Aircraft back support nacelle lip opening and closing structure and aircraft

Abstract

The invention discloses an aircraft back support nacelle lip opening and closing structure and an aircraft. The aircraft back support nacelle lip opening and closing structure comprises two lip skin capable of being opened and closed, a supporting frame, a supporting partition plate, a lip opening and closing connecting rod mechanism and a locking mechanism. The lip skin comprises a first lip skin and a second lip skin; the supporting frame is fixedly arranged on the inner side of the first lip skin; the supporting partition plate is located between the first lip skin and the second lip skin and fixed to the upper surface of the wing. The lip opening and closing connecting rod mechanism is hinged to the supporting frame, and the supporting partition plate is hinged to the second lip skin. The lip opening and closing connecting rod mechanism comprises an elastic component, and the elastic component is located between the first lip skin and the second lip skin. The locking mechanism is in linkage fit with the first lip skin and the second lip skin. According to the lip opening and closing connecting rod mechanism, translation opening and closing of the lip are achieved through cooperation of the elastic component and the connecting rod, and a smoother opening and closing mode is provided for a back supporting type nacelle; the maintenance space of the wing surface can be further expanded through translation opening and closing, the maintenance efficiency can be improved when a nacelle and a lip are maintained, and the maintenance time is saved.

Description

Technical Field

[0001] The present invention relates to the field of aircraft structural design, and in particular to an opening and closing structure for the lip of an aircraft back support nacelle and an aircraft. Background Art

[0002] An aircraft engine is a device that provides power for an aircraft and is one of the core components of an aircraft. An aircraft engine is generally located below the wing or at the rear of the fuselage, and in a few aircraft, the engine is located above the leading edge of the wing (such as a propeller engine). However, when maintenance personnel inspect and repair the aircraft engine installed in these positions, it is very inconvenient, and the upper surface of the wing in the area where the engine airflow is ejected needs to be treated with high-temperature resistant materials and surface treatment; when the engine is hung below the wing, the height of the landing gear is relatively high, the overall height of the aircraft is too high, and the stability of the entire aircraft is also poor. In order to reduce the height of the landing gear and the overall height of the aircraft and increase stability, a back support engine structure has been developed. However, the existing back support engine structure still has problems such as a tight space on the upper surface of the wing in the array (multi-row engine) structure and a relatively tight installation space, so it is impossible to achieve overall disassembly and installation, resulting in difficult maintenance.

[0003] Therefore, there is an urgent need to provide a solution for the opening and closing structure of the lip of an aircraft back support nacelle. Summary of the Invention

[0004] In order to solve the above problems, the technical solution of the present invention provides an opening and closing structure for the lip of an aircraft back support nacelle and an aircraft, which can realize the rapid opening and closing of the back support engine structure and solve the problem of difficult maintenance.

[0005] According to the first aspect embodiment of the technical solution of the present invention, an opening and closing structure for the lip of an aircraft back support nacelle is provided, including: two lip skins that can be opened and closed, a support frame, a support partition, a lip opening and closing link mechanism, and a locking mechanism;

[0006] The lip skin includes a first lip skin and a second lip skin;

[0007] The support frame is fixedly arranged inside the first lip skin;

[0008] The support partition is located between the first lip skin and the second lip skin and is fixed on the upper surface of the wing;

[0009] The lip opening and closing link mechanism is respectively hinged to the support frame, the support partition, and the second lip skin;

[0010] The lip opening and closing link mechanism includes an elastic member, and the elastic member is located between the first lip skin and the second lip skin;

[0011] The locking mechanism is linked and cooperates with the first lip skin and the second lip skin.

[0012] In the above solution, the lip opening and closing link mechanism further includes a rotating frame and a driven link;

[0013] The rotating frame includes a driving link and a straight rod. One end of the driving link is hinged to the straight rod, and the other end is hinged to the middle part of the second lip skin;

[0014] The straight rod is hinged to the support partition;

[0015] One end of the driven link is hinged to the support partition, and the other end is hinged to the lower part of the lip skin;

[0016] The elastic member is hinged to the driving link.

