Auxiliary tool for assembling aircraft wings

Abstract

The utility model discloses an auxiliary tool for assembling aircraft wings, and relates to the technical field of general aviation auxiliary equipment. Comprising a supporting base, a hydraulic jack is rotationally arranged on the upper surface of the supporting base, a vertically-arranged lifting rod is arranged on the top face of the hydraulic jack, and a wing connecting structure is arranged at the top of the lifting rod. On one hand, through the design of the supporting base, the hydraulic jack, the lifting rod and the wing connecting structure, the assembling efficiency of the aircraft wings and the aircraft body is improved, the auxiliary tool cannot move after being wholly conveyed to a designated position, and the overall positioning effect is good; on the other hand, the hydraulic jack is rotationally arranged on the upper surface of the supporting base, so that the assembling flexibility of the aircraft wings and the aircraft body is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of general aviation auxiliary equipment, in particular to auxiliary tooling for assembling aircraft wings. Background Art

[0002] The wing is an important part of an aircraft, responsible for providing lift and stability.

[0003] Prior art discloses an auxiliary tool for assembling an aircraft wing, documented in Publication No. CN208453259U. The tool comprises a support body, a removable lifting device mounted on the support body and connected to the wing, and a jack mounted on the support body and used to lift the lifting device. The support body also includes casters mounted on a base. The auxiliary tool facilitates assembly of the wing onto the aircraft fuselage by arranging the lifting device and the jack. The tool features a simple structure, ease of use, low cost, and ease of maintenance, improving the efficiency of wing-to-fuselage assembly.

[0004] However, in the prior art, the auxiliary tooling bracket body is fixed and rotated by casters provided at the bottom of the bracket body. The entire auxiliary tooling must be rotated by rotating the casters, and the adjustment range is large, resulting in poor positioning effect of the auxiliary tooling. Utility Model Content

[0005] In response to the above technical problems, the present application solves the problem in the prior art that the bracket body of the auxiliary tooling is fixed and rotated by casters provided at the bottom of the bracket body. The entire auxiliary tooling must be rotated by rotating the casters, and the adjustment range is large, resulting in poor positioning effect of the auxiliary tooling.

[0006] In order to achieve the above-mentioned purpose, the technical solution adopted in this application is: an auxiliary tooling for aircraft wing assembly, comprising a support base, a hydraulic jack is rotatably provided on the upper surface of the support base, a vertically arranged lifting rod is provided on the top surface of the hydraulic jack, and a wing connection structure is provided on the top of the lifting rod.

[0007] In order to better realize the present utility model, further, a square mounting hole is opened in the center of the support base, the top edge of the mounting hole is fixedly connected with the lower lobe rotating shell, the top of the lower lobe rotating shell is connected with the upper lobe rotating shell by bolts, and a through hole is opened at the center position of the upper lobe rotating shell, and a horizontally rotating mounting space is formed between the lower lobe rotating shell and the upper lobe rotating shell, and a turntable is rotatably arranged in the mounting space, and the upper surface of the turntable is provided with a turntable boss extending upward and passing through the through hole at the center position of the upper lobe rotating shell, and the upper surface of the turntable boss is fixedly connected to the bottom of the hydraulic jack.

[0008] In order to better realize the present invention, further, a plurality of locking holes are opened on the outer peripheral wall surface of the turntable boss and are evenly spaced;

[0009] A locking structure is provided on the upper surface of the upper petal rotating shell, the locking structure comprising a locking box body, a locking rod, a guide rod and a return spring. A cylindrical receiving channel is provided in the locking box body. The locking box body has limiting channels of reduced diameter at both ends of the receiving channel, which are arranged concentrically with and communicate with the receiving channel, forming an annular stepped transition.

