A connecting structure of a wing and a strut in an aircraft body structure

Abstract

This invention discloses a connection structure between a wing and a support arm in an aircraft fuselage structure, including a front beam, a rear beam, a left support arm, a right support arm, reinforcing ribs, and support arm connectors. The front beam and rear beam are connected by reinforcing ribs to form a composite beam. The left and right semi-circular support arms are spliced ​​together to form a hollow cylindrical composite support arm. The composite beam and the composite support arm are vertically assembled and fixed by the support arm connectors. The support arm connectors consist of an inner support ring and an outer connecting plate, simultaneously achieving support arm splicing reinforcement and beam-arm connection fixation. The connection point is provided with a longitudinal support plate and an opening reinforcement to reinforce the connection node, support arm joint, and weak areas of the opening. This invention adopts a fully bolted detachable assembly structure, which is convenient for disassembly, assembly, and maintenance. It solves the problems of insufficient stiffness, uneven load transfer, and easy deformation and loosening of traditional connection structures, effectively improving connection strength and structural stability, while taking into account the requirements of lightweight design. It can be widely adapted to various eVTOL aircraft configurations such as compound wings and tiltrotor aircraft.

Description

Technical Field

[0001] This invention belongs to the field of aircraft airframe structure technology, and specifically relates to a connection structure between the wing and the support arm in an aircraft airframe structure. Background Technology

[0002] Against the backdrop of the rapid development of the low-altitude economy, new types of aircraft such as electric vertical takeoff and landing (eVTOL) aircraft and flying cars widely adopt compound wing and tilt rotor configurations. These aircraft are generally equipped with multiple rotor structures and need to rely on outriggers as the mounting support carriers for the rotors. The connection structure between the outriggers and the wings becomes the core stress-bearing part of the aircraft body.

[0003] The existing connection structures between aircraft wings and booms have many defects: traditional connection structures are mostly integral welded or one-piece molded structures, which are difficult to disassemble and assemble, and have high costs for later maintenance and parts replacement; some split connection structures have problems with insufficient structural rigidity and uneven load distribution. During the flight of the aircraft, rotor vibration loads and aerodynamic loads can easily cause deformation and loosening of the connection parts, affecting flight safety; at the same time, the support and reinforcement structure design of the existing connection structure is unreasonable, the structural strength of the boom splicing seams and connection openings is weak, the overall structural stability and load-bearing capacity are poor, and it cannot meet the design requirements of lightweight, high load and easy maintenance of new aircraft. Summary of the Invention

[0004] The purpose of this invention is to provide a connection structure between the wing and the support arm in an aircraft fuselage structure, so as to solve the technical problems of weak rigidity, inconvenient disassembly and assembly, insufficient strength of seams and openings, and uneven load transfer in the existing wing-support arm connection structure.

[0005] To solve the above-mentioned technical problems, the present invention provides a connection structure between the wing and the support arm in the airframe structure of an aircraft, including a front beam, a rear beam, a left support arm and a right support arm;

[0006] The front beam and the rear beam are arranged at intervals and are connected and fixed by at least one set of reinforcing ribs to form a composite beam.

[0007] The left support arm and the right support arm are spliced ​​and assembled, and the two are connected and fixed by at least one set of support arm connectors to form a combined support arm.

[0008] The composite beam and the composite support arm are arranged perpendicularly, and the two are connected and fixed by the support arm connector.

[0009] Preferably, the front beam and the rear beam have the same structure, are C-shaped as a whole, and have openings facing each other, while the reinforcing ribs are fitted into the openings of the front beam and the rear beam.

[0010] Preferably, the reinforcing ribs are provided in two sets, and are arranged at intervals along the length direction of the composite beam.

[0011] Preferably, the reinforcing rib is a shell structure with mating steps at both ends, which are mated with the openings of the front beam and the rear beam respectively; and the two end faces are also provided with rib connection holes, so that the front beam, the rear beam and the reinforcing rib are connected and fixed by bolts.

[0012] Preferably, the left support arm and the right support arm are both semicircular, and the two are spliced ​​together to form a hollow cylindrical structure.

[0013] Preferably, the outrigger connector has two sets, corresponding to the front beam and the rear beam respectively, each including an inner support ring and an outer connecting plate; the inner support ring is connected and fixed to the combined outrigger, and the outer connecting plate is connected and fixed to the combined beam.

[0014] Preferably, the inner support ring supports the inner circles of both the left and right support arms, and a ring connection hole is provided on the ring wall, so that the left support arm, the right support arm and the inner support ring are connected and fixed by bolts.

