JP2001001994A - Control device for aircraft - Google Patents

Abstract

PROBLEM TO BE SOLVED: To maintain a stable operability for an aircraft with a high elevation angle flight enabled. SOLUTION: This device is provided with an operation mode about a fuselage axis with an operation using a control stick 10 and an operation mode about a stability axis with a turn operation of a rotation shaft 11 provided on the control stick 10. During a normal elevation angle flight, a flight in the operation mode about the fuselage axis or the stability axis with the control stick 10 as usual is enabled. During a high elevation angle flight, a flight in the operation mode about the stability axis with the operation of the rotation shaft 11 independent of the operation mode about the fuselage axis is enabled, and a pilot can operate the rotation shaft 11 for a direct operation in the operation mode about the stability axis without considering a manipulated variable of the control stick 10, thereby enabling a stable control operation by the pilot.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flight control device for an aircraft, and more particularly to a flight control device for an aircraft capable of flying at a high angle of attack.

[0002]

2. Description of the Related Art An aircraft control device controls the attitude of an aircraft in accordance with a pilot's intention to operate, and as shown in FIG.
The roll operation is performed by tilting and standing in the left-right direction y, the pitch operation is performed by tilting and standing in the front-rear direction x, and the yaw operation is performed by operating the rudder pedal 102.

[0003] Taking the operation around the stable axis Xa of the aircraft by the control device as an example and referring to the conceptual diagram of the roll operation of the stable axis shown in FIG. 6, the pilot will perform the roll operation about the stable axis Xa (step S101). Then, the distribution amount between the operation amount of the control stick 101 and the operation amount of the rudder pedal 102 is determined based on the pilot's control feeling based on the flight speed and angle of attack of the own aircraft (step S102). Is rolled in the horizontal direction y (step S103), and the acceleration and posture applied to the body and the rate of change thereof are incorporated in order to enhance the stability of the body based on the roll operation amount. Corrected by the flight controller (step S
104), a control device for generating a moment about the body axis X based on a signal from the flight controller, for example, an aileron and a thrust changing mechanism is operated (step S105).

In parallel with this, based on the determination of the operation amount of the rudder pedal 102 in step S102, the rudder pedal 102 is operated, and the yaw operation is performed by the rudder pedal 102 (step S106). The flight controller incorporates the acceleration, attitude, change rate, and the like applied to the airframe (step S10).
7) The operation about the stable axis Xa is performed by operating a control device that generates a moment about the body axis Z, for example, a rudder and a thrust changing mechanism (step S1).
08).

[0005] Another operation around the stable axis Xa will be described with reference to a conceptual view of a stable axis roll operation shown in FIG.

Based on the intention of the pilot to roll around the stable axis Xa (step S111), the control stick 101 is tilted and raised in the left-right direction y to perform a roll operation with the control stick 101 (step S112), and the amount of operation Is distributed to a moment control signal about the body axis X and a moment control signal about the body axis Z according to the flight speed, angle of attack, and the like of the aircraft according to a control rule preset by the flight controller 103 based on S113) is performed.

The distributed moment control signal about the body axis X is corrected according to the acceleration and posture applied to the body and the rate of change thereof in order to enhance the stability of the body (step S114). Then, a control device for generating the moment, for example, an aileron and a thrust changing mechanism is operated (step S115).

At the same time, the moment control signal about the body axis Z is corrected in accordance with the acceleration and posture applied to the body and the rate of change thereof in order to enhance the stability of the body (step S116), and the moment control signal is rotated about the body axis Z. The operation around the stable axis Xa is performed by operating the control device that generates the moment (for example, the rudder and the thrust changing mechanism) (step S117).

[0009]

According to the above control device, the flight controller is preset in the flight controller based on the operation amount of the tilting and raising operation of the control stick and the operation of the rudder pedal, or the tilting and raising operation of the control stick. Based on the control law, it compensates according to the rate of change of its own aircraft's acceleration, attitude, etc., complements the pilot's sensing ability, activates the aileron, rudder, thrust change mechanism, etc., and performs roll operation around the stable axis Xa. ing.

However, in an aircraft capable of high-angle-of-attack flight motion as shown in FIG. 8, the stable axis Xa, which is the flight direction during normal angle-of-attack flight, and the body axis X direction substantially coincide with each other or extremely. On the other hand, when flying at high angles of attack, the stable axis X
a greatly deviates from the body axis X. Due to this deviation, the pilot's steering feeling during the normal angle of attack flight and the high angle of attack flight are greatly different. Makes it difficult to steer.

