Unmanned aerial vehicle fuselage trepanning method

Abstract

The invention belongs to the technical field of flight equipment manufacturing, and discloses an unmanned aerial vehicle fuselage trepanning method which comprises the steps that a positioning sample plate and a pore plate are manufactured, and a datum hole is formed in the pore plate; the positioning sample plate is fixedly attached to the inner side wall of the machine body and abuts against the at least two positioning structures at the same time, the trepanning area of the outer side wall of the machine body is determined through the positions of the positioning structures, and the pore plate is fixedly attached to the positioning sample plate and corresponds to the trepanning area; a positioning hole is drilled in the outer side wall of the machine body through the datum hole, and the positioning sample plate and the pore plate are taken down after the positioning hole is drilled; a hole plate is attached to the outer side wall of the machine body, and a positioning piece penetrates through the positioning hole and the datum hole to position the hole plate; drawing a cutting line on the outer side wall of the machine body by taking the outer contour of the pore plate as a reference, and taking down the pore plate after drawing is completed; and a hole is formed in the outer side wall of the machine body by taking the cutting line as an outline. According to the method, holes can be accurately formed in the outer side wall of the machine body, operation is easy and convenient, and the positioning accuracy is effectively guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of flight equipment manufacturing, and particularly to a method for opening holes in a drone fuselage. Background Art

[0002] Refer to Figure 1 As shown, during the development of the current drone project, the assembly between the fuselage 1' and the landing gear 2' is involved. Usually, a keyway hole 3' for fixing and inserting the landing gear 2' is opened on the outer sidewall of the fuselage 1'. The hole-opening process is often completed by means of positioning with a reference part, manual scribing positioning, assembly hole positioning, assembly fixture positioning method, etc.

[0003] However, in the prior art, there are no any marks and structural positioning references on the outer peripheral wall of the fuselage 1'. The accuracy of directly scribing on the outer sidewall of the fuselage 1' is not high and the difficulty is great. Therefore, it is not convenient to directly open holes from the outside to the inside; although there are internal structures that can assist in positioning inside the fuselage 1', directly opening holes from the inner sidewall of the fuselage 1' to the outer sidewall will be difficult to operate due to the narrow operating space of the barrel section of the fuselage 1'. Summary of the Invention

[0004] The purpose of the present invention is to provide a method for opening holes in a drone fuselage, which uses a positioning template and a hole plate in cooperation, and accurately opens holes on the outer sidewall of the fuselage according to the internal positioning reference of the drone, with simple and convenient operation and effectively guaranteed positioning accuracy.

[0005] To achieve this purpose, the present invention adopts the following technical solutions:

[0006] A method for opening holes in a drone fuselage, used for opening holes in the fuselage of a drone. The inside of the fuselage at least includes two positioning structures. The method for opening holes in the drone fuselage mainly includes the following steps:

[0007] S100. Manufacture a positioning template and a hole plate, and open a reference hole on the hole plate;

[0008] S200. Fix and fit the positioning template to the inner sidewall of the fuselage and simultaneously abut against at least two of the positioning structures. Determine the hole-opening area on the outer sidewall of the fuselage through the positions of the positioning structures, and fix and fit the hole plate to the positioning template and corresponding to the hole-opening area;

[0009] S300. Drill corresponding positioning holes on the outer sidewall of the fuselage through the reference hole. The positioning holes penetrate from the inner sidewall of the fuselage to the outer sidewall. Subsequently, remove the positioning template from the inner sidewall of the fuselage and remove the hole plate from the positioning template;

[0010] S400. Attach the orifice plate to the outer wall of the fuselage, align the positioning holes with the corresponding reference holes, and pass positioning members through the positioning holes and the reference holes to position the orifice plate.

[0011] S500. Using the outer contour of the orifice plate as a reference, draw a cutting line on the outer wall of the fuselage. After completion, remove the orifice plate.

[0012] S600. Open a hole on the outer wall of the fuselage along the cutting line.

