Airplane flap assembling mechanism

Abstract

The utility model relates to the technical field of aircraft assembling and forming, and discloses an aircraft flap assembling mechanism which comprises a frame, a positioning support, a skin appearance clamping plate, a skin lug positioner and a flap rotating shaft rib box positioner, the positioning support is detachably installed on the top of the frame, the skin appearance clamping plate is installed on the top of the positioning support, and the flap rotating shaft rib box positioner is installed on the skin lug positioner. The skin lug positioner is arranged in the middle of the skin appearance clamping plate, and the flap rotating shaft rib box positioner is detachably connected to the middle of the positioning support. The problems that in the prior art, an assembling mechanism is low in precision, long in production period, high in manufacturing cost and short in service life are solved.

Description

Technical Field

[0001] This utility model patent relates to the technical field of aircraft assembly and molding, and specifically, to an aircraft flap assembly mechanism. Background Art

[0002] Aircraft assembly is a crucial step in aircraft manufacturing. A key characteristic of aircraft manufacturing is the coordinated approach to ensuring coordination between parts, parts and tooling, and tooling, thereby guaranteeing assembly accuracy. Through a series of specialized process equipment, the shapes and dimensions required for coordination are simulated and then gradually transferred to parts and components. Aircraft structures differ from general mechanical products. During assembly, qualified components cannot be guaranteed solely by the machining accuracy of the parts' shapes and dimensions. Therefore, specialized assembly process equipment is developed for components and parts of different aircraft models.

[0003] The Chinese patent with publication number CN116494170A discloses a positioning and clamping device for assembling the front flap of an aircraft, which relates to the technical field of the equipment manufacturing industry. The positioning and clamping device for assembling the front flap of an aircraft comprises an aircraft flap, a positioning frame and a clamping mechanism. The positioning frame is located below the aircraft flap, and the positioning frame comprises a fixed cylinder, a movable sleeve, a screw, a knob block and a positioning rod. The positioning and clamping device for assembling the front flap of an aircraft can position the aircraft flap, drive the movable sleeve to move on the outer wall of the fixed cylinder, and change the distance between the two groups of positioning rods at the top of the two groups of movable sleeves, so that the positioning rods and the positioning rods can position aircraft flaps of different sizes, thereby improving the applicability of the device. Due to the first rotating wheel, the second rotating wheel and the third rotating wheel, the aircraft flap is pushed and placed on the positioning frame, which can avoid sliding friction between the positioning frame and the aircraft flap, thereby reducing friction and damage to the aircraft flap.

[0004] The assembly mechanism provided by the utility model can be applied to aircraft assembly, specifically to an aircraft flap assembly production line. The assembly mechanism is made of metal material with high strength and long service life. It can effectively solve the problem of aircraft flap assembly, improve the assembly accuracy of aircraft flaps, further reduce the production cycle and manufacturing cost, and realize rapid assembly. Utility Model Content

[0005] The utility model aims to provide an aircraft flap assembly mechanism, aiming to solve the problems of low assembly precision, long production cycle, high manufacturing cost and short service life in the prior art.

[0006] The utility model is implemented as follows: an aircraft flap assembly mechanism includes a frame, a positioning support, a skin shape card plate, a skin ear locator and a flap shaft rib box locator, the positioning support is detachably mounted on the top of the frame, the skin shape card plate is mounted on the top of the positioning support, the skin ear locator is placed in the middle of the skin shape card plate, and the flap shaft rib box locator is detachably connected to the middle of the positioning support.

[0007] The positioning support is connected to the frame through a quick-release positioning pin, and the skin shape clamping plate is installed on the top of the positioning support through the positioning pin.

[0008] The skin ear piece locator is connected to the skin shape clamping plate through a locating pin.

[0009] The flap shaft rib box locator is connected to the skin shape clamping plate through a quick-release locating pin.

[0010] A fixing bushing is installed on the flap shaft rib box positioner.

[0011] It also includes legs and adjustable feet. The legs are welded to the bottom of the frame. The frame is a frame-shaped structure formed by cross-welding of multiple hollow tubes. The adjustable feet can be adjusted and installed at the bottom of the legs.

[0012] The utility model further comprises measuring blocks, which are installed on the top of the frame at four corners.

[0013] Compared with the prior art, the present invention has the following beneficial effects:

[0014] The positioning support and the skin shape clamp are connected to the frame. Through quick-release positioning pins, screws and positioning pins, a 2mm process gap is reserved between the skin shape clamp and the flap skin. By adjusting the thickness of the process gasket, the product can be quickly positioned and disassembled.

[0015] The skin ear locator is installed with a fixing bushing and a positioning pin, and the flap skin is connected to the skin ear locator through the reserved process ear hole, which ensures the assembly accuracy and speeds up the assembly efficiency.

[0016] The flap shaft rib box positioning locking pin is connected to the flap shaft rib box positioner to ensure assembly accuracy while accelerating assembly efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a structural schematic diagram of an aircraft flap assembly mechanism of the utility model;

[0018] Figure 2 yes Figure 1 A partial enlarged view of the middle skin shape plate.

