JPH06127484A - Pitch variation controller of helicopter wing - Google Patents

Abstract

PURPOSE: To provide a pitch change controller for helicopter wings which has a simple structure and maintenance and can attain a high efficiency using operating instructions concerning the direction control for performing desired motions of a helicopter, i.e., control of the cyclic pitch and collective pitch, without danger of impairing the safety during flying. CONSTITUTION: A pair of instruction arms 31, 39 and a first and second bars 22, 33 connected to swing arms 29, 34 are provided for selective transmission of the cyclic pitch and collective pitch. The first bar 22 is coaxially disposed to a bushing 42 connected to a third cross bar 39' and has a third swing arm 34a at the midpoint. Joint vertical connection rods 37 are provided at both ends of the third swing arm 34a and selectively transmit the pitch to a wing positioning mechanism 43. A connection rod 8a engaged with the wing extends from the mechanism 43 through a tubular mast 27.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a controller for a rotor blade of a helicopter, and more particularly to a novel blade pitch change controller for moving a helicopter in a desired direction.

[0002]

2. Description of the Related Art Conventionally, the above type of device is already known, and it is possible to manually control the blade from the machine room to change the position of the helicopter. However, the size of its component parts and the need to tilt the helicopter are unnecessary. The structural and structural factors resulting from the undesired forces that tend to generate vibrations of the vehicle adversely affect the stability of the vehicle. Since this type of machine flies differently than conventional airplanes, a helicopter commander that performs a complex function is one of the most complex parts of a helicopter. In fact, the helicopter is levitated by the motion of the rotor, and the blades of the rotor are manually controlled from the cabin. Vertical fly is generated by the combination of increased rotor rotation and blade pitch. The displacement and the change in direction are performed by inclining the perfect rotation circular surface formed by the rotor blade during the rotation of the rotor blade, which allows the helicopter to move forward, reverse, and move laterally.

Motion occurs as a result of the angle of attack of the wings. Because of this, the wing is in communication with the rotor mast and moves vertically without affecting the mast to perform what is known as fluttering. In addition to this fluttering hinge mechanism, the wing has a powerful and resistant hinge mechanism that allows the wing to move forward and backward slightly at the base height (root height) where it is hinged to the mast. Prevents fatigue destruction.

This type of articulated rotor, having multiple blades that can individually or together flutter to counteract forward movement, transmits commanded motion to the blades to produce cyclic pitch changes, collective pitch changes. It is commanded by an interlocking mechanism in the helicopter called a "circle ring" or "diaphragm". Activating the cyclic pitch command, known as the "lever" on the front of the pilot in the cabin, controls the displacement of the helicopter with respect to the longitudinal and transverse axes, and actuating the pilot's left pitch or collective command causes the vertical axis to move. The displacement of the helicopter is controlled via the. By appropriately combining both commands, that is, the cyclic pitch, the collective pitch and the force generated by the anti-torque rotor, the entire helicopter can be controlled.

As described above, the interlocking mechanism capable of transmitting and controlling the pitch to the blade is known as a "vibrating plate".
Although this mechanism is effective for a specific function, it has a drawback due to the size of the component and the influence based on this size. That is, the vibration plate forms a rotating body, and when a command is applied, a force is generated at a predetermined point on the rotating surface by the link mechanism to rotate the rotating body on a surface different from the common rotating surface. As is well known, the rotating body exhibits a gyroscopic effect.

In a mechanism called a "vibration plate" as shown in FIGS. 13 and 14, the wing 3 is hinged to the mast 2 by the flexible portion 5, and the hub 1 functioning as a chin portion is fixed to the mast 2. The wing makes a semi-rigid motion about its flap axis a. The wing 3 has a swing arm 6 connected to its base.
It can be smoothly rotated around the pitch changing spindle 7. The vibrating plate 9 includes a rotating portion 9a and a fixed portion 9b connected to the cyclic / command lever 11 by a rod 10, and the swing arm 6 is pivotally attached to the connecting plate 9 by a connecting rod 8.

