KR102153511B1 - A control transfer member for a pitch control device of a ducted rotorcraft tail rotor - Google Patents

Abstract

The present invention relates to a control movable member (15) for a pitch control device (14) of a ducted rotorcraft tail rotor, which constitutes a rotation shaft (15i) and extends at least partially parallel to the rotation shaft (15i). It comprises an annular connector (15a) comprising four push rods (15b), in which case each of the at least two push rods (15b) is attached to the associated pitch lever (14b) of the rotor blade of the ducted rotorcraft tail rotor. Provided to be bonded, each of the annular connector 15a and the at least two push rods 15b comprises a composite material, in particular a fiber reinforced polymer.

Description

A control moving member for a pitch control device of a ducted rotorcraft tail rotor {A CONTROL TRANSFER MEMBER FOR A PITCH CONTROL DEVICE OF A DUCTED ROTORCRAFT TAIL ROTOR}

The present invention relates to a control transfer member for a pitch control device of a ducted tail rotor.

테일 로터의 형태로 덕트된 회전익기 테일 로터로서 구현된다. 이러한 덕트형 부분에는 가로 덕트를 형성하는 슈라우드(shroud)가 제공된다. 하지만, 그러한 카운터-토크 로터, 그리고 더 구체적으로는 덕트된 회전익기 테일 로터의 구조 및 배치는 일반적으로 그것을 회전 구동하기 위한 알맞은 수단과 함께, 당업자에게 공지되어 있고, 그것의 더 상세한 설명은 간략함과 간결함을 위해 생략된다.Document US4,809,931 describes a rotorcraft with a main rotor and a counter-torque rotor present in the tail boom of such a rotorcraft. These counter-torque rotors are rotatably arranged in a transverse duct located in the ducted part of the tail boom, and thus Fenestron

It is implemented as a ducted rotorcraft tail rotor in the form of a tail rotor. This duct-like part is provided with a shroud forming a transverse duct. However, the structure and arrangement of such a counter-torque rotor, and more specifically a ducted rotorcraft tail rotor, is generally known to those skilled in the art, with suitable means for driving it rotationally, and a more detailed description thereof is brief. And omitted for brevity.

In addition, documents US3,594,097, US4,626,172, US4,626,173, US5,306,119, and US5,383,767 are suitable pitches for controlling the collective pitch of the corresponding rotor blades of a ducted rotorcraft tail rotor. Describe the control devices. More specifically, these pitch control devices each include a hub composed of several components, and as main components of these components, a hub body, a splined flange on which the hub body is mounted, and A pitch control member, also referred to as a "control spider" is included. This hub body is provided for connecting the suspension of the corresponding rotor blades and the associated tail gearbox that drives the ducted rotor blades tail rotor. These rotor blades must be supported along their blade axes to enable rotation around the blade axes, and thus the pitch angle control of the rotor blades.

In all of these pitch control devices, the control spider is separated into two parts for accessibility and assembly reasons, these two parts being a control spider acting as a control moving member and a control input member. It is a center plate. These center plates are usually used for connection to each tail rotor actuator after installation to a given rotorcraft.

The control spider, i.e. the control spider ring in combination with the center plate, should be as stiff as possible to ensure the necessary control and range of control despite possible deformations under load. Therefore, each of the push rods provided in the control spider ring should be as strong and stiff as possible in both the pushing and pulling directions.

Also, due to the high rotational speed of the ducted rotorcraft tail rotor in operation, the control spider ring needs to be centered on the center plate. This is usually realized by a step provided in the outer circumference of the center plate, which step is in contact with the control spider ring. That is, the control spider ring is usually implemented in the form of a cup with a bottom section provided with a cut out portion for accommodating the center plate.

In operation, such pitch angle control is carried out by the control spider, which causes the vertical strikes of the associated control spider actuator, i.e., the rotation of the rotor blades in a direction perpendicular to the respective rotor axis. Change to More specifically, each vertical strike of the control spider actuator can be converted into rotation of the rotor blades by providing a lever arm between the control spider and the rotor blades, which by means of the associated bearings hub body).

While the control spider creates a relatively stiff connection from the control spider actuator to the rotor blades, to ensure the required control capability of the ducted rotorcraft tail rotor, all components are inspected under it, such as the blade bolts. To keep them accessible. However, the connection of a given rotor blade to the control spider through the lever arm is susceptible to several different manufacturing tolerances. These manufacturing tolerances depend on the exact position and length of each of the rotor blades from the hub body towards each other, and of each lever arm of the control spider itself. As a result of the number of fundamental rotor blades, all individual fabrication tolerances of each connection are added together, resulting in a perceptible total fabrication tolerance.

