JPS6044198B2 - Rudder pedal position adjustment device - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a rudder pedal position adjustment device, which is capable of being incorporated in a limited space below an instrument panel and capable of simultaneously adjusting the front and rear positions of both left end rudder pedals. This invention relates to a rudder pedal position adjustment device.

Generally, directional control of an aircraft is performed by a pilot operating a rudder pedal with his/her foot.

It is desirable that the rudder pedal be located at a position where the pilot can comfortably press it with his/her foot when seated in the seat.

However, the length of each pilot's legs varies depending on their physique, so in order to improve the operability of the rudder pedals for a particular pilot, it is necessary to adjust the distance between the seat and the rudder pedals by adjusting the distance between the seat and the rudder pedals. Must be adjusted according to the length of the foot. For this adjustment, the seat may be made to be movable back and forth, or the rudder pedal may be made to be movable back and forth. A conventional example in which the rudder pedal can be moved back and forth uses a stopper and a rack to adjust the relative mounting angle between the pedal hanger and the arm that transmits the output to the rudder.

This involves attaching a rudder pedal to the free end of a pedal hanger that can swing around a pivot, placing a rudder drive shaft coaxially with the pivot, and extending an arm from this drive shaft. A J-spring-loaded pawl is provided, and this pawl is adapted to engage with the teeth of a rack fixed to the pedal hanger side. In such a device, when adjusting the position of the rudder pedal, the handle is used to pull a wire, the tip of the wire moves the pawl backward, the rudder pedal is rotated around its axis, and the handle is turned at the appropriate position. It is designed to be released so that the retaining pawl and the rack can be engaged. However, with this type of conventional device, it is difficult to adjust the left and right rudder pedals at the same time, which makes adjustment time-consuming, and it is difficult to adjust the left and right rudder pedals at the same time using the text indicator on the side of the footrest. There was also the problem that it was time-consuming to confirm the information, as it had to be confirmed each time.

Furthermore, these pedal position adjustment mechanisms require similar parts to be arranged for the left and right rudder pedals, resulting in an overall increase in the number of parts and high costs. Furthermore, a conventional device for adjusting the position of a rudder pedal using a screw jack is known.

This system transmits the rotation of the handle to the screw jack via a flexible wire, and by changing the distance between the pedal hanger and the bell crank, the front and rear positions of the pedals can be adjusted. However, with this type of jack, the flexible wire moves as the screw jack moves, which is dangerous as the wire may catch on other aircraft structures, and the handle must be rotated many times to make adjustments. There was also the problem that it was time consuming.

Additionally, a common problem with the conventional rudder pedal position adjustment devices mentioned above is that the members and parts that make up these devices get into the instrument storage space on the back of the instrument panel, reducing the space available for use. be.

Therefore, the effective space for installing meters is reduced, the number of meters is reduced, or the shape of the meters is restricted, which makes it difficult to install the meters. The present invention solves these problems with conventional devices and allows simultaneous adjustment of the forward and backward positions of both rudder petals 7 by simply pulling the adjustment rod, without reducing the instrument storage space on the back of the instrument panel. Let's provide a rudder pedal position adjustment device that can be incorporated. That is.

An embodiment of the rudder pedal position adjustment device according to the present invention will be described below.

In FIG. 1, reference numeral 1 indicates a hinge shaft extending toward the left side, and on this hinge shaft 1 there is a hollow pivot 2R,
2L are arranged coaxially at intervals.

These pivots 2R and 2L are supported by the fuselage via appropriate bearings. The bases of two parallel pedal hangers 3R and 4R are rotatably mounted on the pivot shaft 2R, and the lower free ends of these hangers, which hang downward, have a pin 5R. The lower end of the pedal 6R is pivotally supported via.

Similarly, the bases of two parallel pedal hangers 3L and 4L are rotatably attached to the left pivot shaft 2L when facing the front, and the lower free ends of these hangers are rotatably mounted. The lower end of the pedal 6L is pivotally supported via the pin 5L. ) A bifurcated bracket 7R that protrudes rearward is provided at the base of the pedal hanger 3R, and a connecting rod 9R is connected to the bracket 7R via a pin 8R.
The upper end of the is connected with a pin.

