Detachable T-shaped empennage central connecting structure of airplane

Abstract

The invention discloses a detachable T-shaped empennage center connecting structure of an airplane, and belongs to the technical field of airplane empennage structure design, the detachable T-shaped empennage center connecting structure of the airplane comprises a vertical fin structure, a vertical fin structure and a T-shaped fin structure, the vertical fin structure comprises a vertical fin main box section wall plate, a vertical fin front beam, a vertical fin rear beam, a box section wing rib and a vertical tail end rib structure; wherein the end rib lower side web plate surface of the vertical tail end rib structure is respectively connected with the vertical tail front beam and the vertical tail rear beam through the connecting angle section; an end rib edge strip of the vertical tail end rib structure is connected with a vertical tail main box section wall plate; the horizontal tail structure comprises a left horizontal stabilizer, a right horizontal stabilizer, a central butt joint rib structure, a front beam connecting band plate, a rear beam connecting band plate, a horizontal tail front connector and a horizontal tail rear connector. Wherein the left horizontal stabilizer and the right horizontal stabilizer are fixedly connected to the two sides of the central butt-joint rib structure, the front beam connecting band plate is fixedly connected to the front end face of the central butt-joint rib structure, and the rear beam connecting band plate is fixedly connected to the rear end face of the central butt-joint rib structure; wherein the horizontal tail structure is fixed to the top end of the vertical tail structure, and the horizontal tail structure is fixedly connected to the vertical tail end rib structure through the horizontal tail front connector and the horizontal tail rear connector. According to the invention, the structure efficiency is improved and the structure weight is reduced while the requirement of quick disassembly and assembly of the horizontal tail is met.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft tail structure design, and particularly to a detachable T-shaped tail central connection structure for aircraft. Background Art

[0002] In the field of transport aircraft design, for aircraft with T-shaped tails, the horizontal tail is installed at the upper end of the vertical tail, and the two parts of the horizontal tail and the vertical tail need to be connected to transfer loads. The connection form between the high horizontal tail and the single vertical tail generally adopts the method of mating fixed brackets, that is: the flat tail bracket, namely the assembly interface, is fixed on the main load-bearing beam of the main box section of the high horizontal tail component, and the vertical tail bracket, namely the assembly interface, is fixed on the top of the vertical tail box section. During assembly, the assembly interfaces of the two are mated, then fixing bolts are installed in the bracket mating area, and then a fairing is installed between the vertical tail and the horizontal tail to envelope the connection part to meet the aerodynamic requirements.

[0003] Problems existing in the prior art are as follows: For general fixed high horizontal tail aircraft, its central connection structure is mostly of a fixed connection form. For aircraft with large loads, usually in the central docking area of the horizontal tail, a central box section structure is formed. The front beam, rear beam, and intermediate short beam of the horizontal tail central box section are respectively connected to the front beam, rear beam, and web of the vertical tail box section by a group of nails in a fixed connection to form an intersecting mating structural form. This connection method has many problems. First, there are many and complex assembly interfaces, resulting in difficult assembly positioning, and complex assembly tools and time-consuming are required. Second, the assembly space is limited, and it is difficult to achieve assembly with conventional tools. Third, the connection structure is complex, with many connecting parts and fasteners, increasing the weight while reducing the structural reliability. Fourth, it is necessary to simultaneously achieve the matching of the positions of the front beam and rear beam structures of the horizontal tail main box section and the corresponding beam structures of the vertical tail box section, resulting in limited design space and it is difficult to ensure a better design result. Fifth, adopting a fixed connection form, because it is not detachable, it will bring great difficulties and costs to transportation and maintenance. For aircraft with small loads, the front and rear wing beams of the horizontal stabilizer are used as the horizontal tail connection structure, and the front and rear wing beams of the vertical tail are used as the vertical tail connection structure. Then, a pair of horizontal and vertical tail connection joints are used to connect the front and rear wing beams of the horizontal tail and the vertical tail with fasteners respectively. This connection form has direct load transfer, and the number of fasteners and connecting parts is small, reducing the structural weight. However, this connection form uses a group of nails for connection, which is not conducive to disassembly, transportation, and maintenance; and the double-wing beam configuration of the horizontal tail and the integral vertical tail beam rib configuration both make the applicable range of this central connection structure solution extremely limited and can only be used for small aircraft.

