A wing-mounted aircraft engine suspension structure

Abstract

The present application belongs to the technical field of wing-mounted aircraft engine suspension structure design, and specifically relates to a wing-mounted aircraft engine suspension structure, including: a suspension bracket for connecting to the bottom of a wing; a suspension shell, one side of which is connected to the bottom of the suspension bracket, and the other side of which has a suspension groove, and a side wall of which has a plurality of suspension holes; each suspension hole is distributed around the suspension groove and is connected to the suspension groove; a suspension block is arranged in the suspension groove, and is gap-matched with the suspension groove, and is used to connect to the aircraft engine; a plurality of suspension connecting rods, one end of which has a protruding portion on the outer wall; the other end of each suspension connecting rod passes through a corresponding suspension hole, and the end is hinged on the suspension block and is gap-matched with the corresponding suspension hole; a plurality of disc springs, each disc spring is correspondingly sleeved on the outer periphery of a suspension connecting rod, and both ends abut between the suspension shell and the corresponding protruding portion.

Description

Technical Field

[0001] The present application belongs to the technical field of wing-mounted aircraft engine suspension structure design, and specifically relates to a wing-mounted aircraft engine suspension structure. Background Art

[0002] The wing-mounted aircraft engine is suspended under the wing of the aircraft through a suspension structure. The current suspension structure is mostly a rigid structure. In order to make it have a certain vibration isolation effect, multiple rubber flexible joints are arranged on it. This technical solution has the following defects:

[0003] 1) The rubber flexible joint has a small load-bearing capacity and weak adaptive ability, and is easily damaged when subjected to a large load impact;

[0004] 2) Rubber flexible joints are susceptible to external erosion and are susceptible to high temperature ablation near aircraft engines, and may even cause fires. They have a limited lifespan and low safety.

[0005] This application is proposed in view of the above-mentioned technical defects.

[0006] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the invention

[0007] The purpose of the present application is to provide a wing-mounted aircraft engine suspension structure to overcome or alleviate at least one of the known technical deficiencies.

[0008] The technical solution of this application is:

[0009] A wing-mounted aircraft engine suspension structure, comprising:

[0010] A suspension bracket for connecting to the underside of the wing;

[0011] A suspension housing, one side of which is connected to the bottom of the suspension bracket, the other side of which is provided with a suspension groove, and a side wall of which is provided with a plurality of suspension holes; each of the suspension holes is distributed around the suspension groove and is connected with the suspension groove;

[0012] A suspension block is arranged in the suspension groove and is matched with the suspension groove gap to be connected to the aircraft engine;

[0013] A plurality of suspension connecting rods, one end of which has a protruding portion on the outer wall; the other end of each suspension connecting rod passes through a corresponding suspension hole, and the end is hinged on the suspension block and fits with the corresponding suspension hole clearance;

[0014] A plurality of disc springs, each disc spring is sleeved on the outer periphery of a suspension connecting rod, and two ends of the disc spring abut against between the suspension shell and the corresponding protruding part.

[0015] According to at least one embodiment of the present application, in the above-mentioned wing-mounted aircraft engine suspension structure, each suspension link has one end facing the suspension block and is hinged to the suspension block through a single-ear and double-ear structure.

[0016] According to at least one embodiment of the present application, in the above-mentioned wing-mounted aircraft engine suspension structure, one end of each suspension link facing the suspension block is screwed to the corresponding single-ear and double-ear structure.

[0017] According to at least one embodiment of the present application, in the above-mentioned wing-mounted aircraft engine suspension structure, the single and double ears of each single and double ear structure are hinged by a joint bearing.

[0018] According to at least one embodiment of the present application, the above-mentioned wing-mounted aircraft engine suspension structure further includes:

[0019] A plurality of first gaskets are provided, each of which is sleeved on the outer periphery of a suspension link and is located between the corresponding disc spring and the protruding portion.

[0020] According to at least one embodiment of the present application, the above-mentioned wing-mounted aircraft engine suspension structure further includes:

[0021] A plurality of second gaskets, each first gasket correspondingly sleeved on the periphery of a suspension link, are located between the corresponding disc spring and the suspension housing.

[0022] According to at least one embodiment of the present application, in the above-mentioned wing-mounted aircraft engine suspension structure, the outer wall of the suspension housing has a plurality of annular grooves, each of which surrounds a corresponding suspension hole and is connected to the corresponding suspension hole;

[0023] Each second gasket ring is clamped in the corresponding annular clamping groove and is loosely matched with the corresponding suspension connecting rod.

