KR101192497B1

KR101192497B1 - Rotating test module for aircraft rotor having balance weight

Info

Publication number: KR101192497B1
Application number: KR20100035882A
Authority: KR
Inventors: 하해용
Original assignee: 한국항공우주산업 주식회사
Priority date: 2010-04-19
Filing date: 2010-04-19
Publication date: 2012-10-17
Also published as: KR20110116459A

Abstract

The present invention relates to a rotating test body module for an aircraft rotor having a balance weight to form a balance weight on the rotating test body module mounted to the main rotor or tail rotor of the aircraft so that the rotor blades can rotate more stably. The present invention is rotatable about a main rotor blade formed in the main rotor and rotated about a gas at a first face oriented to provide vertical lift to the body, and a transverse axis parallel to the first face at the tail of the body. And a thrust component parallel to the first plane, adapted to rotate on a second plane parallel to the longitudinal axis of the plane and having a small angle to the vertical axis of the plane. 10. An aircraft comprising a tail rotor blade formed on a tail rotor and oriented to provide the tail of the body in a direction to stabilize the aircraft and oriented to provide a vertical lift thrust component to the tail of the body; A cylindrical rotating test module module is formed on the center line of the tail rotor, wherein the rotating test module module includes: Forms at least one or more balance weights to the test body rotation module upper or lower end of the mold. Therefore, by preventing the CG offset that may occur from the center of rotation, to prevent the vibration due to unbalance, and also to prevent the vibration to prevent the damage of the main rotor blades or tail rotor blades, it is possible to prevent damage to the PCM equipment have.

Description

Rotating test module for aircraft rotor having balance weight

The present invention relates to a rotating test body module for an aircraft rotor, and more particularly, to form a balance weight on a rotating test module mounted on a main rotor or a tail rotor of an aircraft, so that the rotor blade can rotate more stably. The present invention relates to a rotating test module module for an aircraft rotor.

In general, a helicopter (Helicopter) is a main rotor installed on the upper part of the fuselage, that is, an aircraft capable of rotating up and down almost vertically without a runway by rotating a main rotor, which can move in forward, backward, and left and right directions. Of course, it has a functional feature that can be stopped in the air.

At this time, a tail rotor (ie, auxiliary rotor blade) is further installed in the tail portion of the fuselage to prevent the fuselage of the helicopter from being rotated together and maintain the direction due to the rotation of the main rotor. There is also disclosed a form in which two rotors are installed and rotated in opposite directions to prevent rotation of the fuselage.

The tail rotor, including the main rotor, is a very important member for the flight of the helicopter, and can be equipped with a rotating test module module such as a flight code modulator (PCM) device for flight testing.

As such, when the flight test PCM equipment is mounted on the main rotor of the aircraft, there is a possibility that a CG offset is generated from the center of rotation, and when a CG offset occurs, vibration due to unbalance occurs.

In addition, if the PCM equipment falls down due to the vibration of the entire aircraft, the mounting load of the PCM equipment, and the damage of the PCM bolt due to the vibration, the main blade, the tail blade, and the PCM equipment may be damaged. There was also a problem.

The present invention has been made to solve the above problems, by forming a balance weight on the rotating test module module mounted on the main rotor or tail rotor of the aircraft aircraft rotor having a balance weight to enable the rotor blades to rotate more stably The purpose is to provide a rotational test specimen module.

Rotation test body module for an aircraft rotor having a balance weight according to the present invention for achieving the above object is a test body module for an aircraft rotor to test the rotation with respect to the main rotor or tail rotor of the rotorcraft, the rotation test body for the aircraft rotor The module may be a PCM device, wherein the PCM device is mounted and detached on an outer center line of the main rotor or tail rotor, and the PCM device includes at least one balance weight along a cylindrical circumference at an upper end or a lower end. By providing a rotation test body module for an aircraft rotor having a balance weight, characterized in that to prevent the rotor rotation imbalance caused by the mounting of the PCM equipment.

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The rotating test module is a PCM (Pulse Code Modulator) equipment, the rotating test module is more preferably formed in the form of a ring in the center hollow.

According to the rotation test body module for an aircraft rotor having a balance weight according to the present invention configured as described above, by forming a balance weight on a rotating test body module mounted on the main rotor or tail rotor of the aircraft so that the rotor blades can rotate more stably. By doing so, it is possible to prevent the CG offset that may occur from the rotation center, and to prevent the vibration due to unbalance (Unbalance).

In addition, it is possible to prevent the vibration of the main rotor blade or tail rotor blade by preventing the vibration, it is possible to prevent the damage of the PCM equipment.

1 is a plan view of a helicopter for showing a rotating test body module for an aircraft rotor having a balance weight according to the present invention.
Figure 2 is a view showing a first embodiment of a rotary test body module for an aircraft rotor having a balance weight according to the present invention.
Figure 3 is a view showing a second embodiment of a rotary test body module for an aircraft rotor having a balance weight according to the present invention.
Figure 4 is a view showing a third embodiment of the rotary test body module for an aircraft rotor having a balance weight according to the present invention.
5 is a view showing a fourth embodiment of a rotating test body module for an aircraft rotor having a balance weight according to the present invention;

Hereinafter, the present invention will be described in detail with reference to the preferred embodiments of the present invention with reference to the accompanying drawings. It is to be understood that the words or words used in the present specification and claims are not to be construed in a conventional or dictionary sense and that the inventor can properly define the concept of a term in order to describe its invention in the best possible way And should be construed in light of the meanings and concepts consistent with the technical idea of the present invention. Therefore, the embodiments described in this specification and the configurations shown in the drawings are merely the most preferred embodiments of the present invention and do not represent all the technical ideas of the present invention. Therefore, It is to be understood that equivalents and modifications are possible. Here, like reference numerals in the drawings denote like elements.

1 is a plan view of a helicopter for showing a rotating test body module for an aircraft rotor having a balance weight according to the present invention.

As shown, the present invention includes a body 12, a main rotor blade 14, a main rotor 16, a tail rotor blade 20, a tail rotor 21, and a stabilizer plate 22.

As shown in FIG. 1, the aircraft 10 of the present invention includes a body 12 and a main rotor blade 14 that rotates about a rotor rotor main rotor 16. The aircraft 10 has a tail pylon 18, on top of which a tail rotor blade 20 is mounted on the tail rotor 21 that provides a tail thrust to the tail of the body 12. The aircraft does not rotate clockwise against the force of the rotor blade 14 rotating counterclockwise during flight.

To this end, the present invention provides a main rotor blade (14) formed in the main rotor (16) arranged to rotate with respect to the gas at a first surface oriented to provide vertical lift to the body (12), and the tail of the body (12). And a stabilizer plate 22 rotatably disposed about a horizontal axis parallel to the first surface, and adapted to rotate on a second surface parallel to the longitudinal axis of the body and having a small angle with respect to the vertical axis of the body 12. And to provide a thrust component parallel to the first surface to the tail of the gas in a direction stabilizing the gas against reverse rotational forces resulting from the rotation of the main rotor blades 14, and a vertical lift thrust component at the tail of the gas. A tail rotor blade 20 oriented to provide and formed in the tail rotor 21.

2 is a view showing a first embodiment of a rotating test body module for an aircraft rotor having a balance weight according to the present invention.

As shown, the present invention forms a cylindrical rotating test body module 30 on the centerline of each main rotor 16 of the aircraft 10, the rotary test body module 30, the cylindrical rotating test body At least one balance weight 31 is formed at an upper end of the module 30.

At this time, the rotation test body module 30 is preferably in the center of the hollow ring shape.

In addition, the rotation test body module 30 is more preferably a pulse code modulator (PCM) equipment.

3 is a view showing a second embodiment of a rotating test body module for an aircraft rotor having a balance weight according to the present invention.

As shown, the present invention forms a cylindrical rotating specimen module 30 on the centerline of each of the main rotors 16 of the aircraft 10, wherein the rotating specimen module 30, the cylindrical upper end circumferential surface A plurality of balance weights 31 are formed at least two or more so as to be symmetrical to the left and right surfaces facing each other.

Therefore, it is preferable that the shape is formed continuously along the circumferential surface similarly to the shape of a ring having a hollow state in the middle.

Figure 4 is a view showing a third embodiment of a rotary test body module for an aircraft rotor having a balance weight according to the present invention.

As shown, the present invention forms a cylindrical rotating specimen module 30 on the centerline of each of the main rotors 16 of the aircraft 10, wherein the rotating specimen module 30, the cylindrical upper end circumferential surface At least four of the balance weights 31 may be formed to be symmetrical with respect to the left and right surfaces facing each other.

5 is a view showing a fourth embodiment of the rotary test body module for an aircraft rotor having a balance weight according to the present invention.

As shown, the present invention forms a cylindrical rotating test body module 30 on the centerline of each main rotor 16 of the aircraft 10, the rotary test body module 30, the cylindrical rotating test body At least one balance weight 31 is formed at the upper and lower ends of the module 30, respectively.

At this time, the rotation test body module 30, PCM (Pulse Code Modulator) equipment, the shape of the ring is preferably.

Therefore, by forming a balance weight on the rotating test module module mounted on the main rotor or tail rotor of the aircraft to allow the rotor blades to rotate more stably, it prevents the CG offset that may occur from the center of rotation, unbalanced (unbalanced) In addition, by preventing the vibration, the vibration of the main rotor or tail rotor can be prevented by preventing the vibration, it is possible to prevent the damage of the PCM equipment.

It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined in the appended claims and their equivalents. Of course, such modifications are within the scope of the claims.

12 gas 14 main rotor blade
16: main rotor 20: tail rotor
21: tail rotor 22: stable plate
30: rotation test body module 31: balance weight

Claims

In the test body module for an aircraft rotor to test the rotation of the rotor rotor main rotor or tail rotor,
The rotational test body module for the aircraft rotor is PCM equipment, characterized in that the PCM equipment is mounted and detached on the outer center line of the main rotor or tail rotor,
The PCM equipment includes at least one or more balance weights along the cylindrical circumference at the upper end or the lower end, to prevent the rotor rotation imbalance due to the mounting of the PCM equipment rotation test body module for an aircraft rotor having a balance weight.

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The method of claim 1,
The rotation test body module,
Rotary test body module for an aircraft rotor having a balance weight, characterized in that the ring shape.