Fuselage and horizontal tail integrated structure for eVTOL aircraft

Abstract

The utility model discloses a fuselage and horizontal tail integrated structure for an eVTOL aircraft, and relates to the technical field of aircrafts. The integrated structure comprises a rear fuselage structure and a horizontal tail structure; the rear fuselage structure comprises a rear fuselage upper longitudinal beam, a rear fuselage lower longitudinal beam, a rear fuselage frame and a rear fuselage skin, the rear fuselage frame is welded between the rear fuselage upper longitudinal beam and the rear fuselage lower longitudinal beam, and the rear fuselage skin is connected with the rear fuselage frame through bolts; the horizontal tail structure comprises a horizontal tail front beam, a horizontal tail rear beam, horizontal tail box section ribs and a horizontal tail skin, a plurality of horizontal tail box section ribs are uniformly fixed between the horizontal tail front beam and the horizontal tail rear beam, and each horizontal tail box section rib is fixedly connected with the horizontal tail skin; the rear fuselage upper longitudinal beam is in glue joint with the horizontal tail front beam, the rear fuselage upper longitudinal beam is in glue riveting with the horizontal tail front beam through a metal connector, and the rear fuselage skin is in lap joint with the horizontal tail skin. According to the fuselage and horizontal tail integrated structure, the number of parts can be reduced, the assembly working hours can be shortened, the weight of an aircraft can be reduced, and the design of the aircraft is more reasonable.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft, especially a fuselage and flat tail integrated structure for eVTOL aircraft. BACKGROUND

[0002] The flat tail is an important structure of the aircraft, and the elevator of the aircraft is installed on the flat tail box section to provide the pitch control of the aircraft. At present, the fuselage and the flat tail of most aircrafts are manufactured and assembled separately, and finally connected in the final assembly stage.

[0003] The existing flat tail and fuselage connection scheme is suitable for large-sized aircrafts, and the flat tail and the fuselage are separately manufactured and assembled, which is more reasonable.

[0004] For eVTOL small aircrafts, the size of the flat tail and the fuselage is not large, and the scheme of separate manufacturing and assembly in the final assembly stage has the defects of large number of parts, long assembly time and labor, and is not conducive to weight reduction of the aircraft. Based on this, the utility model provides a fuselage and flat tail integrated structure for eVTOL aircraft. SUMMARY

[0005] The utility model provides a kind of fuselage and flat tail integrated structure for eVTOL aircraft, comprising: rear fuselage structure (1) and flat tail structure (2);Rear fuselage structure (1) includes rear fuselage upper longitudinal beam (11), rear fuselage lower longitudinal beam (12), rear fuselage frame (13) and rear fuselage skin (14), rear fuselage frame (13) is welded between rear fuselage upper longitudinal beam (11) and rear fuselage lower longitudinal beam (12), rear fuselage skin (14) is covered in the fuselage structure of rear fuselage longitudinal beam (11) and rear fuselage frame (13) composition, with rear fuselage frame (13) is connected by bolt;Flat tail structure (2) includes flat tail front beam (21), flat tail rear beam (22), flat tail box section rib (23) and flat tail skin (24), multiple flat tail box section ribs (23) are evenly fixed between flat tail front beam (21) and flat tail rear beam (22), and each flat tail box section rib (23) is fixedly connected with flat tail skin (24);Rear fuselage upper longitudinal beam (11) is fixed by cementing method with flat tail front beam (21), rear fuselage upper longitudinal beam (11) is connected by metal joint (112) cement riveting with flat tail front beam (21), and rear fuselage skin (14) is lap jointed and fixed above flat tail box section rib (23) in the middle of flat tail structure (2) with flat tail skin (24).

[0006] The utility model discloses a kind of fuselage and flat tail integrated structure for eVTOL aircraft as described above, wherein, recess capable of accommodating rear fuselage longitudinal beam (11) is set in rear fuselage frame (13) outer edge, and rear fuselage longitudinal beam (11) is respectively installed in the recess of rear fuselage frame (13) outer edge, and is fixed by bolt.

[0007] The fuselage and horizontal tail integrated structure for the eVTOL aircraft, wherein the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are designed as "C" section beams, and the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are fixed by gluing.

[0008] The fuselage and horizontal tail integrated structure for the eVTOL aircraft, wherein the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are designed as "C" section beams, and the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are fixed by gluing.