The motion of moving the diaphragm 9 up and down is added to the motion of the cyclic pitch command. The fixed portion 9b is connected to the means for transmitting the vertical movement when the collective pitch command 12 is activated. Cyclic pitch mechanism 11
Has an arm 13 that transmits a force that tilts the diaphragm 9 in the longitudinal direction, and an arm 14 that engages the command arm 15 and tilts the diaphragm laterally.

When the cyclic control command 11 is actuated from the machine room, the command is transmitted by the belt-shaped member 8 ', so that the conventional type of command given to the so-called joint rotor causes the vibration lever connected to the wing 3 by the link mechanism. 9 can be moved and tilted arbitrarily. The wing 3 is a diaphragm 9
The desired movement is achieved by following the inclination of a and fluttering to determine the position where the rotary plate is inclined.

Since the vibrating plate 9 moves up and down on the rotating shaft and similarly displaces the connecting rod 8 connected to the blade 3, the blade 3 is moved regardless of the position of the blade 3 by the operation of the collective pitch command 12. The pitch of is increased or decreased, and the blade is kept parallel to the rotation axis of the mast 4.

Since the mechanism schematically shown in FIGS. 13 and 14 is coaxially arranged outside the shaft for transmitting the rotational force to the blades of the main rotor, it is necessary to use a large diameter bearing. further,
The spherical pivot member of the diaphragm is enlarged so that the shaft can pass through its center.

In the above mechanism, it is necessary to use the automatic lubrication mechanism or the spherical pivot member for the movable part, which increases the friction of the command mechanism.

Due to its size, the mechanism called "vibration plate" is a rotating body which exhibits the gyroscopic effect when rotating on different planes. The control rod, which actually transmits the movement of the control lever in the cabin, moves the wing to a point 90 ° forward of the position where the desired displacement is produced by the gyroscopic movement.

The blade acts as a gyroscope when actuated rapidly, and is rotated 90 degrees in the direction of rotation where torque or force is applied.
Give resistance to the ° point. Thus, when the cyclic control device moves, this motion is transmitted to the rotor by the link mechanism, and a force is generated at a predetermined point on the rotating surface with respect to the point at which the force is applied.

Since this gyroscope effect affects the command and disturbs the stability of the helicopter, it is necessary to devise the command. To overcome this drawback, servo command 16 or friction damper 17 device is used to limit the motion of the wing as shown in Fig. 15 to maintain the center of gravity without changing the wing and helicopter levitation during flight. We try not to make excessive changes that affect the.

Most helicopters also use stabilizing bars to prevent destabilization. The bar rotates beneath the joint rotor and acts as a gyroscope that maintains the axis of rotation, avoiding vibrations that disturb the machine.

[0016] As described above, the conventional command mechanism called "vibration plate" has some drawbacks although it fulfills a specific purpose, and as a result of the aforementioned drawbacks that disturb the stability of the helicopter, Friction dampers and stabilizing bars were used to avoid excessive vibrations due to changes in the center of gravity of the device.

Therefore, the problem of asymmetrical levitation obtained by using proper positioning of the attack angle of the wing is of great concern, and at present the proper positioning is obtained by the mechanism described above, which is sized. Since it is large, it is necessary to further devise the command so that this effect is not impaired.

[0018]

SUMMARY OF THE INVENTION It is an object of the present invention to provide directional control, or cyclic control, for causing a helicopter to perform a desired motion without risking safety during flight.
An object of the present invention is to provide a device having a simple structure and maintenance that can achieve high efficiency by using operation commands related to control of pitch and collective pitch.

