KR20010094107A - Aircraft's rudder and brake pedal device - Google Patents

Abstract

PURPOSE: One body of a rudder and a brake pedal for an aircraft is provided to minimize the initial friction and to increase accuracy in operating the brake and the pedal. CONSTITUTION: A rudder and brake pedal device is composed of a pedal shaft unit(30) having pedal unit supporting brackets held by a supporting rod(42) to turn; left and right pedal body assemblies including a pedal(12) turned in the lower part; a brake bell crank supporting bracket held by the supporting rod to turn between pedal unit supporting brackets; left and right brake bell crank assemblies(80) turning around the supporting rod by interlocking with the pedal, and operating the brake unit; left and right rudder bell crank assemblies(100) turned by the supporting rod between brake bell crank supporting brackets, connected to interlocking flexible cables and a push-pull rod to control the rudder, and connected to a steering wheel to control a landing gear; and a pedal position adjusting assembly connected to the rudder bell crank assemblies and the pedal shaft unit to adjust the distance between connecting points. The rudder, the brake and the pedal are controlled accurately under the control of the pilot by reducing the initial friction.

Description

Rudder and brake pedal devices for aircrafts {AIRCRAFT'S RUDDER AND BRAKE PEDAL DEVICE}

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to rudder and brake pedal devices of aircraft, and more particularly to rudder and brake pedal devices of aircraft with minimal initial frictional forces acting on the pedals.

In general, an aircraft is provided with a rudder surface capable of turning left and right in the rear of a vertical tail wing and a pedal for turning the rudder from side to side as a means for converting the direction in flight from side to side. In order to change the direction of the landing gear is provided with a landing gear steering mechanism for turning the front wheel landing gear to the left and right, and a brake system for braking while driving on the ground.

Here, the pedal is operated by both feet of the pilot, it is installed to adjust the position back and forth according to the physical condition of the pilot.

Such rudder and brake pedal devices are known from the applicant's patent no. 156339 (name of invention: brake ladder pedal devices of light aircraft). The prior art has a simple structure, but the position adjustment of the pedal is very quick, simple, and light weight, there was an advantage suitable for the aircraft. In addition, the position of the pedal was able to adjust the position on the ground as well as flying. However, the prior art has a problem in that a significant amount of friction force exists in the pedals due to the use of each separate system bonded to each other.

The present invention has been made to solve the above problems, the present invention is to change the existing design method of each part integrally designed to reduce the initial friction force, the response of the rudder and brake accurately respond to the pilot's steering force The purpose is to achieve operation and pedal position adjustment.

BRIEF DESCRIPTION OF THE DRAWINGS It is a schematic diagram of the rudder and brake pedal apparatus of this invention, Comprising: It is the perspective view seen from the upper side of the cockpit side (henceforth when viewed from a cockpit side.).

2A is a plan view of the pedal shaft unit, and FIG. 2B is a front view of the pedal shaft unit.

3A is a front view of the brake bell crank assembly, and FIG. 3B is a right side view of the brake bell crank assembly.

4A is a left side view of the rudder bell crank assembly, and FIG. 4B is a front view of the rudder bell crank assembly.

Figure 5a is a front view of the removable guide block support bracket for supporting the guide block of the pedal position adjustment actuator assembly, Figure 5b is a right side view.

6A is a perspective view of the pedal positioning actuator assembly, and FIG. 6B is a front view.

7, 8 and 9 are schematic views showing a front view, a plan view, and a left side view of the rudder and brake pedal device of the present invention, respectively.

*** Description of the symbols for the main parts of the drawings ***

12: pedal 30: pedal shaft unit

31. 33: Pedal shaft unit support bracket portion 37: Integrated guide block support bracket portion

