Assembly tool for inner and outer double-skin fuselage of electric aircraft

Abstract

The utility model relates to the technical field of aircraft assembly tools, in particular to an inner and outer double-skin fuselage assembly tool of an electric aircraft, which comprises a fuselage belly tool, an inner and outer double-skin fuselage assembly tool and an outer and inner double-skin fuselage assembly tool, and is characterized in that the fuselage belly tool is used for supporting and fixing a fuselage belly; the fuselage tail tool is used for supporting and fixing the tail of the fuselage; the two skin tools are arranged, the two skin tools are used for supporting and fixing a fuselage left skin and a fuselage right skin correspondingly, and the two skin tools are symmetrically arranged relative to the fuselage abdomen tool so that the two skin tools can be distributed in a separated mode; the two skin tools are symmetrically arranged relative to the fuselage belly tool, so that the two skin tools are distributed in a separated mode, the distance between the two skin tools can be adjusted, and therefore the separated double-skin tool can adapt to fuselage appearance faces of aircrafts of various models.

Description

TECHNICAL FIELD

[0001] The utility model relates to aircraft assembly tooling technical field especially relates to a kind of inside and outside double skin fuselage assembly tooling of electric aircraft. BACKGROUND

[0002] Aircraft process equipment is short for aircraft tooling, and the design and manufacture of aircraft tooling is a key link in aircraft product manufacturing, aircraft tooling supports the whole process of aircraft parts manufacturing and assembly, aircraft tooling has an extremely important position in aviation main machine factory production, aircraft tooling runs through the whole aircraft product development and production process, and the skin fuselage assembly tooling is a common aircraft tooling. SUMMARY

[0003] The utility model discloses a kind of inside and outside double skin fuselage assembly tooling of electric aircraft, with the advantage that the fuselage shape surface of multiple models of aircraft can be adapted.

[0004] To solve the above technical problems, the utility model adopts the following technical scheme:

[0005] A kind of inside and outside double skin fuselage assembly tooling of electric aircraft, comprising:

[0006] Fuselage abdominal tooling, the fuselage abdominal tooling is used to support and fix fuselage abdomen;

[0007] Fuselage tail tooling, the fuselage tail tooling is used to support and fix fuselage tail;

[0008] Skin tooling, the skin tooling is provided with two, two The skin tooling is used for left skin and right skin of fuselage to support and fix, two The skin tooling is symmetrically arranged about fuselage abdominal tooling, so that two The skin tooling is distributed in separated mode, each The skin tooling includes second fixed frame fixedly installed on ground, skin front section moving frame slidingly installed on second fixed frame, skin rear section moving frame slidingly installed on second fixed frame, at least one fuselage inner skin clamping plate installed on skin front section moving frame, at least one fuselage outer skin front section clamping plate installed on skin front section moving frame and at least one fuselage outer skin rear section clamping plate installed on skin rear section moving frame, and each The skin tooling is sliding adjustable tooling, so that two The skin tooling can adapt to the fuselage shape surface of multiple models of aircraft.

[0009] Preferably, the belly tooling comprises a first bottom frame fixedly installed on the ground and at least two first positioners installed on the top of the first bottom frame, and the at least two first positioners are respectively used for fixing the transverse frame of the belly and the longitudinal frame of the belly.

[0010] Further, each of the first positioners comprises a first positioning bracket installed on the first bottom frame and a first positioning pin installed on the first positioning bracket.

[0011] Further, the tail tooling comprises a first fixed frame fixedly installed on the ground, a moving frame slidably installed on the first fixed frame, at least one tail frame positioning plate installed on the moving frame, and at least one second positioner installed on the tail frame positioning plate, and the at least one second positioner is used for fixing the tail.

[0012] Further, the bottom of the moving frame is fixedly installed with a first sliding block, the top of the first fixed frame is fixedly installed with a first sliding rail matched with the first sliding block, and at least one limiting hole is formed in the first sliding rail, and the moving frame is limited and fixed by inserting the positioning rod into the limiting hole after moving to the fixed position.