[0019]

The present invention relates to a pitch change control device for a helicopter blade, which issues a manual command for a large and small wing length helicopter, and is attached to an end of a command mast rotatably instructed on a helicopter structure. At least 1
A main rotor having a pair of wings and rotating about the axis of rotation of the command mast, the wings being attached to a hub on the mast via flap flexures, the flexures being perpendicular to the axis of rotation of the mast. The connecting rod that determines the cyclic pitch changing axis in the direction, and transmits the cyclic pitch and collective pitch is commanded by the mechanism that positions the connecting rod with respect to the mast, and the lever device mounted in the structure is A lever, a cyclic pitch generally called a pitch, a collective pitch
In a pitch change control device, comprising a pair of command arms for pitch, the wings being connected to a pitch swing arm connecting to an end of a connecting rod and to a lever device, the lever devices being mutually It is provided with a pair of first and second bars which are parallel and separated from each other, and the first bar has an articulated structure and forms a cantilever bar with respect to a fixed support portion to the helicopter structure. Connected to a cyclic pitch command arm by connecting it to a cantilever bar with a one-joint swing arm, and the cantilever bar is supported at a fixed point on the structure in the lateral direction of a pair of bars and is integrated with the collective pitch command arm. Coaxially to a bush that articulates to a third bar, the free ends of the pair of bars are interconnected by a second swing arm that is connected to the cantilever bar, with the cantilever bar at a midpoint. 3 swing And a connecting rod arranged vertically for selectively transmitting the pitch to the blade positioning mechanism at the ends of the third swing arm and the second swing arm. The mechanism is composed of both pitch transmission parts, has a joint point for a connecting rod and a yoke rotatably attached to the member, transmits the cyclic pitch, and the member transmits an angle with respect to the rotation axis of the mast. Position and axial position can be taken, the yoke has a joint portion in the lateral direction with respect to the mast rotation axis,
The joint comprises means for connecting a pair of connecting rods parallel to the axis of rotation, the means being connected to a lateral pin to the yoke and arranged in the mast tube for a pair of connecting rods. Is connected to a swing arm that positions the rotor blades.

The gist of the present invention is to provide a command for an operation related to directional control for causing a helicopter to perform a desired motion, that is, control of cyclic pitch and collective pitch, without risking the safety during flight. It is a device that is simple in structure and maintenance that can be used to achieve high efficiency. Although the diaphragm is one of the main causes of the problem due to its size, the present invention does not have a diaphragm, and thus provides a simple device that largely overcomes the above-mentioned drawbacks.

The device of the present invention can be applied to any helicopter of any size, and the cyclic pitch and the collective pitch are transmitted by the device having the minimum number of parts. This minimum parts count device is fastened to the wing by two connecting rods on the one hand, and to a pair of levers by three connecting rods on the other hand to form a manual command device in the cabin for steering the helicopter. Is possible.

The arm of the tripod has a tubular central portion,
The pins of the bearing yoke on the two small bearings are rotatably mounted in the center. The three connecting rods are articulated via their ends to the arms of the tripod, so that the collective pitch can be transmitted in the same way as the cyclic pitch.

On the other hand, the yoke has a pair of parallel arms,
Each arm includes a bearing that defines the joint axis of the cross member. The cross member is provided with two recesses for bearings which form the connection points of the ends of the pair of connecting rods. The connecting rods each engage each wing and are kept parallel to the rotor axis at all times during pitch transmission.
Determine the pitch and collective pitch.

Since the yoke rotates together with the rotor mast and is linked to the tripod-like member, the yoke can take an angle and height exactly the same as the tripod-like member takes according to the command lever.

The three connecting rods for transmitting cyclic pitch and collective pitch, which are connected to the arms of the tripod-shaped member, are connected via the lower end to the end of the bar having one end and the other end connected to the support. It is articulated and at the midpoint of the bar is articulated to both ends of a cross member or rocker arm fixed to the bar. Further, since the bar is connected to the pitch, the connecting rod can move vertically according to the pitch to transfer the collective pitch to the blade.

