Aircraft bulkhead positioning device

Abstract

The utility model belongs to the technical field of aircraft manufacturing and assembling, and discloses an aircraft bulkhead positioning device which comprises a base, a bent plate, a plurality of supporting pieces and a plurality of clamping mechanisms. A plurality of strip-shaped grooves are formed in the base, the shapes of the different strip-shaped grooves are different, and the shape of each strip-shaped groove corresponds to the shape of one partition frame. And the bent plate can be inserted into any strip-shaped groove. The multiple supporting pieces are sequentially arranged on the base and abut against the bent plate, adsorption holes are formed in the supporting pieces, and the partition frame is tightly pressed on the supporting pieces through the adsorption holes. The clamping mechanism is detachably connected to the base and clamps the base and the supporting piece. According to the positioning tool, various bulkheads can be positioned, the production quantity of the tool is reduced, the manufacturing cost is reduced, the designability and interchangeability of the positioning device are improved, the positioning tool can be built at any time during use and can be disassembled and stored after use, and the storage space is saved; the supporting piece can be produced and managed in a standardized mode, and replacement and maintenance cost in later use can be reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to aircraft manufacturing assembly technical field especially, relate to a kind of aircraft bulkhead positioning device. BACKGROUND

[0002] Airplane frame assembly is mainly composed of machine edge strip, frame web, reinforcing profile and machine joint, and frame assembly is one of the main skeleton structural components of aircraft, and is the key load-bearing component and structural component in the whole machine structure, and plays an important role in the strength of the whole machine. The frame assembly is numerous, and the outline of various frame assemblies is similar. The size radius of different sections is slightly different. When positioning and processing, different radius bulkheads need to be distinguished and processed.

[0003] Currently, for the positioning of frame parts machining, metal hard tooling is mostly used, that is, a set of matching machining positioning tooling is manufactured according to each type of bulkhead part, to ensure the positioning accuracy and machining accuracy of the frame part. Therefore, a large number of positioning toolings with similar shape and structure are needed, which not only increases the manufacturing cost of tooling, but also increases the management cost due to the storage and protection of tooling, which brings a huge burden to production.

[0004] Therefore, there is an urgent need for an aircraft bulkhead positioning device to solve the above problems. UTILITY MODEL CONTENT

[0005] The utility model aims to provide an aircraft bulkhead positioning device that can position bulkheads of various curved shapes and save production and management costs of positioning tooling.

[0006] To achieve this purpose, the utility model adopts the following technical solutions:

[0007] An aircraft bulkhead positioning device is provided, comprising:

[0008] A base is provided with a plurality of strip-shaped grooves, and the shapes of different strip-shaped grooves are different. The shape of each strip-shaped groove corresponds to the shape of a bulkhead.

[0009] A bent plate can be inserted into any strip-shaped groove.

[0010] A plurality of support members are arranged in sequence on the base and abut against the bent plate. The support members are provided with adsorption holes that press the bulkhead against the support members.

[0011] A plurality of clamping mechanisms are detachably connected to the base. The clamping mechanisms clamp the base and the support members.

[0012] As an alternative of the aircraft partition frame positioning device, the detection assembly is detachably connected to the base, and the detection assembly presses the partition frame on the support against the bent plate.

[0013] As an alternative of the aircraft partition frame positioning device, the detection assembly comprises a lifting piece and a sensing pressure head, the lifting piece is connected to the base, and the sensing pressure head is movably connected to the lifting piece.

[0014] As an alternative of the aircraft partition frame positioning device, the detection assembly further comprises a bracket and a moving piece, the bracket is fixed to the lifting piece, the moving piece is movably connected to the bracket, and the sensing pressure head is connected to one end of the moving piece close to the bent plate.

[0015] As an alternative of the aircraft partition frame positioning device, the detection assembly further comprises a display element, and the display element is signal-connected with the sensing pressure head.

[0016] As an alternative of the aircraft partition frame positioning device, the clamping mechanism comprises a pressing piece and a connecting bolt, one end of the pressing piece is connected to the base, and the other end of the pressing piece is pressed against the support, a threaded hole is arranged on the base, and the connecting bolt is threadedly connected with the threaded hole and the pressing piece.

