Assembly fixture and assembly method for aircraft hood

Abstract

The invention relates to the technical field of aircraft assembly, and provides an assembly fixture and an assembly method.The assembly fixture of the aircraft engine hood comprises a bottom supporting frame, a front supporting assembly, a rear supporting assembly and a partition plate assembly, the front supporting assembly is detachably arranged on the bottom supporting frame and is in sliding fit with the bottom supporting frame, and the rear supporting assembly is detachably arranged on the rear supporting assembly; the front supporting assembly is used for supporting and limiting the front engine hood. The rear supporting assembly is detachably arranged on the bottom supporting frame and is in sliding fit with the bottom supporting frame, and the rear supporting assembly is used for supporting and limiting the rear engine hood; the partition plate assembly is detachably arranged between the front supporting assembly and the rear supporting assembly, the partition plate assembly is provided with a limiting contour matched with the engine hood, and the limiting contour is used for supporting and limiting the engine hood. According to the assembling fixture of the aircraft engine hood, by arranging the front supporting assembly, the rear supporting assembly and the partition plate assembly, a steel structure and a contour clamping plate can be omitted, and the assembling efficiency of the engine hood is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft assembly, and particularly relates to an assembly jig and an assembly method for an aircraft engine hood. Background Art

[0002] Aircraft have a large number of parts and the assembly process is quite complex. Among them, the material of the aircraft engine hood is relatively soft and is prone to deformation during the assembly process. Moreover, its assembly accuracy requirements are relatively high, so relatively high requirements are also put forward for the jig assisting its assembly. The traditional assembly jig for the aircraft engine hood has too many jig parts. Generally, complex steel structures need to be arranged inside the aircraft engine hood to support the engine hood from the inside out. At the same time, multiple external contour clamping plates are also required for pulling to limit the position of the engine hood. The processes such as disassembly, assembly, and debugging of this structure are complicated, and it can only be used for one aircraft at a time. The entire assembly process wastes a lot of time, manpower, and material resources, which seriously affects the subsequent assembly work of the aircraft and seriously delays the offline time of the aircraft. Summary of the Invention

[0003] The first aspect of the present invention provides an assembly jig for an aircraft engine hood, which is used to solve the defect that the existing assembly jig needs to be equipped with complex steel structures. By supporting and limiting the engine hood through the front support assembly, the rear support assembly, and the partition assembly, the steel structures and multiple contour clamping plates for support can be eliminated, and the overall assembly efficiency on the aircraft engine hood assembly line can be improved.

[0004] The second aspect of the present invention provides an assembly method for an aircraft engine hood.

[0005] The assembly jig for the aircraft engine hood provided by the present invention includes: A bottom support frame; A front support assembly, detachably arranged on the bottom support frame and slidably cooperating with the bottom support frame, and the front support assembly is used to support and limit the front engine hood; A rear support assembly, detachably arranged on the bottom support frame and slidably cooperating with the bottom support frame, and the rear support assembly is used to support and limit the rear engine hood; A partition assembly, detachably arranged between the front support assembly and the rear support assembly, and the partition assembly is provided with a limiting contour adapted to the engine hood, and the limiting contour is used to support and limit the engine hood.

[0006] According to the assembly jig for the aircraft engine hood provided by the present invention, the partition assembly includes: A base plate, detachably arranged between the front support assembly and the rear support assembly, and a contour through groove is provided on the base plate; A front contour card member is arranged on a side of the base plate facing the front hood and is arranged on the outside of the front hood. The edge contour of the front contour card member is adapted to the outer contour of the front hood. The front contour card member matches the contour through groove to support and limit the front hood. The rear contour cardboard component is arranged on the side of the substrate facing the rear engine hood and on the outer side of the rear engine hood. The edge contour of the rear contour cardboard component is adapted to the outer contour of the rear engine hood, and the rear contour cardboard component matches the contour through groove to support and limit the rear engine hood.

[0007] According to the assembly jig of the aircraft engine cover provided by the present invention, the rear profile card plate component comprises: A rear contour card plate, wherein the edge contour of the rear contour card plate is adapted to the outer contour of the rear engine hood, and the rear contour card plate matches the contour through groove, so as to support and limit the rear engine hood; a plurality of waist-shaped holes are arranged at intervals on the rear contour card plate, and the axes of the waist-shaped holes face the rear engine hood, and a limiting rod matching the waist-shaped holes is provided on the base plate; A locking member is fixed to the base plate and abuts against a side of the rear contour card plate away from the rear engine cover. The locking member is used to push the rear contour card plate component to move along the axial direction of the waist-shaped hole.

[0008] According to the assembly jig of the aircraft engine cowl provided by the present invention, the front support assembly comprises: A front support frame is detachably arranged at the front end of the bottom support frame and slidably cooperates with the bottom support frame; A front support block is detachably mounted on the bottom support frame and slidably cooperates with the bottom support frame and is located between the front support frame and the partition assembly. A limiting portion is provided on the front support block. The shape of the limiting portion matches the shape of the engine hood lamp holder. The limiting portion is used to limit the movement of the front engine hood along its own axis direction. A front support card plate is slidably connected to the front support frame at one end and connected to the partition assembly at the other end. The contour edge of the front support card plate is adapted to the outer contour of the front engine hood.

[0009] According to the assembly jig of the aircraft engine cowl provided by the present invention, the front support assembly further comprises a plurality of front pulling members, the front pulling members are arranged at intervals on the front support card plate and are detachably connected to the front engine cowl.

