Outer protection type assembly fixture for lower half part of airplane

Abstract

The utility model discloses an aircraft lower half outer protection type assembly fixture which comprises a universal fixture frame, a plurality of stand columns are arranged on the two sides of the universal fixture frame, a plurality of shape fixing clamping plates are arranged on the universal fixture frame, and the shape fixing clamping plates are arranged on the universal fixture frame. A plurality of vacuum adsorption discs are detachably arranged on the fixed shape clamping plate, pressing positioners are arranged on the stand columns at the outer side end and the end clamping plate, auxiliary positioning and guiding systems are symmetrically arranged on the inner wall of the universal type frame, a machine body external part positioner is arranged on the universal type frame, and a machine body external part positioning device is arranged on the machine body external part positioner. And a plurality of machine body external part positioners are arranged.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft manufacturing, and more specifically, it relates to an outer shape protection assembly jig for the lower part of an aircraft. Background Art

[0002] With the continuous improvement of the requirements for aircraft performance, people have put forward higher and higher requirements for the theoretical shape of aircraft, and have also paid more and more attention to the aircraft shape quality, making it meet the requirements of stable quality, high production rate, and long fatigue life. The most significant feature of the fuselage structure of a large airliner is its large size and stable and reliable aircraft performance. The aerodynamic layout of the fuselage is an important factor affecting aircraft performance, and the aerodynamic layout of the aircraft is mainly affected by the aircraft shape. The assembly accuracy of the aircraft shape largely determines the final quality, manufacturing cost, and cycle of the aircraft. This is reflected in the aircraft manufacturing and assembly technology that requires the aircraft theoretical shape to be always ensured not to exceed the tolerance during the assembly process. With the implementation of the major special project of China's C919 large aircraft, continuous progress has been made in aspects such as integrating into the international aviation industry chain and the wide and in-depth application of aircraft digital manufacturing and assembly technology. China's aircraft manufacturing and assembly technology has developed rapidly, but there is still a gap compared with foreign advanced aircraft manufacturing enterprises in the control of the aircraft theoretical shape. The control of the aircraft shape has become a bottleneck restricting China's aircraft manufacturing and assembly technology capabilities. It is extremely urgent to solve the problem of shape over-tolerance during aircraft assembly. How to design a shape protection assembly jig with stable structure, high strength and stiffness, not easy to deform, and capable of effectively protecting the shape of aircraft products is a technical problem that needs to be solved urgently by those skilled in the art. Content of the Utility Model

[0003] Aiming at the problems existing in the prior art, the utility model provides an outer shape protection assembly jig for the lower part of an aircraft to solve the technical problem mentioned in the background art of designing a shape protection assembly jig with stable structure, high strength and stiffness, not easy to deform, and capable of effectively protecting the shape of aircraft products.

[0004] To achieve the above object, the utility model provides the following technical solution: an outer shape protection assembly jig for the lower part of an aircraft, including a general jig frame. There are columns provided on both sides of the general jig frame, and a plurality of columns are provided. There are fixed shape clamping plates provided on the general jig frame, and a plurality of fixed shape clamping plates are provided. Vacuum suction cups are detachably provided on the fixed shape clamping plates, and a plurality of vacuum suction cups are provided. Pressing and positioning devices are provided on the outer side ends of the columns and the end head clamping plates. Auxiliary positioning and guiding systems are symmetrically provided on the inner wall of the general jig frame. There are body external part positioners provided on the general jig frame, and a plurality of body external part positioners are provided.

[0005] The present utility model is further configured such that the general-purpose frame is formed by welding or bolt-connecting square steel with different cross-sections, and is locally in a triangular stable structure, ensuring sufficient stiffness during use and avoiding displacement and deformation.

[0006] The present utility model is further configured such that the fixed contour clamping plate is converted from the theoretical contour of the aircraft fuselage. The fixed contour clamping plate is provided with a plurality of K-hole locators, which facilitate the positioning of the skin.

[0007] The present utility model is further configured such that the vacuum suction cup is controlled by an external vacuum air source. The vacuum suction cup is provided with an L-shaped plate, and the L-shaped plate and the fixed contour clamping plate are bolt-connected, facilitating the disassembly and assembly of the vacuum suction cup.

[0008] The present utility model is further configured such that the pressing locators are evenly distributed on the columns and end head clamping plates at both ends of the general-purpose frame, ensuring the pressing effect on the fuselage.

