CN219619373U - Aircraft side guide rail with positioning function - Google Patents

Abstract

The utility model relates to the technical field of aircrafts, in particular to an aircraft side guide rail with a positioning function, which comprises: the aircraft side guide rail body, two constant head tanks have all been seted up to the both sides of aircraft side guide rail body, two spacing grooves have been seted up to the bottom of aircraft side guide rail body, the inner chamber of spacing groove is provided with the ring, annular groove has been seted up on the surface of ring, annular groove's inner chamber is provided with the transmission piece of two symmetries, and one side that two transmission pieces are on the back of the body is equal fixedly connected with L shape piece, the top fixedly connected with locating piece of L shape piece, the both sides of L shape piece are all rotated and are connected with the connecting block. The utility model has the advantages of high positioning precision and flexible use, can ensure the positioning stability of the side guide rail of the airplane by a triangular positioning method in the actual use process, is convenient for a user to connect the side guide rail of the airplane with the side wing body, and avoids the occurrence of installation deviation in the installation process.

Description

Aircraft side guide rail with positioning function

Technical Field

The utility model relates to the technical field of aircrafts, in particular to an aircraft side guide rail with a positioning function.

Background

An aircraft refers to an aircraft which is heavier than air and flies above, in and below the atmosphere, and most of the aircraft consists of the following six main parts, namely: wings, fuselages, tails, landing gear, handling systems, and power units. They each have their unique functions.

According to the side guide rail reinforcement for the aircraft disclosed in the publication No. CN207759070U, the side plates are arranged on the outer sides of the wing bodies of the aircraft, then the side plates are connected with the side guide rails, the side guide rails slide in guide channels in the guide rails, when the side guide rails are subjected to larger pressure in the warehouse-out process, the first connecting blocks and the second connecting blocks on the supporting plates cooperate, the buffer effect can be achieved under the action of the springs and the rubber pads, the side guide rails can be effectively prevented from being damaged by the pressure, the rollers are driven by the connecting rods to roll left and right in the arc-shaped seats, and the buffer of the pressure is completed by the cooperation of the first connecting blocks and the second connecting blocks on the two sides; the whole device can strengthen the joint strength of the guide rail and the airplane wing body, has a buffer function, can effectively prevent the guide rail from being damaged in the process of leaving a warehouse, and prolongs the service life of the guide rail.

The guide rail is prevented from being damaged in the warehouse-out process though the reinforcing piece is formed by the first connecting block, the second connecting block, the spring, the rubber pad and other parts, so that the problem that the guide rail of the existing device is insufficient in strength and easy to damage is solved.

When the side guide rail of the airplane is used, the side guide rail needs to be connected with the wing body of the airplane, most of the side guide rails for the airplane on the market and the patents are not provided with positioning structures, so that when the side guide rail is connected with the wing body of the airplane, the side guide rail can move along with the connecting force, and further the side guide rail deviates from the original track, the connecting difficulty is improved, the working strength of a user is improved, and the working efficiency is reduced.

Disclosure of Invention

The utility model aims to provide the airplane side guide rail with the positioning function, which has the advantages of good positioning effect and flexible use and solves the problems of the background technology.

In order to achieve the above purpose, the present utility model provides the following technical solutions: an aircraft side rail with positioning function, comprising: the aircraft side guide rail body, two constant head tanks have all been seted up to the both sides of aircraft side guide rail body, two spacing grooves have been seted up to the bottom of aircraft side guide rail body, the inner chamber of spacing groove is provided with the ring, annular groove has been seted up on the surface of ring, annular groove's inner chamber is provided with two symmetrical transmission pieces, and one side that two transmission pieces are on the back of the body is equal fixedly connected with L shape piece, the top fixedly connected with locating piece of L shape piece, the both sides of L shape piece are all rotated and are connected with the connecting block, the bottom fixedly connected with installation piece of connecting block, the inside top of ring is seted up flutedly, the screw hole has been seted up to the inside bottom of ring, the inner chamber threaded connection of screw hole has the threaded rod, the top fixedly connected with plectane of threaded rod, the surface and the recess looks adaptation of plectane, the bottom of threaded rod runs through to the bottom of ring.

Furthermore, as one preferable mode of the utility model, the bottom of the circular ring is fixedly connected with a connecting ring, the inner cavity of the connecting ring is matched with the threaded rod, the surface of the connecting ring is sleeved with a spring, and the top end of the connecting ring is fixedly connected with the circular ring.

Furthermore, as one preferable mode of the utility model, the surface of the circular ring is fixedly connected with two symmetrically arranged limiting blocks, and the limiting blocks are matched with the limiting grooves.

Further, as a preferable aspect of the present utility model, the diameter of the recess is larger than the diameter of the screw hole.

Further, as one preferable aspect of the present utility model, a rotating block is fixedly connected to the bottom of the threaded rod, and the bottom end of the spring is fixedly connected to the rotating block.

The beneficial effects are that the technical scheme of the utility model has the following technical effects: the utility model has the advantages of high positioning precision and flexible use, can ensure the positioning stability of the side guide rail of the airplane by a triangular positioning method in the actual use process, is convenient for a user to connect the side guide rail of the airplane with the side wing body, avoids the occurrence of mounting deviation in the mounting process, influences the normal use of the side guide rail, has simple structure, convenient use, does not need to detach parts, has better universality, namely completes the positioning of the side guide rail, and therefore, the positioning structure has good market prospect and is worthy of popularization.

It should be understood that all combinations of the foregoing concepts, as well as additional concepts described in more detail below, may be considered a part of the inventive subject matter of the present disclosure as long as such concepts are not mutually inconsistent.

Drawings

The accompanying drawings are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate the utility model and together with the embodiments of the utility model, serve to explain the utility model. In the drawings:

FIG. 1 is a schematic diagram of the structure of the present utility model;

FIG. 2 is a bottom perspective view of a partial structure of the present utility model;

FIG. 3 is a perspective view of a positioning structure according to the present utility model;

FIG. 4 is a schematic perspective view of a partial structure of the present utility model;

fig. 5 is a schematic perspective view of a partial structure of the present utility model.

In the drawings, the meanings of the reference numerals are as follows: 1. an aircraft side rail body; 2. a positioning groove; 3. a limit groove; 4. a circular ring; 5. an annular groove; 6. a transmission block; 7. an L-shaped block; 8. a positioning block; 9. a connecting block; 10. a groove; 11. a threaded hole; 12. a threaded rod; 13. a circular plate; 14. a connecting ring; 15. a spring; 16. a limiting block; 17. a mounting block; 18. and rotating the block.

Detailed Description

The technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and in order to better understand the technical content of the present utility model, specific embodiments are specifically described below with reference to the accompanying drawings. Aspects of the utility model are described in this disclosure with reference to the drawings, in which are shown a number of illustrative embodiments. It should be appreciated that the various concepts and embodiments described above, as well as those described in more detail below, may be implemented in any of a wide variety of ways. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

As shown in fig. 1 to 5: the embodiment provides an aircraft side rail with positioning function, including: the aircraft side guide rail body 1, two constant head tanks 2 have all been seted up to the both sides of aircraft side guide rail body 1, two spacing grooves 3 have been seted up to the bottom of aircraft side guide rail body 1, the inner chamber of spacing groove 3 is provided with ring 4, annular groove 5 has been seted up on the surface of ring 4, the inner chamber of annular groove 5 is provided with two symmetrical transmission piece 6, the equal fixedly connected with L shape piece 7 in one side that two transmission piece 6 are opposite to, the top fixedly connected with locating piece 8 of L shape piece 7, the both sides of L shape piece 7 all rotate and are connected with connecting block 9, the bottom fixedly connected with installation piece 17 of connecting block 9, recess 10 has been seted up at the inside top of ring 4, threaded hole 11 has been seted up to the inside bottom of ring 4, the diameter of recess 10 is greater than the diameter of threaded hole 11, threaded rod 12 is connected with to the inner chamber screw thread of threaded hole 11, the top fixedly connected with 13 of threaded rod 12, the surface and the recess 10 looks adaptation of plectane 13, the bottom of plectane 12 runs through to the bottom of ring 4.

Specifically, the bottom fixedly connected with go-between 14 of ring 4, the inner chamber and the threaded rod 12 looks adaptation of go-between 14, the surface cover of go-between 14 is equipped with spring 15, the top and the ring 4 fixed connection of go-between 14, the bottom fixedly connected with turning block 18 of threaded rod 12, the bottom and the turning block 18 fixed connection of spring 15.

In this embodiment: through the cooperation of the connecting ring 14, the spring 15 and the rotating block 18, the buffer effect on the working of the 12 is achieved.

Specifically, two symmetrically arranged limiting blocks 16 are fixedly connected to the surface of the circular ring 4, and the limiting blocks 16 are matched with the limiting grooves 3.

In this embodiment: through the setting of stopper 16, played the effect of carrying out spacing with ring 4, prevented that ring 4 is appearing pivoted phenomenon.

The working principle and the using flow of the utility model are as follows: the user is through the inner chamber with ring 4 and stopper 16 embedding spacing groove 3, rotates threaded rod 12, and threaded rod 12 uses through the cooperation with screw hole 11, drives ring 4 downwardly moving, and ring 4 passes through plectane 13 and drives ring 4 downwardly moving, and ring 4 uses through the cooperation of annular groove 5 and drive piece 6, drives two L shape pieces 7 and uses connecting block 9 as the axle center to the relative one side removal, and L shape piece 7 drives locating piece 8 card into the inner chamber of constant head tank 2, and then accomplishes the purpose of location.

It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions.

While the utility model has been described with reference to preferred embodiments, it is not intended to be limiting. Those skilled in the art will appreciate that various modifications and adaptations can be made without departing from the spirit and scope of the present utility model. Accordingly, the scope of the utility model is defined by the appended claims.

Claims (5)

1. An aircraft side rail with positioning function, comprising: aircraft side guide rail body (1), its characterized in that: two constant head tanks (2) have all been seted up to the both sides of aircraft side guide rail body (1), two spacing groove (3) have been seted up to the bottom of aircraft side guide rail body (1), the inner chamber of spacing groove (3) is provided with ring (4), annular groove (5) have been seted up on the surface of ring (4), the inner chamber of annular groove (5) is provided with two symmetrical transmission piece (6), the equal fixedly connected with L shape piece (7) in one side that two transmission piece (6) are on the back of the body mutually, the top fixedly connected with locating piece (8) of L shape piece (7), the both sides of L shape piece (7) are all rotated and are connected with connecting block (9), the bottom fixedly connected with installation piece (17) of connecting block (9), fluted (10) are seted up at the inside top of ring (4), threaded hole (11) are seted up to the inside bottom of ring (4), threaded rod (12) are threaded connection in the inner chamber of threaded hole (11), the top fixedly connected with plectane (13) of threaded rod (12), the top fixedly connected with round plate (13) of plectane (13) and the bottom of recess (12) looks, bottom of wearing to ring (4).

2. An aircraft side rail with positioning function according to claim 1, characterized in that: the bottom fixedly connected with go-between (14) of ring (4), the inner chamber and the threaded rod (12) looks adaptation of go-between (14), the surface cover of go-between (14) is equipped with spring (15), the top and the ring (4) fixed connection of go-between (14).

3. An aircraft side rail with positioning function according to claim 1, characterized in that: two symmetrically arranged limiting blocks (16) are fixedly connected to the surface of the circular ring (4), and the limiting blocks (16) are matched with the limiting grooves (3).

4. An aircraft side rail with positioning function according to claim 1, characterized in that: the diameter of the groove (10) is larger than that of the threaded hole (11).

5. An aircraft side rail with positioning function according to claim 2, characterized in that: the bottom of threaded rod (12) is fixedly connected with rotary block (18), the bottom of spring (15) and rotary block (18) fixed connection.