CN210734487U

CN210734487U - Low-wear aircraft tire

Info

Publication number: CN210734487U
Application number: CN201921675786.1U
Authority: CN
Inventors: 王林
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-09-30
Filing date: 2019-09-30
Publication date: 2020-06-12
Anticipated expiration: 2029-09-30

Abstract

The utility model relates to a low wearing and tearing aircraft tire, include: the tire body is connected with an undercarriage of an airplane; the plurality of the convex parts are arranged along the axial end face of the tire body and are uniformly arranged along the circumferential direction of the tire body; each lug boss is provided with a first inclined plane and a second inclined plane along the tangential direction of the tire body, the included angle between the first inclined plane and the axial side face of the tire body is smaller than the included angle between the second inclined plane and the axial side face of the tire body, and the first inclined plane at the lower part of the tire body is arranged corresponding to the advancing direction of the airplane, so that the airplane can advance in the process. The utility model discloses tire and ground contact instantaneous relative speed when reducing the aircraft and descending have effectively reduced the frictional force on tire and ground, therefore have reduced the ground and to the wearing and tearing of tire, have prolonged the life of tire, and the longer number of times can be used to the same tire material model, saves the cost, can avoid the aircraft to take place to blow out the problem basically moreover, solves the potential safety hazard.

Description

Low-wear aircraft tire

Technical Field

The utility model relates to a low wearing and tearing aircraft tire.

Background

In the prior art, all airplanes adopt a landing mode that a rear wheel is grounded firstly, because most rear main wheels of the airplanes are main bearing wheels, and the rear main wheels are grounded firstly, so that most of the weight of an airplane body can be borne, and secondly, the lifting force of the airplane is increased by lifting a nose when the airplane lands on the ground, so that the airplane can land on the ground lightly at a low speed; but the rear side tire does not basically rotate when the aircraft lands at present, because the aircraft weight is very big, inertia is big when falling to the ground, make the relative velocity on tire and ground very big, can cause the serious wearing and tearing of tire, tire and ground looks mutual friction can both produce the macroscopically dense smoke when landing, current aircraft tire needs periodic replacement, general civil aviation passenger plane landing number of times just needs to be changed the tire about 200, the use cost of aircraft tire has been improved greatly, and when the tire was in fatigue state, ground service staff holds when not good change frequency, the tire bursts in the twinkling of an eye easily because of the aircraft landing, the condition that the aircraft landing takes place the tire burst also takes place occasionally when reality uses, there is very big potential safety hazard.

SUMMERY OF THE UTILITY MODEL

The utility model provides a low-wear aircraft tire, which has reasonable structural design, reduces the instantaneous relative speed of the contact between the tire and the ground when the aircraft lands, effectively reduces the friction force between the tire and the ground, thereby reducing the abrasion of the ground to the tire, prolonging the service life of the tire, using the same tire material model for a longer time, saving the cost, basically avoiding the problem of tire burst of the aircraft and solving the potential safety hazard; in addition, the moment of inertia generated by the rotation of the tire of the airplane can play a certain stabilizing role in the airplane taking off or landing to a certain extent, and the problems in the prior art are solved.

The utility model discloses a solve the technical scheme that above-mentioned technical problem adopted and be: a low wear aircraft tire, comprising:

the tire body is connected with an undercarriage of an airplane;

the plurality of the convex parts are arranged along the axial end face of the tire body and are uniformly arranged along the circumferential direction of the tire body; every the bellying is followed the tangential direction of tire body is formed with first inclined plane and second inclined plane, the first inclined plane with the contained angle of tire body axial side is less than the second inclined plane with the contained angle of tire body axial side, the tire body lower part position first inclined plane with the aircraft direction of advance sets up correspondingly, makes the aircraft in the in-process of advancing, the windage that the first inclined plane of bellying bore is greater than the windage that the second inclined plane bore, so that the tire body produces the corotation the same with aircraft direction of advance.

Furthermore, the convex parts are symmetrically arranged along two axial side surfaces of the tire body.

Furthermore, the protruding portions are of wedge-shaped structures, and the plurality of protruding portions are annularly arranged along the circumferential direction of the tire body.

Further, at least one of the convex parts is arranged along the radial direction of the tire body.

Further, the protruding portions are of strip structures, and the protruding portions of the strip structures are arranged along the radial direction of the tire body.

Further, the convex part is an arc-shaped structure arranged along the radial direction of the tire body.

Furthermore, one side of the inner arc surface of the arc-shaped structure protruding part positioned at the lower part of the tire body is arranged corresponding to the advancing direction of the airplane.

The utility model adopts the above structure has the advantages that the structure design is reasonable, the relative speed of the tire and the ground in the moment of contact is reduced when the airplane lands, and the friction force between the tire and the ground is effectively reduced, so that the abrasion of the ground to the tire is reduced, the service life of the tire is prolonged, the same tire material model can be used for a longer time, the cost is saved, the problem of tire burst of the airplane can be basically avoided, and the potential safety hazard is solved; in addition, the moment of inertia generated by the rotation of the aircraft tire can play a certain stabilizing role on the aircraft taking off or landing.

Drawings

Fig. 1 is a schematic structural diagram of a first embodiment of the present invention.

Fig. 2 is a schematic view of a partial cross-sectional structure of the protruding portion of the present invention.

Fig. 3 is a schematic structural diagram of a second embodiment of the present invention.

Fig. 4 is a schematic structural diagram of a third embodiment of the present invention.