42: through support rod 54, 56: universal joint

62: guide block 65: removable guide block support bracket

72: pedal position adjustment actuator support bracket

74: gearbox 77: screw shaft shaft

80: brake bell crank assembly

83, 87: Brake bell crank support bracket

100: rudder bell crank assembly 142: left and right interlocking flexible cable

The present invention is to achieve the above object, the present invention is a pedal shaft unit having a pedal shaft unit support bracket portion integrally supported by a rotatable support rod fixed to both sides of the fuselage body, and the lower end is rotatable A pair of left and right pedal body assemblies comprising pedals to be supported; A pair of left and right brake bell crank support brackets rotatably supported by the through support rods between the pedal shaft unit support brackets and interlocked with the pedals to operate the brake mechanism by rotating the through support rods in a rotational center. Brake bell crank assembly; Left and right interlocking flexible cables and direct or indirect rudder operation at positions biased by the through support rods and rotatably supported by the through support rods between the brake bell crank support brackets. By being connected to the push-pull rod, the rudder is controlled by the rotation centering the through support rod, and connected to the steering mechanism at another position biased to the point rotatably supported by the through support rod, A pair of left and right rudder bell crank assemblies for controlling the landing gear by a rotation centering the through support rod; It is connected to the rudder bell crank assembly and rotatably connected to the pedal shaft unit, and provides a rudder and brake pedal device comprising a pedal position adjustment assembly that can adjust the distance between both connection points.

The pedal position adjusting assembly may have various embodiments, but according to a preferred embodiment of the present invention, the pedal position adjusting assembly includes a driving means, a universal joint connected to a rotation shaft of the driving means, and a rotation force from the universal joint. A gearbox for receiving a change in direction of the rotational shaft, connecting the gearbox to the rudder bell crank assembly, a pedal positioning actuator support bracket portion, a rotatable screw shaft shaft connected to the gearbox, and the screw shaft shaft It is made to include a guide block movable in the axial direction of the screw shaft shaft, the pedal shaft unit is fixed to the detachable guide block support bracket, integral type formed integrally with the detachable guide block support bracket and the pedal shaft unit Between the guide block support brackets The guide block is rotatably supported.

As the driving means, an electric motor using a flight power source is preferably used.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. Since the rudder and brake pedal devices of the present invention are generally left and right symmetrical, unless otherwise specified, the description of one side (eg, the left side) applies equally to the other side (eg, right side). In the present specification, the left part of the rudder and brake pedal apparatus of the present invention will be described. BRIEF DESCRIPTION OF THE DRAWINGS It is a schematic diagram of the rudder and brake pedal apparatus of this invention, and is a perspective view seen from the upper left side of a cockpit side. As shown, the rudder and brake pedal device of the present invention is divided into a pedal body assembly, a brake bell crank assembly 80, a rudder bell crank assembly 100 and a pedal position adjustment assembly.

The pedal body assembly is schematically composed of a pedal 12, a vertical bar 14, a connecting rod 22 and a pedal shaft unit 30. The vertical bar 14 is fixed with a high lock to reduce frictional force loss in the pedal 12.

When the pilot actuates the pedal 12, the actuation force is sent to the rudder surface (not shown) or brake mechanism (not shown) through the brake bell crank assembly 80 or the rudder bell crank assembly 100.

The pedal position adjustment assembly allows the position of the pedal body assembly to be adjusted back and forth according to the physical condition of the pilot, and the pedal position adjustment assembly is roughly the electric motor 52, the universal joints 54 and 56, and the pedal position adjustment actuator assembly. 60 and a detachable guide block support bracket 65. The electric motor 52 receives the torque of the motor using the flying power, and transmits the torque to the pedal position adjustment actuator assembly 60, and the pedal position adjustment actuator assembly 60 receives the torque to receive the position of the pedal. Function to adjust.

The rudder bell crank assembly 100 is connected to the flexible cable 142 for interlocking the left and right, and at the same time, it is connected to the flexible cable 148 for interlocking the front and rear in the case of two-seater (in the case of a single-seater, the rudder operation push It is directly connected to the full load (hereafter described on a two-seater aircraft unless otherwise specified). The flexible cables 142 and 148 are formed in one loop, and the pulleys 144 for position movement of the cables are installed to support or smoothly operate the cables. The 145 is a turnbuckle used for cable length adjustment and cable and cable connection fixing. The rudder bell crank assembly 100 is connected to the cables 142, 148 by a cable fixing block 152, the ends of each cable is ball treatment.