More specifically, when attaching the control spider to the rotor blades, the respective added manufacturing tolerances of the hub body, center plate, control spider, and lever arms must be compensated, which means that if they do not, they will interlock the respective components. (interlocking) may result. In addition, movements resulting from the pitch control of the rotor blades must be compensated. In other words, the control spider actuator, and thus the vertical movements performed by the control spider, result in a rotational movement of the rotor blades around their respective longitudinal axes, thus resulting in a lateral movement of the lever arms. Moreover, the control spider actuator is rotatably mounted around its vertical axis so that it can result in the lateral movement of the respective push rods of the control spider, which should be compensated for even the relatively minor rotation of the control spider actuator around the vertical axis. .

In a widely known design, maximum manufacturing tolerances are considered. To deal with these maximum manufacturing tolerances, often oblong bushings are in use in control spiders, in which case the spherical joint of the lever arms can move sideways, or vice versa. These free movements result in incomplete controllability even though the vibrations, different characteristics at each of the neutral pitch positions, and even the respective control changes are only within a small range of control.

In addition, each movement of the control spider with respect to the rotor blades results in wear in the rectangular bushing or spherical joint. In order to reduce this wear to an acceptable degree, expensive materials hardened for the realization of the corresponding components of the pitch control device need to be used. However, this requirement along with the stiffness requirements described above usually results in relatively heavy pitch control devices as a result of the respective selected materials and implementations. In addition, separation of the existing pitch control device from a relatively large number of different components is required due to fundamental assembly processes. Moreover, this required centering requires a complete replacement of the existing pitch control device if the respective limits are exceeded.

It is therefore an object of the present invention to provide a new control spider and, in particular, a new control movement member for the pitch control device of a ducted rotorcraft tail rotor, which shows a reduced weight with a simplified structure, at least for conventional use. It allows the omission of rectangular bushings and spherical joints.

This object is solved by a control movable member comprising the features of claim 1, which control movable member is for a pitch control device of a ducted tail rotor.

More specifically, according to the invention, the control moving member for the pitch control device of the ducted rotorcraft tail rotor comprises a ring comprising at least two push rods forming an axis of rotation and extending at least partially parallel to such axis of rotation It includes a ring-shaped connector. Each of the at least two push rods is provided for coupling to an associated pitch lever of the rotor blade of the ducted tail rotor. Each of these annular connectors and at least two push rods comprises a composite material, in particular a fiber reinforced polymer.

According to one aspect, the annular connector and each of the at least two push rods, and preferably the entire inventive control moving member, are implemented using carbon fiber reinforced polymers. However, other fiber-reinforced polymers such as glass fiber-reinforced polymers or Aramid fiber-reinforced polymers can be used as well or simultaneously.

Advantageously, by implementing the control moving member of the present invention as a composite control spider ring using a composite material, such a composite control spider ring preferably comprises sideways elastic push rods, each configuration due to fabrication tolerances. The aforementioned possible intermeshing of the components can be reliably avoided. The required lateral stretch of the push rods is preferably produced by a torsional soft cross section at the top of each push rod. Therefore, in order to compensate for the fundamental manufacturing tolerances, which are usually within the range of ±0.5 mm, the possibility of bending the push rods sufficiently far in the radial direction of the control moving member of the present invention is possible by means of smooth cross sections, while the arm ( The required pull and push stiffness of the arms) can be realized.

Further, by implementing the push rods using composite materials, the associated rotor blades of a given ducted rotorcraft tail rotor can be securely fixed to the control moving member of the present invention. Hence movements or manufacturing tolerances resulting from the pitch control of the associated rotor blades can be advantageously compensated without the need for rectangular bushings, universal joints, or ball joints. However, if nonetheless such rectangular bushings, universal joints, or ball joints are used, the lateral elasticity of the push rods reduces play between the control moving member of the present invention and the respective blade connections. A relatively high push and pull ensures stiffness and strength of the push rods, resulting in more direct control of the appropriate and thus associated rotor blades and less wear of rectangular bushings, universal joints, or ball joints. In other words, the movement of the control moving member of the invention relative to the associated rotor blades can be advantageously eliminated so that the wear of rectangular bushings, universal joints, or ball joints is greatly reduced. Also, instead of the conventional ball joint-bushing combination, a ball bearing can be used.