Similarly, a bifurcated bracket 7L is provided at the base of the pedal hanger 3L, and the upper end of the connecting rod 9L is connected to the bracket 7L via a pin 8L. has been done. The lower ends of these connecting rods 9R, 9L are connected to a rudder pedal position adjustment device 10'' as described later. This pedal position adjustment device 10 is arranged below the pedals 6R, 6L, and the device 10 Hollow pivot shafts 12R and 12L are arranged at intervals on the hinge line 11 extending to the left side and the right side.
have.

These pivots 12R, 12L are supported on the fuselage via appropriate bearings, and the inner ends of these pivots 12R, 12L are
A swing bracket 13 having a substantially S'H-shaped planar shape is fitted in a tiltable manner. This swing bracket 13 is composed of two parallel side plates 14, 14, and an upper support plate 15 and a lower support plate 16 that are spanned between these side plates. Further, a notch 17 is formed near the front end of the side plate 14, and one side of this notch 17 has three
Adjustment grooves 17a, 17b, and 17c are formed across stages. Of course, the number of adjustment grooves can be increased or decreased as necessary. On the other hand, a drive shaft 18 parallel to the hinge line 11 is rotatably supported by a bearing (not shown) at the lower front of the swing bracket 13, and a pair of arms are mounted on the drive shaft 18. 19, 19 are fixed, and an engagement pin 20 is provided at the tip of each of these arms 19, 19 to protrude inward.

In the illustrated example, this engagement pin 20 has a central adjustment groove 17c.
The grooves 17a and 17b can be switched to fit in the upper and lower grooves 17a and 17b. At the shaft end of the drive shaft 18,
The lower end of the lever 21 is fixed, and the upper end of the lever 21 extends upward, and a spring 23 is elastically loaded between the upper end of the lever 21 and the bracket 22.

The upper end of the lever 21 is connected to the front end of an adjustment rod 24 that extends rearward directly below the instrument panel.The rear end of the adjustment rod 24 extends to a position where it can be easily operated by the pilot. A knob 25 is attached. The spring force of the spring 23 pulls the lever 21 forward, thereby causing the engagement pin 20 to move into the adjustment grooves 17a, 17b, 17c.
It maintains engagement with one of the grooves to prevent it from slipping out. Further, a bell crank 26 is fixed to the outer end of the pivot shaft 12R, and the bell crank 26 is provided with arms 27 and 28 having bifurcated tips that project outward at an angle of approximately S90 degrees.

Similarly, a bell crank 29 is fixed to the outer end of the pivot shaft 12L, and the bell crank 29 has arms 30 and 31 with bifurcated tips that project outward at an angle of approximately S90 degrees. Furthermore, the lower support plate 16 of the swing bracket 13
A coil spring 33 is stretched between the bracket 34 on the fuselage structure side, and the spring force of this spring 33 is applied in a direction that causes the swing bracket 13 to rotate around the hinge line 11 counterclockwise in the figure. I'm wearing a bias skirt.

Next, a mechanism for steering the rudder will be explained.

In FIG. 1, a vertical shaft 35 extending vertically is rotatably attached to the center of the upper support plate 15 of the swing bracket 13, and the center portion of a swing arm 36 is attached to the upper end of this vertical shaft 35. The right end of the swing arm 36 in the drawing is pin-coupled to one end of a link rod 37, and the other end of the link rod 37 is pin-coupled to the arm 27 of the bell crank 26. On the other hand, the left end of the swing arm 36 in the figure is pin-coupled to one end of a link rod 38, and the other end of the link rod 38 is pin-coupled to the arm 30 of the bell crank 29.