[0013] Further, at least one second positioner is installed on each of the inner skin positioning plate, the front skin positioning plate and the rear skin positioning plate.

[0014] Further, the bottom of the front skin moving frame and the rear skin moving frame is installed with a second sliding block, the top of the second fixed frame is fixedly installed with a second sliding rail matched with the second sliding block, and at least one limiting hole is formed in the second sliding rail, and the front skin moving frame and the rear skin moving frame are limited and fixed by inserting the positioning rod into the limiting hole after moving to the fixed position.

[0015] Further, each of the second positioners comprises a first screw rod and a first nut threadedly connected with the first screw rod.

[0016] The beneficial effects of the utility model are as follows:

[0017] The two skin toolings are symmetrically arranged relative to the belly tooling, so that the two skin toolings are separately distributed, and the spacing between the two skin toolings can be adjusted, so that the separate double-skin tooling can adapt to the fuselage shapes of various models of aircrafts.

[0018] The fuselage tooling adopts a sliding rail form, realizes high-precision positioning through a precision guide mechanism, and ensures the strict alignment of the skin, the framework and other components. BRIEF DESCRIPTION OF DRAWINGS

[0019] In order to more clearly illustrate the technical scheme of the embodiments of the present application, the drawings needed in the embodiment description will be briefly introduced as follows. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0020] Figure 1 is a three-dimensional schematic view of the present application.

[0021] Figure 2 is a schematic view of the belly of the fuselage tool in use.

[0022] Figure 3 is a schematic view of the tail of the fuselage tool in use. Figure 2 is an enlarged schematic view of the structure at A in the present application.

[0023] Figure 4 is a schematic view of the tail of the fuselage tool in use.

[0024] Figure 5 is an enlarged schematic view of the structure at B in the present application. Figure 4

[0025] Figure 6 is another perspective view of the tail of the fuselage tool in use.

[0026] Figure 7 is an enlarged schematic view of the structure at C in the present application. Figure 6

[0027] Figure 8 is a schematic view of the skin tool in use.

[0028] Figure 9 is an enlarged schematic view of the structure at D in the present application. Figure 8

[0029] In the figure, the identification is as follows: 1, belly of the fuselage tool; 2, tail of the fuselage tool; 3, skin tool; 101, first bottom frame; 102, first positioner; 1021, first positioning bracket; 1022, first positioning pin; 201, first fixed frame; 202, moving frame; 203, tail frame positioning clamping plate; 204, second positioner; 2011, first slide rail; 2021, first sliding block; 2041, first screw; 2042, first nut; 301, second fixed frame; 302, skin front section moving frame; 303, skin rear section moving frame; 304, fuselage inner skin clamping plate; 305, fuselage outer skin front section clamping plate; 306, fuselage outer skin rear section clamping plate; 3011, second slide rail; 3021, second sliding block. ​​​DETAILED DESCRIPTION

[0030] The technical solutions in the embodiments of the utility model will be apparently and completely described in connection with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the protection scope of the utility model.

[0031] It should be understood that the terms "comprising" and "including" as used in the specification and the appended claims indicate the presence of the recited features, integers, steps, operations, elements, and / or components but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof.

[0032] It should also be understood that the terms used in the utility model specification are only for the purpose of describing specific embodiments and are not intended to limit the utility model. As used in the utility model specification and the appended claims, the singular forms "a", "an" and "the" are intended to include the plural forms unless the context clearly indicates otherwise.

[0033] It should be further understood that the term "and / or" as used in the utility model specification and the appended claims means any combination of one or more of the associated listed items and all possible combinations, and includes these combinations.