[0010] According to the assembly jig of the aircraft engine cowl provided by the present invention, the rear support assembly comprises: A rear support frame, detachably arranged on the bottom support frame, slidably cooperating with the bottom support frame, and detachably connected to the partition assembly; A first support clamping plate, detachably arranged on the upper side of the rear support frame, slidably cooperating with the rear support frame, and the contour edge of the first support clamping plate is adapted to the outer contour of the rear engine hood; A second support clamping plate, detachably arranged on the bottom support frame, slidably cooperating with the bottom support frame, and the contour edge of the second support clamping plate is adapted to the outer contour of the rear engine hood.

[0011] According to the assembly jig for an aircraft engine hood provided by the present invention, the rear support assembly further includes a third support clamping plate, which is detachably arranged on the rear support frame and located between the first support clamping plate and the second support clamping plate, and the contour edge of the third support clamping plate is adapted to the outer contour of the rear engine hood; a plurality of rear pulling members are arranged at intervals on the third support clamping plate, and the rear pulling members are detachably connected to the rear engine hood.

[0012] According to the assembly jig for an aircraft engine hood provided by the present invention, it further includes a walking assembly, which is arranged at the bottom of the bottom support frame, and the walking assembly is used to move the assembly jig for the aircraft engine hood.

[0013] According to the assembly jig for an aircraft engine hood provided by the present invention, it further includes a leveling assembly, which is arranged at the bottom of the bottom support frame, and the leveling assembly is used to adjust the levelness of the assembly jig for the aircraft engine hood.

[0014] The assembly method for an aircraft engine hood provided by the second aspect of the present invention includes: Correspondingly installing the front engine hood partition and the rear engine hood partition on the partition assembly; Sheathing the rear engine hood skin on the rear engine hood partition to complete the assembly of the rear engine hood, and supporting and limiting the rear engine hood through the rear support assembly and the partition assembly; Sheathing the front engine hood skin on the front engine hood partition to complete the assembly of the front engine hood, and supporting and limiting the front engine hood through the front support assembly and the partition assembly; Removing the partition assembly, docking and fixing the front engine hood and the rear engine hood to complete the assembly of the engine hood.

[0015] The assembly jig for an aircraft engine hood provided by the present invention can easily achieve the assembly of the aircraft engine hood through the cooperation among the front support assembly, the rear support assembly, and the partition assembly provided on the bottom support frame. Additionally, by providing a limiting profile on the partition assembly, the aircraft engine hood can be supported and limited from the middle through the limiting profile. Moreover, both the front support assembly and the rear support assembly are slidably engaged with the bottom support frame. In this way, when the assembly jig is used in the assembly process of aircraft engine hoods under different conditions, the positions of the front support assembly, the rear support assembly, and the partition assembly relative to the bottom support frame can be adjusted to meet the assembly requirements of aircraft engine hoods under different conditions, achieving multi-purpose use of a single machine.

[0016] Compared with the prior art, for the assembly jig of the aircraft engine hood provided by the present invention, the front engine hood is limited by the front support assembly, the rear engine hood is limited by the rear support assembly, and at the same time, the partition assembly supports and limits from the middle of the engine hood. In this way, it is possible to eliminate the need to provide a steel structure for support inside the aircraft engine hood and to eliminate multiple contour clamping plates for external traction, which can reduce the overall number of parts of the assembly jig and reduce the processes in the disassembly, assembly, debugging, etc. of the assembly jig. Additionally, for the assembly jig provided by the present invention, the positions of the front support assembly, the rear support assembly, and the partition assembly relative to the bottom support frame can all be adaptively adjusted, which can meet the assembly requirements of different aircraft engine hoods, break the limitation of one machine for one use in the prior art, and achieve the function of multi-purpose use of a single machine. Based on this, the overall assembly efficiency on the aircraft engine hood assembly line can be greatly improved, the manpower and material resources in the overall assembly process can be saved, the impact of the aircraft engine hood assembly process on the subsequent aircraft assembly work can be reduced, and the time for the aircraft to roll off the production line can be increased. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0018] Figure 1 It is a schematic structural diagram of an aircraft engine hood provided by an embodiment of the present invention.

[0019] Figure 2 It is a schematic structural diagram of a front engine hood provided by an embodiment of the present invention.

[0020] Figure 3 It is a schematic structural diagram of a rear engine hood provided by an embodiment of the present invention.

[0021] Figure 4It is an assembly schematic diagram of an aircraft engine hood provided by an embodiment of the present invention from a certain perspective.

[0022] Figure 5 It is an assembly schematic diagram of an aircraft engine hood provided by an embodiment of the present invention from another perspective.

[0023] Figure 6 It is an overall structural schematic diagram of an assembly jig for an aircraft engine hood provided by an embodiment of the present invention from a certain perspective.

[0024] Figure 7 It is an overall structural schematic diagram of an assembly jig for an aircraft engine hood provided by an embodiment of the present invention from another perspective.

[0025] Figure 8 It is the front view of a partition assembly provided by an embodiment of the present invention.

[0026] Figure 9 It is the rear view of a partition assembly provided by an embodiment of the present invention.

