JP2021172183A - Shield member and helicopter - Google Patents

Abstract

To improve functions of a helicopter by utilizing a blowdown of a main rotor shielded by a shield member.SOLUTION: A shield member is disposed in a shell of a helicopter so as to shield a blowdown that is blown down toward the shell according to rotation of a main rotor. The shield member includes a hydrodynamics structure that generates a driving force causing the shell to rotate in a rotation direction of the main rotor, from an air flow that is guided by the shield member so as to flow from a center side to an outer peripheral side.SELECTED DRAWING: Figure 4

Description

The present invention relates to a shielding member provided on the fuselage of a helicopter and which shields the blow-down that is blown downward toward the fuselage as the main rotor rotates, and a helicopter having the shielding member.

A helicopter that flies by the lift generated by rotating the main rotor over the fuselage will generate a strong wind that blows downward toward the fuselage as the main rotor rotates, that is, a downwash of the main rotor. ..

As shown in Patent Document 1, the unloading of the main rotor interferes with the work performed in the space under the fuselage of the helicopter in flight, such as rescue work and unloading work. Therefore, in Patent Document 1, a part of the blow-down of the main rotor is shielded by a shielding member suspended from the fuselage of the helicopter.

However, the shielding member suspended from the fuselage of the helicopter cannot secure a sufficiently large working space under the fuselage, and the shielding member is not stable due to the blow-down of the main rotor. Therefore, the applicant of the present application has proposed a shielding member provided on the fuselage of the helicopter to shield the blow-down that is blown downward toward the fuselage as the main rotor rotates.

Japanese Unexamined Patent Publication No. 05-21278

In the shielding member proposed by the applicant of the present application, the blow-down of the main rotor shielded by the shielding member is not effectively utilized. Therefore, it is an object of the present invention to improve the function of the helicopter by utilizing the blow-down of the main rotor shielded by the shielding member. Specifically, the purpose is to reduce the load on the tail rotor for canceling the reaction force of the rotation of the main rotor acting on the fuselage by utilizing the blow-down of the main rotor shielded by the shielding member. Alternatively, the purpose is to increase the propulsive force for advancing the helicopter by utilizing the blow-down of the main rotor shielded by the shielding member.

In order to solve the above problem, the shielding member according to claim 1 is a shielding member provided on the fuselage of the helicopter and shielding the blow-down that is blown downward toward the fuselage as the main rotor rotates. The shielding member is characterized by having a hydrodynamic structure that generates a driving force in a direction that rotates the body in the rotation direction of the main rotor from an air flow that is guided by the shielding member and flows from the center side to the outer peripheral side. ..

In order to solve the above problem, the shielding member according to claim 4 is a shielding member provided on the fuselage of the helicopter and shielding the blow-down that is blown downward toward the fuselage as the main rotor rotates. The shielding member is characterized by having a hydrodynamic structure that generates a driving force in a direction that pushes the fuselage toward the front side of the helicopter from an air flow that is guided by the shielding member and flows from the center side to the outer peripheral side.

In the examples of the embodiments of these inventions, the shielding member is the diameter of the main rotor in which the hydrodynamic structure is partitioned by a guide wall erected from the shielding surface of the shielding member toward the main rotor. It is an airflow groove that is continuous in the direction.

In the examples of the embodiments of these inventions, the cross section of the shielding member parallel to the shielding surface of the guide wall is curved in the direction opposite to the direction of the driving force to be generated.

In order to solve the above problems, the helicopter according to claim 7 or 8 is characterized by having the shielding member provided with the hydrodynamic structure.

According to the shielding member of claim 1, the hydrodynamic structure generates a driving force in the direction of rotating the fuselage in the rotation direction of the main rotor from the air flow flowing along the shielding member. Therefore, it is possible to effectively utilize the blow-down of the main rotor shielded by the shielding member and reduce the load on the tail rotor for canceling the rotational reaction force of the main rotor acting on the fuselage of the helicopter.

According to the shielding member of claim 4, the hydrodynamic structure generates a driving force in a direction of pushing the fuselage forward from the airflow flowing along the shielding member. Therefore, it is possible to effectively utilize the blow-down of the main rotor shielded by the shielding member to increase the propulsive force for advancing the helicopter.