[0034] Embodiments

[0035] Please refer to Figures 1-9 As shown in the figure, an inner and outer double-skin fuselage assembly tool of an electric aircraft, a fuselage belly tool 1, a fuselage tail tool 2 and a skin tool 3, the fuselage belly tool 1 is used to support and fix the fuselage belly, the fuselage tail tool 2 is used to support and fix the fuselage tail, and the skin tool 3 is provided with two, two skin tools 3 are respectively used for supporting and fixing the left skin of the fuselage and the right skin of the fuselage, two skin tools 3 are symmetrically arranged about the fuselage belly tool 1, so that two skin tools 3 are separately distributed, and each skin tool 3 is a sliding adjustable tool, the distance between two skin tools 3 can be adjusted, so that two skin tools 3 can adapt to the fuselage shape of various models of aircraft.

[0036] As Figures 2-3 shown, the fuselage belly tool 1 includes a first bottom frame 101 fixedly installed on the ground and at least two first positioners 102 installed on the top of the first bottom frame 101, the fuselage belly tool 1 is fixedly connected with the ground as a whole, so as to ensure that the aircraft does not displace during assembly and does not affect the assembly precision of the aircraft.

[0037] As shown in Figure 3 At least two first positioners 102 are respectively used for fixing the transverse frame of the fuselage belly and the longitudinal frame of the fuselage belly;

[0038] The first positioner 102 generally comprises two parts, i.e. a first positioning bracket 1021 and a first positioning pin 1022, and the first positioning bracket 1021 is fixedly connected to the first bottom frame 101 through bolts; when the first positioning pin 1022 of the first positioner 102 is aligned with the holes of the transverse frame of the fuselage belly and the longitudinal frame of the fuselage belly, the first positioning pin 1022 is inserted into the holes to fix the aircraft parts;

[0039] Each first positioner 102 comprises a first positioning bracket 1021 mounted on the first bottom frame 101 and a first positioning pin 1022 mounted on the first positioning bracket 1021;

[0040] The first positioning pin 1022 can be a positioning rod with a handle, and when the first positioning pin 1022 of the first positioner 102 is aligned with the holes of the transverse frame of the fuselage belly and the longitudinal frame of the fuselage belly, the first positioning pin 1022 is inserted into the holes through the handle to fix the aircraft parts;

[0041] In addition, the first positioning pin 1022 can also be a positioning rod with a handle, and there is an external thread on the positioning rod, and the first positioning bracket 1021 is a threaded hole; when the first positioning pin 1022 of the first positioner 102 is aligned with the holes of the transverse frame of the fuselage belly and the longitudinal frame of the fuselage belly, the first positioning pin 1022 is rotated into the holes through the handle to fix the aircraft parts;

[0042] It should be noted that the first positioning bracket 1021 varies according to the structure of the aircraft parts in different positions.

[0043] As shown in Figures 4-7 The fuselage tail tooling 2 comprises a first fixed frame 201 fixedly installed on the ground, a moving frame 202 slidably installed on the first fixed frame 201, at least one tail frame positioning clamping plate 203 installed on the moving frame 202, and at least one second positioner 204 installed on the tail frame positioning clamping plate 203, the at least one second positioner 204 is used for fixing the fuselage tail, the first fixed frame 201 is used to provide support for the fuselage tail tooling 2, and the first fixed frame 201 is fixedly connected to the ground to ensure that the aircraft does not move during assembly and does not affect the assembly precision of the aircraft;

[0044] As shown in Figure 4 and Figure 6As shown, the actual shape and size of the tail frame positioning plate 203 are designed to follow the composite frame and metal frame at the tail of the fuselage.

[0045] like Figure 5 and Figure 7 As shown, the composite frame and metal frame at the rear of the fuselage are respectively installed on the corresponding tail frame positioning plate 203. When the holes opened in the composite frame and metal frame at the rear of the fuselage correspond one-to-one with the holes opened in the tail frame positioning plate 203, the second locator 204 can fix the composite frame and metal frame at the rear of the fuselage onto the corresponding tail frame positioning plate 203.