[0027] Figure 10 It is Figure 9 The partial enlarged structural schematic diagram at position A in

[0028] Reference numerals: 10: Front engine hood; 11: Front engine hood skin; 12: Front engine hood partition; 13: Engine hood lamp socket; 20: Rear engine hood; 21: Rear engine hood skin; 22: Rear engine hood partition; 100: Bottom support frame; 200: Front support assembly; 210: Front support frame; 220: Front support block; 221: Limiting part; 230: Front support clamping plate; 231: Front pulling part; 300: Rear support assembly; 310: Rear support frame; 320: First support clamping plate; 330: Second support clamping plate; 340: Third support clamping plate; 341: Rear pulling part; 400: Partition assembly; 410: Limiting contour; 420: Substrate; 421: Contour through slot; 430: Front contour clamping plate part; 440: Rear contour clamping plate part; 441: Rear contour clamping plate; 442: Kidney-shaped hole; 443: Limiting rod; 444: Locking part; 500: Walking assembly; 600: Leveling assembly. Detailed implementation manners

[0029] To make the objectives, technical solutions and advantages of the present invention more clear, the technical solutions in the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present invention without creative work fall within the scope of protection of the present invention.

[0030] In the description of the embodiments of the present application, it should be noted that unless otherwise clearly defined and limited, the terms "connected" and "connected" should be understood in a broad sense. For example, it 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 directly connected, or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood in specific situations.

[0031] In the embodiments of the present application, unless otherwise clearly defined and limited, the first feature being "on" or "under" the second feature can be that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on" the second feature can be that the first feature is directly above or obliquely above the second feature, or merely indicates that the first feature has a higher horizontal height than the second feature. The first feature being "under", "beneath" and "under" the second feature can be that the first feature is directly below or obliquely below the second feature, or merely indicates that the first feature has a lower horizontal height than the second feature.

[0032] In the description of this specification, the descriptions with reference to terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the embodiments of the present application. In this specification, the schematic descriptions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0033] The following is combined with Figures 1 to 10 , to describe the embodiments of the present invention. It should be understood that the following description is only a schematic implementation manner of the present invention and does not constitute any limitation to the present invention.

[0034] Figure 1 is a schematic structural diagram of an aircraft engine hood provided by an embodiment of the present invention; Figure 2It is a schematic structural diagram of the front engine hood provided by an embodiment of the present invention; Figure 3 It is a schematic structural diagram of the rear engine hood provided by an embodiment of the present invention.

[0035] Refer to Figure 1 、 Figure 2 and Figure 3 ,The aircraft engine hood includes two parts, namely the front engine hood 10 and the rear engine hood 20. The front engine hood 10 includes a front engine hood skin 11 and a front engine hood partition 12, and the bottom of the front engine hood 10 is an engine hood lamp socket 13; the rear engine hood 20 includes a rear engine hood skin 21 and a rear engine hood partition 22.

[0036] Figure 4 It is an assembly schematic diagram of the aircraft engine hood provided by an embodiment of the present invention from one perspective; Figure 5 It is an assembly schematic diagram of the aircraft engine hood provided by an embodiment of the present invention from another perspective; Figure 6 It is an overall structural schematic diagram of the assembly jig for the aircraft engine hood provided by an embodiment of the present invention from one perspective; Figure 7 It is an overall structural schematic diagram of the assembly jig for the aircraft engine hood provided by an embodiment of the present invention from another perspective.

[0037] Refer to Figure 4 、 Figure 5 、 Figure 6 and Figure 7 ,A first aspect of the present invention provides an assembly jig for an aircraft engine hood, hereinafter simply referred to as an assembly jig. The assembly jig includes a bottom support frame 100, a front support assembly 200, a rear support assembly 300, and a partition assembly 400. The front support assembly 200, the rear support assembly 300, and the partition assembly 400 are all provided on the upper surface of the bottom support frame 100. The front support assembly 200 and the rear support assembly 300 are oppositely arranged on both sides of the partition assembly 400. In other words, the partition assembly 400 is provided between the front support assembly 200 and the rear support assembly 300.

[0038] The front support assembly 200 is detachably connected to the bottom support frame 100 and is slidably engaged therewith, that is, the front support assembly 200 can slide relative to the bottom support frame 100, and the front support assembly 200 is used to limit the front engine hood 10. Similarly, the rear support assembly 300 is also detachably connected to the bottom support frame 100 and is also slidably engaged therewith. In other words, the rear support assembly 300 can also slide relative to the bottom support frame 100, and the rear support assembly 300 is used to limit the rear engine hood 20.

[0039] Figure 8 It is the front view of the partition assembly provided by an embodiment of the present invention.

[0040] One side of the partition assembly 400 is detachably connected to the front support assembly 200, and the other side is detachably connected to the rear support assembly 300. The partition assembly 400 is provided with a limiting profile 410 adapted to the engine hood. The limiting profile 410 is used to limit the engine hood. In some cases, the limiting profile 410 can also be used to inspect the deformation problem of the aircraft engine hood.

[0041] Specifically, during assembly, first, the front engine hood partition 12 and the rear engine hood partition 22 need to be respectively installed in the limiting profiles 410 on both sides of the partition assembly 400 and fixed by fasteners. Secondly, an adhesive is applied to the outer side of the front engine hood partition 12, and then the front engine hood skin 11 is covered on the front engine hood partition 12. At the same time, the position of the front engine hood skin 11 is adjusted and limited by the front support assembly 200. The excess adhesive between the front engine hood skin 11 and the front engine hood partition 12 can be pushed by the front support assembly 200 to move the front engine hood skin 11 towards the partition assembly 400. During this process, due to the existence of the limiting profile 410, the contacting positions between the front engine hood skin 11 and the front engine hood partition 12 will be squeezed against each other, so that the excess adhesive can be extruded to achieve the effect of controlling the adhesive thickness.

