JP2630676B2 - Rotor wing helicopter with flap - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION A. Object of the Invention (Industrial Application Field) The present invention relates to an interaction between a flap attached to a leading edge or a trailing edge of a helicopter rotor blade and an auxiliary wing generating a seesaw effect. The present invention relates to a helicopter that averages the lift of each rotor, eliminates vibration of the fuselage, and enables stable flight.

(Prior Art) Generally, the vertical flight of a helicopter is stable because the lift of each rotor is equal.

However, in a level flight, the rotors vibrate due to the gyro-effect precession and flapping and dragging, due to the unbalanced lift of both rotors at the beginning or due to gusts and the like.

 These are inherent disadvantages of helicopters.

For this reason, stabilizers were employed. For example, bell
UH-1H Stabilizing Bar (Airport Annual Jane ')
All the world aircraft 1984-85,
(Refer to the 12th line from the bottom right of page 322) and Hiller UH-
This is a 12ET servo rotor (see line 17 from the bottom left column of the same yearbook 418).

These are mechanisms for adjusting the pitch angle of each rotor according to changes in the attitude of the helicopter. However, there is a difference in lift between the rotors, and the above drawback has not been completely solved.

(Problems to be solved by the invention) The present invention solves the drawbacks inherent in conventional helicopters,
The purpose is to obtain a stable helicopter.

B Configuration of the Invention (Means for Solving the Problems) Basically, means for eliminating the unbalanced lift difference between the rotors is considered. The part of the seesaw bar with the auxiliary wing at the tip,
In this method, the lift of the auxiliary wing is applied to the flap by interlocking with the flap of the rotor, and the lift of each rotor is equalized by the seesaw effect.

(Action) One rotor and the aileron directly above it have the same aerodynamic conditions. When the lift of the rotor is large, the lift of the auxiliary wing is also large. For this reason, when the auxiliary wing is raised above the horizontal reference, the flap linked to the seesaw bar and the connecting rod is directed upward through the hinge of the rotary wing, so that the flap effect of the rotary wing is reduced.

The auxiliary wing on the opposite side is lower than the horizontal reference due to the seesaw effect with the spherical seesaw head as a fulcrum, and the attached flaps associated therewith are also lowered, and the flap effect of the rotary wing is increased.

 Thus, the lift of each rotor is equalized.

(First Embodiment) FIG. 1 of the first embodiment shows a state in which a rotary wing rotates clockwise 10 degrees from a rotation reference point 0 degrees shown in FIG. 2 during a vertical flight of a helicopter.

(A) Transmission of rotational force The power of the prime mover (not shown) of the helicopter 1 is transmitted to the rotary shaft 2 as a rotational force. In FIG. 2, this rotational force is transmitted to the gimbal inner wheel 5x of the rotary wing head 5 and further to the cymbal outer wheel 5y, and becomes rotary blade power. In addition, inner ring 5x
Is sliding back and forth around A, outer ring 5y is sliding left and right around B,
Each can be tilted.

The rotating blades 3 and 4 are attached to the outer edge of the outer ring 5y at a pitch angle α.

The strength of the rotating blades is adjusted by the prime mover throttle and mixture (not shown).

(B) Auxiliary wing and flap In FIG. 1, a support frame 8 is provided directly above the roots of both rotors, and a spherical seesaw head 9 having a ball bearing shown in FIG. It can be freely tilted forward, backward, left and right. At both ends of the seesaw bar 10, at a pitch angle α,
The auxiliary wings 11 and 12 are attached.

A terminal 10a and a terminal 10b are provided on the seesaw bar 10 at two positions equidistant from the center of the seesaw head to the left and right.

Terminals 6a and 7a are provided on the flap 6 at the leading edge of the rotor 3 and the flap 7 at the leading edge of the rotor 4, respectively.

The terminals are made of bolts and corresponding nuts. The same applies hereinafter.

The exploded perspective view of FIG. 4 shows that the connecting rod 1 is connected to the terminals 10a and 6a.
Insert the ends at both ends of 3 and tighten the bolt. The end also has a slip between the bolt and the nut. In addition, both nuts adhere to the seesaw bar and the flap, respectively.

Thus, the auxiliary wing 11 and the flap 6 form a link mechanism. Similarly, the ends at both ends of the connecting rod 14 are inserted into the terminal 10b and the terminal 7a, and the auxiliary wing 12 and the flap 7 are linked.

Therefore, when there is a difference between the lifts of the rotors, for example, if the lift of the rotor 3 becomes larger than the lift of the rotor 4,
The lift of the auxiliary wing 11 becomes larger than the lift of the auxiliary wing 12, and this force acts on the connecting rod 13, and the flap 6 is raised to reduce the flap effect, so that the lift of both rotors is equalized.

FIG. 5 shows a side view of the section taken along the line CC 'of FIG. 1, in which the flap 6 is connected to the rotor 3 at the elevation angle β by the hinge 3a, and the flap 7 is connected to the rotor 4 by the hinge 4a.

(C) Maneuvering In FIGS. 1 and 2 and FIG. 6 showing the side surface of the swash plate, when the control stake 21 is pushed forward from the neutral position, the front of the fixed star of the swash plate 17 is passed through the connecting rod 18. The terminal 17a attached to
The terminal 17c of the movable star is also inclined downward.