[0046] Specifically, such as Figure 5 and Figure 7 As shown, each second positioner 204 includes a first screw 2041 and a first nut 2042 threadedly connected to the first screw 2041. A handle is fixedly installed on the first screw 2041 and the first nut 2042 to facilitate the user's operation of the first screw 2041 and the first nut 2042.

[0047] The composite frame at the rear of the fuselage is installed on the corresponding tail frame positioning plate 203. When the holes in the composite frame at the rear of the fuselage correspond one-to-one with the holes in the tail frame positioning plate 203, the first screw 2041 is passed through the holes in the tail frame positioning plate 203 and the composite frame at the rear of the fuselage and extends out of the holes. Then, the first nut 2042 is screwed onto the part of the first screw 2041 that extends out of the holes. The composite frame is fixed by the cooperation of the first screw 2041 and the first nut 2042.

[0048] The metal frame at the rear of the fuselage is fixed in the same way as the composite frame at the rear of the fuselage, and will not be described in detail here.

[0049] The bottom of the movable frame 202 is fixedly installed with a first sliding block 2021, and the top of the first fixed frame 201 is fixedly installed with a first slide rail 2011 that cooperates with the first sliding block 2021. At least one limiting hole is provided on the first slide rail 2011. When the movable frame 202 moves to the fixed position, it is fixed by inserting a positioning rod into the limiting hole.

[0050] The first sliding block 2021 can adopt an Ω-shaped track groove, and the first slide rail 2011 can adopt an Ω-shaped guide rail. This arrangement allows the precision tolerance between the first sliding block 2021 and the first slide rail 2011 to be controlled within 0.05mm-0.10mm, thereby forming a precision guiding mechanism to ensure assembly accuracy.

[0051] The mobile frame 202 is capable of moving close to and away from the belly tooling 1 on the first fixed frame 201 through the cooperation of the first sliding block 2021 and the first sliding rail 2011. When the mobile frame 202 moves to a theoretical position, the position of the mobile frame 202 is fixed by inserting the positioning rod into the limiting hole provided on the first sliding rail 2011 to limit the first sliding block 2021. When the positioning rod is inserted into the limiting hole, a gap is left between the positioning rod and the mobile frame 202, which facilitates the removal of the positioning rod.

[0052] As shown in Figure 1 、 Figure 8 and Figure 9 , each skin tooling 3 comprises a second fixed frame 301 fixedly installed on the ground, a skin front section mobile frame 302 slidingly installed on the second fixed frame 301, a skin rear section mobile frame 303 slidingly installed on the second fixed frame 301, at least one fuselage inner skin clamping plate 304 installed on the skin front section mobile frame 302, at least one fuselage outer skin front section clamping plate 305 installed on the skin front section mobile frame 302, and at least one fuselage outer skin rear section clamping plate 306 installed on the skin rear section mobile frame 303. At least one second positioner 204 is installed on each of the fuselage inner skin clamping plate 304, the fuselage outer skin front section clamping plate 305, and the fuselage outer skin rear section clamping plate 306. The second fixed frame 301 is used to provide support for the fuselage skin tooling and is fixed with the ground to ensure that the aircraft does not displace during assembly and does not affect the assembly precision of the aircraft;

[0053] Each second positioner 204 comprises a first screw rod 2041 and a first screw nut 2042 threadedly connected with the first screw rod 2041. A handle is fixedly installed on each of the first screw rod 2041 and the first screw nut 2042 to facilitate the operation of the first screw rod 2041 and the first screw nut 2042 by the user;

[0054] The bottom of each of the skin front section mobile frame 302 and the skin rear section mobile frame 303 is provided with a second sliding block 3021. The top of the second fixed frame 301 is fixedly provided with a second sliding rail 3011 cooperating with the second sliding block 3021. At least one limiting hole is provided on the second sliding rail 3011. When the skin front section mobile frame 302 and the skin rear section mobile frame 303 move to a fixed position, the position is fixed by inserting a positioning rod into the limiting hole;

