

[0010] Further, the drive plate includes a fixed plate, a motor fixedly installed in the inner wall of the fixed plate, and a screw rod fixedly installed at the driving end of the motor and threadedly connected with the main clamping component.

[0011] Further, a spring is fixedly connected with the end of the side wall of the pressing plate, the end of the spring is fixedly connected with the side wall of the fixed frame, a damper is arranged in the inner wall of the spring, a rubber sleeve is sleeved on the outer wall of the abutment post, and an anti-slip pattern is formed on the surface of the rubber sleeve.

[0012] Further, a sliding column is fixedly installed on the side wall of the rack, and the outer wall of the sliding column is slidably connected with the inner wall of the fixed frame.

[0013] Further, a secondary clamping component is rotatably installed at the end of the pull rod away from the first connecting rod, the secondary clamping component has the same structure as the main clamping component, a bottom bonding assembly is fixedly installed at the end of the secondary clamping component, and the internal structure of the bottom bonding assembly is the same as that of the top bonding assembly.

[0014] Compared with the prior art, the utility model has the following beneficial effects:

[0015] 1. In the top bonding assembly and the bottom bonding assembly, the two abutment posts can automatically and synchronously adjust the position according to the curvature and curved surface of the wing surface, and finally tightly abut the wing surface. Through the meshing transmission design of the gear lever, the two abutment posts are driven by the same gear lever, and the abutting action is completed synchronously, so that the clamping force is evenly distributed in the contact area of the wing surface, effectively avoiding the situation that the local force is too large or too small, greatly reducing the pressure concentration on the wing surface, thereby avoiding damage to the wing surface, and ensuring the flight performance and flight safety of the aircraft wing.

[0016] 2, the motor drives the screw rod to rotate, the main clamping assembly converts the rotary motion of the screw rod into linear motion along the axial direction by means of the helix angle of the screw thread and friction, when the motor stops running, the screw rod plays a role by virtue of its self-locking characteristics, ensures the stability and safety of the clamping process, and avoids clamping failure or wing damage caused by displacement. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is a front structure schematic view of a multi-material composite clamping device;

[0018] Figure 2 It is an enlarged structure schematic view of a fitting assembly of a multi-material composite clamping device;

[0019] Figure 3 It is an internal structure schematic view of a fitting assembly of a multi-material composite clamping device;

[0020] Figure 4 It is an internal structure schematic view of a clamping assembly of a multi-material composite clamping device;

[0021] Figure 5 It is an enlarged structure schematic view of a rack of a multi-material composite clamping device.

[0022] In the figure: 1, drive plate; 101, fixed plate; 102, motor; 103, screw rod;

[0023] 2, main clamping assembly; 201, pull rod; 202, connecting rod one; 203, connecting rod two; 204, connecting rod three; 205, support rod; 206, clamping arm;

[0024] 3, top fitting assembly; 301, pressing plate; 302, spring; 303, damper; 304, fixed rod; 305, fixed frame; 306, abutment column; 307, gear rod; 308, rack; 309, sliding column;

[0025] 4, auxiliary clamping assembly;

[0026] 5, bottom fitting assembly. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0028] Please refer to Figure 1 -

[0029] Figure 5 The utility model provides a technical scheme: a multi -material composite clamping device, including the main clamping component 2 end that drive board 1 inner wall fixed mounting is equipped with top adhesion component 3, and top adhesion component 3 is with the fixed mounting pressure plate 301 at the end of main clamping component 2 base body, and the fixed rod 304 is fixed on the lateral wall of pressure plate 301, and the fixed frame 305 is slidably installed on the outer wall of fixed rod 304, and the two racks 308 are slidably installed on the inner wall of fixed frame 305, and the abutment 306 is fixed on the end of rack 308, and the gear bar 307 that is rotatably connected with the end inner wall of fixed rod 304 at the center is used to realize meshing transmission to the two racks 308. When main clamping component 2 continuously moves and drives top adhesion component 3 to approach the aircraft wing, if the abutment 306 of one end of rack 308 first contacts the surface of the wing, the rack 308 stops moving due to the obstruction of the wing, but the continuous driving of main clamping component 2 will cause pressure plate 301 to exert pressure on fixed rod 304, and then push fixed frame 305 to continue moving. At this time, under the meshing transmission effect of gear bar 307, the originally stationary rack 308 will transmit power to the gear bar 307 engaged with it, and the gear bar 307 will then drive the rack 308 on the other side to move until the abutment 306 at the end of the rack 308 also contacts the surface of the wing. Through this ingenious transmission design, the two abutments 306 can automatically and synchronously adjust their positions according to the curvature and curved surface of the wing surface, and finally tightly abut against the wing surface. In this process, since the movement of the two abutments 306 is coordinated by the same gear bar 307, they can accurately and synchronously complete the abutting action, so that the clamping force is evenly distributed on the contact area of the wing surface, effectively avoiding the situation of excessive or insufficient local stress, greatly reducing the pressure concentration on the wing surface, and thus providing stable and damage-free clamping protection for the aircraft wing.

