JP2001025582A - Rudder - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a rudder device which is driven by shape memory alloys, is capable of making switching, etc., of a progression direction by relatively rapidly switching rudders and may be reduced in size and weight. SOLUTION: This rudder device is provided with the first rudder 17 and the second rudder 19 and drives these rudders 17 and 19 by respectively separate monostable type shape memory alloy actuators. The rudders are so constituted that symmetrical rudder actions are effected when the first rudder 17 is moved in the prescribed first direction by the shape memory alloy 21 of the monostable type shape memory alloy actuator for the rudder 17 and when the second rudder 19 is moved in the prescribed second direction by the shape memory alloy 23 of the monostable type shape memory alloy actuator for the rudder 19.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rudder device driven by a shape memory alloy actuator, which is suitable as a rudder device for a model ship or an aircraft.

[0002]

2. Description of the Related Art FIGS. 1 and 2 show an example of a conventionally known differential shape memory alloy actuator. Support members 2 and 3 are fixed to the main body 1, and pins 4 and 5 are attached to these support members 2 and 3, respectively. A rotation shaft 7 provided at the center of the operation end member 6 is rotatably supported by the main body 1. A first shape memory alloy 9 wound in a coil shape is interposed between a pin 8 and a pin 4 provided at one end of the operation end member 6, while the other end of the operation end member 6 is provided. A second shape memory alloy 11 wound in a coil shape is interposed between the pin 10 and the pin 5 provided in the above. The second shape memory alloy 11
Stores the short shape shown in FIG. The first shape memory alloy 9 stores the same short shape as the second shape memory alloy 11.

In this differential type shape memory alloy actuator, when the first shape memory alloy 9 is cooled,
When the second shape memory alloy 11 is heated, as shown in FIG. 1, the second shape memory alloy 11 returns to the stored short shape, and rotates the operation end member 6 clockwise in FIG. The one shape memory alloy 9 is stretched and deformed in a macroscopic manner (for reference, in this case, in a true sense, each part of the first shape memory alloy 9 is bent and twisted). Conversely, when the first shape memory alloy 9 is heated while the second shape memory alloy 11 is cooling, the first shape memory alloy 9 returns to the stored short shape, and the operation is performed. The end member 6 is rotated counterclockwise in the drawing, and the second shape memory alloy 11 is expanded and deformed in a macroscopic view.
Thereby, a symmetrical movement can be performed in the figure.

FIGS. 4 and 5 show an example of a conventionally known monostable type shape memory alloy actuator. Support members 2 and 3 are fixed to the main body 1, and pins 4 and 5 are attached to these support members 2 and 3, respectively. A rotation shaft 7 provided at the center of the operation end member 6 is rotatably supported by the main body 1. A tension coil spring 12 made of a non-shape memory alloy material is interposed between a pin 8 provided at one end of the operation end member 6 and the pin 4. 6 is urged counterclockwise in the figure. A shape memory alloy 13 wound in a coil shape is interposed between a pin 10 and a pin 5 provided at the other end of the operation end member 6, and the shape memory alloy 13 is shown in FIG. I remember such a short shape.

In this monostable shape memory alloy actuator, when the shape memory alloy 13 is cooled,
As shown in FIG. 4, the operating end member 6 is rotated counterclockwise in the drawing by the force of the spring, and the shape memory alloy 13 is elongated and deformed macroscopically. On the other hand, when the shape memory alloy 13 is heated, as shown in FIG. 5, the shape memory alloy 13 returns to the short shape memorized against the spring 12, and
The operation end member 6 is rotated clockwise in the drawing.

[0006]

In the differential shape memory alloy actuator as shown in FIGS. 1 and 2, when the operating direction is switched, the shape memory alloy 9 or 11 which has been heated up to that time is not sufficiently cooled (see FIG. 1). While the shape recovery power has not been lost), the other shape memory alloy 11 or 9
Is heated, the two shape memory alloys 9 and 11 exert a shape recovery force in opposite directions to each other and do not move. The shape-restoring force of the shape-memory alloys 9 and 11 is larger than the yield limit depending on how strain is applied in a low-temperature state. In the worst case, not only cannot the actuator be moved, but also the shape memory alloy 9,
11 was broken or plastically deformed, and the actuator was broken.