In the figure, 1, a tire body; 2. a boss portion; 3. a first inclined plane; 4. a second inclined plane.

Detailed Description

In order to clearly illustrate the technical features of the present invention, the present invention is explained in detail by the following embodiments in combination with the accompanying drawings.

In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application, however, the present application may be practiced in other ways than those described herein, and therefore the scope of the present application is not limited by the specific embodiments disclosed below.

In addition, in the description of the present application, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", and the like, indicate orientations and positional relationships based on those shown in the drawings, are only for convenience of description and simplicity of description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present application.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.

In this application, unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections, removable connections, or integral parts; the connection can be mechanical connection, electrical connection or communication; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

In this application, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through intervening media. In the description herein, reference to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

As shown in fig. 1-4, a low-wear aircraft tire comprises a tire body 1 and a boss 2, wherein the tire body 1 is connected with an aircraft landing gear; a plurality of the convex parts 2 are arranged along the axial end face of the tire body 1, and the convex parts 2 are uniformly arranged along the circumferential direction of the tire body 1; every bellying 2 is formed with first inclined plane 3 and second inclined plane 4 along the tangential direction of tire body 1, the contained angle of first inclined plane 3 and tire body 1 axial side is less than the contained angle of second inclined plane 4 and tire body 1 axial side, the first inclined plane 3 and the aircraft direction of advance of tire body 1 lower part position set up correspondingly, make the aircraft in the in-process of advancing, the windage that the first inclined plane 3 of bellying 2 bore is greater than the windage that the second inclined plane 4 bore, so that make tire body 1 produce the corotation the same with aircraft direction of advance. When the tire is used, the relative speed of the tire body 1 at the moment of contact with the ground when an airplane lands is reduced, and the friction force between the tire body 1 and the ground is effectively reduced, so that the abrasion of the ground to the tire body 1 is reduced, the service life of the tire is prolonged, the tire with the same material model can be used for a longer time, the cost is saved, the problem of tire burst of the airplane can be basically avoided, and the potential safety hazard is solved; in addition, the moment of inertia generated by the rotation of the aircraft tire can play a certain stabilizing role on the aircraft taking off or landing.

In the preferred embodiment, the protrusions 2 are symmetrically arranged along both axial sides of the tire body 1. During the use, set up bellying 2 and also can make tire body 1 rotate at tire body 1's axial unilateral, compare the mode that axial bilateral symmetry set up bellying 2 in this embodiment, the unilateral sets up the tire body 1 of bellying 2 and is relatively low in the rotation efficiency under same wind-force condition, nevertheless can also take place to rotate, play certain effect, under the comparison, bellying 2 sets up the atress that can make whole tire more balanced along tire body 1's axial bilateral symmetry, tire body 1's rotation effect is better.

In a preferred embodiment, specifically, the protruding portion 2 is provided with a wedge-shaped structure, and the plurality of protruding portions 2 are annularly arranged along the circumferential direction of the tire body 1. The bulge 2 with the wedge-shaped structure can effectively express the structural characteristics of the first inclined surface 3 and the second inclined surface 4 as a specific implementation mode of the scheme, so that the combination of the tire body 1 and the bulge 2 is more effective, and the bulge 2 is favorable for pushing the tire body 1 to rotate after receiving wind power.

In a preferred embodiment, the raised portion 2 is provided with at least one in the radial direction of the tire body 1.

As shown in fig. 3, specifically, the protruding portion 2 is provided as a strip structure, and a plurality of protruding portions 2 of the strip structure are arranged along the radial direction of the tire body 1.

As shown in fig. 4, in the preferred embodiment, the convex portion 2 is provided in an arc-shaped configuration disposed in the radial direction of the tire body 1.

In the preferred embodiment, the intrados side of the arc-shaped structural protrusion 2 located at the lower position of the tire body 1 is disposed corresponding to the advancing direction of the aircraft.

When the aircraft taking-off or landing gear is in a put-down state, the first inclined surface 4 of the boss 2 facing the flight direction and located below the aircraft tire body 1 bears a larger wind resistance coefficient, and the second inclined surface 4 bears a small wind resistance coefficient.

The above-mentioned specific embodiments can not be regarded as the restriction to the scope of protection of the utility model, to technical personnel in this technical field, it is right the utility model discloses any replacement improvement or transform that embodiment made all fall within the scope of protection of the utility model.

The parts of the present invention not described in detail are the known techniques of those skilled in the art.

Claims

1. A low wear aircraft tire, comprising:

the tire body is connected with an undercarriage of an airplane;

2. A low wear aircraft tire according to claim 1, wherein said raised portions are symmetrically disposed along both axial sides of said tire body.

3. A low wear aircraft tire according to claim 1 or 2, wherein said lugs are provided in a wedge-like configuration, and a plurality of said lugs are arranged annularly along the circumferential direction of said tire body.

4. A low wear aircraft tire according to claim 3, wherein said raised portion is provided with at least one in a radial direction of said tire body.

5. A low wear aircraft tire according to claim 1 or 2, wherein said raised portion is provided as a bar-shaped structure, said raised portions of a plurality of bar-shaped structures being arranged in a radial direction of said tire body.

6. A low wear aircraft tire according to claim 1 or 2, wherein said raised portion is provided as an arcuate structure disposed radially along said tire body.

7. A low-wear aircraft tire according to claim 6, wherein the intrados side of the arcuate structural lugs at the lower portion of the tire body is disposed in correspondence with the direction of travel of the aircraft.