[0010] The rod body of the locking rod is slidably sleeved in the limiting channel close to the side of the turntable boss, and one end of the locking rod extends out of the limiting channel and matches the locking hole, and the other end of the locking rod extends into the receiving channel, and the other end of the locking rod is configured as a slider matching the inner contour of the receiving channel;

[0011] One end of the guide rod is fixedly connected to the slider, and the other end of the guide rod extends out of the limiting channel of the locking structure away from the turntable boss side. The return spring is sleeved on the guide rod, and one end of the return spring is fixedly connected to the slider, and the other end of the return spring is fixedly connected to the annular transition away from the turntable boss side.

[0012] In order to better realize the present utility model, further, a pair of guide rods are provided on the upper surface of the turntable boss, which are symmetrically arranged vertically. A connecting sleeve is fixedly provided at the upper position of the outside of the lifting rod, and a guide sleeve is slidingly provided at the upper position of the outside of the guide rod. The guide sleeve and the connecting sleeve are fixedly connected by a connecting rod.

[0013] In order to better realize the present invention, further, the wing connection structure includes a support frame, a wing connection member and a support cylinder.

[0014] The top of the lifting rod is fixedly connected to a support frame, and a support cylinder is provided on the support frame. The middle part of the wing connector is sleeved in the support cylinder in a threaded connection manner, and the two ends of the wing connector are located outside the support cylinder. A rotating disk is provided at one end of the wing connector, and a handle is provided on the rotating disk. A pin hole is opened on the other end of the wing connector.

[0015] In order to better implement the present invention, further, a pair of symmetrically arranged reinforcement frames are respectively provided at the middle and lower sections of the two guide rods;

[0016] The support base is located on the upper surface of the outer periphery of the lower lobe rotating shell and is provided with an annular guide support groove. An annular slider is provided in the sliding sleeve of the annular guide support groove. The upper surface of the annular slider is fixedly connected to the bottom of the reinforcement frame, and the annular slider is arranged concentrically with the turntable.

[0017] In order to better implement the present invention, an electromagnetic lock is further provided on the contact surface between the annular guide support groove and the annular slider.

[0018] Compared with the prior art, the technical solution provided by the present invention has the following beneficial effects:

[0019] 1. The utility model, on the one hand, improves the assembly efficiency of the aircraft wing and fuselage through the design of the support base, hydraulic jack, lifting rod and wing connection structure, and the auxiliary tooling will not move after being transported to the designated position as a whole, so the overall positioning effect is good; on the other hand, by rotatably setting the hydraulic jack on the upper surface of the support base, the assembly flexibility of the aircraft wing and fuselage is improved.

[0020] 2. The utility model realizes the rotation adjustment of the lifting rod and the wing connection structure through the design of the lower petal rotating shell, the upper petal rotating shell, the bolts, the turntable boss and the turntable, avoiding the need for the entire tooling to be constantly rotated and adjusted when the wing and the fuselage are assembled.

[0021] 3. The utility model, through the coordinated design of the turntable boss, the locking hole and the locking structure, can ensure that the lifting rod and the wing connection structure can be rotated and adjusted while also being locked.

[0022] 4. The utility model plays a stable guiding role on the lifting rod through the coordinated design of the guide sleeve, the support frame, the connecting rod and the connecting sleeve.

[0023] 5. The present invention utilizes a design in which the middle portion of the wing connector is threadedly sleeved within the support cylinder. This allows the wing connector to be adjusted to an appropriate length range for different wing specifications (after adjustment, a locking agent such as Permatex 242 can be applied to the threaded connection to prevent relative rotation between the wing connector and the support cylinder. Alternatively, the locking nut can be rotated to lock the wing connector). This allows for better insertion into a pre-established, through-hole on the wingtip of an aircraft, thereby providing support for the aircraft wing. Furthermore, the wing connector extends from the other end of the hole (including the pin hole), and after a limit pin is inserted through the pin hole, it limits the position of the aircraft wing.

[0024] 6. The utility model further strengthens the supporting force area of ​​the reinforcement frame through the coordinated design of the annular guide support groove and the annular slider, and the reinforcement frame further improves the stability of the guide rod.