2A is a plan view of the pedal shaft unit 30, and FIG. 2B is a front view of the pedal shaft unit 30. As shown in FIG. As shown in the drawing, a plurality of openings are formed in the pedal shaft unit 30, and the openings 32 formed in the pedal shaft unit support bracket portion 31 and the openings formed in the pedal shaft unit support bracket portion 33 ( A through support rod 42 is fitted to the 34, and the through support rod 42 is fixed to a fuselage frame (not shown) of the aircraft. The brake bell crank assembly 80 and the rudder bell crank assembly 100 are rotatably fitted to the through support rod 42 between the opening 32 and the opening 34. In addition, the opening 36 is bolted to the pedestal side, that is, the inside. The broken line 65 is fixed to the pedal shaft unit 30 as the detachable guide block support bracket portion 65, and serves to reduce the frictional force of the pedal. The guide block 62 of the pedal position adjustment actuator 60 is formed in the opening 68 formed in the guide block support bracket 65 and the opening 38 formed in the integrated guide block support bracket portion 37 of the pedal shaft unit 30. ) Is rotatably supported.

3A is a front view of the brake bell crank assembly 80, and FIG. 3B is a right side view of the brake bell crank assembly 80. As shown, the brake bell crank assembly has a plurality of openings, which are connected to the brake mechanism. A through support rod 42 is fitted into the opening 84 and the opening 88 to rotatably support the brake bell crank assembly 80. In addition, the connecting rod 22 is rotatably connected to the opening 86. The actuation of the brake is such that, as the pilot presses the upper end of the pedal, the connecting rod 22 pivotally connected to the pedal 12 is moved downwardly to the rotational center of the point 16, whereby the connecting rod 22 The brake bell crank 80 connected to the wheel also pivots the through support rod 42 at the center of rotation, and this force is transmitted to the brake mechanism.

The front and rear brake bell cranks are connected by an interlocking rod (not shown), and the brake mechanism is operated while the other pedal is linked together no matter which pedal is pressed.

The return of the pedal is restored by a return actuator (not shown) using hydraulic pressure in the rear seat. However, the return actuator is to restore the four front and rear left and right pedals, the left side is on the left side of the rear seat, the right side is located on the right side of the rear seat.

4A is a left side view of the rudder bell crank assembly 100, and FIG. 4B is a front view of the rudder bell crank assembly 100. A plurality of openings are formed in the rudder bell crank assembly 100, and the cable fixing block 152 is rotatably connected to the opening 102, and a pedal position adjustment actuator is provided between the opening 106 and the opening 104. A support bracket portion 72 is connected, and a through support rod 42 is fitted to the opening 112 and the opening 108 to rotatably support the rudder bell crank assembly. A steering rod (not shown) is connected to the opening 114. The steering rod is only connected to the front rudder bell crank.

The operation of the rudder is, for example, when the pilot pushes the lower end of the left pedal 12 forward, the pedal body assembly rotates the through support rod 42 to the center of rotation, and at the same time, moves the pedal position adjustment actuator assembly 60. The rudder bell crank assembly 100 connected to each other also rotates integrally so that the upper end of the rudder bell crank is pulled backward, thereby pulling the left and right interlocking cables 142. Therefore, the upper end of the rudder bell crank assembly rotates forwardly around the through support rod, and pulls the flexible cable for forward and backward interlocking and the push pull rod for rudder operation (not shown) on the right side. This will be delivered to the rudder.

The above describes the operation of the front landing gear in the folded state, that is, the operation in the process of flying. When the aircraft is traveling on the ground, the steering of the rudder bell crank assembly is performed simultaneously with the left and right rotation of the rudder as described above. Through the rod, the direction of the front wheel landing gear is switched to change the driving direction.

5A is a front view of the detachable guide block support bracket 65 for supporting the guide block 62 of the pedal position adjustment actuator assembly 60, and FIG. 5B is a right side view. As described in FIG. 2A, the detachable guide block support bracket 65 is fixed to the pedal shaft unit 30. In addition, the guide block 62 is rotatable between the opening 68 formed in the detachable guide block support bracket 65 and the opening 38 formed in the integrated guide block support bracket portion 37 of the pedal shaft unit 30. Is supported.