If the roll operation of the control stick is made to correspond to the roll operation around the stable axis Xa during a high angle of attack flight, the pilot loses the control means around the body axis X, and the pilot to the aircraft is lost. It is feared that the intended operation of the device will be hindered.

SUMMARY OF THE INVENTION Accordingly, an object of the present invention, which has been made in view of the above points, is to provide a pilot control device for an aircraft capable of ensuring a pilot's intended controllability in an aircraft capable of flying at a high angle of attack.

[0013]

According to a first aspect of the present invention, there is provided an aircraft control device including a control stick, a flight controller, and a control device for generating a moment about an airframe axis. The operation signal of the control stick is corrected in accordance with a control rule set in advance by the flight controller, and a control device that generates a moment about the body axis by the corrected operation signal is operated to perform a roll operation around the body. An operation mode around the body axis and a control for correcting an operation signal by the rotation operation of the control stick in accordance with a control rule preset by the flight controller, and generating a moment about the body axis with the corrected operation signal. And an operation mode around a stable axis for performing a roll operation around the stable axis by operating the device.

According to the first aspect of the present invention, since there are provided an operation mode around the body axis by operating the control stick and an operation mode around the stable axis by rotating the rotary shaft, for example, the stable axis in the flight direction is provided. At the time of normal angle-of-attack flight in which the body axis is approximately the same or very similar, flight in the operation mode around the body axis by the control stick becomes possible as before, while the stable axis and the body At the time of high angle-of-attack flight in which the axis greatly deviates, it becomes possible to fly in the operation mode around the stable axis by rotating the control stick,
The pilot does not need to consider the amount of control of the control stick,
By rotating the control stick, it is possible to operate directly in the operation mode around the stable axis, and even when there is a lot of transition between normal angle of attack flight and high angle of attack flight, the stability intended by the pilot Steering operation can be achieved.

According to a second aspect of the present invention, in the aircraft control device according to the first aspect, the control stick emits an operation signal in accordance with an operating force applied to the control stick in the left, right, front, rear, and rotational directions. It is a formula.

According to a second aspect of the present invention, the control stick is of a force type, and an operation mode around the body axis is controlled by an operating force applied to the control rod in the left-right and front-rear directions, and is applied in the rotation direction of the control stick. The operation in the operation mode around the stable axis is performed by the operation force.

According to a third aspect of the present invention, in the control device for an aircraft according to the second aspect, the control rod is operated in the rotation direction when the operation force in the rotation direction of the control rod is equal to or less than a predetermined operation force. A filter function that does not generate an operation signal by force is provided.

According to the third aspect of the present invention, since the operation signal is prevented from being transmitted when the rotation of the control stick is equal to or less than the predetermined operation force, an unnecessary stable shaft is not required when the pilot unconsciously rotates the control stick. The shift to the turning operation mode can be prevented beforehand.

According to a fourth aspect of the present invention, in the control device for an aircraft according to the first aspect, the control stick is a travel type which emits the operation signal in accordance with a moving operation amount of the control stick in the left, right, front, rear, and rotational directions. There is a feature.

According to a fourth aspect of the present invention, the control stick is of a travel type, and an operation mode around the body axis is controlled by a movement operation amount of the control stick in the left-right and front-rear directions. Accordingly, the operation in the operation mode around the stable axis is performed.

According to a fifth aspect of the present invention, in the control device for an aircraft according to the fourth aspect, when the rotation angle of the control stick is equal to or less than a predetermined angle, the control signal is based on the amount of movement operation in the rotation direction. A filter function that does not generate a noise is provided.

According to the fifth aspect of the present invention, since the operation signal is prevented from being transmitted when the rotation angle of the control stick is equal to or less than the predetermined angle, when the pilot unintentionally rotates the control stick, an unnecessary stable axis rotation is prevented. The transition to the operation mode can be prevented beforehand.

According to a sixth aspect of the present invention, in the control device for an aircraft according to the fourth or fifth aspect, the control stick is provided with an operation reaction force that resists the rotational operation force of the control stick. I do.

According to the invention of claim 6, by applying an operation reaction force that resists the rotation operation force of the control stick, when the rotation force is applied to the control stick by the pilot unconsciously, the rotation of the control stick is prevented. Thus, the unnecessary shift to the stable axis operation mode can be prevented beforehand.

