V-shaped empennage and fuselage connecting structure

Abstract

The invention discloses a V-shaped empennage and fuselage connecting structure and belongs to the technical field of aircraft design, the fuselage is of a square structure, six pairs of single-lug connectors in two rows are symmetrically arranged on the top of the fuselage, two V-shaped empennages comprise front beams, middle beams, rear beams, front beam connectors, rear beam connectors, ribs and empennage wallboards, the front beam connectors and the rear beam connectors are of inflection structures, and the front beam connectors and the rear beam connectors are of an inflection structure. The upper end of the middle beam is in lap joint with the front beam and the rear beam respectively, the lower end of the middle beam is connected with the single-lug connector on the fuselage, the middle beam is also of an inflection structure, the upper portion of the middle beam is parallel to the front beam and the rear beam, the lower portion of the middle beam is a connector connected with the single-lug connector on the fuselage, and the structure solves the assembly problem that the butt joint installation angle of the V-shaped empennage structure and the fuselage is large. In addition, the scale container loading efficiency is optimized, the empennage fuselage interface is simple, and the empennage fuselage interface is easy to install, the empennage load transfer efficiency is improved, and meanwhile the reliability of the load transfer system is remarkably improved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft design and relates to a V-shaped tail and fuselage connection structure. Background Art

[0002] With the rapid growth in air transport demand, unmanned transport aircraft (UAVs) have garnered widespread attention as an efficient, flexible, and sustainable air transport solution. V-tail UAVs, in particular, have become a research hotspot due to their superior flight performance, adaptability, and reliability in complex environments. However, in practical applications, V-tail UAVs face numerous technical challenges.

[0003] First of all, in terms of fuselage layout design, how to optimize the loading efficiency of scale containers and the requirement of a simple and easy-to-install tail-fuselage interface have always been key issues in improving the functions of transport aircraft.

[0004] Secondly, the load-carrying efficiency of a V-tail transport aircraft has always been a key factor influencing its performance. As a crucial load-carrying structure, the tail must withstand significant load pressure. However, in existing designs, the tail's load-carrying system has low reliability and is prone to malfunction or failure.

[0005] Furthermore, the tail root area of ​​a V-tail transport aircraft has crucial safety and security requirements. This area typically experiences significant stress concentration, and damage or failure there could lead to a decrease in the safety of the entire aircraft, or even loss of control. Therefore, improving the safety and security of this area has become a key research area.

[0006] Finally, the installation angle when the V-shaped tail structure is docked with the fuselage is too large, which increases the difficulty of overall assembly efficiency.

[0007] In summary, the current development of V-tail transport aircraft technology still faces numerous challenges, including fuselage layout optimization, payload efficiency improvement, safety enhancement, and installation angle optimization. To address these challenges, this paper proposes an innovative solution to promote the technological advancement and practical application of V-tail unmanned transport aircraft. Summary of the Invention

[0008] In view of this, the present invention provides a V-shaped tail-to-fuselage connection structure. Through innovative design concepts and technical means, the fuselage layout design achieves the optimization of scale container loading efficiency and the requirement of a simple and easy-to-install tail-to-fuselage interface. Furthermore, this structure significantly improves the reliability of the transfer system while improving the tail's load-carrying efficiency. Furthermore, the present invention also places special emphasis on the safety and protection performance of the tail root area, effectively improving its anti-destructive and impact resistance. Finally, this technology successfully solves the assembly problem of the V-shaped tail structure and the fuselage with a large installation angle.

[0009] The technical solution of the present invention:

[0010] A V-shaped tail and fuselage connection structure includes: a V-shaped tail 1, a fuselage 2 and a shear wall panel 3. The fuselage 2 is arranged in a square structure. Two V-shaped tails 1 are symmetrically arranged above the fuselage 2 and connected to the fuselage 2 through a joint. The shear wall panel 3 is connected to the connection between the two sides of the two V-shaped tails 1 and the skin of the fuselage 2 to form an aerodynamic shape.

