KR20230006174A - Rotor apparatus of coaxial counter-rotating aircraft - Google Patents

Abstract

The present invention relates to a rotor device for a coaxial counter-rotating aircraft, which operates as at least a part among a collective control input, a cyclic control input, and a yawing control input is co-linked. According to an embodiment of the present invention, the rotor device for a coaxial counter-rotating aircraft can simplify a component of a rotor unit by separating the collective control input and the cyclic control input. According to the present invention, the rotor device for a coaxial counter-rotating aircraft can minimize an additional component composition for yaw control by linking a device for the yaw control of an aircraft to a device for the collective control input. The rotor device for a coaxial counter-rotating aircraft includes a first rotor unit, a second rotor unit, a gearbox, and a link assembly.

Description

Rotor device of coaxial inverted flight {ROTOR APPARATUS OF COAXIAL COUNTER-ROTATING AIRCRAFT}

The present invention relates to a rotor device for a coaxial inverted aircraft, and more particularly, separates a collective control input from a cyclic control input and adjusts the distribution to each rotor unit, thereby simplifying the structure of the rotor It relates to a rotor device for a coaxial inversion aircraft.

In general, in a rotorcraft such as a helicopter, lift and thrust are obtained by rotating a rotor (rotary wing). At this time, torque is generated by the rotational moment of the rotor, and a tail rotor was used to offset this, but this causes power loss unrelated to lift generation.

Therefore, a configuration of a rotor capable of canceling rotational moment while using all the power of the helicopter to generate lift has been developed. Representatively, a tandem rotor helicopter with two rotors placed back and forth, a side-by-side rotor helicopter with two rotors placed side-by-side, and a helicopter with two rotors placed up and down There is a coaxial rotor helicopter and the like.

Here, the coaxial reversing rotor configuration has the advantage of canceling torque without power loss by arranging two main rotors up and down on a concentric shaft and driving them to rotate opposite to each other.

In the coaxial reversal rotary wing aircraft (e.g., Ka-32A12 Rotor) that is being used, an additional lever is applied to apply differential collective steering input for yaw control. This connects both the upper swash plate and the lower swash plate through a rod end in order to input both the collective control input/cyclic control input of the upper and lower rotors. .

However, this conventional method has a disadvantage in that additional components for steering are disposed on the rotor, so that the number of components in the rotor control part is large. In addition, since the upper swash plate and the lower swash plate must be connected to each other in order to distribute the steering input to the upper and lower rotors, there is a problem in that a number of externally exposed parts adversely affect aircraft drag.

Therefore, there is a need to propose a rotor technology for simplifying the upper rotor structure and reducing the number of parts exposed to the outside of the mast as components of the upper rotor.

Republic of Korea Patent Registration No. 10-0675345 (Registration on 2007.01.22.)

An object of the present invention is to simplify the upper rotor structure and to provide a rotor device for a coaxial inverted aircraft to reduce the number of parts exposed to the outside of the mast as a component of the upper rotor.

It is rotatably installed on a main shaft extending from the fuselage of the aircraft, a first rotor unit including a plurality of first blades, and an independently rotatable installation based on the same main shaft as the first rotor unit, A second rotor unit including a plurality of second blades rotated on the upper side of the blades, a gearbox configured to transmit power generated from the engine to the first rotor unit and the second rotor unit, one side of which is fixed to the aircraft And a link assembly configured to transmit collective input, cyclic input, and yawing input to the first rotor unit and the second rotor unit, wherein the link assembly includes a collective input link It includes an assembly, a cyclic input link assembly and a yaw input link assembly, wherein the collective input link assembly is rotatably connected to the collective fixed plate at a first point between the collective fixed plate provided on one side of the gearbox and both ends, A first collective lever configured to adjust a vertical position of a non-rotating swash plate connected to a second point located at one end, wherein the cyclic input link assembly includes a first point and a second point of the first collective lever A rotor device for a coaxial inverted aircraft may be provided that is relatively rotatably connected to the first collective lever around a third point between the rotor and has one end configured to adjust the angle of the non-rotating swash plate.