In order to prevent such a situation from occurring, the heating temperature is minimized, and when the operation direction is switched, the shape memory alloy 9 or 11 on the side which has been heated up to that time is sufficiently cooled. After that, the other shape memory alloy 11 or 9 had to be heated. FIG. 3 is a time chart of the operation of the conventional differential shape memory alloy actuator showing such a situation. Between the cooling time of the first shape memory alloy 9 and the cooling time of the second shape memory alloy 11, there is wasted time during which the actuator cannot be moved. Since the cooling rate of the shape memory alloy depends on its heat capacity, it is usually much slower than the heating rate, so that the wasted time is considerably long, and the response of the actuator is very poor.

Therefore, it is practically impossible to drive a rudder such as a ship or an aircraft by the differential type shape memory alloy actuator as shown in FIGS.

On the other hand, in the monostable type shape memory alloy actuator shown in FIGS. 4 and 5, unless the operating end member 6 is restrained from the outside, an excessive force is not applied to the shape memory alloy 13 by heating. High actuator performance can be obtained. However, the stable point of operation is
It was always the side that was pulled by the spring 12 of the non-shape memory alloy material and could not get symmetrical motion. Therefore, it is impossible to control the traveling direction of a ship, an aircraft, or the like by driving one rudder in a symmetric direction.

The present invention has been made in view of such conventional circumstances, and one object of the present invention is to provide a steering device driven by a shape memory alloy.

Another object of the present invention is to provide a rudder device capable of relatively quickly switching rudder and changing a traveling direction.

Another object of the present invention is to provide a rudder device that can be reduced in size and weight.

Other objects of the present invention will become clear from the following description.

[0014]

A rudder device according to the present invention comprises:
The first and second rudders are provided, and these rudders are driven by different monostable type shape memory alloy actuators, respectively, so that a symmetric rudder effect is achieved. That is, the rudder device according to the present invention is linked to the first and second rudder so as to move the first rudder in a predetermined first direction when a shape recovery force is generated. A first shape memory alloy, first urging means for urging the first rudder in a direction opposite to the first direction, and when a shape restoring force is generated, the second rudder is moved to a predetermined position. A second shape memory alloy linked to the second rudder to move the second rudder in a second direction; and a second urging means for urging the second rudder in a direction opposite to the second direction. When the first rudder is moved in the first direction and when the second rudder is moved in the second direction, a symmetric rudder action is performed. It is something that has become.

In the present invention, when the first shape memory alloy is heated, the shape memory alloy generates a shape restoring force, and moves the first rudder in the first direction, while moving the second shape memory alloy. When heated, the shape memory alloy generates a shape recovery force,
Move the second rudder in the second direction. When the first rudder is moved in the first direction, and when the second rudder is moved in the second direction, a symmetric rudder action is performed.

When the first shape memory alloy is heated to move the first rudder in the first direction, and when it is necessary to perform a symmetrical rudder action, The heating of the second shape memory alloy is simultaneously stopped while heating the second shape memory alloy. Then, the second rudder is moved in the second direction, but since the first shape memory alloy does not cool down immediately after the heating is stopped, it is moved in the first direction for a certain time. It is in a state of being left. For this reason, the first rudder is temporarily moved in the first direction, and the second rudder is moved in the second direction. Although a phenomenon such as an increase in lift occurs, as the first shape memory alloy cools, the first rudder is moved in the opposite direction to the first direction by the first biasing means, and returns to the initial position. Going, and only the second rudder is operating.

Conversely, when the second shape memory alloy is heated to move the second rudder in the second direction, and when it becomes necessary to perform a symmetric rudder action, Then, the heating of the second shape memory alloy is stopped, and at the same time, the first shape memory alloy is heated. Then, the first rudder is moved in the first direction, but since the second shape memory alloy does not cool down immediately after the heating is stopped, it is moved in the second direction for a certain time. It is in a state of being left. For this reason, the first rudder is temporarily moved in the first direction, and the second rudder is moved in the second direction. Although a phenomenon such as an increase in lift occurs, as the second shape memory alloy cools, the second biasing means moves the second rudder in a direction opposite to the second direction, and returns to the initial position. Go, and only the first rudder is in operation.

