JPH0534480Y2 - - Google Patents

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a stopper device for an aircraft control system. In particular, the present invention provides a control system in which two different control surfaces are steered by steering one control member in two different directions, when the amount of steering in one direction of the control member exceeds a predetermined range. , relates to a stopper device that limits the amount of steering in other directions.

[Conventional technology]

A control member such as an aircraft control stick can be used to steer a control surface such as a stabilizer by steering in one direction, for example in the longitudinal direction, and to control a control surface such as an aileron by steering in another direction, for example in the lateral direction. do. In such a control system, for example, when the stabilizer is steered beyond a predetermined range, the steerable range of the aileron must be limited to a small value.

Conventionally, in order to limit the steering range of a certain control surface depending on conditions such as the speed of the aircraft, the raising and lowering of the landing gear, and the steering angle of other control surfaces, detection means such as sensors or switches for detecting these conditions have been provided. A configuration is adopted in which the stopper or limiter is operated electrically or hydraulically in response to a detection signal from the detection means.

This conventional configuration requires the detection means and the stopper or limiter to be placed apart and connected by electrical wiring, and also requires hydraulic piping when hydraulic means is used as the actuation means. However, there were problems in that the structure was relatively complex and the space required for installation was large. Furthermore, this conventional configuration also had the problem that it could not be arranged compactly near the control member.

[Problem that the invention aims to solve]

The present invention is a conventional control system stopper.
The object of the present invention is to solve the problem that the structure is relatively complicated, requires a large space for installation, and cannot be compactly arranged near the control member.

[Means to solve the problem]

In order to solve the above problems, in this invention,
The steering member is provided with a stopper means for limiting the steering range of the steering member in the first direction, and the stopper means is brought into an actuated position when the steering member is steered beyond a predetermined range in the second direction, so that the steering member The steering wheel is configured to prevent steering beyond a predetermined range in the first direction. That is, in the stopper device for an aircraft control system according to the present invention, the first control surface is steered by operating one control member in the first direction, and the second control surface is steered by operating the single control member in the second direction. This invention relates to a control system of an aircraft that has come to be operated in the first direction, and includes a stopper means for operation in the first direction, and the stopper means prevents the control member from being steered beyond a predetermined range in the first direction. and a non-operating position that does not restrict steering in the first direction, and is activated when the steering member is steered beyond a predetermined range in the second direction to move the stopper means to the operating position. Valve means are provided for. The stopper means has a hydraulic plunger whose tip is arranged to engage the control member at a predetermined position in the first direction, and a hydraulic chamber is formed behind the hydraulic plunger. The pressure causes the plunger to be pushed against the steering member and prevented from retracting. Further, the valve means communicates between the hydraulic pressure chamber and the reservoir in an openable and closable manner, and the valve means communicates with the hydraulic pressure chamber and the reservoir when the steering member is steered beyond a predetermined range in the second direction. and said reservoir, and the stop means is thereby fixed in the operative position.

[Effect]

In the above configuration of the present invention, the control member is the second
When the vehicle is steered in the direction beyond the predetermined range, the stopper means is actuated by the switching means,
Take up working position. Therefore, the stopper means prevents the steering member from being steered beyond the predetermined range in the first direction. Such a mechanism can be compactly incorporated in the vicinity of the control member.

〔Example〕

An embodiment in which the present invention is applied to a stabilizer and aileron control system will be described below with reference to the drawings.
Referring first to FIG. 1, on a support bracket 1 provided on the fuselage, a bell crank shaft 2 of a stabilizer control system is supported rotatably about a transverse axis 3 by a bearing brat 4. A crank arm 5 is provided at one end of the bell crankshaft 2, and this crank arm 5 is connected to a rod (not shown) of a stabilizer control system. The other end of the bell crankshaft 2 is connected to a control stick 7 via an arm 6.

The arm 6 has a lower end fixed to the bell crank shaft 2, and an upper end connected to the control stick 7 by a shaft 8 extending in the front-rear direction.
is rotatably coupled to the front and rear shafts 9. The control stick 7 has a yoke 7a extending downward from the position where it is connected to the arm 6, and this yoke 7a is connected to a rod (not shown) of an aileron control system.

Referring to FIGS. 2 to 4, the arm 6 is provided with plungers 10 and 11, one each on the upper and lower surfaces of the arm 6, which constitute a stopper. The control stick 7 has an engagement surface 12 formed above the arm 6 that engages with a stopper 10, and the stopper 11 is arranged to engage with a side surface 13 of the yoke 7a. As shown in FIG. 3, a switching valve 14 is provided at the lower rear surface of the arm 6.
A reservoir 15 is provided at the bottom of the entire surface.

FIG. 5 shows the overall structure of the stopper device, in which each of the plungers 10 and 11 is inserted into a housing 16, and is biased in the projecting direction by a spring 17 disposed within the housing 16.
A liquid chamber 18 is formed within the housing 16, and this liquid chamber 18 is connected to the switching valve 1 by a liquid passage 19 formed inside the arm 6, as shown in FIG.
4 and is connected to the reservoir 15. As shown in FIG. 5, the valve 14 has a valve housing 20 disposed within the liquid passageway 19.
A valve seat 20a is formed within the housing 20, and the liquid passage 19 passes through the valve seat 20a within the housing 20.