Meanwhile, the collective input link assembly includes the first collective input link assembly configured to adjust the vertical position of the first non-rotating swash plate of the first rotor unit and the second non-rotating swash plate of the second rotor unit. A second collective input link assembly configured to adjust a vertical position and a second collective lever configured to simultaneously move the first collective input link assembly and the second collective input link assembly in the same direction.

In addition, one end of the second collective lever may be connected to the gearbox to be angularly adjustable.

On the other hand, the yaw input link assembly is angularly connected to the upper side of the T link and the T link configured to be angularly adjustable on the second collective lever, and yawing configured to adjust the angle of the T link according to position adjustment. It receives the sub-link and the driving force, and includes a yawing control lever configured to adjust the position of the yawing sub-link while pivoting around a point of the gearbox, and the two points spaced apart in opposite directions from the rotation center of the T-link It is connected to a pair of first collective levers capable of adjusting the position of the pair of first collective levers, respectively, and the positions of the pair of first collective levers are adjusted in opposite directions as the angle of the T link is changed. can be configured.

Meanwhile, when the angle of the second collective lever is adjusted, the pair of first collective levers may be adjusted in the same direction while the position of the T link is adjusted.

Meanwhile, the non-rotating swash plates are configured as a pair so as to be provided at the upper and lower parts of the gear box, respectively, and further include a pair of rotating swash plates configured to rotate while being supported by the non-rotating swash plates. and a reversing link assembly configured to transmit power from the pair of rotating swash plates to the second rotor unit through the inside of the mast.

The rotor device of the coaxial inverted aircraft according to an embodiment of the present invention can simplify the components of the rotor unit by separating the collective control input and the cyclic control input.

In addition, by linking a device for yaw control of an aircraft with a device for collective control input, it is possible to minimize the configuration of additional parts for yaw control.

As a result, it is possible to greatly simplify the complicated upper rotor structure of the existing coaxial inverted aircraft, and there is an effect of greatly improving reliability in terms of design or performance of the aircraft.

1 is a perspective view of a rotor device of a coaxial inversion aircraft according to the present invention.
Figure 2 is a side view of the rotor device of the coaxial inversion aircraft shown in Figure 1;
FIG. 3 is a partially enlarged view centering on the gearbox of FIG. 2 .
4 is a partially enlarged view showing the front of the gearbox.
5A is an exploded perspective view of a link assembly;
Figure 5b is an exploded perspective view showing the connection relationship of the link assembly.
Figure 6 is a partially cut-away cross-sectional view showing the underside of the mast and a portion of the inverted link assembly.
7 is a conceptual diagram illustrating the operation concept of a link assembly at the time of collective input.
8 is a conceptual diagram showing the operation concept of a link assembly when a cyclic input is performed.
9 is a conceptual diagram showing the operating concept of the link assembly when yaw is input.
FIG. 10 is a partially enlarged view of the state of FIG. 9 by enlarging the T rod as the center.
11a, 11b and 11c are diagrams showing an operating state when a collective input is generated.
12a, 12b and 12c are diagrams showing operating states when a cyclic input is generated.
13a, 13b and 13c are diagrams showing an operating state when a yaw input occurs.

Hereinafter, according to an embodiment of the present invention, will be described in detail with reference to the accompanying drawings. In addition, in the description of the following embodiments, the name of each component may be called a different name in the art. However, if they have functional similarity and identity, even if a modified embodiment is employed, it can be regarded as an equivalent configuration. In addition, signs added to each component are described for convenience of description. However, the contents of the drawings in which these symbols are written do not limit each component to the scope in the drawings. Likewise, even if an embodiment in which the configuration in the drawings is partially modified is employed, it can be regarded as an equivalent configuration if there is functional similarity and identity. In addition, in light of the level of a general technician in the relevant technical field, if it is recognized as a component that should be included, the description thereof will be omitted.