[0055] The second sliding block 3021 can adopt an Ω track slot, and the second sliding rail 3011 can adopt an Ω guide rail. In this way, the precision tolerance between the second sliding block 3021 and the second sliding rail 3011 is controlled within 0.05mm-0.10mm, thereby forming a precision guide mechanism to ensure assembly precision;

[0056] The skin front section moving frame 302 and the skin rear section moving frame 303 are arranged on the second fixed frame 301 through the cooperation of the second sliding block 3021 and the second sliding rail 3011, and can move close to and away from the fuselage belly tool 1. When the skin front section moving frame 302 and the skin rear section moving frame 303 move to the theoretical position, the position of the skin front section moving frame 302 and the skin rear section moving frame 303 is fixed by inserting the positioning rod into the limiting hole arranged on the second sliding rail 3011 to limit the second sliding block 3021. When the positioning rod is inserted into the limiting hole, a gap is left between the positioning rod and the moving frame 202, which facilitates the removal of the positioning rod.

[0057] Through the movable arrangement of the skin front section moving frame 302 and the skin rear section moving frame 303, the distance between the two skin front section moving frames 302 and the distance between the two skin rear section moving frames 303 arranged symmetrically with respect to the fuselage belly tool 1 can be adjusted, so that the fuselage shape surface of various models of aircrafts can be adapted.

[0058] Working principle:

[0059] Installation of the inner skin of the fuselage:

[0060] The front section composite frame of the fuselage is installed on the corresponding skin front section clamping plate 305 of the outer skin of the fuselage. When the holes arranged on the skin front section clamping plate 305 of the outer skin of the fuselage and the holes arranged on the front section composite frame of the fuselage correspond one by one, the first screw rod 2041 is inserted through the holes arranged on the skin front section clamping plate 305 of the outer skin of the fuselage and the front section composite frame of the fuselage and extends out of the holes, and then the first screw nut 2042 is screwed on the part of the first screw rod 2041 extending out of the holes. The first screw rod 2041 and the first screw nut 2042 cooperate to complete the fixation of the front end composite frame of the fuselage.

[0061] The inner skin is positioned on the skin front section moving frame 302 through the positioning hole of the inner skin, the inner skin clamping plate 304 is installed and attached to the inner skin of the fuselage, and finally the inner skin of the fuselage is fixed on the front section composite frame of the fuselage through the bolts.

[0062] Installation of the outer skin of the fuselage:

[0063] The tail section composite frame of the fuselage is installed on the corresponding tail frame positioning clamping plate 203. When the holes arranged on the tail section composite frame of the fuselage and the holes arranged on the tail frame positioning clamping plate 203 correspond one by one, the first screw rod 2041 is inserted through the holes arranged on the tail frame positioning clamping plate 203 and the tail section composite frame of the fuselage and extends out of the holes, and then the first screw nut 2042 is screwed on the part of the first screw rod 2041 extending out of the holes. The first screw rod 2041 and the first screw nut 2042 cooperate to complete the fixation of the tail section composite frame of the fuselage.

[0064] The outer skin is positioned on the skin front section moving frame 302 and the skin rear section moving frame 303 through the positioning hole of the fuselage outer skin, so that the fuselage outer skin front section clamping plate 305 and the fuselage outer skin rear section clamping plate 306 are attached to the fuselage outer skin, and finally the skin is attached to the fuselage front section composite frame and the fuselage rear section composite frame through the second sliding block 3021 and the second sliding rail 3011.

[0065] In summary, the two skin tooling 3 are symmetrically arranged relative to the fuselage belly tooling 1, so that the two skin tooling 3 are separately distributed, and the spacing between the two skin tooling 3 can be adjusted, so that the double skin tooling 3 of the utility model is separately distributed and can be adapted to the fuselage shape of various models of aircrafts;

[0066] Meanwhile, the fuselage tooling of the utility model adopts a sliding rail form, high-precision positioning is realized through a precision guide mechanism, and strict alignment of the skin, the framework and other components is ensured.