[0025]

DESCRIPTION OF THE PREFERRED EMBODIMENTS (First Embodiment) Hereinafter, a first embodiment of the present invention will be described with reference to FIG.
This will be described with reference to a conceptual diagram of the stable axis roll operation shown in FIG. 2 and a flight operation mode area explanatory diagram shown in FIG.

In FIG. 1, reference numeral 10 denotes a control stick disposed on the body 1, which is a force (moment sensing) type, and which is operated in an operation mode around the body axis by operating the control stick 10. Is obtained. For example, an operation signal is generated from the control stick 10 by an operation force such as a moment or a pressing force generated by a pressing action on the control stick 10 in the left-right direction y, and the control signal is flown based on a preset control rule. The roll operation around the machine body axis X is performed after the correction by the controller 13.

On the other hand, an operation signal is generated from the control stick 10 by an operating force such as a pressing force or a moment generated by a pressing action on the control stick 10 from the front-rear direction x, and the operation signal is transmitted to a control law set in advance. Is corrected by the flight controller 13 on the basis of the pitch operation.

Further, near the upper end of the control rod 10 having excellent operability, there is provided a rotary shaft 11 for detecting an operating force acting in the direction of rotation of the control rod 10 around its axis.
Functions as a grip portion, and detects a rotation operation force to the rotation portion 11 to generate an operation signal, thereby obtaining an operation mode around a stable axis.

An operation signal is transmitted from the rotation shaft 11 to the flight controller 13 by the rotation operation force of the rotation shaft 11, and the operation signal is corrected based on a control law preset in the flight controller 13 to stabilize the flight controller 13. A roll operation around the axis Xa is performed. The operating force of the rotating shaft 11 is set to be proportional to the generated roll angular velocity about the stable axis Xa.

Further, when the pilot applies the operation force in the rotational direction to the rotary shaft 11 unconsciously, it is possible to prevent the operation mode from shifting to the operation mode around the stable axis, that is, the roll command about the stable axis Xa is issued. In order to prevent the transmission, the moment when the rotational operation force of the rotating shaft 11 does not reach a predetermined value or more, or when the control stick 10 exerts a predetermined moment or pressing force from the left-right direction y or the front-rear direction z. Is applied, a filter function using a limiter, a dead band, or the like is provided so that an operation signal is not transmitted from the rotary shaft 11 assuming that the pilot is performing a roll operation around the body axis X.

In addition, it is important for a pilot of this type that can fly at a high angle of attack that the pilot can quickly recognize his / her angle of attack without increasing the workload of the pilot. The angle of attack and airspeed of the aircraft are displayed on the helmet mounted display.

The flight controller 13 outputs an operation signal by a roll operation for pressing the control stick 10 in, for example, the left and right direction y and a yaw operation by depressing the rudder pedal 12, based on a preset control rule, for example, a flight speed or a flight speed. The corrected signal is transmitted to a control device that generates a moment about the body axis X and a control device that generates a moment about the body axis Z after correcting the angle of attack, the acceleration and posture applied to the body and the rate of change thereof, and the like. It is configured to be operated.

On the other hand, an operation signal transmitted in accordance with an operation amount such as a roll operation around the stable axis Xa by an operation force in the rotation direction on the rotation axis 11 is generated based on a control rule preset by the flight controller 13. A control device that corrects according to the flight speed, the angle of attack, the acceleration and attitude applied to the fuselage, and the rate of change thereof, and generates a moment about the fuselage axis X and a control device that generates a moment about the fuselage axis Z To the stable axis X
It is configured to execute a roll operation around a.

Next, the operation of this embodiment will be described with reference to the conceptual diagram of the operation of the stable shaft roll shown in FIG.

Based on the intention of the pilot to perform a roll operation around the body axis X (step S1), the pilot determines the amount of operation of the control stick 10 based on the pilot's operational feeling such as the flight speed and angle of attack of the pilot, and controls the pilot. By pressing the rod 10 in the left and right direction y and performing a roll operation (step S2), an operation mode around the body axis is obtained, and an operation signal based on the operation amount is transmitted by the flight controller 13 to enhance the stability of the body. Correction is made according to a control law incorporating the acceleration and posture applied to the body and the rate of change thereof (step S
3) Activate a control device that generates a moment about the body axis X based on the corrected signal from the flight controller 13, for example, an aileron and a thrust changing mechanism (step S4).