[0009] Compared with the prior art, the present utility model provides an external shape-preserving assembly jig for the lower half of an aircraft, having the following beneficial effects:

[0010] 1. The theoretical contour of the aircraft fuselage is converted into the surface of the fixed contour clamping plate. The general-purpose frame is located outside the fuselage skin, leaving sufficient passage for installing parts during the assembly of the lower half of the aircraft fuselage.

[0011] 2. The vacuum suction cup can maintain a vacuum state for a long time and can keep the fuselage and the jig in close contact for a long time without applying external force.

[0012] 3. The fixed jig frame is composed of general-purpose steel frames, and the number of steel frames can be increased or decreased according to specific needs to achieve modular manufacturing. The columns on both sides of the jig frame can be retracted when not in use, saving parking space.

[0013] 4. The guiding system can realize positioning and placement conveniently and quickly, has the function of absorbing energy, and can avoid hard contact.

[0014] 5. The K-hole locators are used to position the skin and fix the position of the skin on the shape-preserving jig. The external part locators of the fuselage are used to position the external fairing joint parts of the fuselage. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the preferred overall structure of an external shape-preserving assembly jig for the lower half of an aircraft;

[0016] Figure 2 It is an exploded view of the mating structure of the fixed contour clamping plate of the preferred external shape-preserving assembly jig for the lower half of an aircraft;

[0017] Figure 3Schematic diagram of a preferred clamping and positioning device structure for the outer protective assembly jig of the lower part of an aircraft

[0018] Figure 4 Schematic diagram of a preferred structure of the cooperation between a vacuum suction disc and an L-shaped plate for the outer protective assembly jig of the lower part of an aircraft

[0019] Figure 5 Schematic diagram of a preferred auxiliary positioning and guiding system structure for the outer protective assembly jig of the lower part of an aircraft

[0020] Figure 6 Schematic diagram of a preferred locator structure for external parts of the fuselage of the outer protective assembly jig of the lower part of an aircraft

[0021] In the figure: 1. General jig frame; 2. Column; 3. Fixed contour clamping plate; 4. Vacuum suction disc; 5. Clamping and positioning device; 6. Auxiliary positioning and guiding system; 7. Locator for external parts of the fuselage; 8. K-hole locator; 9. L-shaped plate Detailed implementation manners

[0022] It should be noted that, without conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The present utility model will be described in detail below with reference to the drawings and in conjunction with the embodiments

[0023] It should be pointed out that unless otherwise specified, all technical and scientific terms used in this application have the same meaning as commonly understood by those of ordinary skill in the technical field to which this application belongs

[0024] In the present utility model, unless otherwise stated, the orientations such as "upper and lower" are generally in the directions shown in the drawings, or in the vertical, perpendicular or gravitational directions; similarly, for the convenience of understanding and description, "left and right" are generally left and right as shown in the drawings; "inside and outside" refer to the inside and outside relative to the contours of the respective components, but the above orientation terms do not limit the present utility model

[0025] Please refer to Figure 1-6 , an outer protective assembly jig for the lower part of an aircraft, including a general jig frame 1, columns 2 are provided on both sides of the general jig frame 1, there are multiple columns 2, a fixed contour clamping plate 3 is provided on the general jig frame 1, there are multiple fixed contour clamping plates 3, a vacuum suction disc 4 is detachably provided on the fixed contour clamping plate 3, there are multiple vacuum suction discs 4, clamping and positioning devices 5 are provided on the outer side end columns 2 and the end head clamping plates, auxiliary positioning and guiding systems 6 are symmetrically provided on the inner wall of the general jig frame 1, and locators 7 for external parts of the fuselage are provided on the general jig frame 1, and there are multiple locators 7 for external parts of the fuselage

[0026] Please refer to Figure 1, as an implementation of the general - type frame 1: The general - type frame 1 is formed by welding or bolt - connecting square steel with different cross - sections, and part of it has a triangular stable structure.

[0027] Specifically, the general - type frame 1 has sufficient stiffness during use and does not undergo large displacement deformation.

[0028] Please refer to Figure 1 and Figure 2 , as an implementation of the fixed - shape clamping plate 3: The fixed - shape clamping plate 3 is converted from the theoretical shape of the aircraft fuselage. The fixed - shape clamping plate 3 is provided with a plurality of K - hole locators 8.

[0029] Specifically, the K - hole locator 8 is used to position the skin at each position by connecting with the DA hole of the skin.

[0030] Please refer to Figure 4 , as an implementation of the vacuum suction cup 4: The vacuum suction cup 4 is controlled by an external vacuum air source. The vacuum suction cup 4 is provided with an L - shaped plate 9, and the L - shaped plate 9 and the fixed - shape clamping plate 3 are bolt - connected.

[0031] Specifically, the L - shaped plate 9 is installed corresponding to the fixed - shape clamping plate 3, and the bolts are passed through and tightened for fixation.

[0032] Please refer to Figure 1 and Figure 3 , as an implementation of the pressing and positioning device 5: The pressing and positioning devices 5 are evenly distributed on the columns 2 at both ends of the general - type frame 1 and the end - head clamping plates.

[0033] Specifically, the pressing and positioning devices 5 are evenly distributed on the columns 2 at both ends of the general - type frame 1 and the end - head fixed - shape clamping plate 3, and are in a pressed state after the fuselage is attached to the fixed - shape clamping plate 3.

[0034] In summary, when the overall equipment is in use:

[0035] Confirm that the body external part locator 7 and the K-hole locator 8 of the general-purpose frame 1 are in the non-inflated state and in the low position. Start the auxiliary locator, slowly approach the body to the general-purpose frame 1, and adjust the conformal position through the fine-tuning bolts to make the body skin and the K-hole locator 8 aligned. Install the K-hole locating pin and start the vacuum suction cup. Open the intermediate valve to make the vacuum suction cup fit with the body, then drive down the two side columns 2 and fix them. Check the adsorption of the two side fixed profile plates 3 to the body, adjust and clamp the K-hole locator 8 at the bottom of the column 2 according to the actual situation of the body skin, release all the vacuum air sources again, start the vacuum air sources again in the order of first the middle and then the two sides, and cycle 2 times to release the assembly stress. Slowly lower the K-hole locator 8 and the body external part locator 7 in the transfer platform to make the general-purpose frame 1 and the body reach the theoretical position, make the general-purpose frame 1 fit with the body, then press and lock the compression locator 5, close the air valve, and keep the vacuum air pump connected.

[0036] The main implementation steps are as follows:

[0037] Inspection before starting work; overall hoisting; centering by the auxiliary positioning and guiding system 6; fine-tuning on the free moving device; start the K-hole locator 8 and align the K-holes; start the vacuum suction disc 4 and lower the column 2 to fix; check the adsorption situation; cycle the vacuum air source switch; the general-purpose frame 1 and the body reach the theoretical position.

[0038] In all the solutions mentioned above, for the connection between two components, welding, bolt and nut mating connection, bolt or screw connection, or other well-known connection methods can be selected according to the actual situation, which will not be elaborated one by one here. For those that involve fixed connection mentioned above, welding is preferably considered. Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An outer protective assembly jig for the lower part of an aircraft, comprising a general jig frame (1), with columns (2) provided on both sides of the general jig frame (1), and a plurality of the columns (2) are provided. Its characteristics are: The general - type frame (1) is provided with fixed - shape clamping plates (3). There are multiple fixed - shape clamping plates (3). Removably arranged on the fixed - shape clamping plates (3) are multiple vacuum suction cups (4). Pressing and positioning devices (5) are provided on the outer - side ends of the columns (2) and the end - head clamping plates. Symmetrically arranged on the inner wall of the general - type frame (1) is an auxiliary positioning and guiding system (6). The general - type frame (1) is provided with external - body - part positioners (7), and there are multiple external - body - part positioners (7).

2. The external protection and assembly jig for the lower part of an aircraft according to claim 1, characterized in that: The general - type frame (1) is formed by welding or bolt - connecting square steel with different cross - sections, and is partially in a triangular stable structure.

3. The external protection and assembly jig for the lower part of an aircraft according to claim 1, characterized in that: The fixed - shape clamping plate (3) is converted from the theoretical shape of the aircraft fuselage. The fixed - shape clamping plate (3) is provided with multiple K - hole positioners (8).

4. The external protection and assembly jig for the lower part of an aircraft according to claim 1, characterized in that: The vacuum suction cup (4) is controlled by an external vacuum air source. The vacuum suction cup (4) is provided with an L - shaped plate (9), and the L - shaped plate (9) and the fixed - shape clamping plate (3) are bolt - connected.

5. The external protective assembly jig for the lower part of an aircraft according to claim 1, characterized in that: The pressing and positioning devices (5) are evenly distributed on the columns (2) and the end - head clamping plates at both ends of the general - type frame (1).

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