According to the shielding member of claim 2 or 5, the airflow groove partitioned by the guide wall functions as a hydrodynamic structure to generate a driving force in a required direction.

According to claim 3 or 6, the airflow groove partitioned by the curved guide wall functions as a hydrodynamic structure to generate a driving force in a required direction.

According to the helicopter of claim 7 or 8, the shielding member having a hydrodynamic structure generates a driving force for the fuselage that cannot be generated by the shielding member having no hydrodynamic structure. Therefore, the function of the helicopter can be improved by utilizing the driving force generated by the hydrodynamic structure.

It is explanatory drawing of the structure of the helicopter of Embodiment 1, and is the side view of the helicopter which has the shielding member which formed the airflow groove as a hydrodynamic structure. It is explanatory drawing of the structure of the shielding member in Embodiment 1, (a) is a plan view, (b) is a side view, (c) is an XX cross-sectional view of (a). It is explanatory drawing of the structure which attaches the shielding member to a helicopter, (a) is the sectional view of the state which attached the shielding member to the fuselage, and (b) is the sectional view which expanded the attachment part of the shielding member. It is explanatory drawing of the structure of the helicopter of Embodiment 1, and is the top view of the helicopter which attached the shielding member which formed the airflow groove. It is explanatory drawing of the structure of the shielding member in Embodiment 2, (a) is a plan view, (b) is a side view, (c) is an XX cross-sectional view of (a). It is explanatory drawing of the structure of the helicopter of Embodiment 2, and is the top view of the helicopter which attached the shielding member which formed the airflow groove. It is explanatory drawing of the structure of the helicopter of the comparative example, and is the side view of the helicopter to which the shielding member which does not form the hydrodynamic structure is attached.

Hereinafter, embodiments of the helicopter of the present invention will be described in detail with reference to the accompanying drawings. First, a comparative helicopter according to the invention previously proposed by the applicant of the present application will be described. In the first embodiment shown in FIGS. 1 to 4, the shielding member 10H mounted on the helicopter 1H of the comparative example shown in FIG. 7 is changed to the shielding member 10 according to the present invention in which the hydrodynamic structure 11 is formed. The other configurations and operations are the same as those of the helicopter 1H and the shielding member 10H of the comparative example. Therefore, in FIGS. 1 to 4, the members common to the helicopter 1H of FIG. 7 are designated by the same reference numerals, and duplicate description is omitted. Further, in order to facilitate the illustration of the shielding member 10, the thickness of the material, the overall thickness, the size of the nut, the width of the airflow groove, and the like are exaggerated and described to be larger than the actual one. Therefore, the airflow grooves are described as having a lower density than the actual one, a small number of the airflow grooves, and a thicker one than the actual one. Therefore, the present invention is not limited to the structure and dimensions specifically estimated with reference to FIGS. 1 to 4.

(Comparison example)
As shown in FIG. 7, the helicopter 1H of the comparative example uses the lift F1 generated by rotating the main rotor 3 above the fuselage 2 to levitate the fuselage 2 in the air and ascend the entire fuselage in the air. Lower. By tilting the main rotor 3, the helicopter 1H uses a part of the lift F1 of the main rotor 3 as a propulsion force to control the flight in the horizontal direction and the flight direction. The periphery of the actual shaft 3a includes a complicated mechanism for controlling the main rotor 3, but it is shown in a simplified manner in FIGS. 1 to 7.

The engine 4 is housed in the upper part of the fuselage 2. The driving force of the engine 4 is transmitted from a gear train (not shown) to the main rotor 3 via the shaft 3a. When the main rotor 3 rotates, air flows along the streamlined cross section of the main rotor 3 and lift is generated on the cross section of the main rotor 3. The total lifts F1 and F1 generated by the rotation of the entire main rotor 3 raise the main rotor 3, and the fuselage 2 is lifted into the air via the shaft 3a.

