An unmanned transport aircraft fuselage assembly jig

Abstract

This utility model discloses a fuselage assembly jig for an unmanned transport aircraft, comprising a main frame with multiple external clamps axially mounted inside. The main frame is a frame structure, with multiple upper mounting seats and multiple lower mounting seats installed on the upper and lower sides of the main frame. First supports are installed at both ends of opposite sides of the upper and lower mounting seats, and a second support is installed between two first supports. The external clamps include side clamps, upper clamps, and lower clamps. By installing multiple external clamps within the main frame according to the fuselage shape, and utilizing the shaping space within the external clamps that adapts to the fuselage's streamline, the four sections of the front and rear fuselage panels can be simultaneously shaped and assembled. This combines the traditional panel riveting jig and the overall fuselage assembly jig into one, reducing the number of jigs and lowering costs.

Description

Technical Field

[0001] This utility model relates to the field of unmanned transport aircraft manufacturing technology, and in particular to an unmanned transport aircraft fuselage assembly jig. Background Technology

[0002] The fuselage structure of a certain unmanned transport aircraft consists of a forward fuselage and a rear fuselage, with their docking points designed for separation. The main perimeter structure of the forward and rear fuselages is composed of four sections of panels (top, bottom, left, and right), each panel being riveted together from components such as frame plates, stringers, and skin. The front of the fuselage is connected to the nose cone, and the bottom of the fuselage has a drop-out hatch. The docking points between the fuselage and the center wing, as well as the docking points between the fuselage and the vertical and horizontal stabilizers, require very high positional precision. Traditional processes and tooling configurations would require at least multiple sets of riveting jigs for each panel and one set of fuselage assembly jigs. This results in a large number of tooling components, high costs, and does not meet the requirements for low-cost UAV manufacturing. Furthermore, the tooling occupies a significant amount of space. Utility Model Content

[0003] The technical problem to be solved by this utility model is to address the problems existing in the background art and provide an unmanned transport aircraft fuselage assembly frame. The assembly frame is designed based on the product digital model, and the traditional wall panel riveting frame and fuselage overall docking assembly frame are combined into one, reducing the number of frames and lowering the cost.

[0004] To achieve the above-mentioned technical features, the purpose of this utility model is as follows: An unmanned transport aircraft fuselage assembly frame includes a main frame with multiple external clamps axially mounted inside. The main frame is a frame structure. Multiple upper mounting seats and multiple lower mounting seats are respectively mounted on the upper and lower sides inside the main frame. First supports are respectively mounted on the two ends of the upper and lower mounting seats on opposite sides. A second support is installed between the two first supports. The external clamps include side clamps, upper clamps, and lower clamps. Two side clamps are longitudinally symmetrically mounted. The upper and lower ends of the side clamps are detachably connected to the first supports on the upper and lower mounting seats, respectively. The upper clamp is detachably mounted on the second support of the upper mounting seat, and the lower clamp is detachably mounted on the second support of the lower mounting seat. The upper clamp, lower clamp, and side clamps together form a shaping space, and the shaping space within the multiple external clamps is set according to the shape of the fuselage.

[0005] The main frame includes a front frame and a rear frame. The front frame has a rectangular frame structure, and the rear frame has a trapezoidal frame structure. The front frame and the rear frame are fixedly connected by two crossbeams on the upper and lower sides respectively.

[0006] The two ends of the upper and lower crossbeams are detachably connected and supported by two support rods.

[0007] The main frame is supported by a support column at its bottom.

[0008] The main frame is also equipped with a head cover positioning component, which is installed at an angle at the front of the main frame. The head cover positioning component is used to position the head end of the fuselage.