[0017] In the above solution, one end of the driving link is an arc part, and the other end is a straight line part. The end of the arc part is hinged to the straight rod.

[0018] In the above solution, a connecting piece is provided on the arc part, and the elastic member is hinged to the driving link through the connecting piece.

[0019] In the above solution, when the lip skin is in the closed state, the elastic member is arranged obliquely upward along the end hinged to the driving link.

[0020] In the above solution, when the lip skin is in the closed state, the elastic member is compressed.

[0021] In the above solution, the locking mechanism includes a zip fastener and a handle;

[0022] The zip fastener fixes the bottoms of the first lip skin and the second lip skin respectively, and the handle is connected to the zip fastener.

[0023] In the above solution, the elastic member is a gas spring.

[0024] In the above solution, a sealing strip is provided at the edge of the first lip skin and / or the second lip skin at the opening and closing positions.

[0025] According to the second aspect embodiment of the technical solution of the present invention, an aircraft is provided, and the aircraft is provided with the lip opening and closing structure as described in any one of the above.

[0026] Advantages of the present invention:

[0027] An aircraft back support nacelle lip opening and closing structure and an aircraft disclosed by the present invention. The cooperation between the elastic component and the connecting rod of the lip opening and closing connecting rod mechanism realizes the translational opening and closing of the lip, providing a smoother opening and closing method for the back support nacelle; the translational opening and closing can further expand the space for wing surface maintenance of the aircraft, and can improve the maintenance efficiency and save maintenance time when maintaining the nacelle and the lip. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on the structures shown in these drawings.

[0029] Figure 1 Schematic diagram of the aircraft back support nacelle lip opening and closing structure disclosed by the present invention in the closed state;

[0030] Figure 2 Schematic diagram of the aircraft back support nacelle lip opening and closing structure disclosed by the present invention in the translational start state;

[0031] Figure 3 Schematic diagram of the aircraft back support nacelle lip opening and closing structure disclosed by the present invention in the opening and rising state;

[0032] Figure 4 Schematic diagram of the aircraft back support nacelle lip opening and closing structure disclosed by the present invention in the final opening state;

[0033] Figure 5 Enlarged view of the driving connecting rod and the elastic component of the aircraft back support nacelle lip opening and closing structure disclosed by the present invention;

[0034] Figure 6 Overall layout diagram of the lip opening and closing connecting rod mechanism of the aircraft back support nacelle lip opening and closing structure disclosed by the present invention;

[0035] Figure 7 Schematic diagram of the locking mechanism of the aircraft back support nacelle lip opening and closing structure disclosed by the present invention;

[0036] Figure 8 Global view of the aircraft back support nacelle disclosed by the present invention.

[0037] Wherein, driving connecting rod - 1; driven connecting rod - 2; elastic component - 3; connecting piece - 4; second lip skin - 5; support frame - 6; sealing strip - 7; straight rod - 8; handle - 9; zip fastener - 10.

[0038] The realization of the object, functional characteristics and advantages of the present invention will be further described with reference to the embodiments and the drawings. Detailed implementation manners

[0039] Here, exemplary embodiments will be described in detail, and examples thereof are shown in the accompanying drawings. When the following description refers to the accompanying drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The implementation manners described in the following exemplary embodiments do not represent all implementation manners consistent with the present disclosure. On the contrary, they are merely examples of devices and methods consistent with some aspects of the present disclosure as detailed in the appended claims.

[0040] The terms "first", "second", etc. in the specification and claims of the present disclosure are used to distinguish similar objects and do not necessarily describe a specific order or sequence. It should be understood that such data can be interchanged under appropriate circumstances so that the embodiments of the present disclosure described herein can be implemented in an order other than those illustrated or described herein, for example.

[0041] In addition, the terms "comprising" and "having" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or device that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units not clearly listed or inherent to these processes, methods, products, or devices.

[0042] Multiple, including two or more than two.

[0043] And / or, it should be understood that for the term "and / or" used in the present disclosure, it is merely a description of the association relationship of associated objects, indicating that three relationships can exist. For example, A and / or B can represent: A exists alone, A and B exist simultaneously, and B exists alone, these three situations.

