Aviation cylindrical part shape correcting device

Abstract

The utility model discloses an aviation cylindrical piece shape righting device which comprises a supporting inner container located in a cylindrical piece, a pressure control mechanism and an outer restraining frame installed outside the cylindrical piece, and the outer restraining frame provides counter-acting force support for a flexible air bag to exert shape righting force. The flexible air bag capable of being independently pressurized is used for applying orthopedic force, point or line pressure of a traditional rigid pressure head is replaced with uniform surface pressure, the orthopedic force is softly distributed in a whole deformation area, indentation, scratching or internal tissue damage caused by stress concentration are completely avoided, true nondestructive orthopedic is achieved, and the orthopedic effect is good. By means of the method, it is ensured that the shape righting force is accurately acted on a target deformation area, secondary deformation caused by the fact that the shape righting force is transmitted to the periphery is avoided, the method can adapt to the inner diameters of different cylindrical parts within a certain range, the production preparation cost is reduced, the shape righting period is shortened, and therefore the aviation cylindrical parts of multiple varieties and small batches can be better treated.

Description

Technical Field

[0001] This utility model relates to the field of aerospace component straightening technology, and in particular to an aerospace cylindrical component straightening device. Background Technology

[0002] Aerospace cylindrical components, such as aircraft engine casings, rocket body sections, and fuselage structural components, are key load-bearing parts in modern aerospace vehicles. These components are typically characterized by thin walls, high dimensional accuracy requirements, special materials (such as titanium alloys, high-temperature alloys, and composite materials), and extremely high value. During manufacturing, transportation, or assembly, these thin-walled cylindrical components inevitably experience shape deviations exceeding design tolerances due to various factors, such as dents, out-of-tolerance ovality, or localized twisting, necessitating precision straightening.

[0003] However, existing methods and devices for straightening generally face a contradiction between the "rigidity" of the straightening force and the "flexibility" of protecting the parts when dealing with such high-value, high-precision aerospace cylindrical parts. Traditional straightening methods often use hydraulic presses with rigid molds or multi-point rigid indenters to apply pressure, employing a "hard-on-hard" approach. This easily leads to excessive stress concentration at the straightening point, resulting in new indentations, scratches, or even microscopic damage to the internal structure of the material while eliminating the original deformation. How to apply a straightening force sufficient to induce plastic deformation in the parts while ensuring the "flexibility" of the contact process to avoid secondary damage is a major challenge of existing technologies.

[0004] Furthermore, most existing mechanical or simple hydraulic straightening devices rely primarily on experience and manual estimation by operators, which easily leads to inadequate straightening or overcorrection. When applying external pressure to a point on a thin-walled cylindrical component, if there is no ideal support inside that can completely conform to the non-deformable area, the straightening force will be transmitted to the surrounding area, causing new deformations in other locations. It is difficult to achieve a perfect fit with the inner wall of the cylindrical component, or the supporting function is separate from and uncoordinated with the external straightening pressure process, making it difficult to achieve precise and localized straightening results. Therefore, there is an urgent need for a straightening device for aerospace cylindrical components. Utility Model Content

[0005] The purpose of this utility model is to address the deficiencies in the existing technology by proposing an aerospace cylindrical component straightening device.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A shaping device for aircraft cylindrical components, used for shape correction of hollow cylindrical components, the device comprising:

[0008] The inner support liner is located inside the cylindrical component. The inner support liner includes an inner liner skeleton, which is composed of multiple arc-shaped support tiles evenly distributed and connected along the circumference. Each arc-shaped support tile has a flexible airbag integrated or pasted on its outer surface.

[0009] An expansion mechanism is used to drive the arc-shaped support tiles to expand or contract radially synchronously, so that the flexible airbag fits against the inner wall of the cylindrical component in a pre-pressurized or unpressurized state.

[0010] The pressure control mechanism includes a pressure supply assembly and a multi-way control tube, which is connected to each flexible airbag via independent tubing for selectively injecting pressurized fluid into one or more flexible airbags to apply orthopedic force.

[0011] And an external constraint frame installed outside the cylindrical component, which provides reaction force support for applying orthopedic force to the flexible airbag.

[0012] Furthermore, adjacent curved support tiles are connected by elastic connectors;

[0013] The elastic connector has a hollow structure, and its internal hollow space is connected to the internal air cavity of the flexible airbag.

