CN211013530U

CN211013530U - Angle feedback device of aircraft nose wheel turning system

Info

Publication number: CN211013530U
Application number: CN202020092132.2U
Authority: CN
Inventors: 刘哲; 郭龙斐
Original assignee: Xi'an Honghang Electromechanical Equipment Co ltd
Current assignee: Xi'an Honghang Electromechanical Equipment Co ltd
Priority date: 2020-01-15
Filing date: 2020-01-15
Publication date: 2020-07-14
Anticipated expiration: 2030-01-15

Abstract

The utility model discloses an angle feedback device of an airplane front wheel steering system, which comprises a steering cylinder, a steering rod is embedded in the steering cylinder, the bottom end of the steering rod is fixedly connected with a clamp fork, the outer walls of the two ends of the steering rod are fixedly sleeved with limit rings, the outer wall of the middle part of the steering rod is fixedly sleeved with a shifting fork, a front wheel is embedded in the clamp fork, two extension rods are symmetrically arranged on the outer wall of the top end of the clamp fork, one side of the steering cylinder is fixedly connected with a convex ring, one side of the convex ring is provided with an arc-shaped groove, and an arc-shaped strip is embedded in the arc-shaped groove. In addition, the angular displacement sensor and the shifting lever can be driven to change positions by rotating the knob.

Description

Angle feedback device of aircraft nose wheel turning system

Technical Field

The utility model relates to an angle feedback device, in particular to angle feedback device of aircraft nose wheel system of turning belongs to aircraft nose wheel system field of turning.

Background

The amphibious aircraft has special requirements on the design of a front wheel steering system, and the electric-transmission front wheel steering system can be smoothly used on the amphibious aircraft on the premise of meeting the requirements of water resistance and corrosion resistance. The design of a control system, a turning control valve and a feedback sensor is an important link of system design, and at present, a front wheel feedback structure of an amphibious aircraft does not have an adjusting function, so that the angle feedback structure of the front wheel turning system of the aircraft is inconvenient to debug.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an angle feedback device of aircraft nose wheel system of turning 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: an angle feedback device of an aircraft front wheel steering system comprises a steering cylinder, wherein a steering rod is embedded in the steering cylinder, a clamp fork is fixedly connected to the bottom end of the steering rod, limiting rings are fixedly sleeved on the outer walls of two ends of the steering rod respectively, a shifting fork is fixedly sleeved on the outer wall of the middle part of the steering rod, a front wheel is embedded in the clamp fork, two extension rods are symmetrically arranged on the outer wall of the top end of the clamp fork, a convex ring is fixedly connected to one side of the steering cylinder, an arc-shaped groove is formed in one side of the convex ring, an arc-shaped strip is embedded in the arc-shaped groove, a countersunk groove is formed in the outer side of the arc-shaped strip, a track plate is fixedly connected to the inner wall of the arc-shaped strip, bosses are fixedly connected to the lower sides of two ends of the track plate, a threaded rod is arranged between the two bosses, one end of the threaded rod, the fixed cover in the outside of threaded rod is equipped with the slider, the fixed angle displacement sensor that inlays of downside of slider, the output fixedly connected with driving lever of angle displacement sensor.

Preferably, the bottom end of the deflector rod extends into a groove on the clamping fork, and the deflector rod is in an L-shaped structure.

Preferably, the threaded rod is in threaded connection with a sliding block, and the sliding block is in sliding connection with the track plate.

Preferably, the knob is in a regular hexagonal structure.

Preferably, the arc-shaped groove and the arc-shaped strip are bonded through sealing glue.

Compared with the prior art, the beneficial effects of the utility model are that: the utility model relates to an angle feedback device of aircraft nose wheel system of turning, have structural design reasonable and characteristics of adjustable precision, during the use, when the double-layered fork drives steering column angle of adjustment, the shift fork can stir the driving lever and turn to, and then drive angle displacement sensor's output shaft rotates, thereby the angular displacement volume of real-time feedback shift fork and steering column, furthermore, it can drive angle displacement sensor and driving lever relocation to rotate the knob, the distance between driving lever and the steering column is more near, the amplitude of oscillation of driving lever is less, the distance between driving lever and the steering column is more far away, the amplitude of oscillation of driving lever is big more, this kind of design can let angle displacement sensor's selection space bigger.

Drawings

Fig. 1 is a side sectional view of the present invention;

FIG. 2 is a top sectional view of the present invention;

fig. 3 is an enlarged view of the structure at a in fig. 1 of the present invention;

fig. 4 is a schematic structural diagram of the shifting fork of the present invention.

In the figure: 1. a steering cylinder; 2. a steering lever; 3. a shifting fork; 4. a convex ring; 5. a limiting ring; 6. an extension rod; 7. a clamping fork; 8. a front wheel; 9. an arc-shaped slot; 10. an arc-shaped strip; 11. a countersunk groove; 12. a knob; 13. a threaded rod; 14. a slider; 15. a track plate; 16. a boss; 17. an angular displacement sensor; 18. a deflector rod.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-4, the present invention provides a technical solution: an angle feedback device of an airplane front wheel steering system comprises a steering cylinder 1, a steering rod 2 is embedded in the steering cylinder 1, a clamping fork 7 is fixedly connected to the bottom end of the steering rod 2, limiting rings 5 are fixedly sleeved on the outer walls of two ends of the steering rod 2, a shifting fork 3 is fixedly sleeved on the outer wall of the middle portion of the steering rod 2, a front wheel 8 is embedded in the clamping fork 7, two extension rods 6 are symmetrically arranged on the outer wall of the top end of the clamping fork 7, a convex ring 4 is fixedly connected to one side of the steering cylinder 1, an arc-shaped groove 9 is formed in one side of the convex ring 4, an arc-shaped bar 10 is embedded in the arc-shaped groove 9, a countersunk groove 11 is formed in the outer side of the arc-shaped bar 10, a track plate 15 is fixedly connected to the inner wall of the arc-shaped bar 10, bosses 16 are fixedly connected to the lower sides of two ends of the track plate 15, a threaded rod 13 is arranged between the two bosses, the outside of threaded rod 13 is fixed the cover and is equipped with slider 14, and the fixed embedding of the downside of slider 14 is equipped with angular displacement sensor 17, and angular displacement sensor 17's output fixedly connected with driving lever 18.

The bottom end of a shifting rod 18 extends into a groove on the clamping fork 7, the shifting rod 18 is in an L-shaped structure, the shifting fork 3 drives the shifting rod 18 to rotate, a threaded rod 13 is in threaded connection with a sliding block 14, the sliding block 14 is in sliding connection with a track plate 15 and is convenient to adjust, a knob 12 is in a regular hexagon structure and is convenient to screw and rotate, and the arc-shaped groove 9 and the arc-shaped strip 10 are bonded through sealing glue and have a sealing effect.

Specifically, when the utility model is used, the extension rod 6 is connected with the guide rod of the steering system of the front wheel 8 of the airplane, the direction of the extension rod 6 is adjusted by the guide rod, when the swing amplitude of the angular displacement sensor 17 is adjusted, the knob 12 needs to be rotated by a wrench, the threaded rod 13 is rotated, and the thread driving slider 14 moves along the track plate 15, so that the shift rod 18 can slide in the groove of the shift fork 3, and further the linear distance between the shift rod 18 and the steering rod 2 is changed, when the clamping fork 7 drives the steering rod 2 to adjust the angle, the shift fork 3 can shift the shift rod 18 to rotate, and further the output shaft of the angular displacement sensor 17 is driven to rotate, thereby the angular displacement of the shift fork 3 and the steering rod 2 is fed back in real time, further, the closer the distance between the shift rod 18 and the steering rod 2, the smaller the swing amplitude of the shift rod 18, the farther the distance between, this design allows for a larger selection space for the angular displacement sensor 17.

In the description of the present invention, it is to be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "other end", "upper", "one side", "top", "inner", "front", "center", "both ends", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

Furthermore, the terms "first", "second", "third", "fourth" are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated, whereby the features defined as "first", "second", "third", "fourth" may explicitly or implicitly include at least one such feature.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "disposed," "connected," "fixed," "screwed" and the like are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, and may be connected through the inside of two elements or in an interaction relationship between two elements, unless otherwise specifically defined, and the specific meaning of the above terms in the present invention will be understood by those skilled in the art according to specific situations.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The angle feedback device of the aircraft front wheel steering system is characterized by comprising a steering cylinder (1), a steering rod (2) is embedded in the steering cylinder (1), a clamp fork (7) is fixedly connected to the bottom end of the steering rod (2), limiting rings (5) are fixedly sleeved on the outer walls of the two ends of the steering rod (2), a shifting fork (3) is fixedly sleeved on the outer wall of the middle of the steering rod (2), a front wheel (8) is embedded in the clamp fork (7), two extension rods (6) are symmetrically arranged on the outer wall of the top end of the clamp fork (7), a convex ring (4) is fixedly connected to one side of the steering cylinder (1), an arc-shaped groove (9) is formed in one side of the convex ring (4), an arc-shaped strip (10) is embedded in the arc-shaped groove (9), a countersunk groove (11) is formed in the outer side of the arc-shaped strip (10), and a track plate (15) is fixedly connected to the inner wall of the, equal fixedly connected with boss (16) of both ends downside of track board (15), two be equipped with threaded rod (13) between boss (16), the one end of threaded rod (13) all passes arc strip (10) and extends to countersunk head groove (11) in, threaded rod (13) end fixedly connected with knob (12), the outside fixed cover of threaded rod (13) is equipped with slider (14), the fixed embedding of downside of slider (14) is equipped with angle displacement sensor (17), the output fixedly connected with driving lever (18) of angle displacement sensor (17).

2. The angle feedback device of an aircraft nose wheel steering system according to claim 1, wherein the bottom end of the deflector rod (18) extends into a groove on the fork (7), and the deflector rod (18) is in an L shape.

3. The angle feedback device of an aircraft nose wheel steering system according to claim 1, wherein: the threaded rod (13) is in threaded connection with the sliding block (14), and the sliding block (14) is in sliding connection with the track plate (15).

4. The angle feedback device of an aircraft nose wheel steering system according to claim 1, wherein: the knob (12) is in a regular hexagonal structure.

5. The angle feedback device of an aircraft nose wheel steering system according to claim 1, wherein: the arc-shaped groove (9) is bonded with the arc-shaped strip (10) through sealing glue.