[0024] According to at least one embodiment of the present application, in the above-mentioned wing-mounted aircraft engine suspension structure, there are multiple groups of suspension shells and their corresponding suspension blocks, suspension connecting rods, and disc springs. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 is a schematic diagram of a wing-mounted aircraft engine suspension structure provided in an embodiment of the present application;

[0026] Figure 2 It is a partial schematic diagram of the wing-mounted aircraft engine suspension structure provided in an embodiment of the present application;

[0027] in:

[0028] 1-suspension bracket; 2-suspension housing; 3-suspension block; 4-suspension connecting rod; 5-disc spring; 6-single and double ear structure; 7-spherical bearing; 8-first gasket; 9-second gasket.

[0029] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and cannot be understood as limitations on this patent. DETAILED DESCRIPTION

[0030] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0031] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall be the common meanings understood by the general technicians in the field to which this application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inside", "outside" and other words indicating orientation used in the description of this application are only used to indicate the relative direction or positional relationship, and do not imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, so it cannot be understood as a limitation on this application. The "first", "second", "third" and similar terms used in the description of this application are only used for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The similar words "one", "one" or "the" used in the description of this application should not be understood as an absolute limitation on quantity, but should be understood as the existence of at least one. The similar words "including" or "comprising" used in the description of this application mean that the elements or objects appearing in front of the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0032] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0033] The following is combined with Figure 1 to Figure 2 This application is described in further detail.

[0034] A wing-mounted aircraft engine suspension structure, comprising:

[0035] A suspension bracket 1, used for connecting to the lower side of the wing;

[0036] A suspension housing 2, one side of which is connected to the bottom of the suspension bracket 1, and the other side of which has a suspension groove, and a side wall of which has a plurality of suspension holes; each suspension hole ring is connected to the suspension groove and is distributed around the suspension groove, and can be distributed on the bottom wall and side wall of the suspension groove, and the number of the suspension holes is not less than three;

[0037] The suspension block 3 is arranged in the suspension groove and cooperates with the large gap between the suspension grooves to be connected to the aircraft engine;

[0038] A plurality of suspension connecting rods 4, one end of which has a protruding portion on the outer wall; the other end of each suspension connecting rod 4 passes through a corresponding suspension hole, and the end is hinged on the suspension block 3 and fits with the corresponding suspension hole gap;

[0039] A plurality of disc springs 5 ​​are provided, each disc spring 5 is sleeved on the outer periphery of a suspension link 4, and both ends of the disc spring 5 are pressed against between the suspension housing 2 and the corresponding protruding part.

[0040] With the wing-mounted aircraft engine suspension structure disclosed in the above embodiment, the aircraft engine is suspended under the wing. The vibration load transmitted by the aircraft engine can be transmitted to each suspension link 4 through the suspension block 3. The vibration load borne by each suspension link 4 can be absorbed by the corresponding disc spring 5 through deformation, thereby having a vibration isolation effect.

[0041] As for the wing-mounted aircraft engine suspension structure disclosed in the above-mentioned embodiment, it can be understood by technicians in the field that its design realizes vibration isolation by deforming multiple disc springs 5 ​​to absorb the vibration load transmitted by the aircraft engine. The disc spring 5 has a strong load-bearing capacity, and its stiffness changes nonlinearly. It has a strong adaptability, can resist external erosion, ablate at high temperature, will not cause fire, is not easily damaged, and has a long service life.

[0042] For the wing-mounted aircraft engine suspension structure disclosed in the above-mentioned embodiment, technicians in the field can also understand that the suspension block 3 is designed to be directly connected to the aircraft engine, and the gap is set in the suspension groove of the suspension shell 2. One end of each suspension link 4 passes through the corresponding suspension hole on the suspension shell 2, is hinged on the suspension block 3, and cooperates with the corresponding suspension hole gap, so that the suspension block 3 has multiple dimensions of freedom in the suspension groove, which can effectively realize the absorption of the vibration load of the aircraft engine, thereby achieving a better vibration isolation effect.

[0043] In some optional embodiments, in the above-mentioned wing-mounted aircraft engine suspension structure, each suspension link 4 faces one end of the suspension block 3 and is hinged to the suspension block 3 through a single-double-ear structure 6.

[0044] In some optional embodiments, in the above-mentioned wing-mounted aircraft engine suspension structure, each suspension link 4 is screwed to the corresponding single-ear and double-ear structure 6 at one end facing the suspension block 3, so that the pre-tightening degree of the corresponding disc spring 5 can be adjusted by twisting, thereby ensuring the absorption of the vibration load of the aircraft engine.