In parallel with this, or independently, based on the pilot's willingness to roll around the body axis Z (step S5), the pilot uses the rudder pedal 12 according to the maneuvering sensation of his own flight speed and angle of attack. The operation amount is determined, and the yaw operation is performed by depressing the rudder pedal 12 (step S6).

The operation signal based on the operation amount of the rudder pedal 12 is corrected by the flight controller 13 in accordance with a control rule incorporating acceleration, attitude, change rate, and the like applied to the body (step S7), and the corrected flight is performed. Controller 13
By operating a control device, such as a rudder and a thrust changing mechanism, which generates a moment about the fuselage Z-axis in response to a signal from the control unit (step S8), the control by the control rod 10 and the rudder pedal 12 is performed in the same manner as in the related art. .

On the other hand, based on the intention of the pilot to perform a roll operation about the stable axis Xa (step S9), a rotational force is applied to the rotary shaft 11 provided on the control stick 10 by the pilot's sense of control, thereby providing a stable shaft. A rotation operation mode is obtained, and the roll operation around the stable axis Xa is performed by operating the rotation shaft 11 in consideration of the operation force of the rotation shaft 11 (step S10).

An operation signal from the rotating shaft 11 based on the operating force of the rotating shaft 11 is applied to the flight controller 13 in accordance with a control law based on the flight speed, angle of attack, etc. of the own machine, in accordance with a roll operation around the stable axis Xa. To the moment control signal about the body axis X and the moment control signal about the body Z (step S11).

The distributed moment control signal about the fuselage axis X is corrected according to the acceleration and attitude applied to the fuselage and the rate of change thereof in order to enhance the stability of the fuselage (step S3). A control device, such as an aileron and a thrust changing mechanism, is operated to generate a moment about the body axis X corresponding to the roll operation about the stable axis Xa based on the signal corrected by 13 (step S4).

At the same time, the moment control signal about the body axis Z distributed in step S11 is corrected according to the acceleration and posture applied to the body and the rate of change thereof in order to enhance the stability of the body (step S7). The control device, such as a rudder and a thrust changing mechanism, is operated to generate a moment about the body axis Z corresponding to the roll operation about the stable axis Xa based on the signal corrected by the flight controller 13 (step S8). The stable axis Xa
A surrounding roll operation is performed.

Therefore, in addition to the control by the roll operation around the body axis X by the operation of the control stick 11 and the rudder pedal 12 as in the prior art, the stable axis X by the operation force on the rotary shaft 11
Roll operation around a can be performed.

Next, FIG. 3 is an explanatory view of a flight operation mode area showing a main applicable operation area. An operation mode area around the body axis by the control stick 10 and the rudder pedal 12 and a stable axis around the stable axis by the rotary shaft 11 are shown. The operation mode area will be described. In this operation mode area explanatory diagram, a circle indicates an adaptable area, and a cross indicates an inappropriate area.

In a flight region where the flight speed V is relatively high and the angle of attack α is relatively large, and the flight angle is high, the direction of the body axis X and the direction of the stable axis Xa, which is the flight direction of the body 1, are greatly different. While it is difficult to fly in the operation mode around the body axis using the control stick 11 and the rudder pedal 12, this flight region is suitable for flight steering in the operation mode around the stable axis by the rotational operation force on the rotating shaft 11.

In a normal angle-of-attack flight area where the flight speed V is relatively high and the angle of attack α is relatively small, although the flight is at a high speed, the direction of the body axis X and the direction of the stable axis Xa, which is the flight direction, substantially coincide with each other. Since it is very similar, it is suitable for flight control in the conventional operation mode around the body axis using the control rod 11 and the rudder pedal 12, but in this flight region, flight control in the operation mode around the stable axis for operating the rotation axis 11 It does not require.

In a flight area where the flight speed V is relatively low and the angle of attack α is relatively large and the angle of attack is relatively large, although the body axis X and the direction of the stable axis Xa, which is the flight direction, are different, since the flight is low speed, In this flight region, the flight control in the operation mode around the stable axis by the operation of the rotating shaft 11 is also possible.

In a normal angle-of-attack flight region where the flight speed V is relatively low and the angle of attack α is relatively small, the flight is at a low speed and the direction of the body axis X and the direction of the stable axis Xa, which is the flight direction, substantially coincide with each other. Since it is very similar, it is suitable for flight control in the operation mode around the body axis using the control rod 11 and the rudder pedal 12 as in the related art, while in this flight region, the operation mode around the stable axis for operating the rotation axis 11 It does not require a flight maneuver.