[0013] Preferably, in step S100, manufacturing the positioning template mainly includes:

[0014] S111. Draw a template model on 3D software that fits the curvature of the inner wall of the fuselage.

[0015] S112. According to the template model, use a cutting machine to cut out the positioning template on the plate.

[0016] Preferably, in step S100, manufacturing the orifice plate mainly includes:

[0017] S121. Determine the size and outer contour of the hole to be opened on the outer wall of the fuselage.

[0018] S122. According to the size and outer contour of the hole to be opened on the outer wall of the fuselage, use a cutting machine to cut out the orifice plate on the plate.

[0019] Preferably, in step S112, use a laser cutting machine to cut out the positioning template on the plate; in step S122, use a laser cutting machine to cut out the orifice plate on the plate.

[0020] Preferably, in step S100, open at least two reference holes on the orifice plate.

[0021] Preferably, in step S200, the positioning template is adhesively attached to the inner wall of the fuselage with an adhesive; the orifice plate is adhesively attached to the positioning template with an adhesive.

[0022] Preferably, in step S300, use a drilling device to pass through the reference hole and the positioning template and drill the positioning hole on the outer wall of the fuselage. The aperture of the positioning hole is the same as that of the reference hole.

[0023] Preferably, in step S400, the orifice plate is adhesively attached to the outer wall of the fuselage with an adhesive.

[0024] Preferably, two reference holes are opened on the orifice plate;

[0025] In step S400, the positioning member is set as a positioning clamp, the positioning clamp includes two clamping portions, each of the clamping portions penetrates through the corresponding positioning hole and the reference hole, and the hole plate can be positioned on the outer side wall of the fuselage under the clamping action of the two clamping portions.

[0026] Preferably, step S600 is specifically as follows:

[0027] S610. Use a cutting device to cut into the outer side wall of the fuselage inside the cutting line;

[0028] S620. Move the cutting device to move the cutting trajectory to the cutting line;

[0029] S630. Coincide the cutting trajectory with the cutting line to open a hole in the outer side wall of the fuselage.

[0030] Beneficial effects:

[0031] The method for opening a hole in the fuselage of the unmanned aerial vehicle provided by the present invention first manufactures a positioning template and a hole plate, and opens a reference hole on the hole plate; fixes and fits the positioning template to the inner side wall of the fuselage and simultaneously abuts against at least two positioning structures, determines the hole opening area on the outer side wall of the fuselage through the positions of the positioning structures, and fixes and fits the hole plate to the positioning template and corresponding to the hole opening area; drills corresponding positioning holes on the outer side wall of the fuselage through the reference holes, the positioning holes penetrate from the inner side wall of the fuselage to the outer side wall, then removes the positioning template from the inner side wall of the fuselage, and removes the hole plate from the positioning template; fits the hole plate to the outer side wall of the fuselage, aligns the positioning holes with the corresponding reference holes, and passes a positioning member through the positioning holes and the reference holes to position the hole plate; outlines a cutting line on the outer side wall of the fuselage based on the outer contour of the hole plate, and removes the hole plate after the outlining is completed; opens a hole on the outer side wall of the fuselage with the cutting line as the contour. This method is simple and convenient to operate, uses a positioning template and a hole plate in cooperation, and accurately opens a hole on the outer side wall of the fuselage according to the internal positioning reference of the fuselage of the unmanned aerial vehicle, effectively ensuring the positioning accuracy. Description of the drawings

[0032] Figure 1 is an exploded schematic diagram of part of the structure of an unmanned aerial vehicle in the prior art;

[0033] Figure 2 is a schematic flow chart of the method for opening a hole in the fuselage of the unmanned aerial vehicle provided by the present invention;

[0034] Figure 3 is a schematic diagram of forming a hole opening area in step S200 of the present invention;

[0035] Figure 4 is a schematic diagram of fixing and fitting the hole plate to the hole opening area in step S200 of the present invention;

[0036] Figure 5 It is a schematic diagram of the internal structure of the fuselage after step S300 of the present invention is completed;

[0037] Figure 6 It is a schematic diagram of the external structure of the fuselage corresponding to steps S400 to S500 of the present invention;

[0038] Figure 7 It is a schematic diagram of the external structure of the fuselage corresponding to step S600 of the present invention.