According to one aspect, implementing the control movable member of the present invention as a composite control spider using complex materials allows to reduce the overall weight of the control movable member, thus controlling the respective pitch for the ducted rotorcraft tail rotor. Allows to significantly reduce the overall weight of the device compared to conventional metallic designs. However, the fundamental manufacturing costs can be kept at least at a comparable value.

Preferably, the push rods of the control movable member of the present invention are designed to be sufficiently flexible to allow installation of the control movable member of the present invention after installation of each ducted rotorcraft tail rotor in a given rotorcraft. Thus, an associated control input member, for example a given center plate, can be advantageously integrated into the control moving member of the invention. Therefore, weight and costs can be reduced even further.

More specifically, according to one aspect, the push rods of the control movable member of the present invention are stretchable in the circumferential direction of the control movable member, and alternatively or additionally are stretchable also in the radial direction of the control movable member. Further, the push rods are made stiff in their longitudinal direction in order to precisely move the respective control loads on the rotor blades of the ducted rotorcraft tail rotor.

Advantageously, the elasticity in the circumferential direction is realized by a torsionally soft area provided at the top of each push rod, which is for example a U-shaped cut-out in the annular connector of the control moving member of the invention. ). The elasticity of each push rod in the radial direction of the control moving member is advantageously obtained by the flat design of each push rod with a rectangular cross section. The required stiffness in the longitudinal direction of each push rod is preferably provided by using a stiff composite material such as carbon fiber reinforced polymers on the one hand, and on the other hand stiffening ribs located on top of each push rod. rib). These reinforcing ribs advantageously move the respective pushing and pulling loads of the push rods from the respective rotor blade forces to the annular connector.

In order to meet the need to remove the state-of-the-art rectangular bushings, each enabling sideways movement, a movement in the circumferential direction of the control moving member of approximately ±0.5 to 0.7 mm is sufficient. In addition, by using carbon fiber reinforced polymers, the fundamental risk of fatigue failure due to periodic bending and vibrations is eliminated due to the respective material characteristics.

According to one preferred embodiment, each of the at least two push rods has a first portion extending at least approximately radially outward from the annular connector, at least approximately perpendicular to the first portion and at least approximately parallel to the axis of rotation. And a second portion extending so as to be.

According to another preferred embodiment, at least one of the at least two push rods is an annular connector via an associated reinforcing rib disposed between the annular connector and a first portion of at least one of the at least two push rods. Is connected to

According to another preferred embodiment, each of the at least two push rods has at least approximately L-shape.

According to another preferred embodiment, each of the at least two push rods has a first predetermined stiffness in a direction parallel to the axis of rotation of the annular connector, and a second predetermined stiffness in a direction in contact with the control moving member. In this case, the first predetermined rigidity is greater than the second predetermined rigidity.

According to another preferred embodiment, each of the at least two push rods is connected to the annular connector via an associated reinforcing rib to provide a first predetermined stiffness.

According to another preferred embodiment, each of the at least two push rods comprises a torsion-soft region to provide a second predetermined stiffness.

According to another preferred embodiment, each of the at least two push rods includes a third predetermined stiffness in a direction transverse to the axis of rotation of the annular connector, and this third predetermined stiffness is the first predetermined stiffness. Less than

According to another preferred embodiment, each of the at least two push rods includes a stretchable area to provide a third predetermined stiffness.

According to another preferred embodiment, each of the at least two push rods has a first predetermined stiffness in a direction parallel to the axis of rotation of the annular connector and a first predetermined stiffness in a direction transverse to the axis of rotation of the annular connector. 2 predetermined stiffness, in which case the first predetermined stiffness is greater than the second predetermined stiffness.

According to another preferred embodiment, each of the at least two push rods is connected to the annular connector via an associated reinforcing rib to provide a first predetermined stiffness.

According to another preferred embodiment, each of the at least two push rods comprises an elastic region to provide a second predetermined stiffness.

According to another preferred embodiment, the composite material comprises at least one of carbon fiber reinforced polymers, glass fiber reinforced polymers, and aramid fiber reinforced polymers.

According to another preferred embodiment, the annular connector and at least two push rods form a spider-shaped structure.

