Aircraft back support nacelle lip opening and closing structure and aircraft

Abstract

The utility model discloses an airplane back support nacelle lip opening and closing structure and an airplane. The airplane back support nacelle lip opening and closing structure comprises two lip skin which can be arranged in an opening and closing mode, 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] This utility model relates to the field of aircraft structural design, and in particular to an aircraft back-support nacelle lip opening and closing structure and an aircraft. Background Technology

[0002] Aircraft engines are the devices that provide power to aircraft and are one of the core components of an aircraft. Aircraft engines are generally located under the wings or at the rear of the fuselage, with a few aircraft having their engines located on the upper leading edge of the wing (such as propeller engines). However, engines mounted in these positions are very inconvenient for maintenance personnel to inspect and repair, and the upper surface of the wing where the engine exhaust exits requires high-temperature resistant materials and surface treatment; with the engine mounted under the wing, the landing gear height is too high, resulting in an excessively high overall aircraft height and poor stability. To reduce the landing gear height and overall aircraft height and increase stability, the dorsal-supported engine structure was developed. However, existing dorsal-supported engine structures still suffer from the problem of limited space on the upper surface of the wing for array (multi-row engine) structures, making installation space difficult and hindering complete disassembly and installation, thus leading to maintenance difficulties.

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

[0004] To address the above problems, this utility model provides an aircraft back-support nacelle lip opening and closing structure and an aircraft, which enables rapid opening and closing of the back-support engine structure, solving the problem of maintenance difficulties.

[0005] According to a first aspect of the present invention, an aircraft back support nacelle lip opening and closing structure is provided, comprising: two closable lip skins, a support frame, a support partition, a lip opening and closing linkage mechanism, and a locking mechanism.

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

[0007] The support frame is fixedly installed on the inner side of the first lip skin;

[0008] 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;

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

[0010] The lip opening and closing linkage mechanism includes an elastic component, which is located between the first lip skin and the second lip skin.

[0011] The locking mechanism works in conjunction with the first and second lip skins.

[0012] In the above scheme, the lip opening and closing linkage mechanism also includes a rotating frame and a driven link;

[0013] The rotating frame includes 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 of the second lip skin.

[0014] The straight rod is hinged to the supporting 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 component is hinged to the active connecting rod.

[0017] In the above scheme, one end of the active connecting rod is an arc-shaped part and the other end is a straight part, and the end of the arc-shaped part is hinged to the straight rod.

[0018] In the above scheme, the arc-shaped part is provided with a connecting piece, and the elastic component is hinged to the active connecting rod through the connecting piece.

[0019] In the above scheme, when the lip skin is in the closed state, the elastic component is inclined upward along the end that is hinged to the active connecting rod.

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

[0021] In the above solution, the locking mechanism includes a pull lock and a handle;

[0022] The zipper secures the bottom of the first lip skin and the second lip skin respectively, and the handle is connected to the zipper.

[0023] In the above scheme, the elastic component is a gas spring.

[0024] In the above scheme, the first lip skin and / or the second lip skin are provided with sealing strips at the edges of the open and closed positions.

[0025] According to a second aspect of the present invention, an aircraft is provided, the aircraft being provided with a lip opening and closing structure as described above.

[0026] The beneficial effects of this utility model are:

[0027] This utility model discloses an aircraft back-support nacelle lip opening and closing structure and an aircraft. The elastic component and the linkage of the lip opening and closing linkage mechanism realize 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 maintenance on the wing surface, improve maintenance efficiency and save maintenance time when maintaining the nacelle and lip. Attached Figure Description

[0028] 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 or the prior art will be briefly introduced below. Obviously, the drawings described below are only some 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.

[0029] Figure 1 This is a schematic diagram of the aircraft back support nacelle lip opening and closing structure disclosed in this utility model in the closed state.

[0030] Figure 2 This is a schematic diagram of the aircraft back support nacelle lip opening and closing structure disclosed in this utility model in the translational start-up state.

[0031] Figure 3 This is a schematic diagram of the aircraft back support nacelle lip opening and closing structure disclosed in this utility model in the open and ascending state.

[0032] Figure 4 This is a schematic diagram of the aircraft back support nacelle lip opening and closing structure disclosed in this utility model in the final open state.