[0025] 7. The utility model, through the design of the electromagnetic lock, further strengthens the supporting force area of ​​the reinforcement frame, and cooperates with the locking structure provided on the upper surface of the upper lobe rotating shell to achieve double locking. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without paying any creative labor.

[0027] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0028] Figure 2 This is a schematic structural diagram of the support base in the present utility model;

[0029] Figure 3 This is a schematic diagram of the structure of the turntable boss, locking hole and turntable in the utility model;

[0030] Figure 4 It is a structural schematic diagram of the guide sleeve, connecting rod and connecting sleeve in the utility model.

[0031] In the figure: 100-support base; 200-hydraulic jack; 300-lifting rod; 101-lower lobe rotating shell; 102-upper lobe rotating shell; 103-bolt; 104-turntable boss; 105-locking hole; 106-turntable; 107-locking structure; 301-guide rod; 302-guide sleeve; 303-support frame; 304-connecting rod; 305-wing connecting piece; 306-pin hole; 307-support cylinder; 308-rotating disk; 309-handle; 310-reinforcement frame; 311-connecting sleeve; 312-annular guide support groove; 313-annular slider. DETAILED DESCRIPTION

[0032] To make the objectives, technical solutions, and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Generally, the components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations.

[0033] Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the present application for protection, but merely represents selected embodiments of the present application. All other embodiments obtained by persons of ordinary skill in the art based on the embodiments in the present application without making any creative efforts shall fall within the scope of protection of the present application.

[0034] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0035] In the description of this application, it should be noted that if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the accompanying drawings, or the orientation or position relationship in which the product of the application is usually placed when in use. It is only for the convenience of describing this application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, it cannot be understood as a limitation on this application. In addition, if the terms "first", "second", etc. appear in the description of this application, they are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0036] Furthermore, the use of terms such as "horizontal" and "vertical" in the description of this application does not necessarily imply that a component must be absolutely horizontal or suspended, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical" and does not mean that the structure must be completely horizontal, but rather that it can be slightly tilted.

[0037] It should also be noted that, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood broadly. For example, they may refer to fixed connections, detachable connections, or integral connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal connections between two components. A person of ordinary skill in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.

[0038] Example 1

[0039] like Figures 1 to 2 As shown, the utility model discloses an auxiliary tooling for assembling an aircraft wing, comprising a support base 100, on the upper surface of which a hydraulic jack 200 is rotatably provided, the top surface of the hydraulic jack 200 is provided with a vertically arranged lifting rod 300, and the top of the lifting rod 300 is provided with a wing connection structure.

[0040] On the one hand, the design of the support base 100, the hydraulic jack 200, the lifting rod 300 and the wing connection structure improves the assembly efficiency of the aircraft wing and fuselage; on the other hand, the assembly flexibility of the aircraft wing and fuselage is improved.

[0041] like Figures 1 to 3 As shown, in this embodiment, a square mounting hole is provided at the center of the support base 100, and the top edge of the mounting hole is fixedly connected to the lower lobe rotating shell 101, and the top of the lower lobe rotating shell 101 is connected to the upper lobe rotating shell 102 by bolts 103, and a through hole is provided at the center position of the upper lobe rotating shell 102, and a horizontally rotating mounting space is formed between the lower lobe rotating shell 101 and the upper lobe rotating shell 102, and a turntable 106 is rotatably arranged in the mounting space (the outer contour of the turntable 106 is in conformity with the inner contour of the mounting space), and the upper surface of the turntable 106 is provided with a turntable boss 104 extending upward and passing through the through hole at the center position of the upper lobe rotating shell 102, and the upper surface of the turntable boss 104 is fixedly connected to the bottom of the hydraulic jack 200.

[0042] Through the design of the lower lobe rotating shell 101, the upper lobe rotating shell 102, the bolt 103, the turntable boss 104 and the turntable 106, the rotation adjustment of the lifting rod 300 and the wing connection structure is achieved, avoiding the need for the entire tooling to be continuously rotated and adjusted when the wing and the fuselage are assembled.