The present invention also provides a pitch control device for a ducted tail rotor of a rotorcraft. This pitch control device, as described above, includes a control moving member according to the present invention and a disc-shaped control input member. This disk-shaped control input member is provided for mounting to the associated pitch control shaft of the ducted tail rotor and is preferably securely attached to the control moving member in a removable manner.

The reason for the use of the disk-shaped control input member is the need to connect the control moving member to the rotor blades and the associated pitch control shaft, each with an associated drive shaft. In order to realize these connections, a control movement member is placed in each hub body of a given rotor hub of a ducted tail rotor before the rotor blades are mounted on the hub body. Therefore, every single rotor blade can be first connected to the control moving member and then assembled to the hub body, for example with bolts.

However, for each positioning to reach the bolts, an opening in the center of the hub body that allows access to the bolts with a tool and allows for the afterwards attachment of the complete tail rotor to a given rotorcraft. There is a need for opening). This is achieved by means of a control input member mounted on the control moving member and an associated pitch control shaft each having an associated drive shaft in the final mounting step.

It should be noted that the above-described flow of mounting steps is required when the push rods of the control movable member are rigid in the radial direction of the control movable member. However, the push rods could alternatively be designed to be radially stretchable. In this case, it is possible to initially assemble each tail rotor without a control moving member, and in that case, for example, after mounting the tail rotor on a given rotorcraft, for example, a spherical ball head bolt mounted on the pitch lever of each rotor blade. Can be attached to the associated rotor blades, for example by reorienting the push rods far enough radially inward to position them in a cylindrical bushing mounted on the push rod. Alternatively, only a cylindrical bolt is fixed to the pitch lever of the rotor blade, and a spherical bearing is used in the push rod. In either case, it is fundamental to have enough elasticity to change the direction of the push rods for assembly on the one hand, but not to lose the rigidity on the other, and this is to ensure the precise movement of the control loads in the correct predetermined position. It is required to hold the control moving member.

As a result of the above-described configuration, manufacturing costs are reduced and a pitch control device having a relatively light weight can be obtained. Advantageously, these pitch control devices of the present invention are each easily adaptable to fundamental stiffness requirements. Also, assembling the pitch control device on a given rotorcraft can be simplified.

Preferred embodiments of the present invention are outlined through examples in the description that follows with reference to the accompanying drawings. In these appended drawings, components and elements that are identical or functioning identically are denoted by the same reference numerals and letters, and are thus described only once in the following description.
1 is a side view of a rotorcraft with a ducted tail rotor according to the invention and an enlarged perspective view of a tail rotor with such a duct.
Fig. 2 is a partially cut-away plan view of the ducted tail rotor of Fig. 1 with a pitch control device according to the invention.
Fig. 3 is a perspective view of the pitch control device of Fig. 2 with a control input member and a control movement member according to the present invention.
Figure 4 is a perspective view of the control moving member of Figure 3;

1 shows a rotorcraft 1 with a fuselage 2 comprising a tail boom 2a. The rotorcraft 1 is implemented by way of example, and is therefore also referred to as a helicopter for simplicity hereinafter.

The helicopter 1 provides at least one main rotor 1a configured to provide lift and forward thrust during operation, and counter-torque during operation, i.e. to one side. It comprises at least one counter-torque device 8 configured to counter the torque produced by the rotation of at least one main rotor 1a for the purpose of maintaining the balance of the helicopter 1 in terms of its yaw. However, it should be noted that the invention is not limited to helicopters, but can likewise be applied to other aircraft equipped with at least one counter-torque device and rotating wings according to the invention.

This at least one counter-torque device 8 is exemplarily provided in the aft section 1b of the tail boom 2a, which is preferably at least one duct-type part 7. Include it. For example, such a spot section (1b) is a fin (5) in the form of a T-tail with a tail wing (5a) and a rudder (5b) and It further includes a bumper (4). The tail wing 5a is preferably adjustable in its inclination and can make up for the functioning of the horizontal stabilizer. Alternatively, or in addition, the helicopter 1 is provided with a suitable horizontal stabilizer. The rudder 5b is preferably adapted to provide for enhanced directional control of the helicopter 1 and has large angles to reduce the given lateral drag of the fin 5 in sideward flight. To be preferably refracted.