[0044] As Figures 1 to 8 shown, an embodiment of the technical solution of the present invention provides an opening and closing structure for the lip of an aircraft back support nacelle, including: two lip skins that can be opened and closed, a support frame 6, a support partition, a lip opening and closing link mechanism, and a locking mechanism.

[0045] The lip skins include a first lip skin and a second lip skin 5; the support frame 6 is fixedly arranged inside the first lip skin; the support partition is located between the first lip skin and the second lip skin 5 and is fixed on the upper surface of the wing; the lip opening and closing link mechanism is respectively hinged to the support frame 6, the support partition, and the second lip skin 5; the lip opening and closing link mechanism includes an elastic member 3, and the elastic member 3 is located between the first lip skin and the second lip skin 5; the locking mechanism is in linkage cooperation with the first lip skin and the second lip skin 5.

[0046] Specifically, the lip opening and closing link mechanism further includes a rotating frame and a driven link 2; the rotating frame includes a driving link 1 and a straight rod 8. One end of the driving link 1 is hinged to the straight rod 8, and the other end is hinged to the middle of the second lip skin 5; the straight rod 8 is hinged to the support partition; one end of the driven link 2 is hinged to the support partition, and the other end is hinged to the lower part of the lip skin; the elastic member 3 is hinged to the driving link 1.

[0047] Since there are multiple hinge points of the lip opening and closing link mechanism on and inside the lip skin, the mobility of the lip opening and closing link mechanism is increased. The entire lip opening and closing link rotating shaft mechanism enables the shown lip to be opened and closed translationally, making the opening and closing smoother and facilitating maintenance.

[0048] Further, one end of the driving link 1 is an arc portion, and the other end is a straight line portion. The end of the arc portion is hinged to the straight rod 8. A connecting piece 4 is provided on the arc portion, and the elastic member 3 is hinged to the driving link 1 through the connecting piece 4.

[0049] When the lip skin is in the closed state, the elastic member 3 is compressed, and the elastic member 3 is arranged obliquely upward along the end hinged to the driving link 1. The hinge point of the elastic member 3 and the driving link 1 is the highest point of the lip opening and closing link mechanism. Furthermore, it is ensured that the acting force of the elastic member 3 is obliquely upward when the lip is closed, so that the driving link 1 is fixed upward by the force.

[0050] The locking mechanism includes a zip fastener 10 and a handle 9. Specifically, the zip fastener 10 is fixed to the bottoms of the first lip skin and the second lip skin 5 respectively, and the handle 9 is connected to the zip fastener 10. By rotating the handle 9, the zip fasteners 10 on both sides are driven to realize the closing and locking of the lip.

[0051] Sealing strips 7 are provided at the edges of the first lip skin and / or the second lip skin 5 at the opening and closing positions. The sealing effect is improved. Specifically, the first lip skin and the second lip skin 5 have a stepped structure that can cooperate with each other at the opening, and the sealing strips 7 are arranged on one or two stepped structures, further improving the sealing effect.

[0052] Preferably in this embodiment, the elastic member 3 is a gas spring. When the lip is opened, the driving link 1 is driven by the thrust of the gas spring.

[0053] Preferably in this embodiment, hinge plates are provided on the support frame 6, the support partition, and the second lip skin 5, and the driving link 1, the straight rod 8, and the driven link 2 are hinged through the hinge plates.

[0054] In this embodiment, the opening and closing process of the lip opening and closing structure is specifically as follows:

[0055] When the lip needs to be opened, rotate the handle 9 to unzip the zipper 10. After the elastic member 3 becomes horizontal and then gradually tilts downward, the elastic member 3 provides a thrust to the active link 1, prompting the active link 1 to rotate downward and automatically open. During the opening process, the lip opening and closing structure first translates forward a certain distance and then lifts upward. This lip opening and closing structure is easy to install, firm and reliable, enabling the lip to open and close smoothly. The lip opening and closing link mechanism makes the maintenance of the integral lip simpler and more convenient.

