Connecting structure of empennage and fuselage and airplane
By designing a tail-wing connection structure containing multiple sets of tail-wing connection ribs, fuselage connection ribs, fuselage connection angle box and reinforcement with plates, the problems of unreasonable load transfer, stress concentration and insufficient stiffness in the prior art are solved, and higher shear and torsion resistance are achieved, and the service life of the structure is extended.
Patent Information
- Application Number
- CN202510184458.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-19
- Publication Date
- 2025-05-23
AI Technical Summary
The existing connecting structure of the tail wing and fuselage have problems with unreasonable load transmission path, stress concentration and low stiffness, which affects the service life of the structure.
A connection structure between the tail wing and the fuselage is adopted, including the first tail wing connecting rib, the second tail wing connecting rib, the fuselage connecting rib, the fuselage connecting angle box and the reinforcement belt plate. The design of these components forms a reasonable load transfer path to improve the shear resistance and torsional stiffness of the structure.
This connection structure effectively reduces stress concentration at the connection, improves the shear and torsional stiffness of the structure, extends the service life, and is simple in design and easy to install.
Smart Images
Figure CN120024490A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the field of aircraft body structures, and in particular to a connection structure between a tail wing and a fuselage and an aircraft. Background Art
[0002] The connection between the tail and the fuselage is an important part of the aircraft structural design, among which the tail includes conventional tail, H-shaped tail, T-shaped tail and V-tail. When the horizontal tail is connected to the fuselage, the commonly used connection forms are "integral bulkhead type", that is, the rear beam of the horizontal tail box is connected to the fuselage bulkhead through an ear connection structure; or "multi-link type", that is, the horizontal tail box beam is connected to the fuselage through multiple connecting rods, and the heading, lateral and vertical loads are transmitted to the fuselage through the connecting rods respectively. When the vertical tail is connected to the fuselage, connecting corner boxes and shear plates are usually used to connect the vertical tail to the fuselage frame and fuselage skin to achieve effective transmission of bending, shear and torsion loads. For the tail connection structure, structural weight, load transfer efficiency, assembly and maintenance convenience are the design focuses.
[0003] 201810966876X, a tail connection mechanism. This patent proposes a tail connection mechanism, which connects the fuselage and the tail assembly through a tail connecting rod, wherein the tail assembly and the tail connecting rod are detachably fixedly connected, and the tail assembly and the tail crossbar are fixedly connected by ear bolts. The overall tail structure is easy to disassemble and assemble, has good portability, and is easy to maintain, reducing the difficulty of tail maintenance.
[0004] 202111431696.X, balancing horizontal tail connection structure. This patent proposes a tail connection mechanism, which connects the fuselage and the tail assembly through a tail connecting rod, wherein the tail assembly and the tail connecting rod are detachably fixedly connected, and the tail assembly and the tail crossbar are fixedly connected with ear bolts. The overall tail structure is easy to disassemble and assemble, has good portability, and is easy to maintain, reducing the difficulty of tail maintenance.
[0005] Document: T-tail joint assemblies for aircraft. The document relates to a T-tail joint assembly for an aircraft, which is used to connect a left horizontal tail and a right horizontal tail to a vertical tail, wherein the connection with the horizontal tail is in the form of a corner box and a lap strap, and the connection with the vertical tail is mainly in the form of a connecting ear.
[0006] The above connection structures all have the following defects: the load transfer path is not entirely reasonable, there is a stress concentration problem, the rigidity is small, and the service life of the structure is affected. Summary of the invention
[0007] The purpose of the present invention is to overcome the shortcomings of the prior art and provide a connection structure between a tail and a fuselage and an aircraft, which is particularly suitable for connecting the vertical tail or horizontal tail and the fuselage of a new energy aircraft with a smaller take-off weight. The connection structure has a simple design, light weight, and a reasonable structural load transfer path.