The joint end of the bar is connected to a command arm for performing the cycle pitch of the wing. The command arm is fixed to a swing arm connected to the bar and the second bar, and an end portion of the second bar operates a third one of three connecting rods connected to the tripod member. Connect to the arm of the swing arm. Each connecting rod is selectively displaced by the command of this arm corresponding to the "lever", and the yoke takes an angle similar to that of the tripod member.

Therefore, in the both-type diaphragm and the present invention, the pitch of the blade is determined by vertically displacing the connecting rod connected to the blade to change the vertical position of the support point of the rod.

In the case of a two-blade helicopter, the straight line connecting the support points of the connecting rods that articulate the blades forms one plane when the blades rotate, so this plane is a plane perpendicular to the mast corresponding to the main rotor. The angle they make and the vertical distance to the zero level determine the vertical position of the connecting rod connected to the wing at any given moment.

The apparatus of the present invention is novel in that the inclination of the reference plane and the vertical position can be obtained by different methods. Conventionally,
The angle of the reference plane is determined by the two connecting rods on which the cyclic pitch lever acts and the pivot point of the diaphragm, the vertical position of the reference plane being determined by the other connecting rods from the collective pitch. It is determined by raising and lowering the pivot point. In short, it is necessary to use a diaphragm mounted on a displaceable support of the vertical axis of the rotor. Therefore, in order for this diaphragm to be able to pivot beyond its own center, it must be outside the shaft which transmits the force to the main rotor.

Since the reference plane of the device of the present invention is defined by three connecting rods without pivot points, it is necessary to use a large diameter bearing to overcome the shaft diameter in any helicopter. It is not necessary to use the diaphragm, which had been upsized.

As described above, the known device behaves as a rotating body due to the large size required, and when it rotates on different planes, a gyro effect is produced, and the result disturbs the command and the stability of the device. For this reason, it is necessary to use mechanical friction dampers and stabilizing bars to avoid the loss of stability of the device during flight.

On the other hand, since the device proposed by the present invention is small in size and has almost no gyroscopic effect, it is possible to directly use the command, and it is not necessary to use the stabilizing means without elaborating the command. . This feature is suitable for small helicopters where conventional devices are not applicable due to their size.

Since the number of parts used is small, the manufacturing cost is significantly lower than that of the conventional device. Also, with this new collective pitch and cyclic pitch controller, the helicopter is extremely stable no matter what maneuver it takes during flight.

The present invention will be described in detail below with reference to examples.

1 to 12, the mechanism for manually commanding the blade pitch of the helicopter is a manual operation lever device 20.
And a device 21 for positioning the support points of the connecting rods 8a-8'a which drive the wings 3a. The "diaphragm mechanism" has been described with reference to FIGS. 13 and 14 and its drawbacks have already been described. The cyclic pitch and collective pitch in the case of this mechanism are set by the devices 20-21.

As shown in FIGS. 1 and 6, the lever device 20 includes a main cantilever bar 22. The bar has end pins 23 that are connected to a support 24 that is an integral part of the tubular structure or frame 25. Figure 12 shows the overall shape of the tubular frame.
Shown in. The upper portion of the structure 25 is defined by a platform 26 on which the tubular mast 27 is mounted. The wing 3a is attached to the upper free end of the tubular mast (see FIG. 3), the lower end of the mast being attached to the wing 3a positioning device by a plate 27 'in a groove 27 ".
Articulate to 21.

The cantilever bar 22 is connected to a lateral pin 28 at a position of an end spaced apart from the supporting portion 24, and a pair of small plates 29'-2.
The first swing arm 29 made of 9 ″ is attached to the bar 22 by the pin 28.
It is attached to both sides of. Then, the end of the plate 29'-29 "is fixed to the arm 31 by the fixing member 30. A so-called cyclic command" lever "arranged on the front face of the pilot.
The lever device 20 constituting the above is operated by the arm 31.

