JPH07156890A - Helicopter - Google Patents

Abstract

PURPOSE:To prevent the occurrence of aerodynamic interference between a tail rotor and a vertical tail, exhibit respective functions sufficiently, and improve maximum speed by installing the tail rotor in an upper part of a tail cone in a fuselage through a tail rotor support part. CONSTITUTION:In a helicopter, a main rotor 2 is rotated by an engine 4 through a rotary shaft 3, and a tail rotor 30 is rotated to cope with torque acting in the inverse ditection of the rotational direction of this. In this case, through a tail rotor support part 31, the tail rotor 30 is installed between a part wider than a width of a fuselage 5 in a rear part of the fuselage 5 and a horizontal tail 6 or a vertical tail 7, that is, in an upper part of a tail cone. A longitudinal directional position of the tail rotor 30 may be either position when it exists in the upper part of the tail cone. As for a lateral directional position, the tail rotor 30 may be situated on the fuselage center line of a helicopter, or may by disloacted to either the left or the right.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a helicopter capable of reducing aerodynamic interference between a tail rotor and a vertical tail.

[0002]

2. Description of the Related Art As shown in FIG. 24, in a conventional single-rotor helicopter, a main rotor 2 is mounted on an upper portion of a body 5 and is rotated by the power of an engine 4 mounted on the body 5. When the main rotor 2 rotates, FIG.
As shown in (B), the main rotor torque 10 in the direction opposite to the main rotor rotation direction 9 acts, and the helicopter itself also rotates, so that it cannot fly as it is. Therefore, in the conventional single-rotor helicopter, the tail rotor 8 is attached to the upper portion of the vertical tail 7 of the helicopter as shown in FIG. 24, or the tail rotor 15 is provided in the vertical tail 14 as shown in FIG. 25 (A). 25B, or the tail rotor 29 is embedded in the body 28 as shown in FIG. 25B, and the yaw moment 13 due to the tail rotor thrust around the center of gravity 12 is generated as shown in FIG. 24B. It was used to cancel the main rotor torque 10.

[0003]

In the conventional single-rotor helicopter 1, when the tail rotor 8 is mounted on the upper portion of the vertical tail 7 as shown in FIG. 24, the tail rotor 8 and the vertical tail 7 are extremely difficult. With approaching 1
Since the portions are overlapped, the tail rotor 8 and the vertical stabilizer 7 aerodynamically interfere with each other as shown in FIG. 26, and the efficiency of the tail rotor 8 is deteriorated. In order to compensate for the deterioration, the tail rotor 8 having a larger size must be mounted. At the same time, the effectiveness of the vertical tail 7 is also deteriorated, and it is necessary to mount the vertical tail 7 having a larger dimension to compensate for the deterioration as in the case of the tail rotor 8. Therefore, these increase the weight of the helicopter and increase the aerodynamic resistance. As a result, the performance of the helicopter was deteriorated.

Further, as shown in FIG. 25, when the tail rotor 15 is embedded in the vertical tail 14, since one portion of the vertical tail 14 is cut out, its structural strength becomes weaker, and therefore it is necessary to reinforce it. Occurs. On the other hand, vertical tail 1
4 The effective area of the main body is also reduced, and it contributes to the directional stability of the helicopter of the vertical stabilizer 14 (when the helicopter slides sideways, the aerodynamic force that directs the nose of the helicopter in the wind direction acts on the helicopter). The vertical dimension of the vertical stabilizer 14 needs to be increased to compensate for this. Therefore, the shape must be abnormal as shown in FIG. When the tail rotor 29 is embedded in the body 28 as shown in FIG.
There is a problem that a part of No. 8 is cut out, a weight is increased for reinforcement, and a mechanism and a structure are complicated.

A conventional helicopter performs a wide range of flight from hovering (air stop) flight to horizontal flight only by the main rotor 2, and thrust in the front-back direction obtained by the main rotor 2 (because of the aerodynamic resistance of the helicopter). Therefore, the maximum speed of a helicopter is extremely small compared to that of an airplane, which is a disadvantage (the maximum speed of a conventional helicopter is 120 to 1).
It is about 50 knots). Therefore, it is strongly required to improve the maximum speed of the helicopter. The present invention is
It is an object of the present invention to provide a helicopter capable of solving the above problems of the conventional method.

[0006]

[Means for Solving the Problems]

(First Means) A helicopter according to the present invention is a helicopter having a tail rotor, wherein the tail rotor 3 is provided above the tail cone 100 via a tail rotor support portion 31.
It is characterized in that 0 is provided. (Second Means) A helicopter according to the present invention is a helicopter having a tail rotor, wherein the tail rotor 3 is provided below the tail cone 100 via a tail rotor support portion 39.
It is characterized in that 0 is provided. (Third Means) A helicopter according to the present invention is a helicopter having a tail rotor, characterized in that a tail rotor 45 is provided on a side of the tail cone 100 via a tail rotor support portion (46, 47, 48). And (Fourth Means) A helicopter according to the present invention is characterized in that, in a helicopter having a tail rotor, a tail rotor 57 is provided at a rear end portion of a wide rear portion of a body via a tail rotor support portion 58. To do. (Fifth Means) The helicopter according to the present invention is
The means of 3 or 4 is characterized in that the tail rotor with duct (34, 52, 60) is provided via the tail rotor support portion with duct (35, 41, 53, 61). (Sixth Means) A helicopter according to the present invention is the helicopter according to the fifth means, wherein the tail rotor support portion (35, 4) with a duct is provided.
1, 66, 70) via a tail rotor (3
4, 65, 69) and a shaping member (37, 38, 4) around the ducted tail rotor support.
3, 67, 68, 71). (Seventh Means) The helicopter according to the present invention is
The means of 3, 4, 5 or 6 is characterized in that the tail rotor or the tail rotor with a duct is mounted so as to be inclined with respect to the center line 32 of the body of the helicopter.