[0015] Preferably, the outer connecting plate is attached to the outer wall of the front beam or the rear beam, and the outer connecting plate has multiple plate connection holes, and the front beam, the rear beam and the outer connecting plate are connected and fixed by bolts.

[0016] Preferably, a longitudinal support plate is provided at the connection between the composite beam and the composite support arm, and the longitudinal support plate is arranged along the length direction of the composite support arm; and both ends of the longitudinal support plate are provided with folded edges, which are overlapped and fixed with the overlapping platform of the support arm connector through the folded edges.

[0017] Preferably, the combined support arm is provided with an opening reinforcement on the side away from the combined beam, and the opening reinforcement is arranged at the joint between the left support arm and the right support arm; the opening reinforcement is generally arc-shaped, fits and is fixed to the inner wall of the combined support arm, and overlaps and is fixed with the lap groove of the support arm connector.

[0018] In summary, the beneficial effects of the above-described technical solutions conceived by this invention compared with the prior art include:

[0019] 1. This invention adopts a split assembly structure. The wing side is formed by splicing the front beam and rear beam with reinforcing ribs to form a composite beam. The support arm side is formed by splicing the left and right semi-circular support arms to form a hollow cylindrical composite support arm. The entire process adopts bolt-detachable mechanical connection, abandoning the traditional one-piece molding and welding fixing method. It is convenient to disassemble and assemble, which facilitates the later inspection, replacement and maintenance of parts, and greatly reduces the aircraft operation and maintenance cost.

[0020] 2. This invention features a dedicated outrigger connector. The inner support ring enables the splicing and fixing of the left and right outriggers and provides internal support. The outer connecting plate enables a reliable connection between the outriggers and the wing composite beam. The dual connection structure enables layered load transfer, solving the problems of uneven load transfer and loose connections in traditional structures, and significantly improving connection reliability.

[0021] 3. The present invention forms a box-type composite beam structure by combining C-shaped front and rear beams with interlocking reinforcing ribs, which effectively improves the torsional stiffness of the wing connection area and the overall structural strength. The two sets of spaced reinforcing ribs can evenly distribute the load, avoid local stress concentration in the wing, and improve the stability of the airframe structure.

[0022] 4. The present invention adds a longitudinal support plate and an opening reinforcement. The longitudinal support plate provides longitudinal reinforcement to the connection node, improving the bending resistance at the connection between the support arm and the wing. The arc-shaped opening reinforcement fits into the inner wall of the support arm joint, effectively strengthening the structural strength of the support arm splicing opening and joint position, making up for the strength shortcomings of the split support arm structure, and adapting to the high-speed flight and high-frequency vibration conditions of the rotor of the aircraft.

[0023] 5. The present invention has a compact overall structure and light weight, which is suitable for the lightweight design requirements of carbon fiber composite materials for aircraft. At the same time, the structure has strong versatility and can be widely adapted to various eVTOL aircraft configurations such as compound wings and tiltrotor aircraft, making it widely applicable. Attached Figure Description

[0024] Figure 1 A first-view view of the connection structure between the wing and the support arm in the aircraft fuselage structure provided by the present invention;

[0025] Figure 2 A second-view diagram of the connection structure between the wing and the support arm in the aircraft fuselage structure provided by the present invention;

[0026] Figure 3 An exploded view of the connection structure between the wing and the support arm in the aircraft fuselage structure provided by the present invention;

[0027] Figure 4 A schematic diagram of the reinforcing ribs provided by the present invention;

[0028] Figure 5 A schematic diagram of the structure of the support arm connector provided by the present invention;

[0029] Figure 6 A schematic diagram of the structure of the longitudinal support plate provided by the present invention;

[0030] Figure 7 This is a schematic diagram of the structure of the opening reinforcement provided by the present invention.

[0031] The meanings of the markings in the attached diagram are as follows:

[0032] In the diagram: 1-Front beam, 2-Rear beam, 3-Left support arm, 4-Right support arm, 5-Reinforcing rib, 51-Matching step, 52-Rib connection hole, 6-Support arm connector, 61-Inner support ring, 62-Outer connecting plate, 63-Ring connection hole, 64-Plate connection hole, 65-Overlap platform, 66-Overlap groove, 7-Longitudinal support plate, 71-Folded edge, 8-Opening reinforcement. Detailed Implementation

[0033] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of the present invention will become clearer from the following description and claims. It should be noted that the drawings are all in a very simplified form and use non-precise proportions, and are only used to facilitate and clarify the illustration of the embodiments of the present invention.

[0034] In the description of this invention, it should be understood that the orientation or positional relationship indicated by terms such as "spaced arrangement", "fitting installation", and "fitting fixation" are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the purpose of simplifying the description of this invention, and are not intended to indicate or limit that the referred components must have a specific orientation, structure and operation, and should not be construed as a limitation of this invention; at the same time, the term "at least a group" means two or more, and "corresponding" means that the structure matches and the positions are arranged accordingly.

[0035] Example

[0036] This invention provides a connection structure between the wing and the support arm in an aircraft fuselage structure. Please refer to [link / reference]. Figure 1-3 It includes a front beam 1, a rear beam 2, a left support arm 3, and a right support arm 4; the front beam 1 and the rear beam 2 are spaced apart and are connected and fixed by at least one set of reinforcing ribs 5 to form a composite beam; the left support arm 3 and the right support arm 4 are spliced ​​and assembled and are connected and fixed by at least one set of support arm connectors 6 to form a composite support arm; the composite beam and the composite support arm are arranged perpendicularly and are connected and fixed by the support arm connectors 6.

[0037] In this embodiment, the front beam 1 and the rear beam 2 have the same structure, both being C-shaped structures. They are arranged in parallel with their openings facing each other. Two sets of reinforcing ribs 5 are evenly spaced along the length of the combined beam and are fitted into the opposite openings of the front beam 1 and the rear beam 2.

[0038] For further details, please refer to Figure 4The reinforcing rib 5 adopts a hollow shell structure, which is lightweight and has high structural strength. It has an integrally formed interlocking step 51 at both ends, which is precisely interlocked and positioned with the openings of the front beam 1 and the rear beam 2 through the interlocking step 51. At the same time, the end faces of the reinforcing rib 5 are provided with rib connection holes 52. During assembly, the front beam 1, the rear beam 2 and the reinforcing rib 5 are fastened together by bolts through the rib connection holes 52, forming a closed box-type composite beam, which greatly improves the torsional stiffness and load-bearing capacity of the wing connection area.

[0039] Specifically, both the left support arm 3 and the right support arm 4 are semi-circular arc structures. When symmetrically spliced ​​together, they can form a complete hollow cylindrical combined support arm. The hollow structure can minimize the structural weight and meet the lightweight design requirements of the aircraft.

[0040] Furthermore, such as Figure 5 As shown, the two sets of support arm connectors 6 are arranged corresponding to the positions of the front beam 1 and the rear beam 2, respectively. Each set of support arm connectors 6 consists of an inner support ring 61 and an outer connecting plate 62.

[0041] During the assembly of the outriggers, the inner support ring 61 fits against the inner circular wall of the left outrigger 3 and the right outrigger 4, achieving precise alignment and support of the left and right outriggers. Multiple sets of ring connection holes 63 are evenly opened on the ring wall of the inner support ring 61. By passing bolts through the ring connection holes 63, the left outrigger 3, the right outrigger 4 and the inner support ring 61 are fastened together, realizing the overall forming and fixing of the combined outriggers, effectively preventing the outrigger splicing position from loosening or misaligning.

[0042] An outer connecting plate 62 is integrally connected to the inner support ring 61. The outer connecting plate 62 fits against the outer wall of the corresponding front beam 1 or rear beam 2. Multiple plate connecting holes 64 are arrayed on the outer connecting plate 62. The outer connecting plate 62 is fastened to the corresponding front beam 1 or rear beam 2 by bolts passing through the plate connecting holes 64, thereby realizing the vertical fixed assembly of the combined support arm and the combined beam. The support arm connector 6 simultaneously completes the splicing of the support arm itself and the bidirectional fixation of the support arm and the wing. The connection structure is compact and the stress is even.

[0043] To further enhance the structural strength of the connection nodes, longitudinal support plates 7 are installed at the connection points between the composite beam and the composite support arm. For example... Figure 3 and Figure 6 As shown, the longitudinal support plate 7 is arranged longitudinally along the length of the combined support arm, which can effectively resist the bending moment generated by the load on the support arm. The longitudinal support plate 7 has symmetrical flanges 71 at both ends, and the outer side of the support arm connector 6 is provided with an overlapping platform 65 that matches the flanges 71. The longitudinal support plate 7 is fixed by overlapping the flanges 71 at both ends with the overlapping platform 65, realizing the coordinated force of multiple structures and further improving the stability and deformation resistance of the connection node.

[0044] Meanwhile, at the end of the combined support arm furthest from the combined beam, an arc-shaped opening reinforcement 8 is provided at the splice joint between the left support arm 3 and the right support arm 4, such as... Figure 3 and Figure 7 As shown, the opening reinforcement 8 is integrally fitted and fixed to the inner wall of the combined outrigger, and the end of the opening reinforcement 8 overlaps and is fixed with the lap groove 66 of the outrigger connector 6. The opening reinforcement 8 can effectively fill the structural weak areas caused by the splicing of the split outrigger, and provide all-round reinforcement to the opening and joint positions of the outrigger, so as to avoid cracking and deformation problems at the end of the outrigger under aerodynamic loads and rotor vibration loads.

[0045] The invention adopts a fully bolted detachable assembly structure, with no welding or integral solidification structure, making assembly, disassembly, and maintenance convenient. Through the synergistic effect of multiple reinforcing structures, it solves the problems of insufficient rigidity, weak strength, and uneven load transfer in traditional wing arm connection structures, taking into account lightweight, high reliability, and easy maintenance, and is fully adaptable to the usage requirements of various compound wings and tiltrotor eVTOL aircraft.

[0046] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A connection structure between a wing and a support arm in an aircraft fuselage structure, characterized in that, It includes the front beam (1), the rear beam (2), the left support arm (3) and the right support arm (4); The front beam (1) and the rear beam (2) are arranged at intervals and are connected and fixed by at least one set of reinforcing ribs (5) to form a composite beam; The left support arm (3) and the right support arm (4) are spliced ​​and assembled, and the two are connected and fixed by at least one set of support arm connectors (6) to form a combined support arm; The combined beam and the combined support arm are arranged perpendicularly, and the two are connected and fixed by the support arm connector (6).

2. The connection structure between the wing and the support arm in an aircraft fuselage structure according to claim 1, characterized in that, The front beam (1) and the rear beam (2) have the same structure and are C-shaped. Their openings face each other, and the reinforcing rib (5) is fitted into the openings of the front beam (1) and the rear beam (2).

3. The connection structure between the wing and the support arm in an aircraft fuselage structure according to claim 2, characterized in that, The reinforcing ribs (5) are provided in two sets, and are arranged at intervals along the length of the composite beam.

4. The connection structure between the wing and the support arm in an aircraft fuselage structure according to claim 3, characterized in that, The reinforcing rib (5) is a shell structure with mating steps (51) at both ends. The mating steps (51) are mated with the openings of the front beam (1) and the rear beam (2) respectively. The two end faces are also provided with rib connection holes (52), and the front beam (1), the rear beam (2) and the reinforcing rib (5) are connected and fixed by bolts.

5. The connection structure between the wing and the support arm in an aircraft fuselage structure according to claim 1, characterized in that, The left support arm (3) and the right support arm (4) are both semicircles, and they are spliced ​​together to form a hollow cylindrical structure.

6. The connection structure between the wing and the support arm in an aircraft fuselage structure according to claim 5, characterized in that, The arm connector (6) is provided in two sets, corresponding to the front beam (1) and the rear beam (2) respectively. It includes an inner support ring (61) and an outer connecting plate (62). The inner support ring (61) is connected and fixed to the combined arm, and the outer connecting plate (62) is connected and fixed to the combined beam.

7. The connection structure between the wing and the support arm in an aircraft fuselage structure according to claim 6, characterized in that, The inner support ring (61) simultaneously supports the inner circles of the left support arm (3) and the right support arm (4), and a ring connection hole (63) is provided on the ring wall. The left support arm (3), the right support arm (4) and the inner support ring (61) are connected and fixed by bolts.

8. The connection structure between the wing and the support arm in an aircraft fuselage structure according to claim 6, characterized in that, The outer connecting plate (62) is attached to the outer wall of the front beam (1) or the rear beam (2), and the outer connecting plate (62) is provided with multiple plate connection holes (64), and the front beam (1), the rear beam (2) and the outer connecting plate (62) are connected and fixed by bolts.

9. The connection structure between the wing and the support arm in an aircraft fuselage structure according to claim 6, characterized in that, The connection between the composite beam and the composite support arm is provided with a longitudinal support plate (7), which is arranged along the length direction of the composite support arm; and the two ends of the longitudinal support plate (7) are provided with folded edges (71), which are overlapped and fixed with the overlapping platform (65) of the support arm connector (6) through the folded edges (71).

10. The connection structure between the wing and the support arm in an aircraft fuselage structure according to claim 6, characterized in that, An opening reinforcement (8) is provided on the side of the combined support arm away from the combined beam. The opening reinforcement (8) is located at the joint between the left support arm (3) and the right support arm (4). The opening reinforcement (8) is arc-shaped and fits and is fixed to the inner wall of the combined support arm. It also overlaps and is fixed to the lap groove (66) of the support arm connector (6).

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