The opposite end of the small plates 29'-29 "is attached to the second bar 33.
Is connected to a pin 32 for pulling. The second bar extends parallel to the bar 22, and the free ends of both bars 22, 23 are linked by the second swing arm 34. The second swing arm has a joint shaft 35.
A small bent plate connected to the first bar 22 and the branches 34'-34 "of this small bent plate are connected by pins 36-36 'to the second bar 33 and the lower end of the vertical connecting rod 37, respectively. It

At a position adjacent to the second swing arm 34, the bar
22 includes a third swing arm 34a. The third swing arm is fixed to the bar 22 and comprises a small lateral plate. The free ends of the small transverse plates are connected to the lower ends of the connecting rods 37 ', 37 "by pins 38, 38'. These connecting rods are end connecting rods.
Together with 37, the positioning means of the positioning device 21 is formed.

Further, the lever device 20 is provided with a second command arm 39 corresponding to a collective pitch which is usually arranged on the left side of the pilot. This arm 39 has a portion 39 'which is transverse to the bars 22, 33 and which connects to a fixed point 40 of the structure 25. The middle point of this part 39 'of the arm 39 then forms a lever arm 39 "and is connected to a shaft 41, which is connected to a tab 42' of a bush 42 coaxial with the bar 22.

The illustrated connecting rods 37, 37 ', 37 "are arms.
The movements of the blades 31 and 39 are transmitted to the positioning device 21 of the connecting rods 8a and 8a 'for driving the blade 3a to set the cyclic pitch and collective pitch of the blades.

As can be seen from the structural relationship of the elements of the device 20, the cyclic pitch command arm 31 has arrows a and b.
When displaced as described above, the first swing arm 29 articulates on the pin 28 fixed to the bar 22. Due to this back-and-forth movement, the bar 33 is displaced as shown by the arrow c, and as a result, the second swing arm 34 makes a selective articulation around the pin 35.

When the arm 31 is further displaced laterally, the bar 22 pivots on its axis as shown by arrows d and e, and moves the third swing arm 34a as shown by arrows f and g. The entire device 20 articulates up and down as shown by arrows h and i to move the arm 39 corresponding to the pitch.

The device 21 comprises a tripod member 43. This member comprises a tubular central portion 44 from which three strip-shaped arms 44,
Protruding 45 ', 45 ". Two band-shaped arms
45 ', 45 "is in the mid-plane of the central portion 44 and the rest of the strip arms 45 are in the plane perpendicular to the mid-plane. Therefore, the arm 45 is spaced 90 ° from the arms 45', 45". is doing. The arm 45, 45 ', 45 "is formed with a row of holes 46, 46', 46" for positioning the corresponding pin 46, 46 ', 46 "which is connected to the upper end of the connecting rod 37, 37', 37". ing. The arms 45 'and 45 "and the third swing arm 34a are on the same plane.

A pair of bearings 48 of the tripod member 43 are connected to both ends of the central portion 44. Therefore, the shaft 49 of the yoke 50 fixed by the fixing member 51 to the shaft end 4a of the central member 44.
It is possible to rotate. The shaft 49 of the yoke 50 is arranged coaxially with the rotation axis x of the rotor 4.

The yoke 50 is provided with a pair of arms 52, 52 'for balancing the cross member 54. Bearings 53 and 53 'are fitted in these arms to define an axis y in the lateral direction with respect to the rotation axis x of the mast 4. The journal shafts 55, 55 'at both ends of the cross member are rotatably fitted in the bearings 53, 53'.

The cross member 54 comprises two parts 54 'and 54 ", which are of the same shape and have a pair of opposed recesses. The two parts together form a housing, The bearings 57, 57 'are housed at positions where the pair of connecting rods 8a, 8a' connect around the link pins 58, 58 '. As described above, the connecting rods 8a, 8a' connect to the wing 3a. It engages with the arm 6a, and moves the blade with respect to the flexure portion 5a according to the pitch change.