[0007]

The tail rotor 30, 45, 57 is provided through the tail rotor supporting portion at any one or a plurality of upper, lower, and lateral portions (including oblique portions) of the tail cone 100 of the rear body of the helicopter body 5. Does not cause aerodynamic interference with the vertical tail 7 unlike the conventional tail rotor 8, and the tail rotor and the vertical tail are independent,
Each effect can be fully exerted.

Vertical tail 7 of a conventional helicopter
The problem of the structure and strength of
There is no increase in weight or aerodynamic drag. The mechanism is also simplified, and there is no need for space for wiring, piping, etc. in the vertical stabilizer 7.

In place of the tail rotor, the tail rotor with duct 3 is provided through a tail rotor supporting portion with duct.
When 4, 52, 60, 65, and 69 are installed, the thrust can be increased by the duct as shown in FIG. 23, and if the area is the same, the tail rotor with duct is about 1.5 times as much as a simple tail rotor without duct. You can obtain the above thrust,
Further, assuming that the thrust is constant, the tail rotor with a duct may have an area of about 0.7 or less of the tail rotor without a duct, which is advantageous. The duct also has the advantage of serving as a protective device that prevents people or objects from hitting the helicopter.

When the tail rotor with a duct is mounted on the upper portion, the lower portion, or both of the tail cone 100 of the rear body of the helicopter, the shaping members 37, 38,
By attaching 43, 44, 68, 71, the aerodynamic force acting on the shaping member can contribute to an increase in the directional stability of the helicopter, and the aerodynamic resistance acting around the tail rotor with a duct and the tail rotor supporting portion with a duct can be reduced. It can contribute to the improvement of high speed performance and climbing performance.

When the rotating surface of the tail rotor or the tail rotor with duct is not parallel to the fuselage center line 32 but is mounted at a constant angle as shown in FIG. 22, in addition to the lateral thrust component 76, the forward thrust component 75. This positive thrust component makes it possible to improve the high-speed performance of the helicopter.

[0012]

Embodiments of the present invention will be described with reference to the drawings. First Embodiment A first embodiment of the present invention will be described with reference to FIG. 1A is a side view of the first embodiment, and FIG.
1B is a view of the first embodiment viewed from above, and FIG. 1C is a cross-sectional view of the first embodiment viewed from the rear.

In the first embodiment, a tail rotor support portion 31 is provided above a tail rotor support portion 31 at an upper portion between a wide portion of the fuselage 5 at the rear portion of the helicopter and the horizontal stabilizer 6 or the vertical stabilizer 7. Mount the rotor 30.

The position of the tail rotor 30 in the front-rear direction may be any position as long as it is above the tail cone, and the position of the tail rotor 30 in the left-right direction may be located on the center line 32 of the body of the helicopter. It may be located to the right or the left side from 32. Although FIG. 1A shows the case where the tail rotor support portion 31 is perpendicular to the tail cone 100, it may be oblique.

When the tail rotor 30 is mounted as shown in FIG. 1, aerodynamic interference with the vertical tail 7 does not occur unlike the conventional tail rotor 8, so that the tail rotor 30 and the vertical tail 7 have their respective functions. It can be fully exerted without loss. The mechanism and the like can be simplified, the structure of the vertical stabilizer 7 is simplified, and the problem of insufficient strength is eliminated. Therefore, no reinforcement is required, and neither weight increase nor aerodynamic resistance increase occurs. It is not necessary to secure a space for wiring, piping, etc. in the vertical stabilizer 7, and a great effect can be obtained.

Since the tail rotor 30 is mounted on the upper portion of the tail cone at the rear of the body 5, the height of the tail rotor 30 is lower than the height of the vertical tail 7, and the height of the tail rotor 30 is lower than that of the conventional helicopter. You can Therefore, the height of the hangar may be lower than before, and the tail rotor 30
It also makes it easier to perform inspections and maintenance work, and contributes to improving work efficiency. The distribution of the cross-sectional area on the plane perpendicular to the centerline 32 can be made smooth, and the aerodynamic drag can be reduced, which contributes to the improvement of high-speed performance (maximum speed, cruise speed) and climbing performance (climbing rate, climbing limit). it can. Second Embodiment A second embodiment of the present invention will be described with reference to FIG. 2A is a side view according to the second embodiment, and FIG.
FIG. 2B is a view of the second embodiment seen from above, and FIG. 2C is a sectional view of the second embodiment seen from the rear.

In the second embodiment, a plurality of tail rotors 30 are mounted on a tail cone at the rear of the body 5 of the helicopter via a plurality of tail rotor support portions 31. The tail rotor support portion 31 may be vertical or oblique to the tail rotor.

If the tail rotors 30 have the same size, the larger the number of the tail rotors 30, the more the tail rotors 30.
The thrust obtained by is large. Therefore, the yaw moment 13 due to the tail rotor thrust around the center of gravity 12 also increases.

The other functions, actions and effects are similar to those of the first embodiment. Third Embodiment A third embodiment of the present invention will be described with reference to FIG. 3A is a side view of the third embodiment, and FIG.
3B is a view of the third embodiment seen from above, and FIG. 3C is a view of the third embodiment seen from the rear.