[0011] The fuselage 2 has a square structure layout, which is convenient for loading cargo, and the tail-fuselage interface structure is simple, which improves the assembly processability. The fuselage 2 includes a fuselage frame 21 and a fuselage wall panel 22 wrapped outside the fuselage frame 21. Six pairs of single-ear joints are provided on the top of the fuselage 2, which are divided into two rows and symmetrically arranged on the left and right sides of the top of the fuselage frame 21. Each row includes three pairs of joints at the front, middle and rear. Each pair of joints is arranged side by side, and the single-ear joints and the fuselage frame 21 are an integral part.

[0012] The two V-shaped tail fins 1 are respectively the left tail fin and the right tail fin, and the two are mirror images of each other, and both include a front beam 11, a middle beam 12, a rear beam 13, a rib 14, a tail panel 15, a front beam joint 16 and a rear beam joint 17; the front beam joint 16 is mainly a triangular frame structure, and two double-ear joints are provided at the bottom, which are used to connect with the paired front joints on the top of the fuselage 2 by connecting bolts, and a web is provided on one side of the triangular frame on the outside, and the web and the triangular frame adopt a bending structure so that the web extends obliquely backward and upward and has the same angle as the front beam 11, and the web overlaps the front beam 11; the rear beam joint 17 is mainly a web, and two double-ear joints are provided at the bottom of the web. The rear beam joint 17 also adopts a bending structure, and its web and double-ear joint are parallel to the web and double-ear joint of the front beam joint 16 respectively, and the two double-ear joints of the rear beam joint 17 are connected with the paired rear joints on the fuselage 2 by connecting bolts. It is overlapped with the rear beam 13, and the front beam 11 is parallel to the rear beam 13; a rib 14 is connected between the middle parts of the front beam 11 and the rear beam 13, and the bottom of the rib 14 is connected to the middle beam 12 near the side of the rear beam 13. The middle beam 12 also adopts a bent structure, the upper part of which is parallel to the front beam 11 and the rear beam 13, and the lower part is a triangular frame structure, parallel to the triangular frame of the front beam joint 16. Two double-ear joints are provided at the bottom of the middle beam 12 for connecting to the paired middle joints on the fuselage 2 through connecting bolts; ribs 14 are further connected between the middle beam 12 and the front beam 11 and the rear beam 13, and another rib 14 is connected between the triangular frame at the lower part of the middle beam 12 and the front beam joint 16; tail wall panels 15 are installed on both sides of the outside of the left and right tail fins; the left and right tail fins are connected to the single-ear joint on the fuselage 2 through the front beam joint 16, the middle beam 12 and the rear beam joint 17 respectively, to transfer the lateral load and vertical load of the V-shaped tail 1.

[0013] The shear panel 3 includes a shear skin 31 and an L-shaped sheet metal angle 32 arranged on both sides of the shear skin 31. The shear skin 31 is fixedly connected to the L-shaped sheet metal angle 32 or is an integrated structure. There are four shear skins 31 in total, which are connected to the junction of the tail panel 15 and the fuselage panel 22 on both sides of the left tail and the right tail through the L-shaped sheet metal angle 32 to form an aerodynamic shape for transmitting the heading load of the V-shaped tail 1. Since the shear panel 3 has weak lateral and vertical stiffness on the fuselage 2 and is easy to deform, it can be ensured that the shear panel 3 does not participate in the transmission of lateral and vertical loads.

[0014] A gap of 2 to 5 mm is provided between the single-ear joint on the fuselage frame 21 and the double-ear joints of the front beam joint 16 , the middle beam 12 and the rear beam joint 17 to ensure that the joints do not participate in transmitting the heading load.

[0015] The center beam 12 is arranged close to the rear beam 13 and is designed for damage safety. The front beam joint 16, the rear beam joint 17, and the front joint and rear joint on the top of the fuselage 2 and their connecting bolts are all tight fits. The double-ear joint of the center beam 12 and the center joint on the top of the fuselage 2 and their connecting bolts have a clearance of 0.5 to 2 mm to ensure that after the rear beam joint 16 is damaged, the load is redistributed after the V-shaped tail 1 is deformed, and the center beam 12 begins to bear the load and is able to bear the corresponding load.