However, it should be noted that the pin 5, the rudder 5b, and the tee-tail configuration of the horizontal stabilizer are merely described to illustrate one typical embodiment of the present invention, and thus are not intended to limit the present invention. do. Instead, the invention, as described below, can be applied to any ducted portion of a rotorcraft, whether or not the tee-tail pin or other configured pin has a rudder, and with or without a horizontal stabilizer. This is done regardless of whether it is provided in the ducted part.

Preferably, in the duct-like part 7 at least one counter-torque rotor 8a is rotatably arranged, forming at least one transverse duct 6 preferentially having at least a substantially circular or annular cross-section. A shroud 3 is provided. At least one transverse duct 6 exemplarily extends through the shroud 3. Further, in order to rotatably support the at least one counter-torque rotor 8a, at least one counter-torque stator 8b is fixedly arranged inside the at least one transverse duct 6.

테일 로터의 형태로 구현된다. 따라서, 간단함과 명확함을 위해, 카운터-토크 장치(8)와, 특히 카운터-토크 로터(8a)는 이후 "덕트된 테일 로터"와 "덕트된 회전익기 테일 로터"라고 각각 부르기도 한다.The counter-torque rotor 8a, the counter-torque stator 8b, and the shroud 3, i.e. the transverse duct 6 exemplarily form at least one counter-torque device 8 of the helicopter 1 and , It is in the form of a ducted tail rotor, and more specifically Fenestron

It is implemented in the form of a tail rotor. Thus, for simplicity and clarity, the counter-torque device 8 and, in particular, the counter-torque rotor 8a are also referred to hereinafter as "ducted tail rotors" and "ducted rotorcraft tail rotors", respectively.

The at least one ducted tail rotor 8a exemplarily includes a rotor hub 9 having a rotor shaft and a plurality of rotor blades 10 attached to such a rotor hub 9. The rotor blades 10 are preferably, but not necessarily, distributed in an angularly uneven manner on the rotor hub 9 using phase modulation. More specifically, the phase modulation is such that, for example, the geometric angular positions of the rotor blades 10 on the rotor hub 9 are distributed using the sinusoidal modulation law described in patent document EP0680871A1. As such, a technique for reshaping the noise-frequency spectrum is described, and the teachings of this EP0680871A1 are expressly incorporated in the specification of this application.

At least one counter-torque stator (8b) is fixedly arranged inside at least one transverse duct (6) and illustrates a drive shaft fairing (11) connecting the gearbox fairing (12) to the shroud (3) Includes enemies. The drive shaft fairing 11 is preferably adapted to receive the power transfer shaft of at least one ducted tail rotor 8a. The gearbox fairing 12 is also connected to the shroud 3 by an associated stator vane (13 in Fig. 2). Preferably, the gearbox fairing 12 is adapted to receive the rotor drive transmission of at least one ducted tail rotor 8a, and is also adapted to receive pitch fluctuation mechanisms for the rotor blades 10. Can be.

FIG. 2 shows the ducted part 7 of FIG. 1 with at least one ducted tail rotor 8a and at least one counter-torque stator 8b, these are at least one transverse duct of the shroud 3 It is placed in (6). Preferably, the at least one ducted tail rotor 8a is disposed close to the at least one counter-torque stator 8b side, more specifically the air flow generated by the ducted tail rotor 8a in operation ( air flow) is arranged upwards against at least one counter-torque stator (8b).

At least one ducted tail rotor 8a comprises rotor blades 10 and a rotor hub 9, which is exemplarily covered by a rotor hub cover 9a. At least one counter-torque stator (8b) is fixedly arranged inside at least one transverse duct (6) and comprises a drive shaft fairing (11) connecting the gearbox fairing (12) to the shroud (3). The gearbox fairing 12 is connected to the shroud 3 by means of associated stator vanes 13.

According to one aspect, the ducted tail rotor 8a is provided with a pitch control device 14 which is at least preferably adapted for controlling the collective pitch of the rotor blades 10. This pitch control device 14 is preferably operable by means of an associated pitch control shaft 14a, which associated pitch control shaft 14a is operated, for example, by means of pitch varying mechanisms received in the gearbox fairing 12.

FIG. 3 shows the pitch control device 14 of FIG. 2, which pitch control device 14 is at least preferably adapted for use with the ducted tail rotor 8a of the helicopter 1 of FIG. 1. According to one aspect, the pitch control device 14 includes at least one control moving member 15 and a control input member 16.

