A repair process for hyperboloid honeycomb panels on an aircraft

Abstract

The present application relates to the technical field of aircraft component maintenance, and discloses a hyperboloid honeycomb plate maintenance process on an aircraft, which comprises the following steps: placing a honeycomb plate replacement part on a mold of an aircraft component to form a maintenance assembly, the placement position of the honeycomb plate replacement part on the mold of the aircraft component is consistent with the position of a damaged honeycomb plate on the aircraft component, the back plate of the honeycomb plate replacement part is knocked to make the honeycomb plate replacement part adhere to the mold; the maintenance assembly is placed in a sealed bag to be vacuumized, and the sealed bag is attached to the surface of the maintenance assembly; the damaged honeycomb plate is placed on the honeycomb plate replacement part to be cut, so that the honeycomb plate replacement part and the damaged honeycomb plate are cut to the same size; and the honeycomb plate replacement part is bonded to the honeycomb plate reattachment area. The hyperboloid honeycomb plate maintenance process on the aircraft improves the maintenance adhesion of the honeycomb plate, improves the bonding quality, can also improve the work efficiency, and effectively avoids damage spreading.

Description

Technical Field

[0001] This invention relates to the technical field of aircraft component repair, and in particular to a repair process for hyperboloid honeycomb panels on aircraft. Background Technology

[0002] Due to its excellent structural strength and rigidity, as well as its lightweight design, metal honeycomb panel material is increasingly used in civil aircraft components, leading to a corresponding increase in maintenance volume. Extensive repair experience has revealed that the manufacturer's manual recommends fabricating a new honeycomb panel of the same dimensions and orientation before bonding and curing.

[0003] The existing technical solution manual does not provide detailed instructions for the repair of honeycomb panels. Since the honeycomb panels commonly used for repair are flat, while the commonly used structure is a hyperboloid streamlined shape, there is a significant difference in their appearance, making it difficult to install them in place. Furthermore, during the bonding process, due to the mismatch in appearance, the replacement honeycomb panel, which is straighter, is often prone to damage or compression of adjacent honeycomb panels during repair and replacement, affecting the bonding quality, reducing work efficiency, and easily expanding the scope of damage. Summary of the Invention

[0004] The invention aims to address at least one of the technical problems existing in the prior art. It provides a repair process for hyperboloid honeycomb panels on aircraft, improving the fit of the honeycomb panels during repair and overcoming the drawback of compression damage to the surrounding honeycomb panels during the repair process. This not only improves bonding quality but also increases work efficiency and effectively prevents damage propagation.

[0005] To achieve the above objectives, the present invention provides a repair process for hyperboloid honeycomb panels on aircraft, comprising the following steps:

[0006] The step of determining the extent of damage involves obtaining the damaged honeycomb panel from the aircraft component requiring repair, with the honeycomb panel re-attachment area exposed on the aircraft component.

[0007] Material preparation steps: Place the damaged honeycomb panel on the honeycomb panel and cut it according to the edge shape of the damaged honeycomb panel to obtain a honeycomb panel replacement part. The edge of the honeycomb panel replacement part protrudes a length a relative to the edge of the damaged honeycomb panel, where a ≥ 6cm.

[0008] In the pre-shaping step, the honeycomb panel replacement part is placed on the mold of the aircraft component to form a repair assembly. The placement position of the honeycomb panel replacement part on the mold of the aircraft component is consistent with the position of the damaged honeycomb panel on the aircraft component. The back plate of the honeycomb panel replacement part is tapped to make the honeycomb panel replacement part adhere to the mold.

[0009] In the shaping step, the repair component is placed in a sealed bag and vacuum-sealed, with the sealed bag adhering to the surface of the repair component;

[0010] The repair step involves placing the damaged honeycomb panel on the honeycomb panel replacement part and cutting it so that the honeycomb panel replacement part is cut to the same size as the damaged honeycomb panel.

[0011] In the bonding step, the honeycomb panel replacement is bonded to the honeycomb panel re-attachment area.

[0012] As a preferred embodiment, in the pre-shaping step, the hammering direction of the honeycomb panel replacement is from the center outwards.

