CN111731473A - An aircraft landing gear wheel synchronization device - Google Patents

Abstract

The invention discloses an aircraft landing gear wheel synchronizing device, which is installed on the wheel. The wheel includes a wheel hub and a tire mounted on the wheel hub. A plurality of air ducts are evenly installed on the circumference of the wheel hub. One end is closed, and the diameter of the air duct is gradually reduced from the open end to the closed end; the forward direction of the aircraft is assumed to be the straight-line traveling direction, and the installation direction of the air duct satisfies the following conditions: when the air duct is located directly below the center point of the wheel, the air The open end of the barrel is facing the forward direction of the aircraft. The invention installs a plurality of air ducts on the hub of the wheel to drive the wheel to rotate, so that the wheel reaches a higher rotational speed before hitting the ground, the impact force received when it contacts the ground is significantly reduced, the friction is reduced, and the solution is greatly reduced. The impact force is greatly increased, the stability of the aircraft landing is significantly increased, and a "soft landing" is truly realized, avoiding difficult problems such as the breaking of the landing gear and the tire burst when the aircraft is landing.

Description

An aircraft landing gear wheel synchronization device

technical field

The invention relates to a matching device for aircraft landing gear, in particular to a wheel synchronizing device for aircraft landing gear.

Background technique

In today's world aviation field, the landing gear of the aircraft is often broken or the tire blows out when the aircraft is landing, and the loss cannot be estimated. Analyze the reasons. Because the wheels on the landing gear of the aircraft touch the ground and contact the ground with high-speed and high-pressure friction, when the tires are stationary To increase the speed to the flight speed of the aircraft in an instant, it is necessary to overcome the huge resistance, which directly acts on the tires, causing huge friction between the tires and the ground. Breaking leads to disaster.

To sum up, the problem of strong friction with the ground caused by the asynchrony between the wheels and the aircraft can be solved only by accelerating the wheels to the flight speed when the aircraft lands. Experienced captains use the "water point" method to buffer the impact force of the ground on the tires. Then the impact force when the wheel touches the ground will be significantly reduced, which can protect the aircraft and reduce safety accidents.

SUMMARY OF THE INVENTION

An object of the present invention is to provide an aircraft landing gear wheel synchronizing device capable of rotating the wheels at high speed before contacting the ground when the aircraft lands in order to solve the above problems.

The present invention realizes above-mentioned purpose through following technical scheme:

An aircraft landing gear wheel synchronizing device is mounted on a wheel, the wheel includes a hub and a tire mounted on the hub, the aircraft landing gear wheel synchronizing device includes a plurality of air ducts, a plurality of The air duct is evenly installed on the circumference of the hub, one end of the air duct is open and the other end is closed, and the diameter of the air duct is gradually reduced from the open end to the closed end; The installation direction of the air duct satisfies the following conditions: when the air duct is located just below the center point of the wheel, the open end of the air duct is facing the forward direction of the aircraft.

In the above structure, the air duct is used to drive the wheels to rotate under the action of wind resistance after the landing gear of the aircraft is opened. state; with the extension of the time after the landing gear is opened, the rotation speed of the wheel is getting closer and closer to the rotation speed corresponding to the flight speed of the aircraft. ; The number of air ducts is determined according to needs, and multiple air ducts can be installed in the inner and outer circumferential directions of the hub.

Preferably, in order to minimize the resistance when the closed end of the air duct is subjected to wind resistance on the premise of ensuring that the open end of the air duct is driven to rotate by wind resistance, one side of the air duct is close to the circumferential wall of the hub and the two arcs are the same, The opposite side of the air duct gradually approaches the wheel hub from the open end to the closed end until the two sides converge at a point and are in a convex arc shape.

Preferably, in order to stabilize the connection and minimize the wind resistance of the closed end of the air duct, the side of the air duct that is close to the circumferential wall of the hub is welded and connected to the hub.

According to requirements, the air duct is installed on one side or both sides of the wheel hub.

The beneficial effects of the present invention are:

In the present invention, a plurality of air ducts are installed on the hub of the wheel, and the open end of the air duct is driven to rotate by the wind when it is subjected to wind resistance, so as to drive the wheel to rotate, so that the wheel can reach a higher rotational speed before landing on the ground and contact the ground. The impact force received during the time is significantly reduced, the friction is reduced, the impact force is greatly resolved, the stability of the aircraft landing is significantly increased, and a "soft landing" is truly realized, avoiding the breaking of the landing gear and the tire burst when the aircraft is landing. Tough question.

Description of drawings

Fig. 1 is a schematic front view of the structure of the wheel synchronizing device of an aircraft landing gear according to the present invention, and the left side in the figure is the forward direction of the aircraft.

Detailed ways

The present invention will be further described below in conjunction with the accompanying drawings:

As shown in FIG. 1 , the wheel synchronizing device of the aircraft landing gear of the present invention is installed on the wheel 1, and the wheel 1 includes a hub 12 and a tire 11 mounted on the hub 12. The aircraft landing gear wheel synchronizing device includes A plurality of air ducts 2, the plurality of air ducts 2 are evenly installed on the circumference of the hub 12, one end of the air duct 2 is open and the other end is closed, and the diameter of the air duct 2 gradually decreases from the open end 22 to the closed end 21; The traveling direction (left side in the figure) is the straight traveling direction, and the installation direction of the air duct 2 satisfies the following conditions: when the air duct 2 is located directly below the center point of the wheel 1, the open end 22 of the air duct 2 is facing the front of the aircraft row direction.

Preferably, one side of the air duct 2 is close to the circumferential wall of the hub 12 and the two arcs are the same, and the opposite side of the air duct 2 gradually approaches the hub 12 from the open end 22 to the closed end 21 until the two sides converge at a point and In the shape of an outward convex arc, the side of the air duct 2 close to the circumferential wall of the hub 12 is welded and connected with the hub 12 ; the air duct 2 is installed on one or both sides of the hub 12 .

As shown in Figure 1, the working principle of the wheel synchronizing device of the aircraft landing gear of the present invention is as follows:

The aircraft will open the landing gear before landing, and the wheel 1 installed on the landing gear will be exposed to the air after extending below the aircraft. The airflow direction is opposite to the forward direction of the aircraft. When going down, the air flow will generate a thrust on the open end 22 of the blower 2, and the thrust is the largest when the blower 2 is located directly below the center point of the wheel 1. The thrust pushes the blower 2 to drive the wheel 1 to rotate, and the rotation direction is It is counterclockwise in the figure, which just corresponds to the forward direction of the aircraft; when the air duct 2 is located above the center point of the wheel 1, the airflow will produce resistance to the closed end 21 of the air duct 2 and the outer wall of the cylinder, but due to the wind The open end 22 of the drum 2 is larger than the closed end 21, so the resistance is smaller than the above-mentioned thrust, so the air drum 2 will drive the motor wheel 1 to rotate and the rotation speed will increase. At the moment when the wheel 1 hits the ground, the impact force between the wheel 1 and the ground will be significantly reduced compared to the static state, reducing friction, greatly resolving the impact force, and significantly increasing the stability of the aircraft's landing. A "soft landing" is achieved, which avoids difficult problems such as broken landing gear and tire burst when the plane lands.

In addition, the time for opening the landing gear can be advanced as required, so that the air cylinder 2 drives the wheel 1 to accelerate for a longer time. It is also possible to combine the active driving mode of the wheel 1 to maximize the rotation speed of the wheel 1 before it contacts the ground. Raise it to match the flight speed, so that the plane will land more smoothly.

The above-described embodiments are only preferred embodiments of the present invention, and are not intended to limit the technical solutions of the present invention. As long as the technical solutions that can be realized on the basis of the above-described embodiments without creative work, all should be regarded as falling into the patent of the present invention. within the scope of protection of rights.

Claims (4)

1. An aircraft landing gear wheel synchronisation device mounted on a wheel comprising a hub and a tyre mounted on the hub, characterised in that: the airplane wheel synchronizing device of the airplane landing gear comprises a plurality of air ducts, the air ducts are uniformly arranged on the circumference of the hub, one end of each air duct is open, the other end of each air duct is closed, and the diameter of each air duct is gradually reduced from the open end to the closed end; the advancing direction of the airplane is set as the straight advancing direction, and the installation direction of the air duct meets the following conditions: when the air duct is positioned under the central point of the airplane wheel, the opening end of the air duct is over against the advancing direction of the airplane.

2. An aircraft landing gear wheel synchronisation device according to claim 1, wherein: one side of the air duct is close to the circumferential wall of the hub and has the same radian with the circumferential wall of the hub, and the opposite other side of the air duct is gradually close to the hub from the opening end to the closed end until the two sides are gathered together at one point and are in an outward convex arc shape.

3. An aircraft landing gear wheel synchronisation device according to claim 2, wherein: and one side of the air duct close to the circumferential wall of the hub is connected with the hub in a welding manner.

4. An aircraft landing gear wheel synchronisation device according to claim 1, 2 or 3, wherein: the air duct is installed on one side or two sides of the hub.

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