[0004] Therefore, there is an urgent need to provide a new connection method. Summary of the Invention

[0005] For this reason, the objective of the present invention is to provide a new detachable T-shaped tail central connection structure for an aircraft. By designing the vertical fin end rib and the horizontal stabilizer central docking structure form, as well as the connection method between the horizontal stabilizer and the vertical fin, the transmission path of the horizontal stabilizer load to the vertical fin is optimized. While solving the need for quick disassembly and assembly of the horizontal stabilizer, it is not restricted by the relative spatial position arrangement between the horizontal stabilizer and the vertical fin. At the same time, the structural efficiency is improved and the structural weight is reduced.

[0006] According to the technical solution of the present invention, a detachable T-shaped tail central connection structure for an aircraft is provided. Among them, the detachable T-shaped tail central connection structure for an aircraft is used to connect the horizontal stabilizer structure and the vertical fin structure of the T-shaped tail, and includes:

[0007] The vertical fin structure includes a vertical fin main box section wall panel, a vertical fin front beam, a vertical fin rear beam, box section wing ribs and a vertical fin end rib structure; among them, the lower ventral surface of the end rib of the vertical fin end rib structure is respectively connected to the vertical fin front beam and the vertical fin rear beam through connecting angle sections; the end rib flange of the vertical fin end rib structure is connected to the vertical fin main box section wall panel;

[0008] The horizontal stabilizer structure includes left and right horizontal stabilizers, a central docking rib structure, a front beam connecting strip plate, a rear beam connecting strip plate, a horizontal stabilizer front joint and a horizontal stabilizer rear joint; among them, the left and right horizontal stabilizers are fixedly connected to both sides of the central docking rib structure, the front beam connecting strip plate is fixedly connected to the front end face of the central docking rib structure, and the rear beam connecting strip plate is fixedly connected to the rear end face of the central docking rib structure;

[0009] Among them, the horizontal stabilizer structure is fixed to the top of the vertical fin structure, and the horizontal stabilizer structure is fixedly connected to the vertical fin end rib structure through the horizontal stabilizer front joint and the horizontal stabilizer rear joint.

[0010] Furthermore, the left and right horizontal stabilizer structures include upper and lower stiffened wall panels, a horizontal stabilizer front beam, a horizontal stabilizer rear beam and stabilizer structure wing ribs.

[0011] Furthermore, the upper and lower stiffened wall panels are co-cured formed wall panels of composite material skins and T-shaped stringers.

[0012] Furthermore, the cross-sections of the horizontal stabilizer front beam and the horizontal stabilizer rear beam are "C" shaped, and they are composite material laminate structures. The horizontal stabilizer front beam opens backward along the course direction, and the horizontal stabilizer rear beam opens forward along the course direction.

[0013] Furthermore, the cross-section of the stabilizer structure wing rib is "C" shaped, and it is a composite material laminate structure. The opening direction is from the wing tip to the wing root.

[0014] Furthermore, the central docking rib structure includes an upper T-shaped connecting strip plate, a docking rib web and a lower T-shaped connecting strip plate,

[0015] Among them, the vertical ribs of the upper T-shaped connecting strip plate and the lower T-shaped connecting strip plate of the central docking rib structure are respectively connected to the docking rib web through fasteners to form an "I" shaped structure.

[0016] Furthermore, the upper and lower stiffened panel plates of the left and right horizontal stabilizer structures are respectively connected through the upper and lower T-shaped connecting strip plates of the central docking rib structure, and the webs of the front beam of the horizontal stabilizer and the rear beam of the horizontal stabilizer of the left and right horizontal stabilizer structures are respectively connected through the front beam connecting strip plate and the rear beam connecting strip plate.

[0017] Furthermore, the front horizontal stabilizer joint is arranged at the leading edge position of the central docking area of the central docking rib structure, and one side with a vertical rib web surface is fixedly connected to the front beam connecting strip plate through fasteners; the rear horizontal stabilizer joint is arranged at the trailing edge position of the central docking area of the central docking rib structure, and one side with a vertical rib web surface is fixedly connected to the rear beam connecting strip plate through fasteners.

