JP2001097288A - Helicopter ducted fan - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a helicopter ducted fan provided at the tail structure of a helicopter, capable of preventing a torque generated on the helicopter, used for operation of yawing and polarity, and capable of eliminating such defects that an efficiency is low because a clearance between the blade end of a rotor blade and a duct inner peripheral surface cannot be reduced and the diameter of a hub is increased and the operating space for the rotor blade is reduced because a rotor blade drive device and a pitch control device are incorporated in the hub. SOLUTION: This helicopter ducted fan comprises bearings connecting the blade end of a rotor blade, provided between the inner peripheral surfaces of a ring rotating in a duct and a duct and the outer peripheral surface of the ring, and reducing a clearance between the blade end of the rotor blade and the inner peripheral surface of the duct with the rotor blade is rotated so that the rotor blade can be rotated at high speeds 11. Thus, a trouble that the clearance produced between the blade end and the inner peripheral surface of the duct is increased can be eliminated.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention prevents a helicopter from rotating when the main rotor provided above the helicopter is rotated in a direction opposite to the direction of rotation of the main rotor. The present invention relates to a helicopter-ducted fan for maintaining operability such as yaw stability at the time of hovering or flight, a direction for stably directing an accurate flight direction, and in particular, a wing tip of a rotor blade and a rotor blade. The shroud, which forms the tail structure of the helicopter for installation, has a small gap with the inner peripheral surface of the duct that is horizontally penetrated in the direction perpendicular to the fuselage axis, reducing the outflow of working fluid from the gap, The present invention relates to a helicopter ducted fan capable of improving the operating efficiency of a rotor blade.

Further, the present invention can reduce the diameter of a hub that supports the base end of a rotor blade that is disposed at the center of a duct and that rotates by the operation of a ring whose wing ends are connected to each other. The present invention relates to a helicopter ducted fan that can reduce the ratio of the diameter of the hub to the diameter of the rotor, thereby increasing the working space of the rotor blade, and thereby reducing the diameter of the duct provided horizontally through the shroud and the diameter of the rotor blade.

[0003]

2. Description of the Related Art In a so-called single-rotor helicopter in which a single main rotor is provided above a helicopter so that the helicopter flies by a lift generated by this rotation, the rotation direction of the main rotor is determined when the main rotor rotates. Since a torque is generated to rotate the helicopter in the reverse direction, it is necessary to prevent the rotation from occurring. Furthermore, when hovering to fly stationary at a certain position in the air, which is a feature of the helicopter, or during flight to fly to the destination to achieve the flight purpose of the helicopter, yaw stability of the helicopter, or There is a demand for operability to ensure flight stability in which a flight can be performed while maintaining an accurate direction.

To this end, as shown in FIG. 9, a fuselage 02 having a main rotor 07 provided thereon is integrated with a tail boom 03 extending rearward, and a tail structure 04 of the helicopter 01 is formed. A shroud 05 to be formed is provided with a duct 06 penetrating horizontally in a direction perpendicular to the direction of the fuselage 02 (front of the fuselage axis), and the center of the duct 06 is provided with a duct 06 as shown in FIG. A hub 09 is supported coaxially with the duct 06 and is supported by a column 08 protruding from the inner peripheral surface. The hub 09 is installed in the hub 09 and a power transmission in which a driving force is transmitted from an engine 013 as described later. By the mechanism 016, the rotor blade 010 is rotated around the outer periphery of the hub 09 to generate a thrust in a direction orthogonal to the body axis direction.

The tail structure 04 is provided in addition to the above-described shroud 05 and extends upward from the shroud 05, and is fixed to the rudder 011 and the rudder 011 orthogonally to the rudder 011 to maintain stability in the flight direction. A horizontal rudder 012 for maintaining the stability of the helicopter 01 in the pitch plane is provided.

The operation of the rotor blade 010 is performed by transmitting the output of an engine 013 installed inside the fuselage 02 to a main gear box 014 and rotating the main rotor 07 as shown in a conceptual diagram of FIG. Axis 0
7a, a part of the driving force is branched off, and the tail drive shaft 015 passes through the inside of the tail boom 03 and the inside of the column 08 to form the hub 0.
The power is transmitted to a power transmission mechanism 016 provided in the motor 9 and the power transmission mechanism 016 rotates the rotor blade 010 at a constant speed.

That is, as shown in FIG. 12, a power transmission mechanism 01 is provided at the rear end of a tail drive shaft 015 extending into a hub 09 provided in a duct 06.
6, the bevel gear 017 is fixed, and this bevel gear 017 meshes with the drive bevel gear 018 rotatably supported around the axis of the hub 09 in the tail gear box 09a to rotate. Thus, the hub casing 019 integrated with the drive bevel gear 018 is rotated, and the rotor blade 010 whose base end is fixed to the hub casing 019 is rotated at a constant speed.

Further, a pitch control device 0 is provided in the hub 09.
20 is provided, and the magnitude of the thrust generated by the rotor blade 010 that rotates at a constant speed is determined by the servo control device 02 constituting the pitch control device 020.
3 is connected to a control stick installed in the cockpit, and the pitch change rod 021 is moved forward and backward as indicated by an arrow by moving the control stick back and forth. Is rotated around the pivot axis to operate.

That is, the rod 027 penetrating through the hub casing 019 is operated in the axial direction in accordance with the amount of rotation of the lever 022, and
By operating the pitch control spider 024 connected to one end of the helicopter 01, the tie bar 025 is operated in accordance with the operation of the pitch control spider 024, and the pitch angle of the rotor blade 010 is changed according to the steering operation. A thrust that can maintain rocking stability or operability for flying in an accurate flight direction is generated.

[0010] Thus, between the blade tip of the rotor blade 010 rotating at high speed in the duct 06 and the inner peripheral surface of the duct 06 for rotating the rotor blade 010 on the outer peripheral surface of the hub 09 supported at the center. Needs to be provided with a gap 027 (clearance), and since the rotor blade 010 extends in the radial direction by centrifugal force due to high-speed rotation, the gap 026 needs to be made large with a margin. . Usually, in the case of the rotor blade 010 provided in the duct 06 of 1 to 1.2 m, a gap 027 of about 5 m / m is provided.

However, the flow of the air passing through the gap 027 acts to reduce the thrust for maintaining the operability of the helicopter 01. Therefore, when the gap 027 becomes large, the rotor having a predetermined size becomes large. The thrust that can be generated by the blade 010 is reduced. For example, the gap 027 described above is changed from the gap 0 of 5 m / m to 3 m / m.
In the case of 6, the thrust of the rotor blade 010 is 5
The effect on the thrust generation of the rotor blade 010 is so great that it is said that it can be improved by 10%.