Hereinafter, 'input' will be described on the premise that a series of processes for adjusting a blade by transmitting power and changing a position or angle by a mechanically connected lever or connecting rod will be described.

In addition, below, the connecting rod may be provided with bearings configured to be rotatably connected to other structures at both ends, and the length between both ends may be adjustable. As an example, it may be a rod end bearing capable of adjusting the length.

1 is a perspective view of a rotor device 1 of a coaxial inversion aircraft according to the present invention.

Referring to FIG. 1, the rotor device 1 of the coaxial inversion aircraft according to the present invention includes a rotor unit, a mast 10, a gearbox 20, a link assembly 50, a drive unit, and a reversing link assembly 60. can do.

The rotor unit may include a first rotor unit 30 and a second rotor unit 40 configured to rotate in the opposite direction to the first rotor unit 30 . The first rotor unit 30 is configured to rotate at least one first blade 31 disposed at a relatively lower side, and the second rotor unit 40 rotates coaxially with the first rotor unit 30. And, it is configured to rotate at least one second blade 41 rotating on the upper side of the first blade 31. On the other hand, the number of blades may be configured in plurality, but in this specification, the first blade 31 and the second blade 41 will be described on the premise that each consists of three blades formed spaced apart at the same angle.

The mast 10 extends upward from the gearbox 20 and is configured to support and fix the rotating first rotor unit 30 and the second rotor unit 40 . The mast 10 may have a hollow cylindrical structure with an empty inner side.

The gearbox 20 is configured to receive power from the engine and transmit rotational force to the first rotor unit 30 and the second rotor unit 40 at the same gear ratio. The gearbox 20 may be connected to and fixed to the frame of the aircraft. However, since the internal structure of the gearbox 20 may be configured in various ways, a detailed description thereof will be omitted.

The link structure may be configured to transfer a blade pitch, a cyclic input, and a yaw input of a rotor unit that rotates with a coaxial inversion. The link structure may include a plurality of levers 400 connected to the levers and a plurality of levers connected to one side of the gearbox 20 to enable pivoting, that is, angle adjustment. Meanwhile, the link structure will be described in detail later.

The driving unit is configured to transmit power for adjusting pitch angles of the first blade 31 and the second blade 41 . The driving unit may include a collective driving unit 70, a cyclic driving unit 80, and a yaw driving unit 90. Each driving unit is configured to be connected to each connecting rod 400 of the link structure to transmit power to the link structure. As an example, it may be configured and connected to a linear or rotary actuator.

The reversing link assembly 60 is configured to transmit an input from the lower side of the gearbox 20 through the inside of the mast 10 to the second blade 41 disposed on the upper side. The reversing link assembly 60 includes a plurality of levers and connecting rods 400, and reverses the input generated from the link assembly 50 and transfers it to the inside of the mast 10, and also the top of the mast 10. The input direction is reversed again and transmitted to the second blade 41.

FIG. 2 is a side view of the rotor device 1 of the coaxial inversion aircraft shown in FIG. 1 .

Referring to FIG. 2, the rotor device 1 of the coaxial inversion aircraft according to the present invention includes a gearbox 20, a first rotor unit 30, a second rotor unit 40 and a reversing link assembly 60 in the conventional It may be provided with a configuration applied to the coaxial inversion aircraft of.

That is, a first non-rotating swash plate 32 is provided on the upper side of the gearbox 20, and the first non-rotating swash plate 32 is configured to move a predetermined distance in the vertical direction on the mast 10. can In addition, a first rotating swash plate 33 rotating together with the first blade 31 while being supported by the first non-rotating swash plate 32 may be provided.

Meanwhile, a second non-rotating swash plate 42 is provided on the lower side of the gearbox 20, and the second non-rotating swash plate is also configured to move vertically from the lower side of the gearbox 20. can (collective input). In addition, a second rotating swash plate 43 configured to be rotatable while being supported by the second non-rotating swash plate 42 may be provided.

