Semi-automatic alignment aircraft skin chemical milling contour shifting tool
By designing a semi-automatic alignment of aircraft skin milling profile shift tool, the principle of magnets attracting and repulsing each other and the design of roller return springs is solved, and the problem of precise replication of the inner surface of the skin milling step profile in the prior art is difficult to accurately replicate, realizing the precise copying and repair efficiency of the outer surface of the skin.
Patent Information
- Application Number
- CN202420896173.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-26
- Publication Date
- 2025-05-02
- Estimated Expiration
- 2034-04-26
AI Technical Summary
The prior art is difficult to accurately copy the contour of the melting step on the inner surface of the aircraft skin to the outer surface of the skin, resulting in the fastener installation not being firmly installed during the external reinforcement of the skin, which affects the repair effect.
A semi-automatic alignment of the aircraft skin milling profile shift tool is designed. Using the principle of magnet attracting each other with different poles and repulsing each other with the same poles, the active end assembly and the driven end assembly are semi-automatically aligned. Combined with the design of rollers and return springs, the precise replication of the contour of the milling step is ensured.
It realizes accurate replication of the outline of the milling step on the outer surface of the aircraft skin, improves the efficiency and accuracy of the external reinforcement of the skin, and ensures that the fasteners are installed firmly.
Smart Images
Figure CN222818442U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft ground maintenance, in particular to a semi-automatic alignment aircraft skinning milling contour transfer tool. Background Art
[0002] The fuselage skin of the aircraft is made of aluminum alloy. All aircraft skins leaving the factory must undergo a chemical milling process, that is, while ensuring the strength of the fuselage skin, the local skin thickness is reduced as needed, and several relatively thin milled areas are produced on the inner surface of the skin by chemical milling. After this treatment, the overall weight of the aircraft can be greatly reduced. At the same time, the milled skin can effectively control cracks from overflowing the milled area, thereby achieving the effect of controlling the scope of the cracks and greatly improving the safety of the aircraft.
[0003] When the aircraft skin is hit and the dents cannot be repaired, the most efficient way to deal with it is to perform external skin reinforcement repair, that is, to cut off the damaged skin and replace the reinforced skin. When performing external skin reinforcement repair, in order to avoid destroying the function of the milling area to control the crack range, the fasteners of the reinforcement repair should avoid the milling step as much as possible. If the fastener end sits on the milling step, the fastener will be installed unsecured, resulting in the failure of the external skin reinforcement repair.
[0004] Since the fuselage is a closed box, when performing external skin reinforcement repairs, maintenance personnel outside the fuselage cannot identify the position of the milling steps in the milling area on the inner surface of the skin. Therefore, it is necessary to find a way to copy the contour line of the milling steps in the inner area of the skin to the outer surface of the skin. At present, the method adopted by maintenance personnel is that one person holds a magnet inside the fuselage and moves the magnet slowly along the edge of the milling step in the milling area, and another person holds a magnet at a corresponding position outside the fuselage through the skin to correspond to the internal magnet, and uses the adsorption principle of the magnet for adsorption positioning, and then the external maintenance personnel use a scribing pen to draw the corresponding points, so as to copy the approximate outline of the milling steps in the milling area of the skin to the outer surface of the skin. This method requires two people inside and outside to maintain good communication at all times to confirm the next moving direction, which is inefficient. Moreover, since the external scribing pen is omnidirectional and free to move, it can only roughly determine the position of the milling area, but cannot accurately draw the edge contour of the milling step, and the positioning is inaccurate. Utility Model Content
[0005] In view of the deficiencies in the prior art, the utility model provides a semi-automatic alignment aircraft skin milling contour transfer tool to overcome the deficiencies in the prior art.
[0006] In order to achieve the above objectives, the present invention is implemented through the following technical solutions:
[0007] A semi-automatic alignment aircraft skinning milling contour transfer tool, comprising an active end component and a driven end component that are relatively arranged;
[0008] The active end assembly comprises an active end non-magnetic shell, an active end magnet group arranged in the active end non-magnetic shell, and an active end positioning rod arranged on the outer wall of the active end non-magnetic shell;
[0009] The driven end assembly comprises a driven end non-magnetic shell, a driven end magnet group arranged in the driven end non-magnetic shell, and a driven end scribing pen arranged on the outer wall of the driven end non-magnetic shell;
[0010] The active end magnet group corresponds to the driven end magnet group; the active end positioning rod corresponds to the driven end scoring pen.
