JP3448240B2 - Aircraft control system - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft maneuvering system, which is based on human-powered maneuvering and uses an electric or hydraulic actuator together to assist the manipulating force of a pilot.
The system is designed to obtain the necessary steering force to reduce the weight and cost of the aircraft control system.

[0002]

2. Description of the Related Art FIG. 3 is a control system diagram of a conventional human power control system. 41 is a control column operated by a pilot, 42 is a rod, and 42a, 42b, 42
The control column 41 has one end 42a.
, And the other end is connected to 42b. The central portion of the rod 42b is connected to the fixed side, the other end is connected to the rod 42c, the other end of the rod 42c is connected to the control surface 43, and the movement of the control column 41 is transmitted to the control surface.

When the pilot operates the control column 41, the input is transmitted from the control column 41 to the control surface 43 by the rods 42a, 42b and 42c. Although such a human-powered maneuvering system can be made lightweight and low in cost due to the simplicity of the system, the manipulating force required by the pilot increases with an increase in the size and speed of the machine, and the manpower cannot be steered only by manpower. Therefore, there is an aircraft that employs the servo tab system shown in FIG. 4 to reduce the pilot operation force.

FIG. 4 is a control system diagram of a conventional servo tab system. In the figure, 51 is a control column, 52
Is a rod whose one end is connected to the control column 51. Reference numeral 53 is a servo tab, and 54 is a control surface. The other end of the rod 52 is connected to the servo tab 53.

In the servo tab system having the above structure, the input from the control column 51 is transmitted to the servo tab 53 by the rod 52. By steering the servo tab 53, aerodynamic force acts on the tab control surface 54, and the control surface 54 is steered using this aerodynamic force. Power is reduced. Since this servo tab system has a system configuration that is not much different from the human-powered steering system described in FIG. 3, it is expected to be light in weight and low in cost. However, if aerodynamic force does not work on the control surface such as at stall, steering is impossible turn into. In the servo tab method, the tab is manually steered and the rudder surface is moved by the aerodynamic force acting on the tab. Lightweight and low cost can be expected, but the steering ability is affected by the airflow state around the tab.

In the system shown in FIG. 3 , as described above, the operating force required by the pilot increases with an increase in the size and speed of the body, and gradually it becomes impossible to steer with only human power. Therefore, in order to reduce the pilot operation force, a servo tab system is adopted for small and medium-sized aircraft, and a maneuvering system using hydraulic pressure is employed for large aircraft such as jet transport aircraft.

FIG. 5 is a control system diagram of a conventional hydraulic type mechanical control system. In the figure, 61 is a control column,
62 is a rod, one end of 62a is connected to the control column 61, and the other end is connected to 62b. One end of the rod 62b is rotatably connected to the fixed side, and the rods 62c and 64 are directly connected to each other. Rod 62
c is connected to the hydraulic actuator 63, and the rod 64 is connected to the artificial sensation device 65. The hydraulic actuator 63 is further connected to the control surface 64 and configured to drive the control surface 64.

In the hydraulic maneuvering system having the above structure,
The input from the control column 61 is the rod 62a,
It is transmitted to the hydraulic actuator 63 by 62b and 62c, and the hydraulic actuator 63 drives the control surface 64. Therefore, unlike the servo tab system, the steering ability is not affected by the air flow condition, but the system becomes complicated due to the equipment of the hydraulic actuator 63 and the related hydraulic system, and the weight and cost increase. Further, since the aerodynamic load on the control surface is not directly transmitted to the pilot, it is necessary to equip a device that artificially gives a pilot steering feel, that is, an artificial sensation device 65.

[0009]

As described above, in the human-powered maneuvering method described with reference to FIG. 3 , the system is simplified, and the weight and cost are reduced. However, the size of the body is increased and the speed is increased. As the pilot goes on, the operating power of the pilot also increases, which imposes a heavy burden on the pilot.

[0010] In addition, in Sabotabu method described in FIG. 4,
It is expected to be lightweight and low in cost as in the case of the human-powered steering system, but if the aerodynamic force does not act on the rudder surface, the maneuvering becomes impossible, and the maneuvering ability is easily affected by the airflow state around the tab.

Furthermore, in the hydraulic mechanical power steering system described with reference to FIG. 5 , the hydraulic actuator and the related hydraulic system are complicated, the weight of the device is large, and the cost is high. Further, since the aerodynamic load on the control surface is not directly transmitted to the pilot, it is necessary to equip an artificial sensory device for giving the pilot a steering feeling.