[0042] The assembly between the rear engine hood skin 21 and the rear engine hood partition 22 is similar to the assembly between the front engine hood skin 11 and the front engine hood partition 12. First, an adhesive needs to be applied to the outer side of the rear engine hood partition 22, and then the rear engine hood skin 21 is covered on the rear engine hood partition 22. At the same time, the position of the rear engine hood skin 21 is adjusted and limited by the rear support assembly 300. The adhesive between the rear engine hood skin 21 and the rear engine hood partition 22 can also be adjusted with the help of the limiting profile 410. For the specific detailed process, please refer to the following text.

[0043] Refer to Figures 1 to 8 It can be understood that the assembly jig for the aircraft engine hood provided by the embodiment of the present invention can easily realize the assembly of the aircraft engine hood by arranging the front support assembly 200, the rear support assembly 300 and the partition assembly 400 on the bottom support frame 100 and based on the cooperation among the three. In addition, by arranging the limiting profile 410 on the partition assembly 400, in this way, the aircraft engine hood can be supported and limited from the middle by the limiting profile 410. In addition, both the front support assembly 200 and the rear support assembly 300 are slidably matched with the bottom support frame 100. In this way, when the assembly jig is used for the assembly process of the aircraft engine hood in different situations, the positions of the front support assembly 200, the rear support assembly 300 and the partition assembly 400 relative to the bottom support frame 100 can be adjusted to meet the assembly requirements of the aircraft engine hood in different situations, realizing multi-purpose use of one machine.

[0044] Compared with the prior art, the assembly jig for an aircraft engine hood provided by the embodiment of the present invention positions the front engine hood 10 through the front support assembly 200, positions the rear engine hood 20 through the rear support assembly 300, and simultaneously supports and positions from the middle of the engine hood through the partition assembly 400. In this way, it is possible to eliminate the steel structure for support inside the aircraft engine hood and eliminate multiple contour clamping plates for external pulling, which can reduce the overall number of parts of the assembly jig and reduce the processes in the processes of disassembling, assembling, and debugging the assembly jig. In addition, for the assembly jig provided by the present invention, the positions of the front support assembly 200, the rear support assembly 300, and the partition assembly 400 relative to the bottom support frame 100 can be adjusted adaptively, so as to meet the assembly requirements of different aircraft engine hoods, break the limitation of one jig for one aircraft in the prior art, and realize the function of one jig for multiple uses. Based on this, the overall assembly efficiency on the aircraft engine hood assembly line can be greatly improved, the manpower and material resources in the overall assembly process can be saved, the impact of the aircraft engine hood assembly process on the subsequent aircraft assembly work can be reduced, and the time for the aircraft to roll off the production line can be increased.

[0045] Figure 9 It is the rear view of the partition assembly provided by the embodiment of the present invention.

[0046] Refer to Figure 8 and Figure 9 In an optional embodiment of the present invention, the partition assembly 400 includes a base plate 420, a front contour clamping plate component 430, and a rear contour clamping plate component 440. Among them, the base plate 420 is detachably arranged between the front support assembly 200 and the rear support assembly 300. A contour through groove 421 is provided on the upper side of the base plate 420, and the shape of the contour through groove 421 is adapted to the front edge of the upper side of the rear engine hood 20. During the assembly process, the front edge of the upper side of the rear engine hood 20 can pass through the base plate 420 through the contour through groove 421 and contact the front engine hood 10.

[0047] It should be noted that the aforementioned limiting contour 410 includes a front limiting contour and a rear limiting contour. The front limiting contour is used to support and position the front engine hood 10, and the rear limiting contour is used to support and position the rear engine hood 20. The front limiting contour and the rear limiting contour share the contour through groove 421.

[0048] The front contour clamping plate component 430 is arranged on the side of the base plate 420 facing the front engine hood 10 and on the outside of the front engine hood 10. The edge contour of the front contour clamping plate component 430 facing the front engine hood 10 is adapted to the outer contour of the front engine hood 10, and the edge of the front contour clamping plate component 430 matches the edge of the contour through groove 421 to form a front limiting contour. In an optional embodiment of the present invention, the front contour clamping plate component 430 includes a first front contour clamping plate and a second front contour clamping plate, and the first front contour clamping plate and the second front contour clamping plate are oppositely arranged on both sides of the front engine hood 10.

[0049] It can be understood that by pushing the front hood skin 11 towards the partition assembly 400 through the front support assembly 200, during this process, the outer side of the front hood skin 11 will abut against the first front contour clamping plate and the second front contour clamping plate. Since the first front contour clamping plate and the second front contour clamping plate are fixed on the substrate 420, the first front contour clamping plate and the second front contour clamping plate will exert extrusion on the front hood skin 11. In this way, the positions where the front hood skin 11 contacts the front hood partition 12 will be mutually extruded, and thus the excess adhesive can be extruded to achieve the effect of controlling the adhesive thickness of the bonding.

[0050] The rear contour clamping plate component 440 is arranged on one side of the substrate 420 facing the rear hood 20 and on the outer side of the rear hood 20. The edge contour of the rear contour clamping plate component 440 facing the rear hood 20 is adapted to the outer contour of the rear hood 20, and the edge of the rear contour clamping plate component 440 matches the edge of the contour through groove 421 for forming a rear limit contour. Similar to the front hood 10, the adhesive between the rear hood skin 21 and the rear hood partition 22 can also be adjusted by means of the rear contour clamping plate component 440.