[0043] like Figure 1 and Figure 3 As shown, in this embodiment, a plurality of locking holes 105 are formed on the outer peripheral wall of the turntable boss 104 and are evenly spaced.

[0044] A locking structure is provided on the upper surface of the upper petal rotating shell 102, and the locking structure includes a locking box body, a locking rod, a guide rod and a return spring. A cylindrical receiving channel is provided in the locking box body, and the locking box body has limiting channels of reduced diameter at both ends of the receiving channel, which are arranged concentrically with and communicate with the receiving channel, forming an annular stepped transition.

[0045] The rod body of the locking rod is slidably sleeved in the limiting channel near the side of the turntable boss 104, and one end of the locking rod extends out of the limiting channel and matches the locking hole 105, and the other end of the locking rod extends into the receiving channel, and the other end of the locking rod is configured as a slider matching the inner contour of the receiving channel;

[0046] One end of the guide rod is fixedly connected to the slider, and the other end of the guide rod extends out of the limiting channel of the locking structure away from the turntable boss 104. The return spring is sleeved on the guide rod, and one end of the return spring is fixedly connected to the slider, and the other end of the return spring is fixedly connected to the annular transition away from the turntable boss 104.

[0047] Through the coordinated design of the turntable boss 104, the locking hole 105 and the locking structure, on the one hand, the lifting rod 300 and the wing connection structure can be locked while being able to rotate and adjust.

[0048] like Figure 1 、 Figure 3 and Figure 4 As shown, in this embodiment, a pair of guide rods 301 are provided on the upper surface of the turntable boss 104 and are symmetrically arranged vertically. A connecting sleeve 311 is fixedly provided at the upper section of the outside of the lifting rod 300, and a guide sleeve 302 is slidably provided at the upper section of the outside of the guide rod 301. The guide sleeve 302 and the connecting sleeve 311 are fixedly connected by a connecting rod 304.

[0049] The coordinated design of the guide sleeve 302 , the support frame 303 , the connecting rod 304 and the connecting sleeve 311 provides a stable guiding effect on the lifting rod 300 .

[0050] like Figure 1 As shown, in this embodiment, the wing connection structure includes a support frame 303, a wing connection member 305 and a support cylinder 307.

[0051] The top of the lifting rod 300 is fixedly connected to a support frame 303, and a support cylinder 307 is provided on the support frame 303. The middle part of the wing connecting member 305 is threadedly sleeved in the support cylinder 307, and the two ends of the wing connecting member 305 are located outside the support cylinder 307. A rotating disk 308 is provided at one end of the wing connecting member 305, and a handle 309 is provided on the rotating disk 308. A pin hole 306 is opened on the other end of the wing connecting member 305.

[0052] By designing that the middle portion of the wing connector 305 is threadedly sleeved within the support cylinder 307, the wing connector 305 can be adjusted to a suitable length range for different wing specifications (after adjustment, Permatex 242 locking agent can be applied to the threaded connection position to prevent relative rotation between the wing connector 305 and the support cylinder 307. Of course, the locking nut can also be rotated to lock it), so that it can be better inserted into the pre-opened and through-hole on the wingtip of the aircraft wing to provide support for the aircraft wing. In addition, the wing connector 305 extends from the other end of the shaft hole (including the pin hole 306), and after the limit pin is inserted into the pin hole 306, it plays a limiting role on the aircraft wing.

[0053] like Figures 1 to 3 As shown, in this embodiment, a pair of symmetrically arranged reinforcement frames 310 are respectively provided at the middle and lower sections of the two guide rods 301;

[0054] The support base 100 is located on the upper surface of the outer periphery of the lower lobe rotating shell 101 and is provided with an annular guide support groove 312. An annular slider 313 is slidingly sleeved in the annular guide support groove 312. The upper surface of the annular slider 313 is fixedly connected to the bottom of the reinforcement frame 310, and the annular slider 313 is concentrically arranged with the turntable 106.

