Aircraft engine firewall and wing connecting structure

Abstract

An aircraft engine firewall and wing connecting structure belongs to the technical field of aircraft manufacturing, is used for improving the connecting strength between a wing and an engine nacelle, and comprises a wing and an aircraft engine nacelle, the aircraft engine nacelle comprises a front firewall, a rear firewall, an upper firewall, a box-shaped machining part, a second joint, a third joint, a reinforcing connecting rod and a reinforcing rib, the upper firewall is arranged between the front firewall and the rear firewall, the second connector is arranged on the rear end face of the front firewall, the third connector is arranged on the front end face of the rear firewall, a reinforcing connecting rod is connected between the second connector and the third connector, and the box-shaped machining part is arranged in a wing. The reinforcing rib is of a triangular structure, the reinforcing rib is arranged on the rear end face of the rear firewall, the front end of the reinforcing rib, the rear firewall and the third connector are connected through screws, and the upper end of the reinforcing rib, the wing skin and the box-shaped machining part are connected through screws.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft manufacturing, and relates to a connection structure between an aircraft engine firewall and a wing. Background Technique

[0002] The stability of the connection structure between an aircraft engine nacelle and a wing is crucial for flight safety. As a protective cover for the aircraft's core equipment - the engine, the nacelle not only protects the engine from external damage, but also fixes the engine and optimizes the engine airflow to ensure that the engine can operate normally in various usage environments and flight states. The design and manufacture of the nacelle are related to key aviation technologies such as aircraft performance, operation safety, system reliability, weight, and cost. The stability of the connection structure between the nacelle and the wing directly affects the aerodynamic performance and structural integrity of the aircraft. For example, the engine pylon section is the transitional section between the engine, nacelle, and wing. It is one of the important structural sections of a large aircraft and plays a key role in transmitting the engine thrust, absorbing engine vibration, and isolating the engine fire area. An unstable connection between the nacelle and the wing may lead to serious safety hazards. Historically, accidents caused by problems with the connection structure between the nacelle and the wing have occurred from time to time. For example, Boeing has received many fault reports of cracks in the lower edge strip of the engine pylon and cracks or bending of the connecting pins. Content of the Utility Model

[0003] In view of this, the utility model discloses a connection structure between an aircraft engine firewall and a wing, and the specific scheme is as follows:

[0004] A connection structure between an aircraft engine firewall and a wing, including a wing. The wing includes wing ribs, stringers, and wing skins. There are several groups of wing ribs arranged evenly along the wingspan direction. The wing skin covers the outside of the wing ribs. The stringers are arranged on the wing ribs and extend along the wingspan direction. It also includes an aircraft engine nacelle. The aircraft engine nacelle includes a front firewall, a rear firewall, an upper firewall, a box-shaped machined part, a second joint, a third joint, a strengthening link, and a strengthening rib;

[0005] The front firewall and the rear firewall are arranged at intervals. The upper firewall is arranged between the front firewall and the rear firewall. The front end of the upper firewall is connected to the front firewall, and the rear end of the upper firewall is connected to the rear firewall. The second joint is arranged on the rear end face of the front firewall, and the third joint is arranged on the front end face of the rear firewall. A strengthening link is connected between the second joint and the third joint;

[0006] The box-shaped machined part is arranged inside the wing. The box-shaped machined part is of a square structure and is riveted to the stringers and the wing ribs.

[0007] The reinforcing rib is of a triangular structure and is arranged on the rear end face of the rear firewall. The front end of the reinforcing rib, the rear firewall, and the third joint are connected by screws. The upper end of the reinforcing rib, the wing skin, and the box-shaped machined part are connected by screws.

[0008] As a supplement to the technical solution of the present utility model, the box-shaped machined part is of a groove-like structure with an open upper part, and reinforcing ribs are arranged on the lower bottom surface of its groove.

[0009] As a supplement to the technical solution of the present utility model, the aircraft engine nacelle further includes a first joint, the first joint is arranged on the front end face of the front firewall, and the wing further includes an I-beam and a transition piece;

[0010] The I-beam is arranged at the front end of the rib. The transition piece is an L-shaped structure composed of two mutually perpendicular plate surfaces. Its horizontal plate surface is connected to the I-beam, and the vertical plate surface is connected to the rib. The I-beam is connected to the first joint and the front firewall by bolts.

[0011] As a supplement to the technical solution of the present utility model, the aircraft engine nacelle further includes a first support rib. The lower bottom end of the first support rib is provided with a flange. The first support rib is screwed to the upper end face of the upper firewall through the flange at its lower bottom end. The front end of the first support rib is riveted to the rear end face of the front firewall, and the upper end of the first support rib is riveted to the wing skin.

[0012] As a supplement to the technical solution of the present utility model, the aircraft engine nacelle further includes a second support rib. The second support rib is vertically arranged on the upper firewall, and the lower end of the second support rib is provided with a flange. The second support rib is screwed to the upper end face of the upper firewall through the flange at its lower end, and the upper end of the second support rib is riveted to the wing skin.

[0013] As a supplement to the technical solution of the present utility model, the aircraft engine nacelle further includes an engine rear suspension point mounting box. A vertically opened through hole is provided on the upper firewall. The lower bottom surface of the engine rear suspension point mounting box is provided with a groove. The engine rear suspension point mounting box is located above the through hole on the upper firewall, and the lower end of the engine rear suspension point mounting box is connected to the upper firewall, and the upper end of the engine rear suspension point mounting box is connected to the wing skin.

[0014] Beneficial effects: The present utility model discloses a connection structure between an engine nacelle and a wing, which makes the connection strength between the two higher. The front firewall and the rear firewall are reinforced through a reinforcing connecting rod, and at the same time, the cooperation between the third joint and the reinforcing rib realizes the connection with the wing to support the wing. The load of the wing on the rear firewall is transmitted to the reinforcing connecting rod through the cooperation of the third joint and the reinforcing rib, without damaging the structure of the rear firewall, and the connection structure is more stable. In addition, through the connection relationship between the first joint, the front firewall, and the wing rib, the load of the wing can be transmitted to the mounting joint structure through the front firewall and the first joint, making the structure more stable. Brief Description of the Drawings

[0015] Figure 1 It is a three-dimensional structure schematic diagram of the present utility model.

[0016] Figure 2 It is a schematic diagram of the wing structure.

[0017] Figure 3 It is a schematic diagram of the wing structure.

[0018] Figure 4 It is a three-dimensional structure schematic diagram of the present utility model.

[0019] Figure 5 It is a three-dimensional structure schematic diagram of the present utility model.

[0020] Figure 6 It is a schematic diagram of the firewall structure.

[0021] Figure 7 It is a schematic diagram of the firewall structure.

[0022] Figure 8 It is a schematic diagram of the wing structure.

[0023] Figure 9 It is a schematic diagram of the wing structure.

[0024] In the figure: 1. Wing; 2. Wing rib; 3. Longeron; 4. Wing skin; 5. Aircraft engine nacelle; 6. Front firewall; 7. Rear firewall; 8. Upper firewall; 9. First joint; 10. Second joint; 11. Third joint; 12. Box-shaped machined part; 13. Reinforcing connecting rod; 14. Reinforcing rib; 15. I-beam; 16. Adapter; 17. First support rib; 18. Second support rib; 19. Engine rear suspension point mounting box. Detailed Embodiment

[0025] In the description of the present utility model, it should be understood that the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In the description of the present utility model, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically defined.

[0026] In the present utility model, unless otherwise clearly specified and defined, the terms "mounted", "connected", "connected to", "fixed", etc. shall be construed in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection, or communicable with each other; it may be directly connected, or indirectly connected through an intermediate medium, and may be the communication inside two components or the interaction relationship between two components, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0027] As Figures 1 to 9 shown, the connection structure between the aircraft engine firewall and the wing includes the aircraft engine nacelle 5 and the wing 1.

[0028] As Figure 2 、 Figure 3 shown, the aircraft wing 1 includes wing ribs 2, stringers 3, and wing skin 4. The wing ribs 2 are the transverse load-bearing skeletons of the wing 1, are provided with several groups and are evenly arranged along the wingspan direction, generally conform to the shape of the airfoil, maintain the cross-sectional shape of the wing 1, and the wing skin 4 covers the outside of the wing ribs 2. The stringers are members extending along the wingspan direction. Grooves for the stringers 3 to pass through are provided in the upper and lower parts of the wing ribs 2. The stringers 3 pass through the grooves on the wing ribs 2 and are connected to the wing ribs 2. The wing ribs 2 and the stringers 3 form a lattice-like structure inside the wing 1, improving the torsional resistance of the wing 1.

[0029] As Figures 4 to 7 shown, the aircraft engine nacelle 5 includes a front firewall 6, a rear firewall 7, an upper firewall 8, a box-shaped machining part 12, a second joint 10, a third joint 11, a strengthening link 13, a strengthening rib 14, and a box-shaped machining part 12.

[0030] The front firewall 6 and the rear firewall 7 are spaced apart. The upper firewall 8 is arranged between the front firewall 6 and the rear firewall 7. The front end of the upper firewall 8 is connected to the front firewall 6, and the rear end of the upper firewall 8 is connected to the rear firewall 7. The second joint 10 is arranged on the rear end face of the front firewall 6, and the third joint 11 is arranged on the front end face of the rear firewall 7. A strengthening link 13 is connected between the second joint 10 and the third joint 11 to improve the overall stability of the structure through the strengthening link 13.

[0031] The box-shaped machine-added part 12 is arranged inside the wing 1. The box-shaped machine-added part has a square structure and is arranged between two adjacent longerons 3 and is riveted to the two longerons 3 respectively. Specifically, the front end of the box-shaped machine-added part 12 is connected to the first longeron 3, and the rear end of the box-shaped machine-added part 12 is connected to the second longeron 3. The side of the box-shaped machine-added part 12 is riveted to the rib 2.

[0032] The reinforcing rib 14 has a triangular structure. The reinforcing rib 14 is arranged on the rear end face of the rear firewall 7. The front end of the reinforcing rib 14, the rear firewall 7, and the third joint 11 are connected by screws. The upper end of the reinforcing rib 14, the wing skin 4, and the box-shaped machine-added part 12 are connected by screws. The reinforcing rib 14 is used as a connecting part between the rear firewall 7 plate and the wing 1. Setting it as a triangular structure improves the support stability of the reinforcing rib 14.

[0033] In the traditional technical solution, usually, an opening is made on the rear firewall 7, and then the front end of the reinforcing link 13 is connected to the front firewall 6, and the rear end of the reinforcing link 13 passes through the opening on the rear firewall 7 and is connected to the wing 1. To achieve the sealing of the rear firewall 7, a fireproof sealing material needs to be arranged on the outer periphery of the reinforcing link 13 at the opening position of the rear firewall 7. The above process requires opening the rear firewall 7 and setting a fireproof sealing material, which is cumbersome and has poor effects. In addition, there is no reinforcing structure between the front firewall 6 and the rear firewall 7, and the structural stability is poor.

[0034] In the present utility model, through the setting of the above technical solution, it is realized that the front firewall 6 and the rear firewall 7 are strengthened through the reinforcing link 13. At the same time, the cooperation of the third joint 11 and the reinforcing rib 14 is used to connect with the wing 1 to support the wing 1. The load of the wing 1 on the rear firewall 7 and the cooperation of the third joint 11 and the reinforcing rib 14 are transmitted to the reinforcing link 13, without damaging the structure of the rear firewall 7, and the connection structure has stronger stability.

[0035] As a supplement to the above technical solution, the box-shaped machine-added part 12 has a groove-like structure with an open upper part. Its side is used to connect with the longeron 3 and the rib 2. Reinforcing ribs are arranged on the bottom surface of the box-shaped machine-added part 12 to improve its structural stability.

[0036] As a preferred technical solution of the present utility model, the aircraft engine nacelle 5 further includes a first joint 9. The first joint 9 is arranged on the front end face of the front firewall 6. The first joint 9, the front firewall 6, and the rib 2 of the wing 1 are connected by bolts. The first joint 9 is used to connect with the mounting frame of the engine nacelle through a mounting joint structure. The mounting frame is arranged on the front side of the front firewall and is used to connect with the front suspension point of the aircraft engine. Through the above setting, it is realized that the load of the wing 1 can be transmitted to the mounting joint structure through the front firewall 6 and the first joint 9, making the structure more stable.

[0037] As shown in Figure 8 , Figure 9 and

[0038] shown, as a preferred technical solution of the present utility model, the wing further includes an I-beam 15, an adapter 16,

[0039] The I-beam 15 is arranged at the front end of the rib. The adapter 16 is an L-shaped structure composed of two mutually perpendicular plate surfaces. Its horizontal plate surface is connected to the I-beam 15, and the vertical plate surface is connected to the rib 2. Two groups of I-beams 15 should be provided and are respectively arranged at both ends of the I-beam 15 in the length direction for respectively connecting the two ribs 2 to the I-beam 15. The I-beam 15 is connected to the first joint 9 and the front firewall 6 by bolts. To reduce the weight of the front firewall, a thin plate with a relatively thin thickness is selected for the front firewall. Since the first joint is used to connect to the mounting node, in order to avoid deformation of the front firewall under force, an I-beam is provided so that the load applied by the first joint can be directly transmitted to the wing through the I-beam, improving the structural strength.

[0040] As a preferred technical solution of the present utility model, the aircraft engine nacelle 5 further includes a first support rib 17. The lower end of the first support rib 17 is provided with a flange. The first support rib 17 is screwed to the upper end surface of the upper firewall 8 through the flange at its lower end. The front end of the first support rib 17 is riveted to the rear end surface of the front firewall 6, and the upper end of the first support rib 17 is riveted to the wing skin 4.

[0041] Two groups of the first support ribs 17 are provided and arranged at intervals.

[0042] By providing the first support rib 17, the connection strength between the engine nacelle and the wing 1 is further improved.

[0043] As a preferred technical solution of the present utility model, the aircraft engine nacelle 5 further includes a second support rib 18. The second support rib 18 is vertically arranged on the upper firewall 8, and the lower end of the second support rib 18 is provided with a flange. The second support rib 18 is screwed to the upper end surface of the upper firewall 8 through the flange at its lower end, and the upper end of the second support rib 18 is riveted to the wing skin 4.

[0044] Two groups of the second support ribs 18 are provided, and the length direction of the second support rib 18 is perpendicular to the length direction of the first support rib 17. The length direction of the first support rib 17 is perpendicular to the plane where the front firewall 6 is located, and the length direction of the second support rib 18 is parallel to the plane where the front firewall 6 is located.

[0045] Two groups of the second support ribs 18 are provided and are arranged outside the first support rib 17. The outside of the first support rib 17 is the side close to the edge of the upper firewall 8. The side edge of the second support rib 18 is provided with a flange for connecting to the skin of the engine nacelle.As a preferred technical solution of the present utility model, the aircraft engine nacelle 5 further includes an engine rear suspension point mounting box 19. A through hole is vertically formed on the upper firewall 8. A groove is provided on the lower bottom surface of the engine rear suspension point mounting box 19. The engine rear suspension point mounting box 19 is located above the through hole on the upper firewall 8, and the lower end of the engine rear suspension point mounting box 19 is connected to the upper firewall 8. The connection position between the engine rear suspension point mounting box 19 and the upper firewall 8 is located on the outer periphery of the through hole on the upper firewall 8, so that the through hole on the upper firewall 8 is communicated with the inner space of the groove of the engine rear suspension point mounting box 19. The rear suspension point of the engine is connected to the engine rear suspension point mounting box 19 through an adapter 16. One end of the adapter 16 is connected to the rear suspension point of the engine, and the other end passes through the through hole on the upper firewall 8 and is connected to the engine rear suspension point mounting box 19. The upper end of the engine rear suspension point mounting box 19 is connected to the wing skin 4.

[0046] In the above structure, through the setting of the engine rear suspension point mounting box 19, the isolation between the second fire zone and the wing 1 is realized. At the same time, through the design of the engine rear suspension point mounting box 19, the connection between the engine and the wing 1 is realized, the connection strength between the engine nacelle and the wing 1 is improved, the load borne by the upper firewall 8 is reduced, and the structural stability of the upper firewall 8 is improved.

[0047] The above is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, makes equivalent substitutions or changes, and should be covered within the protection scope of the present invention.

Claims

1. An aircraft engine firewall and wing connection structure, comprising a wing (1), wherein the wing (1) comprises a wing rib (2), a long stringer (3), and a wing skin (4), wherein the wing rib (2) is provided in a plurality of groups and is evenly arranged along the wingspan direction, the wing skin (4) is covered on the outside of the wing rib (2), and the long stringer (3) is provided on the wing rib (2) and extends along the wingspan direction; It is characterized in that Also included is an aircraft engine nacelle (5), wherein the aircraft engine nacelle (5) comprises a front firewall (6), a rear firewall (7), an upper firewall (8), a box-shaped machine addition (12), a second joint (10), a third joint (11), a reinforcing connecting rod (13), and a reinforcing rib (14); The front firewall (6) and the rear firewall (7) are arranged at intervals, the upper firewall (8) is arranged between the front firewall (6) and the rear firewall (7), the front end of the upper firewall (8) is connected to the front firewall (6), and the rear end of the upper firewall (8) is connected to the rear firewall (7), the second joint (10) is arranged on the rear end surface of the front firewall (6), the third joint (11) is arranged on the front end surface of the rear firewall (7), and a reinforcing connecting rod (13) is connected between the second joint (10) and the third joint (11); The box-shaped machined part (12) is arranged inside the wing (1), has a square structure and is riveted to the long stringer (3) and the wing rib (2). The reinforcing rib (14) is a triangular structure. The reinforcing rib (14) is arranged on the rear end surface of the rear firewall (7). The front end of the reinforcing rib (14), the rear firewall (7), and the third joint (11) are connected by screws. The upper end of the reinforcing rib (14), the wing skin (4), and the box-shaped machined part (12) are connected by screws.

2. The aircraft engine firewall and wing connection structure according to claim 1, characterized in that: The box-shaped machine added part (12) is a groove-shaped structure with an upper opening, and a reinforcing rib is arranged on the lower bottom surface of the groove.

3. The aircraft engine firewall and wing connection structure according to claim 1, characterized in that: The aircraft engine nacelle (5) further comprises a first joint (9), wherein the first joint (9) is arranged on the front end surface of the front firewall (6), and the wing (1) further comprises an I-beam (15) and an adapter (16); The I-beam (15) is arranged at the front end of the wing rib (2); the adapter (16) is an L-shaped structure composed of two mutually perpendicular plate surfaces, wherein the horizontal plate surface is connected to the I-beam (15) and the vertical plate surface is connected to the wing rib (2); the I-beam (15) is connected to the first joint (9) and the front firewall (6) by bolts.

4. The aircraft engine firewall and wing connection structure according to claim 1, characterized in that: The aircraft engine nacelle (5) further comprises a first supporting rib (17), the lower end of the first supporting rib (17) being provided with a bent edge, the first supporting rib (17) being screwed to the upper end face of the upper firewall (8) via the bent edge of the lower end, the front end of the first supporting rib (17) being riveted to the rear end face of the front firewall (6), and the upper end of the first supporting rib (17) being riveted to the wing skin (4).

5. The aircraft engine firewall and wing connection structure according to claim 1, characterized in that: The aircraft engine nacelle (5) further comprises a second supporting rib (18), the second supporting rib (18) being vertically arranged on the upper firewall (8), and the lower end of the second supporting rib (18) being provided with a bent edge, the second supporting rib (18) being screwed to the upper end surface of the upper firewall (8) through the bent edge at its lower end, and the upper end of the second supporting rib (18) being riveted to the wing skin (4).

6. The aircraft engine firewall and wing connection structure according to claim 1, characterized in that: The aircraft engine nacelle (5) also includes an engine rear suspension point installation box (19), the upper firewall (8) is provided with a through hole opened vertically, the lower bottom surface of the engine rear suspension point installation box (19) is provided with a groove, the engine rear suspension point installation box (19) is located above the through hole on the upper firewall (8), and the lower end of the engine rear suspension point installation box (19) is connected to the upper firewall (8), and the upper end of the engine rear suspension point installation box (19) is connected to the wing skin (4).

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