[0011] Furthermore, the active end magnet group includes an active end first magnet, an active end second magnet and an active end third magnet; the active end first magnet, the active end second magnet and the active end third magnet are spaced apart in an isosceles triangle, and the S poles of the active end first magnet and the active end second magnet face the inside of the active end magnet assembly groove, while the N pole of the active end third magnet faces the inside of the active end magnet assembly groove.
[0012] Furthermore, the driven end magnet group includes a first driven end magnet, a second driven end magnet and a third driven end magnet; the first driven end magnet, the second driven end magnet and the third driven end magnet are spaced apart in an isosceles triangle, and the N poles of the first driven end magnet and the second driven end magnet face the inside of the driven end magnet assembly groove, while the S pole of the third driven end magnet faces the inside of the driven end magnet assembly groove, and the first driven end magnet, the second driven end magnet and the third driven end magnet correspond one-to-one to the first active end magnet, the second active end magnet and the third active end magnet, respectively.
[0013] Preferably, the active end positioning rod is installed outside the active end non-magnetic shell through an active end positioning frame, and a roller is rotatably provided on one end of the active end positioning rod facing the milling area.
[0014] Preferably, the driven end scoring pen is installed on the outside of the driven end non-magnetic shell through a driven end positioning frame; the driven end positioning frame includes a driven end positioning plate and a driven end limiting plate arranged in parallel; the driven end positioning plate is provided with a pen loading hole for the driven end scoring pen to be inserted; the driven end limiting plate is provided with a blind hole corresponding to the pen loading hole, and a reset spring is provided in the blind hole of the driven end limiting plate; the rear end of the driven end scoring pen is inserted into the blind hole of the driven end limiting plate from the pen loading hole and resists the reset spring.
[0015] Preferably, an active end magnet assembly groove is provided on the end surface of the active end non-magnetic shell facing the inner surface of the skin, and the active end magnet assembly groove is installed in the active end magnet group.
[0016] Preferably, an active end ball groove is further provided on the end surface of the active end non-magnetic shell facing the inner surface of the skin, and the active end ball groove is equipped with an active end ball.
[0017] Preferably, a driven end magnet assembly groove is provided on the end surface of the driven end non-magnetic shell facing the outer surface of the skin, and the driven end magnet assembly groove is installed in the driven end magnet group.
[0018] Preferably, a driven end ball groove is further provided on the end surface of the driven end non-magnetic shell facing the inner surface of the skin, and the driven end ball is assembled in the driven end ball groove.
[0019] Preferably, the third magnet at the active end and the positioning rod at the active end are respectively located on both sides of the line connecting the first magnet at the active end and the second magnet at the active end; the third magnet at the driven end and the scratching pen at the driven end are respectively located on both sides of the line connecting the first magnet at the driven end and the second magnet at the driven end.
[0020] Compared with the prior art, the beneficial effects of the utility model are:
[0021] 1) The present invention relates to a semi-automatic alignment tool for aircraft skinning milling contour transfer, wherein the S poles of the first magnet at the active end and the second magnet at the active end face the inside of the active end magnet assembly slot, while the N pole of the third magnet at the active end faces the inside of the active end magnet assembly slot; the N poles of the first magnet at the driven end and the second magnet at the driven end face the inside of the driven end magnet assembly slot, while the S pole of the third magnet at the driven end faces the inside of the driven end magnet assembly slot, and the first magnet at the driven end, the second magnet at the driven end and the third magnet at the driven end correspond to the first magnet at the active end, the second magnet at the active end and the third magnet at the active end, respectively; by utilizing the principle that opposite poles of magnets attract each other and like poles repel each other, the semi-automatic alignment effect of the active end component and the driven end component is achieved, and the alignment efficiency is high.
[0022] 2) In this case, a semi-automatic alignment tool for the milling contour of aircraft skin is provided, and a small-radius roller is provided on the active end positioning rod. The roller always fits the edge of the milling step contour during movement, and can better fit the corner of the milling step contour, so that the milling step contour drawn on the outer surface of the skin is more accurate.
[0023] 3) In this case, a semi-automatic alignment tool for aircraft skin milling contour transfer is disclosed, wherein the driven end positioning frame includes a driven end positioning plate and a driven end limiting plate; the driven end positioning plate is used to install a driven end scoring pen; the driven end limiting plate is provided with a blind hole, in which a return spring is provided, and the rear end of the driven end scoring pen abuts against the return spring, and under the action of the return spring, the tip of the driven end scoring pen keeps in contact with the outer surface of the skin to avoid unclear or broken lines.