[0018] Furthermore, both the front horizontal stabilizer joint and the rear horizontal stabilizer joint are of angle box type structures, and two bolt holes and one pin hole are opened on the bottom surfaces thereof.

[0019] Furthermore, the vertical fin end rib structure is arranged at the top of the vertical fin and is the sealing rib of the main box section of the vertical fin, which is integrally machined.

[0020] Furthermore, two bosses are designed on the upper side web of the vertical fin end rib structure, and a plurality of bolt holes, barrel nut installation holes and pin holes are opened on each of the bosses.

[0021] The bolt holes and pin holes on the bosses correspond to the bolt holes and pin holes on the bottom surfaces of the front horizontal stabilizer joint and the rear horizontal stabilizer joint respectively.

[0022] A plurality of barrel nuts are installed on the bosses; a plurality of tie bolts respectively pass through the bolt holes on the bottom surfaces of the front horizontal stabilizer joint and the rear horizontal stabilizer joint and cooperate with the plurality of barrel nuts.

[0023] A plurality of pin shafts respectively pass through the pin holes on the bottom surfaces of the front horizontal stabilizer joint and the rear horizontal stabilizer joint and are connected to the bosses of the vertical fin end rib.

[0024] Furthermore, the connecting angle bar is of an "L" shaped stiffened strip plate configuration, and it is respectively connected to the web of the vertical fin end rib structure and the webs of the front beam of the vertical fin and the rear beam of the vertical fin through multiple rows of fasteners.

[0025] Furthermore, the cross-sections of the front beam of the vertical fin and the rear beam of the vertical fin are of "C" type and are composite material laminate structures. The front beam of the vertical fin has an opening facing forward in the flight direction, and the rear beam of the vertical fin has an opening facing forward in the flight direction.

[0026] Furthermore, the box section wall plates of the horizontal stabilizer structure and the vertical fin structure are the prototype structures of the tail wing stabilizer.

[0027] Advantages of the present invention:

[0028] 1. A new type of detachable fixed connection structure between the high-level horizontal tail and the vertical tail is proposed, as well as the connection schemes and configurations of surrounding beams, ribs, connecting strip plates, etc. The overall scheme has a small number of structures, a clear load transfer path, and is easy to assemble and disassemble;

[0029] 2. In the present invention, the entire horizontal tail is connected to the vertical tail end rib through two front and rear tension joints, with a clear interface and good openness of the assembly space;

[0030] 3. During assembly, positioning can be achieved by borrowing two front and rear pin shafts, and then connecting with tension bolts and barrel nuts. When disassembling, the tension bolts are withdrawn to disassemble the horizontal tail, and the assembly and disassembly are convenient;

[0031] 4. The configuration of the vertical tail end rib in the present invention provides a structural interface for the installation of the horizontal tail while ensuring the structural integrity of the vertical tail box section, reducing the number of parts and connecting structures, and improving the overall structural efficiency. Description of the Drawings

[0032] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on the structures shown in these drawings.

[0033] Figure 1 Shows the structural diagram of the vertical tail end rib according to an embodiment of the present invention;

[0034] Figure 2 Shows the structural diagrams of the front joint and the rear joint of the horizontal tail according to an embodiment of the present invention;

[0035] Figure 3 Shows the layout diagram of the structural scheme of the front joint and the rear joint of the horizontal tail according to an embodiment of the present invention;

[0036] Figure 4 Shows the layout diagram of the structural scheme of the vertical tail end rib, connecting angle section and beam according to an embodiment of the present invention;

[0037] Figure 5 Shows the layout diagram of the structural scheme of the connection between the front joint, the rear joint of the horizontal tail and the vertical tail end rib according to an embodiment of the present invention;

[0038] Figure 6 Shows the assembly schematic diagram of the horizontal tail structure and the vertical tail structure according to an embodiment of the present invention.