In the third embodiment, the tail rotor 34 with a duct is mounted on the tail cone at the rear of the body 5 of the helicopter via the tail rotor supporting portion 35 with a duct. Although FIG. 3A shows the case where the tail rotor support portion 35 is perpendicular to the tail cone 100, it may be oblique. In the first embodiment, only the tail rotor 30 is mounted, but in the third embodiment, the tail rotor 34 with a duct is mounted.

When the tail rotor with a duct has the same area as shown in FIG. 23, it is possible to obtain a thrust of about 1.5 times or more that of the tail rotor without a duct. The rotor may have an area of less than about 0.7 of a ductless tail rotor.

Further, the duct can prevent a person or an object from hitting the tail rotor. Therefore, there is an effect that the safety is improved, and at the same time, it is possible to protect the tail rotor from being damaged.

The other functions, actions and effects are the same as in the case of the first embodiment. Fourth Embodiment A fourth embodiment of the present invention will be described with reference to FIG. 4A is a side view of the fourth embodiment, and FIG.
4B is a view of the fourth embodiment seen from above, and FIG. 4C is a view of the fourth embodiment seen from the rear.

In the fourth embodiment, a plurality of ducted tail rotors 34 are mounted on the tail cone at the rear of the body 5 of the helicopter via a plurality of ducted tail rotor support portions 35. The larger the number of tail rotors, the larger the yaw moment due to the tail rotor thrust.

The function, function, and effect of the ducted tail rotor 34 are the same as those in the third embodiment.
Other functions, actions and effects are the same as those in the first embodiment. Fifth Embodiment A fifth embodiment of the present invention will be described with reference to FIG. 5A is a side view of the fifth embodiment, and FIG.
5B is a view of the fifth embodiment seen from above, and FIG. 5C is a sectional view of the fifth embodiment seen from the rear.

In the fifth embodiment, a shaping member 37 is attached around the tail rotor with duct 34 and the tail rotor support portion with duct 35 in the third embodiment. In the fifth embodiment, the tail rotor with duct 34 and the support portion 35 are covered with a shaping member 37 so that the air flow can be made smoother. By doing so, the aerodynamic resistance of the ducted tail rotor 34 and the ducted tail rotor support portion 35 can be reduced to contribute to the improvement of the high speed performance and the ascending performance of the helicopter. At the same time, the aerodynamic force acting on the shaping member 37 can contribute to an increase in the directional stability of the helicopter.

The shaping member 3 is attached to the tail rotor 34 with a duct.
Since 7 is added, it is possible to prevent a person or thing from hitting the tail rotor with duct 34. Therefore, it is possible to contribute to the improvement of safety, and at the same time, it is possible to prevent the tail rotor with duct 34 from being broken. Sixth Embodiment A sixth embodiment of the present invention will be described with reference to FIG. 6A is a side view of the sixth embodiment, and FIG.
6B is a view of the sixth embodiment seen from above, and FIG. 6C is a sectional view of the sixth embodiment seen from the rear.

In the sixth embodiment, a shaping member 38 is mounted around the tail rotor with duct 34 and the tail rotor support portion with duct 35 in the fourth embodiment. In the sixth embodiment, the shaping member 3 is provided around the tail rotor with duct 34 and the tail rotor support portion with duct 35 in the fourth embodiment.
It is covered with 8 to make the air flow smoother. By doing so, the aerodynamic resistance of the ducted tail rotor 34 and the ducted tail rotor support portion 35 can be reduced to contribute to the improvement of the high speed performance and the ascending performance of the helicopter. At the same time, the aerodynamic force acting on the shaping member 38 can contribute to an increase in the directional stability of the helicopter.

Since the shaping member 38 is further added to the tail rotor 34 with duct, it is possible to prevent a person or thing from hitting the tail rotor 34 with duct. Therefore, it is possible to contribute to the improvement of safety, and at the same time, it is possible to prevent the tail rotor with duct 34 from being broken. Seventh Embodiment A seventh embodiment of the present invention will be described with reference to FIG. FIG. 7A is a side view of the seventh embodiment, and FIG.
7B is a view of the seventh embodiment seen from above, and FIG. 7C is a sectional view of the seventh embodiment seen from the rear.

In the seventh embodiment, the tail rotor 30 is attached to the lower portion of the tail rotor at the rear of the body 5 of the helicopter via the tail rotor support portion 39. The position of the tail rotor 30 in the front-rear direction may be any position between the tail cones, and the position of the tail rotor 30 may be located on the center line 32 of the helicopter in the left-right direction. Alternatively, it may be displaced to the left.

When the tail rotor 30 is mounted as shown in FIG. 7, there is no aerodynamic interference with the vertical tail 7 unlike the conventional tail rotor 8 and the functions of the tail rotor 30 and the vertical tail 7 are not impaired. It can be fully demonstrated. The mechanism etc. can be simplified, the structure of the vertical tail 7 is not complicated, the problem of insufficient strength is eliminated, no reinforcement is required, and there is no increase in weight or aerodynamic resistance.
There is no need for space such as piping, which is a great advantage.

Since the tail rotor 30 has a small diameter, it can be mounted on the lower portion of the rear portion of the body 5. Therefore, the overall height can be made lower than that of the conventional helicopter. Therefore, the height of the hangar can be made lower than before, and the inspection and maintenance work of the tail rotor 30 can be easily performed and the safety can be easily ensured.