[0024] 4) In this case, a semi-automatic alignment aircraft skin milling contour transfer tool is provided with multiple rollers on both the active end component and the driven end component to ensure that the active end component and the driven end component move more smoothly on the aircraft skin surface.
[0025] In order to more clearly understand the present invention, the following will describe the preferred implementation modes of the present invention in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS
[0026] Figure 1 , Figure 2 This is a reference diagram of the use state of the utility model;
[0027] Figure 3 , Figure 4 It is a schematic diagram of the mechanism of the active end component of the utility model;
[0028] Figure 5 , Figure 6 It is a schematic diagram of the mechanism of the driven end assembly of the utility model;
[0029] Figure 7 It is an exploded view of the utility model.
[0030] Figure ID:
[0031] 1-active end assembly, 2-driven end assembly, 9-aircraft skin; 11-active end non-magnetic shell, 13 active end positioning rod, 14-active end ball; 121-active end first magnet, 122-active end second magnet, 123-active end third magnet, 131-roller; 21-driven end non-magnetic shell, 23-driven end scribing pen, 24-driven end ball; 221-driven end first magnet, 222-driven end second magnet, 223-driven end third magnet; 251-driven end positioning plate, 252-driven end limit plate, 253-reset spring. DETAILED DESCRIPTION
[0032] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, 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 therefore cannot be understood as a limitation on the present invention. In the description of the present invention, unless otherwise specified, "multiple" means two or more.
[0033] In addition, if there are terms such as "first" and "second", they are only used for descriptive purposes, mainly to distinguish different devices, elements or components (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance and quantity of the indicated devices, elements or components, and cannot be understood as indicating or implying relative importance.
[0034] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installed", "provided with", "mounted / connected", "connected", etc. should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of two components; for ordinary technicians in this field, the specific meanings of the above terms in the utility model can be understood according to specific circumstances.
[0035] See also Figure 1-7 The utility model provides a semi-automatic alignment aircraft skin milling contour transfer tool, comprising an active end component (1) used on the inner surface of the aircraft skin 9 and a corresponding driven end component (2) used on the outer surface of the aircraft skin 9.
[0036] The active end assembly (1) comprises an active end non-magnetic shell (11), an active end magnet group arranged in the active end non-magnetic shell (11), and an active end positioning rod (13) arranged on the outer wall of the active end non-magnetic shell (11).
[0037] The active end non-magnetic shell (11) has an active end magnet assembly groove on its end surface facing the inner surface of the skin, and an active end magnet group is installed in the active end magnet assembly groove.
[0038] The active end magnet group comprises an active end first magnet (121), an active end second magnet (122) and an active end third magnet (123); the active end first magnet (121), the active end second magnet (122) and the active end third magnet (123) are spaced apart in an isosceles triangle, and the S poles of the active end first magnet (121) and the active end second magnet (122) face the inside of the active end magnet assembly groove, while the N pole of the active end third magnet (123) faces the inside of the active end magnet assembly groove.
[0039] Preferably, in this embodiment, the active end non-magnetic housing (11) is provided with three active end magnet assembly grooves, and the three active end magnet assembly grooves are respectively equipped with an active end first magnet (121), an active end second magnet (122) and an active end third magnet (123).
[0040] The active end positioning rod (13) is installed outside the active end non-magnetic housing (11) through an active end positioning frame, and a roller (131) is rotatably provided on one end of the active end positioning rod (13) facing the milling area.
[0041] Preferably, in this embodiment, an active end ball groove is provided on the end surface of the active end non-magnetic shell (11) facing the inner surface of the skin, and an active end ball (14) is mounted in the active end ball groove.
[0042] Preferably, in this embodiment, there are three active end ball grooves, three active end balls (14) are respectively installed in the three active end ball grooves, and the three active end ball grooves and the three active end magnet assembly grooves are staggered.
[0043] The driven end assembly (2) comprises a driven end non-magnetic shell (21), a driven end magnet group arranged in the driven end non-magnetic shell (21), and a driven end scribing pen (23) arranged on the outer wall of the driven end non-magnetic shell (21).
[0044] The driven end non-magnetic housing (21) is provided with a driven end magnet assembly groove on its end surface facing the outer surface of the skin, and a driven end magnet group is installed in the driven end magnet assembly groove.