[0030] Please refer to Figure 4 The utility model provides a technical scheme: a multi -material composite clamping device, drive board 1 includes fixed plate 101, and the inner wall is installed motor 102, and the drive end of motor 102 is fixedly connected with screw rod 103, and the synchronous rotation of screw rod 103 is driven through the drive end, when screw rod 103 rotates under the driving of motor 102, main clamping component 2 converts the rotational motion of screw rod 103 into linear motion along the axial direction by the helix angle of thread and friction, when motor 102 stops running, screw rod 103 plays a role by its thread self-locking characteristic, ensures the stability and safety of clamping process, avoids the clamping failure or wing damage caused by displacement.

[0031] Please refer to Figure 4The utility model provides a kind of technical scheme: a multi-material composite clamping device, including main clamping component 2 with screw 103 as drive axis, when screw 103 rotates under the drive of motor 102, pull rod 201 moves along axial steady straight line, is transmitted by the rotary connection of its end portion connecting rod one 202, make connecting rod one 202 generate swing action, connecting rod one 202 conduction swing torque to connecting rod two 203 connected with it, drive connecting rod two 203 synchronous movement, further through the rotary connection of connecting rod two 203 end portion and clamping arm 206, linear driving force is converted into the rotary motion of clamping arm 206 around the end portion of support rod 205, in this process, one end of support rod 205 is firmly fixed in the inner wall of fixed plate 101, the other end is rotatably connected with the inner wall of one end of clamping arm 206 away from connecting rod three 204, and clamping arm 206, connecting rod two 203 jointly form a dynamically stable triangular support structure, when clamping arm 206 is subjected to external force from wing during clamping, the triangular force system quickly responds, and the external force is dispersed to the entire structural framework through support rod 205, to avoid excessive concentration of local stress. In addition, the end of pull rod 201 away from connecting rod one 202 is also rotatably installed with auxiliary clamping component 4, and the auxiliary clamping component 4 adopts the same structure design as the main clamping component 2, and the symmetrical layout further enhances the balance and synergy of the overall clamping device, providing double protection for accurate clamping under complex working conditions.

[0032] Please refer to Figure 2 、 Figure 3 The utility model provides a kind of technical scheme: a multi-material composite clamping device, including the elastic connection system that spring 302 is built between the side wall end portion of pressing plate 301 and the side wall of fixed frame 305, and the dynamic buffer system formed by damper 303 nested in the inner wall of spring 302, when pressing plate 301 is subjected to displacement by external force impact, spring 302 occurs elastic deformation in the process of stretching or compression, and its internal metal spiral structure stores a large amount of elastic potential energy due to the change of intermolecular force, when external force is removed, spring 302 releases elastic potential energy based on Hooke's law, and its deformation recovery force is converted into linear driving force to pressing plate 301, drives pressing plate 301 to rebound to initial position with initial velocity v0, at this time, the hydraulic oil damping medium filled in the inner wall of spring 302 nested damper 303, the vibration amplitude of pressing plate 301 is exponentially attenuated, under the synergistic effect of spring 302 and damper 303, the resetting process of pressing plate 301 is converted from free vibration into forced damped vibration, and its displacement time curve is changed from the damped oscillation of underdamped system to the non-oscillating regression of critical damping or overdamped system, to ensure the rapid response capability of pressing plate 301 within 0.2-0.5 seconds after the disappearance of external force, and reduce the reset impact force to 15%-30% of the original value by damping energy consumption, to improve the dynamic stability and reliability of mechanical system.

[0033] Please refer toFigure 1 The utility model provides a technical scheme: a multi -material composite clamping device, including the fixed installation of bottom laminating component 5 in the end of vice clamping component 4, bottom laminating component 5 and top laminating component 3 internal structure are same, and top laminating component 3 and bottom laminating component 5 can respectively laminating wing upper surface streamline convex and lower surface reinforcing rib recess.

[0034] Please refer to Figure 5 The utility model provides a technical scheme: a multi -material composite clamping device, including the fixed installation of bottom laminating component 5 in the end of vice clamping component 4, bottom laminating component 5 and top laminating component 3 internal structure are same, and top laminating component 3 and bottom laminating component 5 can respectively laminating wing upper surface streamline convex and lower surface reinforcing rib recess.