The connecting rods 8a and 8a 'are arranged inside the mast 27 and are parallel to the rotation axis x of the mast 27. The tubular mast 27 is connected to the interior of the crosspiece member 54 by a pin 59 passing through both parts 54 ', 54 "of the crosspiece member. The tubular mast 27 projects through the platform 26 of the structure 25. The tubular mast 27 can be freely rotated by means (not shown) provided on the table.

Next, the operation of the present invention will be described with reference to FIGS. 10, 11 and 12.

When the pilot operates the command arm 39 pitch in the direction of arrow m in the collective pitch command of FIGS. 1 and 11, the bar 39 'integrated with the arm is fixed at a fixed point.
It is moved around 40 in the direction of the arrow m'and angularly displaces the lever arm 39 "connected to the bush 42 by the shaft 41. As a result, the bar 22 on the support 24 articulates and swings. 34, 34a are lifted (Fig. 7), so that the upper ends of the connecting rods 37, 37 ', 37 "are engaged with the arms 45, 45', 45" of the tripod-like member 43 (Fig. 11). The bearing or coupling point changes the vertical position of the tripod.

The tripod member 43 is a cross member by the yoke 50.
Since it is attached to the 54, the vertical displacement of the tripod-shaped member 43 is transmitted to the cross member 54, and therefore the connecting rods 8a, 8a '.
Moves upward in parallel with the rotation axis x of the mast 27.

The command arm 39 is directed in the direction opposite to the above, and the arrow m
When actuated in the direction, the connecting rods 8a, 8a 'descend in reverse and change the plane of rotation of the blade 3 (Fig. 11).

When the cyclic pitch command is issued, the pilot operates the arm 32. This arm performs a series of movements by a link mechanism and is generally called a "lever". When arm 31 is moved in the direction of arrow o, FIG.
Swing arm 29, FIG. 1 is articulated around pin 28 and pin 32 pulls bar 33. When the bar 33 moves, the second swing arm 34
Is articulated around pin 35 of bar 22 and branch of arm 34
34 ″ is angularly displaced. This angular displacement causes the connecting rod 37 to rise and change the position of the tripod 43 (FIG. 10).
The rotation surface of the yoke 50 changes.

Since the connecting rods 8a and 8a 'are attached to the yoke 50 by the cross member on the yoke 50, the connecting rods 8a and 8a' periodically move up and down in parallel with the rotation axis x of the tubular mast 27 with respect to the surface formed by the tripod member 43. .

When the arm 31 is displaced in the direction of the arrow p, FIG. 12, the operation opposite to that described above is performed, as can be easily understood from FIGS.

When the arm 31 is moved in the direction of arrow q together with the first swing arm 29, the bar 22 is rotated in the direction of arrow q to move the third arm.
The oscillating arm 34a tilts, and this tilting lowers the connecting rod 37 ″ and raises the connecting rod 37 ′, but the position of the connecting rod 37 does not change (FIG. 1).
The position of the member 43 is changed so that the yoke 50 and thus the engagement member 54 of the connecting rods 8a, 8a ', the new plane of rotation of FIG.

As a matter of course, if the arm 31 is moved in the direction of the arrow n, the operation opposite to the above-mentioned displacement is performed.

[0058]

As described above, in general, a "lever",
By combining the movements of the arms 31, 39 called "pitch", a desired cyclic pitch or collective pitch can be obtained for all steering functions of the helicopter.

[Brief description of drawings]

FIG. 1 is a perspective view showing main elements of a helicopter blade pitch manual command mechanism according to the present invention.

FIG. 2 is an exploded perspective view of a mechanical device of the present invention for changing a support point of a connecting rod for angular positioning of a wing.

FIG. 3 is a front view of a portion of the apparatus of FIG. 2 related to a helicopter structure.

FIG. 4 is a cross-sectional plan view of the device for determining the position of the connecting bearings of the connecting rods connecting to the wing and the position of the cross members articulating the connecting rods.

5 is a cross-sectional view taken along line 1-1 of FIG.

FIG. 6 is a schematic side view showing a manual lever device which is arranged in the cabin to position the connecting rod command device.