However, the large-diameter rotor blade 01
When the helicopter 01 is installed, the aerodynamic characteristics of the helicopter 01 at the time of flight are deteriorated due to the increase in the diameter of the duct 06, and a large driving force is required for the operation of the rotor blade 010. It is necessary to increase the diameter of the rotor blade 010, and the weight increases. Further, in order to solve this problem, it is conceivable to change the gap 026 from 5 m / m to 3 m / m. However, if the gap 026 is simply reduced, the rotor blade 010 rotating at a high speed in the duct 06 can be used. , Because it is stretched in the radial direction by centrifugal force,
26 is reduced to about 1 m / m, so that the blade tip of the rotor blade 010 contacts the inner peripheral surface of the duct 06,
There is also a disadvantage that the helicopter 01 cannot be controlled due to damage.

[0013] As described above, the tail drive shaft 015 is transmitted through the inside of the support post 08,
A power transmission mechanism 016 comprising a bevel gear 017 for rotating the rotor blade 010 at a constant speed, a drive bevel gear 018, a hub casing 019 supported by a tail rotor gear box 020, and a control rod installed in a cockpit. The pitch change rod 021 is operated by a steering operation to change the angle of attack of the rotor blade 010, thereby changing the thrust generated by the rotor blade 010. Lever 022, rod penetrating through hub casing 019, pitch control spider 024 connected to one end of this rod, and pitch control spider 0
24, the individual rotor blades 010
Since the pitch control device 020 including the tie bar 025 for changing the angle of attack is built in, the (streamlined) column 08 protruding from the inner peripheral surface of the duct 06 is provided at the center of the duct 06. It is arranged coaxially with the duct 06, and rotates the rotor blade 010 around its outer periphery,
There is also a problem that the diameter of the cylindrical hub 09 that generates thrust increases, and the ratio of the diameter of the hub 09 to the diameter of the duct 06 increases.

That is, a hub 0 incorporating the above-described power transmission mechanism 016 and pitch control device 020
9 has a diameter of 50 to 60 cm, and is provided in a duct 06 having a diameter of 1 to 1.2 m, which is usually drilled in the shroud 05. Large ratio to the diameter of For this reason, the working space of the rotor blade 010 formed between the inner peripheral surface of the duct 06 and the outer peripheral surface of the hub 09 becomes smaller, and the helicopter 01 flies in the yaw stability or the accurate flight direction. In order to install a rotor blade 010 capable of generating a thrust large enough to maintain operability, it is necessary to increase the diameter of a duct 06 provided to penetrate the shroud 05 horizontally, as described above. However, there is a problem that the aerodynamic characteristics at the time of flight 01 deteriorate and the weight increases.

[0015]

SUMMARY OF THE INVENTION An object of the present invention is to provide a conventional helicopter, in particular, a single rotor helicopter, in which the main rotor provided above the helicopter is rotated when the main rotor is rotated. In order to prevent the generation of torque that would cause the helicopter to rotate in the opposite direction, and to maintain the yaw stability and accurate directional maneuverability when hovering or flying the helicopter, The gap between the blade tip of the rotor blade that generates thrust in the direction orthogonal to the inner circumference of the duct where the rotor blade is installed is reduced, and the outflow of working fluid from the gap is reduced, thereby improving the operating efficiency of the rotor blade. To reduce the size of the rotor blade and the duct in which it is installed, and to reduce the gap And by and to provide a helicopter ducted fan capable of preventing damage that may occur in the rotor blades.

According to the present invention, a power transmission mechanism is provided at the center of the duct, and a power transmission mechanism is built in. The drive shaft is transmitted to the transmission mechanism by a tail drive shaft from an engine via a main gear box. In order to solve the problem that has occurred with the increase in the diameter of the hub caused by rotating the rotor blade at a constant speed, the rotor blade is driven by driving the blade tip side instead of driving the rotor blade on the base end side. While operating the blades, the magnitude of thrust is not changed by controlling the pitch of the rotor blades, but by changing the number of revolutions of the rotor blades, eliminating the need for a power transmission mechanism and a built-in pitch control device. The working space of the rotor blades by reducing the ratio of the hub diameter to the duct diameter. Can, consequently is an object of the present invention to provide a helicopter ducted fan that can reduce the diameter of the duct.

[0017]

For this reason, the first helicopter ducted fan of the present invention has the following means.

(1) A shroud forming a tail structure of a helicopter is provided in a duct horizontally penetrated, and is rotated in the duct to generate a thrust in a direction orthogonal to the body axis to rotate the main rotor. In addition to preventing the helicopter torque from being generated at the same time, the wing tips of the rotor blades are connected to each other to maintain yaw stability and operability when hovering or flying the helicopter. Provided with a ring that rotates.

(2) It is interposed between the inner peripheral surface of the duct and the outer peripheral surface of the ring to reduce the gap between the blade end of the rotor blade and the inner peripheral surface of the duct when the rotor blade rotates, and A bearing is provided to prevent the blade tip from colliding with the inner peripheral surface and being damaged, thereby enabling the rotor blade to rotate at high speed in the duct.

(A) Thus, the helicopter ducted fan of the present invention can be provided by the means (1) and (2) described above.
Damage due to contact between the wing tip and the inner peripheral surface of the duct is reliably prevented, the gap generated between the inner peripheral surface of the duct and the outer peripheral surface of the ring is reduced, and the rotor blade can be rotated at high speed. , The flow rate of air flowing out of the gap can be reduced, the operating efficiency of the rotor blades can be improved, the thrust can be increased, and the generation of torque that rotates the helicopter, which occurs in the direction opposite to the rotation direction of the main rotor, is prevented Rotor blades that generate the thrust necessary to maintain yaw stability during hovering or flight of a helicopter and operability for directing an accurate flight direction, and the size of a duct for installing the rotor blades Can be reduced, the aerodynamic characteristics of the helicopter during flight can be reduced, and the weight can be gradually reduced, thereby improving the flight performance of the helicopter. It is possible to above.

A second helicopter ducted fan according to the present invention has the following means in addition to the above means (1) and (2).

(3) A driving force branched from an engine for driving the main engine, which is disposed coaxially at the center of the duct, is transmitted to the base end of the rotor blade via a tail drive shaft, and the rotor blade is connected to the main shaft. A hub with a built-in power transmission mechanism was provided. It should be noted that the power transmission mechanism may be built in the hub as in the conventional case, and a pitch control device may be built in the hub.

(4) In the ring connecting the blade tips of the rotor blades to each other, holes formed in the radial direction of the ring are provided corresponding to the circumferential positions of the blade tips respectively provided.

(5) The blade can be freely moved in the radial direction in a hole formed in the radial direction of the ring to freely expand and contract in the radial direction of the rotor blade which occurs in the radial direction when the rotor blade operates. An end-supporting projection was provided on the blade tip of the rotor blade. In addition, it is preferable that the protrusion that moves in the hole does not protrude from the outer peripheral surface of the ring when the rotor blade is fully extended, and has a length that does not fall out of the hole even when the rotor blade is reduced to the minimum.