[0039] The implementation, functional features, and advantages of the present invention will be further described in conjunction with embodiments with reference to the accompanying drawings. Detailed implementation manners

[0040] Here, exemplary embodiments will be described in detail, and examples thereof are shown in the accompanying drawings. When the following description refers to the accompanying drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The implementation manners described in the following exemplary embodiments do not represent all implementation manners consistent with the present disclosure. On the contrary, they are merely examples of devices and methods consistent with some aspects of the present disclosure as detailed in the appended claims.

[0041] The terms "first", "second", etc. in the specification and claims of the present disclosure are used to distinguish similar objects and do not necessarily have to be used to describe a specific order or sequence. It should be understood that such data can be interchanged under appropriate circumstances so that the embodiments of the present disclosure described herein can be implemented in an order other than those illustrated or described herein. The orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "left", "right", "vertical", "horizontal", "upper", "lower", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the embodiments of the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the protection scope of the present invention.

[0042] In addition, the terms "comprising" and "having" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or device that comprises a series of steps or units does not necessarily have to be limited to those steps or units clearly listed, but may include other steps or units not clearly listed or inherent to these processes, methods, products, or devices.

[0043] "Plurality" includes two or more.

[0044] And / or, it should be understood that for the term "and / or" used in the present disclosure, it is merely a description of the association relationship of associated objects, indicating that three relationships can exist. For example, A and / or B can represent: A exists alone, A and B exist simultaneously, and B exists alone.

[0045] The technical solution of the present invention provides an aircraft detachable T-tail central connection structure, which includes left and right horizontal stabilizers, a central docking rib (upper T-shaped connection strip plate, docking rib web plate, lower T-shaped connection strip plate), a front joint, a rear joint, a front beam connection strip plate, a rear beam connection strip plate, a vertical tail end rib, a vertical tail front beam, a vertical tail rear beam, a front beam connection angle section, a rear beam connection angle section, four groups of tension bolts, and two pin shafts. Except for the components in the detachable connection area, the rest of the components are connected through mechanical connection or hybrid connection (such as a combination of mechanical connection and bonding) to form a connection relationship, constituting the central connection structure of the tail wing, which is used to connect the horizontal tail and the vertical tail of the T-tail and transfer loads.

[0046] In a preferred embodiment, the structures of the left and right horizontal stabilizers are composed of upper and lower stiffened panel, horizontal tail front beam, horizontal tail rear beam, and wing ribs; the upper and lower stiffened panel are co-cured formed panels of composite skin and T-shaped stringers; the cross-sections of the horizontal tail front beam and the horizontal tail rear beam are "C" shaped, with composite laminate structures. The front beam has an opening facing backward along the course direction, and the rear beam has an opening facing forward along the course direction; the cross-section of the wing rib is "C" shaped, with a composite laminate structure, and the opening direction points from the wing tip to the wing root.

[0047] In a preferred embodiment, the structure of the central docking rib is composed of an upper T-shaped connection strip plate, a docking rib web plate, and a lower T-shaped connection strip plate. The vertical ribs of the upper and lower T-shaped connection strip plates are respectively connected to the docking rib web plate through fasteners to form an "I"-shaped central docking rib structure, which is used to connect the left and right horizontal stabilizers.

[0048] In a preferred embodiment, the structure of the horizontal tail is composed of the left and right horizontal stabilizers, the central docking rib structure, the front beam connection strip plate, and the rear beam connection strip plate. The upper and lower wall plates of the horizontal stabilizer box section are respectively connected through the upper and lower T-shaped connection strip plates. The webs of the front and rear beams of the left and right horizontal tails are respectively connected through the front beam connection strip plate and the rear beam connection strip plate to jointly form the structure of the horizontal tail.

[0049] In a preferred embodiment, the front joint is arranged at the leading edge position of the central docking area of the horizontal tail, and is a corner box structure. One side of it with a vertical rib web plate is fixedly connected to the front beam connection strip plate through fasteners. Two bolt holes and one pin hole are opened on its bottom surface for connecting with the vertical tail end rib; the rear joint is arranged at the trailing edge position of the central docking area of the horizontal tail, and is a corner box structure. One side of it with a vertical rib web plate is designed to match the configuration of the rear beam connection strip plate, and is fixedly connected to the rear beam connection strip plate through fasteners. Two bolt holes and one pin hole are opened on its bottom surface for connecting with the vertical tail.