[0039] In the figure:

[0040] 1', fuselage; 2', landing gear; 3', slot hole;

[0041] 1, fuselage; 101, cutting line; 11, positioning structure; 12, positioning hole;

[0042] 2, positioning template; 21, reference line;

[0043] 3, hole plate; 31, reference hole;

[0044] 4, positioning member; 41, clamping portion. Specific Embodiments

[0045] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It can be understood that the specific embodiments described herein are only for explaining the present invention, rather than limiting the present invention. In addition, it should be noted that for the sake of description, only parts related to the present invention rather than all structures are shown in the drawings.

[0046] In the description of the present invention, unless otherwise clearly defined and limited, the terms "connected", "connected to", and "fixed" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0047] In the present invention, unless otherwise clearly specified and defined, the first feature being "on" or "under" the second feature may include direct contact between the first and second features, or may include the first and second features not being in direct contact but in contact through additional features therebetween. Moreover, the first feature being "above", "over" and "on top of" the second feature includes the first feature being directly above and obliquely above the second feature, or merely indicating that the horizontal height of the first feature is higher than that of the second feature. The first feature being "under", "beneath" and "underneath" the second feature includes the first feature being directly below and obliquely below the second feature, or merely indicating that the horizontal height of the first feature is less than that of the second feature.

[0048] In the description of this embodiment, the orientation or positional relationships such as "up", "down", "right", etc. are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of description and simplifying the operation, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be construed as a limitation of the present invention. In addition, the terms "first" and "second" are only used for distinction in description and have no special meaning.

[0049] This embodiment provides a method for opening holes in the fuselage of a drone. Refer to Figures 2 to 7 As shown, the method for opening holes in the fuselage of a drone is used to open holes in the fuselage 1 of the drone, and the interior of the fuselage 1 includes at least two positioning structures 11.

[0050] It is worth mentioning that the positioning structure 11 is a structural member inside the fuselage 1, which serves as a reference for determining the hole-opening area of the fuselage 1 in subsequent steps.

[0051] The method for opening holes in the fuselage of a drone mainly includes the following steps:

[0052] S100. Fabricate a positioning template 2 and a hole plate 3, and open a reference hole 31 on the hole plate 3;

[0053] S200. Fix and attach the positioning template 2 to the inner wall of the fuselage 1 and simultaneously abut against at least two positioning structures 11. Determine the hole-opening area on the outer wall of the fuselage 1 based on the positions of the positioning structures 11, and fix and attach the hole plate 3 to the positioning template 2 corresponding to the hole-opening area;

[0054] S300. Drill corresponding positioning holes 12 on the outer wall of the fuselage 1 through the reference hole 31. The positioning holes 12 penetrate from the inner wall of the fuselage 1 to the outer wall. Subsequently, remove the positioning template 2 from the inner wall of the fuselage 1 and remove the hole plate 3 from the positioning template 2;

[0055] S400. Attach the hole plate 3 to the outer wall of the fuselage 1, align the positioning holes 12 with the corresponding reference holes 31, and pass a positioning member 4 through the positioning holes 12 and the reference holes 31 to position the hole plate;

[0056] S500. Taking the outer contour of the orifice plate 3 as a reference, draw a cutting line 101 on the outer side wall of the fuselage 1. After the drawing is completed, remove the orifice plate 3.

[0057] S600. Using the cutting line 101 as a contour, open a hole on the outer side wall of the fuselage 1.

[0058] Specifically, in step S100, manufacturing the positioning template 2 mainly includes:

[0059] S111. Draw a template model on 3D software that is adapted to the inner side wall curvature of the fuselage 1.