Therefore, the present invention simplifies the system without adopting a complicated hydraulic system, and assists the pilot's operating force by using an actuator based on the human-powered steering system or the servo tab system. It is an object of the present invention to provide an aircraft control system capable of accurately obtaining a necessary steering force.

[0013]

The present invention provides the following means (1) to ( 2 ) for solving the above-mentioned problems.

(1) In the aircraft control system, the operating force of the control column by the pilot is transmitted to the servo tab on the control surface to steer the servo tab and the aerodynamic force acting on the control surface steers the control surface. A displacement sensor mounted on a column for detecting the displacement of the control column, a steering angle sensor for detecting the angle of the control surface, an actuator for rotationally driving the control surface, and detection of the displacement sensor and the control sensor. A control of an aircraft, comprising a controller that takes in a signal, compares the two signals, and when the angle of the control surface is insufficient, controls the actuator to drive the actuator to compensate for the insufficient angle. system.

(2) In the aircraft control system, the pilot column control force is transmitted to the servo tab on the control surface to steer the servo tab, and the control surface is steered by the aerodynamic force acting on the control surface. An auxiliary tab is provided on the surface, an actuator for rotationally driving the auxiliary tab, a displacement sensor attached to the control column for detecting the displacement of the control column, and a steering angle sensor for detecting the angle of the control surface If, before Symbol captures a detection signal of the displacement sensor and the steering angle sensor, controls so if the angle of the control surface by comparing the two signals is insufficient compensate for angle of shortage driving the actuator An aircraft control system, comprising: a controller.

In (1) of the present invention, based on the servo tab system, an actuator for driving the control surface is added,
The pilot stroke of the control column is input to the controller from the displacement sensor, and the steering angle is input to the controller from the steering angle sensor. When the controller compares the signals from both sensors and determines that the desired steering angle cannot be obtained because the aerodynamic force acting on the servo tabs is insufficient and the steering angle is insufficient, the actuator is driven and the steering angle is insufficient. Control to assist minutes. (1) of the present invention is lighter than the maneuvering method,
It is a low-cost system.

In the item (2) of the present invention, an auxiliary tab is provided on the basis of the servo tab system, and this is driven by an actuator for driving the tab. In this system, the pilot stroke of the control column is input from the displacement sensor and the steering angle is input to the controller from the steering angle sensor, and the controller compares the signals from both sensors and the aerodynamic force generated by the servo tab for driving the control surface is insufficient. However, if it is determined that the desired steering angle cannot be obtained,
The actuator is driven, the auxiliary tab is steered to add a steering angle corresponding to the shortage, and control is performed to assist the shortage of aerodynamic force. Also in (2) of the present invention, the system is lighter in weight and lower in cost than the maneuvering method.

[0018]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will be specifically described below with reference to the drawings. FIG. 1 is a configuration diagram of an aircraft control system according to a first embodiment of the present invention. In the figure, reference numeral 1 is a control column operated by a pilot, and 2 is a rod, one end of which is connected to the control column 1 and the other end of which is connected to the rod 9a. Three
Is a servo tab, the servo tab 3 is connected to the rod 9b, and the rod 9b is connected to the rod 9a. The other end of the rod 9a is connected to the rod 2, and the central portion is connected to the fixed side. Reference numeral 4 denotes a displacement sensor attached to the control column 1 for detecting the displacement of the control column 1, that is, the pilot stroke. Reference numeral 5 denotes a rudder angle sensor, which detects the angle of the rudder surface 8. Reference numeral 7 denotes a control surface drive actuator, which rotates the control surface 8.

Reference numeral 6 denotes a controller, which is a displacement sensor 4,
Each signal of the steering angle sensor 5 is input to control the drive of the control surface drive actuator 7 as described later.

The control system of the first embodiment having the above-mentioned structure is based on the servo tab system. When the pilot operates the control column 1, the operation force is transmitted to the rod 2 and the movement of the rod 2 is transmitted to the rod 9.
It is transmitted to the servo tab 3 via a and 9b, and the servo tab 3
To steer together with the aerodynamic force applied to the control surface 8. At this time, the pilot stroke is measured by the displacement sensor 4, and the angle of the control surface 8 driven by the servo tab 3 is measured by the steering angle sensor 5.
Respectively, and the detection signals are input to the controller 6.