When the tail rotor 30 is added to the lower part of the tail cone, the aerodynamic resistance of the body 5 can be reduced. Therefore, it can contribute to the improvement of the high-speed performance and the climbing performance of the helicopter.
Further, since the distribution of the cross-sectional area on the surface perpendicular to the center line 32 becomes smooth, the aerodynamic resistance can be reduced also from that surface, which can contribute to the improvement of high-speed performance and climbing performance.

Although FIG. 7 shows the case where there is one tail rotor, there may be a plurality of tail rotors, and the tail rotor support portion 39 may be perpendicular to the tail cone 100 or may be oblique. Eighth Embodiment An eighth embodiment of the present invention will be described with reference to FIG. 8A is a side view of the eighth embodiment, and FIG.
8B is a view of the eighth embodiment seen from above, and FIG. 8C is a sectional view of the eighth embodiment seen from the rear.

In the eighth embodiment, the tail rotor 34 with a duct is attached to the lower portion of the tail cone at the rear of the body 5 of the helicopter via the tail rotor supporting portion 41 with a duct. In the seventh embodiment, the mere tail rotor 30 is mounted, but in the eighth embodiment, the tail rotor 34 with a duct is mounted. The tail rotor support is a tail cone 10
It may be perpendicular to 0 or may be oblique.

The function, action and effect of the tail rotor 34 with a duct are the same as in the case of the third embodiment.
Although FIG. 8 shows the case where each of the tail rotor with duct 34 and the tail rotor support portion 41 with duct is single, each of the tail rotor with duct 34 and tail rotor support portion 41 with duct is plural as long as the space permits. So, you can attach any number.

The larger the number of ducted tail rotors 34, the greater the effectiveness of the ducted tail rotors 34, which is more convenient. Ninth Embodiment A ninth embodiment of the present invention will be described with reference to FIG. 9A is a side view of the ninth embodiment, and FIG.
FIG. 9B is a view of the ninth embodiment seen from above, and FIG. 9C is a sectional view of the ninth embodiment seen from the rear.

In the ninth embodiment, a shaping member 43 is mounted around the tail rotor with duct 34 and the tail rotor support portion 41 with duct in the eighth embodiment. In the ninth embodiment, the tail rotor 34 with a duct and the tail rotor support portion 41 with a duct of the eighth embodiment are covered with a shaping member 43 to make the air flow smoother. By doing so, the aerodynamic resistance of the ducted tail rotor 34 and the ducted tail rotor support portion 35 can be reduced to contribute to the improvement of the high speed performance and the ascending performance of the helicopter. At the same time, the aerodynamic force acting on the shaping member 43 can contribute to the increase in the directional stability of the helicopter.

Since the shaping member 43 is further added to the tail rotor with duct 34, it is possible to prevent a person or object from hitting the tail rotor with duct 34, which contributes to the improvement of safety, and at the same time, the tail rotor with duct 34. Can be prevented from breaking. Tenth Embodiment A tenth embodiment of the present invention will be described with reference to FIG. FIG. 10A is a side view of the tenth embodiment,
FIG. 10B is a view of the tenth embodiment seen from above,
(C) shows a sectional view of the tenth embodiment as viewed from the rear.

In the tenth embodiment, a plurality of ducted tail rotors 69 are attached to the tail cone of the rear body of the helicopter body 5 via the tail rotor supporting portions 70 with ducts, and the tail rotor 69 with ducts is mounted. And the shaping member 7 around the tail rotor supporting portion 70 with the duct.
Cover with 1. In addition to the fact that the number of tail rotors with ducts 69 is plural and the thrust of the tail rotors with ducts is large, and that the shaping 71 contributes to the reduction of aerodynamic resistance,
This is the same as the ninth embodiment and has the same functions, actions, effects, and characteristics as the ninth embodiment.

The tail rotors 69 with ducts may be the same or different in size. Eleventh Embodiment An eleventh embodiment of the present invention will be described with reference to FIG. FIG. 11A is a side view of the eleventh embodiment,
11B is a view of the eleventh embodiment as seen from above, FIG.
(C) shows a sectional view of the eleventh embodiment as seen from the rear.

In the eleventh embodiment, the tail rotor 30 is attached to the upper and lower portions of the tail cone 100 at the rear of the body 5 of the helicopter via the tail rotor support portions 31 and 39, respectively. That is, the first embodiment shown in FIG.
This corresponds to a combination of the seventh embodiment shown in FIG. Therefore, it has the functions, actions, effects, and characteristics of both the first and seventh embodiments.

In FIG. 11A, the front and rear positions of the tail rotor 30 are the same in the upper and lower parts, but the front and rear positions of the upper and lower parts may be different. A combination of the upper rotor and the lower rotor, one of which is the tail rotor 30 and the other of which is the tail rotor with a duct 34 may be combined.

The tail rotor portions 31 and 39 may be vertical or oblique to the tail cone 100. Further, a plurality of tail rotors 30 may be provided at each of the upper portion and the lower portion of the tail cone. Twelfth Embodiment A twelfth embodiment of the present invention will be described with reference to FIG. 12A is a side view of the twelfth embodiment, FIG. 12B is a top view of the twelfth embodiment, and FIG. 12C is a rear view of the twelfth embodiment. A sectional view is shown.

In the twelfth embodiment, the tail rotors 34 with ducts are mounted one by one on the upper and lower parts of the tail cone 100 at the rear of the body 5 of the helicopter via the tail rotor support portions 35, 41 with ducts. That is, it corresponds to a combination of the third embodiment shown in FIG. 3 and the eighth embodiment shown in FIG. Therefore, it has the functions, actions, effects, and characteristics of both the third embodiment and the eighth embodiment described above.