(B) As a result, the helicopter ducted fan of the present invention provides the above (3) to (3)
By means of (5), even when the rotor blade is most stretched during high-speed rotation, damage due to contact can be prevented, the rotor blade can be rotated at high speed, and the inner peripheral surface of the duct and the outer periphery of the ring The gap generated between the gap and the surface can be made extremely small, the flow rate of air flowing out of the gap can be reduced, the operating efficiency of the rotor blade can be improved, and the thrust can be increased.

A third helicopter ducted fan according to the present invention has the following features in addition to the features (1) and (2) described above.

(6) The wing tip is fixed to the inner peripheral surface, and is wound around the outer peripheral surface of a ring that rotates in a recess formed in the inner peripheral surface of the duct, and the outer periphery of the ring is moved by the movement. Activate the surface,
A belt was provided to rotate the rotor blade to generate thrust.

(7) An actuator that operates a belt with a driving force supplied directly from an engine that drives the main rotor, a generator that operates with a driving force from the engine, or a pulley that is driven with a driving force supplied from a battery. Provided. The belt is formed of a material such as elastic hard rubber, and the belt is provided between the outer peripheral surface of the belt and a recess formed in the inner peripheral surface of the duct through which the belt passes. It is preferable to provide a pressing roller or the like that presses from the surface.

(C) As a result, the helicopter ducted fan of the present invention has the above (6) to (6) in addition to the above (a).
By means of (7), the power transmission mechanism, the pitch control device, and the like are provided at the center of the duct and are transmitted from the engine to the power transmission mechanism in the hub by the tail drive shaft via the main gear box. Unlike a ducted fan, the rotor blade is rotated by a driving force applied to the rotor blade, and the angle of attack of the rotor blade is changed by a pitch control device to change the magnitude of thrust. The rotor blade is operated via the ring by the driving belt wound around the outer peripheral surface of the rotor blade, so that the rotor blade is driven by the engine, or is charged by the generator driven by the engine or the generator. It is easy to control the speed and drive the motor by the motor operated by the electric power from the battery.

This makes it easy to control the number of rotations of the rotor blade at a fixed pitch angle, and eliminates the need for a pitch control device for changing the thrust of the rotor blade by a mechanical mechanism. Further, even when the rotor blades are operated directly by the driving force from the engine, a transmission mechanism for changing the rotation speed of the rotor blades, that is, the magnitude of the thrust outside the duct, must be provided in the duct, particularly in the hub. And can be installed outside the duct.

As described above, the rotor blade is driven by the driving belt, and the hub can be configured to only support the base end portion of the rotating rotor blade. Therefore, the diameter of the hub can be reduced, and the rotor with respect to the diameter of the duct can be reduced. Since the working space of the blade can be increased, the diameter of the rotor blade and the duct can be reduced, and the rotor required to maintain yaw stability during hovering or flight of the helicopter and operability to direct the correct flight direction. The size of the blade and the duct for installing it can be reduced, the aerodynamic characteristics of the helicopter during flight do not deteriorate, and the weight can be reduced gradually, improving the flight performance of the helicopter be able to.

A fourth helicopter ducted fan according to the present invention includes the following means in addition to the means (6) and (7).

(8) An outer peripheral surface around which the belt is wound is formed in a triangular shape, and an annular ring is provided which is rotated in a recess formed in the inner peripheral surface of the duct.

(9) Two sides formed on the outer peripheral surface of the ring
Each side surface is provided, and a flat contact surface is formed between the belt and the ring, and the ring is pressed by a pressing force applied to the belt, and the rotor blade is driven according to the operation of the belt. A rotating conical bearing is provided.

(D) Thus, in addition to the above (a) and (c), the helicopter ducted fan of the present invention can absorb the thrust force generated by the generation of the thrust of the rotor blade by the conical bearing, and can receive the thrust bearing and the like. Device becomes unnecessary. Further, since the ring is pressed by the belt via the conical bearing, the pressing force by the belt is uniformly applied to the ring and increases, and the rotation of the rotor blade is adjusted according to the thrust required for the rotor blade. This can be ensured according to the operation of the belt to be operated.

The fifth helicopter ducted fan of the present invention has the following means in addition to the above means (1) and (2).

(10) A driving roller for rolling while pressing the outer peripheral surface of the ring with the wing tip fixed to the inner peripheral surface with the outer peripheral surface to rotate the rotor blade through the circular ring is provided. Was. It should be noted that even if one drive roller having a length substantially equal to the width of the ring is provided, about one-third of the width of the ring is provided.
You may provide two pieces of two lengths.

(11) A driving force from an engine for driving the main rotor, a generator driven by the engine, or an actuator for operating a driving roller with electric power supplied from a battery is provided.

(12) A plurality of rings are arranged at equal pitches on the outer peripheral surface of the ring other than the position where the driving roller is provided, and the load applied to the ring by the driving roller is equalized when the rotor blade rotates. Roller was provided.

(E) Thus, the helicopter ducted fan of the present invention has the same operation and effect as (c) in addition to (a), and also has the advantages (6) to
Compared with the third and fourth aspects of the present invention which require the space for laying the belt as the means of (9), the space for installing the drive roller is small, the periphery of the duct is cut out, and the rotor is cut off. The space that needs to be provided to drive the blade can be reduced.

A sixth embodiment of the helicopter ducted fan of the present invention has the following means in addition to the above means (1) and (2).

(13) The wing tip is made to protrude radially from the outer peripheral surface of the ring fixed to the inner peripheral surface, and a protrusion having a coil winding arranged at an interval in the peripheral direction is provided inside. In addition, only one protrusion may protrude from the center in the width direction of the ring, or two protrusions may be separated from each other in the width direction.

(14) A center hub which is wound around a coil winding portion provided on the projection and is operated by an engine which drives a main rotor, or which receives power from a battery or supports a base end of a rotating rotor blade. , A coil supplied by a power line inserted into a hole formed in the inside of the rotor blade and in the radial direction of the ring.

(15) A coil winding portion is provided, a gap is provided between the outer periphery of the projection around which the coil is wound, and a gap is provided to surround the projection, and the rotor blade is energized by electric power (current) supplied to the coil. A permanent magnet for generating a rotating electromagnetic force is provided.

(F) As a result, the helicopter ducted fan of the present invention can provide the same operation and effect as (c) in addition to (a), and can reduce the current flowing through the coil and the magnetic field generated by the permanent magnet. Since the rotor blade can be rotated by the generated electromagnetic force, the rotor blade drive device can be a device having no movable portion,
It is possible to eliminate the restriction on the space and to make the drive device highly reliable without failure of the drive device. Also, by changing the magnitude of the current supplied to the coil,
The rotor blade can be rotated at a rotational speed capable of generating a required thrust.