The terminal 5a of the rotary head 5 is tilted downward by the mediation of the connecting rod 15 connected to the terminal 17c. Therefore, the outer ring 5y is inclined downward. As a result, the rotor 3 and the rotor 4 tilt downward, and the helicopter can advance from vertical flight.

If the control stick 21 is pulled backward, the above is reversed, and the helicopter moves backward.

The assembling of the link mechanism is in accordance with the above item (b). The same applies hereinafter. When the control stick 21 is tilted to the left and the terminal 17b attached to the fixed star side of the swash plate 17 is tilted to the left through the connecting rod 19, the terminal 17d of the movable star also tilts to the left. Terminal 17d
The terminal 5b of the rotary head 5 is tilted to the left by the intermediary of the connecting rod 16 which is connected to the rotating head 5. Therefore, the outer ring 5y inclines to the left, and the helicopter advances to the left.

If the control stick 21 is tilted to the right, the above is reversed, and the helicopter proceeds to the right.

Further, if the control stick 21 is freely operated, it is possible to fly in a desired direction.

The terminals 5a and 5b and the connecting rods 15 and 16
Are mounted so that their spatial positions are 90 degrees from each other when viewed from the rotation axis.

(D) Others The tail rotor 20 and the directional control device, the prime mover, the aviation instrument, the electric switch, the skid, and the like are provided with ordinary equipment.

(Second Embodiment) FIG. 7 shows a second embodiment, in which a flap 6 and a flap 7 are attached to the trailing edge of the rotor 3 and the trailing edge of the rotor 4 of the helicopter 1, respectively. The flap, with the left and right parts of the seesaw bar 10 with the auxiliary wings 12,
They are connected by connecting rods 13 and 14, respectively. The method of connection is in accordance with FIG. Other configurations are as described above. The attachment of the flap to the rotor is based on the usual example.

C. Effects of the Invention (a) Unbalanced lift of each rotor is always equalized, and the gyro effect hardly causes pressurization.

(B) Unbalanced flapping and dragging do not occur.

(C) The life of the rotor, the body parts and the body is prolonged because of no vibration.

[Brief description of the drawings]

1 is a longitudinal sectional view of a helicopter according to a first embodiment of the present invention. FIG. 2 is a plan view showing a rotary wing head and a rotary wing. FIG. 3 is a side view showing a part of a seesaw head in cross section. FIG. 4 is an exploded perspective view of a seesaw bar, a flap and a connecting rod. FIG. 5 is a cross-sectional view showing a connection between a rotor and a flap. FIG. 6 is a side view showing a swash plate. FIG. Connection plan view of the trailing edge of the rotor and the flap 1. Helicopter, 2 ... Rotary shaft, 3, 4 ... Rotor,
5 ... rotating head, 6, 7 ... flap, 8 ... support frame,
9… seesaw head, 10… seesaw stick, 11,12 ……
Auxiliary wings, 17 swash plate, 20 tail wings, 21 control stick

Claims (2)

(57) [Claims] A rotor (3) and a rotor (4) located above a helicopter fuselage (1) are fixed to the outer edge of a rotor head (5) at a constant pitch angle, and these rotors are A mechanism for receiving a rotational force from a rotating shaft (2) of a prime mover installed in a helicopter fuselage, wherein flaps (6) are provided at the leading edge of the rotating wing (3) and the leading edge of the rotating wing (4), respectively.
And a flap (7), a support frame (8) is provided directly above the roots of both rotors, a spherical seesaw head (9) is attached to the top of the support frame, and the upper part of the spherical seesaw head is used as a fulcrum. Attached to the both ends are fixed wings (11) and auxiliary wings (12) at a fixed pitch angle, respectively. The left and right portions of the seesaw bar and the flap are connected to the connecting rod (13) and connecting rod, respectively. (14), the auxiliary wing and flap are linked, and the seesaw effect of the lift of the auxiliary wing reduces the flap effect of the rotor with high lift and the flap effect of the rotor with low lift to increase each rotation. The difference in rotor lift due to the difference in blade pitch angle or the difference in airspeed in the direction of travel of each rotor is equalized by flap operation, and flapping and dragging of each rotor is reduced. A helicopter that reduces the vibration of the helicopter fuselage and enables stable flight. 2. A rotor (3) and a rotor (4) located above a helicopter fuselage (1) are fixed to an outer edge of a rotor head (5) at a constant pitch angle, and these rotors are A flap (6) and a flap (7) are attached to the trailing edge of the rotating blade (3) and the trailing edge of the rotating blade (4), respectively, by receiving the rotating force from the rotating shaft (2) of the prime mover. From above, a spherical seesaw head (9) is provided at the top of the support frame (8) just above the support frame (8). And the ailerons (12) are attached, and the flap and the left and right parts of the seesaw bar are connected with the connecting rods (13) and (14), respectively. Rotation with low lift Increase the wing flap effect,
A helicopter that equalizes the difference between the lifts of both rotors by flap operation, reduces flapping and dragging of each rotor, prevents vibration of the helicopter fuselage, and enables stable flight.