A landing skid 5 is provided on the lower surface of the fuselage 2. The skid 5 may be replaced with a retractable landing gear or the like provided with wheels. An entrance / exit 2b is provided on the side surface of the fuselage 2, and the entrance / exit 2b is covered with the cabin slide doors 2a and 2a so as to be openable and closable. A driver's seat is provided in front of the fuselage 2, and a wide field of view on the front side is secured from the driver's seat by the front window 2c.

The aileron 7 is provided so as to project from both side surfaces of the fuselage 2, and has a streamlined cross-sectional shape. The aileron 7 can adjust the angle of the cross section with respect to the air flow, and generates lift while the helicopter 1 is advancing to lift the fuselage 2 and reduce the load of the lift F1 generated by the main rotor 3. The vertical stabilizer 8 stabilizes the aerial attitude of the fuselage 2 during flight.

In the helicopter 1H of the comparative example, as the main rotor 3 rotates, a strong wind that blows downward toward the fuselage 2 and downwash D1 and D2 of the main rotor 3 are generated. Since the blow-down D1 and D2 of the main rotor 3 interfere with the work performed in the space outside the fuselage of the helicopter in flight, in the helicopter 1H, a shielding member 10H for shielding the blow-down D2 is provided on the upper surface of the fuselage 2. It is provided to secure a work space during flight under the shielding member 10H.

The shielding member 10H covers the region E2 below the main rotor 3 and shields the blow-down D2 toward the region E2. Therefore, in the helicopter 1H of the comparative example, the blow-down D2 toward the region E2 hits the shielding member 10H, bends outward, flows along the shielding member 10H, wraps around the edge of the shielding member 10H, and joins the blowing-down D1. do. Since the shielding member 10H does not have a hydrodynamic structure (11: FIGS. 3, 12, 13: 5), it is not possible to utilize the blow-down D2 to generate an effective driving force for the body 2.

(Embodiment 1)
As shown in FIG. 1, the helicopter 1 of the first embodiment is equipped with the shielding member 10 shown in FIG. 2 instead of the shielding member 10H of the comparative example. Since the shielding member 10 has the hydrodynamic structure 11, it is possible to utilize the blow-down D2 of the main rotor 3 to generate an effective driving force for the body 2. The shielding member 10 having the hydrodynamic structure 11 generates a driving force by utilizing the airflow D3 of the blow-down D2 flowing from the center side to the outer peripheral side, and reduces the load on the tail rotor 6.

As shown in FIG. 1, the shielding member 10 is attached to the upper surface of the body 2 by using eight nuts 10a in two rows. The shielding member 10 is provided on the fuselage 2 of the helicopter 1 and shields the blow-down D2 that is blown downward toward the fuselage 2 as the main rotor 3 rotates.

The shielding member 10 is a thick disk-shaped member in which the airflow grooves 11c, which is an example of the hydrodynamic structure 11, are arranged in the circumferential direction. As shown in FIG. 2C, in the shielding member 10, a circular mounting plate 10e on the center side and an annular shielding plate 10g on the outer peripheral side are connected by a cylindrical upright wall 10h.

As shown in FIG. 1, a wide field of view on the front side is secured by the front window 2c from the driver's seat. The shielding member 10 is formed of a transparent resin material so as not to obstruct the upper view from the front window 2c. As shown in FIG. 4, the portion of the shielding plate 10 g that protrudes outward from the body 2 is formed of a transparent acrylic resin plate. Since the shielding member 10 does not obstruct the upper view, the operator can secure a wide field of view, and the shielding member 10 does not interfere with the operation of the helicopter by the operator.

The portion of the shielding plate 10g that overlaps the body 2 and the portion that is close to the body 2, the mounting plate 10e, and the upright wall 10h are made of a heat-resistant material. Since the portion of the shielding plate 10g exposed to high temperature, the mounting plate 10e, and the upright wall 10h are made of a metal material, the overall strength of the shielding member 10 is increased to reduce the weight, and the exhaust heat of the engine 4 and the high temperature are increased. The influence of the exhaust gas can be avoided.