In FIG. 12 (A), the front and rear positions of the tail rotor with duct 34 are the same in the upper and lower parts, but the front and rear positions of the tail rotor with duct in the upper part and the lower part are different, and there is a deviation. Even if there is. Further, one of the upper and lower parts may be a combination of the ducted tail rotor 34 and the other may be the tail rotor 30, and the upper part may be either the ducted tail rotor supporting part 35 or 36, and the lower part may be the ducted tail rotor supporting part 41 or 42. It may be a combination. The ducted tail rotor support portions 35, 41 may be perpendicular or oblique to the tail cone. Further, a plurality of tail rotors 34 with ducts may be provided in the upper and lower portions of the tail cone, respectively. 13th Embodiment A 13th embodiment of the present invention will be described with reference to FIG. 13A is a side view of the thirteenth embodiment, FIG. 13B is a top view of the thirteenth embodiment, and FIG. 13C is a rear view of the thirteenth embodiment. A sectional view is shown.

In the thirteenth embodiment, the tail rotors 34 with ducts are mounted one by one on the upper and lower parts of the tail cone 100 at the rear of the body 5 of the helicopter via the tail rotor support portions 35, 41 with ducts, respectively. The surroundings are covered with shaping members 37 and 43. That is, it corresponds to a combination of the fifth embodiment shown in FIG. 5 and the ninth embodiment shown in FIG. Therefore, it has the functions, actions, effects, and characteristics of both the fifth and ninth embodiments described above.

In FIG. 13 (A), the front and rear positions of the tail rotor with duct 34 are the same in the upper and lower parts, but the front and rear positions of the tail rotor with duct in the upper part and the lower part are different, and there is a deviation. Even if there is. Further, any combination of the tail rotor supporting portions 35 and 36 with the duct at the upper portion and the tail rotor supporting portions 41 and 42 with the duct at the lower portion may be used. There may be a plurality of ducted tail rotors 34 at the top and bottom of the tail cone 100. Fourteenth Embodiment A fourteenth embodiment of the present invention will be described with reference to FIG. FIG. 14A is a side view of the fourteenth embodiment,
FIG. 14B is a view of the fourteenth embodiment seen from above,
(C) shows a sectional view of the fourteenth embodiment as viewed from the rear.

In the fourteenth embodiment, one tail rotor 45 is mounted via a tail rotor support 46 on one side of the tail cone 100 at the rear of the helicopter body 5.
The position of the tail rotor 45 in the front-rear direction is the tail cone 10
Any position between 0 may be used. Although the tail rotor 45 is mounted on the port side in FIG. 14, it may be mounted on the starboard side.

When the tail rotor 45 is mounted as shown in FIG. 14, the respective functions of the tail rotor 45 and the vertical tail 7 are impaired without causing aerodynamic interference with the vertical tail 7 unlike the conventional tail rotor. Can be fully demonstrated without. The mechanism can be simplified, problems of the structure and strength of the vertical stabilizer 7 are eliminated, reinforcement is not required, weight is not increased, aerodynamic resistance is not increased, and space for wiring, piping, etc. in the vertical stabilizer 7 is not required. Obtainable.

Since the tail rotor 45 is mounted on the rear lateral portion of the body 5, the height of the tail rotor 45 is lower than the height of the vertical stabilizer 7, and the overall height is lower than that of the conventional helicopter. Therefore, the height of the hangar can be made lower than in the conventional case, and the inspection and maintenance work of the tail rotor 45 can be performed easily, safety can be easily ensured, and work efficiency can be improved. Further, since the distribution of the cross-sectional area on the plane perpendicular to the center line 32 becomes smooth, it is possible to reduce the aerodynamic resistance and contribute to the improvement of the high speed performance and the climbing performance. One tail rotor 45 may be provided on each of the port side and the starboard side of the tail cone 100. A plurality of tail rotors may be provided on the port side and / or the starboard side of the tail cone 100. Fifteenth Embodiment A fifteenth embodiment of the present invention will be described with reference to FIG. FIG. 15 shows a sectional view of the fifteenth embodiment as seen from the rear. In the fourteenth embodiment, the tail rotor 45 is located right beside the body 5, but in the fifteenth embodiment, the tail rotor 45 is mounted diagonally above the body 5 via the tail rotor support 47. In FIG. 15, the tail rotor 45
Indicates diagonally upward on the port side, but may be diagonally upward on the starboard side. By doing so, the tail rotor 45 is separated from the body 5, and the efficiency of the tail rotor 45 becomes better.

Others have the same functions, actions, effects and characteristics as those of the 14th embodiment. Sixteenth Embodiment A sixteenth embodiment of the present invention will be described with reference to FIG. FIG. 16 shows a sectional view of the twenty-ninth embodiment as seen from the rear. In the sixteenth embodiment, the tail rotor 45 has the body 5
However, in the sixteenth embodiment, the tail rotor 45 is mounted diagonally below the body 5 via the tail rotor support 48. Although the tail rotor 45 is shown in the diagonally downward port side in FIG. 16, it may be in the diagonally downward starboard position. By doing so, the tail rotor 45 is separated from the body 5, and the efficiency of the tail rotor 45 becomes better.

Others have the same functions, actions, effects and characteristics as those of the 14th embodiment. Seventeenth Embodiment A seventeenth embodiment of the present invention will be described with reference to FIG. FIG. 17A is a side view of the seventeenth embodiment,
17B is a view of the seventeenth embodiment seen from above, FIG.
(C) shows a sectional view of the seventeenth embodiment as viewed from the rear.