The controller 6 compares the two, and when the rudder angle is insufficient with respect to the pilot stroke, a signal for rotating the rudder surface drive actuator 7 for a predetermined amount is output, and the shortage is output. compensate. The controller 6 previously holds characteristic data of the optimum rotation angle of the control surface 8 for the pilot stroke, compares the input pilot stroke with the steering angle to determine whether or not it is appropriate, and When the corner is insufficient, the actuator is driven.

According to the control system of the first embodiment described above, the following effects can be obtained.

(1) In the conventional servo tab system shown in FIG. 4 , since the aerodynamic force acting on the tab is used to drive the control surface,
Steering ability is affected by the airflow around the tabs. In the first embodiment of the present invention, when the aerodynamic force acting on the tab 3 is insufficient and the desired steering angle cannot be obtained, the control surface drive actuator 7 is operated to compensate for the insufficient aerodynamic force and You can take a corner.

(2) The controller 6 compares the input pilot stroke with the steering angle, and when the steering angle is insufficient with respect to the pilot stroke, the controller 6 drives the control surface drive actuator 7 to determine the shortage. In order to compensate for this, the pilot stroke and rudder angle are 1
Corresponds to one.

(3) Although any actuator may be used for driving the control surface, when an electric actuator is used, a complicated hydraulic system is not required, and a human-powered steering system having a simple structure is possible. Therefore, the weight of the control system is reduced, and the cost can be reduced.

FIG. 2 is a configuration diagram of an aircraft control system according to a second embodiment of the present invention. In the figure, 1 is a control column, 2 is a rod connecting to the control column 1, and 3 is a servo tab, which is connected to a rod 19b. The rod 19b is connected to the rod 19a, the other end of the rod 19a is connected to the rod 2, and the central portion thereof is connected to the fixed side. A displacement sensor 4 detects the displacement of the control column 1, that is, the pilot stroke. Reference numeral 5 denotes a rudder angle sensor, which detects the angle of the rudder surface 8. Reference numeral 9 is a rudder face, and 17 is a tab drive actuator, which rotates the trim tab 18. Reference numeral 16 denotes a controller, which inputs detection signals from the displacement sensor 4 and the steering angle sensor 5, rotates the tab drive actuator 17, and steers the trim tab 17.

The operation system of the second embodiment having the above-mentioned structure is based on the servo tab system, and when the pilot operates the control column 1, the operation force thereof steers the servo tab 3 via the rod 2 and the rods 19a and 19b. Then, the steering is performed together with the aerodynamic force acting on the control surface 9. At this time,
The pilot stroke is detected by the displacement sensor 4, and the angle of the control surface is detected by the steering angle sensor 5, and the detection signals are input to the controller 16.

The controller 16 compares the two, and when the steering angle is insufficient for the pilot stroke,
A signal for performing a predetermined amount of rotation is output to the tab driving actuator 17, and the tab for assisting the pilot operating force, that is, the trim tab 18 is driven by the actuator 17 to be used for the steering surface steering, and the steering surface driving generated by the servo tab 3 Make up for the lack of aerodynamic power. The controller 16 has a pilot
It has characteristic data of the rotation angle of the control surface 9 that is appropriate for the stroke, compares the input pilot stroke with the steering angle to determine whether it is appropriate, and when the steering angle is insufficient. Controls the actuator 17.

According to the control system of the second embodiment described above, the following effects can be obtained.

(1) In the conventional servo tab system shown in FIG. 4 , since the aerodynamic force acting on the tab is used to drive the control surface,
Steering ability is affected by the airflow around the tabs. According to the second embodiment of the present invention, when the aerodynamic force acting on the servo tab is insufficient and the desired steering angle cannot be obtained, the tab tab actuator 17 drives the trim tab 18 for assisting the pilot operation force to steer the steering wheel. A desired rudder angle can be achieved by compensating for the lack of aerodynamic force for surface drive.

(2) The controller 16 compares the input pilot stroke with the rudder angle, and when the rudder angle is insufficient with respect to the pilot stroke, the insufficient portion is driven by the trim tab 18 for assisting the pilot operating force. In order to make up for the shortage, the pilot stroke and rudder angle correspond to each other in a one-to-one manner, similar to the manual operation method.