[0055] The coordinated design of the annular guide support groove 312 and the annular slider 313 further strengthens the support force area of ​​the reinforcement frame 310 , and the reinforcement frame further improves the stability of the guide rod.

[0056] like Figures 1 to 2 As shown, in this embodiment, an electromagnetic lock is provided on the contact surface between the annular guide support groove 312 and the annular slider 313 .

[0057] Through the design of the electromagnetic lock, on the basis of further strengthening the supporting force area of ​​the reinforcement frame 310, it cooperates with the locking structure set on the upper surface of the upper lobe rotating shell 102 to achieve double locking.

[0058] Working principle:

[0059] The wing connector 305 is connected to the aircraft wing to be assembled. The hydraulic jack 200 below the wing connector 305 can drive the aircraft wing to be assembled to rise and fall synchronously when it is raised and lowered, conveniently controlling the assembly of the aircraft wing to be assembled with the fuselage. During use, the wing connector 305 is connected to the wingtip of the aircraft wing to be assembled, and then the other end of the aircraft wing to be assembled, opposite the wingtip, is placed into the fuselage using manpower (or lifting equipment). The hydraulic jack 200 then lifts the wing connector 305 via the lifting rod 300, and the wing connector 305 drives the aircraft wing to move upward synchronously. The aircraft wing is lifted to a predetermined height, so that the mounting holes on the aircraft wing are aligned with the mounting holes on the fuselage. Finally, the mounting pins are inserted into the mounting holes of the aircraft wing and fuselage, thereby completing the assembly of the aircraft wing and fuselage.

[0060] The wing connector 305 is connected to the wingtip of the aircraft wing. The wingtip of the aircraft wing has a through-hole through which the wing connector 305 can be inserted and passed. The portion of the wing connector 305 that passes through the hole is provided with a pin hole 306. A stop pin is inserted into the pin hole 306 to limit the position of the aircraft wing. The wing connector 305 is horizontally arranged and can provide support for the aircraft wing. The wing connector 305 is cylindrical, with its axis perpendicular to the length of the lifting rod 300. The diameter of the wing connector 305 is approximately the same as the diameter of the hole in the wingtip of the aircraft wing. The wing connector 305 is provided with a pin hole 306 for inserting a limit pin. The limit pin is also used to limit the aircraft wing in the axial direction of the wing connector 305. The limit pin can be inserted into the pin hole 306 and can also be pulled out from the pin hole 306, which facilitates the disassembly and assembly between the wing connector 305 and the aircraft wing.

[0061] in,

[0062] Before connecting the wing connector 305 to the wingtip of the aircraft wing, the tooling is moved to a designated location. The turntable 106 is then adjusted so that the wing connector 305 faces the wingtip of the aircraft wing. The hydraulic jack 200 is then used to adjust the height of the lifting rod 300 until the wing connector 305 reaches the designated height. The locking mechanism 107 and / or electromagnetic lock is then activated to lock the turntable 106 and lifting rod 300. This improves the assembly flexibility of the aircraft wing and fuselage.

[0063] By turning the handle 309, the rotating disk 308 rotates, driving the wing connector 305 to rotate relative to the support cylinder 307. This adjusts the length of the side of the wing connector 305 facing the wingtip to accommodate the wingtip's axial hole. This ensures that the wing connector 305 is long enough to pass through the wingtip's axial hole and that the pin hole 306 is located outside the side being passed through. After the length of the wing connector 305 is adjusted, it is locked using Permatex 242 locking agent and / or a lock nut. This improves the assembly flexibility between the wing and the fuselage.

[0064] The foregoing description is merely a preferred embodiment of the present application and is not intended to limit the present application. Persons skilled in the art will readily appreciate that various modifications and variations are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present application shall be included within the scope of protection of the present application.

Claims

1. An auxiliary tool for assembling an aircraft wing, characterized by: The invention comprises a support base (100), a hydraulic jack (200) is rotatably provided on the upper surface of the support base (100), a vertically arranged lifting rod (300) is provided on the top surface of the hydraulic jack (200), and a wing connection structure is provided on the top of the lifting rod (300).