The control input member 16 is preferably provided for mounting on the pitch control shaft 14a of the ducted tail rotor 8a of FIGS. 1 and 2. Therefore, in the control input member 16, the axial movements of the pitch control shaft 14a are axial movements of the control input member 16, that is, in the direction of the rotational axis 15i of the control input member 16. It can be moved directly by the pitch control shaft 14a to bring about the movements of. These axial movements of the control input member 16 cause the control moving member 15 to move in the axial direction when it is moved in the axial direction.

According to one aspect, the control input member 16 is at least approximately disk-shaped and comprises a central part 16a. This central part 16a is preferably an accommodation 16b provided for being mounted to at least partially receive the pitch control shaft 14a of the ducted tail rotor 8a of FIGS. 1 and 2, respectively. Each has a mounting component.

Preferably, this control input member 16 is securely attached to the control moving member 15 in a preferably removable manner. This tight attachment is made preferentially using suitable attachment elements 17 such as screws, bolts, and/or rivets.

The control moving member 15 preferably comprises an annular connector 15a forming a rotating shaft 15i, which when mounting both the control moving member 15 and the control input member 16 to each other, These are common to the control movement member 15 and the control input member 16. The annular connector 15a is preferentially connected to at least two push rods 15b, and these push rods 15b exemplarily extend at least partially parallel to the axis of rotation 15i. According to one aspect, the annular connector 15a and at least two push rods 15b form a spider-shaped structure.

Preferably, each of the annular connector 15a and at least two push rods 15b comprises a composite material, in particular a fiber reinforced polymer. More specifically, this composite material preferably includes at least one of carbon fiber reinforced polymers, glass fiber reinforced polymers, and aramid fiber reinforced polymers.

According to one aspect, each of the at least two push rods 15b is shown in Fig. 1 and so that the control moving member 15 can move the pitch control movements of the pitch control device 14 to the associated pitch levers in Fig. 4. It is provided for coupling to the associated pitch lever of the rotor blades 10 of the ducted tail rotor 8a of FIG. 2. Therefore, the control movement member 15 preferably comprises at least two push rods each coupled to a respective associated pitch lever. More specifically, each push rod typically includes a guide lug for receiving and receiving an associated pitch lever, respectively.

Preferably, one push rod is provided for each pitch lever of each rotor blade 10 of the ducted tail rotor 8a of FIGS. 1 and 2. However, for simplicity and clarity of the drawing, only one push rod is indicated by reference symbol 15b, and only one guide lug provided by this single push rod 15b is indicated by reference symbol 15c. , Only one pitch lever is illustrated and denoted by reference symbol 14b.

It should be noted that, for the sake of simplicity and clarity of description, only one push rod hereinafter indicated by reference symbol 15b is described in more detail. However, this detailed description of the push rod 15b should be understood to be representative for each push rod of the control moving member 15.

According to one aspect, the push rod 15b has at least approximately L-shape. More specifically, the push rod 15b preferably comprises a first portion 15j extending at least approximately radially outward from the annular connector 15a. In other words, the first part 15j is not only firmly attached, but also preferably formed as an integral part of the annular connector 15a, the annular connector 15a which is at least approximately perpendicular to the axis of rotation 15i. ) Exemplarily form radial protrusions each having an extension of ).

Illustratively, the push rod 15b and, in particular, the first portion 15j are formed by creating respective cut-outs in the annular connector 15a. More specifically, according to one aspect, the annular connector 15a initially surrounds the first portion 15j. Then, each cut portion 15f at the outer periphery of the annular connector 15a so that the first portion 15j of the push rod 15b remains between the two adjacent cut portions 15f in the circumferential direction. It is precisely machined by cutting out at least approximately U-shaped parts with

Preferably, the push rod 15b further comprises a second portion 15k that preferentially extends at least approximately perpendicular from the first portion 15j and at least approximately parallel to the rotation axis 15i. The second part 15k is preferably firmly attached and is preferentially formed as an integral part of the first part 15j. Preferably, at least the second portion 15k exhibits a flat design with a rectangular cross section. Exemplarily, the first portion 15j and the second portion 15k form the aforementioned L-shape.

According to one aspect, the push rod 15b is also connected to the annular connector 15a via an associated reinforcing rib 15e. The associated reinforcing rib 15e is preferably arranged between the first part 15j of the push rod 15b and the annular connector 15a.

Further, the push rod 15b preferably includes a soft torsion region 15h and an optional stretchable region 15g. The soft torsional region 15h is preferably arranged in the region of the push rod 15b where the first part 15j meets the second part 15k. Any stretchable area 15g is typically provided as part of the second portion 15k.