As shown in FIG. 3A, the shielding member 10 is detachably attached and fixed to the upper surface of the fuselage 2 of the helicopter 1. As shown in FIG. 3B, anchor bolts 10c are provided on the upper surface of the body 2 so as to project upward. The shielding member 10 is fixed to the upper surface of the body 2 by inserting the mounting holes 10b of the mounting plate 10e into the anchor bolts 10c and tightening the nuts 10a respectively.

As shown in FIG. 4, the shielding member 10 has a circular contour centered on the shaft 3a of the main rotor 3. The shielding member 10 covers a region E2 having a width A larger than the width B of the body 2 on the lower center side of the main rotor 3. Therefore, the influence of the unshielded down blow-down (D1: FIG. 7) of the main rotor 3 and the influence of the down-screening (D2: FIG. 1) are symmetrical with respect to the fuselage 2 and almost all around. Appears evenly. Therefore, the attitude of the fuselage 2 of the helicopter 1 during flight is stable, and the attitude of the fuselage 2 is unlikely to become unstable due to the operation of the helicopter 1.

As shown in FIG. 4, the main rotor 3 is provided with one to two blades 3b that rotate in the direction of arrow R1 to generate lift (F1: FIG. 1). When the main rotor 3 rotates in the direction of arrow R1, the reaction force of the main rotor 3 causes the body 2 to rotate the body 2 in the direction of arrow R2 in a plane parallel to the rotation surface of the main rotor 3. Works. The helicopter 1 is provided with a tail rotor 6 at the rear end of the fuselage 2 in order to offset this rotational force and stop the rotation of the fuselage 2 in the arrow R2 direction. The tail rotor 6 is driven by a motor mechanism (not shown) to rotate, thereby generating thrust F2 in the direction opposite to the arrow R2 direction of the fuselage 2. The helicopter 1 has a gyro sensor that detects the rotation of the body 2, and automatically adjusts the rotation speed of the tail rotor 6 per minute so as to stop the rotation of the body 2 in the arrow R2 direction measured by the gyro sensor. ..

In the helicopter 1, by having the shielding member 10 provided with the hydrodynamic structure 11, the shielding member 10 is subjected to a rotational force by utilizing the airflow D3 of the blow-down D2 flowing from the center side to the outer peripheral side along the shielding member 10. It is occurring. Then, the load on the tail rotor 6 is reduced by utilizing this rotational force, and the number of revolutions per minute of the tail rotor 6 is lowered as compared with the comparative example.

As shown in FIG. 2C, the airflow groove 11c, which is an example of the hydrodynamic structure 11, has a main rotor from the airflow D3, which is guided by the shielding member 10 and flows from the center side to the outer periphery side, to the fuselage (2: FIG. 4). A driving force in the direction of rotation in the rotation direction (R1) of 3 is generated. As shown in FIG. 2A, the shielding member 10 has an airflow groove 11c continuous in the diameter direction of the main rotor 3. The two adjacent airflow grooves 11c are separated by a guide wall 11b that stands up from the shielding surface 11a of the shielding member 10 toward the main rotor 3 and is continuous in the radial direction. In the guide wall 11b, the central side of the shielding member 10 is connected to the upright wall 10h, and the outer peripheral side (tip side) is curved in the direction of arrow R2.

In the shielding member 10, the airflow groove 11c partitioned by the guide wall 11b causes the shielding member 10 to generate a driving force for rotation in the direction opposite to the arrow R2. The horizontal cross section of the guide wall 11b of the airflow groove 11c parallel to the shielding surface 11a is curved in the direction opposite to the driving force to be generated. The guide wall 11b is formed in the diametrical direction on the central side, is curved in the arrow R2 direction on the outer peripheral side, and is connected to the outlet 11d. As shown in FIG. 2C, when the airflow D3 flows from the center side to the outer peripheral side of the shielding member 10, the airflow groove 11c exerts the following three hydrodynamic forces on the shielding member 10. Make it work

(1) Injection: The airflow D3 is guided by the guide wall 11b and is injected from the outlet 11d on the outer periphery of the shielding member 10. The reaction force of the injection causes a driving force in the direction of arrow R1 to act on the shielding member 10 via the guide wall 11b. (2) Bending of the flow path: The airflow D3 is guided by the curved guide wall 11b and flows in the direction of arrow R2. Can be bent in the direction. The reaction force of the airflow D3 at this time causes the shielding member 10 to act on the shielding member 10 in the direction of the arrow R1 via the guide wall 11b. (3) Lift acting on the guide wall 11b: The airflow flowing outside the curve of the guide wall 11b The flow velocity is higher than the air flow flowing inside. Therefore, a lift (horizontal direction) is generated on the guide wall 11b in a direction opposite to the bending direction (convex direction).

