Integrated engine nacelle hanging structure

Abstract

The utility model provides an integrated engine nacelle hanging structure which comprises a curved surface bottom plate integrally arranged with a fairing, the bottom plate is fixed below the fairing, longitudinal beams integrally arranged with the bottom plate are symmetrically installed on the two sides of the inner side of the bottom plate in the course direction, and the longitudinal beams are fixed on the bottom plate. The front end of the longitudinal beam is far away from the gravity center of the fairing, the rear end of the longitudinal beam is close to the gravity center of the fairing, and a front lifting lug connector and a rear lifting lug connector which are integrally arranged with the longitudinal beam are installed in the vertical direction of the front end and the rear end of the longitudinal beam respectively. The bottom plate, the longitudinal beam, the front lifting lug connector and the rear lifting lug connector form a nacelle used for containing an engine, and the front lifting lug connector and the rear lifting lug connector are connected with a front ring and a rear ring of the engine respectively through installation connectors of the engine so that the engine can be hung in the nacelle. The hanging structure has the advantages of being short in assembly period, light in weight, direct in force transmission path and easy to maintain.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft structure technology, and in particular relates to an integrated engine nacelle sling structure. Background Technology

[0002] The engine nacelle is the interface between the engine and the wing. It is responsible for hoisting the engine, transferring the engine load, and providing a passage for fuel, environmental control, electrical, hydraulic and other systems pipelines between the engine and the aircraft wing.

[0003] While traditional engine nacelle pylon structures are stable and reliable, they also have several drawbacks: ① Long assembly cycle: Traditional engine nacelle pylon structures typically consist of multiple complex components, requiring complex assembly processes, increasing development costs and slowing down development speed. ② Excessive weight: The use of various types of parts in traditional engine nacelle pylon structures necessitates consideration of the connecting structures and fasteners between components, resulting in excessive weight of the structure and fasteners, increasing the overall weight of the aircraft and affecting fuel efficiency and flight performance. ③ Indirect force transmission path: Due to the combination of various structural components, traditional engine nacelle pylon structures are prone to indirect force transmission paths, leading to structural design redundancy. ④ Difficult maintenance: Traditional engine nacelle pylon structures typically consist of multiple complex components, requiring disassembly and reassembly for maintenance, which is time-consuming and prone to damage or incorrect installation.

[0004] Therefore, there is an urgent need to provide an integrated engine nacelle suspension structure that can overcome the above-mentioned technical problems. Utility Model Content

[0005] This utility model addresses the shortcomings of existing technologies by providing an integrated engine nacelle suspension structure, which achieves the goals of short assembly cycle, light structural weight, direct force transmission path, and simple maintenance.

[0006] To achieve the above objectives, the present invention provides the following technical solution:

[0007] An integrated engine nacelle mounting structure includes a curved base plate integrally formed with the fairing and fixed below the fairing. Longitudinal beams integrally formed with the base plate are symmetrically mounted on both inner sides of the base plate along the flight direction. The front ends of the longitudinal beams are away from the center of gravity of the fairing, and the rear ends are close to the center of gravity of the fairing. Front and rear lifting lugs integrally formed with the longitudinal beams are respectively mounted on the front and rear ends of the longitudinal beams in the vertical direction. The base plate, the longitudinal beams, the front lifting lugs, and the rear lifting lugs form a nacelle for accommodating the engine. The front and rear lifting lugs are connected to the engine's front and rear rings respectively via engine mounting joints to complete the engine mounting within the nacelle.

[0008] As a preferred embodiment of the integrated engine nacelle suspension structure of this utility model, the front lifting lug joint is provided with a front lifting lug hole for connecting with the front ring of the engine, and the rear lifting lug joint is provided with a rear lifting lug hole for connecting with the rear ring of the engine.

[0009] As a preferred embodiment of the integrated engine nacelle suspension structure of this utility model, a plurality of light-reducing grooves are arranged on the inner side of the base plate along the heading direction and extending to the bottom of the fairing, and a reinforcing rib is installed between two adjacent light-reducing grooves.

[0010] As a preferred embodiment of the integrated engine nacelle suspension structure of this utility model, an open maintenance compartment connected to the fairing is provided above the base plate, and the maintenance compartment communicates with the base plate.

[0011] As a preferred embodiment of the integrated engine nacelle mounting structure of this utility model, countersunk holes are provided at the four corners of the upper end face of the fairing end, and the upper end face of the fairing end is fixedly connected to the underside of the wing surface by fastening screws passing through the countersunk holes.

[0012] As a preferred embodiment of the integrated engine nacelle suspension structure of this utility model, a plurality of light-reducing grooves are distributed on the upper end surface of the fairing end.

[0013] As a preferred embodiment of the integrated engine nacelle suspension structure described in this utility model, the suspension structure is made of 38CrA alloy structural steel.

[0014] Compared with the prior art, the present invention will have at least the following beneficial effects:

[0015] ① The engine nacelle suspension structure adopts a one-piece fabrication structure made of 38CrA alloy structural steel. This effectively reduces assembly time, structural weight, and maintenance complexity while meeting the strength and rigidity requirements of the suspension structure, ensuring its stable and reliable operation during actual flight. Furthermore, the one-piece fabrication design using 38CrA alloy structural steel simplifies the assembly of structural components, making the force transmission path more direct and reducing structural design redundancy. ② The weight-reducing groove can reduce the overall weight of the suspension structure to a certain extent, lowering the overall weight of the aircraft, improving fuel efficiency, and enhancing flight performance. ③ The maintenance bay design facilitates personnel maintenance of the engine nacelle suspension structure. Maintenance does not require disassembly or reassembly, avoiding errors and damage during maintenance, effectively improving maintenance efficiency and reducing maintenance time costs. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are merely exemplary embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort, wherein:

[0017] Figure 1 This is a schematic diagram of the integrated engine nacelle suspension structure of this utility model;

[0018] Figure 2 This is another perspective schematic diagram of the integrated engine nacelle suspension structure of this utility model;

[0019] Figure 3 for Figure 1 A bottom view;

[0020] Figure 4 for Figure 1 Top view.

[0021] The reference numerals in the figures include:

[0022] 1. Base plate; 2. Fairing; 3. Longitudinal beam; 4. Front lifting lug connector; 40. Front lifting lug hole; 5. Rear lifting lug connector; 50. Rear lifting lug hole; 6. Nacelle; 7. Lightening groove; 8. Reinforcing rib; 9. Maintenance compartment; 10. Upper end face; 11. Countersunk hole. Detailed Implementation

[0023] The technical solutions in the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are merely exemplary embodiments of this utility model, and not the only embodiments.

[0024] like Figures 1 to 4As shown, the integrated engine nacelle mounting structure includes a curved base plate 1 integrally formed with the fairing 2. The base plate 1 is I-shaped and fixed below the fairing 2. Longitudinal beams 3, integrally formed with the base plate 1, are symmetrically installed on both sides of the inner side of the base plate 1 along the flight direction. The front end of the longitudinal beams 3 is away from the center of gravity of the fairing 2, and the rear end of the longitudinal beams 3 is close to the center of gravity of the fairing 2. A front lifting lug joint 4 and a rear lifting lug joint 5, integrally formed with the longitudinal beams 3, are respectively installed in the vertical direction at the front and rear ends of the longitudinal beams 3. The base plate 1, longitudinal beams 3, front lifting lug joint 4, and rear lifting lug joint 5 form a nacelle 6 for accommodating the engine. The front lifting lug joint 4 and rear lifting lug joint 5 are connected to the engine's front and rear rings respectively via engine mounting joints to complete the engine mounting within the nacelle 6. To facilitate the connection between the front hanger lug connector 4 and the front ring of the engine, a front hanger lug hole 40 for connection with the front ring of the engine is provided on the front hanger lug connector 4. The number of front hanger lug holes 40 can be set to several. In this embodiment, the number of front hanger lug holes 40 is three. To further enhance the connection and fixing effect between the front hanger lug connector 4 and the front ring, the front hanger lug holes 40 are distributed in a triangular shape. Similarly, to facilitate the connection between the rear hanger lug connector 5 and the rear ring of the engine, a rear hanger lug hole 50 for connection with the rear ring of the engine is provided on the rear hanger lug connector 5. The number of rear hanger lug holes 50 can also be set to several. In this embodiment, the number of rear hanger lug holes 50 is also three. To further enhance the connection and fixing effect between the rear hanger lug connector 5 and the rear ring, the rear hanger lug holes 50 are distributed in an inverted triangular shape.

[0025] In this embodiment, the engine nacelle 6 suspension structure is made of 38CrA alloy structural steel. More specifically, the engine nacelle 6 suspension structure in this embodiment adopts an integrated 38CrA alloy structural steel structure. This design can effectively reduce the assembly cycle, structural weight, and maintenance complexity of the suspension structure while meeting the strength and rigidity requirements of the suspension structure. It can ensure that the suspension structure can play its role stably and reliably in actual flight. At the same time, the design of the integrated 38CrA alloy structural steel structure simplifies the assembly of the structural components of the suspension structure, makes the force transmission path more direct, and reduces structural design redundancy.

[0026] like Figure 3 As shown, in order to reduce the overall weight of the suspension structure and meet the requirements of lightweight, sealing performance and strength, multiple weight-reducing grooves 7 are arranged on the inner side of the base plate 1 along the flight direction and extending to the bottom of the fairing 2. The design of multiple weight-reducing grooves 7 can reduce the overall weight of the suspension structure to a certain extent, reduce the overall weight of the aircraft, improve fuel efficiency and improve the flight performance of the aircraft. The setting of weight-reducing grooves 7 reduces the overall weight of the suspension structure. In order to improve the stability and safety of the suspension structure, reinforcing ribs 8 are installed between two adjacent weight-reducing grooves 7.

[0027] like Figure 1 and Figure 3 As shown, an open maintenance compartment 9 connected to the fairing 2 is provided above the base plate 1. The maintenance compartment 9 is connected to the base plate 1. This design facilitates personnel to perform equipment maintenance on the engine nacelle 6 suspension structure. During maintenance, it is not necessary to disassemble the suspension structure or reassemble it after maintenance, which avoids errors and damage to the equipment during maintenance, effectively improving maintenance efficiency and reducing maintenance time costs.

[0028] like Figure 4 As shown, countersunk holes 11 are provided at the four corners of the upper end face 10 at the end of the fairing 2. The upper end face 10 at the end of the fairing 2 is fixedly connected to the underside of the wing surface by fastening screws passing through the countersunk holes 11. This countersunk design can enhance the connection effect between the fairing 2 and the underside of the wing surface. At the same time, this design can reduce the engine fuel consumption of the sling structure, improve the aerodynamic drag coefficient of the aircraft, and thus avoid the strong aerodynamic drag generated by the aircraft during flight from affecting the performance of the sling structure. It can also improve the economy of the aircraft.

[0029] like Figure 4 As shown, similarly, in order to further reduce the overall weight of the suspension structure, multiple weight-reducing grooves 7 are distributed on the upper end face 10 of the fairing 2 above the base plate 1. This reduces the weight when the upper end face 10 of the fairing 2 is connected to the wing surface. Similarly, multiple reinforcing ribs 8 are also provided around the weight-reducing grooves 7 on the upper end face 10 of the fairing 2 to enhance the stability and safety of the weight-reducing grooves 7.

[0030] The above description is merely a preferred embodiment of this utility model. The protection scope of this utility model is not limited to the above embodiments. All technical solutions falling within the scope of this utility model's concept are protected. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principle of this utility model should also be considered within the protection scope of this utility model.

Claims

1. An integrated engine nacelle suspension structure, characterized in that, The suspension structure includes a curved base plate (1) integrally formed with the fairing (2). The base plate (1) is fixed below the fairing (2). On the inner sides of the base plate (1), longitudinal beams (3) integrally formed with the base plate (1) are symmetrically installed along the flight direction. The front end of the longitudinal beam (3) is far away from the center of gravity of the fairing (2), and the rear end of the longitudinal beam (3) is close to the center of gravity of the fairing (2). The front end and rear end of the longitudinal beam (3) are respectively installed with a front lifting lug joint (4) and a rear lifting lug joint (5) integrally formed with the longitudinal beam (3) in the vertical direction. The base plate (1), the longitudinal beam (3), the front lifting lug joint (4) and the rear lifting lug joint (5) form a nacelle (6) for accommodating the engine. The front lifting lug joint (4) and the rear lifting lug joint (5) are connected to the front ring and the rear ring of the engine respectively through the engine mounting joint to complete the suspension of the engine in the nacelle (6).

2. The integrated engine nacelle suspension structure according to claim 1, characterized in that, The front hanger connector (4) is provided with a front hanger hole (40) for connecting with the front ring of the engine, and the rear hanger connector (5) is provided with a rear hanger hole (50) for connecting with the rear ring of the engine.

3. The integrated engine nacelle suspension structure according to claim 1, characterized in that, The bottom plate (1) has a plurality of light-reducing grooves (7) arranged along the heading direction and extending to the bottom of the fairing (2), and a reinforcing rib (8) is installed between two adjacent light-reducing grooves (7).

4. The integrated engine nacelle suspension structure according to claim 3, characterized in that, An open maintenance compartment (9) connected to the fairing (2) is provided above the base plate (1), and the maintenance compartment (9) communicates with the base plate (1).

5. The integrated engine nacelle suspension structure according to claim 4, characterized in that, The upper end face (10) of the fairing (2) is provided with countersunk holes (11) at the four corners. The upper end face (10) of the fairing (2) is fixedly connected to the underside of the wing surface by fastening screws passing through the countersunk holes (11).

6. The integrated engine nacelle suspension structure according to claim 5, characterized in that, The upper end face (10) of the fairing (2) is provided with a plurality of light-reducing grooves (7).

7. The integrated engine nacelle suspension structure according to claim 1, characterized in that, The suspension structure is made of 38CrA alloy structural steel.

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