[0014] Furthermore, the flexible airbag is a flat airbag, and the outer surface of the arc-shaped support tile is provided with an installation groove that matches the flexible airbag.

[0015] Furthermore, the expansion mechanism is located at the center of the supporting inner liner, which includes a central tie rod with positive and negative threads and multiple expansion sliders that engage with the conical surfaces of the central tie rod. The expansion sliders are used to push the arc-shaped support tile to expand radially.

[0016] Furthermore, each valve in the multi-way control tube is connected to a corresponding flexible airbag via an independent hose.

[0017] Furthermore, the external constraint frame is modularly assembled from multiple standardized rods and multiple adjustable-angle locking joints;

[0018] The external constraint frame is also equipped with a support frame.

[0019] Furthermore, the ends of the members of the external constraint frame are provided with contact plates for stably abutting against the outer surface of the cylindrical member, and at least a mechanical displacement measurement system is installed on at least a portion of the members.

[0020] Furthermore, the installation position of the mechanical displacement measurement system corresponds one-to-one with the position of a specific flexible airbag on the inner liner in the radial direction.

[0021] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0022] By using independently pressurizable flexible airbags to apply orthopedic force, the point or line pressure of the traditional rigid indenter is replaced with uniform surface pressure, and the orthopedic force is gently distributed throughout the deformation area, completely avoiding indentations, scratches or internal tissue damage caused by stress concentration, thus achieving true non-destructive orthopedics. A closed-loop feedback system of internal pressure application and external monitoring is constructed, elevating orthopedic operations to the level of precision engineering.

[0023] By installing a mechanical displacement measurement system on the external constraint frame that corresponds one-to-one with the position of the internal flexible airbags, and driving the supporting inner liner through the expansion mechanism, a uniform, gentle, and stress-free perfect fit support can be achieved on the entire inner wall of the cylindrical component (including all undeformed healthy areas). After establishing the internal support foundation, the flexible airbags in specific areas are selectively inflated through multi-channel control pipes to ensure that the corrective force is precisely applied to the target deformation area without being transmitted to the surrounding area, causing secondary deformation. It can also adapt to different inner diameters of cylindrical components within a certain range, and can be quickly assembled to accommodate cylindrical components of different diameters and lengths, thereby reducing production preparation costs and shortening the correction cycle. This allows for better handling of multiple varieties and small batches of aviation cylindrical components. Attached Figure Description

[0024] The accompanying drawings are provided to further understand the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention and do not constitute a limitation thereof.

[0025] Figure 1 This is one of the overall structural schematic diagrams of the aircraft cylindrical component straightening device proposed in this utility model;

[0026] Figure 2 This is the second schematic diagram of the overall structure of the aircraft cylindrical component straightening device proposed in this utility model;

[0027] Figure 3 This is a schematic diagram of the expansion mechanism of the aerospace cylindrical component straightening device proposed in this utility model.

[0028] Figure 4 This is a schematic diagram of the supporting inner liner of the aerospace cylindrical component straightening device proposed in this utility model.

[0029] In the diagram: 100, inner liner support; 110, inner liner frame; 111, arc-shaped support tile; 112, mounting groove; 120, elastic connector; 130, flexible airbag; 200, expansion mechanism; 210, central tie rod; 220, expansion slider; 300, pressure control mechanism; 310, hose; 320, multi-way control pipe; 330, pressure supply assembly; 400, external constraint frame; 410, rod; 420, locking connector; 430, support frame. Detailed Implementation

[0030] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0031] In the description of this utility model, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0032] Reference Figure 1-4 The aircraft cylindrical component straightening device includes a support liner 100 that can be inserted into the cylindrical component to be straightened. The support liner 100 is composed of an inner liner frame 110, which is formed by multiple arc-shaped support tiles 111 evenly connected circumferentially to form a radially expandable annular structure. On the outer surface of each arc-shaped support tile 111, an independently inflatable flexible airbag 130 is integrated or attached.

[0033] The device is equipped with an expansion mechanism 200, which can drive all the arc-shaped support tiles 111 to expand or contract radially in sync, so that all the flexible airbags 130 can be evenly and gently attached to the entire inner wall of the cylindrical part when they are not filled with high pressure or only pre-filled with a small amount of low pressure, forming comprehensive internal support.