[0051] Figure 10 Yes Figure 9 The partial enlarged structural schematic diagram at position A in

[0052] Refer to Figure 9 And Figure 10 In an alternative embodiment of the present invention, the rear contour clamping plate component 440 includes a rear contour clamping plate 441 and a locking member 444. Among them, the edge contour of the rear contour clamping plate 441 is adapted to the outer contour of the rear hood 20, and the rear contour clamping plate 441 matches the contour through groove 421 for forming a rear limit contour, thereby limiting the rear hood 20.

[0053] In an alternative embodiment of the present invention, a plurality of kidney-shaped holes 442 are spaced on the rear contour clamping plate 441, and the axis of the kidney-shaped holes 442 faces the rear hood 20. At the same time, a limiting rod 443 corresponding to the kidney-shaped holes 442 is arranged on the substrate 420. During assembly, the rear contour clamping plate 441 can be hung on the limiting rod 443 through the kidney-shaped holes 442. It can be understood that due to the shape of the kidney-shaped holes 442, relative movement can occur between the kidney-shaped holes 442 and the limiting rod 443, and the movement direction is limited to the axis direction of the kidney-shaped holes 442, that is, the rear contour clamping plate 441 can move relative to the substrate 420 along the axis direction of the kidney-shaped holes 442.

[0054] The locking member 444 includes a base and a fastener. The base is fixed on the substrate 420. A threaded through hole is provided on the base. The fastener passes through the base. One end of the fastener abuts against the side of the rear contour plate 441 away from the rear hood 20. It can be understood that by tightening the fastener, the fastener can push the rear contour plate 441 to move along the axial direction of the kidney-shaped hole 442. During the actual assembly process, the outer side of the rear hood skin 21 will contact and abut against the rear contour plate 441. By pushing the rear contour plate 441 towards the rear hood 20 with the locking member 444, the rear contour plate 441 will exert extrusion on the rear hood skin 21. In this way, the positions where the rear hood skin 21 contacts the rear hood partition 22 will be extruded against each other, and then the excess adhesive can be squeezed out to achieve the effect of controlling the adhesive thickness.

[0055] In an alternative embodiment of the present invention, similar to the front contour plate component 430, the rear contour plate component 440 also includes a first rear contour plate and a second rear contour plate. The first rear contour plate and the second rear contour plate are oppositely arranged on both sides of the rear hood 20. It can be understood that by dividing the rear contour plate component 440 into the first rear contour plate and the second rear contour plate, it is convenient for the overall installation and transportation of the assembly jig. In addition, by providing the first rear contour plate and the second rear contour plate, the rear hood 20 can be evenly positioned, supported and restricted from both sides of the rear hood 20, which can ensure the high precision and high accuracy of the rear hood 20 during the assembly process.

[0056] Continue to refer to Figure 6 In an alternative embodiment of the present invention, the front support assembly 200 includes a front support frame 210, a front support block 220 and a front support plate 230. The front support frame 210 is detachably arranged at the front end of the bottom support frame 100 and is in sliding fit with the bottom support frame 100. Specifically, a chute can be provided on either the bottom support frame 100 or the front support frame 210, and a slider can be provided on the other one. The sliding fit between the two is achieved by the cooperation of the chute and the slide rail. The sliding direction of the front support frame 210 relative to the bottom support frame 100 can be designed according to actual needs.

[0057] Continue to refer to Figure 6 In an alternative embodiment of the present invention, the bottom support frame 100 and the front support frame 210 can be made of profiles with chutes on their surfaces, and sliders can be provided at the bottom of the front support frame 210. It can be understood that with such a design, the front support frame 210 can slide along the length direction of the chute, that is, it can slide along the left-right direction of the hood. In this way, when the front support frame 210 needs to be moved, the operation requirements can be simply and quickly achieved, saving the time required for the assembly process.

[0058] Continue to refer to Figure 6 , the front support block 220 is detachably arranged on the bottom support frame 100, and the front support block 220 is located between the front support frame 210 and the partition assembly 400. Similar to the sliding fit between the aforementioned front support frame 210 and the bottom support frame 100, the front support block 220 also has a sliding fit with the bottom support frame 100. For the specific setting method of the sliding fit, please refer to the foregoing description. It should be noted that in the embodiment of the present invention, since the front hood 10 needs to be moved along its axis, the relative sliding direction between the front support block 220 and the bottom support frame 100 needs to be parallel to the axis of the front hood 10.

[0059] Continue to refer to Figure 6 , a limiting portion 221 is provided on the upper surface of the front support block 220, and the shape of the limiting portion 221 matches the outer shape of the hood lamp socket 13 in the front hood 10. It can be understood that in addition to supporting the front hood 10 and bearing the weight of the front hood 10, the front support block 220 can also limit the movement of the front hood 10 in the left, right, front and back directions to achieve the precise positioning of the front hood 10, so that after assembly, the geometric shape and size of the front hood 10 reach the specified tolerance range, thereby improving the product accuracy; in addition, the shape of the limiting portion 221 matches the hood lamp socket 13, so that during the assembly process, the product deformation at the bottom of the front hood 10 can also be limited.