[0056] When the lip needs to be closed, rotate the handle 9 to drive the zipper 10 to close the lip opening and closing structure. During the closing process of the lip, the elastic member 3 changes from a horizontal state to an upwardly inclined state, enabling the lip to close automatically.

[0057] According to the second aspect embodiment of the technical solution of the present invention, an aircraft is provided, and the above lip opening and closing structure is provided on the aircraft.

[0058] It should be noted that in this article, the terms "including", "comprising" or any other variant thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or also includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "including a..." does not exclude the existence of additional identical elements in the process, method, article or device including that element.

[0059] The above serial numbers of the embodiments of the present invention are only for description and do not represent the superiority or inferiority of the embodiments.

[0060] Through the description of the above embodiments, those skilled in the art can clearly understand that the above implementation methods can be realized by means of software plus a necessary general hardware platform. Of course, it can also be realized by hardware, but in many cases the former is a better implementation method. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk) and includes several instructions to enable a terminal (which can be a mobile phone, computer, server, air conditioner, or network device, etc.) to execute the methods described in various embodiments of the present invention.

[0061] The embodiments of the present invention have been described above in conjunction with the accompanying drawings. However, the present invention is not limited to the above specific embodiments. The above specific embodiments are merely illustrative and not restrictive. Under the inspiration of the present invention, those of ordinary skill in the art can also make many forms without departing from the spirit and scope protected by the claims of the present invention. These all fall within the protection scope of the present invention.

Claims

1. An aircraft back support nacelle lip opening and closing structure, characterized in that: It includes: two lip skins that can be opened and closed, a support frame, a support partition, a lip opening and closing connecting rod mechanism and a locking mechanism; The lip skin includes a first lip skin and a second lip skin; The support frame is fixedly arranged on the inner side of the first lip cover; The support partition is located between the first lip skin and the second lip skin and is fixed to the upper surface of the wing; The lip opening and closing link mechanism is respectively hinged to the support frame, the support partition and the second lip skin; The lip opening and closing linkage mechanism comprises an elastic component, and the elastic component is located between the first lip skin and the second lip skin; The locking mechanism cooperates with the first lip skin and the second lip skin.

2. The aircraft back support nacelle lip opening and closing structure according to claim 1, characterized in that: The lip opening and closing linkage mechanism also includes a rotating frame and a driven connecting rod; The rotating frame comprises an active connecting rod and a straight rod, one end of the active connecting rod is hinged to the straight rod, and the other end is hinged to the middle part of the second lip skin; The straight rod is hinged to the supporting partition; One end of the driven connecting rod is hinged to the supporting partition, and the other end is hinged to the lower part of the lip skin; The elastic component is hinged to the active connecting rod.

3. The aircraft back support nacelle lip opening and closing structure according to claim 2, characterized in that: One end of the active connecting rod is an arc-shaped portion, and the other end is a straight portion, and the end of the arc-shaped portion is hinged to the straight rod.

4. The aircraft back support nacelle lip opening and closing structure according to claim 3, characterized in that: The arc-shaped portion is provided with a connecting piece, and the elastic component is hinged to the active connecting rod through the connecting piece.

5. The aircraft back support nacelle lip opening and closing structure according to claim 2, characterized in that: When the lip skin is in a closed state, the elastic component is arranged obliquely upward along the end hinged to the active connecting rod.

6. The aircraft back support nacelle lip opening and closing structure according to claim 1, characterized in that: When the lip cover is in a closed state, the elastic component is compressed.

7. The aircraft back support nacelle lip opening and closing structure according to claim 1, characterized in that: The locking mechanism includes a zipper and a handle; The zipper fixes the bottom of the first lip cover and the bottom of the second lip cover respectively, and the handle is connected to the zipper.

8. The aircraft back support nacelle lip opening and closing structure according to claim 1, characterized in that: The elastic component is a gas spring.

9. The aircraft back support nacelle lip opening and closing structure according to claim 1, characterized in that: The first lip skin and / or the second lip skin are provided with sealing strips at the edges of the opening and closing positions.

10. An aircraft, characterized in that: The aircraft is provided with a lip opening and closing structure according to any one of claims 1-9.

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