[0034] The device is equipped with a pressure control mechanism 300, which includes a pressure supply component 330, such as a hand-cranked or foot-operated pump, and a multi-way control line 320. The multi-way control line 320 is connected to each flexible airbag 130 via independent lines, allowing the operator to selectively inject pressurized fluids such as hydraulic oil or compressed air into one or more specific flexible airbags 130.

[0035] The device also includes an external constraint frame 400 mounted on the outside of the cylindrical member, which provides a solid reaction force support for the orthopedic force applied by the internal flexible airbag 130, preventing unwanted overall expansion of the cylindrical member during the orthopedic process.

[0036] In a specific implementation example, the expansion mechanism 200 expands the inner support liner 100 within the cylindrical component, achieving comprehensive, stress-free support of the inner wall. Then, a straightening process is performed by selectively inflating the flexible airbag 130, located below the recessed area of ​​the cylindrical component, using the pressure of the flexible surface to precisely push the recessed area outwards until it returns to its standard shape. The entire process is conducted under the stable constraint of the outer constraint frame 400.

[0037] Multiple arc-shaped support tiles 111 can expand and contract collaboratively as a whole, and adjacent arc-shaped support tiles 111 are connected by an elastic connector 120. The elastic connector 120 is preferably a hollow structure, such as a corrugated pressure-resistant rubber hose, and its internal hollow space is interconnected with the internal air chambers of the flexible airbags 130 connected at both ends, so that the inner liner skeleton 110 has the necessary flexibility in the contracted state, which facilitates the insertion of cylindrical components and may also help to achieve rapid pressure balance when all airbags are pre-inflated at low pressure.

[0038] To ensure that the flexible airbag 130 can be securely fixed to the arc-shaped support tile 111 and protected, the flexible airbag 130 is preferably a flat airbag, and an installation groove 112 matching its shape and size is pre-opened on the outer surface of each arc-shaped support tile 111, in which the flexible airbag 130 is embedded or pasted.

[0039] In one example, the elastic connector 120 ensures the structural integrity and coordinated movement of the entire inner liner skeleton 110 during expansion and contraction, while the mounting groove 112 ensures that the flexible airbag 130 does not undergo undesirable displacement or over-expansion during inflation, so that the force generated can be effectively transmitted to the inner wall of the cylindrical component.

[0040] The expansion mechanism 200 is used to achieve uniform support for the inner liner. It is located at the center of the supporting inner liner 100 and is preferably a double-cone wedge-type expansion mechanism. The mechanism includes a central tie rod 210 with positive and negative threads. Symmetrical, outwardly expanding conical surfaces are machined at both ends of the rod, and multiple expansion sliders 220 are evenly distributed thereon. The inner side of each expansion slider 220 has an inner conical surface that is completely matched with the conical surface of the central tie rod 210, and its outer side rests smoothly against the inner wall of the arc-shaped supporting tile 111.

[0041] In one example, by rotating one end of the central pull rod 210, the positive and negative threads on it will cause the conical portions at both ends to move towards each other. The axial movement will act like a wedge, generating a strong radial thrust perpendicular to the axis outward on the inner conical surfaces of all expansion sliders 220. The thrust will synchronously and smoothly push all expansion sliders 220 outward, thereby driving all arc-shaped support tiles 111 to expand radially until the flexible airbags 130 on their outer surfaces are completely in contact with the inner wall of the cylindrical part, which has a significant force-increasing effect and reliable self-locking performance.

[0042] Each independent valve in the multi-way control pipe 320 of the pressure control mechanism 300 is connected to a corresponding flexible airbag 130 through an independent hose 310, realizing a "one-to-one" control path.

[0043] The pressure supply component 330 provides the system with stable and controllable pressure fluid. In order to achieve quantitative control of the corrective force, a mechanical pressure gauge is also integrated at the pressure output end of the pressure supply component 330. The operator first establishes the system pressure through the pressure supply component 330 and controls the pressure by observing the mechanical pressure gauge. Then, by operating the corresponding valve switch on the multi-way control pipe 320, the fluid with a specific pressure can be accurately and independently injected into any one or more target flexible airbags 130, thereby applying corrective force to the specific deformation area of ​​the cylindrical part.