7 is an enlarged view of the lever device of FIG.

FIG. 8 is a front view of the lever device, and is a diagram showing the movement of one swing arm when applying joint force and applied force to two connecting rods by imaginary lines.

FIG. 9 is a perspective view showing the joining of the cross member and the blade of the pitch transmitting device to the blade.

FIG. 10 is a schematic diagram showing different positions taken by a device for transmitting pitch to a blade to determine cyclic pitch.

FIG. 11 is a schematic view showing different positions taken by the pitch transmission device for inducing a collective pitch.

FIG. 12 is an overall schematic view of a mechanism of the present invention incorporated in a helicopter structure, and is a view for explaining different movements of elements.

FIG. 13: Conventional cyclic type called “vibration plate”
It is a schematic diagram showing a pitch and collective pitch determining mechanism.

FIG. 14 is a diagram showing details of a position taken by a diaphragm when setting a cyclic pitch on a blade.

FIG. 15 is a diagram showing details of a helicopter wing incorporating a mechanical friction damper and a servo command for limiting the movement of an element that assists the use of the diaphragm.

[Explanation of reference symbols]

 1 mast hub 2 mast 3 rotor blade 5 blade flexure 6 swing arm 8 connecting rod 9 vibration plate 11 cyclic pitch command lever 12 collective pitch command lever 20 lever device 21 positioning device 22 first cantilever bar 27 Tubular mast 29 First swing arm 31 Cyclic command arm 33 Second bar 34 Second swing arm 34a Third swing arm 37 Vertical connection rod 39 Collective command arm 42 Bush 43 Tripod member 44 Tubular central portion 45 3 Arm 50 yoke 54 cross member

Claims (10)