According to the embodiment described above, in an aircraft capable of high-angle-of-attack flight motion, a normal angle-of-attack flight in which the direction of the stable axis Xa, which is the flight direction, and the direction of the body axis X are substantially the same or extremely approximate. In the case of the control stick 10
And a flight in the operation mode around the body axis by the rudder pedal 12 and the like, and at the time of high angle of attack flight in which the stable axis Xa, which is the flight direction, and the body axis X direction are largely different, the rotation operation of the rotation axis 11 is performed. Flight maneuver in the operation mode around the stable axis becomes possible.

Further, the pilot does not need to consider the operation amounts of the control stick 10 and the rudder pedal 12, and
1 makes it possible to directly operate in the operation mode around the stable axis, and even when a lot of transitions between the normal angle-of-attack flight and the high angle-of-attack flight occur, the pilot can stably operate. Is easily provided.

(Second Embodiment) Hereinafter, a second embodiment of the present invention will be described with reference to the schematic explanatory diagram of the operating device shown in FIG. 4 and the conceptual diagram of the stable shaft roll operation shown in FIG.

The present embodiment is characterized by a travel type in which the control stick 20 is operated by tilting and standing in the left and right direction y and tilting and standing in the front and rear direction x. Since the configuration is the same as that of the first embodiment, different portions will be mainly described.

The operation stick 20 is tilted in the left-right direction y and the front-rear direction x to obtain an operation mode about the body axis, and the operation stick is tilted in the left-right direction y and moved. According to the quantity, the operation signal is
In the same manner as in the embodiment, a roll operation around the body axis X is performed based on a preset control rule of the flight controller 13, while an operation signal based on a movement operation amount that tilts and erects the control stick 20 in the front-rear direction x. The pitch operation is performed.

Further, the control rod 20 is provided with a rotary shaft 21 corresponding to the rotary shaft 11 of the first embodiment in a rotational direction r about a rotary axis substantially parallel to the extending direction of the control rod 20. It is movably provided, and an operation mode around the stable axis is obtained by a moving operation amount by which the rotary shaft 21 rotates. Is performed, and the moving operation amount of the rotating shaft 21 is configured to be proportional to the generated roll angular velocity about the stable axis Xa.

Further, in the operation mode flight around the body axis rotation at the time of the normal attack angle or the like, the pilot unconsciously turns the rotation axis 2.
In order to prevent the issuance of a roll command about the stable axis Xa when the rotary shaft 1 is rotated, when the rotation angle of the rotary shaft 21 does not reach a predetermined angle or more,
A filter function is provided so that a roll command about the stable axis Xa does not occur when is tilted more than a predetermined amount in the left-right direction y or the front-back direction x.

This filter function can be constituted by a limiter or a dead band as in the first embodiment. In addition, since the control stick 10 swings in the left-right direction y and the front-back direction x, the rotational force acting on the rotating shaft 21 to suppress the rotation of the rotating shaft 21 gripped with the swinging operation. It is preferable that an operation reaction force opposing the above is added to limit the operation amount.

The flight controller 13 outputs an operation signal generated by the roll operation for tilting and raising the control stick 20 in, for example, the left-right direction y and the pitch operation for tilting and raising the control stick 20 in the front-rear direction x. In the same manner as in the first embodiment, in accordance with the control rules of the flight controller 13, the flight speed, the angle of attack, the acceleration applied to the body, the attitude, the rate of change thereof, and the like are corrected, and the moment about the body axis X is calculated by the corrected signal. It is configured to operate a control device that generates the torque, a control device that generates a moment about the body axis Z, and the like.

On the other hand, the stable axis Xa due to the rotation of the rotary shaft 21
An operation signal based on an operation amount such as a roll operation around the vehicle is corrected in accordance with a flight speed, an angle of attack, an acceleration applied to the vehicle, an attitude and a rate of change thereof according to a control rule of the flight controller 13, and the body axis X is corrected by the corrected signal. A control device for generating a moment about the vehicle body, a control device for generating a moment about the body axis Z, and the like are operated to execute a roll operation about the stable axis Xa.