[0019] Reference numerals:

[0020] 1. Frame; 2. Support legs; 3. Adjustable feet; 4. Positioning support; 5. Skin shape clamp; 6. Skin ear locator; 7. Flap shaft rib box locator; 8. Measuring block. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0022] The implementation of the present invention is described in detail below with reference to specific embodiments.

[0023] The same or similar numbers in the drawings of this embodiment correspond to the same or similar parts; in the description of this utility model, it should be understood that if there are terms such as "upper", "lower", "left", "right", etc. indicating directions or positional relationships, they are based on the directions or positional relationships shown in the drawings. This is only for the convenience of describing the utility model and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, the terms describing the positional relationship in the drawings are only used for illustrative purposes and cannot be understood as limiting this patent. For ordinary technicians in this field, the specific meanings of the above terms can be understood according to specific circumstances.

[0024] like Figure 1-2 As shown, the utility model provides an aircraft flap assembly mechanism, including a frame 1, a positioning support 4, a skin shape clamping plate 5, a skin ear locator 6 and a flap shaft rib box locator 7, the positioning support 4 is detachably mounted on the top of the frame 1, the skin shape clamping plate 5 is mounted on the top of the positioning support 4, the skin ear locator 6 is placed in the middle of the skin shape clamping plate 5, and the flap shaft rib box locator 7 is detachably connected to the middle of the positioning support 4.

[0025] The positioning support 4 and the skin shape clamp 5 are connected to the frame 1. Through the quick-release positioning pins, screws and positioning pins, a 2mm process gap is reserved between the skin shape clamp 1 and the flap skin. By adjusting the thickness of the process gasket, the product can be quickly positioned and disassembled.

[0026] The positioning support 4 is connected to the frame 1 through a quick-release positioning pin, and the skin shape clamping plate 5 is installed on the top of the positioning support 4 through the positioning pin.

[0027] The skin ear piece locator 6 is connected to the skin shape clamping plate 5 through a locating pin.

[0028] A fixing bushing and a positioning pin are installed on the skin ear locator 6, and the flap skin is connected to the skin ear locator 6 through the reserved process ear hole, which ensures the assembly accuracy and speeds up the assembly efficiency.

[0029] The flap shaft rib box locator 7 is connected to the skin shape clamping plate 5 through a quick-release locating pin.

[0030] A fixed bushing is installed on the flap shaft rib box positioner 7.

[0031] The flap shaft rib box positioning locking pin is connected to the flap shaft rib box positioner 7 to ensure assembly accuracy while accelerating assembly efficiency.

[0032] It also includes a support leg 2 and an adjustable foot 3. The support leg 2 is welded to the bottom of the frame 1. The frame 1 is a frame-shaped structure formed by cross-welding of multiple hollow tubes. The adjustable foot 3 can be adjusted and installed at the bottom of the support leg 2.

[0033] The frame 1 adopts a hollow steel pipe welded structure, which reduces the weight of the frame while meeting the rigidity. The frame 1 is open on all sides for easy manual operation. At the same time, the legs 2 adopt a height-adjustable structure with symmetrical arrangement at the four corners for adjusting the level of the frame 1.

[0034] It also includes measuring blocks 8, which are installed at the top of the frame at four corners.

[0035] Use professional instruments to conduct professional re-inspection of the mechanism to check the positioning surface accuracy and drilling mechanism position accuracy, effectively ensuring the consistency of different batches of products

[0036] As shown in the drawings, a preferred embodiment of the present invention is provided.

[0037] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent replacements and improvements made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. An aircraft flap assembly mechanism, characterized in that: The invention comprises a frame (1), a positioning support (4), a skin outer shape card plate (5), a skin ear piece positioner (6) and a flap shaft rib box positioner (7), wherein the positioning support (4) is detachably mounted on the top of the frame (1), the skin outer shape card plate (5) is mounted on the top of the positioning support (4), the skin ear piece positioner (6) is placed in the middle of the skin outer shape card plate (5), and the flap shaft rib box positioner (7) is detachably connected to the middle of the positioning support (4).

2. The aircraft flap assembly mechanism according to claim 1, characterized in that: The positioning support (4) is connected to the frame (1) via a quick-release positioning pin, and the skin shape clamping plate (5) is installed on the top of the positioning support (4) via the positioning pin.

3. The aircraft flap assembly mechanism according to claim 2, characterized in that: The skin ear piece locator (6) is connected to the skin outer shape clamping plate (5) via a locating pin.

4. The aircraft flap assembly mechanism according to claim 3, characterized in that: The flap shaft rib box positioner (7) is connected to the skin outer shape clamping plate (5) via a quick-release positioning pin.

5. The aircraft flap assembly mechanism according to claim 4, characterized in that: A fixing bushing is installed on the flap shaft rib box positioner (7).

6. The aircraft flap assembly mechanism according to claim 5, characterized in that: The invention also includes a support leg (2) and an adjustable foot (3), wherein the support leg (2) is welded to the bottom of the frame (1), and the frame (1) is a frame-shaped structure formed by cross-welding of a plurality of hollow tubes, and the adjustable foot (3) can be adjusted and installed at the bottom of the support leg (2).

7. The aircraft flap assembly mechanism according to claim 6, characterized in that: The utility model also comprises measuring blocks (8), which are mounted on the top of the frame at four corners.

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