In the first embodiment, the airflow groove 11c, which is an example of the hydrodynamic structure 11, generates a driving force in the direction of rotating the body 2 in the rotation direction of the main rotor 3 from the airflow D3 flowing along the shielding member 10. Therefore, the load of the tail rotor 6 for canceling the rotational reaction force of the main rotor 3 acting on the fuselage 2 of the helicopter 1 is effectively utilized by effectively utilizing the blow-down D2 of the main rotor 3 shielded by the shielding member 10. It can be mitigated.

In the first embodiment, the shielding member 10 having the airflow groove 11c generates a driving force around the shaft 3a that cannot be generated by the shielding member 10H of the comparative example shown in FIG. 7. Therefore, the function of the helicopter 1 can be improved by utilizing the driving force generated by the hydrodynamic structure 11.

(Embodiment 2)
In the second embodiment, in the helicopter 1 of the first embodiment shown in FIG. 1, a shielding member 10B is attached instead of the shielding member 10. Other configurations and operations in the second embodiment are the same as those of the helicopter 1 and the shielding member 10 of the first embodiment. Therefore, in FIGS. 5 to 6, the members common to the helicopter 1 of FIGS. 1 to 4 are designated by the same reference numerals, and duplicate description is omitted. Further, since the structure of the first embodiment described in FIGS. 1 and 3 is basically the same in the second embodiment, the symbols are replaced and FIGS. 1 and 3 are described in the second embodiment. It is used for.

As shown in FIG. 1, in the helicopter 1B of the second embodiment, the shielding member 10B is attached to the upper surface of the fuselage 2 by using eight nuts 10a in two rows. The shielding member 10B uses the airflow D3 of the downdraft D2 flowing from the center side to the outer peripheral side to generate a propulsive force for the helicopter 1B to move forward. The shielding member 10B is provided on the fuselage 2 of the helicopter 1B, and shields the blow-down D2 that is blown downward toward the fuselage 2 as the main rotor 3 rotates.

As shown in FIG. 5A, the shielding member 10B has hydrodynamic structures 12 and 13 symmetrical with respect to the center line of the helicopter (1B: FIG. 1). The shielding member 10B is a thick disk-shaped member in which the airflow grooves 12c and 13c, which are examples of the hydrodynamic structures 12 and 13, are arranged in the circumferential direction. Although the airflow grooves 12c and 13c are symmetrically provided in the shielding member 10B, the airflow grooves 12c and 13c are slightly deviated from the left-right symmetry by conducting an experiment in consideration of the rotation direction of the main rotor 3. May be provided. As shown in FIG. 5C, in the shielding member 10B, a circular mounting plate 10e on the center side and an annular shielding plate 10g on the outer peripheral side are connected by a cylindrical upright wall 10h.

As shown in FIG. 6, the portion of the shielding plate 10g located on the outside of the body 2 is formed of a transparent acrylic resin plate. The portion of the shielding plate 10g that overlaps the body 2, the portion that is close to the body 2, the mounting plate 10e, and the upright wall 10h are made of a heat-resistant material.

As shown in FIG. 3A, the shielding member 10B is detachably attached and fixed to the upper surface of the fuselage 2 of the helicopter 1B. As shown in FIG. 3B, the shielding member 10B is fixed to the upper surface of the body 2 by using anchor bolts 10c and nuts 10a.

In the second embodiment, by having the shielding member 10B provided with the airflow grooves 12c and 13c, the shielding member 10B uses the airflow D3 of the blow-down D2 flowing from the center side to the outer peripheral side along the shielding member 10B. Helicopter 1 is generating forward propulsion. Then, the burden on the main rotor 3 is reduced by utilizing this propulsive force.

