Aircraft damping platform assembling device and method

Abstract

The invention belongs to the field of aeronautical manufacturing, and relates to an aircraft damping platform assembling device and method.The aircraft damping platform assembling device comprises a supporting frame, two positioning angle seats, an I-shaped seat, a positioning supporting plate and a clamp; four foot plates are arranged on the lower portion of the supporting frame and used for being connected with an aircraft floor. The upper part of the support frame is a flat plate; the two positioning angle seats are symmetrically mounted on the edge of the flat plate; the positioning supporting plate is mounted on the positioning angle seat; a plurality of laser positioning holes are formed in the positioning supporting plate; the clamp is used for fixing the damping platform bending plate on the positioning supporting plate; the I-shaped base is arranged on the positioning supporting plate in a sliding mode and used for positioning and supporting the damping platform I-shaped beam.

Description

Technical Field

[0001] The invention belongs to the field of aviation manufacturing and relates to an aircraft shock absorbing platform assembly device and method. Background Art

[0002] The aircraft shock-absorbing platform is an important component that connects the inner wall of the aircraft fuselage and various electrical cabinets inside the fuselage. Its main function is to enhance the strength of the fuselage and the connection stiffness between the fuselage and the cabinet, and can effectively reduce the vibration of the internal structure of the aircraft due to the change of flight attitude during flight. The aircraft shock-absorbing platform includes plate bending parts, plates, partitions, connectors, I-shaped profiles and other parts, and each part is provided with a surface for assembly. During assembly, the plane of the aircraft frame near the shock-absorbing platform and the axis of the long truss are used as references. The plate bending parts and the plate surfaces are first aligned, fitted, and pressed by drawing lines, and then riveted into a whole. After that, the whole assembly of the plate bending parts is riveted with the partition and I-shaped profile, and finally the shock-absorbing platform is riveted and combined with the inner wall of the fuselage through the connector to complete the assembly. Among them, a pad is arranged between the shock-absorbing platform and the inner wall of the fuselage to eliminate the gap between the surfaces. The traditional assembly method does not rely on auxiliary equipment, has a high degree of flexibility, and occupies less space on site. Therefore, it is widely used in the assembly of aircraft shock-absorbing platforms. However, as an internal auxiliary component of the fuselage, the shock-absorbing platform has not formed a precise and unified assembly method due to its own structure and the particularity of the process, resulting in large differences in the assembly results each time and difficulty in measurement. These shortcomings are increasingly difficult to meet the needs of modern aircraft manufacturing and assembly. The existing assembly method has the following disadvantages: 1. It is difficult to operate, takes a long time, and requires the cooperation of multiple people to complete; 2. The assembly accuracy is poor, and it is impossible to overcome the adverse effects of vibration during the assembly process on the assembly results; 3. The repeated alignment process is prone to damage to the finished parts, resulting in waste; 4. Under the interference of external factors, the consistency of the pod joints of each aircraft after assembly is poor, which cannot meet the requirements of later quality review and troubleshooting. Since the error of the assembly result cannot be quantified, there are certain hidden dangers. Summary of the invention

[0003] The purpose of the present invention is to overcome the shortcomings of the existing technical methods and provide an aircraft shock absorbing platform assembly device and method. Since the shock absorbing platform is composed of plate bending parts, the rigidity is not high, and the assembly is in the later stage of the aircraft assembly, and the assembly accuracy cannot be guaranteed by fixed tooling. This method and structure is based on a full understanding of the internal structure of the aircraft, and flexibly utilizes the existing internal structure of the aircraft, overcomes the problems of low assembly accuracy, poor consistency of results, and low efficiency of the aircraft shock absorbing platform, and can reduce various stresses in the assembly process of the aircraft shock absorbing platform and improve the structural rigidity.