[0017] As an alternative of the aircraft partition frame positioning device, the pressing piece comprises a base and a pressing part, the base is connected to the base, one end of the pressing part is connected to the base, and the other end of the pressing part is pressed against the support, the pressing part is provided with a through hole, and the connecting bolt is arranged in the through hole.

[0018] As an alternative of the aircraft partition frame positioning device, the clamping mechanism further comprises a gasket, and the gasket is arranged between the pressing piece and the support.

[0019] As an alternative of the aircraft partition frame positioning device, at least two top surfaces of the supports are provided with avoiding grooves.

[0020] As an alternative of the aircraft partition frame positioning device, the support is provided with a weight-reducing hole.

[0021] The beneficial effects of the present application are as follows:

[0022] This invention provides an aircraft bulkhead positioning device. For bulkheads of different shapes and profiles, multiple strip grooves matching the curvature of the bulkhead's arc surface are set on the base. When positioning a bulkhead, a bent plate is bent and inserted into the corresponding strip groove, forming an abutment surface identical to the bulkhead's shape. Several support members are placed on the base, arranged side-by-side and sequentially abutting against the abutment surface. A clamping mechanism then fixes all support members to the base. At this point, the tops of the multiple support members form a support surface matching the bending shape of the bent plate. The bulkhead is placed on the support members, with its arc surface abutting against the bent plate. The bulkhead is pressed against the top surface of the support members through suction holes, thus achieving the positioning and clamping of the bulkhead. This aircraft bulkhead positioning device, by machining multiple differently shaped grooves on the base, allows the bending plate to be bent into different shapes. Furthermore, by changing the number and arrangement of the support components, it can be used for positioning and clamping bulkhead parts with various curvature shapes. This reduces the number of tooling components required, lowers manufacturing costs, and improves the designability and interchangeability of the positioning device, facilitating the design and processing of various bulkheads during the R&D phase. It can be assembled at any time during use and disassembled and stored after use, saving storage space. The standardized production and management of multiple support components simplifies the production process and reduces replacement and maintenance costs in later use. Attached Figure Description

[0023] Fig. 1 This is a structural schematic diagram of the aircraft bulkhead positioning device provided by this utility model;

[0024] Fig. 2 This is a top view of the base of the aircraft bulkhead positioning device provided by this utility model;

[0025] Fig. 3 This is a structural schematic diagram of the support component and clamping mechanism of the aircraft bulkhead positioning device provided by this utility model;

[0026] Fig. 4 This is a schematic diagram of the detection component of the aircraft bulkhead positioning device provided by this utility model.

[0027] In the picture:

[0028] 100. Base; 110. Slot; 120. Threaded hole;

[0029] 200. Bend plate; 210. Abutment surface;

[0030] 300. Support component; 310. Adsorption hole; 320. Weight reduction hole;

[0031] 400 Clamping mechanism; 410 Pressing element; 411 Base; 412 Pressing part; 413 Through hole; 420 Connecting bolt; 430 Washer;

[0032] 500, detection assembly; 510, lifting member; 520, sensing pressure head; 530, bracket; 540, moving member; 550, display element. DETAILED DESCRIPTION

[0033] The utility model will be described in further detail below in combination with the drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the utility model, and not limit the utility model. In addition, it should be noted that, in order to facilitate the description, only the part related to the utility model is shown in the drawings, not all structures.

[0034] In the description of the utility model, unless otherwise explicitly specified and limited, the terms "connected", "connected", "fixed" should be understood broadly, for example, it can be fixedly connected, or detachably connected, or integrated, it can be mechanically connected, or electrically connected, it can be directly connected, or indirectly connected through intermediate medium, it can be the internal communication of two elements or the interaction relationship of two elements. For ordinary skilled in the art, the specific meaning of the above terms in the utility model can be understood according to the specific circumstances.

[0035] In the utility model, unless otherwise explicitly specified and limited, the first feature is "on" or "below" the second feature, which can include that the first and second features are in direct contact, or the first and second features are not in direct contact but are in contact through another feature between them. Moreover, the first feature "on", "above" and "above" the second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature "below", "below" and "below" the second feature includes that the first feature is directly below and obliquely below the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature.

