JPH0569895A - Hydraulic control device for aircraft - Google Patents

Abstract

PURPOSE:To contrive smallness in size and lightness in weight of a hydraulic control device for an aircraft. CONSTITUTION:A swivel rotary shaft 34 of a control surface 33 is provided on the center of blade thickness of a wing main unit 30, and an over center variable displacement oil hydraulic motor 1 is connected to this swivel rotary shaft to swivel the control surface up/down symmetrically. A tilt angle of a cam plate 5 of the oil hydraulic motor is controlled by a hydraulic cylinder device 4.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft hydraulic steering system using an over-center variable displacement hydraulic motor.

[0002]

2. Description of the Related Art A conventional aircraft hydraulic steering actuator is shown in FIG. 3, for example. In the figure, 20 is a hydraulic cylinder having two control systems (FC system and UTL system) for fail-safe, and has two independent cylinder chambers. Reference numerals 21a and 21b denote pistons fitted in the respective cylinder chambers of the hydraulic cylinder 20, and the base end of a common rod 22 provided with the pistons 21a and 21b is pivotally supported by the body structure 23. 24 is a bell crank connected to the tip of the hydraulic cylinder 20,
5, the tip portion constitutes the control surface 26.
Reference numeral 27 is a servo valve integrally provided with the hydraulic cylinder 20, and when the control valve 28 is moved by a lever 29, the hydraulic cylinder 20 linearly moves in the left-right direction in the drawing. Therefore, by linearly moving the hydraulic cylinder 20 via the servo valve 27, the bell crank 24 connected to the hydraulic cylinder 20 rotates about the swing rotation shaft 25, and the control surface 26 swings in the vertical direction. To do. That is, the linear motion of the hydraulic cylinder 20 is converted into the swing motion of the control surface 26 by the bell crank 24. Further, the servo valve 27 controls the positioning of the hydraulic cylinder 20, thereby controlling the swing angle of the control surface 26.

FIG. 4 shows the mounting state of the actuator. The hydraulic cylinder 20 is mounted inside the wing body 30, and the swinging rotary shaft 25 is provided with a control surface 26 composed of a bell crank 24 at an asymmetric position. The piston rod 22 is made to swing around the center. In the figure,
Reference numeral 31 is a rear spar of the blade main body 30, which is a member that partitions a fuel tank (not shown) and maintains the strength of the blade structure. Reference numeral 32 is a cover for covering a protruding portion of the actuator to the outside of the wing body 30.

[0004]

As described above, the conventional hydraulic steering system has a structure in which the linear motion of the hydraulic cylinder 20 is converted into the swing motion of the rudder surface 26 by the bell crank 24. The distance L between the swinging rotary shaft 25 and the rear girder 31 becomes long, and the mounting space for the hydraulic cylinder 20 becomes very large, which makes it difficult to reduce the size and weight of the actuator, and it is arranged inside the rear girder 31. There is a problem that the capacity of the fuel tank to be used cannot be increased and that the blade strength is disadvantageous. Further, the swinging rotary shaft 25 of the rudder face 26 must be provided in a vertically asymmetrical position with respect to the wing body 30, and the presence of the cover 32 that covers the protruding portion of the actuator to the outside of the wing body 30 reduces air resistance. Since it becomes large, the load resistance of the steering becomes asymmetrical. Therefore, there are problems that a bias force is applied at the neutral point of the rudder surface 26, and a special auxiliary control circuit is required to balance the load.

The present invention has been made in order to solve the above-mentioned problems, and aims to reduce the size and weight of the actuator, increase the degree of freedom in the design of the wing spar, and improve the aerodynamic performance and the weight of the airframe.
An object of the present invention is to provide an aircraft hydraulic steering system that brings good results in terms of airframe performance such as fuel tank capacity.

[0006]

In order to achieve the above-mentioned object, a hydraulic steering system for an aircraft according to the present invention is provided with an oscillating rotary shaft of a control surface at the wing thickness center of a wing body. Is connected to an over-center variable displacement hydraulic motor to vertically swing the control surface, and a hydraulic cylinder device for controlling the tilt angle of the swash plate of the hydraulic motor is provided.

[0007]

In the hydraulic steering system of the present invention, the control surface can be swung directly by using the over-center variable displacement hydraulic motor, and the actuator becomes small and lightweight. The control surface swings vertically symmetrically. The positioning of the hydraulic motor is controlled by controlling the tilt angle of the swash plate by the hydraulic cylinder device.

[0008]

1 is a block diagram showing an embodiment of the present invention. In the figure, reference numeral 1 is an over-center variable displacement hydraulic motor mounted inside the wing body 30, and its output shaft 2 is connected to a swing rotary shaft 34 of a control surface 33 via a speed reducer 3. The swinging rotary shaft 34 is provided at the center of the blade thickness of the blade main body 30, and one end portion of the rudder surface 33 formed vertically symmetrically is attached to the blade main body 3.
It is centered on 0. Reference numeral 4 is a hydraulic cylinder device that controls the tilt angle of the swash plate 5 of the hydraulic motor 1.