The airflow groove 12c has a propulsive force that pushes the fuselage 2 forward from the airflow D3 that flows from the center side to the outer periphery side guided by the shielding member 10B, and a drive that rotates the fuselage 2 in the rotation direction (R1) of the main rotor 3. Generates force. The airflow groove 13c has a propulsive force that pushes the fuselage 2 forward from the airflow D3 that flows from the center side to the outer periphery side guided by the shielding member 10B, and rotates the fuselage 2 in the opposite direction (R2) of the rotation of the main rotor 3. The driving force to be generated and the driving force to be generated are generated. Therefore, the airflow grooves 12c and 13c cancel each driving force and add the respective propulsive forces to generate a driving force for pushing the shielding member 10B forward.

As shown in FIG. 5A, the airflow groove 12c has a continuous airflow groove 12c in the diameter direction of the main rotor 3. The two adjacent airflow grooves 12c are separated by a guide wall 12b that stands up from the shielding surface 12a of the shielding member 10 toward the main rotor 3 and is continuous in the radial direction. The airflow groove 12c partitioned by the curved guide wall 12b generates a driving force in the direction required for the shielding member 10B. The outer peripheral portion of the guide wall 12b of the airflow groove 12c having a cross section parallel to the shielding surface 12g is curved in the direction opposite to the driving force to be generated. The guide wall 12b is formed in the diametrical direction on the central side and curved in the arrow R1 direction on the outer peripheral side to connect to the outlet 12d.

As shown in FIG. 5A, the airflow groove 13c has a continuous airflow groove 13c in the diameter direction of the main rotor 3. The two adjacent airflow grooves 13c are separated by a guide wall 13b that stands up from the shielding surface 13a of the shielding member 10 toward the main rotor 3 and is continuous in the radial direction. The airflow groove 13c partitioned by the curved guide wall 13b generates a driving force in the direction required for the shielding member 10B. The outer peripheral portion of the cross section of the guide wall 13b of the airflow groove 13c parallel to the shielding surface 13g is curved in the direction opposite to the driving force to be generated. The guide wall 13b is formed in the diametrical direction on the central side, and is curved in the arrow R2 direction on the outer peripheral side to connect to the outlet 13d.

As shown in FIG. 5C, the airflow grooves 12c and 13c have the following three hydrodynamics with respect to the shielding member 10B when the airflow D3 flows from the center side to the outer peripheral side of the shielding member 10B. Apply force

(1) Injection: The airflow D3 is guided by the guide walls 12b and 13b and is injected from the outlets 12d and 13d on the outer periphery of the shielding member 10B. The reaction force of the injection causes the shielding member 10B to act as a driving force in the directions of arrows R2 and R1 via the guide walls 12b and 13b. (2) Bending of the flow path: The airflow D3 is guided by the curved guide walls 12b and 13b. The flow direction is bent in the directions of arrows R1 and R2. The reaction force at this time causes the shielding member 10B to act on the shielding member 10B via the guide walls 12b and 13b in the directions of arrows R2 and R1. The airflow flowing outside has a higher flow velocity than the airflow flowing inside. Therefore, lift (horizontal direction) is generated on the guide walls 12b and 13b in the direction opposite to the bending direction (convex arrows R2 and R1 directions).

In the second embodiment, the airflow grooves 12c and 13c, which are examples of the hydrodynamic structures 12 and 13, generate a driving force in the direction of pushing the fuselage 2 forward from the airflow D3 flowing along the shielding member 10B. Therefore, it is possible to effectively utilize the blow-down D2 of the main rotor 3 shielded by the shielding member 10B to reduce the rotational load of the main rotor 3 for pushing the fuselage 2 of the helicopter 1 forward.

In the second embodiment, the shielding member 10B having the airflow grooves 12c and 13c generates a driving force in the direction of pushing the fuselage 2 forward, which cannot be generated by the shielding member 10H shown in FIG. 7. Therefore, the function of the helicopter 1 can be improved by utilizing the driving force generated by the airflow grooves 12c and 13c.

