Opening cover hole guiding method for closed cavity of aircraft

Abstract

The invention discloses a covering cap hole guiding method for a closed cavity of an aircraft, and the method comprises the steps: preparing a transparent flexible template, and fixing the flexible template on the surface of an aircraft body; the reference holes in the machine body are observed through the flexible template, and the center position of each reference hole is accurately marked on the flexible template; the flexible template is taken down, and the repaired covering cap is installed at the opening of the machine body and fixed; fixing the flexible template with the hole position marks on the machine body again; taking the hole position mark on the flexible template as a processing reference, penetrating through the flexible template, and carrying out lead hole processing on the covering cap below the flexible template; after hole guiding is completed, the flexible template is removed; and the covering cap is taken down and is formally mounted on the machine body through a fastener. The position of the reference hole is transferred from the aircraft body by using the transparent flexible template to form the hole position mark, so that the direct and accurate transfer from the reference hole position of the aircraft body to the covering cap is realized, and the guide hole scene of the closed cavity of the aircraft is perfectly adapted.

Description

Technical Field

[0001] This invention belongs to the field of aircraft manufacturing technology, and specifically relates to a method for creating a pre-hole for a sealed cavity of an aircraft. Background Technology

[0002] In the aerospace field, hatch replacement is a fundamental task in routine maintenance, repair, and overhaul procedures, and its quality directly affects the structural integrity and operational safety of aerospace equipment. Hatch components are bolted to the fuselage. After prolonged flight, both the fuselage and hatch components undergo deformation, causing the bolt holes on the hatch components manufactured according to the design drawings to no longer match the actual hole positions on the fuselage. Therefore, after the gap between the hatch component and the fuselage is adjusted, the hole positions on the hatch component must be determined using the actual hole positions on the fuselage.

[0003] In actual operation, the cover parts create a sealed space on the machine body, preventing operators from drilling inside. To achieve precise alignment between the cover and the existing holes on the machine body, the following methods are currently used: open cavity method, standard tooling method, dedicated drilling tool method, and manual scribing method. However, the open cavity method requires an open cavity, allowing the cover to be placed externally before drilling. This method is completely unsuitable for sealed cavities. The standard tooling method requires the design and manufacture of high-precision standard tooling for specific covers and machine bodies. While it ensures interchangeability and accuracy, the tooling design and manufacturing costs are high, the cycle is long, and its versatility is poor, making it unsuitable for single or small-batch operations. The dedicated drilling tool method requires drilling from the machine body holes to the cover, but on complex machine surfaces with large curvature or limited space, the tool is difficult to install stably and accurately, presenting limitations. The manual scribing method requires manually scribing lines from the existing holes on the machine body to the cover, which is extremely inefficient. Accuracy depends entirely on the operator's experience, is prone to human error, and has poor quality stability. Summary of the Invention

[0004] To address the aforementioned problems, this invention provides a method for obtaining a pilot hole for a sealed cavity of an aircraft, which enables precise and efficient transfer of the reference hole position from the aircraft body to the pilot hole.

[0005] Therefore, the technical solution of the present invention is: a method for a hatch opening for a sealed cavity of an aircraft, comprising the following steps: S1. Prepare a transparent flexible template whose size is adapted to the area on the machine body where the pilot hole is to be drilled; S2. Fix the flexible template to the surface of the machine body so that it fits against the area to be drilled; S3. Observe the reference holes on the machine body through the flexible template, and accurately mark the center position of each reference hole on the flexible template to form a hole position mark that corresponds one-to-one with the reference hole; S4. Remove the flexible template, install the modified cover onto the opening of the machine body, and secure it. S5. Re-fix the flexible template with hole markings onto the machine body, consistent with the fixing position in step S2. S6. Using the hole markings on the flexible template as the processing reference, penetrate the flexible template and perform pre-hole processing on the cap below it; S7. After drilling the holes, remove the flexible template; and remove the cover, and then use fasteners to officially install the cover onto the machine body.

[0006] Based on the above scheme and as a preferred embodiment of the above scheme: in step S3, a recess is processed at the center of the position corresponding to the reference hole of the body on the flexible template, and the recess is used to form a hole position mark.

[0007] Based on the above scheme and as a preferred embodiment of the above scheme: in step S2, after the flexible template is re-fixed to the machine body, a positioning reference line or border is left on the surface of the flexible template or the machine body; in step S5, the flexible template is re-fixed to the initial position of the machine body according to the positioning reference line or border.

[0008] Based on the above scheme and as a preferred embodiment of the above scheme: in steps S2 and S5, the flexible template is temporarily fixed to the surface of the machine body by a low-tack adhesive or paper tape.

[0009] Based on the above scheme and as a preferred embodiment of the above scheme: in step S4, the repaired cap is temporarily fixed to the opening of the machine body by a low-viscosity adhesive and a vacuum suction cup.

[0010] Based on the above scheme and as a preferred embodiment of the above scheme: the flexible template is made of PET or PC material, and the thickness of the flexible template is 0.05mm~0.5mm.

[0011] Compared with the prior art, the beneficial effects of the present invention are: The position of the reference hole is transferred from the airframe using a transparent flexible template to form a hole position mark; after temporarily fixing the cover, the transparent flexible template is fixed to the outside of the cover, realizing the direct and accurate transfer of the reference hole position from the airframe to the cover, eliminating the cumulative error caused by multiple alignments and scribings, and perfectly adapting to the scenario of the pilot hole in the sealed cavity of the aircraft.

[0012] The flexible template can be flexibly adapted to the size of the area to be drilled, and is not sensitive to the curvature of the machine body or the layout of the holes. It is suitable for various complex closed cavities, does not require separate design for specific caps or machine bodies, is inexpensive, simple and easy to operate, and is suitable for single and small batch cap replacement operations. It can also meet the needs of various closed cavity cap drilling in daily maintenance, breaking the applicability limitations of traditional methods.

[0013] The flexible template and the cover are temporarily fixed using low-tack adhesives, paper tape, etc., which makes installation and disassembly simple and will not damage the machine body or the surface of the cover. The flexible template material (PET / PC) is thin and flexible, which can fit the surface of the machine body without affecting the smoothness of subsequent drilling. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the area to be drilled in the machine body; Figure 2 A schematic diagram showing the state of the flexible template being fixed on the surface of the machine body and the hole positions marked; Figure 3 This is a diagram illustrating the temporary fixed state of the lid; Figure 4 This is a schematic diagram showing the flexible template on the outside of the opening.

[0015] The markings in the diagram are: 1. Body, 2. Reference hole, 3. Paper tape, 4. Flexible template, 5. Positioning recess, 6. Cover. Detailed Implementation

[0016] In the description of this invention, it should be noted that directional terms such as "center", "lateral (X)", "longitudinal (Y)", "vertical (Z)", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", and "counterclockwise" indicate the orientation and positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention 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. They should not be construed as limiting the specific protection scope of this invention.

[0017] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features. Thus, the use of "first" and "second" to define a feature may explicitly or implicitly include one or more of that feature. In the description of this invention, "several" or "a number" means two or more, unless otherwise explicitly specified.

[0018] See the attached figures. The method for obtaining the access hole for a sealed cavity of an aircraft, as described in this embodiment, includes the following steps: S1. Select a transparent PET plastic sheet with a thickness of 0.1mm and cut it to a size slightly larger than the cap area as a template; prepare masking tape, a center punch, an electric drill, and a repaired new cap.

[0019] S2. Clean the surface of body 1 and reference hole 2 (e.g.) Figure 1As shown), use masking tape 3 to smoothly fix the flexible template 4 to the area to be drilled on the surface of the body 1, ensuring that it fits tightly against the skin surface without any lifting (as shown). Figure 2 (As shown). Figure 2 Taking a strip template covering a single-sided reference hole as an example, in actual use, the flexible template can be larger than the entire cover mounting position, allowing all reference holes to be drilled onto the same flexible template. Alternatively, it can be divided into multiple strip-shaped flexible templates, used to drill reference holes on each side separately. Simultaneously, a reference position can be found on the machine body, and a positioning baseline can be marked on the flexible template to facilitate subsequent flexible template repositioning.