Furthermore, a crank arm 39 is provided at the lower end of the vertical shaft 35.
is fixed, and the tip of the crank arm 39 is connected via an alignment bearing to one end of a connecting rod 40 that extends coaxially with the hinge line 11 within the pivot shaft 12R, and the other end of the connecting rod 40 is connected to a bell crank 41. is connected to one end of the

One end of a rod 42 is connected to the other end of the bell crank 41, and the other end is connected to a rudder operating arm 43.
A rudder 45 is fixed to the center of the rudder operating arm 43. Next, to explain the brake operation mechanism, a bracket arm 50 is rotatably fitted to the shaft end of the hinge shaft 1, and the bracket arm 50 has two arms 51 spaced apart in the axial direction. , 52.

The upper end of a link rod 53 is pin-coupled to this arm 51, and the lower end of this link rod 53 is pin-coupled to the tip of an arm 54 that projects forward from the lower end of the pedal 6L. These arms 51 and link rods 53 and 54 constitute a four-bar link mechanism, and when a pressing force 8 is applied to the upper end of the pedal 6L, the arms 51 and 52 rotate counterclockwise around the hinge shaft 1. can be done. The operating end of a piston rod 56 of a brake cylinder device 55 is pin-coupled to the tip of the arm 52, and the lower end of the cylinder 57 is pivotally supported by a bracket 58 on the body side. FIG. 2 shows an example in which the above-mentioned rudder pedal adjustment device is installed in the cockpit 60 of an aircraft, with a pilot 61 seated on a seat 62 and with his feet on the pedals 6R and 6L. .

In front of the pilot 61 is an instrument panel 63 on which various instruments necessary for operating the aircraft are mounted. As is clear from the figure, the pedals 6R and 6L are arranged directly below the instrument panel 63, the rudder pedal position adjustment device 10 is arranged below the front of the pedals, and both are connected to the connecting rod 9R.
and 9L. Next, pedal 6R,
How to adjust the front and rear positions of 6L will be explained with reference to FIGS. 1 and 3.

(1) After the pilot is seated in the seat, he applies both his left and right feet to the pedals 6R and 6L and performs rudder steering to bring the control surface to the neutral position and eliminate the longitudinal positional deviation of the left and right pedals. )
(Ii) If the distance between the rudder pedal and the seat does not match the length of the pilot's legs in the condition (1) above, adjust the distance by turning the knob 25 against the spring force of the spring 23. Pull the rod toward you and rotate the drive shaft 18 clockwise in FIG. 1 via the lever 21.

(Ii) When the engagement pin 20 is removed from the groove 17c, the swing bracket 13 is rotated counterclockwise around the hinge line 11 under the action of the spring force of the coil spring 33.

(Iv) When the swing bracket 13 rotates counterclockwise around the hinge line 11, the vertical axis 35
, the swing arm 36 and the link rods 37, 38 also rotate integrally, and this rotation is transmitted to the pedal hangers 3R, 3L via the connecting rods 9R, 9L, and the pedal hangers 3R, 3L follow the hinge line 1 in FIG. The pedals 6R and 6L are rotated synchronously in a counterclockwise direction around the center, and the pedals 6R and 6L are moved to the shortest position for the pilot as shown by the imaginary lines. (v
) If this position is optimal, the adjustment rod 24 may be pushed in to engage the engagement pin 20 with the adjustment groove 17a.

(Vi) If the position set in (Iv) above has moved too far, pull the adjustment rod 24), both pedals 6
Put your feet on R and 6L and push in, link rods 6R and 6
Rotate the swing bracket 13 clockwise around the hinge line 11 in FIG.
It is only necessary that the groove 0 be brought to a position where it meshes with the adjustment groove 17b.

(Company) Once this position is determined, the adjustment rod 24 may be pushed in to maintain engagement between the engagement pin 20 and the adjustment groove 17b. In addition, in the above-described operation, as the swing bracket 13 rotates around the hinge line 11, the vertical shaft 35, the swing arm 36, and the crank arm 39 are rotated.
The crank arm 39 and connecting rod 40 rotate together around the hinge line 1, but since the crank arm 39 and connecting rod 40 use self-aligning bearings, the connecting rod 40
There is no twisting of the pedals, and the operation of adjusting the front and rear positions of the pedals does not affect the rudder steering.

Next, the method of steering the direction will be explained.