[0013] As a preferred embodiment, in the pre-shaping step, if the honeycomb panel replacement part does not adhere well to the mold after being tapped from the center outwards, the honeycomb panel replacement part is repeatedly tapped from the center outwards until it adheres well to the mold.

[0014] As a preferred embodiment, in the pre-shaping step, the tool used for striking is a soft-headed rubber hammer.

[0015] As a preferred embodiment, the head diameter of the soft rubber mallet is set between 25mm and 50mm.

[0016] As a preferred embodiment, in the shaping step, the vacuum negative pressure is set at 9-13 inches of mercury.

[0017] As a preferred embodiment, the vacuum negative pressure is set for at least 2 hours during the shaping step.

[0018] As a preferred embodiment, in the shaping step, the shaping temperature of the honeycomb panel replacement is set at 80-100°C.

[0019] As a preferred embodiment, in the step of determining the damaged area, the re-attached area of ​​the honeycomb panel is cleaned to remove dirt from the re-attached area.

[0020] As a preferred embodiment, during the shaping step, a breathable cotton layer is laid between the sealing bag and the honeycomb panel replacement.

[0021] This invention discloses a repair process for hyperboloid honeycomb panels on aircraft. Compared with existing technologies, its advantages lie in the following: The flat honeycomb panel replacement is pre-shaped by tapping on a mold, allowing for repair without damaging the honeycomb structure around the re-attachment area. Gentle tapping restores the shape of the damaged area and ensures no additional damage or deformation to the surrounding structure. The pre-shaping method is combined with a vacuum negative pressure shaping method. During vacuum negative pressure shaping, the honeycomb panel replacement is further shaped in the mold. Because the vacuum negative pressure causes shrinkage around the honeycomb panel, a certain peripheral allowance needs to be reserved. After vacuum negative pressure shaping, the honeycomb panel replacement is made to match the original structure's shape, facilitating subsequent bonding repair work and improving bonding quality. Attached Figure Description

[0022] Figure 1 This is a structural schematic diagram of the pre-shaping step in an embodiment of the present invention.

[0023] Figure 2 This is a schematic diagram of the structure of the shaping step in an embodiment of the present invention before vacuuming.

[0024] In the picture:

[0025] 10. Mold; 11. Honeycomb panel replacement parts; 12. Soft rubber mallet; 13. Breathable cotton layer; 14. Sealing bag. Detailed Implementation

[0026] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and are not intended to limit the scope of the invention.

[0027] In the description of this invention, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer" used to indicate orientation or positional relationships are based on the orientation or positional relationships shown in the accompanying drawings and are only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0028] In the description of this invention, it should be understood that the terms "connected," "linked," and "fixed," etc., used in this invention should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or a welded connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly defined. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0029] like Figures 1 to 2 As shown, a preferred embodiment of the present invention provides a repair process for hyperboloid honeycomb panels on aircraft, comprising the following steps:

[0030] The step of determining the extent of damage involves obtaining the damaged honeycomb panel from the aircraft component requiring repair, with the honeycomb panel re-attachment area exposed on the aircraft component.

[0031] Material preparation steps: Place the damaged honeycomb panel on the honeycomb panel and cut it according to the edge shape of the damaged honeycomb panel to obtain a honeycomb panel replacement part 11. The edge of the honeycomb panel replacement part 11 protrudes a length a relative to the edge of the damaged honeycomb panel, where a ≥ 6cm.

[0032] Pre-operative procedures, such as Figure 1 As shown, the honeycomb panel replacement part 11 is placed on the mold 10 of the aircraft component to form a repair assembly. The placement position of the honeycomb panel replacement part 11 on the mold 10 of the aircraft component is consistent with the position of the damaged honeycomb panel on the aircraft component. The back plate of the honeycomb panel replacement part 11 is hammered to make the honeycomb panel replacement part 11 adhere to the mold 10.

[0033] Shaping steps, such as Figure 2 As shown, the repair component is placed in a sealed bag 14 and vacuumed, with the sealed bag 14 adhering to the surface of the repair component;

[0034] The repair step involves placing the damaged honeycomb panel on the honeycomb panel replacement part 11 and cutting it so that the honeycomb panel replacement part 11 and the damaged honeycomb panel are cut to the same size.

[0035] In the bonding step, the honeycomb panel replacement part 11 is bonded to the honeycomb panel re-attachment area, and the edge of the honeycomb panel replacement part 11 is attached to the peripheral side surface of the honeycomb panel around the honeycomb panel re-attachment area.

[0036] The aircraft hyperboloid honeycomb panel repair process of this invention involves pre-shaping a flat honeycomb panel replacement part 11 by tapping it on a mold 10, repairing it without damaging the honeycomb structure around the re-attachment area. Gentle tapping restores the shape of the damaged area and ensures no additional damage or deformation to the surrounding structure. The pre-shaping method is combined with a vacuum negative pressure shaping method. During vacuum negative pressure shaping, the honeycomb panel replacement part 11 undergoes further shaping in the mold 10. Because the vacuum negative pressure causes collapse around the honeycomb panel, a certain peripheral allowance needs to be reserved. After vacuum negative pressure shaping, the honeycomb panel replacement part 11 is made to match the original structural shape, facilitating subsequent bonding repair work and improving bonding quality.

[0037] Furthermore, such as Figure 1As shown, in the pre-shaping step, the hammering direction of the honeycomb panel replacement 11 progresses from the center outwards. Since the honeycomb panel replacement 11 has a non-planar hyperboloid shape, hammering from the center towards the edge diffuses the dimensional changes caused by the shape change of the honeycomb panel replacement 11 to the edge, and also disperses the stress concentrated in the center, improving the shaping quality of the honeycomb panel replacement 11. If hammering is performed from the periphery towards the center, the stress in the center of the honeycomb panel replacement 11 will concentrate and cause damage.

[0038] Furthermore, such as Figure 1 As shown, in the pre-shaping step, the tool used for striking is a soft-headed rubber hammer 12 to avoid damage to the honeycomb panel replacement part 11 during the pre-shaping step.

[0039] Furthermore, such as Figure 1 As shown, the head diameter of the soft rubber mallet 12 is set between 25mm and 50mm, which meets the striking requirements of the honeycomb panel and helps to improve striking efficiency.

[0040] Furthermore, such as Figure 1 As shown, in the pre-shaping step, when the honeycomb panel replacement part 11 is tapped from the middle to the outside, if the honeycomb panel replacement part 11 does not fit well with the mold 10, the honeycomb panel replacement part 11 is tapped from the middle to the outside repeatedly until the honeycomb panel replacement part 11 fits well with the mold 10, so as to satisfy the pre-shaping effect of the honeycomb panel replacement part 11, ensure that the honeycomb surface is flat, without depressions or protrusions, and improve the repair quality of the hyperboloid honeycomb panel.

[0041] Furthermore, excessive vacuum negative pressure during shaping will damage the honeycomb structure, while insufficient pressure will result in poor shaping effect. In the shaping step, the vacuum negative pressure is set at 9-13 inches of mercury to meet the shaping requirements of the honeycomb panel replacement 11 and to help improve the shaping effect.

[0042] Furthermore, in the shaping step, the vacuum negative pressure is set for at least 2 hours to ensure that the shape of the honeycomb panel replacement 11 is consistent with the shape of the mold 10.

[0043] Furthermore, in the step of determining the damaged area, the honeycomb panel re-attachment area is cleaned to remove dirt. This is achieved by using cleaning agents, wiping paper, a blower, a grinder, or other tools to clean the honeycomb panel re-attachment area, removing any dirt, residue, or old adhesive, thereby improving the bonding quality of the honeycomb panel replacement 11 in the honeycomb panel re-attachment area.

[0044] Furthermore, in the shaping step, the shaping temperature of the honeycomb panel replacement part 11 is set at 80-100℃. The selection of the shaping temperature should be consistent with the dehumidification temperature of the honeycomb replacement and repair parts. The increase in temperature helps to fix the deformation of the honeycomb panel replacement part 11. Therefore, when the honeycomb shaping temperature is consistent with the dehumidification temperature, it ensures that the honeycomb structure is not damaged due to overheating, and also maintains a certain temperature to improve the honeycomb shaping effect.

[0045] Furthermore, such as Figure 2 As shown, in the shaping step, a breathable cotton layer 13 is laid between the sealing bag 14 and the honeycomb panel replacement 11. The breathable cotton layer 13 helps to protect the honeycomb panel replacement 11 and prevent it from being damaged by pressure.