The above-described rotating swash plate may be provided in a gimbal bearing provided in the mast 10 and tilted when force is applied in a vertical direction at a point spaced apart from the rotational central axis (cyclic input).

On the other hand, inputs generated from the link assembly 50 are transmitted to the non-rotating swash plate, and the resultant movement and tilting of the non-rotating swash plate in a vertical direction causes posture and position adjustment of the rotating swash plate.

As the positions of the rotating swash plate and the connecting rod connected to each blade are adjusted, the angle of the blade may be adjusted. At this time, the pitch angle of the blade is adjusted equally as a whole (collective input), the pitch angle is adjusted according to the rotation angle of the blade (cyclic input), and the first blade 31 and the second blade 41 in the opposite direction Pitch angle (yaw input) adjustment can be made.

Hereinafter, the configuration of the link assembly 50 will be described with reference to FIGS. 3 and 4 .

Figure 3 is a partially enlarged view of the gear box 20 of Figure 2, Figure 4 is a partial enlarged view showing the front of the gear box 20, Figure 5a is an exploded perspective view of the link assembly 50, Figure 5b is an exploded perspective view showing the connection relationship of the link assembly (50).

Referring to FIGS. 3 to 5B , the link assembly 50 may include a collective input link assembly 50 , a cyclic input link assembly 200 and a yaw input link assembly 300 .

The collective input link assembly 50 is configured to equally move the first non-rotating swash plate 32 and the second non-rotating swash plate 42 in the vertical direction by a collective input.

The collective input link assembly 50 may include a first collective input link assembly 110 , a second collective input link assembly 120 and a second collective lever 130 . It may also include a plurality of connecting rods (400).

The first collective input link assembly 110 is configured to transmit a collective input to the first non-rotating swash plate 32 connected to the upper side of the gearbox 20 .

The first collective input link assembly 110 may include a collective fixing plate 111 and a first collective lever 112 . It may also include a plurality of connecting rods (400).

The lower end of the collective fixing plate 111 may be rotatably connected to the upper side of the gearbox 20 and the upper end may be rotatably connected to one side of the first collective lever 112 .

The first collective lever 112 extends to a predetermined length and is installed in the gearbox 20 in a generally horizontal direction, but the angle can be adjusted by a collective input. The first collective lever 112 is configured to be angularly adjustable relative to the above-described collective fixing plate 111 at a first point P1 provided at a central portion. That is, it is configured to be rotatable around the first point P1 like a lever.

The first collective lever 112 may be rotatably connected to the first non-rotating swash plate 32 on the mast 10 at a second point P2 . In addition, it may be rotatably connected to a cyclic input link assembly 200 to be described later at a third point P3 between the first point P1 and the second point P2. Meanwhile, a connecting rod 400 may be connected to a fourth point P4 far from the mast 10 of the first collective lever 112 to receive power from the second collective lever 130 to be described later.

The second collective input link assembly 120 may include the same components as the first collective input assembly described above, and may be provided at a position rotated by 180 degrees with respect to the central axis in the forward and backward directions.

One side of the second collective lever 130 is rotatably connected to the front of the gearbox 20, power is received from the collective driving unit 70 from one side, and an angle is adjusted. In this case, the second collective lever 130 may include a T rod 310 rotatably connected on a central axis of the collective input link assembly 50 in the forward and backward direction. A pair of connecting rods 400 connected to the fourth point P4 of the first collective lever 112 may be connected to two points spaced apart from the rotation center of the T rod 310 in opposite directions.

As a result, when the second collective lever 130 is pivoted, the rotation of the T rod 310 is not performed, and at the same time, the fourth point P4 of the pair of first collective levers 112 generates a translational movement that rises or falls. can make it That is, the upper and lower collective inputs can be synchronized.