[0067] The above is only a specific implementation manner of the utility model, but the protection scope of the utility model is not limited to this, any skilled person in the art can easily think of various equivalent modifications or replacements within the technical range disclosed by the utility model, and these modifications or replacements should be covered in the protection scope of the utility model. Therefore, the protection scope of the utility model should be subject to the protection scope of the claims.

Claims

1. A tooling for assembling an inner and outer double-skin fuselage of an electric aircraft, characterized in that, include: The fuselage belly tooling (1) is used to support and fix the fuselage belly. The tail section tooling (2) is used to support and fix the tail section of the fuselage. The skin fitting (3) is provided in two parts. The two skin fittings (3) are used to support and fix the left skin and the right skin of the fuselage respectively. The two skin fittings (3) are symmetrically arranged about the fuselage belly fitting (1) so that the two skin fittings (3) are distributed separately. Each skin fitting (3) includes a second fixed frame (301) fixedly installed on the ground, a front skin moving frame (302) slidably installed on the second fixed frame (301), a rear skin moving frame (303) slidably installed on the second fixed frame (301), at least one inner skin clamping plate (304) installed on the front skin moving frame (302), at least one outer skin front clamping plate (305) installed on the front skin moving frame (302), and at least one outer skin rear clamping plate (306) installed on the rear skin moving frame (303).

2. The assembly fixture for the inner and outer double-skin fuselage of an electric aircraft according to claim 1, characterized in that, The fuselage belly tooling (1) includes a first bottom frame (101) fixedly installed on the ground and at least two first locators (102) installed on the top of the first bottom frame (101). The at least two first locators (102) are used to fix the transverse frame and the longitudinal frame of the fuselage belly, respectively.

3. The assembly fixture for the inner and outer double-skin fuselage of an electric aircraft according to claim 2, characterized in that, Each of the first locators (102) includes a first positioning bracket (1021) mounted on a first bottom frame (101) and a first positioning pin (1022) mounted on the first positioning bracket (1021).

4. The assembly fixture for the inner and outer double-skin fuselage of an electric aircraft according to claim 1, characterized in that, The tail section fixture (2) includes a first fixed frame (201) fixedly installed on the ground, a movable frame (202) slidably installed on the first fixed frame (201), at least one tail frame positioning plate (203) installed on the movable frame (202), and at least one second locator (204) installed on the tail frame positioning plate (203). At least one second locator (204) is used to fix the tail section of the fuselage.

5. The assembly fixture for the inner and outer double-skin fuselage of an electric aircraft according to claim 4, characterized in that, The bottom of the movable frame (202) is fixedly installed with a first sliding block (2021), and the top of the first fixed frame (201) is fixedly installed with a first slide rail (2011) that cooperates with the first sliding block (2021). The first slide rail (2011) is provided with at least one limiting hole. When the movable frame (202) moves to a fixed position, it is fixed by inserting a positioning rod into the limiting hole.

6. The assembly fixture for the inner and outer double-skin fuselage of an electric aircraft according to claim 1, characterized in that, At least one second locator (204) is installed on the inner fuselage skin clamping plate (304), the front section clamping plate (305) of the outer fuselage skin, and the rear section clamping plate (306) of the outer fuselage skin.

7. The assembly fixture for the inner and outer double-skin fuselage of an electric aircraft according to claim 6, characterized in that, The bottom of both the front moving frame (302) and the rear moving frame (303) of the skin is equipped with a second sliding block (3021). The top of the second fixed frame (301) is fixedly equipped with a second slide rail (3011) that cooperates with the second sliding block (3021). At least one limiting hole is provided on the second slide rail (3011). When the front moving frame (302) and the rear moving frame (303) of the skin move to the fixed position, the positioning rod is inserted into the limiting hole to limit and fix them.

8. The assembly fixture for the inner and outer double-skin fuselage of an electric aircraft according to claim 4 or 6, characterized in that, Each of the second positioners (204) includes a first screw (2041) and a first nut (2042) threadedly connected to the first screw (2041).

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