[0036] In the description of the embodiment, the terms "up", "down", "right", etc. orientation or position relationship is based on the orientation or position relationship shown in the drawings, only for the convenience of description and simplification operation, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, therefore it cannot be understood as a limitation on the utility model. In addition, the terms "first", "second" are only used to distinguish in the description, and have no special meaning.

[0037] As Figs. 1 to 4As shown, the aircraft frame positioning device of the embodiment comprises a base 100, a bending plate 200, a plurality of support members 300 and a plurality of clamping mechanisms 400. The base 100 is provided with a plurality of strip-shaped grooves 110, different strip-shaped grooves 110 have different shapes, and the shape of each strip-shaped groove 110 corresponds to the shape of one type of frame. The bending plate 200 can be inserted into any strip-shaped groove 110. The plurality of support members 300 are arranged in sequence on the base 100 and abut the bending plate 200, and the support member 300 is provided with an adsorption hole 310 that presses the frame against the support member 300. The clamping mechanism 400 is detachably connected to the base 100, and the clamping mechanism 400 clamps the base 100 and the support member 300.

[0038] Based on the above design, the aircraft frame positioning device is provided with a plurality of strip-shaped grooves 110 on the base 100 that match the curvature of the arc surface of the frame according to different shape profiles of the frame. When positioning a type of frame is needed, the bending plate 200 is bent and inserted into the corresponding strip-shaped groove 110, and the bending plate 200 can form an abutting surface 210 that is the same shape as the frame. After the plurality of support members 300 are placed on the base 100 and arranged side by side and abut the abutting surface 210 in sequence, the clamping mechanism 400 is used to fix all the support members 300 on the base 100, and at this time the top of the plurality of support members 300 can form a support surface that matches the bending shape of the bending plate 200. The frame is placed on the support member 300 and the arc surface of the frame abuts the bending plate 200, and the frame is pressed against the top surface of the support member 300 through the adsorption hole 310, so that the positioning and clamping of the frame is realized.

[0039] It can be understood that by machining a plurality of strip-shaped grooves 110 of different shapes on the base 100, the bending plate 200 can be bent to form different shapes, and by changing the number and arrangement of the support members 300, the positioning and clamping of frame parts of various curvature shapes can be achieved, so that one positioning tool can be used to position multiple frames, reducing the number of tooling production and manufacturing costs, improving the designability and interchangeability of the positioning device, and facilitating the design and processing of multiple frames in the research and development stage. The positioning tool can be built at any time during use and can be disassembled and stored after use, saving storage space. The plurality of support members 300 can be standardized in production and management, which is beneficial to simplify the production process and reduce the replacement and maintenance costs in the later stage.

[0040] As preferred, the flatness of the upper and lower planes of the base 100 is required to be within 0.01mm to ensure the stability of positioning. The centers of the plurality of strip-shaped grooves 110 intersect at a point, which concentrates the strip-shaped grooves 110 in the middle of the base 100, so that the clamping mechanism 400 has enough installation position when positioning the support 300. Since the bending plate 200 is often disassembled, the bending plate 200 is arranged in clearance fit with the strip-shaped grooves 110, which facilitates the disassembly and installation of the bending plate 200. In addition, the height of the bending plate 200 is higher than the height of the support 300, so that the spacer frame placed on the support 300 can abut against the bending plate, ensuring the accuracy of positioning.

[0041] Optionally, the support 300 is provided with a weight-reducing hole 320, which is located in the middle of the support 300, so that the support 300 forms an annular structure, which reduces the weight of the support 300 and facilitates the handheld of the support 300 and improves the convenience of moving the support 300.

[0042] Further, the support 300 is also connected with an air suction pipe 330, one end of which is in communication with the adsorption hole 310, and the other end is in communication with an external air extraction device, so as to realize the extraction of air in the adsorption hole 310.

[0043] In the embodiment, the frame of the support 300 is arranged in a straight line type, so that when the support 300 abuts against the bending plate 200, it can only abut against two frames, which reduces the shape error caused by the uneven surface of the support 300 and the bending plate 200, and further improves the accuracy of positioning.