[0060] S112. According to the template model, use a cutting machine to cut out the positioning template 2 on the plate.

[0061] The positioning template 2 is cut correspondingly according to the template model. The side wall that needs to fit with the inner side wall of the fuselage 1 is preferably set to match the inner side wall curvature of the fuselage 1, so that it can be more adapted to fit with the fuselage 1 in subsequent steps.

[0062] Specifically, in step S100, manufacturing the orifice plate 3 mainly includes:

[0063] S121. Determine the size and outer contour of the hole to be opened on the outer side wall of the fuselage 1.

[0064] S122. According to the size and outer contour of the hole to be opened on the outer side wall of the fuselage 1, use a cutting machine to cut out the orifice plate 3 on the plate.

[0065] Specifically, the size and outer contour of the orifice plate 3 are the same as the size and outer contour of the hole to be opened on the outer side wall of the fuselage 1.

[0066] As a preferred embodiment, in step S112, the positioning template 2 is cut out on the plate by a laser cutting machine; in step S122, the orifice plate 3 is cut out on the plate by a laser cutting machine. The laser cutting method has the advantages of good processing quality, low labor cost, high cutting accuracy, and low processing cost.

[0067] Specifically, in step S100, at least two reference holes 31 are opened on the orifice plate 3. With this setting, when using the positioning member 4 to penetrate the positioning holes 12 in subsequent step S400, two or more positioning holes 12 can prevent the orifice plate 3 from rotating relative to the fuselage 1, further ensuring the reliable positioning of the orifice plate 3.

[0068] Specifically, in step S200, the positioning template 2 is fixedly attached to the inner side wall of the fuselage 1 and simultaneously abuts against at least two positioning structures 11. The opening area of the outer side wall of the fuselage 1 is determined by the positions of the positioning structures 11. For easy understanding, it can be combined with Figure 3As shown by the arrow indication, taking the positions of the two positioning structures 11 as a reference, the opening area of the outer wall of the fuselage 1 can be roughly defined. Figure 3 Inside the opening area, a reference line 21 can be generated in combination with the size and contour of the opening on the fuselage 1 in the UAV drawing. Subsequently, the hole plate 3 can be fixedly attached to the reference line 21 of the positioning template 2.

[0069] It is worth mentioning that the above content is only an exemplary description of the positioning of the hole plate 3, and the positioning of the hole plate 3 is not limited to Figure 3 the structural limitations in, and no more limitations will be made here.

[0070] Further, in step S200, the positioning template 2 is adhesively fixed on the inner side wall of the fuselage 1; the hole plate 3 is adhesively fixed on the positioning template 2. With such a setting, it can be ensured that the positioning template 2 and the hole plate 3 can be firmly positioned during the drilling process in step S300, and the positioning template 2 and / or the hole plate 3 can be prevented from moving relative to the fuselage 1.

[0071] Specifically, in step S300, using a drilling device, Figure 4 drill through the reference hole 31 and the positioning template 2 in the direction of the arrow in and drill positioning holes 12 on the outer side wall of the fuselage 1. The aperture of the positioning holes 12 is the same as that of the reference hole 31.

[0072] Specifically, the side end face of the hole plate 3 facing away from the side that fits with the positioning template 2 is the end face that needs to fit with the outer side wall of the fuselage 1 in step S400. In this way, it can be ensured that the fitting direction of the hole plate 3 is correct and the hole plate 3 is prevented from being attached in the wrong direction.

[0073] Preferably, the side end face of the hole plate 3 facing away from the side that fits with the positioning template 2 is also processed into a curved surface that matches the curvature of the outer side face of the fuselage 1. With such a setting, the fit between the hole plate 3 and the outer side wall of the fuselage 1 in step S400 is closer and more reliable, the shape is more adaptable, and the process of outlining the cutting line 101 in step S500 can be more reliable and stable.

[0074] Specifically, two reference holes 31 are provided on the hole plate 3. With such a setting, that is, two corresponding positioning holes 12 will be drilled on the fuselage 1 in step S300, and the two positioning holes 12 are arranged in one-to-one correspondence with the two reference holes 31.