[0044] The external constraint frame 400 provides reaction force support and is modularly assembled from multiple standardized rods 410 and multiple adjustable locking joints 420, enabling it to quickly adapt to cylindrical parts of different diameters and lengths. For ease of movement and on-site fixing, the external constraint frame 400 can also be configured with a support frame 430.

[0045] The ends of the rods 410 of the external constraint frame 400 are provided with contact plates that can stably abut against the outer surface of the cylindrical component. At least one mechanical displacement measuring system is also installed on at least a portion of the rods 410. The core of this measuring system is a dial indicator or lever indicator, whose probe can abut against the vicinity of the contact plate or directly abut against the outer surface of the cylindrical component through a reserved hole on the contact plate.

[0046] The installation position of each mechanical displacement measurement system corresponds one-to-one with the position of a specific flexible airbag 130 on the supporting inner liner 100 in the radial direction.

[0047] In one example, before the straightening process begins, the mechanical displacement measurement system can accurately measure the initial deformation of each part of the cylindrical component. When the operator pressurizes and straightens a flexible airbag 130 inside, the operator can observe the reading changes of the corresponding dial gauge or lever indicator on the outside in real time and continuously. When the indicator reading shows that the deformation at that point has returned to zero or reached the preset tolerance range, the operator can stop pressurizing. Through the closed-loop operation of internal pressure application and external real-time monitoring feedback, the straightening process is transformed from an experience-based operation into a data-supported engineering process, thereby ensuring the accuracy of the straightening and effectively avoiding secondary damage to the parts caused by "overcorrection".

[0048] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A device for correcting the shape of hollow cylindrical components in aircraft, characterized in that, The device includes: The inner support liner (100) located inside the cylindrical component includes an inner liner skeleton (110), which is formed by multiple arc-shaped support tiles (111) evenly distributed and connected in the circumferential direction. Each arc-shaped support tile (111) has a flexible airbag (130) integrated or pasted on its outer surface. An expansion mechanism (200) for driving the arc-shaped support tile (111) to expand or contract synchronously radially, so that the flexible airbag (130) fits against the inner wall of the cylindrical component in a pre-pressurized or unpressurized state; The pressure control mechanism (300) includes a pressure supply assembly (330) and a multi-way control tube (320), which is connected to each of the flexible airbags (130) through independent pipelines for selectively injecting pressurized fluid into one or more of the flexible airbags (130) to apply orthopedic force. And an external constraint frame (400) installed outside the cylindrical component, the external constraint frame (400) providing reaction force support for applying orthopedic force to the flexible airbag (130).

2. The aircraft cylindrical component straightening device according to claim 1, characterized in that, Adjacent arc-shaped support tiles (111) are connected by elastic connectors (120); The elastic connector (120) has a hollow structure, and its internal hollow space is connected to the internal air cavity of the flexible airbag (130).

3. The aircraft cylindrical component straightening device according to claim 1, characterized in that, The flexible airbag (130) is a flat airbag, and the outer surface of the arc-shaped support tile (111) is provided with an installation groove (112) that matches the flexible airbag (130).

4. The aircraft cylindrical component straightening device according to claim 1, characterized in that, The expansion mechanism (200) is located at the center of the support liner (100), and includes a central pull rod (210) with positive and negative threads and a plurality of expansion sliders (220) that engage with the conical surface of the central pull rod (210). The expansion sliders (220) are used to push the arc-shaped support tile (111) to expand radially.

5. The aircraft cylindrical component straightening device according to claim 1, characterized in that, Each valve of the multi-way control tube (320) is connected to a corresponding flexible airbag (130) via an independent hose (310).

6. The aircraft cylindrical component straightening device according to claim 1, characterized in that, The external constraint frame (400) is modularly assembled from multiple standardized rods (410) and multiple adjustable locking joints (420); The external constraint frame (400) is also equipped with a support frame (430).

7. The aircraft cylindrical component straightening device according to claim 6, characterized in that, The ends of the rods (410) of the external constraint frame (400) are provided with contact plates for stably abutting against the outer surface of the cylindrical member, and at least a portion of the rods (410) are also equipped with at least one mechanical displacement measuring system.

8. The aircraft cylindrical component straightening device according to claim 7, characterized in that, The installation position of the mechanical displacement measurement system corresponds radially to the position of a specific flexible airbag (130) on the supporting inner liner (100).

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