[0033] Figure 5 This is an enlarged view of the active linkage and elastic component of the aircraft back support nacelle lip opening and closing structure disclosed in this utility model.

[0034] Figure 6 This is an overall layout diagram of the lip opening and closing linkage mechanism of the aircraft back support nacelle lip opening and closing structure disclosed in this utility model.

[0035] Figure 7 This is a schematic diagram of the locking mechanism of the aircraft back support nacelle lip opening and closing structure disclosed in this utility model.

[0036] Figure 8 This is a global view of the aircraft back-support nacelle disclosed in this utility model.

[0037] Among them, the active link-1; the driven link-2; the elastic component-3; the connecting piece-4; the second lip skin-5; the support frame-6; the sealing strip-7; the straight rod-8; the handle-9; and the zipper-10.

[0038] The realization of the purpose, functional features and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0039] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numerals in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this disclosure. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this disclosure as detailed in the appended claims.

[0040] The terms "first," "second," etc., used in this disclosure are for distinguishing similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such use of data can be interchanged where appropriate so that the embodiments of this disclosure described herein can be implemented, for example, in orders other than those illustrated or described herein.

[0041] Furthermore, the terms “comprising” and “having”, and any variations thereof, are intended to cover non-exclusive inclusion, such that a process, method, system, product, or apparatus that includes a series of steps or units is not necessarily limited to those steps or units that are explicitly listed, but may include other steps or units that are not explicitly listed or that are inherent to such process, method, product, or apparatus.

[0042] Multiple, including two or more.

[0043] And / or, it should be understood that, for the purposes of this disclosure, the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone.

[0044] like Figures 1 to 8 As shown, one embodiment of the present invention provides an aircraft back support nacelle lip opening and closing structure, including: two closable lip skins, a support frame 6, a support partition, a lip opening and closing linkage mechanism, and a locking mechanism.

[0045] The lip skin includes a first lip skin and a second lip skin 5; a support frame 6 is fixedly disposed inside the first lip skin; a support partition is located between the first lip skin and the second lip skin 5 and is fixed to the upper surface of the wing; the lip opening and closing linkage mechanism is hinged to the support frame 6, the support partition and the second lip skin 5 respectively; the lip opening and closing linkage mechanism includes an elastic component 3, which is located between the first lip skin and the second lip skin 5; and a locking mechanism is linked and cooperates with the first lip skin and the second lip skin 5.

[0046] Specifically, the lip opening and closing linkage mechanism also includes a rotating frame and a driven link 2; the rotating frame includes a driving link 1 and a straight link 8, one end of the driving link 1 is hinged to the straight link 8, and the other end is hinged to the middle of the second lip skin 5; the straight link 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 component 3 is hinged to the driving link 1.

[0047] Because the lip opening and closing linkage mechanism has multiple hinge points on and inside the lip skin, the mobility of the lip opening and closing linkage mechanism is increased. The entire lip opening and closing linkage shaft mechanism enables the lip to be opened and closed in translation, making the opening and closing smoother and easier to maintain.

[0048] Furthermore, one end of the active connecting rod 1 is an arc-shaped portion, and the other end is a straight portion. The end of the arc-shaped portion is hinged to the straight rod 8. A connecting piece 4 is provided on the arc-shaped portion, and the elastic component 3 is hinged to the active connecting rod 1 through the connecting piece 4.

[0049] When the lip skin is in the closed state, the elastic component 3 is compressed, and the elastic component 3 is inclined upward along the end that is hinged to the active connecting rod 1. The hinge point between the elastic component 3 and the active connecting rod 1 is the highest point of the lip opening and closing linkage mechanism, thus ensuring that the force of the elastic component 3 is inclined upward when the lip is closed, so that the active connecting rod 1 is fixed upward by force.

[0050] The locking mechanism includes a zipper 10 and a handle 9. Specifically, the zipper 10 fixes the bottom of the first lip skin and the second lip skin 5 respectively, and the handle 9 is connected to the zipper 10. By rotating the handle 9, the zippers 10 on both sides are driven to achieve the closing and locking of the lips.

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

[0052] In this preferred embodiment, the elastic component 3 is a gas spring. When the lip opens, the thrust of the gas spring drives the active connecting rod 1.