This hydraulic steering actuator is constructed as shown in FIG. In FIG. 2, 1 is a hydraulic motor, 3 is a speed reducer, 4 is a hydraulic cylinder device for swash plate tilt angle control, 5 is a swash plate of the hydraulic motor 1, and 33 is a control surface,
Further, 6 is a pressure line of the hydraulic motor 1, 7 is a tank, 8 is a control piston rod of the hydraulic cylinder device 4, and 9 is a servo valve of the hydraulic cylinder device 4, which is connected to the pilot line 10 of the pressure line 6 to control the pilot pressure. It is adapted to supply to the hydraulic cylinder device 4. 11 is a tank, 12
Is a controller, which is a position command signal a for the control surface 33.
And a control surface position detection signal b from a control surface position detector 13 attached to the speed reducer 3, a control surface speed detection signal c from a control surface speed detector 14, and a swash plate tilt of the hydraulic motor 1. The swash plate tilt angle detection signal d from the swash plate tilt angle detector 15 attached to the shaft is input to the controller 12, respectively, and the position command signal a and the control surface position detection signal are supplied in the controller 12. After comparing with b, a drive signal e proportional to the deviation is output to the servo valve 9, and the control surface 33 is feedback-controlled to a required position. In this case, the position of the control surface 33 is fed back to the controller 12 as a main loop, and the movement speed of the control surface 33 and the tilt angle of the swash plate 5 are fed back as a minor loop.

In this embodiment, since the control surface 33 is directly swung by the overcenter variable displacement hydraulic motor 1, the length L between the swinging rotary shaft 34 and the rear girder 31 can be shortened. Therefore, the mounting space for the hydraulic steering actuator is reduced. Therefore, the degree of freedom in designing the blade spars is increased, and the capacity of the fuel tank (not shown) arranged inside the rear spars 31 can be increased. Also,
Since the rudder surface 33 does not have to be formed of a bell crank or the like as in the conventional case, it can be formed symmetrically in the vertical direction, and as a result, there is no protruding portion of the hydraulic steering actuator to the outside of the wing body 30 and the wing body 30 and The control surface 33 can be formed smoothly. Therefore, the aircraft performance such as aerodynamic performance, aircraft weight, fuel tank capacity, etc. is significantly improved.

The operation of the hydraulic steering actuator will be described below. When the position command signal a for the control surface 33 is input to the controller 12, it is compared with the detection value b of the control surface position detector 13, and a drive signal e proportional to the deviation is output to the servo valve 9. Since the pilot pressure of the pressure line 6 of the hydraulic motor 1 is applied to the servo valve 9 through the pilot line 10,
A control flow of pilot pressure is supplied to the hydraulic cylinder device 4 by the servo valve 9 controlled by the controller 12, and the control piston rod 8 of the hydraulic cylinder device 4 is extended or contracted. In this way, the position control of the hydraulic cylinder device 4 corresponding to the position command signal a of the control surface 33 is performed, and the tilt angle of the swash plate 5 is controlled. Further, the + direction and the-direction of the tilt angle correspond to the movement direction of the control surface 33. The output torque of the hydraulic motor 1 is proportional to the product of the tangent of the pressure of the pressure line 6 and the tilt angle of the swash plate 5. Therefore,
The output torque can be controlled even if the pressure in the pressure line 6 is constant. When the position command signal a for the control surface 33 and the detection value b of the control surface position detector 13 match, the hydraulic pressure is adjusted at the position of the tilt angle of the swash plate 5 corresponding to the torque required to hold the control surface 33. The motor 1 stops.

Therefore, since only the flow rate of the pilot line 10 passes through the servo valve 9 used for controlling the positioning of the steering device, a small capacity servo valve can be used and the energy utilization efficiency of the hydraulic system is large. Improves width.

[0013]

As described above, according to the present invention, since the control surface can be directly swung by using the over-center variable displacement hydraulic motor, the hydraulic steering actuator can be reduced in size and weight. In addition to increasing the degree of freedom in designing the girder and increasing the capacity of the fuel tank, the rudder surface can be formed vertically symmetrically, and the wing body and the rudder surface can be formed smoothly, resulting in aerodynamic performance. And aircraft weight,
Airframe performance such as fuel tank capacity is significantly improved.

[Brief description of drawings]

FIG. 1 is a configuration diagram showing an embodiment of the present invention.

FIG. 2 is a hydraulic circuit diagram of a hydraulic steering actuator according to the present invention.

FIG. 3 is a configuration diagram of a conventional hydraulic steering system.

FIG. 4 is a view showing a mounting state of a conventional hydraulic steering device.

[Explanation of symbols]

 1 Over-center variable displacement hydraulic motor 2 Output shaft 3 Speed reducer 4 Hydraulic cylinder device 5 Swash plate 6 Pressure line 9 Servo valve 10 Pilot line 12 Controller 13 Control surface position detector 14 Control surface speed detector 15 Swash plate tilt angle detection Vessel 30 Wing body 31 Rear girder 33 Control surface 34 Swing rotation axis

Claims (1)

[Claims] 1. A wing body, a vertically symmetrical control surface whose one end is pivotally attached to a wing thickness center of the wing body by an oscillating rotary shaft, and a wing main body mounted inside the wing main body. An aircraft hydraulic steering system comprising: an overcenter variable displacement hydraulic motor connected to the hydraulic motor; and a hydraulic cylinder device that controls a tilt angle of a swash plate of the hydraulic motor.