[0009] The headgear positioning assembly includes a slanted side plate, a slanted top plate, a bottom side plate, and a bottom middle plate. The two slanted side plates are symmetrically arranged. A first slanted support is detachably installed on the upper end of the slanted side plate. The first slanted support is fixedly installed with the corresponding upper mounting seat. A transverse connecting seat is detachably installed on the lower end of the slanted side plate. The transverse connecting seat is fixedly installed with the main frame. The inclined top plate is located at the top between the two inclined side plates, and a second inclined support is installed on the inclined top plate. The second inclined support is fixedly installed to the upper mounting base. The two bottom side plates are located at the lower ends of the two inclined side plates respectively, and the bottom side plates are detachably connected to the first support on the corresponding lower mounting base; The bottom center plate is located between the bottom side plates on both sides, and the bottom center plate is detachably connected to the second support on the corresponding lower mounting base.

[0010] Inside the main frame, and in front of the headgear positioning assembly, a headgear pivot positioning assembly is also installed. The headgear pivot positioning assembly includes an arc-shaped support plate. Both sides of the arc-shaped support plate are detachably connected to the headgear positioning assembly via connecting seats. An upper ear seat is installed on the arc-shaped support plate. The upper ear seat is detachably connected to a third support. The third support is installed and connected to an upper pull seat. The upper pull seat is fixed to the upper side of the inside of the main frame. A first positioning pin for positioning the headgear pivot is interlaced on the arc-shaped support plate.

[0011] The main frame is also equipped with a central wing positioning component. The central wing positioning component includes a frame, on which multiple ear plates are fixed. The ear plates are detachably connected to the corresponding shape plates. Multiple downwardly extending first positioning plates are installed on the frame, and second positioning pins are interlaced on the first positioning plates.

[0012] The rear end of the main frame is also equipped with a vertical tail positioning component. The vertical tail positioning component includes a longitudinal lifting beam and a transverse lifting beam. The two transverse lifting beams are respectively fixed to the two ends of the longitudinal lifting beam. The two ends of the transverse lifting beam are respectively fixed with a downwardly extending second positioning plate. A third positioning pin is interlaced on the second positioning plate. A fourth support is installed on the top of the transverse lifting beam. The fourth support is detachably connected to the second support on the corresponding mounting base.

[0013] A flat-tail positioning assembly is also installed on the rear end of the main frame. The flat-tail positioning assembly includes a transverse positioning rod, on which a third positioning plate extends forward. A fourth positioning pin is interlaced on the third positioning plate. A fifth support is installed at each end of the transverse positioning rod, and the fifth support is detachably installed on the main frame.

[0014] The features of this utility model using the above-mentioned technical solution are: 1. This utility model installs multiple shape plates inside the main frame according to the shape of the fuselage. Through the shaping space inside the shape plates, the shaping space is adapted to the streamline of the fuselage, and the four sections of the front fuselage and rear fuselage can be shaped and assembled at the same time. This combines the traditional wall panel riveting frame and the fuselage overall docking assembly frame into one, reducing the number of frames and lowering the cost.

[0015] 2. The main frame of this utility model is also equipped with a head cover positioning component. The head cover positioning component is installed obliquely at the front of the main frame and is used to position the head end of the fuselage.

[0016] 3. Inside the main frame of this utility model and on the front side of the head cover positioning component, a head cover pivot positioning component is also installed, which can position the head cover pivot installation position.

[0017] 4. The main frame of this utility model is also equipped with a central wing positioning component, which is used to position the central wing.

[0018] 5. The rear end of the main frame of this utility model is also equipped with a vertical tail positioning component, which is used to position the vertical tail installation position.

[0019] 6. A flat tail positioning component is also installed on the rear end of the main frame of this utility model, and the flat tail is positioned by the flat tail positioning component. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below.

[0021] Figure 1 This is a schematic diagram of the main structure of this utility model.

[0022] Figure 2 This is a three-dimensional structural diagram of the present invention.

[0023] Figure 3 for Figure 1 A schematic diagram of the three-dimensional structure at point A in the middle.

[0024] Figure 4 for Figure 1A schematic diagram of the three-dimensional structure at point B.

[0025] Figure 5 for Figure 1 A schematic diagram of the three-dimensional structure at point C.

[0026] Figure 6 for Figure 1 A schematic diagram of the three-dimensional structure at point D.

[0027] Figure label: Main frame 10, front frame 11, rear frame 12, column 13, crossbeam 14, support rod 15, upper mounting seat 16, first connecting plate 161, first support 162, second connecting plate 163, second support 164, first inclined support 165, second inclined support 166, lower mounting seat 17, transverse connecting seat 18, upper pull seat 19, upper ear seat 192, third support 191; External clamping plate 20, side clamping plate 21, upper clamping plate 22, lower clamping plate 23, bolt 24, shaping space 25; Headgear positioning assembly 30, inclined side plate 31, inclined top plate 32, bottom side plate 33, bottom middle plate 34; Headgear pivot positioning assembly 40, arc support plate 41, connecting seat 42, first positioning pin 43; Central wing positioning assembly 50, frame 51, ear plate 52, mounting bolt 53, first positioning plate 54, second positioning pin 55; Vertical tail positioning assembly 60, longitudinal lifting beam 61, transverse lifting beam 62, fourth support 621, second positioning plate 63, third positioning pin 64; Flat-tail positioning assembly 70, transverse positioning rod 71, third positioning plate 72, fourth positioning pin 73, fifth support 74. Detailed Implementation

[0028] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0029] It should be noted that the use of terms such as "an embodiment," "an embodiment," "an exemplary embodiment," and "some embodiments" in the specification indicates that the described embodiment may include a specific feature, structure, or characteristic, but not every embodiment necessarily includes that specific feature, structure, or characteristic. Furthermore, when a specific feature, structure, or characteristic is described in connection with an embodiment, implementing such a feature, structure, or characteristic in conjunction with other embodiments (whether explicitly described or not) should be within the knowledge of those skilled in the art.

[0030] Example 1: See Figure 1-3 An assembly frame for an unmanned transport aircraft includes a main frame 10. Multiple external mounting plates 20 are axially mounted within the main frame 10. The main frame 10 has a frame structure. Multiple upper mounting seats 16 and multiple lower mounting seats 17 are respectively mounted on the upper and lower sides inside the main frame 10. First supports 162 are respectively mounted at both ends of opposite sides of the upper and lower mounting seats 16 and 17. A second support 164 is installed between two first supports 162. The external mounting plates 20 include side plates 21, upper plates 22, and lower plates. 23. Two side plates 21 are longitudinally symmetrically installed. The upper and lower ends of the side plates 21 are detachably connected to the first supports 162 on the upper mounting base 16 and the lower mounting base 17, respectively. The upper plate 22 is detachably installed on the second support 164 of the upper mounting base 16, and the lower plate 23 is detachably installed on the second support 164 of the lower mounting base 17. The upper plate 22, the lower plate 23, and the side plates 21 on both sides together form a shaping space 25. The shaping space 25 within the multiple outer profile plates 20 follows the shape of the fuselage. By installing multiple outer profile plates 20 within the main frame 10 according to the shape of the fuselage, and through the shaping space 25 inside the outer profile plates 20, which is adapted to the fuselage streamline, the four sections of the front and rear fuselage panels can be simultaneously shaped and assembled. This combines the traditional panel riveting frame and the overall fuselage assembly frame, reducing the number of frames and lowering costs.

[0031] Specifically, see Figure 3 At the bottom of the upper mounting base 16 and the top of the lower mounting base 17, multiple first connecting plates 161 and second connecting plates 163 are welded at corresponding mounting positions. The first connecting plates 161 are bolted to the first support 162, and the second connecting plates 163 are bolted to the second support 164. In addition, the side clamping plate 21 and the first connecting plate 161, as well as the upper clamping plate 22 and the second support 164, are also detachably connected by bolts 24 so that the outer clamping plate 20 can be removed and the machine body taken out after the machine body is formed.

[0032] See Figure 2The main frame 10 includes a front frame 11 and a rear frame 12. The front frame 11 has a rectangular frame structure, and the rear frame 12 has a trapezoidal frame structure. The front frame 11 and the rear frame 12 are fixedly connected by two crossbeams 14 on the upper and lower sides respectively. The front frame 11 corresponds to the front fuselage of the unmanned transport aircraft fuselage structure, and the rear frame 12 corresponds to the rear fuselage of the unmanned transport aircraft fuselage structure.

[0033] Furthermore, the two ends of the upper and lower crossbeams 14 are detachably connected to two support rods 15 via bolts. This structure improves the structural strength of the main frame 10 located in the middle, preventing deformation of the middle part of the main frame 10 under gravity.

[0034] Furthermore, see Figure 2 A support column 13 is installed at the bottom of the main frame 10. The support column 13 is used to level the main frame 10 and fix it to the ground. The support column 13 includes a column body and a mounting plate welded to the lower end of the column body. The upper end of the column body is welded to the main frame 10, and the mounting plate is connected to the anchor bolts pre-installed in the ground.

[0035] Example 2: Based on Example 1, see Figure 1 , 4 The main frame 10 also has a head cover positioning component 30 installed inside. The head cover positioning component 30 is installed at an angle at the front of the main frame 10 and is used to position the head end of the fuselage.

[0036] Specifically, see Figure 4 The headgear positioning assembly 30 includes a sloping side plate 31, a sloping top plate 32, a bottom side plate 33, and a bottom middle plate 34. The two sloping side plates 31 are symmetrically arranged. A first sloping support 165 is detachably installed on the upper end of the sloping side plate 31. The first sloping support 165 is fixedly installed with the corresponding upper mounting seat 16. A transverse connecting seat 18 is detachably installed on the lower end of the sloping side plate 31. The transverse connecting seat 18 is fixedly installed with the main frame 10. The inclined top plate 32 is located at the top between the two inclined side plates 31. A second inclined support 166 is installed on the inclined top plate 32. The second inclined support 166 is fixedly installed with the upper mounting base 16. Two bottom side plates 33 are located at the lower ends of the two inclined side plates 31 respectively, and the bottom side plates 33 are detachably connected to the first support 162 on the corresponding lower mounting base 17. The bottom center plate 34 is located between the bottom side plates 33 on both sides, and the bottom center plate 34 is detachably connected to the second support 164 on the corresponding lower mounting base 17.

[0037] The head cover positioning component 30 is used to position the head cover end face at the head end of the fuselage.

[0038] Example 3: Based on Example 1 or Example 2, see Figure 4 Inside the main frame 10, and on the front side of the head cover positioning component 30, a head cover pivot positioning component 40 is also installed. Through the above structure, the mounting position of the head cover pivot can be positioned.

[0039] The head cover pivot positioning assembly 40 includes an arc-shaped support plate 41. Both sides of the arc-shaped support plate 41 are detachably connected to the head cover positioning assembly 30 via connecting seats 42. An upper ear seat 192 is mounted on the arc-shaped support plate 41, and the upper ear seat 192 is detachably connected to a third support seat 191. The third support seat 191 is installed and connected to an upper pull seat 19, which is fixedly attached to the upper inner side of the main frame 10. A first positioning pin 43 for positioning the head cover pivot is interlaced on the arc-shaped support plate 41. The position of the first positioning pin 43 is the installation position of the head cover pivot. After the machine body is formed, the first positioning pin 43 is removed.

[0040] Example 4: Based on Example 1, Example 2, or Example 3, see [link to example]. Figure 5 The main frame 10 also has a central wing positioning component 50 installed inside, which is used to position the central wing installation position.

[0041] Specifically, see Figure 5 The central wing positioning assembly 50 includes a frame 51, on which multiple ear plates 52 are fixed. The ear plates 52 are detachably connected to the corresponding shape plates 20 by mounting bolts 53. Multiple downwardly extending first positioning plates 54 are installed on the frame 51. Second positioning pins 55 are interlaced on the first positioning plates 54. After the fuselage is formed, the second positioning pins 55 are pulled out.

[0042] Example 5: Based on Example 1, Example 2, Example 3, or Example 4, see [link to example]. Figure 6 The main frame 10 also has a tail positioning component 60 installed at the rear end, which is used to position the tail installation position.

[0043] Specifically, see Figure 6 The vertical tail positioning assembly 60 includes a longitudinal lifting beam 61 and a transverse lifting beam 62. The two transverse lifting beams 62 are respectively fixed to both ends of the longitudinal lifting beam 61. The two ends of the transverse lifting beam 62 are respectively fixed with a downwardly extending second positioning plate 63. A third positioning pin 64 is inserted on the second positioning plate 63. A fourth support 621 is installed on the top of the transverse lifting beam 62. The fourth support 621 is detachably connected to the second support 164 on the corresponding upper mounting base 16. After the machine body is formed, the third positioning pin 64 is pulled out.

[0044] Example 6: Based on Example 1, Example 2, Example 3, Example 4, or Example 5, see [link to example]. Figure 6 A flat tail positioning component 70 is also installed on the rear end of the main frame 10, and the flat tail is positioned by the flat tail positioning component 70.

[0045] Specifically, see Figure 6 The flat tail positioning assembly 70 includes a transverse positioning rod 71, on which a third positioning plate 72 extends forward. A fourth positioning pin 73 is interposedly installed on the third positioning plate 72. Fifth supports 74 are installed at both ends of the transverse positioning rod 71. The fifth supports 74 are detachably installed on the main frame 10. After the body is formed, the fourth positioning pin 73 is pulled out.

[0046] The working principle or process of the utility model: The main frame 10 of the mold adopts a welded rigid frame structure. After welding, the whole assembly is subjected to stress-relief annealing in the furnace to fully eliminate welding stress and improve its dimensional stability. The outer shape clamp 20 is used to position the skin shape. The docking points of the fuselage with the nose cone, center wing, vertical tail, and horizontal tail are respectively provided with positioning structures on the mold for positioning. The positioning structure positions the frames by positioning the positioning holes on each frame.

[0047] After the fuselage is assembled, remove one side of the support rod 15 and one side of the external clamping plate 20 to remove the assembled fuselage. When removing the fuselage, other components that may affect its removal, such as the external clamping plate 20, must also be removed.

[0048] While specific embodiments of the present invention have been described above, those skilled in the art should understand that the specific embodiments described are merely illustrative and not intended to limit the scope of the present invention. Any modifications and variations made by those skilled in the art in accordance with the spirit of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. A fuselage assembly frame for an unmanned transport aircraft, comprising a main frame (10), wherein a plurality of external clamping plates (20) are axially mounted within the main frame (10), characterized in that: The main frame (10) is a frame structure. Multiple upper mounting seats (16) and multiple lower mounting seats (17) are installed on the upper and lower sides of the main frame (10). First supports (162) are installed at the two ends of opposite sides of the upper and lower mounting seats (16) respectively. A second support (164) is installed between the two first supports (162). The outer frame (20) includes a side plate (21), an upper plate (22), and a lower plate (23). The two side plates (21) are installed symmetrically in the longitudinal direction. The upper and lower ends of 21) are detachably connected to the first support (162) on the upper mounting base (16) and the lower mounting base (17) respectively. The upper clamping plate (22) is detachably installed on the second support (164) of the upper mounting base (16), and the lower clamping plate (23) is detachably installed on the second support (164) of the lower mounting base (17). The upper clamping plate (22), the lower clamping plate (23) and the side clamping plates (21) on both sides enclose and form a shaping space (25). The shaping space (25) in the multiple outer clamping plates (20) is set according to the shape of the fuselage.

2. The unmanned transport aircraft fuselage assembly jig according to claim 1, characterized in that: The main frame (10) includes a front frame (11) and a rear frame (12). The front frame (11) has a rectangular frame structure, and the rear frame (12) has a trapezoidal frame structure. The front frame (11) and the rear frame (12) are fixedly connected by two crossbeams (14) on the upper and lower sides respectively.

3. The unmanned transport aircraft fuselage assembly jig according to claim 2, characterized in that: The two ends of the upper and lower crossbeams (14) are detachably connected to two support rods (15).

4. The unmanned transport aircraft fuselage assembly frame according to any one of claims 1 to 3, characterized in that: The bottom of the main frame (10) is fitted with a support column (13).

5. The unmanned transport aircraft fuselage assembly jig according to claim 1, characterized in that: The main frame (10) is also equipped with a head cover positioning component (30). The head cover positioning component (30) is installed at an angle at the front of the main frame (10). The head cover positioning component (30) is used to position the head end of the fuselage.

6. The unmanned transport aircraft fuselage assembly jig according to claim 5, characterized in that: The headgear positioning assembly (30) includes a sloping side plate (31), a sloping top plate (32), a bottom side plate (33), and a bottom middle plate (34). The two sloping side plates (31) are symmetrically arranged. A first sloping support (165) is detachably installed on the upper end of the sloping side plate (31). The first sloping support (165) is fixedly installed with the corresponding upper mounting seat (16). A transverse connecting seat (18) is detachably installed on the lower end of the sloping side plate (31). The transverse connecting seat (18) is fixedly installed with the main frame (10). The inclined top plate (32) is located at the top between the two inclined side plates (31), and a second inclined support (166) is installed on the inclined top plate (32). The second inclined support (166) is fixed to the upper mounting base (16). Two bottom side plates (33) are located at the lower ends of the two inclined side plates (31) respectively, and the bottom side plates (33) are detachably connected to the first support (162) on the corresponding lower mounting base (17); The bottom center plate (34) is located between the bottom side plates (33) on both sides, and the bottom center plate (34) is detachably connected to the second support (164) on the corresponding lower mounting base (17).

7. The unmanned transport aircraft fuselage assembly jig according to claim 5, characterized in that: Inside the main frame (10), and on the front side of the head cover positioning assembly (30), a head cover pivot positioning assembly (40) is also installed. The head cover pivot positioning assembly (40) includes an arc-shaped support plate (41). The two sides of the arc-shaped support plate (41) are detachably connected to the head cover positioning assembly (30) via connecting seats (42). An upper ear seat (192) is installed on the arc-shaped support plate (41). The upper ear seat (192) is detachably connected to a third support (191). The third support (191) is installed and connected to an upper pull seat (19). The upper pull seat (19) is fixed to the upper side inside the main frame (10). A first positioning pin (43) for positioning the head cover pivot is interlaced on the arc-shaped support plate (41).

8. The unmanned transport aircraft fuselage assembly jig according to claim 1, characterized in that: The main frame (10) is also equipped with a central wing positioning component (50). The central wing positioning component (50) includes a frame (51). Multiple ear plates (52) are fixed on the frame (51). The ear plates (52) are detachably connected to the corresponding shape plate (20). Multiple downwardly extending first positioning plates (54) are installed on the frame (51). Second positioning pins (55) are interlaced on the first positioning plates (54).

9. The unmanned transport aircraft fuselage assembly jig according to claim 1, characterized in that: The main frame (10) is also equipped with a vertical tail positioning component (60) at its rear end. The vertical tail positioning component (60) includes a longitudinal lifting beam (61) and a transverse lifting beam (62). The two transverse lifting beams (62) are respectively fixed to the two ends of the longitudinal lifting beam (61). The two ends of the transverse lifting beam (62) are respectively fixed with a downwardly extending second positioning plate (63). A third positioning pin (64) is inserted on the second positioning plate (63). A fourth support (621) is installed on the top of the transverse lifting beam (62). The fourth support (621) is detachably connected to the second support (164) on the corresponding upper mounting seat (16).

10. The unmanned transport aircraft fuselage assembly jig according to claim 1, characterized in that: A flat-tail positioning assembly (70) is also installed on the rear end of the main frame (10). The flat-tail positioning assembly (70) includes a transverse positioning rod (71), a third positioning plate (72) extending forward is installed on the transverse positioning rod (71), a fourth positioning pin (73) is inserted on the third positioning plate (72), and a fifth support (74) is installed at both ends of the transverse positioning rod (71). The fifth support (74) is detachably installed on the main frame (10).

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