[0046]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the helicopter ducted fan according to the present invention will be described below with reference to the drawings. In the drawings, the same or similar members as those shown in FIGS. A to d are denoted by the same reference numerals, and description thereof will be omitted as much as possible. FIG. 1 is a view showing a first embodiment of a helicopter ducted fan according to the present invention, and FIG. 1 (a) is a perspective view showing a part of a duct 06 near a rotor blade 010 disposed therein, which is partially broken away. 1 (b) shows a rotor blade 010 and a hub 08 for omitting the part A shown in FIG. 1 (a).
FIG.

As shown in the figure, the hub is supported by a (streamlined) column 08 protruding from the inner peripheral surface of the duct 06, and a hub is arranged coaxially with the duct 06 and installed in the hub 09. By the power transmission mechanism 016 to which the driving force is transmitted from the engine 013 shown in FIG. 11, 8 to 10 rotor blades 010 are rotated on the outer periphery of the hub 09, in a direction orthogonal to the body axis direction, that is, Duct 06
A thrust is generated in the direction of the axis. That is, in the operation of the rotor blade 010 in this embodiment, a part of the driving force of the engine 013 installed inside the fuselage 02 shown in the conceptual diagram shown in FIG. And hub 0
The rotor blade 010 is transmitted to a power transmission mechanism 016 provided in the motor 9 and rotated at a constant speed by the power transmission mechanism 016.

For this purpose, the magnitude of the thrust generated by the rotor blade 010 is adjusted by providing a pitch control device 020 similar to that shown in FIG. 12 in the hub 09, and using the pitch control device 020 by the pilot's control stick operation. By changing the angle of attack of the rotor blade 010, the thrust that can maintain the yaw stability of the helicopter 01 or the operability for flying in the accurate flight direction is generated.

Further, 8 to 1 rotating on the outer periphery of the hub 09
The wing tip of the zero rotor blade 010 is connected to the wing tip, and rotates along with the rotation of the rotor blade 010 along the inner peripheral surface of the fairing 1 provided on the peripheral surface of the duct 06. Ring 2 was provided. This rotor blade 010
The ring 2 interconnecting the wing tips is drilled in the radial direction corresponding to the circumferential position of the wing tip provided, and the amount of expansion and contraction generated in the rotor blade 010 when rotating or stationary. The hole 5 is provided to a depth capable of absorbing the water. As shown in FIG. 12, a power transmission mechanism 0 provided in a hub 09 similarly to a conventional helicopter ducted fan.
16, the rotor blade 01 rotating at a constant rotation speed
0 is a pitch control device 0 similarly provided in the hub 09
From 20, the pitch angle is controlled to change the magnitude of the thrust.

At the tip of the rotor blade 010, a rotor 5 which is radially movable in a hole 5 formed in the above-mentioned ring 2 in a radial direction so as to be radially formed when the rotor blade 010 is operated. The blade 010 can be freely expanded and contracted in the radial direction so that it does not protrude from the outer peripheral surface of the ring 2 even when the rotor blade 010 is maximally extended, and also comes out of the hole 5 when the rotor blade 010 is retracted. There is provided a projection 4 which can support the wing tip without any problem.

Further, the inner peripheral surface of the fairing 1 and the ring 2
Bearing 3 is interposed between the outer peripheral surface of
The circumferential movement of the ring 2 on the inner peripheral surface of the fairing 1 is smoothened.

Since the helicopter ducted fan according to the first embodiment is configured as described above, the duct 06
, That is, the gap 6 generated between the inner peripheral surface of the fairing 1 and the wing tip can be reduced, and the contact between the wing tip and the inner peripheral surface of the fairing 1 can be reliably prevented. Damage due to contact can be reliably prevented.

Further, by reducing the gap 6, the flow rate of the air flowing out of the gap 6 can be reduced, the operating efficiency of the rotor blade 010 can be improved and the thrust can be increased, and the rotation of the main rotor 07 can be increased. To prevent the generation of torque for rotating the helicopter 01 generated in the direction, and the thrust necessary for maintaining the yaw stability during hovering or flight of the helicopter 01 and the operability to direct the accurate flight direction. The size of the rotor blade 011 to be generated and the duct 06 for installing the rotor blade 011 can be reduced, the aerodynamic characteristics of the helicopter 01 during flight can be reduced, and the weight can be reduced gradually. Performance can be improved.

Further, the pitch control device 020 is installed in the hub 09.
Is provided so that the angle of attack of the rotor blade 010 can be changed and the magnitude of thrust can be changed by operating the control stick, so that the pitch control device 20 and the installation space are required. Although a problem occurs due to an increase in the diameter, the power transmission mechanism 016 does not need to be provided with a transmission mechanism of the rotor blade 010, and the rotor blade 010 can be rotated at a constant speed similarly to the conventional one. Helicopter ducted fans can be applied immediately.

Next, FIG. 2 is a view showing a second embodiment of the helicopter ducted fan of the present invention, and FIG. 2 (a) shows a fan composed of an integrated rotor blade, ring and hub. FIG. 2B is a front perspective view, and FIG. 2B is a partial perspective view showing a coupled state of the hub and the rotor blade shown in FIG.
3 (c) is a partial perspective view showing the state of connection between the rotor blade and the ring shown in FIG. 2 (a), FIG. 3 (a) is a front view showing the rotor blade and the driving mechanism, and FIG. 3 (b) is FIG. 3A is a perspective view showing a cross section of the ring taken along the line AA, FIG. 3C is a block diagram showing a control device of the actuator shown in FIG. 3A, and FIG. 3) is a sectional view showing a state in which a belt is wound around the outer peripheral surface of the ring, and FIG.
3 is a perspective view of the conical bearing shown in FIG.

As shown in FIG. 2, in the helicopter ducted fan of the present embodiment, as shown in FIG. 2B, the base end of the rotor blade 6 is axially connected to the axial center of the duct 06 described above. Along the outer periphery of a center hub (rotating shaft) 7 pivotally attached to a support member (not shown) provided across the duct 06 at both ends thereof. Fixed to the inner peripheral surface of the ring 8,
As shown in FIG. 2A, a fan 12 composed of an integrated rotor blade 6, a center hub 7, and a ring 8 is formed.

The rotor blade 6 disposed between the center hub 7 and the ring 8 is formed in an airfoil shape so as to generate a predetermined thrust when rotating at a constant rotation speed. , The center hub 7 and the ring 8 are also mounted at a predetermined angle of attack with respect to the rotation surface of the rotor blade 6 rotating in the rotation direction R. The ring 8 to which the blade tip of the rotor hub 7 is fixed is shown in FIG.
As shown in (b), the inner peripheral surface to which the blade tip is fixed is flattened, and the outer peripheral surface has a cross-sectional shape of an isosceles triangle.

