KR20200025726A - landing system of airplane - Google Patents

Abstract

Provided in the present invention is a landing system of an airplane, which comprises: a lower supporter configured on the outside of a landing gear; an upper supporter connected to the lower supporter; a locking device fastening the upper supporter to the lower supporter; and a hydraulic cylinder which can release the locked state of the locking device. Therefore, according to the present invention, the locking device can be embodied through a simple device structure, such that a complicated link structure design becomes unnecessary. In addition, the restrictions of an outer interface can be reduced when the landing gear is folded and unfolded. Moreover, the quick operation of the device can release the locked state, thereby smoothly continuing following processes. In addition, the locking device can be embodied by a small-scale device, thereby minimizing the weight. Furthermore, as the locking device is installed at a link hinge unit to allow the landing gear to be folded and unfolded, a solid locking structure can be embodied.

Description

Landing system of airplane

 The present invention relates to a landing system for safe landing of an aircraft.

Landing system of the conventional aircraft as shown in Figure 1 is configured with a locking device inside the hydraulic actuator, the components to implement the locking function in the hydraulic actuator is located to prevent leakage as the sealing portion for sealing the hydraulic oil increases Design is required and manufacturing and maintenance costs are increased.

In addition, since the components inside the hydraulic actuator cannot be checked for abnormalities with the naked eye at all times, problems such as component wear and damage cannot be checked in advance, and since the locking device is composed of a complicated mechanism structure, The large number increases the weight and increases the manufacturing and assembly costs.

In addition, since the spring for the mechanism operation is exposed to the outside, the locking device loses its function in case of damage due to external impact.

The present invention is to solve the problems of the prior art, the landing structure of the landing device during the landing and ground cycle of the aircraft is firmly maintained, implement a locking mechanism that can maintain the expansion structure with a simple mechanical structure and hydraulic cylinder It is intended to provide a landing system for an aircraft.

Landing system of the aircraft according to the present invention provided to achieve the above object is a lower support configured on the outside of the landing device, an upper support connected to the lower support, a locking device and the lock to bind the upper support and the lower support The unlocking device of the device comprises a hydraulic cylinder.

According to the present invention as described above, it is possible to implement a locking device with a simple mechanism structure, so that no complicated link structure design is required, and the constraint of the external interface when folding and unfolding the landing device can be reduced, and the locking can be quickly performed. It can be released so that subsequent operations can be performed smoothly, and the locking device can be implemented with a small device to minimize weight, and the locking device is installed at the link hinge for folding and unfolding the landing device. Can be implemented.

1 is a view showing the configuration of the present invention
2 is a view showing the configuration of the present invention (landing device unfolded state)
3 is a view showing the configuration of the present invention (landing device folded state)
4 is a diagram showing the main components of the present invention.
5 is a view showing a locking device locked state in the present invention;
Figure 6 is a view showing a lock release state in the present invention

Hereinafter, with reference to the accompanying drawings, specific details for carrying out the present invention will be described in detail.

After the landing device is unlocked as shown in FIG. 2 according to the present invention, the landing device is folded as shown in FIG. 3 by the operation of the hydraulic actuator.

The locking device is implemented with a locking structure in the following principle.

In order to maintain the landing device extended state of FIG. 2, the upper support and the lower support of FIG. 1 should not be rotated based on the hinge point of FIG. 4.

In order to satisfy the above condition, the distance between A point and B point of FIG. 4 may be fixed.

C point is generated by using link 1 of FIG. 4, and B and C points are connected to link 2.

Point C of Figure 4 should be located on the support side relative to the A-B point extension line (left side of the extension line)

When the distance between point A and point B decreases or increases due to external force, link 2 generates a turning force to move the point C to the left of the A-B point extension line.

However, at this time, while the link 1 is fixed by the restraint surface of FIG. 3, the distance between the A point and the B point is fixed, and since the distance between the A-B points is not changed by the external force, the landing device is expanded.

The lock is released by the following operation.

The locking structure must be released to implement the landing gear folded state of FIG. 3.

The link 1 is pushed by the spring force in the hydraulic cylinder of FIG. 5, and the link 1 is in contact with the restraint surface.

When the hydraulic pressure is supplied to the hydraulic cylinder of FIG. 5, the hydraulic force opposite to the spring force acts so that the link 1 is separated from the restraining surface, thereby releasing the locked state as shown in FIG. 6.

Claims (1)

And a lower support configured outside the landing device, an upper support connected to the lower support, a locking device for engaging the upper support and the lower support, and an unlocking hydraulic cylinder of the lock.

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