[0044] Optionally, at least two supports 300 are provided with a clearance groove on the top surface, and the two supports 300 provided with the clearance groove are respectively located at the two ends of the plurality of supports 300. After the spacer frame is machined, the clearance groove can avoid the cutter, and prevent the cutter from colliding with the support 300 when the cutter is retracted, which affects the service life of the cutter.

[0045] Further, the clamping mechanism 400 includes a pressing member 410 and a connecting bolt 420, one end of the pressing member 410 is connected to the base 100, and the other end abuts against the support 300, the base 100 is provided with a threaded hole 120, and the connecting bolt 420 is threadedly connected with the threaded hole 120. When the support 300 needs to be pressed, the connecting bolt 420 is tightened, so that the pressing member 410 presses the support; when it needs to be removed, the connecting bolt 420 is loosened, and the support 300 can be removed. The pressing of the support 300 is realized by the connecting bolt 420, which is simple in structure and convenient to operate.

[0046] Specifically, the pressing member 410 comprises a base 411 and a pressing part 412, the base 411 is detachably connected to the base 100, the pressing part 412 is connected to the base 411 at one end and is pressed on the support member 300 at the other end, the pressing part 412 is provided with a through hole 413, and the connecting bolt 420 is threadedly connected to the threaded hole 120 through the through hole 413.

[0047] Optionally, the base 411 is provided as a triangular base, the inclined surface of the triangular base is arranged towards the support member 300, and the pressing part 412 is pressed on the inclined surface, so that the locking force between the pressing part 412 and the base 411 can be increased.

[0048] Optionally, the through hole 413 is provided as a strip-shaped hole, and the connecting bolt 420 can be moved in the strip-shaped hole after being inserted into the strip-shaped hole, so that the connecting bolt 420 and the threaded hole 120 can be aligned.

[0049] Further, the clamping mechanism 400 further comprises a gasket 430, which is arranged between the pressing member 410 and the support member 300, so as to prevent mutual abrasion between the support member 300 and the pressing member 410 during the pressing process.

[0050] Further, the aircraft frame positioning device further comprises a detection assembly 500, which is detachably connected to the base 100, and the detection assembly 500 presses the frame on the support member 300 on the bent plate 200, so that the frame is tightly attached to the bent plate 200, the shape consistency of the bent plate 200 and the frame is ensured, the error between the arrangement form of the support member 300 and the shape of the frame is reduced, and the accuracy of the frame positioning is improved.

[0051] Specifically, the detection assembly 500 comprises a lifting member 510 and a sensing pressure head 520, the lifting member 510 is connected to the base 100, and the sensing pressure head 520 is movably connected to the lifting member 510, and the sensing pressure head 520 can press the frame and detect the pressure.

[0052] The lifting member 510 is used to lift the sensing pressure head 520, so that the sensing pressure head 520 can be on the same horizontal plane as the frame, and the inclination of the frame when the sensing pressure head 520 presses the frame on the bent plate 200 is prevented. The sensing pressure head 520 can detect the pressure applied to the frame, so that the pressure value borne by the frame is less than a preset pressure value, so that the frame is prevented from being damaged due to excessive pressure when the frame is pressed against the bent plate 200.

[0053] Optionally, the detection assembly 500 further comprises a bracket 530 fixed to the lifting piece 510 and a moving piece 540 movably connected to the bracket 530, and the inductive pressure head 520 is connected to the moving piece 540 close to one end of the bent plate 200. The bracket 530 is L-shaped, one end of which is connected to the lifting piece 510, and the other end is connected to the moving piece 540. In this embodiment, the moving piece 540 is provided as a bolt, which is arranged in the bracket 530 and connected to the inductive pressure head 520, so that the structure is simple and convenient to install.

[0054] Optionally, the detection assembly 500 further comprises a display element 550, which is signal connected to the inductive pressure head 520, and the display element 550 is used for displaying the pressure between the inductive pressure head 520 and the partition frame, so that the pressure value can be more intuitively observed, thereby controlling the movement of the inductive pressure head 520.