As shown in FIG. 3A, a belt 9 made of a material having a certain strength and elasticity is partially wound around the outer peripheral surface of the ring 8. Further, the belt 9 is wound around a pulley 11 operated by an actuator 10 driven by a battery or an engine 013, and the fan 12 shown in FIG. The rotation speed of the fan 12, in other words, the magnitude of the thrust generated by the rotor blade 6 is, as shown in FIG. 3C, an operation signal (MS) of the control device 13 operated by the pilot, or attached to the helicopter 01. Automatic calculation device 14 to which a feedback signal (FS) is input from the rate gyro
A calculation signal (CS) calculated by (AFCS) is input to the actuator 10, and a controlled rotational force from the actuator 10 is transmitted to the pulley 11.
The rotation speed of the pulley 11 is changed.

The belt 9 and the ring 8 that partially wind in the circumferential direction of the ring 8 are arranged in a concave portion provided in the fairing 1 fitted on the inner peripheral surface of the duct 06. As shown in FIG. 3 (e), between the belt 9 and the ring 8 is a frusto-conical cone which rotates around a rotation shaft 16 provided through the axis. The triangular side surface of the bearing 15 is provided in contact with two sides forming the outer peripheral surface of the ring 8.

In this way, a flat surface can be formed on the outer circumferential surface of the ring 8 around which the belt 9 is wound, even though the outer circumferential surface of the ring 8 is formed in a triangular shape. Due to the generated thrust, the movement of the fan 12 trying to move in the axial direction of the duct 06 can be restricted by the wedge effect of the conical bearing 15, and the fairing arranged at a predetermined position in the axial direction of the duct 06. The fan 12 can be rotated while maintaining the center of the fan 1.

Further, in FIG. 3 (e), the rear end of the rotating shaft 16 for rotating the roller 15 around its axis is shown to rotate inside the faring 1, but it is shown in FIG. The rear end of the shaft 16 may be fixed inside the fairing 1 and the roller 15 may be rotated around the rear end. Further, between the outer peripheral surface of the belt 9 wound around the ring 8 and the bottom surface of the concave portion of the fairing 1, a cylindrical roller 17 is provided to prevent the belt 9 from fluttering when the fan 12 is driven. I try to prevent it.

Since the helicopter ducted fan according to the second embodiment is configured as described above, the rotor blade 6 is provided with a motor driven by power from a generator driven by the engine 013 or a battery charged by the generator. The rotor blade 6 can be easily driven by an actuator 10 such as
Thrust change can be performed electrically by controlling the number of revolutions of the rotor, and the need for a pitch control device that changes the thrust of the rotor blade by a mechanical mechanism can be eliminated, reducing the weight and simplifying the structure. Can be.

The rotor blade 6 is connected to the driving belt 9
The hub 7 does not need to incorporate a power transmission mechanism and a pitch control device and can only support the base end portion of the rotor blade 6, can reduce the diameter, and can reduce the diameter of the rotor blade 6 with respect to the diameter of the duct 06. Since the working space can be increased, the diameter of the rotor blade 6 and the duct 06 can be reduced as a result, and in order to maintain yaw stability during hovering or flight of the helicopter and operability for directing a correct flight direction. Necessary rotor blade 6
And the size of the duct 06 in which the helicopter 01 is installed can be reduced, so that the aerodynamic characteristics of the helicopter 01 during flight do not deteriorate and the weight can be gradually reduced, thereby improving the flight performance of the helicopter 01. Can be.

FIG. 4 is a sectional view showing a third embodiment of the helicopter ducted fan according to the present invention. The structure is substantially the same as that of the second embodiment shown in FIG. 2 and FIG. In the second embodiment, a so-called cylindrical annular ring 18, in which the inner and outer peripheral surfaces are flat, is used instead of the ring 8 in which the outer peripheral surface is triangular in the second embodiment. Instead of the bearing 15, a spherical ball bearing 19 is used.

Thus, the same operation and effect as those of the second embodiment can be obtained. However, the ring 8 and the conical bearing 1 in the second embodiment.
In order not to use 5 rotor blades 6
Is applied to the ball bearing 19, and the strength requirements of the cylindrical ring 18 and the ball bearing 19 become stricter, but the structure is simplified as can be seen from the comparison with FIG. , Assembly and maintenance can be easily performed.

FIG. 5 is a view showing a fourth embodiment of the helicopter ducted fan according to the present invention.
FIG. 5 is a front view showing a fan and a drive mechanism including an integrated rotor blade, an annular ring with a projection, and a hub;
FIG. 5B is a perspective view showing a cross section of the ring with a projection taken along a line CC shown in FIG. 5A, FIG. 5C is a cross-sectional view taken along a line DD shown in FIG. FIG. 5D is a perspective view showing the fixing roller shown in FIG. 5C.

As shown in the figure, in the helicopter ducted fan of the present embodiment, the base end of the rotor blade 6 extends along the axis of the duct 06 as in the second embodiment. While being fixed to the outer peripheral surface of the center hub (rotating shaft) 7 erected, the blade end of the rotor blade 6 is fixed to the inner peripheral surface of the ring 20 with projections, as shown in FIG.
As shown in FIG. 7, a fan 21 composed of an integrated rotor blade 6, a center hub 7, and a ring 20 with projections is formed.

The rotor blade 6 disposed between the center hub 7 and the ring 8 is formed in an airfoil shape so as to rotate at a constant rotational speed and generate a predetermined thrust. The mounting angle to the center hub 7 and the ring 20 with projections is also set so as to have a predetermined angle of attack with respect to the rotation surface of the rotor blade 6 rotating in the rotation direction R. Further, as shown in FIG. 5B, the projecting ring 20 to which the blade tip of the rotor blade 6 is fixed has a flat inner circumferential surface to which the blade tip is fixed and a circumferential center at the outer circumferential surface. It has a convex cross-sectional shape provided with a projection 22 in the direction.

As shown in FIG.
As shown in FIG. 3A, three or more fixing rollers 23 are arranged at equal pitches on both sides of the projection 22, and
As in the case of the actuator 10 shown in (a), two divided drive rollers 25 driven by an actuator 24 operated by electric power from a generator driven by a battery or an engine 013 are provided on the left and right sides of the projection 22. The drive roller 25 rotates the fan 21 in the rotation direction indicated by the arrow shown in FIG.

The rotation speed of the fan 21, in other words, the magnitude of the thrust generated by the rotor blade 6, is the same as in the second embodiment, the operation signal (MS) of the control device 13 operated by the pilot, or the helicopter 01. A calculation signal (CS) calculated by an automatic calculation device 14 (AFCS) to which a feedback signal (FS) is input from a rate gyro attached to the actuator 10 is input to the actuator 10,
This is performed by changing the number of rotations of the driving roller 25. Since the drive rollers 25 are arranged in a pair on the left and right sides of the projection 22, even if a thrust is generated in the fan 21 by the rotation of the rotor blade, the thrust is generated by the drive roller 25 and the projection 22. It can be received by contact, and there is no need to specially install a thrust receiver as in the second embodiment.