As described above, when one of the shape memory alloys is heated and one of the rudders is moved in a predetermined direction, and it is necessary to perform a rudder action symmetrical to the one, the one of the above-mentioned one is required. Since the heating of the shape memory alloy can be stopped and the other shape memory alloy can be heated at the same time, the two rudders are temporarily in a state of simultaneously performing a symmetric rudder action, but as a whole, relatively quickly By switching the rudder, the traveling direction can be changed.

By intentionally heating both the first and second shape memory alloys, it is possible to intentionally increase braking, lift, and the like.

Since the rudder device according to the present invention uses a shape memory alloy as a drive source, the size and weight can be reduced.

[0021]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, the present invention will be described based on embodiments.

[0022]

6 to 8 show a first embodiment of the present invention. This embodiment is an embodiment in which the present invention is applied to a model ship rudder. In this embodiment, a right rudder shaft 15 extending vertically is rotatably supported on the right side of the stern of the hull 14, and a left rudder shaft 16 extending vertically is rotatably supported on the left side of the stern. ing. 8, a right rudder 17 (first rudder in the present embodiment) and a central portion of a right arm 18 are fixed to the right rudder shaft 15, while the left rudder is A left rudder 19 (a second rudder in this embodiment) and a central portion of a left arm 20 are fixed to the shaft 16. Between the hull 14 and one end of the right arm 18 is a coiled right shape memory alloy 21 (a first shape memory alloy in the present invention). Between them, a right spring 22 (first biasing means in this embodiment) composed of a tension coil spring made of a non-shape memory alloy material is interposed. Similarly, between the hull 14 and one end of the left arm 20, a left shape memory alloy 23 (the second shape memory alloy in the present invention) wound in a coil shape is provided. Left springs 24 (second urging means in the present embodiment) each composed of a tension coil spring made of a non-shape memory alloy material are interposed between the other ends.

The right shape memory alloy 21 stores a short shape as shown in FIG. The right spring 22
The right rudder 17 is biased in a clockwise direction as viewed from above via the right arm 18 (hereinafter, in the description of the present embodiment, clockwise and counterclockwise directions are viewed from above). ing. Thereby, when the right shape memory alloy 21 is cooling, as shown in FIG. 6, the shape memory alloy 21 is elongated and deformed in a macroscopic manner, and the right rudder 17 is
(Hereinafter, referred to as a straight-ahead position). The left shape memory alloy 23 also stores the same short shape as the right shape memory alloy 21. The left spring 2
4 urges the left rudder 19 counterclockwise via the left arm 20. Thereby, when the left shape memory alloy 23 is cooling, as shown in FIG. 6, the shape memory alloy 23 is elongated and deformed in a macroscopic manner, and the left rudder 19 is
(Hereinafter, referred to as a straight-ahead position). The right and left shape memory alloys 21, 23
Are supplied with current from a drive circuit (not shown).

Next, the operation of this embodiment will be described. Right and left shape memory alloys 21 and 23 are required to make the ship go straight.
No current is supplied to any of the two, and both the shape memory alloys 21 and 23 are cooled. Thereby, as shown in FIG.
The right rudder 17 and the left rudder 19 are both in the straight traveling position.

Next, when it is desired to turn the ship to the right, the drive circuit supplies electricity to the right shape memory alloy 21. Then
The right shape memory alloy 21 is heated to a predetermined temperature range by the Joule heat, and returns to the shape stored in the shape memory alloy 21 and becomes shorter, so that the right rudder 17 is moved from the straight traveling position to the right arm 18 as shown in FIG. And right spring 2 with right rudder shaft 15
2 counterclockwise (first direction in the present invention). As a result, the ship turns right.

Next, when it is desired to turn the ship to the left from the state of turning right, the right shape memory alloy 21 is used.
To the left shape memory alloy 23 from the drive circuit. Then, the left shape memory alloy 23 is heated to a predetermined temperature range by the Joule heat, and returns to the shape stored in the shape memory alloy 23 and becomes shorter. Therefore, as shown by the dashed line position in FIG. 19
Is rotated clockwise (second direction in the present invention) together with the left arm 20 and the left rudder shaft 16 against the left spring 24 from the straight traveling position. At this time, the right shape memory alloy 21
Even if the energization is stopped, it is not cooled immediately, so that it is rotated counterclockwise from the straight traveling position for a certain period of time. Therefore, the right rudder 17 is temporarily rotated counterclockwise from the straight-ahead position and the left rudder 19 is clockwise rotated from the straight-ahead position, and the ship is decelerated by braking. As the 21 cools, the right rudder 17 is rotated clockwise by the force of the right spring 22 and returns to the straight position, so that the ship turns left.