The cyclic input link assembly 200 includes a first cyclic input link assembly 200 for adjusting the angle of the first non-rotating swash plate 32 on the upper side and a second non-rotating swash plate 42 on the lower side. It may include a second cyclic input link assembly 200 for adjusting the angle of.

The first cyclic input link assembly 200 and the second cyclic input link assembly 200 may each include a pair of left and right cyclic input levers 210 .

A pair of left and right cyclic input levers 210 are connected to the aforementioned first collective lever 112 to be rotatable around the third point P3. Both ends of the cyclic input lever 210 are connected to the connecting rod 400, respectively. The connecting rod 400 connected to one point (fifth point P5) of the end adjacent to the mast 10 of the cyclic input lever 210 is disposed in a substantially vertical direction and connected to one side of the non-rotating swash plate. do. Also, among the cyclic input levers 210, the connecting rod 400 at a position spaced apart from the mast 10 (the sixth point P6) may be connected to the cyclic driving unit 80.

Meanwhile, in the first cyclic input link assembly 200 and the second cyclic input link assembly 200, the driving force is simultaneously transmitted from the cyclic driving unit 80 to each left cyclic input lever 210 in the same direction together. will rotate to In addition, each right cyclic input lever 210 also rotates in the same direction when a driving force is transmitted. That is, in the cyclic input link assembly 200, the left and right cyclic inputs are performed independently of each other, but the left pair of cyclic inputs are performed simultaneously and the right pair of cyclic inputs are performed simultaneously.

As a result, the angles of the first non-rotating swash plate 32 and the second non-rotating swash plate 42 are equally adjusted by the cyclic input, and thus the The pitch angle according to the direction of rotation can be equally adjusted.

Meanwhile, the cyclic input lever 210 is configured to be rotatable on the collective lever as described above, and when the angle of the cyclic input lever 210 is adjusted, the position of the third point P3 is adjusted and eventually the collective lever. The position of the rotation center of is adjusted. At this time, the angle adjustment amount of the cyclic input lever 210 according to the adjustment of the collective lever may be determined according to kinematic factors such as the length of the cyclic input lever 210, the length of the collective lever, and the location of the third point P3. there is. That is, each of the levers rotates around one point, but within a range of a certain rotation angle, a range in which the amount of movement in the vertical direction is substantially the same occurs. In this embodiment, the amount of change in the vertical position of the second point P2 of the collective lever and the amount of change in the vertical position of the fifth point P5 of the cyclic input lever 210 may be substantially the same within the movable range of the collective lever. The length of the third point P3, the collective lever, and the cyclic input lever 210 may be determined.

Therefore, even if the vertical position of the non-rotating swash plate is adjusted by the collective input, the vertical position of the fifth point P5 of the cyclic input lever 210 is also changed by the same vertical position change amount. Therefore, even if there is a collective input, if there is no separate cyclic input, the cyclic input remains neutral.

The yaw input link assembly 300 is configured to adjust the pair of first collective levers 112 in opposite directions according to an input. The yaw input link assembly 300 may include a T rod 310, a yawing sub-link 320, and a yaw control lever 330.

The T rod 310 is rotatably connected on the second collective lever 130, and is connected to the pair of first collective levers 112 at two points P7 and P8 spaced apart by the same distance from the center of rotation. Rods 400 may be provided respectively. A yawing sub-link 320 to be described below may be rotatably connected to the upper side of the T rod 310. When force is transmitted from the yawing sub-link 320 to the T rod 310, the angle of the T rod 310 is adjusted on the second collective link, and the pair of first collective links are moved in opposite directions according to the adjusted angle. can be adjusted to the same angle.

The yaw control lever 330 is rotatably connected coaxially with the center of rotation of the above-described second collective link, and extends to one side to receive power from the yaw driver 90 . A connecting rod 400 is provided between the yaw driver 90 and the yaw control lever so that power can be transmitted. The other side of the yaw control lever 330 may be rotatably connected to the yaw sub-link 320 described above. After all, when the yaw control lever 330 rotates, it is possible to transmit force to the T rod 310 through the yawing sub-link 320 and rotate the T rod 310.