The fixing rollers 23 are arranged at three or more places on the outer circumference of the ring 20 with projections as described above, and rotate around the rotation shaft 26 having both ends fixed to a fairing (not shown). The function as a bearing for smooth rotation of the ring 20 with projections is achieved, and the pressing force pressed by the fixing roller 23 is uniformly applied to the ring 20 with projections.

Since the helicopter ducted fan according to the fourth embodiment is configured as described above, the rotor blades 6 are driven by an engine driven by the engine 13 or a motor operated by electric power from a battery charged by the generator. It is easy to drive the rotor blade 6 with a certain pitch angle.
The thrust can be changed electrically by controlling the number of revolutions of the rotor blade, and a pitch control device for changing the thrust of the rotor blade 6 can be eliminated by a mechanical mechanism, the weight can be reduced, and the structure can be simplified. be able to.

Further, the rotor blade 6 is
5, the hub 7 does not need to have a built-in power transmission mechanism and pitch control device, can only support the base end of the rotor blade 6, can reduce the diameter, and can reduce the diameter of the duct 0.
6, the working space of the rotor blade 6 with respect to the diameter of the rotor blade 6 can be increased, so that the rotor blade 6 and the duct 0
6, the rotor blade 6 necessary for maintaining the operability of the helicopter and the size of the duct 06 for installing the rotor blade 6 can be reduced.
The flight performance of the helicopter 01 can be improved without deteriorating the aerodynamic characteristics during flight 1 and reducing the weight.

Further, by driving the rotor blade 6 from the belt 9 in the fourth embodiment to the driving roller 25, the periphery of the duct 06 can be compactly assembled, and the shroud 05 or the tail boom 03 can be compacted. Occupies a large space in the interior.

FIG. 6 is a sectional view showing a fifth embodiment of the helicopter ducted fan according to the present invention.
However, in the present embodiment, the outer peripheral surface of the fourth embodiment is the same as that of the fourth embodiment.
In place of the ring 20 with projections, a so-called cylindrical ring 26 having both flat inner and outer peripheral surfaces is used, and instead of the fixing roller 23, a spherical ball bearing 27 is formed. It is arranged on both sides of the ring 26.

As a result, the same operation and effect as those of the fourth embodiment can be obtained. However, the ring with projection 20 and the projection 22 in the fourth embodiment.
Since the driving rollers 25 are not used from the two rollers disposed on both sides of the cylindrical ring, the thrust generated by the rotor blade 6 is supported by the hole bearing 27, and the thrust of the cylindrical ring 26 and the ball bearing 27 While the strength requirements are stricter, as can be seen from a comparison with FIG. 3D, the structure is simpler, which has the advantage of facilitating assembly and maintenance and inspection. It can be made longer, and the contact surface with the cylindrical ring 26 can be increased, so that the driving force can be increased.

FIG. 7 is a view showing a sixth embodiment of the helicopter ducted fan according to the present invention. FIG. 7 (a) shows a fan comprising a rotor blade, a ring with projections, a hub, and a drive mechanism. 7 (b) is a cross-sectional perspective view taken along the line EE shown in FIG. 7 (a), and FIG. 7 (c) is a transverse cross-sectional view taken along the line EE. FIG. 7D is a partial perspective view of the ring with protrusions when the external magnet is removed in FIG. 7C, and FIG. 7E is a perspective view showing a wiring state in the center hub and the rotor hub. .

As shown in the figure, the helicopter ducted fan according to the present embodiment has the same structure as the second to fifth embodiments except that the base end of the rotor blade 6a has the duct 0 as described above.
6 is fixed to the outer peripheral surface of a center hub 7a installed along the axial center of the shaft center of the rotor 6, and the blade end of the rotor blade 6a is fixed to the inner peripheral surface of a ring 28 with a projection.
(A) integrated rotor blade 6a,
Fan 2 consisting of center hub 7a and ring 28 with projection
9 are formed.

The rotor hub 6a disposed between the center hub 7a and the ring 8 is shaped like an airfoil so as to rotate at a constant speed and generate a predetermined thrust. The mounting angle to the protruding circle 28 is also set so as to be a predetermined angle of attack with respect to the rotation surface of the rotor hub 6a that rotates in the rotation direction R. Further, a protruding ring 28 to which the blade tip of the rotor hub 6 is fixed.
As shown in FIGS. 7 (b) and 7 (c), the inner peripheral surface to which the wing tip is fixed is flattened, and the outer peripheral surface is provided with two projections 30 in the circumferential direction. It has a cross-sectional shape.

Further, on the side of the protruding ring 28, the protruding portion 30 moves left and right by the thrust by the rotation of the rotor blade 6 to prevent collision with a permanent magnet 31 which will be described later. A ball bearing 36 for smooth rotation is provided.

A permanent magnet 31 having an E-shaped cross section is disposed on the outer periphery of the annular ring 28 with a projection so as to cover the projection 30 with a gap therebetween. This permanent magnet 3
1, the magnetic poles disposed between the projections 30 are, for example, S poles, and the magnetic poles disposed on both sides of the projections 30 are N poles.
As a pole, it is arranged in the circumferential direction of the outer peripheral surface of the ring 28 with projection. In addition, as shown in FIG. 7D, a difference of about 5 m / m is provided in the circumferential direction of the projecting ring 28 projecting from the outer peripheral surface in the radial direction. Two pairs of through holes are provided in the width direction at equal pitches in the circumferential direction, and a thin coil winding portion 32 is provided. The coil 33 is wound around the coil winding portion 32. ing.

Further, in this embodiment, the center hub 7 to which the base end of the rotor blade 6a is fixed.
a is formed by a hollow pipe, and a hole is formed in the rotor blade 6a so as to communicate with the inside of the center hub 7a and communicate with the inside in the blade width direction. A power line 34 for supplying power to the coil 33 wound around the coil winding portion 32 is connected to the center hub 7.
a, the coil 33 and the brushes 35 provided at both ends of the center hub 7a are conducted through holes formed in the inside of the rotor blade 6a and the annular ring 28 with the projection.

Since the helicopter ducted fan of the present embodiment is configured as described above, for example, the current having the magnitude controlled by the automatic operation device 14 and the like shown in the second embodiment is applied to the brush 35 and the power line. When supplied to the coil 33 by the coil 34 and caused to flow through the coil 33, the rotor blades 6a,
Fan 2 comprising center hub 7a and projection ring 28
Numeral 9 rotates similarly to the rotor of the motor, and can change the rotation speed by changing the magnitude of the current supplied to the coil 33.

That is, the same operations and effects as those of the second to fifth embodiments can be obtained without specially providing the belt 9, the driving roller 25, and the like for rotating the fan 29.