[0045] The driven end magnet group comprises a driven end first magnet (221), a driven end second magnet (222) and a driven end third magnet (223); the driven end first magnet (221), the driven end second magnet (222) and the driven end third magnet (223) are arranged in an isosceles triangle at intervals, and the N poles of the driven end first magnet (221) and the driven end second magnet (222) face the inside of the driven end magnet assembly groove, while the S pole of the driven end third magnet (223) faces the inside of the driven end magnet assembly groove, and the driven end first magnet (221), the driven end second magnet (222) and the driven end third magnet (223) correspond to the active end first magnet (121), the active end second magnet (122) and the active end third magnet (123) one by one.
[0046] Preferably, in this embodiment, the driven end non-magnetic housing (21) is provided with three driven end magnet assembly grooves, and the three driven end magnet assembly grooves are respectively equipped with a driven end first magnet (221), a driven end second magnet (222) and a driven end third magnet (223).
[0047] The driven end scribing pen (23) is installed outside the driven end non-magnetic housing (21) through a driven end positioning frame, and the driven end scribing pen (23) corresponds to the driving end positioning rod (13).
[0048] Preferably, in this embodiment, a driven end ball groove is provided on the end surface of the driven end non-magnetic shell (21) facing the inner surface of the skin, and a driven end ball (24) is mounted in the driven end ball groove.
[0049] Preferably, in this embodiment, there are three driven end ball grooves in total, three driven end balls (24) are respectively mounted in the three driven end ball grooves, and the three driven end ball grooves and the three driven end magnet mounting grooves are staggered.
[0050] Furthermore, the driven end positioning frame comprises a driven end positioning plate (251) and a driven end limiting plate (252) arranged in parallel; the driven end positioning plate (251) is provided with a pen-loading hole for inserting the driven end scribing pen (23); the driven end limiting plate (252) is provided with a blind hole corresponding to the pen-loading hole, and a return spring (253) is arranged in the blind hole of the driven end limiting plate (252). The rear end of the driven end scribing pen (23) is inserted from the pen-loading hole into the blind hole of the driven end limiting plate (252) and abuts against the return spring (253), and the front end of the driven end scribing pen (23) faces the outer surface of the skin. Under the action of the return spring (253), the pen tip of the driven end scribing pen (23) keeps in contact with the outer surface of the skin, so as to avoid unclear or broken lines.
[0051] Preferably, in this embodiment, the active end third magnet (123) and the active end positioning rod (13) are respectively located on both sides of the line connecting the active end first magnet (121) and the active end second magnet (122).
[0052] Preferably, in this embodiment, the driven end third magnet (223) and the driven end scribing pen (23) are respectively located on both sides of the line connecting the driven end first magnet (221) and the driven end second magnet (222).
[0053] Working principle:
[0054] 1. In the case of alignment, the first magnet (121) at the active end is aligned with the first magnet (221) at the passive end, the second magnet (122) at the active end is aligned with the second magnet (222) at the passive end, the third magnet (123) at the active end is aligned with the third magnet (223) at the passive end, and the active end positioning rod (13) is aligned with the passive end marking pen (23); according to the principle that opposite poles of magnets attract each other and like poles repel each other, the active end magnet group and the passive end magnet group are mutually attracted, and the staff moves the active end assembly (1) in the milling area, and allows the roller (131) on the active end positioning rod (13) to always fit the edge of the milling step contour during the movement, so that the passive end marking pen (23) can draw the milling step contour on the outer surface of the skin. Since the roller (131) of the active end positioning rod (13) has a smaller radius, it can better fit the corner of the milling step contour, and the milling step contour drawn on the outer surface of the skin is more accurate.
[0055] 2. In the case of misalignment, if the third magnet (223) at the driven end is misaligned to the position of the first magnet (121) or the second magnet (122) at the driven end, magnets with the same poles will repel each other (two magnets produce repulsive force and only one magnet produces attractive force). Maintenance personnel can clearly sense the magnetic force of mutual repulsion between the driving end component (1) and the driven end component (2), and can easily correct the error, turning the misalignment into the above-mentioned alignment.
[0056] Compared with the prior art, the present invention is a semi-automatic alignment tool for aircraft skinning milling contour transfer, which utilizes the principle that opposite poles of magnets attract each other and like poles repel each other, so that the active end component and the driven end component are semi-automatically aligned with high efficiency.
[0057] The above-mentioned embodiments only express several implementation methods of the utility model, and the description is relatively specific and detailed, but it cannot be understood as limiting the scope of the utility model patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the utility model, which all belong to the protection scope of the utility model.