[0008] The present invention adopts the following technical solution:
[0009] On the one hand, the present invention provides a connection structure between an empennage and a fuselage, which is used to connect a fuselage tail frame and an empennage box section, and the connection structure comprises: a first empennage connection rib, a second empennage connection rib, a fuselage connection rib, a fuselage connection corner box and a reinforcement strip;
[0010] The number of the first tail connecting ribs and the second tail connecting ribs is 2 or more, and each group of the first tail connecting ribs and the second tail connecting ribs encloses a closed curve for accommodating the tail box section;
[0011] The fuselage connecting rib is used to respectively and fixedly connect the first tail connecting rib and the second tail connecting rib, and one end of the fuselage connecting rib is fixedly connected to the fuselage connecting corner box;
[0012] The reinforcing strip is arranged on the upper and lower parts of the plurality of groups of the first tail connecting ribs and the second tail connecting ribs, and is fixedly connected to the fuselage connecting ribs; the reinforcing strip is fixedly connected to the fuselage connecting corner box at the end;
[0013] The fuselage connection corner box is fixedly connected to the fuselage tail frame, and transmits the load transmitted by the fuselage connection rib and the reinforcement strip to the fuselage tail frame.
[0014] According to any possible implementation described above, there is further provided an implementation, wherein the first tail wing connecting rib is an open structure, comprising a first inner edge strip, a first outer edge strip, a first end edge strip and a first web;
[0015] The first inner edge strip and the outer surface of the skin at the front of the tail box section are mating surfaces, and are fixedly connected by mechanical connection or adhesive connection, or the first inner edge strip and the tail box section are not fixedly connected; the first outer edge strip and the first inner edge strip are connected as a whole by the first web; the first end edge strip is used to achieve a fixed connection with the second tail connecting rib.
[0016] According to any possible implementation described above, there is further provided an implementation, wherein the second tail wing connecting rib is an open structure, including a second inner edge strip, a second outer edge strip, a second end edge strip and a second web;
[0017] The second inner edge strip is a mating surface with the outer surface of the skin at the rear of the tail box section and the outer surface of the tail rear beam, and is fixedly connected by mechanical connection or bonding, or the second inner edge strip and the tail box section are not fixedly connected; the second outer edge strip and the second inner edge strip are connected as a whole by the second web; the second end edge strip is used to achieve a fixed connection with the first tail connecting rib.
[0018] As any possible implementation manner as described above, there is further provided an implementation manner, wherein the first tail wing connecting rib and the second tail wing connecting rib are integrally formed.
[0019] According to any possible implementation described above, there is further provided an implementation, wherein the fuselage connecting rib is an open structure, including a third inner edge strip, a third outer edge strip, a third end edge strip, a third web and a reinforcing rib;
[0020] The third inner edge strip and the outer surface of the skin of the tail box section are mating surfaces, and are fixedly connected by mechanical connection or adhesive connection, or the third inner edge strip and the tail box section are not fixedly connected; the third outer edge strip is matingly connected to the fuselage connection corner box and the reinforcing strip plate; the third end edge strip is matingly connected to the fuselage tail frame and the fuselage connection corner box; the reinforcing rib is arranged on the third end edge strip to enhance the rigidity of the third end edge strip;
[0021] The third web fixedly connects the third inner edge strip and the third outer edge strip into a whole; and the third web is a matching surface with the first web and the second web, so as to realize a fixed connection between the fuselage connecting rib and the first tail connecting rib and the second tail connecting rib.
[0022] According to any possible implementation described above, there is further provided an implementation, wherein the fuselage connection corner box comprises a fourth inner edge strip, a fourth outer edge strip, vertical ribs and a fourth web;
[0023] The end of the fourth inner edge strip is fixedly connected to the reinforcing rib of the fuselage connecting rib, and the vertical rib is an integral structure with the fourth inner edge strip, the fourth outer edge strip, and the fourth web; the fourth web and the third end edge strip of the fuselage tail frame and the fuselage connecting rib are mating surfaces, and a mechanical connection method is used to achieve fixed connection.
