ES1291114U - Aeronautical wheel (Machine-translation by Google Translate, not legally binding) - Google Patents

Abstract

Aeronautical wheel, which includes a tire (21) and a tire (22), characterized by which it includes a tapacubos (3) with a series of fins (4) radials configured to produce the wheel turn (2) with the airspeed. (Machine-translation by Google Translate, not legally binding)

Description

DESCRIPTION

aeronautical wheel

TECHNICAL SECTOR

The present application refers to an improved aeronautical wheel, which reduces the friction due to landing and therefore its wear.

STATE OF THE ART

Airplanes have to land at a high speed in order to maintain their lift in the air. Therefore, when the wheel comes into contact with the ground, since its rotation speed is zero, it rubs against the runway, accelerating its rotation speed until its linear speed equals the speed of the aircraft. This friction burns and wears the tire, greatly reducing its useful life. In addition, the remains of the tire remain attached to the runway, forcing its periodic cleaning for safety, with the consequent cost and stoppage of aeronautical operations during maintenance.

The applicant is not aware of any device similar to the invention.

BRIEF EXPLANATION OF THE INVENTION

The invention consists of an aeronautical wheel according to the first claim and whose variants solve the problems of the state of the art.

The wheel comprises a tire and a rim. Also, a hubcap with a series of radial fins configured to spin the wheel using airspeed relative to the aircraft once the wheels are deployed for landing. The turn will be in the direction in which it will roll once it has landed.

This system solves the problem of high wear of the wheel with low cost of materials, design and assembly, increasing the durability of the set.

The system hardly requires maintenance, being light and of immediate application in any pre-existing aircraft, given that it does not modify the approved flight conditions. Instead, it enables faster braking initiation by getting the wheels into the right condition sooner, and reduces the risk of aquaplaning.

It is usable in all types of aircraft with drop-down wheels, but much more profitable in large aircraft, where, due to its greater weight, greater wear due to friction of the tires with the landing strips.

Preferably, the hubcap wings are of variable geometry to achieve limited final speed.

Likewise, the wheel may comprise one or more speed and ground speed sensors, associated with a brake, which will normally be the aircraft's own.

Other variants are seen in the rest of the report.

DESCRIPTION OF THE FIGURES

For a better understanding of the invention, the following figure is included.

Figure 1: Schematic side view of an example of embodiment.

MODES OF EMBODIMENT OF THE INVENTION

Next, an embodiment of the invention is briefly described, as an illustrative and non-limiting example of the latter.

Figure 1 shows an example of an embodiment applied to a landing gear (1) of a fixed-wing aircraft with two visible wheels (2). These landing gear (1) have a series of wheels (2), depending on the weight of the aircraft and other factors. Thus, a small plane may have only one wheel (2) on each side, plus a simpler rear, while an Airbus A380 will have 22 wheels (2) in total.

The wheels (2) have a tire (21) and a rim (22). This rim (22) is covered by a hubcap (3), according to the invention. The hubcap (3) has a series of radial fins (4) that convert the relative speed of the wind into the rotation of the wheel (2), similar to an anemometer. In this way, once the landing gear (1) is deployed, the wheels (2) pick up speed of rotation, so that when they contact the ground they are already at a speed equal to that of the plane with respect to the ground or close to it, greatly reducing wear due to friction with the ground.

The hubcap (3) can be fixed by means of screws or other elements

The shape and number of the fins (4) will be defined depending on the aircraft for which it is arranged, mainly depending on the weight of the wheel (2) and the expected landing speed. It must be considered that the landing speed can vary depending on the airport (height above sea level, for example) and the conditions at the time (pressure, rain, wind force...), so the landing speed It has to be estimated, either by the average of the design range, as a statistical mode. Every plane and every airline can have an estimated landing speed.

Being a hubcap (3), it is easily applicable to any existing wheel (2).

The turning speed of the wheels (2) at the moment of landing can also be adjusted, automatically or manually. For example, a speed of rotation sensor can be applied, by mechanical, electromechanical or optical means that estimates the speed on the ground to which that speed of rotation corresponds. If it is excessive, you can act on the brakes to adjust the speed. A sensor of contact or proximity to the ground would deactivate the brake when touching the ground, so as not to affect the pilot activities. For example, it can be a vertical ground distance sensor.

Likewise, the fins (4) can be of variable geometry by means of mechanisms that remove or hide the fins (4) or change their curvature. For example, they can be mechanisms based on centrifugal force. This variable geometry makes it possible to obtain a more constant and limited maximum turning speed, bearing in mind that it would always be in relation to the air and its speed with respect to the plane and not in relation to the ground. One ^{embodiment is by means of eccentric masses, connected by articulated arms} to the wheel axle. When turning, the masses open by centrifugal force, affecting the moment of inertia of the wheel-hubcap assembly, and reaching a dynamic balance. The arms in turn are connected to the fins (4), so that when they move by centrifugal force they modify the useful shape of the fins (4).

Claims (1)

1- Aeronautical wheel, comprising a tire (21) and a rim (22), characterized in that it comprises a hubcap (3) with a series of radial fins (4) configured to rotate the wheel (2) with the airspeed. 2- Aeronautical wheel, according to claim 1, characterized in that the ^{wings (4) are of variable geometry.} 3- Aeronautical wheel, according to claim 1, characterized in that it comprises a speed sensor associated with a brake.