[0009] The fuselage and horizontal tail integrated structure for the eVTOL aircraft, wherein the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are designed as "C" section beams, and the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are fixed by gluing.

[0010] The fuselage and horizontal tail integrated structure for the eVTOL aircraft, wherein the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are designed as "C" section beams, and the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are fixed by gluing.

[0011] The fuselage and horizontal tail integrated structure for the eVTOL aircraft, wherein the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are designed as "C" section beams, and the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are fixed by gluing.

[0012] The fuselage and horizontal tail integrated structure for the eVTOL aircraft, wherein the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are designed as "C" section beams, and the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are fixed by gluing.

[0013] The fuselage and horizontal tail integrated structure for the eVTOL aircraft, wherein the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are designed as "C" section beams, and the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are fixed by gluing.

[0014] The fuselage and horizontal tail integrated structure for the eVTOL aircraft, wherein the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are designed as "C" section beams, and the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are fixed by gluing.

[0015] The fuselage and horizontal tail integrated structure for the eVTOL aircraft, wherein the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are designed as "C" section beams, and the rear fuselage longitudinal beam (11) and the horizontal tail front beam (21) are fixed by gluing.

[0016] (1) The fuselage and flat tail integrated structure provided by the utility model can reduce the number of parts, shorten the assembly time, and reduce the weight of the aircraft, so that the design of the aircraft is more reasonable.

[0017] (2) The efficient integration and performance optimization of the structure are realized, which not only improves the overall performance of the aircraft, but also provides a new idea and direction for future aircraft design. BRIEF DESCRIPTION OF DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the utility model or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments described in the utility model, and other drawings can also be obtained by those skilled in the art according to these drawings.

[0019] Figure 1 A fuselage and flat tail integrated structure for an eVTOL aircraft is provided for the embodiments of the utility model;

[0020] Figure 2 For Figure 1 An enlarged view of the connection part of the middle and rear fuselage upper longitudinal beam 11 and the flat tail front beam 21;

[0021] Figure 3 For Figure 1 An enlarged view of the connection part of the middle and rear fuselage lower longitudinal beam 12 and the flat tail front beam 21;

[0022] Figure 4 For Figure 1 An enlarged view of the connection part of the middle and rear fuselage skin 14 and the flat tail skin 24;

[0023] Figure 5 A schematic view of the cross-sectional beam shape of the rear fuselage upper longitudinal beam;

[0024] Figure 6 A schematic view of the cross-sectional beam shape of the rear fuselage lower longitudinal beam.

[0025] Reference signs:

[0026] 1, rear fuselage structure; 2, flat tail structure; 3, vertical tail structure; 11, rear fuselage upper longitudinal beam; 12, rear fuselage lower longitudinal beam; 13, rear fuselage frame; 14, rear fuselage skin; 113, anti-peeling fastener; 114, metal joint; 21, flat tail front beam; 22, flat tail rear beam; 23, flat tail box section rib; 24, flat tail skin; 251, left flat tail; 252, right flat tail; 253, middle fuselage connection section. DETAILED DESCRIPTION

[0027] 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, not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0028] Example

[0029] like Figures 1-4 As shown, this utility model provides an integrated fuselage and horizontal stabilizer structure for an eVTOL aircraft, including: a rear fuselage structure 1 and a horizontal stabilizer structure 2; the rear fuselage structure 1 includes an upper rear fuselage longitudinal beam 11, a lower rear fuselage longitudinal beam 12, a rear fuselage frame 13, and a rear fuselage skin 14, with the rear fuselage frame 13 welded between the upper and lower rear fuselage longitudinal beams 11 and 12, and the rear fuselage skin 14 covering the fuselage structure composed of the rear fuselage longitudinal beams 11 and the rear fuselage frame 13, and connected to the rear fuselage frame 13 by bolts; the horizontal stabilizer structure 2... The structure includes a horizontal tail front beam 21, a horizontal tail rear beam 22, horizontal tail box section ribs 23, and a horizontal tail skin 24. Multiple horizontal tail box section ribs 23 are evenly fixed between the horizontal tail front beam 21 and the horizontal tail rear beam 22, and each horizontal tail box section rib 23 is fixedly connected to the horizontal tail skin 24. The rear fuselage longitudinal beam 11 is fixed to the horizontal tail front beam 21 by adhesive bonding, and the rear fuselage longitudinal beam 11 is connected to the horizontal tail front beam 21 by adhesive riveting through metal joints 112. The rear fuselage skin 14 and the horizontal tail skin 24 are overlapped and fixed above the horizontal tail box section ribs 23 in the middle of the horizontal tail structure 2.