[0024] According to any possible implementation described above, there is further provided an implementation, wherein the reinforcing strip includes a rib connection area, a frame connection area and a fifth web;
[0025] The rib connection area and the third outer edge strip of the fuselage connection rib are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding; the frame connection area and the fourth outer edge strip of the fuselage connection corner box are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding; the fifth web, rib connection area, and frame connection area are an integrated structure.
[0026] As any possible implementation described above, an implementation is further provided, wherein the reinforcing strip plate as a whole is a flat plate structure, or a curved plate structure, or a plate reinforced structure; if it is a plate reinforced structure, the ribs are arranged on the fifth web.
[0027] As for any possible implementation method as described above, an implementation method is further provided, wherein the cross-sections of the first tail wing connecting rib and the second tail wing connecting rib are C-shaped, L-shaped or T-shaped; the cross-section of the fuselage connecting rib is C-shaped, or an L-shaped or T-shaped structure that does not include an inner edge strip; the cross-section of the fuselage connection corner box is C-shaped, or an L-shaped structure that does not include an inner edge strip.
[0028] On the other hand, the present invention further provides an aircraft having the above-mentioned connection structure between the tail wing and the fuselage.
[0029] The beneficial effects of the present invention are:
[0030] 1. The connection structure is connected to the tail skin, and the stress concentration at the connection is reduced based on the tail skin's distributed load transfer method.
[0031] 2. The connection structure is a box-type structure with large heading torsional stiffness.
[0032] 3. The fuselage connecting rib edge strips, fuselage connecting corner boxes and connecting strip plates form a shear-resistant structure with large shear stiffness.
[0033] 4. Simple structure, easy installation, suitable for popularization and application. BRIEF DESCRIPTION OF THE DRAWINGS
[0034] Figure 1 Shown is a schematic diagram of the connection structure between the tail wing and the fuselage, and the installation structure of the tail wing and the fuselage tail frame according to an embodiment of the present invention.
[0035] Figure 2 Shown is a schematic diagram of the overall structure of the connection structure between the tail wing and the fuselage in the embodiment.
[0036] Figure 3 Shown is a schematic structural diagram of the first tail wing connecting rib in the embodiment.
[0037] Figure 4 Shown is a schematic structural diagram of the second tail wing connecting rib in the embodiment.
[0038] Figure 5 Shown is a schematic structural diagram of the fuselage connecting ribs in the embodiment.
[0039] Figure 6 Shown is a schematic structural diagram of a fuselage connection corner box in an embodiment.
[0040] Figure 7Shown is a schematic structural diagram of the reinforcing strip plate in the embodiment.
[0041] Figure 8 Shown is a schematic diagram of a second tail wing connecting rib with an L-shaped cross-section in a certain embodiment.
[0042] Fig. 9 Shown is a schematic diagram of an integrated tail wing connecting rib in a certain embodiment.
[0043] Fig.10 Shown is a schematic diagram of a special-section fuselage connecting rib in a certain embodiment.
[0044] Fig.11 Shown is a schematic diagram of an L-shaped cross-section fuselage connection corner box in a certain embodiment.
[0045] Fig.12 Shown is the stress simulation result of the connection structure under the lift of the tail wing in the embodiment.
[0046] Fig.13 Shown are the stress simulation results of the connection structure under the lateral load and torque Mx in the embodiment.
[0047] In the figure: 1-fuselage tail frame; 2-tail box section; 3-connecting structure between tail and fuselage; 31-first tail connecting rib; 32-second tail connecting rib; 33-fuselage connecting rib; 34-fuselage connecting corner box; 35-reinforcement strip; 311-first inner edge strip; 312-first outer edge strip; 313-first end edge strip; 314-first web; 321-second inner edge strip; 322-second outer edge strip; 323-second end edge strip; 324-second web; 331-third inner edge strip; 332-third outer edge strip; 333-third end edge strip; 334-third web; 335-reinforcement rib; 341-fourth inner edge strip; 342-fourth outer edge strip; 343-vertical rib; 344-fourth web; 351-rib connection area; 352-frame connection area; 353-fifth web. DETAILED DESCRIPTION
[0048] The specific embodiments of the present invention will be described in detail below in conjunction with specific drawings. It should be noted that the technical features or combinations of technical features described in the following embodiments should not be considered isolated, and they can be combined with each other to achieve better technical effects.
[0049] like Figure 1 , Figure 2 As shown, a connection structure 3 between a tail and a fuselage according to an embodiment of the present invention is used to connect a fuselage tail frame 1 and a tail box section 2, and the connection structure 3 includes: a first tail connection rib 31, a second tail connection rib 32, a fuselage connection rib 33, a fuselage connection corner box 34 and a reinforcement strip 35;
[0050] The number of the first tail connecting ribs 31 and the second tail connecting ribs 32 is 2 or more, and each group of the first tail connecting ribs 31 and the second tail connecting ribs 32 encloses a closed curve for accommodating the tail box section 2;
[0051] The fuselage connecting rib 33 is used to respectively and fixedly connect the first tail connecting rib 31 and the second tail connecting rib 32, and one end of the fuselage connecting rib 33 is fixedly connected to the fuselage connecting corner box 34;
[0052] The reinforcing strips 35 are arranged on the upper and lower parts of the plurality of groups of the first tail connecting ribs 31 and the second tail connecting ribs 32, and are fixedly connected to the fuselage connecting ribs 33; the reinforcing strips 35 are fixedly connected to the fuselage connecting corner boxes 34 at their ends;
[0053] The fuselage connection corner box 34 is fixedly connected to the fuselage tail frame 1 , and transfers the load transferred from the fuselage connection rib 33 and the reinforcement strip 35 to the fuselage tail frame 1 .
[0054] In a specific embodiment, Figure 3 As shown, the first tail wing connecting rib 31 is an open structure, including a first inner edge strip 311, a first outer edge strip 312, a first end edge strip 313 and a first web 314;
[0055] The first inner edge strip 311 and the outer surface of the skin at the front of the tail box section 2 are mating surfaces, and are fixedly connected by mechanical connection or gluing, or the first inner edge strip 311 and the tail box section 2 are not fixedly connected; the first outer edge strip 312 and the first inner edge strip 311 are connected as a whole through the first web 314; the first end edge strip 313 is used to achieve a fixed connection with the second tail connecting rib 32.
[0056] In a specific embodiment, Figure 4 As shown, the second tail connecting rib 32 is an open structure, including a second inner edge strip 321, a second outer edge strip 322, a second end edge strip 323 and a second web 324;
[0057] The second inner edge strip 321 is mating with the outer surface of the skin at the rear of the tail box section 2 and the outer surface of the tail rear beam, and is fixedly connected by mechanical connection or gluing, or the second inner edge strip 321 and the tail box section 2 are not fixedly connected; the second outer edge strip 322 and the second inner edge strip 321 are connected as a whole through the second web 324; the second end edge strip 323 is used to achieve a fixed connection with the first tail connecting rib 31.
[0058] In a specific embodiment, the first tail connecting rib 31 and the second tail connecting rib 32 are integrally formed, have better overall rigidity, and are positioned and matched with the skin during the assembly stage of the tail box section 2. Fig. 9 shown.
[0059] In a specific embodiment, Figure 5 As shown, the fuselage connecting rib 33 is an open structure, including a third inner edge strip 331, a third outer edge strip 332, a third end edge strip 333, a third web 334 and a reinforcing rib 335;
[0060] The third inner edge strip 331 and the outer surface of the skin of the tail box section 2 are mating surfaces, and are fixedly connected by mechanical connection or adhesive connection, or the third inner edge strip 331 and the tail box section 2 are not fixedly connected; the third outer edge strip 332 is matched and connected with the fuselage connection corner box 34 and the reinforcing strip plate 35; the third end edge strip 333 is matched and connected with the fuselage tail frame 1 and the fuselage connection corner box 34; the reinforcing rib 335 is arranged on the third end edge strip 333, so as to enhance the rigidity of the third end edge strip 333;
[0061] The third web 334 fixedly connects the third inner edge strip 331 and the third outer edge strip 332 as a whole; and the third web 334 and the first web 314 and the second web 324 are mating surfaces, thereby realizing a fixed connection between the fuselage connecting rib 33 and the first tail connecting rib 31 and the second tail connecting rib 32.
[0062] In a specific embodiment, Figure 6 As shown, the fuselage connection corner box 34 includes a fourth inner edge strip 341, a fourth outer edge strip 342, a vertical rib 343 and a fourth web 344;
[0063] The end of the fourth inner edge strip 341 is fixedly connected to the reinforcing rib 335 of the fuselage connecting rib 33, and the vertical rib 343, the fourth inner edge strip 341, the fourth outer edge strip 342, and the fourth web 344 are an integral structure; the fourth web 344, the fuselage tail frame 1 and the third end edge strip 333 of the fuselage connecting rib 33 are mating surfaces, and a mechanical connection method is used to achieve fixed connection.
[0064] In a specific embodiment, Figure 7 As shown, the reinforcing strip 35 includes a rib connection area 351, a frame connection area 352 and a fifth web 353;
[0065] The rib connection area 351 and the third outer edge strip 332 of the fuselage connection rib 33 are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding; the frame connection area 352 and the fourth outer edge strip 342 of the fuselage connection corner box 34 are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding; the fifth web 353, the rib connection area 351, and the frame connection area 352 are an integrated structure.
[0066] In a specific embodiment, the reinforcing strip plate 35 is a flat plate structure, or a curved plate structure, or a plate reinforced structure. If it is a plate reinforced structure, the ribs are arranged on the fifth web 353 .
[0067] In a specific embodiment, the cross-sections of the first tail connecting rib 31 and the second tail connecting rib 32 are C-shaped, L-shaped or T-shaped; Figure 8 A second tail connecting rib 32 having an L-shaped cross section is shown.
[0068] In a specific embodiment, the cross-section of the fuselage connecting rib 33 is a C-shaped, or L-shaped or T-shaped structure without an inner edge strip; Fig.10 A fuselage connecting rib 33 with a special-shaped cross-section is shown.
[0069] In a specific embodiment, the cross-section of the fuselage connection corner box 34 is C-shaped, or L-shaped without an inner edge strip. Fig.11 A medium L-section fuselage connection corner box 34 is shown.
[0070] In a specific embodiment, the relationship between the mating surfaces of the components is described in detail as follows:
[0071] The first inner edge strip 311 of the first tail connecting rib 31 and the outer surface of the front skin of the tail box section are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding; the first end edge strip 313 and the second end edge strip 323 of the second tail connecting rib 32 are mating surfaces, and are fixedly connected by mechanical connection; the first web 314 and the third web 334 of the fuselage connecting rib 33 are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding.
[0072] The second inner edge strip 321 of the second tail connecting rib 32 is a mating surface with the outer surface of the rear skin of the tail box section and the rear beam of the tail, and is fixedly connected by mechanical connection or adhesive bonding; the second end edge strip 323 is a mating surface with the first end edge strip 313 of the first tail connecting rib 31, and is fixedly connected by mechanical connection; the second web 324 is a mating surface with the third web 334 of the fuselage connecting rib 33, and is fixedly connected by mechanical connection or adhesive bonding.
[0073] The third inner edge strip 331 of the fuselage connecting rib 33 and the outer surface of the skin of the tail box section 1 are mating surfaces, and can be fixedly connected by mechanical connection or adhesive bonding, or can be left unconnected; the third outer edge strip 332 and the end of the fourth outer edge strip 342 of the fuselage connecting corner box 34, and the rib connection area 351 of the reinforcing strip plate 35 are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding; the third end edge strip 333 and the fuselage tail frame 1 and the end of the fourth web 344 of the fuselage connecting corner box 34 are mating surfaces, and are fixedly connected by mechanical connection; the third web 334 and the webs 314 and 324 of the first and second tail connecting ribs 31 and 32 are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding; the reinforcing rib 335 and the end of the fourth inner edge strip 341 of the fuselage connecting corner box 34 are fixedly connected by mechanical connection.
[0074] The end of the fourth inner edge strip 341 of the fuselage connecting corner box 34 is fixedly connected to the reinforcing rib 335 of the fuselage connecting rib 33 by mechanical connection, the end of the fourth outer edge strip 342 is fixedly connected to the third outer edge strip 332 of the fuselage connecting rib 33 by mechanical connection, the vertical rib 343, the fourth inner edge strip 341, the fourth outer edge strip 342 and the fourth web 344 are an integral structure; the fourth web 344, the fuselage frame 1 and the third end edge strip 333 of the fuselage connecting rib 33 are mating surfaces, and are fixedly connected by mechanical connection.
[0075] The rib connection area 351 of the reinforcing strip 35 and the third outer edge strip 332 of the fuselage connection rib 33 are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding; the frame connection area 352 and the fourth outer edge strip 342 of the fuselage connection corner box 34 are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding.
[0076] The load transfer and working principle are explained as follows:
[0077] The tail box section 2 is subjected to various loads during operation, such as Figure 1 The coordinate system shown includes the drag from the X direction, the wing lift in the Y direction, the lateral force in the Z direction, the torques Mx and My caused by the lateral force, and the torque Mz caused by the wing lift.
[0078] The resistance is mainly transmitted by the skin of the tail box section 2 to the heading shear force to the first inner edge strip 311 of the first tail connecting rib 31 and the second inner edge strip 321 of the second tail connecting rib 32, and then transmitted to the third web 334 of the fuselage connecting rib 33 through the first web 314 and the second web 324 of the connecting rib. The fuselage connecting rib 33 directly transmits part of the resistance to the fuselage tail frame 1, and the other part of the resistance is transmitted to the fuselage tail frame 1 through the reinforcing strip plate 35 and the fuselage connecting corner box 34.
[0079] The wing surface lift is mainly transmitted by the skin of the tail box section 2 to the Y-direction load to the first and second inner edge strips 311, 321 of the first and second tail connecting ribs 31 and 32, and then the Y-direction shear force is transmitted to the fuselage connecting rib 33 through its first and second webs 314, 324. The fuselage connecting rib 33 directly transmits most of the load to the fuselage tail frame 1 in the form of Y-direction shear force, and partially transmits part of the load to the fuselage tail frame 1 indirectly in the form of Y-direction shear force through the fuselage connecting corner box 34.
[0080] The lateral force is transmitted from the skin of the tail box section 2 to the first and second tail connection ribs 31 and 32, and then the out-of-plane load is transmitted to the fuselage connection rib 33 through its web connection structure. The fuselage connection rib 33 directly transmits most of the lateral shear force to the fuselage tail frame 1, and part of the load is indirectly transmitted to the fuselage tail frame 1 in the form of lateral shear force through the reinforcing strip plate 35 and the fuselage connection corner box 34. The fuselage connection rib 33, the fuselage connection corner box 34 and the reinforcing strip plate 35 form a lateral shear-resistant structure with large shear stiffness.
[0081] Under the action of the torque Mx, the skin on one side of the tail box section 2 mainly transmits the shear force along the positive direction of the z-axis, and the skin on the other side mainly transmits the shear force along the negative direction of the z-axis. The connection structure is composed of the first and second tail connection ribs 31 and 32, the fuselage connection rib 33, the fuselage connection corner box 34 and the reinforcing strip 35 to form a torsion box type structure, which has strong torsional stiffness around the x-axis. The shear load around the x-axis generated by the torque Mx is effectively transmitted to the fuselage tail frame 1 through the third end edge strip 333 of the fuselage connection rib 33 and the fourth web 344 of the fuselage connection corner box 34.
[0082] Under the action of the torque My, the skin of the tail box section 2 mainly transmits the shear load along the x-direction, and then transmits the x-direction load to the fuselage tail frame 1 through the third end edge strip 333 of the fuselage connecting rib 33.
[0083] Under the action of torque Mz, the skin of the tail box section 2 transmits the shear load along the x-direction, wherein if the shear force of the skin on one side is mainly along the positive direction of the x-axis, the shear force of the skin on the other side is mainly along the negative direction of the x-axis. The x-direction load is then transmitted to the fuselage tail frame 1 through the third end edge strip 333 of the fuselage connection rib 33 and the fourth web 344 of the fuselage connection corner box 34.
[0084] Effect analysis and verification:
[0085] The strength analysis of the connection structure of the present invention is performed based on the design load of the tail structure by using the finite element analysis method. The tail lift load ( Fig.12 ), and under the action of lateral load and torque Mx ( Fig.13 )’s connection structure stress (unit: MPa). The results show that the connection structure stress is small and there is no obvious stress concentration phenomenon.
[0086] The connection structure of the present invention is connected to the fuselage tail frame and the tail wing side skin in a dispersed manner. The connection (mechanical connection) with the fuselage tail frame is achieved through the end edge strips of the fuselage connection ribs and the connection corner box to realize multiple bolt-like fasteners. The connection (mechanical connection) with the tail wing skin is achieved through adhesive bonding and multiple bolt-like fasteners. There is no centralized load transfer method in the form of traditional joint ear connection, which reduces the stress concentration phenomenon. In addition, the ear connection structure usually has weak shear stiffness and torsional stiffness. The connection structure of the present invention forms a box-type structure, and the fuselage tail frame constitutes the bottom of the box, which greatly improves the overall shear stiffness and torsional stiffness.
[0087] The present invention can be used to connect the vertical tail or horizontal tail of a new energy aircraft with a smaller take-off weight to the fuselage, and has the advantages of simple connection structure design, light weight, reasonable structural load transfer path, and convenient assembly of the tail and fuselage.
[0088] Although several embodiments of the present invention have been given herein, those skilled in the art should understand that the embodiments of the present invention may be modified without departing from the spirit of the present invention. The above embodiments are merely exemplary and should not be used as a limitation on the scope of the present invention.
Claims
1. A connection structure between a tail and a fuselage, characterized in that: The connection structure is used to connect the fuselage tail frame and the tail box section, and the connection structure includes: a first tail connecting rib, a second tail connecting rib, a fuselage connecting rib, a fuselage connecting corner box and a reinforcing strip plate; The number of the first tail connecting ribs and the second tail connecting ribs is 2 or more, and each group of the first tail connecting ribs and the second tail connecting ribs encloses a closed curve for accommodating the tail box section; The fuselage connecting rib is used to respectively and fixedly connect the first tail connecting rib and the second tail connecting rib, and one end of the fuselage connecting rib is fixedly connected to the fuselage connecting corner box; The reinforcing strips are arranged on the upper and lower parts of the plurality of groups of the first tail connecting ribs and the second tail connecting ribs, and are fixedly connected to the fuselage connecting ribs; The fuselage connection corner box is fixedly connected to the fuselage tail frame, and transmits the load transmitted by the fuselage connection rib and the reinforcement strip to the fuselage tail frame.
2. The connection structure between the tail and the fuselage according to claim 1, characterized in that: The first tail wing connecting rib is an open structure, comprising a first inner edge strip, a first outer edge strip, a first end edge strip and a first web; The first inner edge strip and the outer surface of the skin at the front of the tail box section are mating surfaces, and are fixedly connected by mechanical connection or adhesive connection, or the first inner edge strip and the tail box section are not fixedly connected; the first outer edge strip and the first inner edge strip are connected as a whole by the first web; the first end edge strip is used to achieve a fixed connection with the second tail connecting rib.
3. The connection structure between the tail and the fuselage according to claim 1, characterized in that: The second tail wing connecting rib is an open structure, including a second inner edge strip, a second outer edge strip, a second end edge strip, and a second web; The second inner edge strip is a mating surface with the outer surface of the skin at the rear of the tail box section and the outer surface of the tail rear beam, and is fixedly connected by mechanical connection or bonding, or the second inner edge strip and the tail box section are not fixedly connected; the second outer edge strip and the second inner edge strip are connected as a whole by the second web; the second end edge strip is used to achieve a fixed connection with the first tail connecting rib.
4. The connection structure between the tail and the fuselage according to claim 1, characterized in that: The first tail wing connecting rib and the second tail wing connecting rib are integrally formed.
5. The connection structure between the tail and the fuselage according to claim 2 or 3, characterized in that: The fuselage connecting rib is an open structure, including a third inner edge strip, a third outer edge strip, a third end edge strip, a third web and a reinforcing rib; The third inner edge strip and the outer surface of the skin of the tail box section are mating surfaces, and are fixedly connected by mechanical connection or adhesive connection, or the third inner edge strip and the tail box section are not fixedly connected; the third outer edge strip is matingly connected with the fuselage connection corner box and the reinforcing strip plate; the third end edge strip is matingly connected with the fuselage tail frame and the fuselage connection corner box; the reinforcing rib is arranged on the third end edge strip to enhance the rigidity of the third end edge strip; The third web fixedly connects the third inner edge strip and the third outer edge strip into a whole; and the third web is a matching surface with the first web and the second web, so as to realize a fixed connection between the fuselage connecting rib and the first tail connecting rib and the second tail connecting rib.
6. The connection structure between the tail and the fuselage according to claim 5, characterized in that: The fuselage connection corner box comprises a fourth inner edge bar, a fourth outer edge bar, vertical ribs and a fourth web; The end of the fourth inner edge strip is fixedly connected to the reinforcing rib of the fuselage connecting rib, and the vertical rib is an integral structure with the fourth inner edge strip, the fourth outer edge strip, and the fourth web; the fourth web and the third end edge strip of the fuselage tail frame and the fuselage connecting rib are mating surfaces, and a mechanical connection method is used to achieve fixed connection.
7. The connection structure between the tail and the fuselage according to claim 5, characterized in that: The reinforcing strip plate comprises a rib connection area, a frame connection area and a fifth web; The rib connection area and the third outer edge strip of the fuselage connection rib are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding; the frame connection area and the fourth outer edge strip of the fuselage connection corner box are mating surfaces, and are fixedly connected by mechanical connection or adhesive bonding; the fifth web, rib connection area, and frame connection area are an integrated structure.
8. The connection structure between the tail and the fuselage according to claim 7, characterized in that: The reinforcing strip plate is a flat plate structure as a whole, or a curved plate structure, or a plate reinforced structure; if it is a plate reinforced structure, the ribs are arranged on the fifth web.
9. The connection structure between the tail and the fuselage according to claim 1, characterized in that: The cross-sections of the first tail connecting rib and the second tail connecting rib are C-shaped, L-shaped or T-shaped; the cross-section of the fuselage connecting rib is C-shaped, or an L-shaped or T-shaped structure without an inner edge strip; the cross-section of the fuselage connecting corner box is C-shaped, or an L-shaped structure without an inner edge strip.
10. An aircraft, characterized in that: The aircraft has a connection structure between the tail and the fuselage as described in any one of claims 1 to 9.