A valve member 21 having a tip end 21a that seats on a valve seat 20a is disposed within the valve housing 20, and the valve member 21 is urged by a spring 22 in a direction away from the valve seat 20a. The switching valve 14 further includes a valve actuation member 23 whose tip end 23 a protrudes from the valve housing 20 .
A spring 24 is provided between the valve actuating member 23 and the valve member 21.
is located. The reservoir 15 has a liquid chamber 15a.
One wall of the liquid chamber 15a is constituted by a diaphragm 25. The diaphragm 25 is urged toward the liquid chamber 15a by a spring 26.
A bleeder 27 is provided in the reservoir 15 and the liquid passage 19 as necessary.

In the configuration described above, the valve actuating member 23 of the switching valve 14 is arranged to face the locking surface 1a of the support bracket 1. Therefore, control stick 7
When the valve actuating member 23 is rotated rearward to raise the pitch and the amount of rotation exceeds a predetermined range, the valve actuating member 23 engages with the locking surface 1a of the support bracket 1. When the control stick 7 is further operated beyond the predetermined range, the valve actuating member 23 is pushed in and pushes the valve member 21 toward the valve seat 20a. Therefore, the tip end 21a of the valve member 21 is the valve seat 20a.
to block the liquid passage 19. By blocking this liquid passage 19, communication between the liquid chamber 18 behind the plungers 10 and 11 and the reservoir 15 is cut off.
The liquid chamber 18 becomes closed. In this state, control stick 7
When the control stick 7 is moved to the left or right to a predetermined range, the control stick 7
The locking surface 12 or the side surface 13 of the yoke 7a engages with the plunger 10 or 11, but since the liquid chamber 18 behind the plunger 10, 11 is in the closed state as described above, the plunger 10 or 11 is not in contact with the liquid. It is not possible to enter the chamber 18. Therefore, the plungers 10 and 11 come to act as a stopper for preventing further rotation of the control stick 7.

When the amount of rearward steering of the control stick 7 does not exceed the above-mentioned predetermined range, the switching valve 14 is kept open, so that the plungers 10 and 11 lock the control stick 7 by operating the control stick 7 in the left and right direction. When engaged with the surface 12 or the side surface 13 of the yoke 7a, the plungers 10, 11 are also pushed into the liquid chamber 18,
The liquid removed from the liquid chamber 18 is transferred to the reservoir 1 while displacing the diaphragm 25 in the reservoir 15.
5 into the liquid chamber 15a. Therefore, the amount of left and right operation of the control stick 7 is no longer limited.

This effect is shown in FIG. In other words, control stick 7
is moved in the longitudinal direction as shown by arrow A to steer the stabilizer. The aileron is also steered by moving left and right as shown by arrow B. control stick 7
is operated backward, the amount of steering exceeds the predetermined range, that is, the range indicated by A' in Fig.
When the switching valve 14 is moved to the range indicated by , the switching valve 14 is closed. At this time, the amount of left-right steering of the control stick 7 is limited to the range shown in FIG. 1 B'. When the steering amount behind the control stick 7 is in the range A', left and right steering can be performed beyond the range B'.
The maximum steering amount is limited to a range of, for example, B'' because the plungers 10 and 11 bottom out on the housing 16.

〔effect〕

As described above, in the present invention, the control member is provided with a stopper means for limiting the steering range of the control member in the first direction, and the stopper means is configured to prevent the control member from being steered beyond a predetermined range in the second direction. Since the stopper device is configured to be placed in the operating position when the steering member is turned to the operating position to prevent the steering member from being steered beyond a predetermined range in the first direction, the stopper device can be compactly incorporated near the steering member, and the structure is also simple. It can be done.

[Brief explanation of the drawing]

Fig. 1 is a perspective view of a control mechanism showing an embodiment of the present invention, Fig. 2 is a rear view of the arm portion of the control mechanism shown in Fig. 1, and Fig. 3 is a side view of the arm portion as seen from the right side. FIG. 4 is a sectional view of the arm portion, and FIG. 5 is a diagram showing the hydraulic circuit. 2...Bell crank shaft, 6...Arm, 7...
Control stick, 10, 11...plunger, 14...switching valve, 15...reservoir, 20a...valve seat,
21...Valve member.

Claims (1)

[Claims for Utility Model Registration] The first control surface is steered by operating one control member in the first direction, and the second control surface is steered by operating the one control member in the second direction.
A stopper device for a flight control system of an aircraft whose control surface is now steered, comprising a stopper means for operation in the first direction, the stopper means controlling the first direction of the control member.
can take an operating position that can prevent steering beyond a predetermined range of directions, and a non-actuating position that does not restrict steering of the steering member in the first direction;
The stopper means has a hydraulic plunger whose tip is disposed to engage the control member at a predetermined position in the first direction, and a hydraulic chamber is formed behind the hydraulic plunger so that the hydraulic The plunger is prevented from being pushed by the control member and retracted by the pressure in the pressure chamber, and includes a valve means for freely opening/closing communication between the hydraulic pressure chamber and the reservoir. Valve means closes communication between the hydraulic pressure chamber and the reservoir when the steering member is steered beyond a predetermined range in the second direction, and the stopper means is thereby fixed in the actuated position. A stopper device for an aircraft control system, characterized in that: