General assembly tool for helicopter assembly and helicopter assembly method

Abstract

The invention relates to the field of helicopter assembly processes, in particular to a final assembly tool for helicopter assembly and a helicopter assembly method. The final assembly tool comprises a final assembly base, a support and an undercarriage tool, the support and the undercarriage tool are installed on the final assembly base, the support is used for assembling a helicopter body of the helicopter, the undercarriage tool is used for assembling an undercarriage of the helicopter, and the undercarriage tool communicates with the support; and the fuselage and the undercarriage can be positioned to a mutual assembly position through the bracket and the undercarriage tool. Due to the integrated design of the undercarriage tool and the final assembly tool, during assembly, the fuselage and the undercarriage can be positioned to the mutual assembly position through the support and the undercarriage tool, operation is easy, use is convenient, the assembly efficiency is improved, and meanwhile the tool design and manufacturing cost is saved.

Description

Technical Field

[0001] The present invention relates to the field of helicopter assembly technology, and in particular to an assembly tool for helicopter assembly and a helicopter assembly method. Background Art

[0002] The landing gear of a helicopter includes a bow beam and a skid. Currently, the difficulty in assembling the landing gear of a helicopter, especially the electric vertical take-off and landing vehicle (eVTOL), mainly focuses on the positioning and installation of the bow beam of the landing gear.

[0003] Therefore, a dedicated ground-based landing gear tooling is required to assemble the landing gear, which is then docked with the helicopter fuselage. Setting up a separate landing gear tooling is expensive, and because tolerances are accumulated at the docking point, the docking process becomes more difficult. This reduces landing gear assembly efficiency, increases tooling costs, and increases commissioning time. Summary of the Invention

[0004] In view of this, the present invention provides a final assembly tool for helicopter assembly and a helicopter assembly method, thereby solving or at least alleviating one or more of the above-mentioned problems and other problems existing in the prior art.

[0005] In order to achieve the aforementioned objectives, a first aspect of the present invention provides an assembly tool for assembling a helicopter, wherein the assembly tool comprises an assembly base, a bracket installed on the assembly base, and a landing gear tool. The bracket is used to assemble the fuselage of the helicopter, and the landing gear tool is used to assemble the landing gear of the helicopter. The landing gear tool is connected to the bracket, and the fuselage and the landing gear can be positioned to a mutual assembly position through the bracket and the landing gear tool.

[0006] In the above-mentioned final assembly tooling, optionally, the final assembly base includes a base plate and a mounting member provided on the base plate, the base plate is used to install the bracket, and a plurality of the mounting members enclose an installation space for the landing gear tooling.

[0007] In the aforementioned final assembly tooling, optionally, the mounting member includes a vertical plate protruding from the base plate; the vertical plate abuts against an edge of the landing gear tooling to define a position of the landing gear tooling.

[0008] In the final assembly tooling as described above, optionally, the landing gear tooling includes side beams located on both sides and end beams located at both ends, and the side beams are connected to the end beams to form a frame structure; and the landing gear tooling includes a skid seat provided on the side beams, and a bow-shaped beam seat provided close to the end beams.

[0009] In the final assembly tooling as described above, optionally, the skid seat includes an end positioning member close to the end side beam, and a side positioning member distributed along the side side beam; the end positioning member is used to abut one end of the skid of the landing gear to limit the two end positions of the skid; the side positioning member is used to limit the circumferential position of the skid.

[0010] In the above-mentioned final assembly tool, optionally, the end positioning member includes an L-shaped plate mounted on the side beam, and an abutment plate connected to the L-shaped plate, wherein the abutment plate extends outward from the side beam and is used to abut one end of the skid; The side positioning member is protruding from the side surface of the side beam, and the side positioning member is provided with a first notch, and the first notch is used to limit the circumferential position of the slide.

[0011] In the above-mentioned assembly tool, optionally, the arched beam seat includes a support column protruding near the end side beam, and a bearing portion provided at the end of the support column; The bearing portion is a groove having two side plates. Second notches are provided at the top ends of the two side plates. The second notches are used to define the circumferential position of the arched beam of the landing gear.

[0012] In the assembly tooling as described above, optionally, the arched beam seat may further include a positioning device, which is a hook extending toward the outside of the side beam, and is used to clamp the end of the arched beam to limit the positions of the two ends of the arched beam.

[0013] In the assembly tooling as described above, optionally, a joint, a clamp and an adjustment gasket may be provided in the groove, the joint being used to clamp the arched beam from the top and bottom ends, the clamp being used to clamp the arched beam from both sides, and the adjustment gasket having a third recess, and the third recess being used to clamp and adjust the assembly position of the arched beam.

[0014] To achieve the aforementioned objective, a second aspect of the present invention provides a method for assembling a helicopter, the method using the final assembly tool as described in any one of the first aspects, the method comprising the following steps: Step A: placing the bow beam and skid of the landing gear of the helicopter on the landing gear tooling of the final assembly tooling; Step B: placing the fuselage of the helicopter in the bracket of the final assembly tool and positioning it in the assembly position with the landing gear; Step C: docking and assembling the arched beam and the fuselage; Step D: The skid of the landing gear is mounted on the arch beam.

[0015] The final assembly tooling of the present invention includes a final assembly base, a bracket mounted on the final assembly base, and a landing gear tooling. The landing gear tooling is connected to the bracket, thereby achieving an integrated design of the landing gear tooling and final assembly tooling, facilitating the simultaneous assembly of the landing gear and fuselage. During assembly, the fuselage and landing gear are positioned relative to each other using the bracket and landing gear tooling. This simple and convenient operation improves assembly efficiency while reducing tooling design and manufacturing costs.

[0016] The present invention also provides a method for assembling a helicopter. The method adopts the aforementioned final assembly tooling, and thus has various features of the aforementioned final assembly tooling, and thus also has its corresponding advantages. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The disclosure of the present invention will become more apparent with reference to the accompanying drawings, which are for illustrative purposes only and are not intended to limit the scope of protection of the present invention.

[0018] Figure 1 The figure is a schematic diagram of the overall structure of an embodiment of the final assembly tooling for helicopter assembly according to the present invention.

[0019] Figure 2 for Figure 1 A schematic diagram of a helicopter assembly of an embodiment of the final assembly tooling.

[0020] Figure 3 for Figure 1 A schematic structural diagram of the final assembly base in an embodiment of the final assembly tooling.

[0021] Figure 4 for Figure 1 A schematic structural diagram of a landing gear tooling of an embodiment of a final assembly tooling.

[0022] Figure 5 for Figure 4 A schematic diagram of the landing gear assembly of a helicopter of an embodiment of the final assembly tooling is shown.

[0023] Figure 6 for Figure 4 A schematic structural diagram of an end positioning member of a landing gear tooling according to an embodiment of the final assembly tooling.

[0024] Figure 7 for Figure 4 FIG. 1 is a partial schematic diagram of a landing gear tooling of an embodiment of a final assembly tooling, showing a bow beam seat.

[0025] Figure 8 for Figure 7 A partial schematic diagram of a bow beam seat of a landing gear tooling of an embodiment of a final assembly tooling.

[0026] Figure 9 for Figure 1 A schematic structural diagram of an adjustment gasket of a bow beam seat of a landing gear tooling according to an embodiment of an assembly tooling.

[0027] Figure 10 The figure is a helicopter assembly flow chart of the final assembly tooling for helicopters of the present invention.

[0028] In the figure: 1- final assembly tooling; 11- final assembly base; 12- base plate; 13- mounting member; 14- support plate; 15- vertical plate; 16- mounting hole; 17- bracket; 18- first end; 19- second end; 2- landing gear tooling; 22- side beam; 23- end beam; 24- reinforcing beam; 3- skid seat; 31- end positioning member; 32- side positioning member; 33- abutment plate; 34- L-shaped plate; 35- back plate; 36- first notch; 4- arched beam seat; 40- third notch; 41- load-bearing part; 42- joint; 43- positioning device; 44- adjusting gasket; 45- clamp; 46- support column; 47- second notch; 48- holding part; 49- adjusting part; 5- landing gear; 51- skid; 52- arched beam; 53- tee pipe; 6- fuselage. DETAILED DESCRIPTION

[0029] With reference to the accompanying drawings and specific embodiments, the structure, composition, characteristics and advantages of the final assembly tool for helicopter assembly and the helicopter assembly method of the present invention will be described below in an exemplary manner. However, all descriptions should not be used to form any limitations on the present invention.

[0030] In addition, for any single technical feature described or implied in the embodiments mentioned in this document, or any single technical feature shown or implied in the drawings, the present invention still allows for continued arbitrary combination or deletion between these technical features (or their equivalents) without any technical obstacles, and thus it should be considered that these more embodiments according to the present invention are also within the scope of the description in this document.

[0031] It should also be noted that the terms "inside", "outside", "top", "bottom", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship of the final assembly tooling used for helicopter assembly as shown in the accompanying drawings, and are only for the convenience of describing the present disclosure and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present disclosure.

[0032] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the quantity of the technical features indicated. Thus, features defined as "first" or "second" may explicitly or implicitly include at least one of these features.

[0033] In the description of the present disclosure, “a plurality of” means at least two, such as two, three or more, unless otherwise clearly defined.

[0034] from Figure 1 It can be seen that the final assembly tool 1 for helicopter assembly of the present invention includes a final assembly base 11, a bracket 17 installed on the final assembly base 11 and a landing gear tool 2. Figure 2 As can be seen, landing gear fixture 2 is used to assemble landing gear 5, and bracket 17 is used to assemble the helicopter fuselage 6 and its components. Landing gear fixture 2 is connected to bracket 17, meaning that during assembly, fuselage 6 placed on bracket 17 and landing gear 5 placed on landing gear fixture 2 are positioned to assemble with each other.

[0035] It should be noted here that, as shown in the figure, the final assembly tool 1 has one end of the nose of the fuselage 6 as the first end 18, the end opposite to the first end 18 as the second end 19, the direction of the fuselage 6 as the top end, and the direction of the landing gear 5 as the bottom end.

[0036] Specifically, if Figure 1 As shown, the final assembly base 11 includes a base plate 12 and a mounting member 13 provided on the base plate 12 . The base plate 12 is used to be placed on the ground or an operating table to support the entire final assembly tool 1 .

[0037] exist Figure 1 In the embodiment, the final assembly bases 11 are multiple components, located at the corners of the first and second ends 18 and 19 of the bottom of the final assembly tool 1, at the midpoint between the first and second ends 18 and 19, and at the midpoint of both sides. A total of eight final assembly bases 11 are provided. The eight final assembly bases 11 are positioned so that a smaller number of them, at both ends and both sides of the bottom of the final assembly tool 1, provide sufficient support for the bracket 17 and the landing gear tool 2, ensuring that the final assembly tool 1 is securely placed on the ground or operating table.

[0038] In an optional embodiment, the number of assembly bases 11 is not limited, and more assembly bases 11 can be provided at the bottom of the assembly tool 1 to strengthen the support of the assembly tool 1. In other embodiments, the assembly base 11 can also be a whole panel that completely covers the bottom of the assembly tool 1 to support the entire assembly tool 1.

[0039] Combine Figure 3 It can be seen that the mounting member 13 is protruding from the base plate 12, the base plate 12 is provided with a mounting hole 16, and the bracket 17 is mounted in the mounting hole 16. Figure 3In the embodiment, mounting member 13 is located in the middle of base plate 12, and mounting holes 16 are provided at the corners of base plate 12 so that brackets 17 avoid mounting member 13. In alternative embodiments, the location and number of mounting holes 16 are not limited and can be provided according to the number of brackets 17 to be installed. Mounting holes 16 can also be provided redundantly to prepare for the need for additional brackets 17 during helicopter assembly.

[0040] Optionally, the bracket 17 can be welded from steel sections to support the entire fuselage 6. The positioning of the fuselage 6 of the bracket 17 is debugged by a laser tracker to ensure the position of the fuselage 6 in the bracket 17, thereby ensuring the accuracy of assembly.

[0041] Combine Figure 1 and Figure 3 It can also be seen that the base plate 12 of each assembly base 11 is provided with a mounting member 13, and the mounting member 13 includes a vertical plate 15 protruding from the base plate 12. Optionally, the base plate 12 may also be provided with a support plate 14 and a vertical plate 15 protruding from the support plate 14. The support plate 14 is stacked on the base plate 12 and is used to place the landing gear tooling 2 (such as Figure 1 As shown), the landing gear tooling 2 is lifted up to keep a certain distance from the ground or the operating table to prevent dust and debris on the ground or the operating table from affecting the assembly of the landing gear 5 by the landing gear tooling 2.

[0042] Combine Figure 4 As shown, multiple vertical plates 15 are arranged along the base plate 12 to form an installation space for placing the landing gear tooling 2. The vertical plates 15 abut against the edges of the landing gear tooling 2, that is, the landing gear tooling 2 is limited to the space enclosed by the vertical plates 15, which is used to limit the position of the landing gear tooling 2.

[0043] exist Figure 3 In this embodiment, the vertical plate 15 is a triangular plate. This plate is simple in structure, compact, and does not interfere with other components of the final assembly tool 1. Furthermore, its shape is stable and facilitates upright support. As shown in the figure, one right-angled side of the triangular plate is mounted on the support plate 14, while the other right-angled side is perpendicular to the support plate 14. The other right-angled side perpendicular to the support plate 14 is used to abut the edge of the landing gear tool 2. Furthermore, the other right-angled sides of the multiple vertical plates 15 arranged along the base plate 12 all face the interior of the final assembly tool 1, thereby enclosing a mounting space for the landing gear tool.

[0044] Furthermore, if Figure 3 As shown, the tip of the triangle plate can be cut into a plane or set to a chamfered angle. The plane or the chamfered angle can prevent the tip from scratching the assembly parts of the helicopter and also prevent the tip from injuring the staff.

[0045] In an optional embodiment, the vertical plate 15 may also be in other shapes, such as but not limited to polygonal, wedge-shaped, convex, etc., as long as it can abut the edge of the landing gear tooling 2 to limit the landing gear tooling 2.

[0046] like Figure 4 As shown, the landing gear tooling 2 includes two side beams 22 disposed opposite to each other on both sides, and two end beams 23 disposed opposite to each other at both ends. The side beams 22 and the end beams 23 are sequentially connected to form a quadrilateral frame structure.

[0047] The side beams 22 and the end beams 23 are placed in the installation space surrounded by the mounting parts 13 of the assembly base 11, that is, the vertical plates 15 of the mounting parts 13 at both ends interact with each other to limit the two ends of the landing gear tooling 2; the vertical plates 15 of the mounting parts 13 at both sides interact with each other to limit the two sides of the landing gear tooling 2, so that the landing gear tooling 2 remains in a fixed position to ensure the landing gear 5 of the helicopter (such as Figure 2 Positioning installation as shown).

[0048] Furthermore, the landing gear tooling 2 also includes a reinforcing beam 24 cross-arranged inside the frame structure surrounded by the side beams 22 and the end beams 23. The reinforcing beam 24 is used to reinforce the frame structure to make the frame structure more stable.

[0049] from Figure 4 It can also be seen that the side beams 22 on both sides are respectively provided with skid seats 3, and the end beams 23 near both ends of the landing gear tooling 2 are respectively provided with arched beam seats 4. Figure 5 As shown, the skid seat 3 is used for placing and positioning a skid 51 of a landing gear 5 of a helicopter, and the arched beam seat 4 is used for placing and positioning an arched beam 52 of the landing gear 5 of the helicopter.

[0050] like Figure 4 As shown, the sled seat 3 includes an end positioning member 31 and a side positioning member 32. Figure 5 As can be seen in the figure, the middle section of the sled 51 is straight and tilted at both ends. The end locating member 31 is located on the side beam 22 near the end beam 23 of the first end 18, and is used to abut one end of the sled 51 to limit the position of the two ends of the sled 51. Multiple side locating members 32 are distributed along the side edges of the side beam 22, supporting the middle section of the sled 51 and defining its circumferential position. Thus, the side locating members 32 cooperate with the end locating members 31 to precisely position the sled 51 in the assembled position.

[0051] Specifically, combined Figure 6As can be seen, the end retainer 31 includes an L-shaped plate 34 mounted on the top surface of the side rail 22, and an abutment plate 33 connected to the L-shaped plate 34. One side of the L-shaped plate 34 is mounted on the top surface of the side rail 22, while the other side extends toward the top. The edge of the abutment plate 33 connects to the edge of the top-extending side panel of the L-shaped plate 34 near the first end 18. The abutment plate 33 forms a right angle with the L-shaped plate 34, extending outward from the side rail 22.

[0052] exist Figure 6 In the embodiment, the other vertical panel of the L-shaped plate 34 is a right-angled trapezoid, and the hypotenuse of the right-angled trapezoid is away from the installation position of the abutment plate 33, thereby reducing the sharp edges of the L-shaped plate 34, preventing the tip of the L-shaped plate 34 from damaging the assembly parts of the helicopter during assembly, and saving the manufacturing materials of the L-shaped plate 34.

[0053] Furthermore, the end positioning member 31 may also be provided with a support plate 35 located between the corners of the L-shaped plate 34. Specifically, the support plate 35 is a triangular plate, the right angles of which fit the corners of the L-shaped plate 34 to support the L-shaped plate 34 and prevent it from deformation.

[0054] When assembling, combine Figure 5 As shown, one end of the slide 51 abuts against the abutment plate 33 to define the positions of both ends of the slide 51. The side surfaces of the end of the slide 51 abut against the L-shaped plate 34, which further defines the positions of both sides of the slide 51.

[0055] like Figure 4 As shown, the side positioning member 32 is located on the side of the side beam 22 and protrudes outward. Figure 4 In the embodiment of the side positioning member 32, a first notch 36 is provided, and the opening of the first notch 36 faces the top. Figure 5 As shown, the shape of the edge of the first recess 36 is adapted to the middle section of the supporting slide 51 , and the curved edges on both sides of the first recess 36 engage with both sides of the slide 51 to define the positions of both sides of the slide 51 .

[0056] It should be noted that the positioning positions of the end positioning member 31 and the side positioning member 32 are adjusted by a laser tracker, and are used to position the slide 51 to ensure the assembly accuracy of the slide 51 .

[0057] from Figure 4 As can be seen, the arched beam seat 4 includes a support column 46 and a bearing portion 41 disposed at the end of the support column 46. The support column 46 protrudes from the reinforcement beam 24 near the end edge beam 23 and extends toward the top. The height of the support column 46 is adapted to fit the midsection of the arched beam 52 pair. The bearing portion 41 is used to support the arched beam 52.

[0058] In order to more stably support the arched beam 52 , at least two arched beam seats 4 are provided in the middle of the reinforcement beam 24 to locate the placement of the arched beam 52 .

[0059] Furthermore, the arched beam seat 4 may further include a positioning device 43 disposed on the top surface of the side beam 22. The positioning device 43 is a curved hook extending from the top surface of the side beam 22 toward the outside of the side surface. The hooks of the positioning devices 43 at both ends of the same side are oriented in opposite directions, respectively, bending toward the adjacent first end 18 or second end 19. The positioning device 43 is used to engage the end of the arched beam 52, that is, the end of the arched beam 52 is embedded in the curved hook, and the position of the arched beam 52 is defined by the positioning devices 43 disposed at opposite ends.

[0060] When assembling, Figure 5 As shown, the middle portion of the arched beam 52 is mounted on the bearing portion 41 , and both ends of the arched beam 52 are respectively clamped to the positioning devices 43 on both sides of the assembly tool 1 .

[0061] In order to more accurately define the position of the arched beam 52, as shown in FIG. Figure 7 As shown, the arched beam seat 4 may further include a joint 42, an adjusting washer 44, and a clamp 45 disposed in the bearing portion 41. The joint 42, the adjusting washer 44, and the clamp 45 are used to limit the arched beam 52.

[0062] Specifically, if Figure 8 As shown, the bearing portion 41 is a groove having two side plates, and a second recess 47 is provided at the top end of the two side plates. The shape of the second recess 47 is adapted to the shape of the arched beam 52 to carry the arched beam 52, that is, the arched beam 52 can be embedded in the second recess 47 and limited in the shape formed by the second recess 47, so that the second recess 47 limits the circumference of the arched beam 52.

[0063] The adjusting washer 44, the clamp 45, and the joint 42 are disposed within the groove. The joint 42 can be disposed on a side panel of the bearing portion 41, with the clamp 45 disposed adjacent to the joint 42. The joint 42 engages the arched beam 52 at both the top and bottom ends, while the clamp 45 engages the arched beam 52 at both sides. As a result, the arched beam 52 passing through the second notch 47 is secured by the joint 42 and the clamp 45 at the top, bottom, and both sides, respectively, to achieve more precise positioning of the arched beam 52.

[0064] It should be noted that the top clamping portion of the connector 42 is used for mounting on the fuselage 6 .

[0065] In order to further adjust the assembly position of the arched beam 52, an adjustment gasket 44 may be provided on the other side plate of the bearing portion 41. Figure 9 As shown, the adjusting gasket 44 includes a holding portion 48 and an adjusting portion 49 connected to the holding portion 48 . The adjusting portion 49 has a third notch 40 , so that the holding portion 48 and the adjusting portion 49 form a herringbone shape.

[0066] like Figure 8 As shown, when the adjusting gasket 44 is installed, the holding portion 48 protrudes from the side plate of the bearing portion 41, so that the clamping angle between the adjusting gasket 44 and the arched beam 52 can be adjusted from the outside through the holding portion 48, thereby adjusting the position of the arched beam 52 through the adjusting portion 49.

[0067] It should be noted that the bearing portion 41 , joint 42 , positioning device 43 , adjustment gasket 44 and clamp 45 of the arched beam seat 4 are all debugged by a laser tracker to ensure the accuracy of the assembly position of the arched beam 52 .

[0068] Furthermore, the present invention also provides a method for assembling a helicopter, which is as follows: Figure 2 and Figure 10 The assembly method is described as follows: Step A: The arched beam 52 and the skid 51 of the helicopter landing gear 5 are placed on the landing gear tooling 2 of the final assembly tooling 1 .

[0069] Specifically, the two skids 51 are respectively placed on the skid seats 3 on both sides of the landing gear tooling 2, the middle part of the skid 51 is placed on the side positioning piece 32 of the skid seat 3, and one end of the skid 51 is abutted against the end positioning piece 31, so that the skid 51 is located at the position defined by the skid seat 3, that is, the assembly position of the skid 51.

[0070] The two arched beams 52 are placed on the arched beam seat 4 near the first end 18 and the second end 19 respectively. The middle section of the arched beam 52 is placed on the bearing portion 41 of the arched beam seat 4. It is positioned by the clamp 45 and the joint 42 in the bearing portion 41, and the position of the arched beam 52 is precisely adjusted by adjusting the gasket 44.

[0071] Both ends of the arched beam 52 abut against the positioning devices 43 located at both ends, and at the positions where the positioning devices 43 are positioned, the ends of the arched beam 52 contact the slider 51 .

[0072] The positioning device 43 cooperates with the bearing portion 41 to accurately position the assembly position of the arched beam 52 .

[0073] Step B: The helicopter fuselage 6 is placed in the bracket 17 of the assembly tool 1 at the top end of the landing gear 5 .

[0074] Specifically, the arched beam mounting portion of the fuselage 6 is aligned with the arched beam 52 through the top end portion of the joint 42 .

[0075] Step C: The arched beam 52 is butt-jointed with the fuselage 6 , that is, the arched beam 52 is assembled at the corresponding position of the bottom of the fuselage 6 .

[0076] Step D: The slide 51 is mounted on the arched beam 52. That is, the contact portion between the slide 51 and the end of the arched beam 52 is connected by a tee pipe 53 (such as Figure 5 as shown) for fixed installation.

[0077] In this way, the assembly of the fuselage 6 and the landing gear 5 is completed.

[0078] The final assembly tool 1 for helicopter assembly of the present invention includes a bracket 17 for installing the fuselage 6 and a landing gear tool 2, that is, the landing gear tool 2 is integrated into the final assembly tool 1, so that the assembly positioning of the fuselage 6 and the landing gear 5 is achieved respectively through the bracket 17 and the landing gear tool 2.

[0079] Moreover, the various positioning components of the skid seat 3 and the arched beam seat 4 of the landing gear tooling 2 of the final assembly tooling 1 of the present invention are debugged by a laser tracker, so that the skid 51 placed on the skid seat 3 and the arched beam 52 placed on the arched beam seat 4 are pre-positioned to the assembly position.

[0080] The integrated design of the landing gear tooling 2 and the final assembly tooling 1 of the present invention facilitates the assembly of the landing gear 5 and the fuselage 6, and can be assembled at the same place. It is simple to operate and easy to use, which improves the assembly efficiency and saves tooling design and manufacturing costs.

[0081] Furthermore, the present invention also provides a method for assembling a helicopter using the aforementioned landing gear fixture 2. The method first installs the arched beam 52 to the fuselage 6, and then installs the skid 51 to the arched beam 52, thereby completing the assembly of the landing gear 5 and the fuselage 6. By adjusting the assembly sequence of the landing gear 5, the assembly and positioning of the fuselage 6 and the landing gear 5 are facilitated, thereby improving the assembly efficiency of the landing gear 5 and the fuselage 6.

[0082] The technical scope of the present invention is not limited to the contents of the above description. Those skilled in the art can make various deformations and modifications to the above embodiments without departing from the technical concept of the present invention, and these deformations and modifications should all fall within the scope of the present invention.

Claims

1. A final assembly tool for helicopter assembly, characterized in that: The final assembly tool (1) comprises a final assembly base (11), a bracket (17) mounted on the final assembly base (11), and a landing gear tool (2); the bracket (17) is used to assemble the fuselage (6) of the helicopter; the landing gear tool (2) is used to assemble the landing gear (5) of the helicopter; the landing gear tool (2) is connected to the bracket (17); the fuselage (6) and the landing gear (5) can be positioned to a mutual assembly position through the bracket (17) and the landing gear tool (2).

2. The final assembly tool according to claim 1, characterized in that: The assembly base (11) comprises a base plate (12) and a mounting member (13) provided on the base plate (12); the base plate (12) is used to mount the bracket (17); and a plurality of the mounting members (13) enclose an installation space for the landing gear tooling (2).

3. The final assembly tool according to claim 2, characterized in that: The mounting member (13) comprises a vertical plate (15) protruding from the base plate (12); the vertical plate (15) abuts against an edge of the landing gear tooling (2) and is used to limit the position of the landing gear tooling (2).

4. The final assembly tool according to claim 1, characterized in that: The landing gear tooling (2) comprises side beams (22) located at both sides, and end beams (23) located at both ends, wherein the side beams (22) and the end beams (23) are connected to form a frame structure; and the landing gear tooling (2) comprises a skid seat (3) arranged on the side beams (22), and a bow-shaped beam seat (4) arranged near the end beams (23).

5. The final assembly tool according to claim 4, characterized in that: The skid seat (3) includes an end positioning member (31) close to the end side beam (23) and a side positioning member (32) distributed along the side side beam (22); the end positioning member (31) is used to abut one end of the skid (51) of the landing gear (5) to limit the two end positions of the skid (51); the side positioning member (32) is used to limit the circumferential position of the skid (51).

6. The final assembly tool according to claim 5, characterized in that: The end positioning member (31) includes an L-shaped plate (34) mounted on the side beam (22), and an abutting plate (33) connected to the L-shaped plate (34), wherein the abutting plate (33) extends toward the outside of the side beam (22) and is used to abut one end of the slide (51); The side positioning member (32) is protruding from the side surface of the side beam (22), and the side positioning member (32) is provided with a first notch (36), and the first notch (36) is used to limit the circumferential position of the slide (51).

7. The final assembly tool according to claim 4, characterized in that: The arched beam seat (4) comprises a support column (46) protrudingly provided near the end side beam (23), and a bearing portion (41) provided at the end of the support column (46); The bearing portion (41) is a groove having two side plates. A second notch (47) is provided at the top end of the two side plates. The second notch (47) is used to limit the circumferential position of the arched beam (52) of the landing gear (5).

8. The final assembly tool according to claim 7, characterized in that: The arched beam seat (4) may further include a positioning device (43), wherein the positioning device (43) is a hook extending toward the outside of the side beam (22), and the positioning device (43) is used to clamp the end of the arched beam (52) to define the positions of the two ends of the arched beam (52).

9. The final assembly tool according to claim 7, characterized in that: A joint (42), a clamp (45) and an adjusting gasket (44) may also be provided in the groove, wherein the joint (42) is used to clamp the arched beam (52) from the top and bottom ends, the clamp (45) is used to clamp the arched beam (52) from both sides, and the adjusting gasket (44) has a third notch (40), and the third notch (40) is used to clamp and adjust the assembly position of the arched beam (52).

10. A method for assembling a helicopter, characterized in that: The assembly method adopts the final assembly tool (1) according to any one of claims 1 to 9, and the assembly method comprises the following steps: Step A: placing the arched beam (52) and the skid (51) of the landing gear (5) of the helicopter on the landing gear tooling (2) of the final assembly tooling (1); Step B: the fuselage (6) of the helicopter is placed in the bracket (17) of the assembly tool (1) and positioned at the assembly position with the landing gear (5); Step C: docking and assembling the arched beam (52) and the fuselage (6); Step D: The skid (51) of the landing gear (5) is mounted on the arched beam (52).

Images