[0050] In a preferred embodiment, the vertical tail end rib structure is arranged at the top of the vertical tail and is the sealing rib of the main box section of the vertical tail. It is integrally machined and formed. The rib flange is connected to the wall panel of the main box section of the vertical tail. The lower side web surface of the end rib is connected to the front beam and the rear beam of the vertical tail respectively through two connecting angles. Two boss structures are designed on the upper side web of the end rib, and two bolt holes, two barrel nut installation holes and one pin hole are opened on each boss; the connecting angle is of an "L"-shaped stiffened strip configuration, and it is connected to the web of the vertical tail end rib and the web of the vertical tail beam respectively through four rows of fasteners; the cross-sections of the front beam and the rear beam of the vertical tail are of a "C" shape and are composite laminate structures. The front beam opens forward along the course direction, and the rear beam opens forward along the course direction.

[0051] In a preferred embodiment, the vertical tail structure is a box section structure, which is composed of a box section wall panel, a vertical tail front beam, a vertical tail rear beam, vertical tail box section ribs and vertical tail end ribs;

[0052] In a preferred embodiment, the box section wall panels of the horizontal tail structure and the vertical tail structure are the prototype structures of the tail wing stabilizer. There is no limitation on its material and structural form here, and it can be adaptively matched with the detachable T-shaped tail wing central connection structure for design.

[0053] Here, the vertical tail box section rib belongs to a general structure and is a part of the vertical tail box section structure.

[0054] In a preferred embodiment, the tail wing beam can include various configurations such as "C" shape and "I" shape, and can be designed for matching according to parameters such as internal load and section stiffness of the structure. No specific configuration and arrangement are limited here.

[0055] Embodiment

[0056] The specific implementation manner of a detachable T-shaped tail wing central connection structure of an aircraft is as follows:

[0057] As Figures 1 to 6 shown, a detachable T-shaped tail wing central connection structure of an aircraft includes left and right horizontal stabilizers 23, a central docking rib (upper T-shaped connection strip 6, docking rib web 7, lower T-shaped connection strip 8), a front joint 2, a rear joint 3, a front beam connection strip 4, a rear beam connection strip 5, a vertical tail end rib 1, a vertical tail front beam 13, a vertical tail rear beam 12, a front beam connection angle 21, a rear beam connection angle 22, four groups of tension bolts and two pin shafts. Except for the components in the detachable connection area, the rest of the components form a connection relationship through mechanical connection or hybrid connection (such as a mixture of mechanical connection and bonding) to form a tail wing central connection structure for connecting the horizontal tail and the vertical tail of the T-shaped tail wing and transmitting loads;

[0058] As Figure 1As shown, the vertical tail end rib 1 is arranged at the top of the vertical tail and is the sealing rib of the main box section of the vertical tail. It is integrally formed by machining. The rib flange is connected to the wall panel of the main box section of the vertical tail. The lower side web surface of the end rib is connected to the front beam 13 and the rear beam 12 of the vertical tail through the front beam connecting angle member 21 and the rear beam connecting angle member 22 respectively. Two boss structures are designed on the upper side web of the end rib, and two bolt holes, two cylindrical nut installation holes and one pin hole are opened on each boss;

[0059] As Figure 2 , Figure 3 shown, the front joint 2 is arranged at the leading edge position of the central docking area of the horizontal tail and is of an angle box type structure. One side of it with a ribbed web surface is fixedly connected to the front beam connecting strip 4 through fasteners. Two bolt holes and one pin hole are opened on its bottom surface to install the tie bolts 14, 15 and the pin shaft 11 so as to connect with the front side boss of the vertical tail end rib 1; the rear joint 3 is arranged at the trailing edge position of the central docking area of the horizontal tail and is of an angle box type structure. One side of it with a ribbed web surface is designed to match the configuration of the rear beam connecting strip 5 and is fixedly connected to the rear beam connecting strip 5 through fasteners. Two bolt holes and one pin hole are opened on its bottom surface to install the tie bolts 17, 18 and the pin shaft 16 so as to connect with the rear side boss of the vertical tail end rib 1;