[0016] Beneficial effects of the present invention:

[0017] 1. Existing V-shaped tails have a large installation angle with the fuselage. The present invention employs a kinked design at the webs of the front and rear beam joints, overlapping the front and rear beams. The center beam joints are integrally designed with the center beam, also employing a kinked structure at the beam webs. This structure resolves the assembly issue of the V-shaped tail structure with a large installation angle between the tail and the fuselage, and is particularly suitable for large unmanned transport aircraft.

[0018] 2. The present invention achieves the optimization of the loading efficiency of the scale container and the requirements of simple and easy installation of the tail fuselage interface;

[0019] 3. While improving the tail wing's load-carrying efficiency, it also significantly enhances the reliability of the load-carrying system.

[0020] 4. Focus on the safety protection performance of the tail root area, effectively improving its anti-destruction and impact resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a schematic diagram according to an embodiment of the present invention;

[0022] Figure 2 yes Figure 1 Schematic diagram of the main body of the mid-fuselage structure;

[0023] Figure 3yes Figure 1 Schematic diagram of the main structure of the left tail wing (left side panel not shown);

[0024] Figure 4 yes Figure 1 Schematic diagram of the tail wing shear panel on the left side of the center;

[0025] Figure 5 yes Figure 1 Schematic diagram of the gap setting for the single-ear and double-ear joints connecting the center beam joint to the fuselage.

[0026] In the figure: 1-V-shaped tail; 2-fuselage; 3-shear wall panel; 11-front beam; 12-middle beam; 13-rear beam; 14-rib; 15-tail wall panel; 16-front beam joint; 17-rear beam joint; 21-fuselage frame; 22-fuselage wall panel; 31-shear skin; 32-L-shaped sheet metal angle. DETAILED DESCRIPTION

[0027] The technical solution of the present invention will be further described below in conjunction with specific embodiments and drawings.

[0028] A V-shaped tail and fuselage connection structure, comprising: a V-shaped tail 1, a fuselage 2 and a shear wall panel 3, such as Figure 1 .

[0029] The fuselage 2 has a square structure, which is convenient for cargo loading, and the tail fuselage interface structure is simple, which improves the assembly process. The fuselage 2 includes a fuselage frame 21 and a fuselage wall panel 22 wrapped outside the fuselage frame 21. Six pairs of single-ear joints are provided on the top of the fuselage 2, which are divided into two rows and symmetrically arranged on the left and right sides of the top of the fuselage frame 21. Each row includes three pairs of joints, namely the front, middle and rear pairs. Each pair of joints is arranged side by side. The single-ear joints and the fuselage frame 21 are integral parts. Figure 2 .

[0030] The V-shaped tail 1 includes a left tail wing and a right tail wing, which are symmetrically arranged above the fuselage 2 as mirror images of each other, and each includes a front beam 11, a middle beam 12, a rear beam 13, a rib 14, a tail panel 15, a front beam joint 16 and a rear beam joint 17. Figure 3The front beam joint 16 is mainly a triangular frame structure, with two double-ear joints at the bottom, which are used to connect with the paired front joints on the top of the fuselage 2 by connecting bolts. A web is provided on one side of the triangular frame on the outside, and the web and the triangular frame adopt a bending structure so that the web extends obliquely upward and rearward and has the same angle as the front beam 11, and the web overlaps the front beam 11; the rear beam joint 17 is mainly a web, with two double-ear joints at the bottom of the web, and the rear beam joint 17 also adopts a bending structure, whose web and double-ear joint are respectively parallel to the web and double-ear joint of the front beam joint 16, and the two double-ear joints of the rear beam joint 17 are connected to the paired rear joints on the fuselage 2 by connecting bolts, whose web overlaps the rear beam 13, and the front beam 11 is parallel to the rear beam 13; the middle part of the front beam 11 and the rear beam 13 is connected The rib 14 is connected to the middle beam 12 at the bottom near the rear beam 13. The middle beam 12 also adopts a bent structure. Its upper part is parallel to the front beam 11 and the rear beam 13, and the lower part is a triangular frame structure, parallel to the triangular frame of the front beam joint 16. Two double-ear joints are provided at the bottom of the middle beam 12, which are used to connect with the paired middle joints on the fuselage 2 through connecting bolts; ribs 14 are further connected between the middle beam 12 and the front beam 11 and the rear beam 13, and another rib 14 is connected between the triangular frame at the bottom of the middle beam 12 and the front beam joint 16; tail wall panels 15 are installed on both sides of the outside of the left and right tail wings; the left and right tail wings are connected to the single-ear joint on the fuselage 2 through the front beam joint 16, the middle beam 12 and the rear beam joint 17 respectively, to transmit the lateral load and vertical load of the V-shaped tail 1.