[0030] The rear fuselage structure 1 includes two upper rear longitudinal beams 11 and three lower rear longitudinal beams 12. The upper rear longitudinal beams 11 adopt a "C" shaped cross-section beam design (e.g., Figure 5 As shown), the rear fuselage lower longitudinal beam 12 adopts an "Ω" shaped cross-section beam design (as shown). Figure 6 (As shown).

[0031] The rear fuselage frame 13 is installed between the two upper rear longitudinal beams 11 and the three lower rear longitudinal beams 12, serving as longitudinal beam support. The rear fuselage frame 13 is welded to the two upper rear longitudinal beams 11 and the three lower rear longitudinal beams 12. This connection method can withstand large loads while maintaining structural integrity. Specifically, five grooves are formed on the outer edge of the rear fuselage frame 13 to accommodate the rear fuselage longitudinal beams. The five rear fuselage longitudinal beams are respectively installed in the grooves on the outer edge of the rear fuselage frame 13 and fixed with bolts. The rear fuselage frame 13 is made of high-strength, lightweight materials to reduce overall weight and improve the load-bearing capacity of the structure.

[0032] The rear fuselage skin 14 covers the fuselage structure composed of the upper rear longitudinal beam 11, the lower rear fuselage longitudinal beam 12, and the rear fuselage frame 13. The rear fuselage skin 14 and the rear fuselage frame 13 are connected by bolts to ensure the connection is firm.

[0033] The rear fuselage structure 1 is vertically arranged with the horizontal tail structure 2, the horizontal tail structure 2 is located at the rear side of the rear fuselage structure 1, and the rear fuselage structure 1 is fixedly connected with the middle section of the horizontal tail structure 2, so as to divide the horizontal tail structure 2 into a left horizontal tail 251, a right horizontal tail 252 and a middle fuselage connecting section 253.

[0034] The horizontal tail structure 2 comprises a horizontal tail skin 24, a horizontal tail front beam 21, a horizontal tail rear beam 22 and horizontal tail box section ribs 23, the horizontal tail front beam 21 and the horizontal tail rear beam 22 are arranged in parallel, and the horizontal tail front beam 21 and the horizontal tail rear beam 22 are fixedly connected through a plurality of horizontal tail box section ribs 23 between the horizontal tail front beam 21 and the horizontal tail rear beam 22, the horizontal tail box section ribs 23 are uniformly distributed between the horizontal tail front beam 21 and the horizontal tail rear beam 22 and are fixedly connected with the horizontal tail front beam 21 and the horizontal tail rear beam 22 respectively. The horizontal tail front beam 21 and the horizontal tail rear beam 22 are used as parallel arranged cross beams, and the plurality of horizontal tail box section ribs 23 are used as parallel arranged longitudinal beams, so that the structure strength and stability are improved, and the overall performance of the aircraft is optimized through the horizontal tail front beam 21, the horizontal tail rear beam 22 and the horizontal tail box section ribs 23.

[0035] Preferably, the middle fuselage connecting section 253 of the horizontal tail front beam 21 and the horizontal tail rear beam 22 is designed to be increased in height and width, that is, the size of the middle fuselage connecting section 253 is greater than that of the left and right horizontal tails 252, so as to adapt to the shape change of the fuselage. The horizontal tail box section rib 23 comprises ten, of which four are arranged on the left horizontal tail 251 and the right horizontal tail 252 respectively, and the other two horizontal tail box section ribs 23 are arranged at the increased height and width of the middle fuselage connecting section 253 of the horizontal tail front beam 21 and the horizontal tail rear beam 22. Further, in order to reduce the weight of the fuselage, the horizontal tail box section rib 23 is a hollow support frame structure.

[0036] The horizontal tail skin 24 is arranged along the extension direction of the horizontal tail front beam 21 and the horizontal tail rear beam 22 with the horizontal tail box section rib 23 as a support point, forming a solid and light structure to withstand various stresses and loads during flight. The horizontal tail skin 24 is connected with the horizontal tail front beam 21 and the horizontal tail rear beam 22 through the combination of cementing and bolting, so as to ensure the stability and reliability of the structure.

[0037] Figure 2 For Figure 1 An enlarged view of the connection part of the rear fuselage longitudinal beam 11 and the horizontal tail front beam 21. The rear fuselage longitudinal beam 11 and the horizontal tail front beam 21 are both designed as "C" shaped cross section beams, and the cross section beams of the rear fuselage longitudinal beam 11 and the horizontal tail front beam 21 are fixedly connected through cementing. Further, in order to enhance the strength and reliability of the connection part of the rear fuselage longitudinal beam 11 and the horizontal tail front beam 21, two anti-peeling fasteners 111 are respectively installed near the upper edge strip and the lower edge strip of the longitudinal beam.

[0038] Figure 3 For Figure 1Figure 2 is an enlarged view of the connection between the rear fuselage lower longeron 12 and the horizontal tail front longeron 21. The rear fuselage lower longeron 12 is designed as an "Ω" cross-section beam. Metal joints 112 are arranged at the contact positions of the rear fuselage lower longeron 12 and the horizontal tail front longeron 21. The rear fuselage lower longeron 12 is connected to the horizontal tail front longeron 21 through the metal joints 112. Preferably, two metal joints 112 are arranged at the contact positions of each rear fuselage longeron 11 and the horizontal tail front longeron 21. The three faces of each metal joint 112 are connected to the flange, web of the rear fuselage lower longeron 12 and the web of the horizontal tail front longeron 21 respectively. The metal joints 112 and the longerons are connected by means of glue riveting, which not only ensures the strength of the structure, but also has good corrosion resistance. The metal joints 112 take into account the difference in thermal expansion coefficient between different components, and special alloy materials are used to ensure good connection performance under different temperature conditions. The shape and size of the metal joints 112 are designed to adapt to the stress distribution under different load conditions, thereby ensuring the long-term stability and reliability of the integrated structure.

[0039] Figure 4 For Figure 1 Figure 3 is an enlarged view of the connection between the rear fuselage skin 14 and the horizontal tail skin 24. The rear fuselage skin 14 segment located in the middle fuselage connecting segment 253 of the horizontal tail structure 2 is fixed between the horizontal tail skin 24 segments of the left and right horizontal tail 252 by means of lap joint. The lap joint position is above the horizontal tail box segment rib 23 at both ends of the middle fuselage connecting segment 253 of the horizontal tail structure 2, and the horizontal tail skin 24 is lap jointed and fixed on the rear fuselage skin 14. The lap joint width is the width of the entire flange of the horizontal tail box segment rib 23. This design not only ensures the strength of the connection position, but also has good aerodynamic performance.

[0040] Behind the middle fuselage connecting segment 253 of the horizontal tail structure 2 is the vertical tail structure 3. The vertical tail skin of the vertical tail structure 3 is connected to the horizontal tail skin 24 and the rear fuselage skin 14 to form an integrated structure, and is coordinated with the aerodynamic layout of the fuselage and the wing in terms of aerodynamic performance. The shape and size of the vertical tail structure 3 are optimized to provide optimal stability and controllability.

[0041] In the embodiments of the present application, the skins are all made of advanced composite materials, which not only have excellent strength and stiffness, but also perform well in weight reduction.

[0042] It is apparent for a person skilled in the art that the present application is not restricted to the details of the foregoing exemplary embodiments, and the present application can be implemented in other concrete forms without departing from the spirit or essential characteristics of the present application. Therefore, the embodiments should be considered in all respects as illustrative and not restrictive, the scope of the present application being indicated by the appended claims rather than that of the foregoing description, and all changes coming within the meaning and range of equivalency of the claims are intended to be embraced therein. Any reference signs in the claims should not be construed as limiting the claims to the figures in which the reference signs are used.

[0043] In the description of the present application, unless otherwise specified and limited, the meaning of "a plurality of" is two or more; the orientation or positional relationship indicated by the terms "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail" and the like is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", "third" and the like are only for the purpose of description and cannot be understood as indicating or implying relative importance.