[0060] Continue to refer to Figure 6 , one end of the front support clamping plate 230 is slidably connected to the front support frame 210, and the other end is connected to the partition assembly 400, and the contour edge of the front support clamping plate 230 is adapted to the outer contour of the front hood 10. It can be understood that during the assembly process, the outer shape of the front hood 10 can be restricted by the front support clamping plate 230, and the outer contour of the entire front hood 10 can be effectively controlled; in addition, by adjusting the position of the front support clamping plate 230 relative to the front support frame 210, the front support clamping plate 230 can meet the assembly requirements of the front hood 10 in different situations, so as to improve the functionality of the assembly jig for multiple uses.

[0061] Continue to refer to Figure 6 , in an alternative embodiment of the present invention, the front support assembly 200 further includes a plurality of front pulling members 231. The front pulling members 231 are arranged at intervals on the side of the front support clamping plate 230 close to the front hood 10 and are detachably connected to the front hood 10. It should be noted that the arrangement of the front pulling members 231 can be adaptively arranged according to actual needs; it can be understood that during the assembly process, the material of the front hood skin 11 is relatively soft, and the upper part of the front hood 10 may be deformed and collapsed. By providing the front pulling members 231, the front hood 10 can be pulled by the front pulling members 231 during the assembly process, thereby avoiding the problem of deformation and collapse of the front hood 10.

[0062] Continue to refer to Figure 7 In an alternative embodiment of the present invention, the rear support assembly 300 includes a rear support frame 310, a first support clamping plate 320 and a second support clamping plate 330. Among them, the rear support frame 310 is detachably arranged on the bottom support frame 100 and is slidably matched with the bottom support frame 100. The sliding matching setting method is similar to that of the front support frame 210 described above, which will not be elaborated here. The rear support frame 310 is also detachably connected to the substrate 420 in the partition assembly 400, so that it can be used to support the substrate 420 and prevent the substrate 420 from tilting.

[0063] Continue to refer to Figure 7 The first support clamping plate 320 is detachably arranged on the upper side of the rear support frame 310 and is slidably matched with the rear support frame 310. In the embodiment of the present invention, two first support clamping plates 320 are provided, and the two first support clamping plates 320 are symmetrically arranged on both sides of the rear engine hood 20 respectively. The contour edge of the first support clamping plate 320 is adapted to the outer contour of the rear engine hood 20. It can be understood that during the assembly process, the outer shape of the rear engine hood 20 can be restricted by the rear support clamping plate, and the outer contour of the rear engine hood 20 can be effectively controlled. In addition, by moving the position of the first support clamping plate 320, the assembly requirements of the rear engine hood 20 in different situations can be met, which is beneficial to the characteristic of the assembly jig being multi-functional.

[0064] Continue to refer to Figure 7 The second support clamping plate 330 is detachably arranged on the bottom support frame 100 and is slidably matched with the bottom support frame 100. The contour edge of the second support clamping plate 330 is adapted to the outer contour of the rear engine hood 20. The second support clamping plate 330 is used to support the rear engine hood 20 and bear the weight of the rear engine hood 20. Based on the cooperation with the partition assembly 400, the second support clamping plate 330 can also limit the movement of the rear engine hood 20 in the left-right, front-back directions, realizing the precise positioning of the rear engine hood 20, so that after assembly, the geometric shape and size of the rear engine hood 20 reach the specified tolerance range, thereby improving the product accuracy. In addition, the shape of the second support clamping plate 330 matches the shape of the bottom of the rear engine hood 20. In this way, during the assembly process, the product deformation at the bottom of the rear engine hood 20 can also be restricted.

[0065] Continue to refer to Figure 7, in an alternative embodiment of the present invention, the rear support assembly 300 further includes a third support card plate 340. The third support card plate 340 is detachably disposed on the rear support frame 310 and is located between the first support card plate 320 and the second support card plate 330. The contour edge of the third support card plate 340 is adapted to the outer contour of the rear hood 20. It can be understood that during the assembly process, the shape of the rear hood 20 can be restricted by the third support card plate 340, and the outer contour of the entire rear hood 20 can be effectively controlled.

[0066] Continue to refer to Figure 7 , in an alternative embodiment of the present invention, a plurality of rear pulling members 341 are spaced apart on the third support card plate 340. The rear pulling members 341 are detachably connected to the rear hood 20. It should be noted that the arrangement of the rear pulling members 341 can be adaptively arranged according to actual needs; it can be understood that during the assembly process, the material of the rear hood skin 21 is relatively soft, and the middle part of the rear hood 20 may be deformed and collapsed. By setting the rear pulling members 341, the rear hood 20 can be pulled by the rear pulling members 341 during the assembly process, thereby avoiding the problem of deformation and collapse of the rear hood 20.

[0067] In an alternative embodiment of the present invention, two third support card plates 340 are provided. The two third support card plates 340 are symmetrically arranged on both sides of the rear hood 20, so that the rear hood 20 can be restricted evenly from both sides, avoiding the problem of uneven force on the rear hood 20.

[0068] Continue to refer to Figure 4 , in an alternative embodiment of the present invention, the assembly jig further includes a walking assembly 500. The walking assembly 500 is disposed at the bottom of the bottom support frame 100. The walking assembly 500 includes four walking wheels, and the four walking wheels are correspondingly arranged at the four diagonals of the bottom support frame 100. It can be understood that by setting the walking assembly 500, the movement of the assembly jig can be facilitated, and the convenience of the assembly jig during transportation can be improved.