In the roll operation or the pitch operation, the first embodiment executes the control stick 10 by operating force from the left-right direction y or the front-rear direction x, whereas the present embodiment moves the control stick 20 to the left. The operation is the same as that of the first embodiment except that it is executed by tilting in the y-direction or in the front-rear direction x, so that the description of the operation and the control by the flight controller 13 is omitted.

In this embodiment, as in the first embodiment, during normal flight at an angle of attack, a flight in the operation mode around the body axis using the control stick 20 and the rudder pedal 12 as in the prior art is performed. During flight at a high angle of attack, it becomes possible to perform flight maneuvering in an operation mode around a stable axis by rotating the rotating shaft 21, and it is necessary to consider the operation amounts of the control stick 20 and the rudder pedal 12. Instead, by rotating the rotating shaft 21, the operation in the operation mode about the stable axis can be directly performed, and a stable maneuvering operation by the pilot in the normal angle of attack flight and the high angle of attack flight can be provided.

In the first embodiment, the rotating shaft 1
Although the operation signal is generated by the operation force in the rotation direction acting on 1, the rotation shaft can be rotated similarly to the second embodiment, and the operation signal can be generated by the rotation amount. It is.

[0061]

According to the aircraft control apparatus of the present invention described above, the operation mode around the body axis by the operation of the control stick and the operation mode around the stable axis by the operation force in the rotation direction of the control stick or the rotation operation amount. Therefore, for example, at the time of normal elevation flight, it becomes possible to fly in the operation mode around the fuselage axis or the stable axis using the same control column as before, while at the time of high elevation flight, the operability is improved. By applying the operation force in the rotation direction of the control stick or by performing the rotation operation, it is possible to fly in the operation mode around the stable axis separated from the operation mode around the body axis, and the pilot considers the operation amount of the control stick. Operation in the direction of rotation without necessity allows operation in the operation mode directly around the stable axis, and there are many transitions between normal and high angle of attack flights. Oite also stable steering operation is easily brought about by the pilot.

[Brief description of the drawings]

FIG. 1 is a schematic explanatory view of an operating device for explaining a first embodiment of an aircraft operating device according to the present invention.

FIG. 2 is a conceptual diagram of a stable shaft roll operation.

FIG. 3 is also an explanatory view of a flight operation mode area.

FIG. 4 is a schematic explanatory view of an operating device for explaining a second embodiment of the aircraft operating device according to the present invention.

FIG. 5 is a schematic explanatory view of a conventional operation device.

FIG. 6 is a conceptual diagram of a stable shaft roll operation.

FIG. 7 is a conceptual diagram of another stable shaft roll operation.

FIG. 8 is an explanatory diagram of a stable axis, a body axis, and the like of an aircraft capable of performing a high angle of flight flight.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Airframe 10 Control stick 11 Rotation axis 12 Rudder pedal 20 Control axis 21 Rotation axis X Aircraft axis Xa Stable axis Z Aircraft axis

Claims (6)

[Claims] 1. A control stick, a flight controller, and a control device for generating a moment about an aircraft body axis, wherein the control signal of the control stick is corrected according to a control rule preset by the flight controller, Activating the control device that generates the moment about the body axis based on the corrected operation signal, and operating the control mode about the body axis for performing a roll operation around the body, and controlling the flight by operating the control signal by rotating the control stick. The operation mode around the stable axis for performing a roll operation around the stable axis by activating a control device that generates a moment about the aircraft body axis by the corrected operation signal by performing a correction according to a control law set in advance by a device. A flight control device for an aircraft, comprising: 2. The aircraft control device according to claim 1, wherein the control stick is of a force type that emits an operation signal in accordance with an operation force applied in the left, right, front, rear, and rotation directions. 3. The control stick is provided with a filter function that does not generate an operation signal due to the operation force in the rotation direction when the operation force in the rotation direction of the control stick is equal to or less than a predetermined operation force. Claim 2
An aircraft control device according to claim 1. 4. The aircraft control device according to claim 1, wherein the control stick is a travel type that issues the operation signal in accordance with the amount of movement of the control stick in the left, right, front, rear, and rotational directions. 5. The control stick according to claim 1, further comprising a filter function that does not generate an operation signal based on the amount of movement in the rotation direction when the rotation angle of the control stick is equal to or less than a predetermined angle. An aircraft control device according to claim 4. 6. The aircraft control device according to claim 4, wherein an operation reaction force against the rotation operation force of the control stick is applied to the control stick.