[Claims] 1. A pitch change control device for a helicopter blade, which particularly issues a manual command to a large and small wing length helicopter, wherein at least 1 is attached to an end of a command mast (27) rotatably supported on a helicopter structure. A main rotor (4) having a pair of blades (3) and rotating around the rotation axis of the command mast, and a hub on the mast via the blade (3) flap flexure (5)
A connecting rod that is attached to (1), defines the axis for changing the cyclic pitch in a direction perpendicular to the rotation axis of the mast (27), and transmits the cyclic pitch and collective pitch ( 8) Mast the connecting rod
A lever device installed in the structure ordered by the mechanism for positioning with respect to (27) is installed in the helicopter machine room and is a pair for cyclic pitch and collective pitch generally called "lever" and "pitch". Pitch change control in which the wing (3) is connected to the pitch swing arm (6) connected to the end of the connecting rod (8) and is connected to the lever device. In the device, the lever device (20) includes a pair of first and second bars (22, 33) which are parallel to each other and spaced apart from each other, and the first bar (22) has an articulated structure and fixedly supports the helicopter structure. A cantilever bar is formed for the part (24), and the bars (22, 33) are linked to the cantilever bar (22) by the first joint swing arm (29) near the support part to provide a cyclic pitch command. Connected to the arm (31), the cantilever bar (22) is located next to the pair of bars (22, 33). Is supported on a fixed point of the structure in the direction the collective pitch command arm (3
9) is coaxially arranged with the bush (42) connected to the third bar (39 '), and the free ends of the pair of bars (22, 33) are connected to the cantilever bar (22). The cantilever bar (22) is interconnected by a second swing arm (34) and has a cross member (34a) as a third swing arm at an intermediate point. At the end of the arm, a vertically arranged connecting rod (3) for selectively transmitting the pitch to the blade positioning mechanism (21).
7) is hingedly connected, and the mechanism (21) consists of both pitch transmission parts (44-45), and the joint point (47) for the connecting rod (37) and the yoke (rotatably attached to the member (44). 50) and transmitting the cyclic pitch, and the member (44) can take an angular position and an axial position with respect to the rotation axis of the mast (27). It comprises a joint (54) transverse to the axis of rotation of the mast, said joint comprising means for connecting a pair of connecting rods (8a) parallel to the axis of rotation, said means comprising a transverse pin. A pair of connecting rods (8a) connected to the yoke (50) via a pipe (27) forming a mast.
The swinging arms (34, 34) for positioning the rotor blades (3)
A helicopter wing pitch change control device characterized by being connected to a). 2. The first swing arm (29) comprises a pair of small plates (29 ', 29 ") on both sides of the cantilever bar (22), the midpoint of these small plates being a cantilever bar (29). 22) is connected to a connecting pin (28) on the lateral side, and the bottom of the plate is parallel to the cantilever bar (22).
Device according to claim 1, characterized in that it is connected to 3) by a second pin (32) and the upper end of the plate (29 ', 29 ") is fixed to the cyclic pitch command arm (31). 3. The second swing arm (34) comprises a bending member,
The first branch portion (34 ″) of this bending member is connected to one of the connecting rods for driving the blade positioning device (21), and the second branch portion (34 ′).
Is connected to the second bar (33), and the middle point of the bending member is the first bar.
Device according to claim 1, characterized in that it is connected to the lateral pin (35) with respect to (22). 4. The third swing arm (34a) is formed by a cross member provided between the second swing arm (34) and a bush (42) connecting the collective pitch command arm (39). The apparatus of claim 1, wherein the apparatus is: 5. A pair of tabs forming a part of the bush (42) by connecting a third bar (39 ') to the bush (42) by means of a small arm (39 ") projecting vertically from its midpoint. A connecting pin (41) fixed to (42 ') is inserted into it across the free end of the small arm, the bush being slightly larger in diameter than the first bar (22) and having a cyclic pitch. 7. The rotation displacement of the first bar according to the operation of the command arm (31) and the vertical displacement of the pair of bars according to the operation of the collective pitch command arm (39) are possible. 1 or 4
Equipment. 6. A blade positioning mechanism (43) having both pitch transmission members comprising three band-like arms (45) protruding from a tubular central portion (44) having a vertical axis so as to extend beyond the upper end of the members. A tripod-like member having a strip arm (45) angularly spaced by 90 ° and comprising a row of holes (47) for articulating the vertical connecting rod (37), wherein the strip arm (45) comprises two The individual pieces are on the same plane and form a pair with the end of the third swing arm (34a), and the third arm (45) forms a pair with one of the branches of the second swing arm (34). The apparatus of claim 1 characterized. 7. The tubular central portion (44) of the tripod member (43) forms a bush of the journal shaft (49) of the yoke (50), and the shaft (4)
Device according to claim 1, characterized in that 9) is rotatably supported between a pair of end bearings (48) of the central part (44). 8. A yoke (50) is provided with a U-shaped portion fixed to a shaft (49) and arranged at an upper end of a central portion (44) of the tripod-shaped member.
The profile branch (52) comprises a bearing (53) defining an articulation axis for the member (54) transmitting the pitch to the connecting rod (8a) for driving the wing (3). Device according to claim 1 or 7, characterized in that it is provided transverse to the axis of rotation of the mast. 9. The blade pitch transmission member (54) has an opposed recess (56) for receiving a lower end of a connecting rod (8a) engaged with the blade (3).
And a member (5) at the bearing (53) of the yoke branch (52) at both ends of the symmetrical member.
The part (59) forming the joint axis of (4) is provided, the holes aligned horizontally are provided in the symmetrical member, the connecting pins (58) are inserted into these holes, and the blades extending parallel to the mast rotation axis ( 3) The connecting pin crosses the lower end of the drive connecting rod (8a) protruding from the tubular mast (27).
Equipment. 10. A yoke (50) freely rotates together with a mast (27) inside a tubular central portion (44) of a tripod-shaped member (43), and a cyclic pitch command arm (31) is formed. Depending on the movement of the collective pitch command arm (39), the tripod member (4
10. The device according to claim 1, wherein the angle and height of 3) are accurately determined.