Conversely, when it is desired to turn the ship rightward from the state of turning left, the power supply to the left shape memory alloy 23 is stopped and the right shape memory alloy 21 is supplied from the drive circuit. Then, the right shape memory alloy 21 is heated and returns to the shape stored in the shape memory alloy 21 and becomes shorter, so that the right rudder 17 rotates counterclockwise from the straight traveling position as shown in FIG. At this time, the left shape memory alloy 2
3 does not cool down immediately even if the power supply is stopped.
During a certain period of time, the vehicle is rotated clockwise from the straight traveling position. Therefore, the right rudder 17 is temporarily rotated in a counterclockwise direction from the straight-ahead position, and the left rudder 19 is rotated in a clockwise direction from the straight-ahead position. As the 23 cools, the left spring 19 is rotated counterclockwise by the force of the left spring 24 and returns to the straight position, so that the ship turns right.

In this rudder device, when it is desired to turn to the opposite side from the state of turning right or left as described above, the heating of one of the shape memory alloys 21 or 23 is stopped and at the same time the other shape memory alloy is turned off. Since 23 or 21 can be heated, although the braking is temporarily applied, the traveling direction can be quickly changed as a whole.

When one of the shape memory alloys 21 or 23 is sufficiently cooled and then the other shape memory alloy 23 or 21 is heated, the traveling direction can be changed without the temporary braking. It can be carried out.

The right and left shape memory alloys 2 are intentionally used.
By heating both 1 and 23, the right rudder 17 can be deliberately braked while being rotated counterclockwise from the straight-ahead position and the left rudder 19 can be rotated clockwise from the straight-ahead position.

FIGS. 9 to 12 show a second embodiment of the present invention. Generally, there are three types of rudder of an airplane, an elevator (elevator), a rudder (rudder), and an aileron (aileron). This embodiment is an embodiment in which the present invention is applied to an aileron of a model radio control aircraft. is there. In this example,
On the trailing edge of the right wing 27 of the model airplane 26, a right wing 2
7 extends along the trailing edge of the right auxiliary wing shaft 28 (see FIG. 10)
Are rotatably supported, while a left auxiliary wing shaft 30 extending along the rear edge of the left main wing 29 is provided on the rear edge side of the left main wing 29.
(See FIG. 12) is rotatably supported.

As shown in FIGS. 10 and 11, a right auxiliary wing 31 (first rudder in this embodiment) and a central portion of a right arm 32 are fixed to the right auxiliary wing shaft 28.
A right shape memory alloy 35 (first shape memory alloy in the present embodiment) wound in a coil shape is interposed between the right main wing 27 and one end of the right arm 32, and the right main wing 27 and the right arm 32 are interposed. A right spring 36 (first biasing means in the present embodiment) composed of a tension coil spring made of a non-shape memory alloy material is interposed between the other end of the spring 32 and the other end. The right shape memory alloy 35 stores a short shape as shown in FIG. The right spring 36 urges the right auxiliary wing 31 upward via the right arm 32. Thus, when the right shape memory alloy 35 is cooled, the shape memory alloy 35 is expanded and deformed in a macroscopic manner, and the right auxiliary wing 3
1 is in a horizontal position as shown in FIG.

As shown in FIG. 12, a left auxiliary wing 33 (second rudder in this embodiment) and a central portion of a left arm 34 are fixed to the left auxiliary wing shaft 30. Between the left main wing 29 and one end of the left arm 34, a left shape memory alloy 37 (the second shape memory alloy in this embodiment) wound in a coil shape is interposed, and the left main wing 29 and the left arm 34 are interposed. A left spring 38 (a second biasing means in the present embodiment) composed of a tension coil spring made of a non-shape memory alloy material is interposed between the other end of the spring 34 and the other end. The left shape memory alloy 37 also stores the same short shape as the right shape memory alloy 35. The left spring 38 urges the left auxiliary wing 33 upward via the left arm 34 and the left auxiliary wing shaft 30. Thus, when the left shape memory alloy 37 is cooled, the shape memory alloy is elongated and deformed macroscopically, and the left auxiliary wing 33 is at a horizontal position as shown in FIG. The right and left shape memory alloys 37 are each supplied with electricity from a drive circuit (not shown).