2. The auxiliary tool for assembling an aircraft wing according to claim 1, characterized in that: A square mounting hole is provided at the center of the support base (100), and a lower lobe rotating shell (101) is fixedly connected to the top edge of the mounting hole. The top of the lower lobe rotating shell (101) is connected to the upper lobe rotating shell (102) by bolts (103). A through hole is provided at the center of the upper lobe rotating shell (102), and a horizontally rotating mounting space is formed between the lower lobe rotating shell (101) and the upper lobe rotating shell (102). A turntable (106) is rotatably provided in the mounting space, and a turntable boss (104) is provided on the upper surface of the turntable (106) which extends upward and passes through the through hole at the center of the upper lobe rotating shell (102). The upper surface of the turntable boss (104) is fixedly connected to the bottom of the hydraulic jack (200).

3. The auxiliary tool for assembling an aircraft wing according to claim 2, characterized in that: The outer peripheral wall surface of the turntable boss (104) is provided with a plurality of locking holes (105) arranged at even intervals; A locking structure is provided on the upper surface of the upper petal rotating shell (102), the locking structure comprising a locking box body, a locking rod, a guide rod and a reset spring, a cylindrical receiving channel is provided in the locking box body, and the locking box body has limiting channels with reduced diameters at both ends of the receiving channel, which are arranged concentrically with and communicate with the receiving channel, and form an annular stepped annular transition; The rod body of the locking rod is slidably sleeved in a limiting channel close to a side of the turntable boss (104), and one end of the locking rod extends out of the limiting channel and matches the locking hole (105), and the other end of the locking rod extends into the receiving channel, and the other end of the locking rod is configured as a slider matching the inner contour of the receiving channel; One end of the guide rod is fixedly connected to the slider, and the other end of the guide rod extends out of the limiting channel of the locking structure away from the turntable boss (104). The return spring is sleeved on the guide rod, and one end of the return spring is fixedly connected to the slider, and the other end of the return spring is fixedly connected to the annular transition away from the turntable boss (104).

4. The auxiliary tool for assembling an aircraft wing according to claim 3, characterized in that: A pair of guide rods (301) are provided on the upper surface of the turntable boss (104) and are symmetrically arranged vertically. A connecting sleeve (311) is fixedly sleeved at the upper section of the exterior of the lifting rod (300). A guide sleeve (302) is slidably sleeved at the upper section of the exterior of the guide rod (301). The guide sleeve (302) and the connecting sleeve (311) are fixedly connected via a connecting rod (304).

5. The auxiliary tool for assembling an aircraft wing according to claim 4, characterized in that: The wing connection structure includes a support frame (303), a wing connection member (305) and a support cylinder (307). The top of the lifting rod (300) is fixedly connected to a support frame (303), and a support cylinder (307) is provided on the support frame (303). The middle part of the wing connecting member (305) is sleeved in the support cylinder (307) in a threaded connection manner, and the two ends of the wing connecting member (305) are located outside the support cylinder (307). A rotating disk (308) is provided at one end of the wing connecting member (305), and a handle (309) is provided on the rotating disk (308). A pin hole (306) is opened on the other end of the wing connecting member (305).

6. The auxiliary tool for assembling an aircraft wing according to claim 5, characterized in that: A pair of symmetrically arranged reinforcement frames (310) are respectively provided at the middle and lower sections of the two guide rods (301); The support base (100) is located on the upper surface of the outer periphery of the lower lobe rotating shell (101) and is provided with an annular guide support groove (312). An annular slider (313) is provided in the sliding sleeve of the annular guide support groove (312). The upper surface of the annular slider (313) is fixedly connected to the bottom of the reinforcing frame (310), and the annular slider (313) is concentrically arranged with the turntable (106).

7. The auxiliary tool for assembling an aircraft wing according to claim 6, characterized in that: An electromagnetic lock is provided on the contact surface between the annular guide support groove (312) and the annular slide block (313).

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