[0046] In summary, this invention provides a repair process for hyperboloid honeycomb panels on aircraft. A flat honeycomb panel replacement part 11 is pre-shaped by tapping on a mold 10, allowing for repair without damaging the honeycomb structure around the re-attachment area. Gentle tapping restores the shape of the damaged area and ensures no additional damage or deformation to the surrounding structure. The pre-shaping method is combined with a vacuum negative pressure shaping method. During vacuum negative pressure shaping, the honeycomb panel replacement part 11 undergoes further shaping in the mold 10. Because the vacuum negative pressure causes collapse around the honeycomb panel, a certain peripheral allowance needs to be reserved. After vacuum negative pressure shaping, the honeycomb panel replacement part 11 is made to match the original structural shape, facilitating subsequent bonding repair work and improving bonding quality.

[0047] The above are merely preferred embodiments of the present invention. It should be noted that those skilled in the art can make several improvements and substitutions without departing from the technical principles of the present invention, and these improvements and substitutions should also be considered within the scope of protection of the present invention.

Claims

1. A process for repairing a hyperbolic honeycomb panel on an aircraft, characterized in that: Includes the following steps: The step of determining the extent of damage involves obtaining the damaged honeycomb panel from the aircraft component requiring repair, with the honeycomb panel re-attachment area exposed on the aircraft component. Material preparation steps: Place the damaged honeycomb panel on the honeycomb panel and cut it according to the edge shape of the damaged honeycomb panel to obtain a honeycomb panel replacement part. The edge of the honeycomb panel replacement part protrudes a length a relative to the edge of the damaged honeycomb panel, where a ≥ 6cm. In the pre-shaping step, the honeycomb panel replacement part is placed on the mold of the aircraft component to form a repair assembly. The placement position of the honeycomb panel replacement part on the mold of the aircraft component is consistent with the position of the damaged honeycomb panel on the aircraft component. The back plate of the honeycomb panel replacement part is tapped to make the honeycomb panel replacement part adhere to the mold. In the shaping step, the repair component is placed in a sealed bag and vacuum-sealed, with the sealed bag adhering to the surface of the repair component; The repair step involves placing the damaged honeycomb panel on the honeycomb panel replacement part and cutting it so that the honeycomb panel replacement part is cut to the same size as the damaged honeycomb panel. In the bonding step, the honeycomb panel replacement is bonded to the honeycomb panel re-attachment area.

2. Double curvature honeycomb panel repair process on board an aircraft according to claim 1, characterized in that: In the pre-shaping step, the hammering direction of the honeycomb panel replacement is from the center outward.

3. Double curvature honeycomb panel repair process on board an aircraft according to claim 2, characterized in that: In the pre-shaping step, if the honeycomb panel replacement part does not fit well with the mold after being tapped from the center to the outside, the honeycomb panel replacement part is tapped from the center to the outside repeatedly until it fits well with the mold.

4. Double curvature honeycomb panel repair process on board an aircraft according to claim 1, characterized in that: In the pre-shaping step, the tool used for striking is a soft-headed rubber hammer.

5. Double curvature honeycomb panel repair process on board an aircraft according to claim 4, characterized in that: The head diameter of the soft rubber mallet is set between 25mm and 50mm.

6. Double curved honeycomb panel repair process on board of an aircraft according to claim 1, characterized in that: In the shaping step, the vacuum negative pressure is set at 9–13 inches of mercury.

7. Double curvature honeycomb panel repair process on board an aircraft according to claim 6, characterized in that: In the shaping step, the vacuum negative pressure is set for at least 2 hours.

8. Double curved honeycomb panel repair process on board of an aircraft according to claim 1, characterized in that: In the shaping step, the shaping temperature of the honeycomb panel replacement is set at 80-100°C.

9. Double curvature honeycomb panel repair process on board an aircraft according to claim 1, characterized in that: In the step of determining the damaged area, the honeycomb panel re-attachment area is cleaned to remove dirt from the honeycomb panel re-attachment area.

10. Double curved honeycomb panel repair process on board of an aircraft according to claim 1, characterized in that: During the shaping step, a breathable cotton layer is laid between the sealing bag and the honeycomb panel replacement.

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