[0060] As Figure 4 shown, the connecting angle members 21, 22 are arranged inside the vertical tail box section and are of an "L" - shaped stiffened angle member structure; the connecting angle members are in total two places, front and rear, near the top of the vertical tail; one bent side of the connecting angle member 21 is connected to the web of the front beam 13 of the vertical tail through four rows of fasteners, and the other bent side is connected to the front end of the web of the vertical tail end rib 1; one bent side of the connecting angle member 22 is connected to the web of the rear beam 12 of the vertical tail through four rows of fasteners, and the other bent side is connected to the rear end of the web of the vertical tail end rib 1; the above - mentioned structures together form the horizontal tail fixing bracket structure at the top of the vertical tail;

[0061] As Figure 3 , Figure 5 shown, the horizontal tail structure is fixed at the top of the vertical tail structure; the pin shafts 11, 16 respectively pass through the pin holes of the front joint 2 and the rear joint 3 and are connected to the web bosses of the vertical tail end rib 1, playing an assembly positioning role; four cylindrical nuts 9, 10, 19, 20 are installed on the web bosses of the vertical tail end rib 1; the four tie bolts 14, 15, 17, 18 respectively pass through the bolt holes of the front joint 2 and the rear joint 3 and cooperate with the cylindrical nuts to realize the connection between the horizontal tail structure and the vertical tail structure; the connection forms of the four tie bolts and the cylindrical nuts and the connection forms of the two pin shafts are shown by local views;

[0062] As Figure 5 , Figure 6As shown, the detachable T-type tail central connection structure of an aircraft and the assembly drawing of the horizontal tail and vertical tail have been shown; the two pin shafts at the front joint 2 and the rear joint 3 play the role of assembly positioning, and at the same time, transfer the course load, lateral load and torsional moment of the horizontal tail to the vertical tail; the four groups of tension bolts at the front joint 2 and the rear joint 3, while meeting the requirements of quick disassembly and installation, transfer the vertical load, pitching moment and rolling moment of the horizontal tail to the vertical tail.

[0063] As Figure 6 shown, the tail beam may include various configurations such as "C" type and "I" type, and can be designed in a matching manner according to parameters such as internal load and sectional stiffness of the structure. No specific configuration and layout are limited here..

[0064] It should be noted that in this article, the term "including", "comprising" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "including one..." does not exclude the existence of additional identical elements in the process, method, article or device including that element.

[0065] The serial numbers of the above embodiments of the present invention are only for description and do not represent the advantages and disadvantages of the embodiments.

[0066] The embodiments of the present invention have been described above in conjunction with the accompanying drawings. However, the present invention is not limited to the above specific embodiments. The above specific embodiments are merely illustrative and not restrictive. Under the inspiration of the present invention, those of ordinary skill in the art can also make many forms without departing from the spirit and scope protected by the claims of the present invention. These all fall within the protection scope of the present invention.

Claims

1. A detachable T-tail central connection structure for an aircraft, characterized in that: The aircraft detachable T-tail central connecting structure is used to connect the T-tail horizontal tail structure and the vertical tail structure, and includes: The vertical tail structure includes a vertical tail main box section wall panel, a vertical tail front beam, a vertical tail rear beam, a box section rib and a vertical tail end rib structure; wherein the lower side web surface of the end rib of the vertical tail end rib structure is connected to the vertical tail front beam and the vertical tail rear beam respectively through connecting angle bars; the end rib edge strip of the vertical tail end rib structure is connected to the vertical tail main box section wall panel; The horizontal tail structure comprises left and right horizontal stabilizers, a central butt joint rib structure, a front beam connecting strip plate, a rear beam connecting strip plate, a front horizontal tail joint and a rear horizontal tail joint; wherein the left and right horizontal stabilizers are fixedly connected to both sides of the central butt joint rib structure, the front beam connecting strip plate is fixedly connected to the front end surface of the central butt joint rib structure, and the rear beam connecting strip plate is fixedly connected to the rear end surface of the central butt joint rib structure; Wherein, the horizontal tail structure is fixed to the top end of the vertical tail structure, and the horizontal tail structure is fixedly connected to the vertical tail end rib structure through a horizontal tail front joint and a horizontal tail rear joint.