For example, when the right pedal 6R is depressed along the arrow 4, the pedal hangers 3R and 4R rotate around the hinge axis 1, and the tip of the arm 7R pushes down the connecting rod 9R, causing the swing arm 36 to rotate around the vertical axis 35. let

Then, the crank arm 39 also rotates in the same direction, pulling the connecting rod 40, and the bell crank 41 rotates counterclockwise in the figure, and the rod 42 rotates in the direction of the steering arm 4.
3 to rotate the rudder 45 counterclockwise.
Even when the left pedal 6L is depressed, the connecting rod 9c
The swing arm 36 is rotated via the right pedal, and driving is transmitted in the same manner as with the right pedal, causing the rudder 45 to rotate clockwise.

Next, the brake operation procedure will be explained with reference to FIG.

The pilot depresses the upper ends of the pedals 6R and 6L to rotate the pedals 6R and 6L around the pins 5R and 5L. Then, as the pedals 6R and 6L incline, the arm 5
4 pulls the link rod 53, moves the arm 51 downward, and rotates the bracket arm 50 counterclockwise. Then, the arm 52 pushes the piston rod 56, pressurizes the brake oil in the brake cylinder device 55, and operates the brake through the hydraulic piping. As is clear from the above description, according to the present invention, since the position adjustment device including the rocking bracket is incorporated below the rudder pedal, the members and parts constituting the adjustment device do not interfere with the instruments on the instrument panel. It is possible to place large instruments without having to worry about it.

Furthermore, since the adjustment device occupies less space on the instrument panel, more instruments can be mounted on the instrument panel.

In particular, as the performance of aircraft improves, aviation instruments become more complex and diverse, and the number of instruments that aircraft must be equipped with tends to increase, so these demands can be met. Furthermore, the front and rear positions of the left and right rudder pedals can be adjusted at once, and the amount of adjustment can be made mechanically the same amount, making it unnecessary to check the amount of adjustment at the time of adjustment. The adjustment work is easy because all you have to do is pull the adjustment rod.

[Brief explanation of drawings]

FIG. 1 is a perspective view showing an embodiment of the rudder pedal position adjusting device according to the present invention, and FIG. 2 is a side view showing the rudder pedal position adjusting device according to the present invention installed in the cockpit of an aircraft. FIG. 3 is an explanatory diagram showing how the rudder pedal is adjusted to move back and forth, and FIG. 4 is an explanatory diagram showing the operating state of the braking device. 1...Hinge shaft, 2R, 2L...Pivot, 3R, 4R, 3L, 4L...Pedal hanger, 6R
, 6L... Pedal, 9R, 9L... Connection rod, 10... Rudder pedal position adjustment device, 11...
...Hinge line, 12R, 12L...
Pivot, 13... Swing bracket, 17a, 17
b, 17c...adjustment groove, 20...engaging pin,
24... Adjustment rod, 26, 29... Bell crank, 2
7, 28, 30, 31... Arm, 35... Vertical axis, 36... Swing arm, 37, 38...
...Link rod.

Claims (1)

[Claims] 1. A pair of left and right pedal hangers whose bases are rotatably fitted around a common pivot and are suspended downward, and a pair of left and right pedals that are pivotably supported around the lower end of the pedal hanger. The rudder pedal thus constitutes a pedal adjustment device disposed below the rudder pedal, the pedal adjustment device comprising a pair of pivots spaced apart on a common hinge line and a pair of pivots at the outer ends of the pivots. A bell crank that is coupled together and has two arms protruding; a swinging bracket that has one end fixed to the inner end of the pivot shaft and the other end provided with a plurality of adjustment grooves; and a vertical shaft that is connected to the swinging bracket. A swing arm whose central portion is connected via a swing arm that is substantially parallel to the hinge line, a pair of link rods that connect both ends of the swing arm and one of the arms of the bell crank, and an engagement pin that engages with the adjustment groove. 1. A rudder pedal position adjustment device, characterized in that the pedal hanger and the remaining arm of the bell crank are connected by a connecting rod.