[0075] In step S400, the positioning member 4 is set as a positioning clip, and the positioning clip includes two clamping portions 41. Each clamping portion 41 passes through the corresponding positioning hole 12 and reference hole 31. The hole plate 3 can be positioned on the outer side wall of the fuselage 1 under the clamping action of the two clamping portions 41. Specifically, an elastic member (not shown) is provided on the positioning clip, and the elastic member can make the two clamping portions 41 always have a tendency to approach and clamp objects. Specifically, the clamping portions 41, the reference holes 31, and the positioning holes 12 are in a one-to-one correspondence relationship, and each clamping portion 41 passes through the corresponding positioning hole 12 and reference hole 31. After the two clamping portions 41 pass through, under the action of the elastic member, the two clamping portions 41 approach each other and are in a clamping state, so that the hole plate 3 can be firmly clamped and positioned on the outer side wall of the fuselage 1.

[0076] Specifically, in step S400, the hole plate 3 is adhesively fixed to the outer side wall of the fuselage 1 by an adhesive. With this setting, it can be ensured that the hole plate 3 can be firmly positioned during the process of passing through the positioning member 4 and the process of drawing the line in step S500, and the hole plate 3 can be prevented from moving relative to the fuselage 1.

[0077] In some other alternative embodiments, the positioning member 4 can also be set as a positioning pin (not shown). The positioning pin, the reference hole 31, and the positioning hole 12 are in a one-to-one correspondence relationship. The positioning pin passes through the corresponding reference hole 31 and positioning hole 12, and can also play the role of positioning the hole plate 12. The fit relationship between the positioning pin and the positioning hole 12 and the reference hole 31 is preferably set as an interference fit.

[0078] Specifically, Figure 7 The dotted line frame in the figure is the outlined cutting line 101. In step S600, taking the cutting line 101 as the contour, opening a hole in the outer side wall of the fuselage 1 specifically includes:

[0079] S610: Use a cutting device to cut into the outer side wall of the fuselage 1 inside the cutting line 101;

[0080] S620: Move the cutting device so that the cutting trajectory moves to the cutting line 101;

[0081] S630: Coincide the cutting trajectory with the cutting line 101 to open a hole in the outer side wall of the fuselage 1.

[0082] Specifically, the cutting device first cuts into the outer side wall of the fuselage 1 inside the cutting line 101, avoiding the cutting tool of the cutting device cutting the part outside the cutting line 101 and not damaging the structure of other parts of the fuselage 1. When the cutting device cuts into the outer side wall of the fuselage 1, during the cutting movement, it gradually approaches the cutting line 101 and finally moves to the cutting line 101. Subsequently, the cutting device moves along the cutting line 101, that is, the cutting trajectory coincides with the cutting line 101, and a hole is successfully opened in the outer side wall of the fuselage 1.

[0083] In summary, the method is simple and convenient to operate. By using the positioning template 2 and the hole plate 3 in combination, positioning holes 12 are pre-opened from the inside to the outside of the fuselage 1 of the UAV according to the internal positioning reference of the fuselage 1 of the UAV. Subsequently, the required hole structure is accurately opened on the outer side wall of the fuselage 1 by means of the hole plate 3, the positioning holes 12 and the positioning member 4, and the positioning accuracy is effectively guaranteed.

[0084] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, rather than limiting the implementation manners of the present invention. For those of ordinary skill in the art, various obvious changes, re-adjustments and substitutions can be made without departing from the protection scope of the present invention. It is not necessary and impossible to enumerate all the implementation manners here. Any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention shall be included in the protection scope of the claims of the present invention.