According to one aspect, the push rod 15b exhibits a first predetermined rigidity in a direction parallel to the rotation axis 15i of the annular connector 15a (20 in Fig. 4). The push rod 15b also preferably exhibits a second predetermined stiffness in a direction (18a in Fig. 4) in contact with the control moving member 15, and optionally or alternatively, the axis of rotation 15i of the annular connector 15a. A third predetermined stiffness is shown in the direction 19a transverse to ). Preferably, the first predetermined stiffness is greater than the second predetermined stiffness, and preferentially, the third predetermined stiffness is less than the first predetermined stiffness.

FIG. 4 further illustrates the preferred features of the control moving member 15 of FIG. 3. As is clear from FIG. 3, the control moving member 15 is securely attached to the control input member 16 of FIG. 3 using suitable attachment elements 17 of FIG. 3. More specifically, the disk-shaped control input member 16 can preferably be firmly attached to the annular connector 15a of the control input member 15, and thus suitable accommodation for the accommodation of suitable attachment elements 17 The portion 15d is provided preferentially. For example, such suitable receptacles 15d can be implemented as threaded holes or the like.

Exemplarily, in FIG. 4, four push rods of the control moving members 15 arranged one after another in the circumferential direction of the annular connector 15a are indicated by reference symbols 15b, respectively. However, for the sake of simplicity and clarity, each of these four push rods 15b only has a different sub of the reference symbols of the push rod 15b of FIG. 3 to separately illustrate the different features of the push rod 15b of FIG. 3. Subgroups are provided. Nevertheless, it should be noted that each of the four push rods 15b, as well as the other of each of the push rods, preferably not indicated, exhibits all of these described different features.

More specifically, for the first push rod 15b exemplified as the push rod displayed at the far left in Fig. 4, the first portion 15j, the second portion 15k, the reinforcing rib 15e, and the pitch lever ( Only the guide love 15c provided for connection to 14b) is shown. According to one aspect, the first push rod 15b is a direction parallel to the rotation axis 15i of the annular connector 15a, that is, the movements of the first push rod 15b in the direction 20 The first predetermined rigidity in (20) is shown. Preferably, the reinforcing rib 15e provides a first predetermined stiffness.

For the second push rod 15b, exemplified as the second marked push rod from the left in FIG. 4, only the torsionally soft region 15h is marked, which is also indicated by the indication 18 It is emphasized by way of example. According to one aspect, the second push rod 15b is a second predetermined in a direction 18a in contact with the movement of the second push rod 15b in the direction 18a, that is, with respect to the control moving member 15. Indicates the stiffness of Preferably, the soft torsional region 15h provides a second predetermined stiffness. Preferentially, the first predetermined stiffness is greater than the second predetermined stiffness.

For the third push rod 15b exemplified as a push rod marked third from the left in FIG. 4, only any or alternative stretchable regions 15g are marked, which are also indicated by the marking 19. It is emphasized by way of example. According to one aspect, the third push rod 15b is a direction transverse to the rotational axis 15i of the annular connector 15a, that is, the movements of the third push rod 15b in the direction 19a The third predetermined stiffness in (19a) is shown. Preferably, any or alternative stretchable area 15g provides a third predetermined stiffness. Preferentially, the third predetermined stiffness is less than the first predetermined stiffness.

For the fourth push rod 15b exemplified as the fourth push rod displayed from the left in Fig. 4, only the cut-out portion 15f is displayed. According to one aspect, this cut-out portion 15f has at least a substantially U-shape and is typically disposed between the third push rod 15b and the fourth push rod 15b.

The first predetermined stiffness is typically illustrated for only the first push rod 15b, the second predetermined stiffness is typically illustrated for only the second push rod 15b, and the third predetermined stiffness is typically illustrated only for the second push rod 15b. It should be noted that typically illustrated for the 3 push rod 15b, the cut-out portion 15f is typically illustrated as being only disposed between the third push rod 15b and the fourth push rod 15b. . However, as explained above, all of these features are preferably applied to each of the push rods 15b, often as described above with respect to FIG. 3.