[0053] In this preferred embodiment, the support frame 6, the support partition, and the second lip skin 5 are all provided with hinge plates, and the active connecting rod 1, the straight rod 8, and the driven connecting rod 2 are hinged through the hinge plates.

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

[0055] When the lip needs to be opened, turn handle 9 to pull open the zipper 10. The elastic component 3, after becoming horizontal, gradually tilts downwards. The elastic component 3 provides thrust to the active linkage 1, causing it to rotate downwards and automatically open. During the opening process, the lip opening and closing structure first moves forward a certain distance and then lifts upwards. This lip opening and closing structure is easy to install, robust, and reliable, allowing the lip to open and close freely. The lip opening and closing linkage mechanism makes maintenance of the integrated lip simpler and more convenient.

[0056] When the lip needs to be closed, the lip opening and closing structure is closed by turning the handle 9 to drive the pull lock 10. During the lip closing process, the elastic component 3 changes from a horizontal state to an upward tilted state, so that the lip can close automatically.

[0057] According to a second aspect of the present invention, an aircraft is provided, wherein the aircraft is provided with the above-described lip opening and closing structure.

[0058] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

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

[0060] Through the above description of the embodiments, those skilled in the art can clearly understand that the above implementation methods can be implemented by means of software plus necessary general-purpose hardware platforms. Of course, they can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of this utility model, 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 cause a terminal (which may be a mobile phone, computer, server, air conditioner, or network device, etc.) to execute the methods described in the various embodiments of this utility model.

[0061] The embodiments of the present invention have been described above with reference to the accompanying drawings. However, the present invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms under the guidance of the present invention without departing from the spirit and scope of the claims. All of these forms are within the protection scope of the present invention.

Claims

1. An opening and closing structure of a back-up nacelle lip of an aircraft, characterized by, The lip opening and closing structure comprises two openable and closable lip skins, a support frame, a support partition, a lip opening and closing linkage mechanism and a locking mechanism. The lip skins comprise a first lip skin and a second lip skin. The support frame is fixedly arranged on the inner side of the first lip skin. 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. The lip opening and closing linkage mechanism is hingedly connected with the support frame, the support partition and the second lip skin respectively. The lip opening and closing linkage mechanism comprises an elastic component, which is located between the first lip skin and the second lip skin. The locking mechanism is linked with the first lip skin and the second lip skin.

2. The opening and closing structure of the lip of the short cowl of the backrest of the aircraft according to claim 1, characterized in that, The lip opening and closing linkage mechanism further comprises a rotating frame and a driven linkage. The rotating frame comprises a driving linkage and a straight rod, one end of the driving linkage is hingedly connected with the straight rod, and the other end is hingedly connected with the middle part of the second lip skin. The straight rod is hingedly connected with the support partition. One end of the driven linkage is hingedly connected with the support partition, and the other end is hingedly connected with the lower part of the lip skin. The elastic component is hingedly connected with the driving linkage.

3. The aircraft buttress nacelle lip opening and closing structure according to claim 2, characterized in that, One end of the driving linkage is an arc-shaped part, and the other end is a straight part, and the end of the arc-shaped part is hingedly connected with the straight rod.

4. The opening and closing structure of the lip of the backrest nacelle of the aircraft according to claim 3, characterized in that, A connecting piece is arranged on the arc-shaped part, and the elastic component is hingedly connected with the driving linkage through the connecting piece.

5. The aircraft buttress nacelle lip opening and closing structure according to Claim 2, characterized by When the lip skin is in the closed state, the elastic component is arranged obliquely upward along the hingedly connected end of the driving linkage.

6. The aircraft buttress nacelle lip opening and closing structure according to Claim 1, characterized in that, When the lip skin is in the closed state, the elastic component is compressed.

7. The aircraft buttress nacelle lip opening and closing structure according to Claim 1, characterized by The locking mechanism comprises a zipper and a handle. The zipper fixes the bottom of the first lip skin and the second lip skin respectively, and the handle is connected with the zipper.

8. The aircraft buttress nacelle lip opening and closing structure according to Claim 1, characterized in that, The elastic component is a gas spring.

9. The aircraft buttress nacelle lip opening and closing structure according to Claim 1, characterized by, The first lip skin and / or the second lip skin is provided with a sealing strip at the edge of the opening and closing position.

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

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