CN217735601U

CN217735601U - Fixing clamp for airplane

Info

Publication number: CN217735601U
Application number: CN202221983981.2U
Authority: CN
Inventors: 段连赫
Original assignee: Harbin Shengxinyuan Machinery Manufacturing Co ltd
Current assignee: Harbin Shengxinyuan Machinery Manufacturing Co ltd
Priority date: 2022-07-29
Filing date: 2022-07-29
Publication date: 2022-11-04
Anticipated expiration: 2032-07-29

Abstract

The utility model discloses an aircraft is with fixed clamp, including the outer loop, rubber packing ring and damping buffer rod, a serial communication port, the rubber packing ring is installed to the inner wall of outer loop, the skin and the outer loop fixed connection of rubber packing ring, the fixed block is installed respectively to the both sides of outer loop, one side of fixed block respectively with outer loop fixed connection, the internally mounted of fixed block has the axostylus axostyle, the both ends of axostylus axostyle respectively with fixed block fixed connection, the damping buffer rod is installed to the middle part of axostylus axostyle, the one end and the axostylus axostyle swing joint of damping buffer rod, the connecting block is installed respectively to the other end of damping buffer rod, one side of connecting block respectively with damping buffer rod swing joint, the bolt is installed respectively to the middle part of outer loop both sides, the bolt respectively with outer loop threaded connection, rubber shock pad is installed respectively to one side of connecting block, one side of rubber shock pad respectively with connecting block fixed connection, the outer loop divide into two half isolating construction, and mutual gomphosis is connected between the outer loop. The utility model discloses simple structure, convenient operation.

Description

Fixing clamp for airplane

Technical Field

The utility model relates to an aircraft design technical field particularly, relates to a fixed clamp is used to aircraft.

Background

As is known, the working environment of an exhaust pipe of an aircraft engine is harsh and is exposed to complex environments such as high temperature, high pressure, high frequency vibration and the like, which results in a plurality of comprehensive factors to be considered in the design of the exhaust pipe of the engine. At present, an engine exhaust pipe generally adopts a single-layer pipe and fixed flange welding mode; or a mode of connecting a double-layer sleeve and a fixed joint with the machine body is adopted. The single-layer pipe and the fixed flange are welded in a mode that the flange welding increases the local rigidity of the pipe, so that the local deformation of the exhaust pipe is limited when the exhaust pipe is thermally deformed, and the exhaust pipe is easy to crack. The double-layer sleeve and fixed joint scheme is generally used for large length and large design space. The length of the exhaust pipe is large, and the design space is small.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an aircraft is with fixed clamp to solve the problem that proposes among the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an aircraft is with fixed clamp, includes outer loop, rubber packing ring and damping buffer beam, its characterized in that, the rubber packing ring is installed to the inner wall of outer loop, the skin of rubber packing ring with outer loop fixed connection, the fixed block is installed respectively to the both sides of outer loop, one side of fixed block respectively with outer loop fixed connection, the internally mounted of fixed block has the axostylus axostyle, the both ends of axostylus axostyle respectively with fixed block fixed connection, the middle part of axostylus axostyle is installed the damping buffer beam, the one end of damping buffer beam with axostylus axostyle swing joint, the connecting block is installed respectively to the other end of damping buffer beam, one side of connecting block respectively with damping buffer beam swing joint, the bolt is installed respectively to the middle part of outer loop both sides, the bolt respectively with outer loop threaded connection.

Furthermore, rubber shock pads are installed respectively to one side of connecting block, one side of rubber shock pad respectively with connecting block fixed connection.

Furthermore, the outer ring is divided into two half-separated structures, and the outer ring is mutually embedded and connected.

Furthermore, the periphery of the connecting block is respectively provided with a fixing screw.

Compared with the prior art, the utility model discloses following beneficial effect has:

the utility model discloses a screw up through the bolt fastening between the outer ring, the rubber packing ring can play the effect of protection to the pipeline, and the damping buffer beam can play the function of buffering when meetting the vibrations collision, and the rubber shock pad on the connecting block can improve stability simultaneously, and this device simple structure, and play fine barrier propterty to pipeline equipment.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a schematic plan view of an aircraft retainer clip in its entirety.