[0069] Continue to refer to Figure 4 , in an alternative embodiment of the present invention, a leveling assembly 600 is further included. The leveling assembly 600 is disposed at the bottom of the bottom support frame 100. The leveling assembly 600 is used to adjust the levelness of the assembly jig. Specifically, the leveling assembly 600 includes four foot cups, and the four foot cups are correspondingly arranged at the four diagonals of the bottom support frame 100. When the walking wheels are simultaneously provided, the foot cups can be arranged inside or outside the two walking wheels. Specifically, it can be adaptively designed according to actual needs.

[0070] It is understandable that by setting the leveling component 600, after the assembly jig is moved to the designated position, the position of the assembly jig can be locked by the leveling component 600 to prevent it from moving or shaking. Additionally, in the case of an uneven bottom surface, the leveling component 600 can also be used to adjust the levelness of the assembly jig, that is, to adjust the relative heights of the four feet to adjust the levelness of the assembly jig, so that the assembly jig can be applied to more complex working environments.

[0071] In an alternative embodiment of the present invention, the entire assembly jig is made of aluminum profiles. It is understandable that aluminum profiles are lightweight, which can greatly reduce the overall weight of the assembly jig and facilitate the assembly and handling of the assembly jig. Additionally, aluminum profiles have the characteristics of simple assembly, high strength, long service life, and good corrosion resistance, which can directly improve product accuracy and extend the service life of the assembly jig. Moreover, aluminum profiles are easy to process, making it convenient to machine chutes and bumps on their surfaces, which can facilitate the realization of the sliding fit in the aforementioned embodiments. Specifically, it can be adaptively designed according to actual situations.

[0072] Refer to Figure 1 and Figure 4 , and the following gives the specific assembly steps of the aircraft engine hood through the assembly jig in the embodiments of the present invention.

[0073] First step, install the front engine hood partition 12 and the rear engine hood partition 22 at the corresponding positions on the base plate 420.

[0074] The base plate 420 is provided with openings and feature holes corresponding to the front engine hood partition 12 and the rear engine hood partition 22, and the front engine hood partition 12 and the rear engine hood partition 22 can be fixed to the base plate 420 through fasteners.

[0075] Second step, apply an adhesive on the outer side of the rear engine hood partition 22, place the lower half of the rear engine hood skin 21 on the second support plate 330, and then adjust the position of the lower half of the rear engine hood skin 21 to make it sleeved on the outer side of the rear engine hood partition 22.

[0076] Third step, push the rear contour plate 441 through the locking member 444 to squeeze the lower half of the rear engine hood skin 21 so that the adhesive between the lower half of the rear engine hood skin 21 and the rear engine hood partition 22 becomes evenly compliant.

[0077] Fourth step, pull the lower half of the rear engine hood skin 21 through the multiple rear pulling members 341 on the third support plate 340 to make its outer contour in a proper position.

[0078] Fifth step, further finely adjust the relative position of the lower half of the rear engine hood skin 21 with the aid of a laser tracker or scanner.

[0079] A reference hole matching a laser tracker or scanner can be pre - set on the substrate 420.

[0080] The sixth step is to install the upper half of the rear engine hood skin 21 and make its front end extend to the other side of the substrate 420 through the contour through - slot 421.

[0081] It should be noted that the contour through - slot 421 can limit the thickness of the adhesive between the upper half of the rear engine hood skin 21 and the rear engine hood partition 22.

[0082] The seventh step is to apply adhesive on the outer side of the front engine hood partition 12.

[0083] The eighth step is to install the front engine hood skin 11, place it on the front support block 220, and limit its position through the front support clamping plate 230.

[0084] The ninth step is to push the front engine hood skin 11 towards the substrate 420 through the front support block 220, squeeze the adhesive between the front engine hood skin 11 and the front engine hood partition 12 through the front contour clamping plate component 430, and dock the front engine hood 10 and the rear engine hood 20.

[0085] The tenth step is to wait for the adhesive to cure.

[0086] The eleventh step is to drive the front engine hood 10 to move away from the substrate 420 through the front support block 220 and remove the partition assembly 400.

[0087] The twelfth step is to drive the front engine hood 10 towards the rear engine hood 20 through the front support block 220, dock the front engine hood 10 and the rear engine hood 20, and fix them into a whole to complete the assembly of the aircraft engine hood.

[0088] It can be understood that in the embodiment of the present invention, by setting the detachable partition assembly 400, after the front and rear engine hoods 20 are cured, the partition assembly 400 can be removed to realize the direct docking of the front and rear engine hoods 20, which can effectively prevent the deformation and docking error of the aircraft engine hood caused by the off - shelf, reduce the workload of workers, shorten the product manufacturing time, improve production efficiency, and ensure product accuracy.

[0089] It should be noted that the technical solutions in the various embodiments of the present invention can be combined with each other, but the basis for combination is that those skilled in the art can implement it; when the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist, that is, it does not belong to the protection scope of the present invention either.

[0090] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An assembly jig for an aircraft engine cowling, characterized in that, include: Bottom support frame (100); A front support assembly (200) is detachably arranged on the bottom support frame (100) and slidably cooperates with the bottom support frame (100), and the front support assembly (200) is used to support and limit the front engine cover (10); a rear support assembly (300) detachably disposed on the bottom support frame (100) and slidably matched with the bottom support frame (100), the rear support assembly (300) being used to support and limit the position of the rear engine cover (20); The partition assembly (400) is detachably arranged between the front support assembly (200) and the rear support assembly (300), and the partition assembly (400) is provided with a limiting contour (410) adapted to the engine hood, and the limiting contour (410) is used to support and limit the engine hood.