[0004] Technical Solution

[0005] An aircraft shock absorbing platform assembly device comprises: a support frame, two positioning angle seats, a work-shaped seat, a positioning support plate, and a clamp;

[0006] The lower part of the support frame has four foot plates for connecting with the aircraft floor; the upper part of the support frame is a flat plate;

[0007] Two positioning angle seats are symmetrically installed on the edge of the flat plate;

[0008] The positioning support plate is installed on the positioning angle seat;

[0009] The positioning support plate is provided with a plurality of laser positioning holes;

[0010] The clamp is used to fix the shock-absorbing platform bent plate on the positioning bracket;

[0011] The I-shaped seat is slidably arranged on the positioning support plate to position and support the I-beam of the shock-absorbing platform.

[0012] Furthermore, each of the four foot plates of the support frame is provided with a mounting hole, which corresponds one to one with the mounting holes on the aircraft floor and is connected to the aircraft floor via positioning pins.

[0013] Furthermore, a plurality of mounting holes are provided on the upper plate of the support frame, and the positioning angle seat is connected to the support frame through positioning pins and is locked through a handle nut.

[0014] Furthermore, the positioning angle seat is in an L-shaped structure, including two mounting surfaces, namely a horizontal mounting surface and a vertical mounting surface;

[0015] The horizontal mounting surface is connected to the upper flat plate of the supporting frame, and the vertical mounting surface is connected to the positioning support plate.

[0016] Further, the positioning support plate is an L-shaped structure, including a vertical support plate and a horizontal support plate;

[0017] The vertical support plate is used to connect with the vertical mounting surface of the positioning angle seat;

[0018] There are three laser positioning holes on the horizontal support plate;

[0019] The relative position relationship between the three laser positioning holes and the four foot plate mounting holes of the support frame is known.

[0020] Furthermore, the three laser positioning holes are distributed in a triangle.

[0021] Furthermore, the vertical installation surface of the positioning angle seat, the horizontal support plate of the positioning support plate, and the upper surface of the I-shaped seat are positioning surfaces.

[0022] A method for assembling an aircraft shock absorbing platform is implemented based on the above-mentioned device, and the method comprises:

[0023] S1: Move the support frame to the assembly area and fix the support frame to the aircraft floor;

[0024] S2: Place laser positioning balls at the three laser positioning holes, collect data of the three laser positioning holes on the positioning pallet through a laser tracker, and adjust the positions of the positioning angle seat and the positioning pallet until the positions of the laser positioning holes match the theoretical positions;

[0025] S3: fit the lower surface of the I-beam of the shock-absorbing platform with the upper horizontal surface of the I-shaped seat, fit the vertical installation surface of the I-beam with the vertical installation surface of the positioning angle seat, and adjust the I-beam in the horizontal direction so that its end face is aligned with the edge of the end face of the I-shaped seat. After alignment, clamp the I-beam and the positioning angle seat with a clamp;

[0026] S4: fit the horizontal mounting surface of the damping platform bent plate with the horizontal support plate of the positioning support plate, fit the vertical mounting surface of the damping platform bent plate with the other vertical mounting surface of the I-beam, and align the end surface of the bent plate with the edge of the end surface of the positioning support plate. After alignment, clamp the bent plate, the positioning support plate and the I-beam with a clamp;

[0027] S5: Drill the mounting holes between the shock absorbing platform and the inner wall of the fuselage, and the parts of the shock absorbing platform. After drilling, connect the shock absorbing platform to the inner wall of the fuselage with rivets;

[0028] S6: Loosen the clamp, remove the positioning pin and handle nut, and make the shock absorbing platform disengage from the positioning device;

[0029] S7: Rotate the entire device 180 degrees and repeat S1 to S6 to complete the assembly of the shock absorbing platform on the other side of the fuselage.