[0055] When the aircraft partition frame positioning device provided in the embodiment is used to position the partition frame, the following steps are included:

[0056] Firstly, the base 100 is placed in the partition frame processing area, and the direction and levelness of the base 100 are adjusted to ensure that the levelness of the plane of the base 100 is within 0.01mm;

[0057] Secondly, the bent plate 200 corresponding to the partition plate to be processed is inserted into the corresponding strip-shaped slot 110;

[0058] Thirdly, the plurality of supporting pieces 300 are sequentially placed on the base 100 and abut against the bent plate 200;

[0059] Fourthly, the clamping mechanism 400 is used to fix all the supporting pieces 300 on the base 100;

[0060] Fifthly, the detection assembly 500 is used to press the partition frame against the bent plate 200;

[0061] Sixthly, the partition frame is pressed against the supporting piece 300 through the adsorption hole 310, and the bent plate 200 and the detection assembly 500 are removed, and the processing of the partition frame can be started.

[0062] Obviously, the above embodiments of the present application are only examples for clearly illustrating the present application, and are not intended to limit the implementation modes of the present application. For those skilled in the art, other different forms of changes or modifications can be made on the basis of the above description. Here, all the implementation modes are not required or can not be exhausted. Any modification, equivalent replacement and improvement made within the spirit and principle of the present application shall be included in the protection scope of the claims of the present application.

Claims

1. An aircraft frame positioning device, characterized by, The application relates to an aircraft partition positioning device. The base (100) is provided with a plurality of strip-shaped grooves (110), different strip-shaped grooves (110) are different in shape, and the shape of each strip-shaped groove (110) corresponds to the shape of a partition. The bending plate (200) can be inserted into any strip-shaped groove (110). A plurality of support members (300) are arranged on the base (100) in sequence and abut against the bending plate (200), the support member (300) is provided with an adsorption hole (310), and the adsorption hole (310) is used for pressing the partition against the support member (300). A plurality of clamping mechanisms (400) are detachably connected to the base (100), and the clamping mechanism (400) clamps the base (100) and the support member (300).

2. The aircraft frame positioning apparatus of claim 1, wherein, The aircraft partition positioning device further comprises a detection assembly (500) which is detachably connected to the base (100) and is used for pressing the partition on the support member (300) against the bending plate (200).

3. The aircraft frame positioning apparatus of claim 2, wherein, The detection assembly (500) comprises a lifting member (510) connected to the base (100) and a sensing pressure head (520) movably connected to the lifting member (510), and the sensing pressure head (520) can press the partition and detect pressure.

4. The aircraft frame positioning apparatus of claim 3, wherein, The detection assembly (500) further comprises a bracket (530) fixed to the lifting member (510) and a moving member (540) movably connected to the bracket (530), and the sensing pressure head (520) is connected to one end of the moving member (540) close to the bending plate (200).

5. The aircraft frame positioning apparatus of claim 3, wherein, The detection assembly (500) further comprises a display element (550) in signal connection with the sensing pressure head (520).

6. The aircraft frame positioning apparatus of claim 1, wherein, The clamping mechanism (400) comprises a pressing member (410) and a connecting bolt (420), one end of the pressing member (410) is connected to the base (100), the other end of the pressing member (410) abuts against the support member (300), the base (100) is provided with a threaded hole (120), and the connecting bolt (420) is arranged to pass through the pressing member (410) and is in threaded connection with the threaded hole (120).

7. The aircraft frame positioning apparatus of claim 6, wherein, The pressing member (410) comprises a base (411) connected to the base (100) and an abutting portion (412) connected to one end of the base (411) and abutting against the support member (300), and the abutting portion (412) is provided with a through hole (413) through which the connecting bolt (420) passes.

8. The aircraft frame positioning apparatus of claim 6, wherein, The clamping mechanism (400) further comprises a gasket (430) arranged between the pressing member (410) and the support member (300).

9. The aircraft frame positioning apparatus of claim 1, wherein, At least two of the support members (300) are provided with a top surface and a relief groove.

10. The aircraft frame positioning apparatus of claim 1, wherein, The support member (300) is provided with a weight-reducing hole (320).

Images