Next, the operation of this embodiment will be described. To make the airplane 26 go straight, the right and left shape memory alloys 3
No current is supplied to any of the first and second shape memory alloys 35 and 37.
37 is in a state of being cooled. Thereby, both the right and left auxiliary wings 31, 33 are at the horizontal position.

Next, when it is desired to turn the airplane 26 to the left, power is supplied to the right shape memory alloy 35 from the drive circuit.
Then, the right shape memory alloy 35 is heated to a predetermined temperature range by the Joule heat, and returns to the shape stored in the shape memory alloy 35 and becomes shorter. As shown in FIG. From the position, together with the right arm 32 and the right auxiliary wing shaft 28, it rotates downward (in the first direction in the present invention) against the right spring 36 to be in a lowered state.
As a result, the lift acting on the right wing increases, and the aircraft leans to the left, and the airplane 26 turns left.

Next, when it is desired to turn the airplane 26 rightward from the state where the vehicle is turning left, the power supply to the right shape memory alloy 35 is stopped, and the power supply to the left shape memory alloy 37 is supplied from the drive circuit. I do. Then, the left shape memory alloy 37 is heated to a predetermined temperature range and returns to the shape stored in the shape memory alloy 37 and becomes shorter, so that the left auxiliary wing 33 is moved as shown by the dashed line position in FIG. From the horizontal position, the left arm 34 and the left auxiliary wing shaft 30 rotate downward against the left spring 38 (the second direction in the present invention, which is the same direction as the first direction) to be in a lowered state. . At this time, the right shape memory alloy 35 does not immediately cool down even when the energization is stopped, so that the right shape memory alloy 35 is in a lowered state for a certain time. For this reason, both the right auxiliary wing 31 and the left auxiliary wing 33 are temporarily lowered, the lift of both wings increases, and the airplane 26 attempts to ascend. However, thereafter, as the right shape memory alloy 35 cools, the right auxiliary wing 31 returns to the horizontal position due to the force of the right spring 36, so that the lift on the right wing side decreases, and the body leans to the right. The airplane 26 turns right.

Conversely, when it is desired to turn the airplane 26 to the left from the state of turning right, the left shape memory alloy 37 is used.
Is stopped, and power is supplied to the right shape memory alloy 35 from the drive circuit. Then, the right shape memory alloy 35 is heated, and returns to the shape stored in the shape memory alloy 35 and becomes shorter. As shown in FIG.
1 descends from the horizontal position together with the right arm 32 and the right auxiliary wing shaft 28 against the right spring 36. At this time, since the left shape memory alloy 37 does not immediately cool down even when the energization is stopped, the left shape memory alloy 37 is in a lowered state for a certain time. For this reason, both the right auxiliary wing 31 and the left auxiliary wing 33 are temporarily lowered, the lift of both wings increases, and the airplane 26 attempts to ascend. However, thereafter, as the left shape memory alloy 37 cools, the force of the left spring 38 causes
Since the left auxiliary wing 33 returns to the horizontal position, the lift on the left wing side decreases, so that the aircraft leans to the left and the airplane 26 turns left.

Here, conventionally, when the airplane 26 turns with the operation of the auxiliary wings, the gravitational component of the lift generally decreases, and the airframe starts to descend. Therefore,
It was necessary to increase the number of revolutions of the engine or the motor to increase the overall lift, or to maintain the horizontal flight state while correcting with the elevator. However, this rudder has a function to correct the descent of the aircraft during turning, although the timing is slightly shifted and the descent temporarily occurs.

That is, in the prior art, for example, when the aircraft is tilted in a left (right) turn and the altitude drops, when the rudder is turned in a hurry in the opposite direction, it is now tilted to the right (left) and the altitude further decreases. However, according to this rudder device, the left (right) turn to the right (left)
When switching back to turning, the lift of both wings increases once,
The descent of the aircraft can be suppressed. In addition, the right and left shape memory alloys 35 and 37 are intentionally heated at the same time, the left and right auxiliary wings 31 and 33 are simultaneously lowered, the lift of both wings can be increased, and the role of the elevator can be doubled. Such properties not only compensate for the responsiveness disadvantages of shape memory alloys, but also provide maneuverability suitable for a novice model airplane flying at relatively slow speeds.