[0030] Beneficial effects: The present invention provides an aircraft shock-absorbing platform assembly device and method, which has the following beneficial effects: (1) When the aircraft is nearly completed and separated from the fixed tooling, the introduction of the laser target ball positioning method significantly improves the assembly accuracy; (2) The aircraft left and right shock-absorbing platforms can be quickly and conveniently switched during assembly; (3) The operation difficulty is reduced and the assembly efficiency is improved. (4) Compared with the traditional line drawing assembly, it avoids the waste of parts, saves costs, and improves the success rate; (5) The entire mechanism is flexible to move and disassemble, and the transition is convenient; (6) The use of the laser target ball positioning method enables the assembly error to be quantified and the assembly result to be traceable. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The present invention includes 5 drawings, and the drawings and the descriptions of the drawings are as follows:

[0032] Figure 1 This is the structural diagram of the aircraft shock absorbing platform tooling;

[0033] Figure 2 This is the structural diagram of the bending plate of the shock absorbing platform;

[0034] Figure 3 This is the I-beam structure diagram of the shock-absorbing platform;

[0035] Figure 4 is a top view of the device;

[0036] Figure 5 Assemble the side view of the shock absorbing platform;

[0037] Among them: 01: positioning support plate, 02: I-shaped seat, 03: positioning angle seat, 04: supporting frame, 05: positioning pin, 06: handle nut, 07: clamp. DETAILED DESCRIPTION

[0038] The present invention is achieved through the following technical solutions: Figure 1 As shown, an aircraft shock absorbing platform assembly device is provided, including a positioning support plate 01, two I-shaped seats 02, two positioning angle seats 03, a supporting frame 04, a plurality of positioning pins 05, a plurality of handle nuts 06, and a plurality of clamps 07.

[0039] The support frame 04 is a frame structure, with a flat plate at the top, an aluminum square tube in the middle, and four foot plates at the bottom. Each foot plate is provided with a mounting hole, and the positions of the four foot plate mounting holes correspond to the mounting holes on the aircraft floor. The support frame 04 is connected to the aircraft floor through positioning pins 05. Several mounting holes are provided on the upper flat plate of the support frame 04. The positioning pins 05 connect the positioning angle seat 03 and the upper flat plate of the support frame 04 through the mounting holes, and are locked by the handle nut 06; the positioning angle seat 03 is an L-shaped structure, containing two mounting planes, namely the horizontal mounting plane and the vertical mounting plane. The horizontal mounting plane is connected to the upper flat plate of the support frame 04, and the vertical mounting plane will be used to position the bending plate of the shock-absorbing platform.

[0040] The positioning angle seat 03 is connected to the positioning support plate 01 by the positioning pin 05 and the handle nut 06. The positioning support plate 01 is an L-shaped structure, including a vertical mounting surface and a horizontal mounting surface. The vertical mounting surface is attached to and connected with the vertical mounting surface of the positioning angle seat 03; its horizontal mounting surface is provided with 3 laser positioning holes, which are distributed in a triangular shape. The 3-point distribution area includes the area where the shock-absorbing platform is located. The positions of the 3 laser holes maintain a positional relationship with the positions of the 4 foot plate mounting holes of the support frame 04. There are several circular weight-reducing holes on the horizontal mounting surface of the positioning support plate 01, which are convenient for the clamp 07 to clamp the positioning support plate 01 and the shock-absorbing platform. The I-shaped seat 02 fits with the upper surface of the positioning support plate and can slide on the horizontal mounting surface of the positioning support plate 01. The 3 main positioning surfaces of the entire device are: the horizontal mounting surface of the positioning support plate 01, the vertical mounting surface of the positioning angle seat 03, and the upper horizontal surface of the I-shaped seat 02.

[0041] Before assembling the shock-absorbing platform, use a laser tracker to collect the spatial three-dimensional measured data of the three laser positioning holes on the positioning pallet 01, and compare the difference between the measured data of the laser collection points of the positioning pallet 01 and the theoretical data. If the difference exceeds the allowable range, re-trim the horizontal mounting surface and the vertical mounting surface of the positioning pallet 01 until they are consistent with the theoretical data; if the data is consistent, it means that the positions of the three main positioning surfaces and the four footplate mounting holes of the support frame 04 have reached the theoretical positions, which meets the assembly requirements.