(3) Although any actuator may be used for driving the tab, when an electric actuator is used, a complicated hydraulic system is not required and a human-powered steering system with a simple structure is possible. Therefore, the weight of the control system is reduced, and the cost can be reduced.

[0033]

The aircraft control system of the present invention is
(1) Attached to the control column in an aircraft control system that transmits the operation force of the control column by the pilot to the servo tab on the control surface to steer the servo tab and steer the control surface with the aerodynamic force acting on the control surface A displacement sensor that detects the displacement of the control column, a steering angle sensor that detects the angle of the control surface, an actuator that rotationally drives the control surface, and a detection signal of the displacement sensor and the control sensor A controller for comparing the two signals and driving the actuator to compensate for the insufficient angle when the angle of the control surface is insufficient is provided. With such a system, based on the servo tab system, the aerodynamic force acting on the servo tab is insufficient to assist the shortage when the desired steering angle cannot be obtained, and it is lighter and lower in cost than the maneuvering system. It can be a steering system.

According to a second aspect of the present invention, in a servo tab type aircraft control system, an auxiliary tab is provided on the control surface, and an actuator for rotationally driving the auxiliary tab is provided.
Attached to the control column, a displacement sensor for detecting the displacement of the control column, and the steering angle sensor for detecting an angle of the control surface, before Symbol captures a detection signal of the displacement sensor and the steering angle sensor, both signals In comparison, when the angle of the control surface is insufficient, the controller is driven to drive the actuator so as to compensate for the insufficient angle. With such a system,
Based on the servo tab method, it is possible to assist the lack of aerodynamic force generated by the servo tab when the aerodynamic force for driving the control surface is insufficient and the desired steering angle cannot be obtained, by steering the auxiliary tab. it can. In addition, it is possible to make the steering system lighter in weight and lower in cost than the maneuvering method.

[Brief description of drawings]

FIG. 1 is a configuration diagram of an aircraft control system according to a first embodiment of the present invention.

FIG. 2 is a configuration diagram of an aircraft control system according to a second embodiment of the present invention.

FIG. 3 is a configuration diagram of a conventional human-powered maneuvering system for an aircraft.

FIG. 4 is a configuration diagram of a conventional servo tab system.

FIG. 5 is a configuration diagram of a conventional hydraulic maneuvering system.

[Explanation of symbols]

1 control column 2, 9a, 9b, 19a, 19b rod 3 servo tab 4 displacement sensor 5 rudder angle sensor 6, 1 6 controller 7 rudder surface drive actuator 8 rudder surface 1 7 tab drive actuator 18 trim tab

─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Hajime Muramoto 10 Oe-cho, Minato-ku, Nagoya City Mitsubishi Heavy Industries, Ltd., Nagoya Aerospace Systems Works (72) Inventor Tetsuo Hayama 10 Oe-cho, Minato-ku, Nagoya Mitsubishi Heavy Industries Nagoya Aerospace Systems Mfg. Co., Ltd. (56) Reference Patent 153502 (JP, C1) US Patent 2325548 (US, A) (58) Fields investigated (Int.Cl. ⁷ , DB name) B64C 9/10 B64C 13 / 38-13/50

Claims (2)

(57) [Claims] 1. A control system for an aircraft, wherein an operation force of a control column by a pilot is transmitted to a servo tab on a control surface to steer the servo tab, and an aerodynamic force acting on the control surface steers the control surface. A displacement sensor for detecting the displacement of the control column, a steering angle sensor for detecting the angle of the control surface, an actuator for rotationally driving the control surface, and detection signals for the displacement sensor and the control sensor. A control system for an aircraft, comprising: a controller that takes in the signals, compares the two signals, and when the angle of the control surface is insufficient, controls the actuator so as to compensate for the insufficient angle. . 2. A control system of an aircraft, wherein an operation force of a control column by a pilot is transmitted to a servo tab of a control surface to steer the servo tab, and an aerodynamic force acting on the control surface steers the control surface. the auxiliary tab provided on an actuator for rotating the same auxiliary tab, attached to the control column, a displacement sensor for detecting the displacement of the control column, and the steering angle sensor for detecting an angle of the control surface , before Symbol captures a detection signal of the displacement sensor and the steering angle sensor, the controller when the angle of the control surface by comparing the two signals is insufficient to control to compensate for the angle of the shortage driving the actuator An aircraft control system comprising: