Elastic connecting structure for aircraft nacelle and engine exhaust nozzle

Abstract

The utility model belongs to the technical field of connection design of an aircraft nacelle and an engine exhaust nozzle, and particularly relates to an elastic connection structure of the aircraft nacelle and the engine exhaust nozzle. The elastic connecting pieces are arranged between the aircraft nacelle and the engine exhaust nozzle in the circumferential direction to form a whole-circle structure. The elastic connecting piece comprises a front lap joint area, a middle transition area, a rear fixing area and a tail end extending area which are connected in sequence, and all the areas are in smooth transition. The front lap joint area is in a step shape and used for being connected to the inner side of an annular lap joint boss arranged in an aircraft nacelle in a lap joint mode. The middle transition area is used for being attached to the inner side of an aircraft nacelle; the rear fixing area extends out of the rear end of the aircraft nacelle and is used for being fixed to the outer side of an engine exhaust nozzle. The tail end extending area is used for being attached to the outer side of an engine exhaust nozzle and is conical.

Description

Technical Field

[0001] This application belongs to the technical field of aircraft nacelle and engine exhaust nozzle connection design, specifically relating to an elastic connection structure between an aircraft nacelle and an engine exhaust nozzle. Background Technology

[0002] Both the aircraft fuselage structure and the engine external structure are rigid structures. In addition to the fixed connections, there are some mechanically interconnected parts that need to be connected with a structure with compensation function. This is to compensate for the relative displacement and installation deviation between the aircraft fuselage structure and the engine external structure through deformation during daily use, so as to prevent rigid collision and wear and structural damage.

[0003] The aircraft nacelle and engine exhaust nozzle are a part that needs to be connected by a structure with compensation function. However, the current aircraft nacelle and engine exhaust nozzle cannot effectively compensate for the relative displacement and installation deviation between the aircraft nacelle and engine exhaust nozzle. Moreover, the structure is complex, inconvenient to disassemble and assemble, and cannot guarantee the smoothness of the fuselage shape, which seriously damages the aerodynamic shape of the aircraft.

[0004] This application is made in view of the aforementioned technical deficiencies. Utility Model Content

[0005] The purpose of this application is to provide a flexible connection structure between an aircraft nacelle and an engine exhaust nozzle, in order to overcome or mitigate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] An elastic connection structure between an aircraft nacelle and an engine exhaust nozzle includes an elastic connecting piece;

[0008] There are multiple elastic connecting pieces, which are arranged circumferentially between the aircraft nacelle and the engine tail nozzle to form a complete ring structure.

[0009] The elastic connecting piece includes a front overlapping area, a middle transition area, a rear fixing area, and an end extension area connected in sequence, with smooth transitions between each area;

[0010] The front overlapping area is stepped, which is used to overlap the inner side of the annular overlapping protrusion set in the aircraft nacelle.

[0011] The intermediate transition zone is used to abut the inside of the aircraft nacelle;

[0012] The rear fixing area extends from the rear of the aircraft nacelle and is used to fix it to the outside of the engine exhaust nozzle;

[0013] The end extension area is used to attach to the outside of the engine exhaust nozzle and is cone-shaped.

[0014] According to at least one embodiment of this application, in the above-described elastic connection structure between the aircraft nacelle and the engine exhaust nozzle, the front overlapping area, the middle transition area, the rear fixing area, and the end extension area of ​​the elastic connecting piece are integrally formed.

[0015] According to at least one embodiment of this application, in the above-described elastic connection structure between the aircraft nacelle and the engine exhaust nozzle, the elastic connecting piece is made of aluminum alloy.

[0016] According to at least one embodiment of this application, in the above-described elastic connection structure between the aircraft nacelle and the engine exhaust nozzle, the rear fixed area and the outer side of the engine exhaust nozzle are connected by riveting.

[0017] According to at least one embodiment of this application, in the above-described elastic connection structure between the aircraft nacelle and the engine exhaust nozzle, the rear fixed area and the outer side of the engine exhaust nozzle are connected by a screw connection.

[0018] According to at least one embodiment of this application, in the above-described elastic connection structure between the aircraft nacelle and the engine exhaust nozzle, the rear fixed area and the outer side of the engine exhaust nozzle are connected by welding.

[0019] This application has at least the following beneficial technical effects:

[0020] A flexible connection structure between an aircraft nacelle and an engine exhaust nozzle is provided. The design utilizes the deformation capacity of the stepped front overlap area of ​​the flexible connecting piece to effectively compensate for the relative displacement and installation deviation between the aircraft nacelle and the engine exhaust nozzle. The intermediate transition area ensures the seal between the aircraft nacelle and the engine exhaust nozzle. The structure is simple, easy to disassemble and assemble, and can ensure the smoothness of the fuselage shape and its aerodynamic shape. Attached Figure Description

[0021] Figure 1 This is a perspective view of the elastic connecting piece provided in the embodiments of this application;

[0022] Figure 2 This is a top view of the elastic connecting piece provided in the embodiment of this application;

[0023] Figure 3 This is a side view of the elastic connecting piece provided in the embodiment of this application;

[0024] Figure 4 This is a front view of the elastic connecting piece provided in the embodiments of this application;

[0025] Figure 5 This is a schematic diagram of the structure of the elastic connecting piece provided in the embodiments of this application;

[0026] Figure 6 This is a schematic diagram of the elastic connecting piece provided in the embodiments of this application being installed in conjunction with an aircraft nacelle;

[0027] in:

[0028] 1-Elastic connecting piece;

[0029] 11-Front overlap area; 12-Middle transition area; 13-Rear fixing area; 14-End extension area.

[0030] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0031] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0032] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms indicating direction used in this application description are used only to indicate relative direction or positional relationship; when the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "comprising" as used in this application description indicates that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, but does not exclude other elements or objects.

[0033] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0034] A flexible connection structure between an aircraft nacelle and an engine exhaust nozzle includes a flexible connecting piece 1, such as... Figure 1-4 As shown.

[0035] There are multiple elastic connecting pieces 1, which are arranged circumferentially between the aircraft nacelle and the engine exhaust nozzle to form a complete ring structure.

[0036] The elastic connecting piece 1 includes a front overlapping area 11, a middle transition area 12, a rear fixing area 13, and an end extension area 14 connected in sequence. The areas are smoothly transitioned and integrally formed. It can be made of aluminum alloy, such as... Figure 5 As shown.

[0037] The forward overlapping area 11 is stepped, designed to overlap the inner side of the annular overlapping boss located inside the aircraft nacelle, allowing for significant structural deformation, such as... Figure 6 As shown.

[0038] The intermediate transition zone 12 is used to abut against the inside of the aircraft nacelle.

[0039] The rear fixing area 13 extends from the rear end of the aircraft nacelle and is used to fix it to the outside of the engine exhaust nozzle. The connection between the rear fixing area 13 and the outside of the engine exhaust nozzle can be riveted, screwed or welded.

[0040] The terminal extension area 14 is used to attach to the outside of the engine exhaust nozzle. Its specific shape can be designed according to the actual needs of aircraft and engine weight, aerodynamics, low detectability, etc., and it can generally be designed as a cone.

[0041] The elastic connection structure between the aircraft nacelle and the engine exhaust nozzle disclosed in the above embodiments adopts a single cantilever fixation to realize the transition connection between the two rigid devices with a step difference, namely the aircraft nacelle and the engine exhaust nozzle. The compensation function for different areas and different degrees of curvature can be realized by adjusting the curvature of the transition surface of the elastic connection piece 1, the wall thickness δ, the material selection, as well as the size and number of pieces.

[0042] In the above-described embodiment, the elastic connection structure between the aircraft nacelle and the engine exhaust nozzle is designed to utilize the deformation capability of the stepped front overlap area 11 of the elastic connecting piece 1 to effectively compensate for the relative displacement and installation deviation between the aircraft nacelle and the engine exhaust nozzle. The intermediate transition area 12 is used to ensure the seal between the aircraft nacelle and the engine exhaust nozzle. The structure is simple, easy to disassemble and assemble, and can ensure the smoothness of the fuselage shape and its aerodynamic shape.

[0043] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of this application.

Claims

1. A flexible connection structure between an aircraft nacelle and an engine exhaust nozzle, characterized in that, Includes elastic connecting piece (1); There are multiple elastic connecting pieces (1), which are arranged circumferentially between the aircraft nacelle and the engine tail nozzle to form a complete ring structure; The elastic connecting piece (1) includes a front overlapping area (11), a middle transition area (12), a rear fixing area (13), and an end extension area (14) connected in sequence, with smooth transitions between each area; The front overlapping area (11) is stepped and is used to overlap the inner side of the annular overlapping protrusion set in the aircraft nacelle. The intermediate transition zone (12) is used to abut against the inside of the aircraft nacelle; The rear fixing area (13) extends from the rear end of the aircraft nacelle and is used to fix it to the outside of the engine exhaust nozzle; The end extension area (14) is used to abut against the outside of the engine tail nozzle and is cone-shaped.

2. The elastic connection structure between the aircraft nacelle and the engine exhaust nozzle according to claim 1, characterized in that, The front overlapping area (11), the middle transition area (12), the rear fixing area (13), and the end extension area (14) of the elastic connecting piece (1) are integrally formed.

3. The elastic connection structure between the aircraft nacelle and the engine exhaust nozzle according to claim 1, characterized in that, The elastic connecting piece (1) is made of aluminum alloy.

4. The elastic connection structure between the aircraft nacelle and the engine exhaust nozzle according to claim 1, characterized in that, The rear fixed area (13) is riveted to the outside of the engine tail nozzle.

5. The elastic connection structure between the aircraft nacelle and the engine exhaust nozzle according to claim 1, characterized in that, The rear fixed area (13) is connected to the outer side of the engine tail nozzle by a screw connection.

6. The elastic connection structure between the aircraft nacelle and the engine exhaust nozzle according to claim 1, characterized in that, The rear fixed area (13) is welded to the outside of the engine tail nozzle.

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