JPH06286696A - Antitorque canceller for main rotor - Google Patents

Abstract

PURPOSE:To provide an antitorque canceller for a main rotor of a helicopter without a tail rotor causing damages and a compressor generating noises. CONSTITUTION:A tail plates 2 provided nearly above and below a position of a tail boom 1 of a helicopter struck by downward blow of a main rotor to generate a lateral air force with a change in the attitude to the flow of the downward blow and an attitude changing means for changing the attitude of the tail plates are provided to constitute an antitorque canceller for the main rotor.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a device for canceling anti-torque of a main rotor of a helicopter.

[0002]

2. Description of the Related Art As is well known, in a helicopter, when the main rotor rotates, the anti-torque of the main rotor causes the airframe to rotate in the opposite direction. Therefore, measures against the reverse rotation are taken.

For example, FIG. 5A shows a conventional tail rotor type helicopter. When the main rotor blade 3 rotates, a counter torque is generated in the entire body, and the body rotates in the opposite direction. In order to prevent the rotation of the machine body, the tail rotor 12 is attached to the rear of the tail boom 1 and the tail rotor 12 is rotated to cancel the anti-torque and stop the rotation of the machine body.

FIG. 5 (b) shows a conventional noter type helicopter in which a jet gas (gas) 4 is jetted from a tail boom 1 to cause a main rotor wake 5 to flow in a non-uniform manner, and a jet torque momentum of the jet gas 4 produces anti-torque. It is a cancellation method and is currently in practical use.

In FIG. 5 (a), 13 is a fuselage, 14 is a turbine engine as a drive source, 15 is a tail, and 16 is a landing skid.

[0006]

The conventional anti-torque canceling means for the main rotor has the following problems to be solved.

That is, in the conventional tail rotor type shown in FIG. 5A, the tail rotor 12 is a rotating body, and if it hits an object, it will be damaged and cause a fatal problem. Also, the tail rotor 1
If the tail rotor 12 comes into contact with a person while rotating the wheel 2, there is a problem of causing a serious injury.

Although the conventional notter type shown in FIG. 5 (b) solves the above problems, it requires a compressor to generate compressed gas to be ejected from the tail boom 1 and causes a large noise. There is a problem that power loss is also large.

In order to solve the above problems, the present invention provides a main rotor anti-torque canceling device that does not have a tail rotor that is a rotating body and a compressor that has a high-speed rotating portion and that does not generate noise or power loss. The purpose is to

[0010]

As a means for solving the above-mentioned problems, the present invention is provided approximately above and below the portion of the tail boom of a helicopter where the main rotor downwind hits, and changes its posture with respect to the downwind flow. An object of the present invention is to provide a main rotor anti-torque canceling device comprising a tail plate for generating aerodynamic force in the lateral direction and a posture changing means for changing the posture of the tail plate.

[0011]

Since the present invention is constructed as described above, it has the following actions.

That is, a tail plate for generating aerodynamic force in the lateral direction is provided almost above and below the portion of the helicopter tail boom where the main rotor is blown down, and the attitude can be changed by the attitude changing means. Since it is configured, if the attitude changing means is operated so as to generate the lateral aerodynamic force causing the drift caused by the attitude change, that is, the lateral thrust in the direction to cancel the anti-torque of the main rotor, the tail rotor and the gas ejection The anti-torque of the main rotor can be canceled without using any means.

[0013]

DESCRIPTION OF THE PREFERRED EMBODIMENTS First and second embodiments of the present invention will be described with reference to FIGS. The same members as those in the conventional example or the previous example are designated by the same reference numerals, and the description thereof will be omitted unless necessary.

First, the construction common to both the first and second embodiments and the generation of thrust in the lateral direction with respect to the machine axis of the helicopter will be described with reference to FIGS. 1 and 2.

FIG. 1 is a view common to both embodiments, and is a bird's-eye view of a helicopter equipped with a tail plate 2. FIG. 2 is an explanatory view of thrust generation by a view of the helicopter tail boom 1 of FIG. 1 in the axial direction. is there.

In FIG. 1, reference numeral 2 denotes an appropriate portion of the tail boom 1, that is, the main rotor blade 3 is reliably blown down and the torque is generated from the rotary shaft of the main rotor blade 3. It is a tail plate that can change its posture above and below the position with the largest distance (span). Others are the same as those in FIG. 5A of the conventional example.

As shown in the figure, the tail plate 2 sandwiches the tail boom 1 from above and below, and the cross-sectional shape seen in the machine axis direction is like a wing cross section (specifically, the front edge of the wing cross section in the vertical direction). And a shape similar to the trailing edge), for example, as shown in FIG. 2 (a) or (b), it is asymmetrical with respect to the vertical center line (not shown) passing through the center of the tail boom 1. As described later, the asymmetry can be relaxed by the posture changing means.