6A is a perspective view of the pedal position adjustment actuator assembly 60, and FIG. 6B is a front view. As shown, the pedal position adjustment actuator assembly 60 is a pedal position adjustment actuator support bracket portion 72 is connected between the gearbox 74, the openings 106 and 104 of the rudder bell crank assembly 100, It consists of a screw shaft shaft 77, a guide block 62 and a stopper 79. When the electric motor 52 is operated, the generated torque is transmitted to the gearbox 74 through the two universal joints 54 and 56, and the direction of the rotation axis of the torque is switched by the engagement of the gears in the gearbox, The shaft shaft 77 is rotated. The guide block 62 having a thread formed in the inner diameter by the rotation of the screw shaft shaft 77 moves along the axial direction of the screw shaft shaft 77, whereby the pedal body assembly rotates the through support rod 42. Will be rotated. The stopper 79 is fixed to the end of the screw shaft shaft 77 so that the guide block 62 does not escape. According to a preferred embodiment of the present invention, a pair of bevel gears are mounted in the gearbox 74.

Moment acting on the pedal body assembly in the above-described pedal position adjustment process is also transmitted to the rudder bell crank assembly 100, the rudder bell crank assembly 100, the left and right interlocking flexible cable 142 and the front and rear interlocking flexible cable ( Since the 148 is connected and these flexible cables form a loop, the rudder bell crank assembly 100 is fixed by the flexible cable to maintain the original state without being rotated, and only the pedal body assembly is rotated.

7, 8 and 9 schematically show a front view, a top view and a left side view of a rudder and brake pedal device according to the invention. As shown in FIG. 8, the through support rod 42 includes an opening 32 formed in the pedal shaft unit support bracket portion 31, an opening 84 formed in the brake bell crank support bracket portion 83, and a rudder bell crank. An opening 112 formed in the assembly 100, an opening 108 formed in the rudder bell crank assembly 100, an opening 88 formed in the brake bell crank support bracket portion 87, and a pedal shaft unit support bracket portion 33. The pedal shaft unit 30, the brake bell crank assembly 80 and the rudder bell crank assembly 100 are rotatably supported by fitting through the opening 34 formed therein.

So far, preferred embodiments of the present invention have been described with reference to the accompanying drawings, but the scope of the invention to be claimed is of course only to be specified by the appended claims. For example, the position (eg, the position of each opening) and the resulting structure of the connection portion of each assembly may be relatively changed without departing from the gist of the present invention as claimed.

According to the present invention of the above-described configuration, by reducing the initial frictional force, it becomes possible to operate the rudder and brakes and the pedal position adjustment accurately responding to the pilot's steering force.

Claims (2)

A pedal shaft unit including a pedal shaft unit support bracket portion integrally rotatably supported by a through support rod fixed to both frames of the body, A pair of left and right pedal body assemblies including a pedal on which a lower end is pivotally supported; A brake bell crank support bracket portion rotatably supported by the through support rod between the pedal shaft unit support brackets, A pair of left and right brake bell crank assemblies interlocked with the pedals to operate the brake mechanism by rotating the through support rod in a rotational center; Rotatably supported by the through support rod between the brake bell crank support brackets, By connecting the left and right interlocking flexible cable and the rudder operation push-pull rod directly or indirectly at a position biased to the point rotatably supported by the through support rod, the rudder is rotated by rotating the through support rod as the center of rotation. Control, A pair of left and right rudder bell crank assemblies which are connected to the steering mechanism at another position biased by the through support rod so as to be rotatable so as to control the landing gear by a rotation centering the through support rod; ; The rudder and brake pedal apparatus of claim 1, further comprising a pedal position control assembly connected to the rudder bell crank assembly and rotatably connected to the pedal shaft unit and capable of adjusting a distance between both connection points. The method of claim 1, wherein the pedal position control assembly comprises a drive means, a universal joint connected to the rotation axis of the drive means, a gear box for receiving a rotational force from the universal joint to change the direction of the rotation axis, and the gear box A pedal position adjustment actuator support bracket portion, a rotatable screw shaft shaft connected to the gearbox, and a guide block movable in the axial direction of the screw shaft shaft by engaging with the screw shaft shaft. Done, A detachable guide block support bracket is fixed to the pedal shaft unit, and the aircraft is characterized in that the guide block is rotatably supported between the detachable guide block support bracket and the integrated guide block support bracket portion formed integrally with the pedal shaft unit. Rudder and brake pedal device.