Claims
1. A semi-automatic positioning aircraft skin milling contour transfer tool, comprising an active end component (1) and a driven end component (2) arranged relatively to each other, characterized in that: The active end assembly (1) comprises an active end non-magnetic shell (11), an active end magnet group arranged in the active end non-magnetic shell (11), and an active end positioning rod (13) arranged on the outer wall of the active end non-magnetic shell (11); The driven end assembly (2) comprises a driven end non-magnetic shell (21), a driven end magnet group arranged in the driven end non-magnetic shell (21), and a driven end scribing pen (23) arranged on the outer wall of the driven end non-magnetic shell (21); The active end magnet group corresponds to the driven end magnet group; the active end positioning rod (13) corresponds to the driven end scribing pen (23).
2. The semi-automatic alignment aircraft skin milling contour transfer tool according to claim 1 is characterized by: The active end magnet group comprises an active end first magnet (121), an active end second magnet (122) and an active end third magnet (123); the active end first magnet (121), the active end second magnet (122) and the active end third magnet (123) are arranged in an isosceles triangle in intervals, and the S poles of the active end first magnet (121) and the active end second magnet (122) face the inside of the active end magnet assembly slot, while the N pole of the active end third magnet (123) faces the inside of the active end magnet assembly slot.
3. The semi-automatic alignment aircraft skin milling contour transfer tool according to claim 2 is characterized by: The driven end magnet group comprises a driven end first magnet (221), a driven end second magnet (222) and a driven end third magnet (223); The first magnet (221) at the driven end, the second magnet (222) at the driven end and the third magnet (223) at the driven end are arranged in an isosceles triangle at intervals, and the N poles of the first magnet (221) at the driven end and the second magnet (222) at the driven end face the interior of the magnet assembly groove at the driven end, while the S pole of the third magnet (223) at the driven end faces the interior of the magnet assembly groove at the driven end, and the first magnet (221) at the driven end, the second magnet (222) at the driven end and the third magnet (223) at the driven end correspond to the first magnet (121) at the driven end, the second magnet (122) at the driven end and the third magnet (123) at the driven end, respectively.
4. The semi-automatic alignment aircraft skin milling contour transfer tool according to claim 3 is characterized by: The active end positioning rod (13) is installed outside the active end non-magnetic housing (11) via an active end positioning frame, and a roller (131) is rotatably provided on one end of the active end positioning rod (13) facing the milling area.
5. The semi-automatic alignment aircraft skin milling contour transfer tool according to claim 3 is characterized by: The driven end marking pen (23) is installed on the outside of the driven end non-magnetic shell (21) through a driven end positioning frame; the driven end positioning frame comprises a driven end positioning plate (251) and a driven end limiting plate (252) arranged in parallel; the driven end positioning plate (251) is provided with a pen loading hole for the driven end marking pen (23) to be inserted; the driven end limiting plate (252) is provided with a blind hole corresponding to the pen loading hole, and a return spring (253) is provided in the blind hole of the driven end limiting plate (252); the rear end of the driven end marking pen (23) is inserted into the blind hole of the driven end limiting plate (252) from the pen loading hole and presses against the return spring (253).
6. The semi-automatic alignment aircraft skin milling contour transfer tool according to claim 3 is characterized by: An active end magnet assembly groove is arranged on the end surface of the active end non-magnetic shell (11) facing the inner surface of the skin, and an active end magnet group is installed in the active end magnet assembly groove.
7. The semi-automatic alignment aircraft skin milling contour transfer tool according to claim 3 is characterized by: An active end ball groove is also provided on the end surface of the active end non-magnetic shell (11) facing the inner surface of the skin, and an active end ball (14) is mounted in the active end ball groove.
8. The semi-automatic alignment aircraft skin milling contour transfer tool according to claim 3 is characterized by: A driven end magnet assembly groove is provided on the end surface of the driven end non-magnetic shell (21) facing the outer surface of the skin, and a driven end magnet group is installed in the driven end magnet assembly groove.
9. The semi-automatic alignment aircraft skin milling contour transfer tool according to claim 3, characterized in that: A driven end ball groove is also provided on the end surface of the driven end non-magnetic housing (21) facing the inner surface of the skin, and a driven end ball (24) is mounted in the driven end ball groove.
10. The semi-automatic alignment aircraft skin milling contour transfer tool according to claim 3, characterized in that: The active end third magnet (123) and the active end positioning rod (13) are respectively located on both sides of the line connecting the active end first magnet (121) and the active end second magnet (122); the passive end third magnet (223) and the passive end scribing pen (23) are respectively located on both sides of the line connecting the passive end first magnet (221) and the passive end second magnet (222).