[0020] S3. The operator can clearly see all the reference holes 2 on the machine body 1 through the flexible template 4. The operator uses a center punch to gently impact the center of each reference hole to form a tiny, touchable positioning pit 5 on the flexible template 4. These pits are high-precision hole position marks, and the hole position marks correspond one-to-one with the reference holes 2.

[0021] S4. Carefully peel off the flexible template 4 and the paper tape 3, and install the modified cover 6 into the opening of the machine body 1. Temporarily fix its position with low-tack double-sided tape (e.g., Figure 3 (As shown).

[0022] S5. Precisely reposition the marked flexible template 4 to its original position in step S2 using the paper tape 3. At this time, the positioning recess 5 on the flexible template is aligned with the original reference hole 2 on the machine body 1 (e.g., ...). Figure 4 (As shown). At the same time, in step S4, the paper tape can be left unremoved, and the flexible template can be flipped open to expose the opening of the machine body 1; then, after the repaired cover 6 is installed at the opening of the machine body 1, the flexible template can be flipped back, so that the positioning recess 5 on the flexible template forms a punch mark on the cover.

[0023] S6. The operator uses an electric drill to place the drill bit tip into the positioning recess 5 on the flexible template 4. The recess can effectively prevent the drill bit from slipping. Start the electric drill and drill vertically downwards to penetrate the flexible template 4 and the cover 6 below it in sequence to complete the drilling of one hole. Repeat this process until all holes are processed.

[0024] S7. After drilling the holes, remove the flexible template 4 and all temporary fixing materials; use fasteners to formally install the cover 6 on the body 1, check the smoothness of the cover 6 installation and the alignment accuracy of the holes, and ensure that all holes are aligned accurately and the cover is installed smoothly.

[0025] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A port plug method for a sealed cavity of an aircraft, characterized by: The method comprises the following steps: S1, preparing a transparent flexible template with a size matching the area to be drilled on the machine body; S2, fixing the flexible template on the surface of the machine body so as to match the area to be drilled; S3, observing the reference holes on the machine body through the flexible template and accurately marking the center positions of the reference holes on the flexible template to form hole position marks corresponding to the reference holes one by one; S4, removing the flexible template and installing the repaired cover on the opening of the machine body and fixing it; S5, re-fixing the flexible template with the hole position marks on the machine body in the same position as that in step S2; S6, taking the hole position marks on the flexible template as the machining reference, drilling through the flexible template and drilling the cover below; S7, removing the flexible template after the drilling is completed; and removing the cover and installing the cover on the machine body through fasteners.

2. A method for a hatch access hole for a sealed cavity of an aircraft as defined in claim 1, wherein: In step S3, a pit is processed at the center of the corresponding position of the flexible template and the reference hole of the machine body, and the hole position mark is formed by the pit.

3. A method for a hatch access hole for a sealed cavity of an aircraft as defined in claim 1, wherein: In step S2, a positioning reference line or a frame is left on the surface of the flexible template or the machine body after the flexible template is re-fixed on the machine body; in step S5, the flexible template is re-fixed on the initial position of the machine body according to the positioning reference line or the frame.

4. A method for a hatch access hole for a sealed cavity of an aircraft as defined in claim 1, wherein: In steps S2 and S5, the flexible template is temporarily fixed on the surface of the machine body by low-adhesion adhesive or paper adhesive tape.

5. A method for a hatch access hole for a sealed cavity of an aircraft as defined in claim 1, wherein: In step S4, the repaired cover is temporarily fixed on the opening of the machine body by low-adhesion adhesive or a vacuum chuck.

6. A method for a hatch access hole for a sealed cavity of an aircraft as defined in claim 1, wherein: The flexible template is made of PET or PC material, and the thickness of the flexible template is 0.05-0.5 mm.

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