2. The assembling jig for an aircraft engine cowling according to claim 1, characterized in that, The partition assembly (400) comprises: A base plate (420) is detachably disposed between the front support assembly (200) and the rear support assembly (300), and a contour through groove (421) is provided on the base plate (420); A front contour card component (430) is arranged on a side of the base plate (420) facing the front hood (10) and is arranged on the outside of the front hood (10); the edge contour of the front contour card component (430) is adapted to the outer contour of the front hood (10); the front contour card component (430) matches the contour through groove (421) to support and limit the front hood (10); A rear contour cardboard component (440) is arranged on a side of the base plate (420) facing the rear engine hood (20) and is arranged on the outside of the rear engine hood (20); the edge contour of the rear contour cardboard component (440) is adapted to the outer contour of the rear engine hood (20); the rear contour cardboard component (440) matches the contour through groove (421) to support and limit the rear engine hood (20).

3. The assembly jig for an aircraft engine cowl according to claim 2, characterized in that, The rear profile cardboard component (440) comprises: a rear profile card plate (441), wherein the edge profile of the rear profile card plate (441) is adapted to the outer profile of the rear hood (20), and the rear profile card plate (441) matches the profile through groove (421) so as to support and limit the rear hood (20); a plurality of waist-shaped holes (442) are arranged at intervals on the rear profile card plate (441), the axes of the waist-shaped holes (442) face the rear hood (20), and a limiting rod (443) matching the waist-shaped holes (442) is provided on the base plate (420); A locking member (444) is fixed to the base plate (420) and abuts against a side of the rear contour card plate (441) facing away from the rear engine cover (20), and the locking member (444) is used to push the rear contour card plate component (440) to move along the axial direction of the waist-shaped hole (442).

4. The assembly jig for an aircraft engine cowl according to claim 1, characterized in that, The front support assembly (200) comprises: A front support frame (210) is detachably provided at the front end of the bottom support frame (100) and is in sliding fit with the bottom support frame (100); A front support block (220) is detachably provided on the bottom support frame (100) and is in sliding fit with the bottom support frame (100). The front support block (220) is located between the front support frame (210) and the partition assembly (400). A limiting portion (221) is provided on the front support block (220). The shape of the limiting portion (221) matches the outer shape of the engine hood lamp socket (13). The limiting portion (221) is used to limit the movement of the front engine hood (10) along its own axis direction; A front support clamping plate (230) has one end slidably connected to the front support frame (210) and the other end connected to the partition assembly (400). The contour edge of the front support clamping plate (230) is adapted to the outer contour of the front engine hood (10).

5. The assembly jig for an aircraft engine cowl according to claim 4, characterized in that, The front support assembly (200) further includes a plurality of front pulling members (231). The front pulling members (231) are spaced apart on the front support clamping plate (230) and are detachably connected to the front engine hood (10).

6. The assembly jig for the aircraft engine hood according to claim 1, characterized in that, The rear support assembly (300) includes: A rear support frame (310) is detachably provided on the bottom support frame (100) and is in sliding fit with the bottom support frame (100), and is detachably connected to the partition assembly (400); A first support clamping plate (320) is detachably provided on the upper side of the rear support frame (310) and is in sliding fit with the rear support frame (310). The contour edge of the first support clamping plate (320) is adapted to the outer contour of the rear engine hood (20); A second support clamping plate (330) is detachably provided on the bottom support frame (100) and is in sliding fit with the bottom support frame (100). The contour edge of the second support clamping plate (330) is adapted to the outer contour of the rear engine hood (20).

7. The assembly jig for the aircraft engine hood according to claim 6, characterized in that, The rear support assembly (300) further includes a third support clamping plate (340). The third support clamping plate (340) is detachably provided on the rear support frame (310) and is located between the first support clamping plate (320) and the second support clamping plate (330). The contour edge of the third support clamping plate (340) is adapted to the outer contour of the rear engine hood (20); A plurality of rear pulling members (341) are spaced apart on the third support clamping plate (340), and the rear pulling members (341) are detachably connected to the rear engine hood (20).

8. The assembly jig for an aircraft engine cowl according to any one of claims 1 to 7, characterized in that, It further includes a walking assembly (500). The walking assembly (500) is provided at the bottom of the bottom support frame (100). The walking assembly (500) is used to move the assembly jig of the aircraft engine hood.

9. The assembly jig for an aircraft engine cowl according to any one of claims 1 to 7, characterized in that, It further includes a leveling assembly (600). The leveling assembly (600) is provided at the bottom of the bottom support frame (100). The leveling assembly (600) is used to adjust the levelness of the assembly jig of the aircraft engine hood.

10. An assembly method for an aircraft engine hood, characterized in that, Includes: The front hood partition (12) and the rear hood partition (22) are correspondingly installed on the partition assembly (400); The rear hood skin (21) is sleeved on the rear hood partition (22) to complete the assembly of the rear hood (20), and the rear hood (20) is supported and positioned by the rear support assembly (300) and the partition assembly (400); The front hood skin (11) is sleeved on the front hood partition (12) to complete the assembly of the front hood (10), and the front hood (10) is supported and positioned by the front support assembly (200) and the partition assembly (400); The partition assembly (400) is removed, and the front hood (10) and the rear hood (20) are docked and fixed to complete the assembly of the hood.

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