In each of the above embodiments, the first and second (right and left) shape memory alloys are heated by energization. However, in the present invention, other shape memory alloys such as infrared and laser heating are used. The first and second shape memory alloys may be heated by some kind of heating method.

Further, in the present invention, the basic form and the form of deformation and shape recovery of the first and second shape memory alloys are not limited to those of the above-described embodiments.

Further, in each of the above embodiments, the first and second biasing means (right and left springs 22, 24, 36, 3
8) is a coil spring, but the first and second biasing means in the present invention include a spring of a type other than the coil spring,
Other types of springs, such as a spring using rubber elasticity made of an elastomer such as rubber, a spring using gas, or a unit other than a spring such as a permanent magnet may be used.

Although the above embodiment is an example in which the present invention is applied to a rudder of a ship and an auxiliary wing of an aircraft, the present invention is also applied to other types of rudder devices such as a rudder and an elevator of an aircraft. It is possible.

[0044]

As described above, the rudder device according to the present invention is driven by the shape memory alloy, can switch the rudder relatively quickly, change the traveling direction, etc., and reduce the size and weight. It is possible to obtain excellent effects such as the formation of

[Brief description of the drawings]

FIG. 1 is a front view showing an example of a conventional differential shape memory alloy actuator in which only one shape memory alloy is heated.

FIG. 2 is a front view showing a state in which both shape memory alloys are cooled in the conventional differential shape memory alloy actuator.

FIG. 3 is a time chart showing an operation of the conventional differential shape memory alloy actuator.

FIG. 4 is a front view showing a state in which a shape memory alloy is cooled in an example of a conventional monostable shape memory alloy actuator.

FIG. 5 is a front view showing a state in which the shape memory alloy is heated in the conventional monostable shape memory alloy actuator.

FIG. 6 is a plan view showing the first embodiment of the rudder device according to the present invention, in which both rudders are in a straight traveling position.

FIG. 7 is a plan view showing a state in which the right rudder is turned in the first embodiment.

FIG. 8 is an enlarged plan view showing the vicinity of a right rudder in the first embodiment.

FIG. 9 is a plan view showing a second embodiment of the rudder device according to the present invention.

FIG. 10 is a sectional view showing a state in which the right auxiliary wing is in a horizontal position in the second embodiment.

FIG. 11 is a sectional view showing a state in which a right auxiliary wing is lowered in the second embodiment.

FIG. 12 is a sectional view showing a state where the left auxiliary wing is in a horizontal position in the second embodiment.

[Explanation of symbols]

 14 Hull 17 Right rudder (first rudder) 19 Left rudder (second rudder) 21 Right shape memory alloy (first shape memory alloy) 22 Right spring (first biasing means) 23 Left shape memory alloy ( 24 Left spring (second biasing means) 26 Airplane 31 Right auxiliary wing (first rudder) 33 Left auxiliary wing (second rudder) 35 Right shape memory alloy (first shape) Memory alloy) 36 right spring (first biasing means) 37 left shape memory alloy (second shape memory alloy) 38 left spring (second biasing means)

Claims (7)

[Claims] A first rudder connected to the first and second rudder so as to move the first rudder in a predetermined first direction when a shape restoring force is generated; Shape memory alloy,
First urging means for urging the first rudder in a direction opposite to the first direction, and when a shape restoring force is generated, the second rudder is moved in a predetermined second direction. A second shape memory alloy linked to the second rudder, and second biasing means for biasing the second rudder in a direction opposite to the second direction; A rudder device configured to perform a symmetrical rudder operation when one rudder is moved in the first direction and when the second rudder is moved in a second direction. 2. The rudder device according to claim 1, wherein the first and second rudder perform a rudder action by acting on a fluid. 3. The rudder device according to claim 2, wherein said first and second rudders are rudder of a ship. 4. The aircraft according to claim 2, wherein the first rudder is a right aileron of the aircraft and the second rudder is a left aileron of the aircraft.
A rudder device as described. 5. The rudder device according to claim 2, wherein said first and second rudders are rudder of an aircraft. 6. The rudder device according to claim 2, wherein said first and second rudders are elevators of an aircraft. 7. The rudder device according to claim 1, wherein said first and second urging means are springs.