[0035] Working principle: when needing to clamp the wing of small manned aircraft, start the motor 102 fixedly installed in the inner wall of fixed plate 101, the driving end of motor 102 starts to rotate, drives the synchronous rotation of the fixed connection of screw rod 103, because the pull rod 201 in main clamping component 2 is connected with the outer wall of screw rod 103 by screw thread, under the rotation of screw rod 103, the pull rod 201 starts to move along the axial direction of screw rod 103. The connecting rod one 202 rotationally installed at the end of pull rod 201 moves, in turn drives the movement of connecting rod two 203, and connecting rod two 203 drives the rotation of clamping arm 206 around the end of support rod 205, so that clamping arm 206 approaches the wing direction, and in the movement of pull rod 201, vice clamping component 4 also synchronously carries out the similar power transmission and movement process with main clamping component 2, approaches the wing from the bottom, cooperates with main clamping component 2 to complete the preliminary clamping of the wing, and top laminating component 3 is fixedly installed at the end of main clamping component 2, when the abutting column 306 at the end of one rack 308 contacts the surface of aircraft wing, because main clamping component 2 and vice clamping component 4 still continuously move relatively, the pressing plate 301 will continuously exert pressure on the fixed rod 304, and the fixed rod 304 fixedly installed on the side wall of pressing plate 301 is pushed to move the fixed frame 305 to the wing direction under the action of pressure. At this time, the rack 308 slidingly installed in the inner wall of fixed frame 305 abuts against the surface of wing, and the gear rod 307 starts to rotate, drives the other end of the tooth peak to mesh and drive the other rack 308 to move, until the abutting column 306 of the other rack 308 also abuts against the surface of wing, in the process, the first rack 308 no longer moves, and the two abutting columns 306 automatically adjust the position according to the arc and curved surface of the surface of wing, to ensure that the surface of wing is closely laminated, and the clamping force is uniformly distributed.

[0036] The above merely illustrates the embodiments of the present application, and does not limit the patent scope of the present application, and any equivalent structure or equivalent process transformation, or direct or indirect application in other related technical fields, which are made according to the content of the present application specification and drawings, are also included in the patent protection scope of the present application.

Claims

1. A multi-material composite clamping device comprising a drive plate (1), characterized in that: The inner wall of the driving plate (1) is fixedly installed with a main clamping assembly (2), the end of the main clamping assembly (2) is fixedly installed with a top fitting assembly (3), the top fitting assembly (3) comprises a pressing plate (301) fixedly installed at the end of the main clamping assembly (2), the side wall of the pressing plate (301) is fixedly installed with a fixed rod (304), the outer wall of the fixed rod (304) is slidably installed with a fixed frame (305), the inner wall of the fixed frame (305) is slidably installed with a rack (308), the end of the rack (308) is fixedly installed with an abutting column (306), the outer wall of the rack (308) is meshingly connected with a gear rod (307), the side, away from the rack (308), of the gear rod (307) is meshingly connected with another rack (308), and the center of the gear rod (307) is rotationally connected with the inner wall of the end of the fixed rod (304).

2. A multi-material composite clamping device as claimed in claim 1, wherein: The driving plate (1) comprises a fixed plate (101), the inner wall of the fixed plate (101) is fixedly installed with a motor (102), the driving end of the motor (102) is fixedly installed with a screw rod (103), and the outer wall of the screw rod (103) is threadedly connected with the main clamping assembly (2).

3. A multi-material composite clamping device as claimed in claim 2, wherein: The main clamping assembly (2) comprises a pull rod (201) threadedly installed on the outer wall of the screw rod (103), the end of the pull rod (201) is rotationally installed with a connecting rod one (202), the end of the connecting rod one (202) is rotationally installed with a connecting rod two (203), the end of the connecting rod two (203) is rotationally installed with a clamping arm (206), the inner wall of the fixed plate (101) is rotationally installed with a supporting rod (205), and the end of the supporting rod (205) is rotationally connected with the inner wall of the end of the clamping arm (206), away from the connecting rod three (204).

4. A multi-material composite clamping device as claimed in claim 3, wherein: The end, away from the connecting rod one (202), of the pull rod (201) is rotationally installed with a secondary clamping assembly (4), and the secondary clamping assembly (4) is identical in structure to the main clamping assembly (2).

5. A multi-material composite clamping device as claimed in claim 4, wherein: The side wall end of the pressing plate (301) is fixedly connected with a spring (302), the end of the spring (302) is fixedly connected with the side wall of the fixed frame (305), and the inner wall of the spring (302) is provided with a damper (303).

6. A multi-material composite clamping device as claimed in claim 5, wherein: The end of the secondary clamping assembly (4) is fixedly installed with a bottom fitting assembly (5), and the bottom fitting assembly (5) is identical in internal structure to the top fitting assembly (3).

7. A multi-material composite clamping device as claimed in claim 6, wherein: The side wall of the rack (308) is fixedly installed with a sliding column (309), and the outer wall of the sliding column (309) is slidably connected with the inner wall of the fixed frame (305).

8. A multi-material composite clamping device as claimed in claim 7, wherein: The outer wall of the abutting column (306) is sleeved with a rubber sleeve, and an anti-skid line is formed on the surface of the rubber sleeve.

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