In the seventeenth embodiment, one tail rotor 52 with a duct is mounted on one lateral side of the tail cone 100 at the rear of the body 5 of the helicopter via a tail rotor support 53 with a duct.

The position of the tail rotor 52 with duct in the front-rear direction may be any position between the tail cones 100. Although the tail rotor 45 with a duct is mounted on the port side in FIG. 17, it may be mounted on the starboard side.

In the embodiment shown in FIG. 14, the tail rotor 4 is simply used.
However, in the seventeenth embodiment, a tail rotor 52 with a duct is attached instead of the tail rotor 45. As shown in FIG. 23, the duct increases the thrust generated by the tail rotor, and if the area is the same, the tail rotor with duct 5
2 can obtain a thrust of about 1.5 times or more that of the tail rotor 45 without duct, and if the thrust is the same, the area of the tail rotor 52 with tact can be about 0.7 or less of that of the tail rotor without duct 45, which is convenient. Is.

Further, the duct acts as a protection to prevent a person or an object from hitting the tail rotor, which contributes to improvement of safety. Other functions, actions, effects,
The characteristics are the same as those in the 14th embodiment. The tail rotor 52 with a duct is installed on both left and right sides of the tail cone 100.
Individual tail rotors may be provided, or a plurality of ducted tail rotors may be provided on the left side, right side, or both sides of the tail cone 100. 18th Embodiment An 18th embodiment of the present invention will be described with reference to FIG. FIG. 18A is a side view of the eighteenth embodiment,
18B is a view of the 18th embodiment seen from above, FIG.
(C) shows a sectional view of the eighteenth embodiment as seen from the rear.

In the eighteenth embodiment, the tail rotor support portion 58 is provided on one side of the rear end portion of the wide portion of the body 5 of the helicopter.
The tail rotor 57 is mounted via. Tail rotor 5
The attachment position of 7 may be any position in the front-rear direction or the left-right direction as long as there is a space at the rear end of the wide portion of the body 5. Although the tail rotor 57 is mounted on the port side in FIG. 18, it may be mounted on the starboard side. Alternatively, it may be provided on both the port side and the starboard side. Only one may be provided at the center of the rear end of the body 5. When the tail rotor 57 is mounted in this way, it does not cause aerodynamic interference with the vertical tail 7 unlike the conventional tail rotor 8 and does not impair the functions of the tail rotor 57 and the vertical tail 7 sufficiently. Can be demonstrated. The mechanism can also be simplified. The problem of complication of the structure of the vertical stabilizer 7 and lack of strength is eliminated, and reinforcement is also unnecessary. There is no increase in weight or aerodynamic resistance, and no space for wiring, piping, etc. is required in the vertical stabilizer 7.

Since the tail rotor 57 is mounted on the rear end of the wide portion of the body 5 and the height of the tail rotor 57 is lower than the height of the vertical tail 7, the overall height is smaller than that of the conventional helicopter. Get lower. Therefore, the height of the hangar may be lower than in the conventional case, and inspection and maintenance work of the tail rotor 57 and the like can be easily performed, safety can be easily ensured, and work efficiency can be improved. The distribution of the cross-sectional area on the plane perpendicular to the center line 32 is also smoothed, so that the aerodynamic resistance is also reduced, which can contribute to the improvement of high-speed performance and climbing performance. 19th Embodiment A 19th embodiment of the present invention will be described with reference to FIG. FIG. 19A is a side view of the nineteenth embodiment,
19B is a view of the nineteenth embodiment seen from above, FIG.
(C) shows a sectional view of the nineteenth embodiment as viewed from the rear.

In the nineteenth embodiment, the tail rotor 60 with a duct is attached to one side of the rear end of the wide portion of the body 5 of the helicopter via the tail rotor support 61 with a duct.

The tail rotor 60 with duct may be attached at any position in the front-rear direction or the left-right direction as long as there is a space at the rear end of the wide portion of the body 5. Although FIG. 19 shows the case where the ducted tail rotor 60 is mounted on the port side, it may be mounted on the starboard side. It may be mounted on both the port side and the starboard side. Only one may be provided at the center of the rear end of the body 5. When the tail rotor with a duct is mounted in this manner, the tail rotor with a duct 60 and the vertical tail 7 do not generate aerodynamic interference with the vertical tail 7 unlike the conventional tail rotor 8.
Can be fully exerted without impairing the respective functions of. The mechanism can also be simplified. The structure of the vertical stabilizer 7 is not complicated, the problem of insufficient strength is eliminated, and reinforcement is also unnecessary. There is no increase in weight or aerodynamic resistance, and there is no need for a space such as wiring or piping in the vertical stabilizer 7. The tail rotor with duct 60 is attached to the rear end of the wide portion of the fuselage 5, and the height of the tail rotor with duct 60 is lower than the height of the vertical tail 7, so that the overall height of the tail rotor 60 is higher than that of the conventional helicopter. Therefore, the height of the hangar can be made lower than in the conventional case, and the inspection and maintenance work of the tail rotor 60 with a duct and the like can be easily performed, safety can be easily ensured, and work efficiency can be improved.