[0031] The shear panel 3 includes a shear skin 31 and an L-shaped sheet metal angle 32 arranged on both sides of the shear skin 31. The shear skin 31 and the L-shaped sheet metal angle 32 are an integral structure. There are four shear skins 31, which are connected to the junction of the tail panel 15 and the fuselage panel 22 on both sides of the left tail and the right tail through the L-shaped sheet metal angle 32 to form an aerodynamic shape for transmitting the heading load of the V-shaped tail 1. Since the shear panel 3 has weak lateral and vertical stiffness on the fuselage 2 and is easy to deform, it can be ensured that the shear panel 3 does not participate in the transmission of lateral and vertical loads. Figure 4 .

[0032] A 2 mm gap is set between the single-ear joint on the fuselage frame 21 and the double-ear joints of the front beam joint 16, the middle beam 12 and the rear beam joint 17 to ensure that the joints do not participate in the transmission of heading loads.

[0033] The center beam 12 is arranged close to the rear beam 13 and is designed for damage safety. The front beam joint 16, the rear beam joint 17, and the front joint and rear joint on the top of the fuselage 2 and their connecting bolts are all tight fit. The double-ear joint of the center beam 12 and the center joint on the top of the fuselage 2 and its connecting bolts have a 0.5mm clearance fit to ensure that after the rear beam joint 16 is damaged, the load is redistributed after the V-shaped tail 1 is deformed, and the center beam 12 begins to bear the load and is able to bear the corresponding load. Figure 5 .

[0034] The webs of the front and rear beam joints 16 and 17 are bent and overlapped with the front and rear beams 11 and 13. The joints of the center beam 12 are integrally designed with the center beam 12, also with a bent structure at the beam webs. This structure solves the problem of the V-shaped tail structure 1 having a large installation angle when docking with the fuselage 2.

[0035] In summary, the present invention achieves the optimization of scale container loading efficiency and the simple, easy-to-install interface between the tail and fuselage in the fuselage layout design. Furthermore, while improving tail load transfer efficiency, this structure significantly enhances the reliability of the transfer system. Furthermore, the present invention also places special emphasis on the safety and protection of the V-shaped tail root area, effectively improving its damage resistance and impact resistance. Finally, this technology successfully resolves the assembly problem of the V-shaped tail structure with the fuselage at a large installation angle.

Claims

1. A V-shaped tail and fuselage connection structure, characterized in that: include: The invention relates to a V-shaped tail (1), a fuselage (2) and a shear panel (3). The fuselage (2) is arranged in a square structure. The two V-shaped tails (1) are symmetrically arranged above the fuselage (2) and connected to the fuselage (2) through a joint. The shear panel (3) is connected to the connection between the two sides of the two V-shaped tails (1) and the skin of the fuselage (2) to form an aerodynamic shape.

2. The V-shaped tail and fuselage connection structure according to claim 1, characterized in that: Specifically: The fuselage (2) comprises a fuselage frame (21) and a fuselage wall panel (22) wrapped around the fuselage frame (21); two rows of single-ear joints are symmetrically arranged on the top of the fuselage (2), and each row comprises front, middle and rear joints; The two V-shaped tail wings (1) are respectively a left tail wing and a right tail wing, and the two are mirror images of each other, and both include a front beam (11), a middle beam (12), a rear beam (13), a rib (14), a tail wing wall plate (15), a front beam joint (16) and a rear beam joint (17); the front beam joint (16) is a triangular frame structure, and a double-ear joint is provided at the bottom for connecting with the front joint at the top of the fuselage (2); a web is provided on the outer side of the triangular frame, and the web is connected to the triangular frame. The shaped frame adopts a bending structure, so that the web extends obliquely upward and backward and has the same angle as the front beam (11), and the web overlaps the front beam (11); the rear beam joint (17) is mainly a web, and a double-ear joint is provided at the bottom of the web. The rear beam joint (17) also adopts a bending structure, and its web and double-ear joint are respectively parallel to the web and double-ear joint of the front beam joint (16). The rear beam joint (17) is connected to the rear joint on the fuselage (2), and its web overlaps the rear beam (13), and the front beam (11) and the rear beam are connected. (13) parallel; a rib (14) is connected between the middle of the front beam (11) and the rear beam (13); the bottom of the rib (14) is connected to the middle beam (12) near the side of the rear beam (13); the middle beam (12) also adopts a bending structure, the upper part of which is parallel to the front beam (11) and the rear beam (13), and the lower part is a triangular frame structure, which is parallel to the triangular frame of the front beam joint (16). A double-ear joint is provided at the bottom of the middle beam (12) for connecting with the middle joint on the fuselage (2); the middle beam (12) A rib (14) is connected to the front beam (11) and the rear beam (13), and another rib (14) is connected between the triangular frame at the bottom of the middle beam (12) and the front beam joint (16); tail panels (15) are installed on both sides of the outside of the left tail wing and the right tail wing; the left tail wing and the right tail wing are connected to the single ear joint on the fuselage (2) through the front beam joint (16), the middle beam (12) and the rear beam joint (17) respectively, so as to transmit the lateral load and vertical load of the V-shaped tail wing (1); The shear panel (3) comprises a shear skin (31) and L-shaped sheet metal angles (32) arranged on both sides of the shear skin (31). A total of four shear skins (31) are provided, which are respectively connected to the junction of the tail panel (15) and the fuselage panel (22) on both sides of the left tail and the right tail through the L-shaped sheet metal angles (32) to form an aerodynamic shape for transmitting the heading load of the V-shaped tail (1).

3. The V-shaped tail and fuselage connection structure according to claim 2, characterized in that: Six pairs of single-ear joints are provided on the top of the fuselage (2), which are symmetrically arranged in two rows on the left and right sides of the top of the fuselage frame (21), and each row includes three pairs of joints at the front, middle and rear sides, and each pair of joints is arranged side by side; two double-ear joints are provided at the bottom of the front beam joint (16), the middle beam (12) and the rear beam joint (17), respectively connected to the paired front, middle and rear joints at the top of the fuselage (2).

4. A V-shaped tail and fuselage connection structure according to claim 2 or 3, characterized in that: The single ear connector and the fuselage frame (21) are an integral part.

5. The V-shaped tail and fuselage connection structure according to claim 2, characterized in that: The shear skin (31) and the L-shaped sheet metal angle (32) are fixedly connected or form an integrated structure.

6. The V-shaped tail and fuselage connection structure according to claim 2, characterized in that: Gaps are provided between the single-ear joint on the fuselage frame (21) and the double-ear joints of the front beam joint (16), the middle beam (12) and the rear beam joint (17) to ensure that the joints do not participate in transmitting the heading load.

7. The V-shaped tail and fuselage connection structure according to claim 6, characterized in that: The gap is 2 to 5 mm.

8. The V-shaped tail and fuselage connection structure according to claim 2, characterized in that: The front beam joint (16), the rear beam joint (17), and the front joint and the rear joint at the top of the fuselage (2) and their connecting bolts are all tightly fitted, and the double-ear joint of the middle beam (12) and the middle joint at the top of the fuselage (2) and its connecting bolts are loosely fitted.

9. The V-shaped tail and fuselage connection structure according to claim 8, characterized in that: The gaps between the double-ear joints of the center beam (12) and the center joint on the top of the fuselage (2) and their connecting bolts are 0.5 to 2 mm.

Images