Reference numerals are as follows:

1. a rubber gasket; 2. a shaft lever; 3. a damping buffer rod; 4. connecting blocks; 5. a fixed block; 6. an outer ring; 7. a bolt; 8. a rubber shock pad.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, rather than all embodiments, and all other embodiments obtained by a person skilled in the art without creative work belong to the scope of protection of the present invention based on the embodiments of the present invention.

In the description of the present invention, it should be noted that the terms "top", "bottom", "one side", "the other side", "front", "back", "middle part", "inside", "top", "bottom", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which is only for the convenience of description and simplification of the description, but does not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention; the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; furthermore, unless expressly stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly and encompass, for example, both fixed and removable coupling as well as integral coupling; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Please refer to fig. 1, according to the embodiment of the present invention, a fixing clamp for an aircraft includes an outer ring 6, a rubber gasket 1 and a damping buffer rod 3, and is characterized in that the rubber gasket 1 is installed on an inner wall of the outer ring 6, an outer layer of the rubber gasket 1 is fixedly connected to the outer ring 6, fixed blocks 5 are respectively installed on two sides of the outer ring 6, one side of each fixed block 5 is fixedly connected to the outer ring 6, an axle rod 2 is installed inside the fixed blocks 5, two ends of the axle rod 2 are respectively fixedly connected to the fixed blocks 5, the damping buffer rod 3 is installed in the middle of the axle rod 2, one end of the damping buffer rod 3 is movably connected to the axle rod 2, a connecting block 3 is respectively installed on the other end of the damping buffer rod 3, one side of the connecting block 3 is respectively movably connected to the damping buffer rod 3, bolts 7 are respectively installed in the middle of two sides of the outer ring 6, and the bolts 7 are respectively connected to the outer ring 6 through threads.

Through the above technical scheme of the utility model, rubber shock pad 8 is installed respectively to one side of connecting block 4, one side of rubber shock pad 8 respectively with 4 fixed connection of connecting block, outer loop 6 divide into two halves isolating construction, and mutual gomphosis between the outer loop 6 is connected, install the fixed screw respectively around the connecting block 4.

The working principle is as follows: the utility model discloses a screw up through the bolt fastening between the outer ring, the rubber packing ring can play the effect of protection to the pipeline, and the damping buffer beam can play the function of buffering when meetting the vibrations collision, and the rubber shock pad on the connecting block can improve stability simultaneously, and this device simple structure, and play fine barrier propterty to pipeline equipment.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described above, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides an aircraft is with fixed clamp, includes outer loop (6), rubber packing ring (1) and damping buffer rod (3), its characterized in that, rubber packing ring (1) are installed to the inner wall of outer loop (6), the skin of rubber packing ring (1) with outer loop (6) fixed connection, fixed block (5) are installed respectively to the both sides of outer loop (6), one side of fixed block (5) respectively with outer loop (6) fixed connection, the internally mounted of fixed block (5) has axostylus axostyle (2), the both ends of axostylus axostyle (2) respectively with fixed block (5) fixed connection, install the middle part of axostylus axostyle (2) damping buffer rod (3), the one end of damping buffer rod (3) with axostylus axostyle (2) swing joint, connecting block (4) are installed respectively to the other end of damping buffer rod (3), one side of connecting block (4) respectively with damping buffer rod (3) swing joint, bolt (7) are installed respectively to the middle part of outer loop (6) both sides, bolt (7) respectively with outer loop (6) threaded connection.

2. A fixing clamp for an aircraft according to claim 1, characterized in that a rubber shock pad (8) is mounted on one side of each connecting block (4), and one side of each rubber shock pad (8) is fixedly connected with each connecting block (4).

3. A fixing clamp for aircraft according to claim 1, characterised in that the outer ring (6) is divided into two separate halves and the outer rings (6) are connected to each other by interlocking engagement.

4. An aircraft mounting clip according to claim 1, wherein the attachment blocks (4) are provided with respective attachment screws around their periphery.