In addition, it should be noted that according to one aspect of the present invention, the stretchable area 15g is only arbitrary. As described above, the stretchable region 15g may also be provided instead of the torsion-soft region 15h. In this case, the push rod 15b includes a first predetermined stiffness in the direction 20 and a second predetermined stiffness in the direction 19a. In this case, the first predetermined stiffness is the second predetermined stiffness. Greater than In this case, the reinforcing rib 15e again provides a first predetermined stiffness, and the now stretchable region 15g provides a second predetermined stiffness. Therefore, it should be noted that all such further modifications are also within the common sense of a person skilled in the art and are therefore also considered to be part of the invention.

1: rotorcraft 1a: main rotor
1b: fuselage stain section 2: fuselage
2a: tail boom 3: shroud
4: bumper 5: pin
5a: tail wing 5b: rudder
6: transverse duct 7: ducted tail part
8: counter-torque device 8a: counter-torque rotor
8b: Counter-torque stator 9: Counter-torque rotor hub
9a: rotor hub cover 10: counter-torque rotor blades
11: Drive shaft fairing 12: Gearbox fairing
13: stator vanes 14: pitch control device
14a: pitch control shaft 14b: pitch lever or horn
15: control movement member 15a: annular connector
15b: push rod 15c: guide lug
15d: receiving portion 15e: push rod reinforcing rib
15f: push rod cutout 15g: elastic push rod area
15h: soft torsional push rod area
15i: rotating shaft 15j: radially protruding portion
15k: axial lever portion 16: control input member
16a: central portion 16b: pitch control shaft receiving portion
17: attachment element
18: Show the soft torsion push rod area
18a: Lateral movement in the circumferential direction
19: flexible push rod area display
19a: radial inward motion
20: longitudinal rigidity direction

Claims (15)

As a control transfer member 15 for a pitch control device 14 of a ducted rotorcraft tail rotor 8a,
It comprises an annular connector (15a) comprising at least two push rods (15b) constituting the rotating shaft (15i) and extending partially or wholly parallel to the rotating shaft (15i),
Each of the at least two push rods 15b is provided for coupling to an associated pitch lever 14b of the rotor blade 10 of the ducted rotorcraft tail rotor 8a,
Each of the annular connector (15a) and the at least two push rods (15b) comprises a composite material,
Each of the at least two push rods (15b) includes a first predetermined rigidity in a direction (20) parallel to the rotation axis (15i) of the annular connector (15a), and the control moving member (15) A control movable member comprising a second predetermined rigidity in a direction (18a) in contact with ), wherein the first predetermined rigidity is greater than the second predetermined rigidity. The method of claim 1,
Each of the at least two push rods (15b) has a first portion (15j) extending at least radially outward from the annular connector (15a), and at least vertically from the first portion (15j) and the axis of rotation A control movement member comprising a second portion 15k extending at least parallel to (15i). The method of claim 2,
At least one of the at least two push rods 15b is an associated reinforcement disposed between the first portion 15j of at least one of the at least two push rods 15b and the annular connector 15a Control movement member connected to the annular connector 15a through a rib 15e. The method of claim 1,
Each of the at least two push rods (15b) has at least an L-shape. The method of claim 1,
Each of the at least two push rods (15b) is connected to the annular connector (15a) via an associated reinforcing rib (15e) to provide the first predetermined rigidity. The method of claim 1,
Each of the at least two push rods (15b) comprises a torsional-soft region (15h) to provide the second predetermined stiffness. The method of claim 1,
Each of the at least two push rods 15b includes a third predetermined rigidity in a direction 19a transverse to the rotation axis 15i of the annular connector 15a, and the third predetermined rigidity Is smaller than the first predetermined rigidity. The method of claim 7,
Each of the at least two push rods (15b) includes an elastic region (15g) to provide the third predetermined rigidity. delete The method of claim 1,
The composite material is a fiber-reinforced polymer. The method of claim 10,
The composite material comprises at least one of carbon fiber reinforced polymers, glass fiber reinforced polymers, and aramid fiber reinforced polymers. The method of claim 1,
The annular connector (15a) and at least two push rods (15b) form a spider-shaped structure. As a pitch control device 14 for the ducted tail rotor 8a of the rotorcraft 1,
The control moving member (15) according to any one of claims 1 to 8, 10 to 12, and
A disc-shaped control input member 16 provided for mounting on the associated pitch control shaft 14a of the ducted tail rotor 8a,
The control input member (16) is firmly attachable to the control movement member (15), a pitch control device. The method of claim 13,
The control input member (16) is firmly attachable to the control moving member (15) in a releasable manner. delete

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