The reason why the tail plate 2 is provided "almost above and below" the tail boom 1 is that the main rotor blade 3 blows down as a whole, and the tail plate 2 descends in a spiral or spiral manner. This is because the wind blows down from a slanting upper position, and the upper and lower positions where the tail plate 2 is attached are not necessarily appropriate to the vertical position when the helicopter is stopped on the ground.

Next, the principle of lateral aerodynamic force generated by the tail plate 2, that is, the principle of lateral thrust generation will be described with reference to FIG.

In FIG. 2, reference numeral 5 designates a main rotor blow-down, which is virtually indicated by a broken line. The tail boom 1 and the tail plate 2 to be placed in the main rotor downwind 5
As described above, the airflow flowing on both sides of the tail boom 1
Since the tail plate 2 and the tail plate 2 are asymmetrical and the path length per unit height (and therefore unit time) is different, the flow is also asymmetrical and the flow velocities are different on the left and right. On the larger side, eg Figure 2
In (a), the static pressure is smaller on the right side of the broken line than on the left side, and aerodynamic force, that is, thrust is generated in the direction of the outlined arrow in the figure. In the opposite case, the result is as shown in FIG. Unless a vortex is generated, the larger the difference between the right and left flow velocities, the larger the thrust generated. Therefore, the stronger the asymmetry, the larger the thrust.

On the other hand, since the helicopter has a large anti-torque corresponding to a flight requiring a large torque such as a high-speed flight and a flight with a heavy load, the thrust is increased to cancel the anti-torque. That is, the counter torque is canceled by making the product of the above-mentioned span and the above-mentioned thrust correspond to the above-mentioned counter torque, but since the span cannot be changed once it is fixed,
The anti-torque may be offset by changing the thrust, and thus by changing the asymmetry between the tail boom 1 and the tail plate 2. The modification of the asymmetry, that is, the modification of the attitude of the tail plate 2 will be described below with reference to the first and second embodiments. It should be noted that here, "posture change" necessarily includes "shape change".

(First Embodiment) A first embodiment will be described with reference to FIG.

FIG. 3 is a schematic view of the main part of this embodiment.
Is a cross-sectional view as seen in the machine axis direction, and (b) is a view taken in the direction of arrow A in (a).

In the figure, 6 is a screw shaft having one end rotatably supported on one side of the tail plate 2 and the other end screwed into a screw hole at the center of the worm passive gear 7 (however, a male screw is omitted). 7), which is rotatably supported around an axis by a member (not shown) and has the screw hole at the center,
A worm passive gear having meshing teeth that engage with the worm drive gear 8 on the outer periphery, 8 is a worm drive gear that is rotationally driven by a stepping motor (not shown), hydraulic pressure, or the like, and engages the worm passive gear 7 to rotate it. Numerals 9 are provided on the upper and lower outer circumferences of the tail boom 1 so as to be half-surrounded in the circumferential direction. It is a guide that supports the front and rear ends so that it can move.

As shown in FIG. 3B, the upper tail plate 2 and the lower tail plate 2 are supported by the respective screw shafts 6 at a point slightly different from each other in the machine axis direction. The apex of the tail plate 2 is the joint point of each side that straddles the left and right, but the joint at this point is also a hinge pin method in which irregularities that are interleaved from each side are vertically passed by pins in the machine axis direction. Or, the bending radius of the bending of that part viewed in the machine axis direction is such that the stretching strain of the surface outer skin or the contraction strain of the inner surface outer skin due to bending when viewed from the neutral axis of the plate thickness is sufficiently within the elastic limit of the material. It may be a mere bent plate body set to have a size capable of withstanding repeated bending.

Alternatively, the tail plate 2 may have a rigid apex angle and be displaced on the guide 9 in accordance with expansion and contraction (movement) of the screw shaft 6, which causes a drift by changing the posture. The configuration may be freely selected within the range of the purpose.

Next, the operation of the above configuration will be described.

When the main rotor blade 3 rotates with a high torque and the counter torque also increases and a large thrust force is required to cancel, the worm drive gear 8 is rotated and each screw shaft 6 attracts each tail plate 2. Operate in the direction. Then, the worm passive gear 7 is driven to rotate, the screw shaft 6 is fed through the inside of the worm passive gear 7, and the vertices of the tail plate 2 are further moved to the asymmetrical eccentric side, for example, as shown in FIG.
Of the tail boom 1 and the tail plates 2 on the left and right sides of the main rotor, and the path length difference of the flow of the main rotor 5 is further widened.
Correspondingly, the flow velocity difference opens and the thrust becomes larger to cancel the anti-torque. Axial torque of the main rotor blade 3,
It is not necessary to make the downwind speed, the airspeed of the helicopter, etc., and the rotation of the worm drive gear 8 interlocked with each other through a computing unit so that the anti-torque is always canceled by the cancel torque without excess or deficiency. is there. If the anti-torque is reduced, perform the reverse operation.

Note that, although FIG. 2 shows separate (a) and (b) in which thrust is generated in the rightward direction and in the leftward direction, generally, the rotation direction of the main rotor blade 3 of the helicopter is fixed and the same. It does not occur that the case (a) has to be selected in some cases and the case (b) has to be selected in some cases for the helicopter.

Therefore, there is no particular need to take measures against the configuration in which the eccentricity of the tail plate 2 moves to the opposite side beyond the plane position of the machine axis, but such a configuration over a wide area is free. Also, depending on the flight situation, if the rotation torque of the main rotor increases, the main rotor will blow down.
2 also increases and the thrust in FIG. 2 also increases, so it is not necessary to change the rotational torque and the attitude of the tail plate 2 in a linear relationship. Therefore, control is possible in a narrow range, and this embodiment has extremely high practicality.

(Second Embodiment) A second embodiment will be described with reference to FIG.

FIG. 4 is a schematic view of the main part of this embodiment as viewed in the machine axis direction. In FIG. 4, one end is at one side of the tail plate 2 and the other end is at the eccentric position of the disc cam 11. A link rotatably and rotatably supported, 11 is a disc arm whose rotary shaft is supported parallel to the machine shaft at a position eccentric to the machine shaft by a required amount in one of the left and right directions. The ends are pivotally supported symmetrically with respect to the axis of the disc arm 11 in such a manner that a push-pull thereof causes a couple. Other configurations are similar to those of the first embodiment.

Since this embodiment is constructed as described above,
By rotating the disk arm 11 reciprocally by a motor, a hydraulic actuator or the like (not shown), the same effect as that of the first embodiment can be obtained.

As described above, according to the first and second embodiments,
Due to the shallow eccentricity of the tail plate 2, the main rotor is blown down to variably diverge the air flow, and the lateral aerodynamic force generated by this, that is, the lateral variable thrust (correctly, the product of the thrust and the above span) exerts a counter torque. Since it is erased, there is an advantage that the possibility of colliding with other objects and destroying them is extremely small as compared with the case where a tail rotor is used as in the related art.

Further, since it does not rotate like a tail rotor, there is an advantage that a person is almost injured.

Further, since the tail plate is attached to the machine body as a moving structure, so to speak, there is an advantage that the problem of noise generation due to the jet gas does not occur unlike the conventional noter type helicopter.

Further, since the driving force required to change the attitude of the tail plate is extremely small, there is an advantage that both cost and power loss are small as compared with the conventional noter type which requires a powerful compressor for producing compressed gas.

[0038]

Since the present invention is constructed as described above, it has the following effects.

That is, according to the present invention, the tail plate attached to the tail boom cancels the anti-torque of the main rotor, so that there is no high-speed rotating portion exposed to the outside unlike the conventional tail rotor, and therefore, it does not interfere with other objects. The collision probability is low, the damage frequency is low, and the safety is high.

Further, unlike the conventional noter type, there is no compressor having a built-in high-speed rotating part, and therefore the noise is small and it is hard to break down, so that the reliability is high.

Further, the cost and power loss are small.

[Brief description of drawings]

FIG. 1 is an overhead view of a helicopter according to first and second embodiments of the present invention,

FIG. 2 is an explanatory view of lateral thrust (aerodynamic force) generation according to the first and second embodiments,

FIG. 3 is a diagram of a main part of the first embodiment, in which (a) is a cross-sectional view as seen in the machine axis direction, (b) is an enlarged view of arrow (A) taken in (a),

FIG. 4 is a cross-sectional view of the main part of the second embodiment as viewed in the machine axis direction,

FIG. 5 is a perspective view of a conventional helicopter, in which (a) is a tail rotor type and (b) is a noter (non-tail type).
It is a figure showing a rotor) type, respectively.

[Explanation of symbols]

 1 Tail boom 2 Tail plate 3 Main rotor blade 5 Main rotor downwind 6 Screw shaft 7 Worm passive gear 8 Worm drive gear 9 Guide 10 Link 11 Disc arm

Claims (1)

[Claims] 1. A tail plate, which is provided substantially above and below a portion of a helicopter tail boom where the main rotor is blown down, and which generates aerodynamic force in the lateral direction by changing its posture with respect to the flow of the downwind, and the tail plate. A main rotor anti-torque canceling device comprising: a posture changing means for changing the posture of the plate.