Claims

1. A method for opening holes in the fuselage of a drone, which is used to open holes in the fuselage (1) of the drone. The interior of the fuselage (1) includes at least two positioning structures (11), and is characterized in that, The method for opening holes in the drone fuselage mainly includes the following steps: S100. Make a positioning template (2) and a hole plate (3), and open a reference hole (31) on the hole plate (3); S200. Fix and attach the positioning template (2) to the inner side wall of the fuselage (1) and simultaneously abut against at least two of the positioning structures (11). Determine the hole-opening area on the outer side wall of the fuselage (1) through the positions of the positioning structures (11), and fix and attach the hole plate (3) to the positioning template (2) corresponding to the hole-opening area; S300. Drill positioning holes (12) on the outer side wall of the fuselage (1) corresponding to the reference hole (31) through the reference hole (31). The positioning holes (12) penetrate from the inner side wall of the fuselage (1) to the outer side wall. Subsequently, remove the positioning template (2) from the inner side wall of the fuselage (1), and remove the hole plate (3) from the positioning template (2); S400. Attach the hole plate (3) to the outer side wall of the fuselage (1), align the positioning holes (12) with the corresponding reference holes (31), and pass a positioning member (4) through the positioning holes (12) and the reference holes (31) to position the hole plate (3); S500. Outline a cutting line (101) on the outer side wall of the fuselage (1) based on the outer contour of the hole plate (3). After outlining, remove the hole plate (3); S600. Open a hole on the outer side wall of the fuselage (1) with the cutting line (101) as the contour.

2. The method for opening holes in the fuselage of an unmanned aerial vehicle according to claim 1, wherein In step S100, making the positioning template (2) mainly includes: S111. Draw a template model on 3D software that fits the curvature of the inner side wall of the fuselage (1); S112. Cut out the positioning template (2) on a plate using a cutting machine according to the template model.

3. The method for opening holes in the fuselage of a drone according to claim 2, wherein, In step S100, making the hole plate (3) mainly includes: S121. Determine the size and outer contour of the hole to be opened on the outer side wall of the fuselage (1); S122. Cut out the hole plate (3) on a plate using a cutting machine according to the size and outer contour of the hole to be opened on the outer side wall of the fuselage (1).

4. The method for opening holes in the fuselage of a drone according to claim 3, characterized in that, In step S112, cut out the positioning template (2) on the plate using a laser cutting machine; in step S122, cut out the hole plate (3) on the plate using a laser cutting machine.

5. The method for opening holes in the fuselage of a drone according to claim 1, wherein, In step S100, open at least two of the reference holes (31) on the hole plate (3).

6. The method for opening holes in the fuselage of a drone according to claim 1, wherein, In step S200, the positioning template (2) is adhesively fixed to the inner side wall of the fuselage (1) with an adhesive; the hole plate (3) is adhesively fixed to the positioning template (2) with an adhesive.

7. The method for opening holes in the fuselage of a drone according to claim 1, wherein In step S300, use a drilling device to pass through the reference hole (31) and the positioning template (2) and drill the positioning holes (12) on the outer side wall of the fuselage (1). The aperture of the positioning holes (12) is the same as that of the reference hole (31).

8. The method for opening holes in the fuselage of a drone according to claim 1, characterized in that In step S400, the hole plate (3) is adhesively fixed to the outer side wall of the fuselage (1) with an adhesive.

9. The method for opening holes in the fuselage of a drone according to claim 5, characterized in that, Two of the reference holes (31) are formed in the orifice plate (3). In step S400, the positioning member (4) is set as a positioning clamp. The positioning clamp includes two clamping portions (41). Each clamping portion (41) passes through the corresponding positioning hole (12) and the reference hole (31). The orifice plate (3) can be positioned on the outer side wall of the fuselage (1) under the clamping action of the two clamping portions (41).

10. The method for opening holes in the fuselage of a drone according to claim 1, wherein, Step S600 specifically includes: S610: Use a cutting device to cut into the outer side wall of the fuselage (1) inside the cutting line (101). S620: Move the cutting device so that the cutting path moves to the cutting line (101). S630: Coincide the cutting path with the cutting line (101) to form an opening on the outer side wall of the fuselage (1).

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