[0042] When assembling the shock-absorbing platform, first move the support frame 04 to the corresponding position on the aircraft floor. Since the aircraft floor is provided with mounting holes for assembly, adjust the position of the support frame 04 so that the four footboard mounting holes of the support frame 04 are aligned with the mounting holes of the aircraft floor and assembled and locked. Since the positioning bracket 01 and the positioning angle seat 03 have been assembled into a whole with the support frame 04, the horizontal mounting surface of the bending plate of the shock-absorbing platform and the vertical mounting surface of the I-beam are respectively fitted with the horizontal mounting surface of the positioning bracket 01 and the vertical mounting surface of the positioning angle seat 03, and the edge of the end face of the shock-absorbing platform is aligned with the edge of the positioning bracket 01, that is, the theoretical position of the shock-absorbing platform and the I-beam is achieved. Tighten the clamp 07, fix the shock-absorbing platform, drill the connection holes between the bending plate of the shock-absorbing platform and the fuselage profile and the I-beam, and then connect and fix them with rivets to complete the assembly. Loosen the clamp 07, the positioning pin 05, and the handle nut 06, and the entire device withdraws from the working area. Rotate the device 180 degrees and transfer it to the symmetrical direction of the aircraft fuselage, and continue to assemble the shock absorbing platform on the other side by matching the mounting holes on the aircraft floor at the corresponding positions.

[0043] Since the device relies on the installation holes on the left and right floors of the aircraft when completing the aircraft floor assembly, the installation holes on the left and right floors of the aircraft need to be made in advance. Since this step is implemented on a fixed assembly tool, it provides a reliable guarantee for the subsequent laser data collection and the positioning of the device.

[0044] Combined with Figure 1 And attached Figure 5 , provides an assembly positioning method and device for an aircraft shock absorbing platform that does not rely on an aircraft assembly jig, which is suitable for completing the precise positioning and assembly of the aircraft shock absorbing platform by using an optical positioning method with the aid of a laser tracker when the interior of the fuselage is completed in the later stage of aircraft assembly. The method and steps are as follows:

[0045] Step 1: Move the support frame 04 to the assembly area, align the mounting holes of the lower foot plate of the support frame 04 with the mounting holes of the aircraft floor, and connect and tighten them with the positioning pins 05 and handle nuts 06. The mounting holes on the floor have been made in advance on the fixed assembly jig, and their positions are accurate, which can be used as a reference for the subsequent assembly process. The support frame 04 has been fixedly connected with the positioning angle seat 03 and the positioning bracket 01. Before the fixed connection, the data of the three laser positioning holes on the horizontal mounting surface of the positioning bracket 01 are collected by the laser tracker, and the positions of the positioning angle seat 03 and the positioning bracket 01 are adjusted until they match the theoretical data. Therefore, the three main positioning surfaces of the entire device, namely: the horizontal mounting surface of the positioning bracket 01, the vertical mounting surface of the positioning angle seat 03, and the upper horizontal surface of the I-shaped seat 02, maintain an accurate positional relationship with the four mounting holes of the aircraft floor, thereby ensuring the accurate positioning of the device on the shock-absorbing platform.

[0046] Step 2: fit the lower surface of the I-beam of the shock-absorbing platform with the upper horizontal surface of the I-shaped seat 02, fit the vertical mounting surface of the I-beam with the vertical mounting surface of the positioning angle seat 03, and adjust the I-beam in the horizontal direction so that its end face is aligned with the edge of the end face of the I-shaped seat 02. After alignment, clamp the I-beam and the positioning angle seat 03 with a clamp;

[0047] Step 3: Fit the horizontal mounting surface of the damping platform bent plate to the horizontal mounting surface of the positioning support plate 01, fit the vertical mounting surface of the damping platform bent plate to the other vertical mounting surface of the I-beam, and align the end surface of the bent plate with the edge of the end surface of the positioning support plate 01. After alignment, clamp the bent plate, the positioning support plate 01 and the I-beam with a clamp;

[0048] Step 4: Connect the partition plate and other connecting parts to the shock-absorbing platform curved plate and I-beam, and clamp them with clamp 07 after the connection is completed;

[0049] Step 5: Drill the mounting holes between the shock absorbing platform and the inner wall of the fuselage, and the parts of the shock absorbing platform. After drilling, connect the shock absorbing platform to the inner wall of the fuselage with rivets;

[0050] Step 6: Loosen the clamp 07, remove the positioning pin 05 and the handle nut 06, and make the shock absorbing platform disengage from the positioning device;

[0051] Step 7: Rotate the entire device 180 degrees and repeat step 1 to complete the assembly of the shock-absorbing platform on the other side of the fuselage.