[0044] In the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "connected", "connected" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium. For a person skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

Claims

1. A fuselage and tailplane integrated structure for an eVTOL aircraft, characterized in that, The utility model relates to a kind of vertical tail structure and horizontal tail structure of aircraft, including: Rear fuselage structure (1) and flat tail structure (2);Rear fuselage structure (1) includes rear fuselage upper longitudinal beam (11), rear fuselage lower longitudinal beam (12), rear fuselage frame (13) and rear fuselage skin (14), rear fuselage frame (13) is welded between rear fuselage upper longitudinal beam (11) and rear fuselage lower longitudinal beam (12), rear fuselage skin (14) covers the fuselage structure outside that rear fuselage upper longitudinal beam (11) and rear fuselage frame (13) are made of, and it is connected by bolt with rear fuselage frame (13);Flat tail structure (2) includes flat tail front beam (21), flat tail rear beam (22), flat tail box section rib (23) and flat tail skin (24), multiple flat tail box section ribs (23) are evenly fixed between flat tail front beam (21) and flat tail rear beam (22), and each flat tail box section rib (23) is fixedly connected with flat tail skin (24);Rear fuselage upper longitudinal beam (11) is fixed by adhesive bonding with flat tail front beam (21), and rear fuselage upper longitudinal beam (11) is fixed by metal joint (112) riveting with flat tail front beam (21), and rear fuselage skin (14) is overlapped and fixed above the flat tail box section rib (23) in the middle of flat tail structure (2) with flat tail skin (24).

2. A fuselage and tailplane integrated structure for an eVTOL aircraft as claimed in claim 1, wherein, Rear fuselage frame (13) outer edge is provided with recess capable of accommodating rear fuselage upper longitudinal beam (11), and rear fuselage upper longitudinal beam (11) is respectively installed in the recess of rear fuselage frame (13) outer edge and is fixed by bolt.

3. A fuselage and tailplane integrated structure for an eVTOL aircraft as claimed in claim 1, wherein, Rear fuselage upper longitudinal beam (11) and flat tail front beam (21) are all designed as "C" section beam, and the section beam of rear fuselage upper longitudinal beam (11) and flat tail front beam (21) is fixed by adhesive bonding.

4. A fuselage and tailplane integrated structure for an eVTOL aircraft as claimed in claim 1, wherein, Rear fuselage lower longitudinal beam (12) is designed as "Ω" section beam.

5. A fuselage and tailplane integrated structure for an eVTOL aircraft as claimed in claim 1, wherein, Rear fuselage structure (1) and flat tail structure (2) are vertically arranged, flat tail structure (2) is located at the rear side of rear fuselage structure (1), and rear fuselage structure (1) and flat tail structure (2) are fixedly connected in the middle section, so that flat tail structure (2) is divided into left flat tail (251), right flat tail (252) and middle fuselage connecting section (253).

6. A fuselage and tailplane integrated structure for an eVTOL aircraft as claimed in claim 5, wherein, Flat tail front beam (21) and flat tail rear beam (22) are arranged in parallel, and are fixedly connected by multiple flat tail box section ribs (23) between flat tail front beam (21) and flat tail rear beam (22), and flat tail box section ribs (23) are evenly distributed between flat tail front beam (21) and flat tail rear beam (22) and are fixedly connected with flat tail front beam (21) and flat tail rear beam (22) respectively.

7. A fuselage and tailplane integrated structure for an eVTOL aircraft as claimed in claim 5, wherein, The size of middle fuselage connecting section (253) of flat tail front beam (21) and flat tail rear beam (22) is greater than that of left flat tail (251) and right flat tail (252).

8. A fuselage and tailplane integrated structure for an eVTOL aircraft as claimed in claim 7, wherein, Flat tail box section rib (23) includes ten, wherein four are arranged in left flat tail (251) and right flat tail (252) respectively, and the other two flat tail box section ribs (23) are arranged in middle fuselage connecting section (253) of flat tail front beam (21) and flat tail rear beam (22).

9. A fuselage and tailplane integrated structure for an eVTOL aircraft as claimed in claim 8, wherein, Flat tail box section rib (23) is hollow support frame structure.

10. A fuselage and tailplane integrated structure for an eVTOL aircraft as claimed in claim 1, wherein, Vertical tail structure (3) is arranged behind flat tail structure (2), and vertical tail skin of vertical tail structure (3) is connected with flat tail skin (24) and rear fuselage skin (14) to form an integral structure.

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