In the first and second embodiments, the shielding member 10 has a circular contour centered on the shaft 3a of the main rotor 3 and is arranged substantially parallel to the rotating surface of the main rotor 3. However, the shielding member according to the present invention may have an elliptical, square, or asymmetrical contour, and the thickness of one portion may be different from the thickness of the other portion. The surface of the shielding member facing the main rotor 3 is not limited to a flat surface, but may be a curved surface, or may be a surface inclined with respect to the rotating surface of the main rotor 3. By designing the airflow groove in consideration of the contour, thickness, and inclination, it is possible to extract an effective driving force for the helicopter fuselage from the airflow flowing along the shielding member.

Further, in the first and second embodiments, the hydrodynamic structure is an airflow groove in which the outer peripheral portion is curved in the direction opposite to the required driving force from the central side portion continuous in the radial direction. However, the hydrodynamic structure is not limited to such an airflow groove. It may be a large number of turbine blades that generate lift in the direction of the required driving force from the airflow flowing in the radial direction along the shielding member.

Further, in the first and second embodiments, a shielding member having a diameter of about 40% of the diameter of the main rotor is shown. However, the size of the shielding member is not limited to this. The size of the shielding member can be arbitrarily set according to the size of the shielding area of the blow-down required under the main rotor.

The present invention is not limited to the shielding member and the helicopter described in the first and second embodiments. It can be widely implemented if the helicopter flies by the lift generated by rotating the main rotor over the fuselage and is blown down by the rotation of the main rotor. It can be carried out from a large aircraft with several tens of people on board to a small aircraft with one person on board. It can also be carried out on unmanned aerial vehicles that do not have pilots or workers. It can also be carried out in an autopilot helicopter that flies according to a remote control or flight program for the purpose of farm work, baggage delivery, photography, search, etc. This is because, in any of the applications, the blow-down of the main rotor can be effectively utilized by providing the shielding member having an appropriate hydrodynamic structure.

1 Helicopter 2 Body 3 Main rotor 3a Shaft 3b Blade 4 Engine 5 Skid 6 Tail rotor 7 Aileron 8 Vertical stabilizer 10, 10B, 10H Shielding member 10a Nut 10b Mounting hole 10c Anchor bolt 10e Mounting plate 10f Opening 10g Shielding plate 10h Standing wall 11, 12, 13 Fluid dynamics structures 11a, 12a, 13a Shielding surfaces 11b, 12b, 13b Guide walls 11c, 12c, 13c Airflow grooves 11d, 12d, 13d Outlet A Shielding member width B Body width D1, D2 Blow-down F1 Lift

Claims (8)

A shielding member provided on the fuselage of a helicopter that shields the blow-down that is blown downward toward the fuselage as the main rotor rotates.
The shielding member is characterized by having a hydrodynamic structure that generates a driving force in a direction in which the body is rotated in the rotation direction of the main rotor from an air flow guided by the shielding member from the center side to the outer peripheral side. , Shielding member. The hydrodynamic structure is a claim that is a continuous airflow groove in the radial direction of the main rotor, which is partitioned by a guide wall erected from the shielding surface of the shielding member toward the main rotor. Item 2. The shielding member according to item 1. The shielding member according to claim 2, wherein the cross section of the guide wall parallel to the shielding surface is curved in the direction opposite to the driving force to be generated. A shielding member provided on the fuselage of a helicopter that shields the blow-down that is blown downward toward the fuselage as the main rotor rotates.
The shielding member has a hydrodynamic structure that generates a driving force in a direction that pushes the fuselage toward the front side of the helicopter from an air flow that is guided by the shielding member and flows from the center side to the outer peripheral side. Element. 4. The hydrodynamic structure is characterized by being a continuous airflow groove in the radial direction of the main rotor, which is partitioned by a guide wall erected from the shielding surface of the shielding member toward the main rotor. The shielding member described in. The shielding member according to claim 5, wherein the cross section of the guide wall parallel to the shielding surface is curved in a direction opposite to the direction of the driving force to be generated. A helicopter comprising the shielding member according to any one of claims 1 to 6. A helicopter having the shielding member according to any one of claims 1 to 3, and not having a tail rotor for canceling the rotational reaction force of the main rotor acting on the fuselage.

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