FIG. 6 is a partially cut-away cross-sectional view showing the lower part of the mast 10 and a portion of the reversing link assembly 60 .

Referring to FIG. 6 , a second non-rotating swash plate 42 is provided below the gearbox 20, and a second non-rotating swash plate 42 is provided below the second non-rotating swash plate 42. ) A second rotary swash plate 43 configured to enable vertical positioning and angle adjustment while being supported by ) may be provided.

The second rotating swash plate 43 and the second non-rotating swash plate 42 are configured to be easily adjusted in the vertical direction, and are provided on gimbal bearings so that their angles can be adjusted.

The second rotation swash plate 43 may be provided with connecting rods 400 spaced apart at the same distance along the circumferential direction. The connecting rod 400 may be connected to the reversing link assembly 60 configured to convert the force transmitted from the lower end of the mast 10 in the opposite direction.

The reversing link assembly 60 includes a rod extending to the bottom and top of the mast 10, and is pivotally connected with the mast 10 to reverse the direction of force at the top and bottom of the mast 10 Can include connecting rods.

Hereinafter, the operation of the link assembly 50 will be described in detail with reference to FIGS. 7 to 10 . In FIGS. 7 to 10, a complicated link structure is shown simplified to aid understanding, and each drive unit and gear box are also omitted.

7 is a conceptual diagram showing the operation concept of the link assembly 50 at the time of collective input.

Referring to FIG. 7 , when an input for raising the connecting rod 400 is generated by the collective driver 70, the angle of the second collective lever 130 is adjusted clockwise. At this time, the T rod 310 connected to the second collective lever 130 moves a predetermined distance upward together. As the vertical position is adjusted, the connecting rod 400 connected to the seventh point P7 on the right side of the T rod 310 and the connecting rod 400 connected to the eighth point P8 on the left side move upward at a predetermined distance together. will move Therefore, the rotation angle of the upper first collective lever 112 is adjusted around the first point P1 so that the fourth point P4 rises, and the second point P2 and the third point P3 going down The lower first collective lever 112 is also adjusted in the same direction. As a result, the first non-rotating swash plate 32 connected to the second point P2 of the first collective lever 112 on the upper side is linearly moved in the lower direction, and also moves to the second point P2 of the first collective lever 112 on the lower side. The second non-rotating swash plate 42 connected to the point P2 is also linearly moved downward.

Meanwhile, as described above, when the vertical position of the non-rotating swash plate is adjusted, the position of the sixth point P6 on the side of the cyclic drive unit 80 does not change, and the left and right sides of the first collective lever 112 Since the third point P3 of the connected cyclic input lever 210 descends, the fifth point P5 descends. As a result, the second point P2 of the first collective lever 112 and the fifth point P5 of the cyclic input lever 210 are mechanically descended by a similar or substantially the same distance by the collective input.

Therefore, since the collective input link assembly 50 and the cyclic input link assembly 200 are co-linked and the position of the cyclic input lever 210 is also adjusted by the collective input, the first and second non-rotating swash plates (42) does not occur and each blade does not receive a cyclic input.

8 is a conceptual diagram showing the operation concept of the link assembly 50 upon cyclic input.

Referring to FIG. 8 , a state when a cyclic input is generated is shown on the left side of FIG. 7 . When the driving force for moving the connecting rod 400 in the downward direction is transmitted from the cyclic driving unit 80 on the left side, the sixth point P6 of the cyclic input lever 210 disposed on the upper side and the cyclic lever disposed on the lower side The sixth point P6 of the input lever 210 descends the same distance at the same time. At this time, since the upper and lower cyclic input levers 210 rotate about the third point P3, the fifth point P5 of the upper and lower cyclic input levers 210 rises. As a result, the angles of the first non-rotating swash plate 32 and the second non-rotating swash plate 42 are adjusted to incline to the left.