Next, FIG. 8 is a sectional view showing a seventh embodiment of the helicopter ducted fan of the present invention. As shown in FIG. I have. However, only one protrusion 30a projects radially from the center of the outer peripheral surface of the ring 28a with a protrusion, and a permanent magnet 31a that covers the protrusion 30a is provided.

[0086]

As described above, the helicopter ducted fan according to the present invention is disposed in a duct penetrating the shroud horizontally, generates thrust in a direction perpendicular to the body axis, and is generated when the main rotor rotates. The inner peripheral surface of an annular duct that connects the blade tips of rotor blades that prevent the helicopter from generating torque and that maintains yaw stability and operability during hovering or flight of the helicopter, and rotates inside the duct A bearing is provided between the rotor blade and the outer peripheral surface of the ring to reduce the gap between the blade end of the rotor blade and the inner peripheral surface of the duct when the rotor blade rotates, thereby providing high-speed rotation of the rotor blade. I made it.

Thus, the helicopter ducted fan of the present invention reliably prevents breakage due to contact between the blade tip and the inner circumferential surface of the duct, and creates a gap between the inner circumferential surface of the duct and the outer circumferential surface of the ring. The rotor blades can be made smaller, the rotor blades can be rotated, the flow rate of air flowing out of the gap can be reduced, the operating efficiency of the rotor blades can be improved and the thrust can be increased, and it is generated in the direction opposite to the rotation direction of the main rotor. A rotor blade for preventing generation of torque for rotating a helicopter, generating thrust necessary for maintaining yaw stability during hovering or flight of the helicopter, and maintaining operability for directing an accurate flight direction, and a rotor blade therefor. Can reduce the size of the duct where the
The weight of the helicopter can be reduced without deteriorating the aerodynamic characteristics of the helicopter during flight, and the flight performance of the helicopter can be improved.

Further, the helicopter ducted fan of the present invention transmits the driving force branched from the engine which is disposed coaxially at the center of the duct and drives the main engine to the base end of the rotor blade to operate the rotor blade. A hub with a built-in power transmission mechanism to be provided, and a hole drilled in the radial direction of the ring is provided on the blade tip of the rotor blade corresponding to the circumferential position of the ring blade tip connecting the blade tip of the rotor blade. In addition, a projection is provided which is made movable in the hole in the radial direction so as to freely expand and contract in the radial direction of the rotor blade in the radial direction when the rotor blade is actuated.

Thus, even when the rotor blade is most extended at the time of high-speed rotation, damage due to contact can be prevented, and the rotor blade can be rotated at high speed, so that the inner peripheral surface of the duct and the outer peripheral surface of the ring can be separated. Can be reduced, the flow rate of air flowing out of the gap can be reduced, the operating efficiency of the rotor blade can be improved, and the thrust can be increased.

Further, in the helicopter ducted fan of the present invention, the blade tip is wound around the outer peripheral surface of the ring fixed to the inner peripheral surface, and the movement causes the outer peripheral surface of the ring to operate, thereby rotating the rotor blade. There is provided an actuator that operates the belt with a belt that generates thrust, a driving force that is supplied from an engine that drives the main rotor, or a pulley that is driven by a driving force that is supplied from a generator or a battery.

[0091] Thereby, it is arranged at the center of the duct,
Rather than the driving force transmitted to the power transmission mechanism in the hub that incorporates a power transmission mechanism, a pitch control device, etc., the rotor blade is driven by a driving belt wound around the outer peripheral surface of an annular ring provided on the wing tip. , So that the rotor blades can be easily controlled and driven by a driving force from the engine, a generator driven by the engine, or a motor that is powered by electric power from a battery charged by the generator. become.

Further, even when the rotor blades are directly operated by the driving force from the engine, the transmission mechanism for changing the rotation speed of the rotor blades, that is, the magnitude of the thrust, is provided outside the duct. Can be. In this way, the rotor blade is driven by the driving belt, and the hub can only support the base end of the rotor blade, so that the diameter of the hub can be reduced and the working space of the rotor blade relative to the diameter of the duct is increased. Can,
The rotor blades and ducts can be reduced in diameter, and the helicopter can be reduced in size to maintain the helicopter's yaw stability and operability for directing an accurate flight direction. The aerodynamic characteristics during flight can be reduced, the weight can be reduced gradually, and the flight performance of the helicopter can be improved.

Further, the helicopter ducted fan of the present invention has a triangular outer peripheral surface around which a belt is wound, and an annular ring which is rotated in a recess formed in the inner peripheral surface of the duct. Side surfaces are provided on two sides formed on the outer peripheral surface, and a flat contact surface is formed between the belt and the ring, and the ring is pressed by a pressing force applied to the belt, thereby forming a belt. A conical bearing for rotating the rotor blade according to the operation is provided.

Thus, the thrust force generated by the generation of the thrust of the rotor blade can be absorbed by the conical bearing, and a device such as a thrust receiver becomes unnecessary. further,
Since the ring is pressed by the belt via the conical bearing, the pressing force of the belt increases, and the rotation of the rotor blade is operated according to the thrust required of the rotor blade. Can be

Further, the helicopter ducted fan of the present invention is a driving roller for rolling while the wing tip presses against the outer peripheral surface of the ring fixed to the inner peripheral surface, and rotating the rotor blade through the ring. An engine for driving the main rotor, or an actuator for operating the driving roller with driving force supplied from a battery, a plurality of actuators are arranged at equal pitches on the outer peripheral surface of the ring, and are driven by the driving roller when the rotor blade rotates. A fixing roller for equalizing the load on the ring is provided.

Thus, compared with the third aspect of the present invention which requires a space for laying a belt, the space for installing the drive roller can be reduced, and around the duct,
The space required to drive the rotor blades can be reduced.

In the helicopter ducted fan of the present invention, the wing tip protrudes radially from the outer peripheral surface of the ring fixed to the inner peripheral surface, and the coil winding portion is disposed inside the inner periphery with a circumferential interval. Part, coil wound part provided on the protrusion,
A coil that is supplied with power from a generator or a battery that is powered by an engine, and a coil that is wound around the coil. And a permanent magnet configured to generate an electromagnetic force for rotating the rotor blade by the applied electric power (current).

Thus, the rotor blade can be rotated by the electromagnetic force generated by the current flowing through the coil and the magnetic field generated by the permanent magnet, so that the driving device of the rotor blade has no movable part. As a result, there is no space restriction, and the drive device can be made highly reliable without failure.

[Brief description of the drawings]

FIG. 1 is a view showing a first embodiment of a helicopter ducted fan according to the present invention, and FIG. 1 (a) is a perspective view, partially cut away, showing a duct 06 in the vicinity in which a rotor blade 010 is arranged. 1B is a front view of the rotor blade 010 and the hub 08, showing the omission of the portion A shown in FIG.