2. The aircraft detachable T-tail central connection structure according to claim 1, characterized in that: The left and right horizontal stabilizer structures include upper and lower stiffened panels, a horizontal tail front beam, a horizontal tail rear beam, and stabilizer structure ribs. Wherein, the upper and lower reinforced wall panels are wall panels formed by co-curing composite material skin and T-shaped long stringers; The cross-section of the horizontal tail front beam and the horizontal tail rear beam is "C"-shaped and is a composite laminate structure. The horizontal tail front beam opens toward the rear along the heading, and the horizontal tail rear beam opens toward the front along the heading; The cross-section of the stabilizer structure rib is "C"-shaped, and is a composite laminate structure, with the opening direction pointing from the wing tip to the wing root.

3. The aircraft detachable T-tail central connection structure according to claim 2, characterized in that: The central butt joint rib structure comprises an upper T-shaped connecting strip plate, a butt joint rib web plate and a lower T-shaped connecting strip plate. Among them, the vertical ribs of the upper T-shaped connecting strip plate and the lower T-shaped connecting strip plate of the central butt-jointed rib structure are respectively connected to the butt-jointed rib web plate through fasteners to form an "I"-shaped structure.

4. The aircraft detachable T-tail central connection structure according to claim 3, characterized in that: The upper and lower stiffened wall panels of the left and right horizontal stabilizer structures are respectively connected by the upper and lower T-shaped connecting strips of the central butt rib structure, and the webs of the horizontal tail front beam and the horizontal tail rear beam of the left and right horizontal stabilizer structures are respectively connected by the front beam connecting strip and the rear beam connecting strip.

5. The aircraft detachable T-tail central connection structure according to claim 4, characterized in that: The front joint of the horizontal tail is arranged at the front edge of the central docking area of ​​the central docking rib structure, and the web surface with vertical ribs on one side is fixedly connected to the front beam connecting strip plate by fasteners; the rear joint of the horizontal tail is arranged at the rear edge of the central docking area of ​​the central docking rib structure, and the web surface with vertical ribs on one side is fixedly connected to the rear beam connecting strip plate by fasteners.

6. The aircraft detachable T-tail central connection structure according to claim 1, characterized in that: The front joint and the rear joint of the horizontal tail are both angle box-type structures, and the bottom surfaces of the two joints are provided with two bolt holes and one pin hole.

7. The aircraft detachable T-tail central connection structure according to claim 1, characterized in that: The upper side web of the vertical tail end rib structure is designed with two bosses, each of which has a plurality of bolt holes, cylindrical nut mounting holes and pin holes. The bolt holes and the pin holes on the boss correspond to the bolt holes and the pin holes on the bottom surface of the horizontal tail front joint and the horizontal tail rear joint; A plurality of barrel nuts are mounted on the boss; a plurality of tension bolts respectively pass through the bolt holes on the bottom surfaces of the horizontal tail front joint and the horizontal tail rear joint and cooperate with the plurality of barrel nuts; A plurality of pin shafts respectively pass through the pin holes on the bottom surfaces of the horizontal tail front joint and the horizontal tail rear joint and are connected to the bosses of the vertical tail end ribs.

8. The aircraft detachable T-tail central connection structure according to claim 1, characterized in that: The connecting angle bar is an "L"-shaped reinforced strip plate configuration, and is connected to the web of the vertical tail end rib structure and the web of the vertical tail front beam and the vertical tail rear beam respectively through multiple rows of fasteners.

9. The aircraft detachable T-tail central connection structure according to claim 1, characterized in that: The vertical tail front beam and the vertical tail rear beam have a "C"-shaped cross-section and are a composite laminate structure. The vertical tail front beam opens forward along the heading, and the vertical tail rear beam opens forward along the heading. Among them, the vertical tail end rib structure is arranged at the top of the vertical tail, is the end rib of the vertical tail main box section, and is an integrated machine addition type.

10. The aircraft detachable T-tail central connection structure according to claim 1, characterized in that: The box-section wall panels of the horizontal tail structure and the vertical tail structure are tail stabilizer dimensional structures.

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