FIG. 9 is a conceptual diagram showing the operation concept of the link assembly 50 when yaw is input, and FIG. 10 is a partially enlarged view showing the T-rod 310 as the center in the state of FIG. 9 enlarged.

Referring to FIGS. 9 and 10 , first, a driving force for pushing the connecting rod upward is transmitted from the yaw driver 90 . The yaw control lever 330 connected to the connecting rod 400 is rotated around the ninth point P9. At this time, the yawing sub-link 320 connected to the other side of the yaw control lever 330 rotates the T rod 310 while moving to the right. At this time, rotation is performed in a counterclockwise direction based on FIG. 10 . When the T rod 310 rotates, the connecting rod 400 connected to the sixth point P6 descends, and the connecting rod connected to the fifth point P5 rises. As a result, the angles of the upper first collective lever 112 and the lower first collective lever 112 are adjusted in opposite directions, and finally, the first non-rotating swash plate 32 and the second non-rotating swash plate The direction of movement in the vertical direction of (42) is reversed.

Hereinafter, the operation of the rotor device 1 according to collective, cyclic and yaw inputs will be described with reference to FIGS. 11A to 13C.

11a, 11b and 11c are diagrams showing an operating state when a collective input is generated.

FIG. 11A shows a state in which the collective input is Max, and a state in which the end of the second collective lever 130 is disposed at the highest vertical position. 11B shows a case where the collective input is neutral. 11C shows a state when the collective input is Min, and a state when the end of the second collective lever 130 is at the lowest vertical position. At this time, the vertical position of the non-rotating swash plate is determined differently, and the overall pitch angle of the first blade 31 and the second blade 41 is adjusted according to the positions of the non-rotating swash plate and the rotating swash plate. this is shown

Meanwhile, FIGS. 11a (b), 11b (b), and 11c (b) show the first collective input link assembly 110, the swash plate, and the first blade 31 viewed from the side, and the operational relationship is appear Meanwhile, as described above, since the first collective link and the cyclic input lever 210 are rotatably connected to each other, the angle of the cyclic input lever 210 connected according to the angle adjustment tendency of the first collective link is also similar. regulated by the trend. Therefore, even if the link between the collective input and the cyclic input is co-linked, when the non-rotating swash plate is raised and lowered by the collective input, the angle of the cyclic input lever 210 is also adjusted, so the non-rotating swash plate is not tilted and moved up and down. It can be.

12a, 12b and 12c are diagrams showing operating states when a cyclic input is generated.

Referring to FIG. 12A, when the cyclic input is Max, a state in which the angles of the left and right cyclic input levers 210 are adjusted opposite to each other is shown. Referring to FIG. 12B, as a neutral position, cyclic input When the angle of the lever 210 is at the initial position, and FIG. 12c shows a state in which the angles of the cyclic input levers 210 are adjusted in the opposite direction to FIG. 12a when the cyclic input is Min.

13a, 13b and 13c are diagrams showing an operating state when a yaw input occurs.

13A to 13C, the T rod 310 is rotated by the yaw input, and the angles of the upper first collective lever 112 and the lower second collective lever 130 are adjusted in opposite directions, Finally, vertical positions between the first non-rotating swash plate 32 and the second non-rotating swash plate 42 can be adjusted in opposite directions.

According to the various embodiments described above, the rotor device of the coaxial inversion aircraft according to an embodiment of the present invention separates the collective control input and the cyclic control input, thereby improving the components of the rotor unit. be able to simplify.

In addition, by linking a device for yaw control of an aircraft with a device for collective control input, it is possible to minimize the configuration of additional parts for yaw control.

As a result, it is possible to greatly simplify the complex upper rotor structure of the existing coaxial inverted aircraft, and greatly improve reliability in terms of design or performance of the aircraft.