FIG. 2 is a view showing a second embodiment of the helicopter ducted fan according to the present invention. FIG. 2 (a) is a front view showing a fan composed of an integrated rotor blade, a ring and a hub, and FIG. 2 (b). 2), a partial perspective view showing a coupled state of the hub and the rotor blade shown in FIG. 2 (a), and FIG.
FIG. 7A is a partial perspective view illustrating a coupled state of the rotor blade and the ring illustrated in FIG.

FIG. 3 is a diagram showing details of the embodiment shown in FIG. 2;
(A) is a front view showing a rotor blade and a driving mechanism, and FIG.
3B is a perspective view showing a cross section of the ring taken along the line AA in FIG. 3A, FIG. 3C is a block diagram showing a control device of the actuator shown in FIG. d) is FIG.
FIG. 3B is a cross-sectional view illustrating a state in which the belt is wound around the outer peripheral surface of the ring, FIG. 3E is a perspective view of the conical bearing illustrated in FIG.

FIG. 4 is a sectional view showing a third embodiment of the helicopter ducted fan according to the present invention;

FIG. 5 is a view showing a fourth embodiment of the helicopter ducted fan according to the present invention, and FIG. 5 (a) is a front view showing a fan and a drive mechanism including an integrated rotor blade, an annular ring with projections and a hub. FIG. 5B is a perspective view showing a cross section of the ring with projections taken along the line CC shown in FIG.
FIG. 5C is a cross-sectional view taken along the line DD shown in FIG. 5A, FIG. 5D is a perspective view showing the fixing roller shown in FIG.

FIG. 6 is a sectional view showing a fifth embodiment of the helicopter ducted fan according to the present invention;

FIG. 7 is a view showing a sixth embodiment of the helicopter ducted fan according to the present invention, and FIG. 7 (a) shows a fan comprising a rotor blade, a ring with a projection, a hub, and a permanent magnet constituting a drive mechanism. FIG. 7B is a front view, and FIG.
Sectional perspective view when cut along arrow EE shown in FIG.
FIG. 7C is a cross-sectional view taken along the line EE, and FIG.
FIG. 7C is a partial perspective view of the ring with projections when the external magnet is removed in FIG. 7C, and FIG. 7E is a perspective view showing a wiring state in the center hub and the rotor hub.

FIG. 8 is a sectional view showing a seventh embodiment of the helicopter ducted fan according to the present invention;

FIG. 9 is an overall side view of a helicopter to which the helicopter ducted fan of the present invention is applied;

FIG. 10 is a perspective view showing the tail structure of FIG. 9;

FIG. 11 is a conceptual diagram showing a power transmission mechanism of a helicopter,

12 is a sectional view of the arrangement of the hub shown in FIG. 10 in the duct and the inside of the hub.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Fairing 2 Conical ring 3 Bearing 4 Projection 5 Hole 6,6a Rotor blade 7,7a Center hub 8 Ring 9 Belt 10 Actuator 11 Pulley 12 Fan 13 Control device 14 Automatic operation device 15 Conical bearing 16 Rotary axis 17 Columnar roller 18 Cylindrical ring 19 Ball bearing 20 Ring with projection 21 Fan 22 Projection 23 Fixing roller 24 Actuator 25 Driving roller 26 Cylindrical ring 27 Ball bearing 28, 28a Ring with projection 29 Fan 30, 30a Projection 31 Permanent magnet 32 Coil winding part 33 Coil 34 Power line 35 Brush 36 Ball bearing 01 Helicopter 02 Body 03 Tail boom 04 Tail structure 05 Shroud 06 Duct 07 Main rotor 07a Rotating axis 08 Support 09 Hub 09a Il gear box 010 Rotor blade 011 Rudder 012 Horizontal rudder 013 Engine 014 Main gear box 015 Tail drive shaft 016 Power transmission mechanism 017 Bevel gear 018 Drive bevel gear 191 Hub casing 020 Pitch control device 021 Pitch changing rod 022 Lever 023 Servo control device 024 Spider for pitch control 025 Tie bar 026 Gap 027 Rod R Rotation direction FS Feedback signal MS Operation signal CS Calculation signal

Claims (6)

[Claims] 1. A helicopter comprising a fuselage, a main rotor, a tail boom, and a tail structure, wherein the rotor blade having a rotor blade disposed in a duct horizontally penetrating a shroud forming the tail structure is operated. A helicopter ducted fan that generates thrust in a direction orthogonal to the fuselage direction to prevent the helicopter from generating torque when the main rotor rotates and to maintain yaw stability and operability during hovering or flight of the helicopter. In the above, the blades of the rotor blades are connected to each other, an annular ring that rotates inside the duct, and a bearing interposed between the inner peripheral surface of the duct and the outer peripheral surface of the annular ring. A helicopter ducted fan characterized by being provided. 2. A hub having a built-in power transmission mechanism for operating the rotor blades with a driving force branched from an engine for driving the main rotor, the hub being disposed coaxially at the center of the duct, Corresponding to the circumferential direction arranged, respectively, holes drilled in the radial direction of the ring,
A projection provided on the wing tip and supporting the wing tip by allowing the rotor blade to expand and contract in a radial direction in the hole and to be generated during operation. 1 helicopter ducted fan. 3. A belt, the wing tip of which is wound around an outer peripheral surface of the ring fixed to an inner peripheral surface to actuate the ring to rotate the rotor blade, and to drive the main rotor. 2. The helicopter-ducted fan according to claim 1, further comprising: an actuator that drives a pulley that operates the belt with a driving force supplied from a power supply including an engine, a battery, or a power generator. 4. An outer peripheral surface around which the belt is wound is formed in a triangular shape, and the ring is formed in a recess formed in an inner peripheral surface of the duct, and is formed on an outer peripheral surface of the ring. Side surfaces are disposed on two sides of the belt, forming a planar contact surface between the belt and the ring, and pressing the ring with a pressing force applied to the belt, 4. A helicopter ducted fan according to claim 3, further comprising: a conical bearing for rotating said rotor blade in accordance with an operation of said helicopter. 5. A driving roller that rolls while rotating the rotor blade while the wing tip presses an outer peripheral surface of the ring fixed to an inner peripheral surface, and an engine or an engine that drives the main rotor. An actuator that operates the driving roller with a driving force supplied from a battery, and is disposed at an equal pitch on an outer peripheral surface of the ring, and the driving roller applies a rotation to the ring when the rotor blade rotates. 2. The helicopter ducted fan according to claim 1, further comprising a fixing roller for evenly distributing a load. 6. A projecting portion in which the wing tip is radially projected from an outer peripheral surface of the annular ring fixed to an inner peripheral surface, and a coil arranged inside the projecting portion at a circumferential interval. A coil wound around the winding portion, and a permanent magnet disposed so as to surround the outer peripheral surface of the protrusion with a gap provided between the coil and the generator. The helicopter-ducted fan according to claim 1, wherein an electromagnetic force is generated by supplying the coil to the coil, and the rotor blade is rotated by the electromagnetic force.