[0045] In some optional embodiments, in the above-mentioned wing-mounted aircraft engine suspension structure, the single and double ears of each single and double ear structure 6 are hinged by a joint bearing 7 to ensure the multi-dimensional movement freedom of the suspension block 3.

[0046] In some optional embodiments, the above-mentioned wing-mounted aircraft engine suspension structure further includes:

[0047] A plurality of first gaskets 8 are provided, each of which is sleeved on the outer periphery of a suspension link 4 and is located between the corresponding disc spring 5 and the protruding portion.

[0048] In some optional embodiments, the above-mentioned wing-mounted aircraft engine suspension structure further includes:

[0049] A plurality of second gaskets 9 , each first gasket 9 is correspondingly sleeved on the outer periphery of a suspension link 4 and is located between the corresponding disc spring 5 and the suspension housing 2 .

[0050] In some optional embodiments, in the above-mentioned wing-mounted aircraft engine suspension structure, the outer wall of the suspension housing 2 has a plurality of annular grooves, each of which surrounds a corresponding suspension hole and is connected to the corresponding suspension hole;

[0051] Each second gasket ring 9 is clamped in the corresponding annular clamping groove and is loosely matched with the corresponding suspension link 4 .

[0052] In some optional embodiments, in the above-mentioned wing-mounted aircraft engine suspension structure, there are multiple groups of suspension shells 2 and their corresponding suspension blocks 3, suspension links 4, and disc springs 5. Their specific number and distribution positions can be determined by relevant technical personnel based on specific actual conditions when applying the technical solution disclosed in this application, and no further detailed description will be given here.

[0053] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0054] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present 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 fall within the scope of protection of the present application.

Claims

1. A wing-mounted aircraft engine suspension structure, characterized in that: include: A suspension bracket (1) for connecting to the lower side of the wing; A suspension housing (2), one side of which is connected to the bottom of the suspension bracket (1), the other side of which is provided with a suspension groove, and a side wall of which is provided with a plurality of suspension holes; each of the suspension holes is distributed around the suspension groove and is in communication with the suspension groove; A suspension block (3) is arranged in the suspension groove and is clearance-matched with the suspension groove to be connected to the aircraft engine; A plurality of suspension connecting rods (4), one end of which has a protruding portion on its outer wall; the other end of each of the suspension connecting rods (4) passes through a corresponding suspension hole, and the end is hinged on the suspension block (3) and is clearance-matched with the corresponding suspension hole; A plurality of disc springs (5), each of the disc springs (5) being sleeved on the outer periphery of a suspension connecting rod (4) with two ends abutting between the suspension housing (2) and a corresponding protruding portion.

2. The wing-mounted aircraft engine suspension structure according to claim 1, characterized in that: One end of each suspension link (4) faces the suspension block (3), and is hinged to the suspension block (3) via a single-double-ear structure (6).

3. The wing-mounted aircraft engine suspension structure according to claim 2, characterized in that: One end of each suspension link (4) facing the suspension block (3) is screwed onto a corresponding single-ear or double-ear structure (6).

4. The wing-mounted aircraft engine suspension structure according to claim 2, characterized in that: The single and double ears of each single and double ear structure (6) are hingedly connected via a joint bearing (7).

5. The wing-mounted aircraft engine suspension structure according to claim 1, characterized in that: Also includes: A plurality of first gaskets (8), each of the first gaskets (8) being sleeved on the outer periphery of a suspension link (4) and located between the corresponding disc spring (5) and the protruding portion.

6. The wing-mounted aircraft engine suspension structure according to claim 1, characterized in that: Also includes: A plurality of second gaskets (9), each of the second gaskets (9) being sleeved on the outer periphery of a suspension link (4) and located between the corresponding disc spring (5) and the suspension housing (2).

7. The wing-mounted aircraft engine suspension structure according to claim 6, characterized in that: The outer wall of the suspension housing (2) has a plurality of annular grooves, each of the annular grooves correspondingly surrounds one of the suspension holes and is connected to the corresponding suspension hole; Each of the second gasket rings (9) is clamped in a corresponding annular clamping groove and is clearance-matched with a corresponding suspension connecting rod (4).

8. The wing-mounted aircraft engine suspension structure according to claim 1, characterized in that: The suspension housing (2) and its corresponding suspension block (3), suspension connecting rod (4), and disc spring (5) include multiple groups.

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