Those skilled in the art to which the present invention pertains will understand that the present invention can be embodied in other specific forms without changing its technical spirit or essential features. Therefore, the embodiments described above should be understood as illustrative in all respects and not limiting. The scope of the present invention is indicated by the following claims rather than the detailed description above, and all changes or modifications derived from the meaning and scope of the claims and equivalent concepts should be construed as being included in the scope of the present invention. do.

1: Rotor device of coaxial inverted aircraft
10: mast
20: gearbox
30: first rotor unit
31: first blade
32: first non-rotating swash plate
33: first rotation swash plate
40: second rotor unit
41: second blade
42: second non-rotating swash plate
43: second rotary swash plate
50: link assembly
60: inversion link assembly
70: collective driving unit
80: cyclic driving unit
90: yawing drive unit
110: first collective input link assembly
111: fixed plate
112: first collective lever
120: second collective input link assembly
130: second collective lever
200: cyclic input link assembly
210: cyclic input lever
300: yaw input link assembly
310: T rod
320: yawing sub link
330: yaw control lever
400: connection load
P1: first point P2: second point
P3: 3rd point P4: 4th point
P5: 5th point P6: 6th point
P7: 7th point P8: 8th point
P9: ninth point

Claims (6)

a first rotor unit rotatably installed on a mast extending from an aircraft fuselage and including a plurality of first blades;
a second rotor unit including a plurality of second blades that are independently rotatably installed on the same main shaft as the first rotor unit and rotated above the first blade;
A gearbox configured to transmit power generated from an engine to the first rotor unit and the second rotor unit, one side of which is fixed to the aircraft; and
A link assembly configured to transmit collective input, cyclic input, and yawing input to the first rotor unit and the second rotor unit,
The link assembly includes a collective input link assembly, a cyclic input link assembly and a yaw input link assembly,
The collective input link assembly,
a collective fixing plate provided on one side of the gearbox; and
A first collective lever rotatably connected to the collective fixed plate at a first point between both ends and configured to adjust a vertical position of the non-rotating swash plate connected to a second point located at one end,
The cyclic input link assembly,
A third point between the first and second points of the first collective lever is relatively rotatably connected to the first collective lever, and one end is capable of adjusting an angle of the non-rotating swash plate. A rotor device of a coaxial inverted aircraft configured to be. According to claim 1,
The collective input link assembly,
a first collective input link assembly configured to adjust a vertical position of a first non-rotating swash plate of the first rotor unit;
a second collective input link assembly configured to adjust a vertical position of a second non-rotating swash plate of the second rotor unit; and
A rotor device of a coaxial inverted aircraft comprising a second collective lever configured to simultaneously move the first collective input link assembly and the second collective input link assembly in the same direction. According to claim 2,
The second collective lever is a rotor device of a coaxial inverted aircraft provided with one end connected to the gearbox to be angularly adjustable. According to claim 3,
The yaw input link assembly,
a T link configured to be angularly adjustable on the second collective lever; and
A yawing sub-link connected to an upper side of the T-link to be angularly adjustable and configured to adjust an angle of the T-link according to position adjustment; and
A yawing control lever configured to receive a driving force and adjust the position of the yawing sub-link while being pivoted about a point of the gearbox,
Two points spaced apart from the rotation center of the T link in opposite directions are connected to a pair of first collective levers capable of adjusting the positions of the pair of first collective levers, respectively,
As the angle of the T link changes, the pair of first collective levers are configured to adjust their positions in opposite directions to each other. According to claim 4,
The second collective lever is configured such that the pair of first collective levers are adjusted in the same direction while the position of the T link is adjusted when the angle is adjusted. According to claim 5,
The non-rotating swash plate is composed of a pair so that it can be respectively provided on the upper and lower parts of the gear box,
Further comprising a pair of rotational swash plates configured to rotate while being supported by the non-rotational swash plate,
A rotor device of a coaxial inverting aircraft further comprising a reversing link assembly configured to transmit power from the pair of rotating swash plates to the second rotor unit through the inside of the mast.

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