Claims

1. An aircraft shock absorbing platform assembly device, characterized in that: The device includes: Support frame, two positioning angle seats, work seat, positioning pallet, clamp; The lower part of the support frame has four foot plates for connection with the aircraft floor; the upper part of the support frame is a flat plate; Two positioning angle seats are symmetrically installed on the edge of the flat plate; The positioning support plate is installed on the positioning angle seat; The positioning support plate is provided with a plurality of laser positioning holes; The clamp is used to fix the shock-absorbing platform bent plate on the positioning bracket; The I-shaped seat is slidably arranged on the positioning support plate to position and support the I-beam of the shock-absorbing platform.

2. The device according to claim 1, characterized in that: Each of the four foot plates of the support frame is provided with a mounting hole, which corresponds one to one with the mounting holes on the aircraft floor and is connected to the aircraft floor through positioning pins.

3. The device according to claim 2, characterized in that: The upper plate of the support frame is provided with a plurality of mounting holes, and the positioning angle seat is connected to the support frame through positioning pins and locked through handle nuts.

4. The device according to claim 3, characterized in that: The positioning angle seat is an L-shaped structure, including two mounting surfaces, namely a horizontal mounting surface and a vertical mounting surface; The horizontal mounting surface is connected to the upper flat plate of the supporting frame, and the vertical mounting surface is connected to the positioning support plate.

5. The device according to claim 4, characterized in that: The positioning pallet is an L-shaped structure, including a vertical pallet and a horizontal pallet; The vertical support plate is used to connect with the vertical mounting surface of the positioning angle seat; There are three laser positioning holes on the horizontal support plate; The relative position relationship between the three laser positioning holes and the four foot plate mounting holes of the support frame is known.

6. The device according to claim 5, characterized in that: The three laser positioning holes are distributed in a triangle.

7. The device according to claim 6, characterized in that: The vertical mounting surface of the positioning angle seat, the horizontal support plate of the positioning support plate, and the upper surface of the I-shaped seat are the positioning surfaces.

8. A method for assembling an aircraft shock absorbing platform, implemented based on any of the above-mentioned devices, characterized in that: Methods include: S1: Move the support frame to the assembly area and fix the support frame to the aircraft floor; S2: Place laser positioning balls at the three laser positioning holes, collect data of the three laser positioning holes on the positioning pallet through a laser tracker, and adjust the positions of the positioning angle seat and the positioning pallet until the positions of the laser positioning holes match the theoretical positions; S3: fit the lower surface of the I-beam of the shock-absorbing platform with the upper horizontal surface of the I-shaped seat, fit the vertical installation surface of the I-beam with the vertical installation surface of the positioning angle seat, and adjust the I-beam in the horizontal direction so that its end face is aligned with the edge of the end face of the I-shaped seat. After alignment, clamp the I-beam and the positioning angle seat with a clamp; S4: fit the horizontal mounting surface of the damping platform bent plate with the horizontal support plate of the positioning support plate, fit the vertical mounting surface of the damping platform bent plate with the other vertical mounting surface of the I-beam, and align the end surface of the bent plate with the edge of the end surface of the positioning support plate. After alignment, clamp the bent plate, the positioning support plate and the I-beam with a clamp; S5: Drill the mounting holes between the shock absorbing platform and the inner wall of the fuselage, and the parts of the shock absorbing platform. After drilling, connect the shock absorbing platform to the inner wall of the fuselage with rivets; S6: Loosen the clamp, remove the positioning pin and handle nut, and make the shock absorbing platform disengage from the positioning device; S7: Rotate the entire device 180 degrees and repeat S1 to S6 to complete the assembly of the shock absorbing platform on the other side of the fuselage.

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