CN219619373U - An aircraft side guide rail with positioning function - Google Patents

Abstract

The utility model relates to the technical field of aircraft, in particular to an aircraft side guide rail with a positioning function, comprising: an aircraft side guide rail body, two positioning grooves are opened on both sides of the aircraft side guide rail body, and the aircraft side guide rail body There are two limit grooves on the bottom of the limit groove, the inner cavity of the limit groove is provided with a ring, the surface of the ring is provided with an annular groove, and the inner cavity of the annular groove is provided with two symmetrical transmission An L-shaped block is fixedly connected to the opposite side of the two transmission blocks, a positioning block is fixedly connected to the top of the L-shaped block, and a connecting block is rotatably connected to both sides of the L-shaped block. The utility model has the advantages of high positioning accuracy and flexible use. In the actual use process, the triangular positioning method can ensure the stability of the positioning of the aircraft side guide rail, and it is convenient for the user to connect the aircraft side guide rail and the aircraft side wing body to avoid During the installation process, installation deviation occurred.

Description

An aircraft side guide rail with positioning function

technical field

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

Background technique

Aircraft refers to a power plant with one or more engines to generate forward thrust or pull, and the fixed wings of the fuselage to generate lift. Aircraft heavier than air that flies above, in, and below the atmosphere. Most aircraft are It consists of the following six main parts, namely: wing, fuselage, empennage, landing gear, control system and power plant. Each has its own unique function.

For example, the publication number is CN207759070U for a side guide rail reinforcement disclosed by an aircraft. By setting a side plate outside the wing body of the aircraft, the side plate and the side guide rail are connected, and the side guide rail slides in the guide rail in the guide rail. During the process, when the side guide rail is subjected to a large pressure, the cooperation between the first connecting block and the second connecting block on the support plate can play a buffering role under the action of the spring and the rubber pad, and can effectively prevent the pressure from damaging the side guide rail. , when under pressure, the connecting rod drives the roller to roll left and right in the arc-shaped seat, and cooperates with the first connecting block and the second connecting block on both sides to complete the pressure buffer; the whole device can strengthen the connection between the guide rail and the wing body of the aircraft Strength, with buffer function, can effectively prevent the damage of the guide rail during the process of leaving the warehouse, and prolong the service life of the guide rail.

Although the first connecting block, the second connecting block, springs and rubber pads are used to form reinforcements, the advantage of preventing the guide rail from being damaged during the delivery process is to solve the problem that the strength of the guide rail in the existing device is not strong enough, and it is easy to Corruption issues.

The side guide rail of the aircraft needs to be connected with the wing body of the aircraft during use. Most of the side guide rails for aircraft on the market and the above-mentioned patents are not provided with a positioning structure. Therefore, when the side guide rail is connected to the wing body of the aircraft, the side guide rail will be The movement along with the force of the connection makes the side guide rail deviate from the original track, which increases the difficulty of the connection, thereby increasing the work intensity of the user and reducing the work efficiency.

Utility model content

The purpose of this utility model is to provide an aircraft side guide rail with positioning function, which has the advantages of good positioning effect and flexible use, and solves the problems raised by the above-mentioned background technology.

In order to achieve the above purpose, the utility model provides the following technical solutions: an aircraft side guide rail with a positioning function, comprising: an aircraft side guide rail body, two positioning grooves are opened on both sides of the aircraft side guide rail body, and the aircraft side guide rail body The bottom of the side rail body is provided with two limit grooves, the inner cavity of the limit groove is provided with a ring, the surface of the ring is provided with an annular groove, and the inner cavity of the annular groove is provided with two Symmetrical transmission blocks, the opposite sides of the two transmission blocks are fixedly connected with an L-shaped block, the top of the L-shaped block is fixedly connected with a positioning block, and both sides of the L-shaped block are rotatably connected with connecting blocks, The bottom of the connecting block is fixedly connected with a mounting block, the top inside the ring is provided with a groove, the bottom inside the ring is provided with a threaded hole, and the inner cavity of the threaded hole is threadedly connected with a threaded rod, so A circular plate is fixedly connected to the top of the threaded rod, the surface of the circular plate fits the groove, and the bottom of the threaded rod penetrates to the bottom of the ring.

Further, as a preferred embodiment of the present invention, the bottom of the circular ring is fixedly connected with a connecting ring, the inner cavity of the connecting ring is adapted to the threaded rod, and the surface of the connecting ring is covered with a spring, so that The top of the connecting ring is fixedly connected with the circular ring.

Further, as a preferred aspect of the present invention, two symmetrically arranged limiting blocks are fixedly connected to the surface of the circular ring, and the limiting blocks are matched with the limiting grooves.

Further, as a preference of the present invention, the diameter of the groove is larger than the diameter of the threaded hole.

Further, as a preferred aspect of the present invention, the bottom of the threaded rod is fixedly connected with a rotating block, and the bottom end of the spring is fixedly connected with the rotating block.

Beneficial effects, the technical solution of the application has the following technical effects: the utility model has the advantages of high positioning accuracy and flexible use. In the actual use process, the triangular positioning method can ensure the stability of the positioning of the aircraft side guide rail and is convenient to use. The aircraft side guide rail is connected with the aircraft side wing body, which avoids the installation deviation during the installation process and affects the normal use of the side guide rail. It is simple in structure, easy to use, no need to disassemble parts, and has good versatility. Therefore, this positioning structure has a good market prospect and is worth promoting.

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

Description of drawings

The accompanying drawings are used to provide a further understanding of the utility model, and constitute a part of the description, and are used to explain the utility model together with the embodiments of the utility model, and do not constitute a limitation to the utility model. In the attached picture:

Fig. 1 is the structural representation of the utility model;

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

Fig. 3 is a three-dimensional schematic diagram of the positioning structure of the utility model;

Fig. 4 is a three-dimensional cross-sectional schematic diagram of a local structure of the utility model;

Fig. 5 is a three-dimensional schematic diagram of a partial structure of the utility model.

In the figure, the meanings of the reference signs are as follows: 1. Aircraft side guide rail body; 2. Positioning groove; 3. Limiting groove; 4. Ring; 5. Annular groove; 6. Transmission block; 7. L-shaped block ; 8, positioning block; 9, connection block; 10, groove; 11, threaded hole; 12, threaded rod; 13, circular plate; 14, connection ring; 15, spring; 16, limit block; 17, installation block ; 18, turn the block.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. described as follows. Aspects of the invention are described in this disclosure with reference to the accompanying drawings, in which a number of illustrated embodiments are shown. It should be appreciated that the various concepts and embodiments introduced above, as well as those concepts and implementations described in more detail below, can be implemented in any of numerous ways. Based on the embodiments of the present utility model, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the scope of protection of the present utility model.

As shown in accompanying drawings 1 to 5: the present embodiment provides an aircraft side guide rail with positioning function, comprising: an aircraft side guide rail body 1, two positioning grooves are provided on both sides of the aircraft side guide rail body 1 2. The bottom of the aircraft side guide rail body 1 is provided with two limiting grooves 3, the inner cavity of the limiting groove 3 is provided with a circular ring 4, and the surface of the circular ring 4 is provided with an annular groove 5, so The inner cavity of the annular groove 5 is provided with two symmetrical transmission blocks 6, and the opposite sides of the two transmission blocks 6 are fixedly connected with an L-shaped block 7, and the top of the L-shaped block 7 is fixedly connected with a positioning block 8. Both sides of the L-shaped block 7 are rotatably connected with a connecting block 9, the bottom of the connecting block 9 is fixedly connected with a mounting block 17, and the top of the ring 4 is provided with a groove 10, and the circle The bottom inside the ring 4 is provided with a threaded hole 11, the diameter of the groove 10 is greater than the diameter of the threaded hole 11, the inner cavity of the threaded hole 11 is threadedly connected with a threaded rod 12, and the top end of the threaded rod 12 is fixedly connected with a A circular plate 13 , the surface of the circular plate 13 is adapted to the groove 10 , and the bottom of the threaded rod 12 penetrates to the bottom of the ring 4 .

Specifically, the bottom of the ring 4 is fixedly connected with a connecting ring 14, the inner cavity of the connecting ring 14 is adapted to the threaded rod 12, and the surface of the connecting ring 14 is sleeved with a spring 15, and the connecting ring The top of 14 is fixedly connected with the ring 4 , the bottom of the threaded rod 12 is fixedly connected with a rotating block 18 , and the bottom end of the spring 15 is fixedly connected with the rotating block 18 .

In this embodiment: through the joint use of the connecting ring 14, the spring 15 and the rotating block 18, the function of buffering the 12 during operation is played.

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

In this embodiment: through the setting of the limiting block 16, the function of limiting the position of the circular ring 4 is played, preventing the phenomenon that the circular ring 4 is rotating.

The working principle and use process of the utility model: the user inserts the ring 4 and the limit block 16 into the inner cavity of the limit groove 3, rotates the threaded rod 12, and the threaded rod 12 is used in conjunction with the threaded hole 11 to drive the circle The ring 4 moves downward, and the circular ring 4 drives the circular ring 4 to move downward through the circular plate 13. The circular ring 4 is used in conjunction with the annular groove 5 and the transmission block 6 to drive the two L-shaped blocks 7 with the connecting block 9 as the axis. The heart moves to the opposite side, and the L-shaped block 7 drives the positioning block 8 to snap into the inner cavity of the positioning groove 2, thereby accomplishing the purpose of positioning.

It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply that there is a relationship between these entities or operations. There is no such actual relationship or order between them.

Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Those with ordinary knowledge in the technical field to which the utility model belongs can make various changes and modifications without departing from the spirit and scope of the utility model. Therefore, the protection scope of the present utility model should be defined by the 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.