The eighteenth embodiment is a simple tail rotor 57.
However, the nineteenth embodiment is a tail rotor 60 with a duct.
Therefore, as shown in FIG. 23, if the area is made the same by the duct, the tail rotor with duct can obtain a thrust of about 1.5 times or more that of the tail rotor without duct, and if the thrust is the same, the tail rotor with duct will have An area of 0.7 or less for the tail rotor without a duct is sufficient, which is convenient for canceling the rotor torque 10. Further, the duct of the tail rotor 60 with a duct can prevent a person or an object from hitting the tail rotor, which is useful for improving safety. Twentieth Embodiment A twentieth embodiment of the present invention will be described with reference to FIG. FIG. 20A is a side view of the twentieth embodiment,
20B is a view of the twentieth embodiment seen from above, FIG.
(C) shows a sectional view of the twentieth embodiment as seen from the rear.

In the twentieth embodiment, the ducted tail rotor 65 is attached to the central portion of the rear end of the wide portion of the body 5 of the helicopter through the ducted tail rotor support portion 66, and the ducted tail rotor is also mounted. A shaping member 67 is added around the duct rotor 65 and the tail rotor supporting portion 66 with a duct to cover them.

Since the shaping member 67 can reduce the aerodynamic resistance, it can contribute to the improvement of the high speed performance and the ascending performance of the helicopter. Twenty-first Embodiment A twenty-first embodiment of the present invention will be described with reference to FIG. FIG. 21A is a side view of the forty-eighth embodiment,
21B is a view of the twenty-first embodiment seen from above, FIG.
(C) shows a sectional view of the twenty-first embodiment seen from the rear.

In the twenty-first embodiment, a plurality of ducted tail rotors 65 are vertically mounted via a ducted tail rotor support portion 66 at the center of the rear end of the wide portion of the body 5 of the helicopter. A shaping member 68 covers the area around the ducted tail rotor 65 and the ducted tail rotor support. The number of tail rotors 65 with ducts is large, and the thrust force of tail rotors 65 with ducts is large, and the shaping member 68 is large, so that it contributes to the reduction of aerodynamic resistance. And has the same functions, actions, effects, and characteristics as the 20th embodiment. The size of the plurality of ducted tail rotors 65 may be the same or different. 22nd Embodiment A 22nd embodiment of the present invention will be described with reference to FIG. FIG. 22 (A) shows a view of the 22nd embodiment from above.

The rotating surface of the tail rotor for the above-described first to twenty-first embodiments was parallel to the body centerline 32, but in the twenty-second embodiment, the rotating surface of the tail rotor 72 is as shown in FIG. The tail rotor 72 is mounted so that it has a fixed angle 74 with the body centerline 32.

By doing so, the yaw moment is generated around the center of gravity 12 of the helicopter by the lateral thrust component 76 of the thrust of the tail rotor to cancel the main rotor torque 10, and a forward thrust component 75 is obtained. The forward thrust 75 and the forward force obtained by inclining the surface of the main rotor 2 advance the helicopter. Therefore, compared to the conventional helicopter, it can contribute to the improvement of the high-speed performance of the helicopter. The twenty-second embodiment can be applied to all the cases of the first to twenty-first embodiments.

[0068]

Since the present invention is constructed as described above, it has the following effects. (1) The tail rotor 8 and the vertical tail of a conventional helicopter are mounted by mounting the tail rotor at any of the upper part, the lower part, the lateral part (including the oblique part) or a plurality of parts of the tail cone 100 at the rear part of the body 5. Since the aerodynamic interference generated between the tail rotor and the vertical tail 7 can be prevented.
Can be fully exerted without impairing the respective functions of.

(2) The power transmission mechanism for driving the tail rotor can be short, and the mechanism can be simplified. (3) Since the problem of the structure and strength of the vertical stabilizer 7 is eliminated, reinforcement is not required, and neither weight increase nor aerodynamic resistance increase occurs. No space for wiring, piping, etc. is required in the vertical stabilizer 7, which also contributes to cost merit.

(4) The tail rotor is the tail cone 100
Since it is attached to the upper part, the lower part, and the lateral part (including the oblique part), the height is lower than the height of the vertical stabilizer 7, and the overall height is lower than that of the conventional helicopter. Therefore, the height of the hangar may be lower than before, and inspection and maintenance work of the tail rotor and the like can be facilitated, which contributes to ensuring and improving safety as well as improving work efficiency.

(5) In addition to the above effects, by installing a tail rotor with a duct instead of the tail rotor,
The following effects can be obtained. As shown in FIG. 23, when the area is the same, the tail rotor with a duct can obtain a thrust of about 1.5 times or more that of the tail rotor without a duct. An area of about 0.7 or less is sufficient.
If done in this way, it is extremely convenient to cancel the main rotor torque 10 generated by the rotation of the main rotor 2.

Further, by providing the duct, it is possible to prevent a person or an object from hitting the rotor, which contributes to improvement of safety. (6) By adding a shaping member to the tail rotor with duct and the tail rotor supporting portion with duct, aerodynamic resistance can be reduced, which can contribute to improvement of high-speed performance and ascent performance of the helicopter.

Further, since the directional stability of the helicopter is increased by the aerodynamic force acting on the shaping member, it is possible to contribute to the increase of the safety of the helicopter. (7) Since the rotation surface of the tail rotor is not parallel to the fuselage center line 32 but the tail rotor is mounted at a constant angle 74, a lateral thrust component 76 and a forward thrust component 75 can be obtained. This lateral thrust component 76 produces a yaw moment about the center of gravity 12 of the helicopter to generate the main rotor torque 10 generated by the main rotor 2.
Which contributes to canceling the
And the thrust obtained by inclining the two surfaces of the main rotor can advance the helicopter. Therefore, it can contribute to the improvement of the high-speed performance of the helicopter as compared with the conventional helicopter.

[Brief description of drawings]

FIG. 1 is a diagram showing a first embodiment of the present invention.

FIG. 2 is a diagram showing a second embodiment of the present invention.

FIG. 3 is a diagram showing a third embodiment of the present invention.

FIG. 4 is a diagram showing a fourth embodiment of the present invention.

FIG. 5 is a diagram showing a fifth embodiment of the present invention.

FIG. 6 is a diagram showing a sixth embodiment of the present invention.

FIG. 7 is a diagram showing a seventh embodiment of the present invention.

FIG. 8 is a diagram showing an eighth embodiment of the present invention.

FIG. 9 is a diagram showing a ninth embodiment of the present invention.

FIG. 10 is a diagram showing a tenth embodiment of the present invention.

FIG. 11 is a diagram showing an eleventh embodiment of the present invention.

FIG. 12 is a diagram showing a twelfth embodiment of the present invention.

FIG. 13 is a diagram showing a thirteenth embodiment of the present invention.

FIG. 14 is a diagram showing a fourteenth embodiment of the present invention.

FIG. 15 is a diagram showing a fifteenth embodiment of the present invention.

FIG. 16 is a diagram showing a sixteenth embodiment of the present invention.

FIG. 17 is a diagram showing a seventeenth embodiment of the present invention.

FIG. 18 is a diagram showing an eighteenth embodiment of the present invention.

FIG. 19 is a diagram showing a nineteenth embodiment of the present invention.

FIG. 20 is a diagram showing a twentieth embodiment of the present invention.

FIG. 21 is a diagram showing a twenty-first embodiment of the present invention.

FIG. 22 is a diagram showing a twenty-second embodiment of the present invention.

FIG. 23 is a diagram showing an effect of a duct.

FIG. 24 is a view showing a conventional single-rotor helicopter.

FIG. 25 is a view showing a conventional tail rotor (fitting type).

FIG. 26 is a diagram showing aerodynamic interference between a conventional tail rotor and a vertical tail.

[Explanation of symbols]

1 ... Helicopter, 2 ... Main rotor, 3 ... Main rotor rotating shaft,
4 ... Engine, 5 ... Fuselage, 6 ... Horizontal stabilizer, 7 ... Vertical stabilizer, 8 ... Tail rotor, 9 ... Main rotor rotation direction, 10 ...
Main rotor torque, 11 ... Direction of travel, 12 ... Center of gravity, 13 ...
Yaw moment due to tail rotor thrust, 14 ... Vertical tail, 15 ... Tail rotor, 28 ... Fuselage, 29 ... Tail rotor, 30 ... Tail rotor, 31 ... Tail rotor support part, 32 ... Fuselage center line, 34 ... Tail with duct Rotor, 35 ... Tail rotor support with duct, 37 ... Shaping member, 38 ... Shaping member, 39 ... Tail rotor support, 4
1 ... Tail rotor support with duct, 43 ... Shaping member,
45 ... Tail rotor, 46 ... Tail rotor support, 47
… Tail rotor support, 48… Tail rotor support, 5
2 ... Tail rotor with duct, 53 ... Tail rotor support with duct, 57 ... Tail rotor, 58 ... Tail rotor support, 60 ... Tail rotor with duct, 61 ... Tail rotor support with duct, 65 ... Tail rotor with duct , 66 ... Tail rotor support with duct, 67 ... Shaping member, 68 ... Shaping member, 69 ... Tail rotor with duct, 70 ... Tail rotor support with duct, 71 ... Shaping member, 72 ... Tail rotor, 73 ... Tail rotor Support portion, 74 ... Angle of tail rotor rotation surface, 75 ... Forward thrust component, 76 ... Lateral thrust component, 77 ... Tail rotor support portion, 78 ... Tail rotor with duct, 79 ... Tail rotor, 80 ... Duct, 81 … Cross-sectional area at the position with tail rotor, 82… Exit area, 83… Thrust without duct, 84… With duct Thrust, 100 ... tail cone.

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Katsumasa Sugiyama 1 at 60 Kyutansho, Iwatsuka-cho, Nakamura-ku, Nagoya, Aichi Nakabishi Engineering Co., Ltd.

Claims (7)

[Claims] 1. A helicopter having a tail rotor, wherein a tail rotor (30) is provided above a tail cone (100) via a tail rotor support (31). 2. A helicopter having a tail rotor, wherein a tail rotor (30) is provided below a tail cone (100) via a tail rotor support (39). 3. In a helicopter having a tail rotor, a tail rotor (45) is provided on a side of a tail cone (100) via a tail rotor support portion (46, 47, 48).
A helicopter characterized by being provided with. 4. A helicopter having a tail rotor, wherein a tail rotor (57) is provided at a rear end portion of a wide portion of a rear portion of the fuselage via a tail rotor support portion (58). 5. A helicopter having a tail rotor, wherein a tail rotor supporting portion (35, 41, 5) with a duct is provided.
Tail rotor with duct (34, 5)
2, 60) are provided.
Or the helicopter according to 4. 6. A helicopter having a tail rotor, wherein a tail rotor support portion (35, 41, 6) with a duct is provided.
Tail rotor (34, 6) with duct through
5, 69) and a shaping member (37, 38, 43, 6) around the tail rotor supporting portion with the duct.
7.68,71).
The described helicopter. 7. A helicopter having a tail rotor, wherein the rotating surface of the tail rotor or the tail rotor with a duct is mounted so as to be inclined with respect to the fuselage center line (32) of the helicopter. The helicopter according to claim 1, 2, 3, 4, 5 or 6.