Airplane pedal capable of coaxially and synchronously adjusting neutral position of pedal

Abstract

The invention belongs to the field of airplane pedal design, and particularly relates to an airplane pedal capable of coaxially and synchronously adjusting the neutral position of a pedal, which comprises a pedal base, a pedal, a parallel four-bar linkage transmission mechanism and a pedal adjusting mechanism, the two sets of pedal plates are symmetrically arranged on the pedal base, the parallel four-connecting-rod transmission mechanism is arranged in front of the two sets of pedal plates, the pedal adjusting mechanism is arranged between the two sets of pedal plates, and the middle of the parallel four-connecting-rod transmission mechanism is connected with the pedal adjusting mechanism. The pedal adjusting mechanism comprises an adjusting handle, a second adjusting pull rod, a first rocker arm, a second rocker arm and a sliding block. The pedal neutral position adjusting mechanism adopts a central integrated design, all transmission parts are integrated together, when a pedal neutral position adjusting fault occurs, the pedal neutral position adjusting mechanism can be integrally replaced, and the adjusting mechanism is directly disassembled and replaced; and even under the condition that the operation condition of the surrounding environment of the pedal in an aircraft cockpit is good, in-situ reloading can be carried out.

Description

Technical Field

[0001] The present application belongs to the field of aircraft pedal design, and in particular relates to an aircraft pedal for coaxially and synchronously adjusting the neutral position of a pedal. Background Art

[0002] In the pilot control system, the main function of the aircraft pedal is to realize the control of aircraft yaw, front wheel turning and wheel brake, and it is one of the important main control systems of the aircraft. Due to the differences in the body shapes of different pilots, the distance between the aircraft pedal and the seat must be adjustable, which is generally achieved by adjusting the front and rear position of the pedal (i.e. adjusting the neutral position of the pedal).

[0003] The horizontal pedal control device used in existing aircraft models has a small application range and a large limitation in the front and rear adjustment method, making it difficult to be universally applied to various aircraft models. Figure 1 As shown in the figure, the device is a horizontal pedal used in a certain type of mechanical control system aircraft, which adopts a mechanical pull-pin adjustment method and is only applicable to soft mechanical control systems, and the pedals on both sides cannot be adjusted synchronously; Figure 2 As shown, the device is a horizontal pedal used in a certain aircraft. The pedal neutral position adjustment mechanism is arranged in the middle of the pedal shaft, and the left and right main connecting rods of the pedal are on both sides of the adjustment mechanism. The solution has a complex structure. When the pedals on both sides are adjusted synchronously, multiple parallel four-bar linkages are required to be coupled together between the left and right main connecting rods, the left and right front connecting rods and the adjustment mechanism. There are many transmission nodes, which increases the friction and idle stroke. The transmission reliability and transmission stiffness are poor, and the adjustment mechanism is prone to failure. When the pedal adjustment mechanism of this structural solution fails, the entire aircraft pedal can only be removed for inspection and repair, which is not conducive to the use and maintenance of the pedal assembly.

[0004] Therefore, how to improve the transmission stiffness of the pedal and the convenience of maintenance is a problem that needs to be solved. Summary of the invention

[0005] The purpose of the present application is to provide an aircraft pedal for coaxially and synchronously adjusting the neutral position of the pedal, so as to solve the problems of poor transmission rigidity and inconvenient maintenance of the existing pedals.

[0006] The technical solution of the present application is: an aircraft pedal for coaxially and synchronously adjusting the pedal neutral position, comprising a pedal base, a pedal pedal, a parallel four-bar linkage transmission mechanism and a pedal adjustment mechanism; the pedal pedals are in total two groups and are symmetrically arranged on the pedal base, the parallel four-bar linkage transmission mechanism is arranged in front of the two groups of pedal pedals, the pedal adjustment mechanism is arranged between the two groups of pedal pedals, and the middle part of the parallel four-bar linkage transmission mechanism is connected to the pedal adjustment mechanism; the pedal adjustment mechanism comprises an adjustment handle, a second adjustment pull rod, a first rocker arm, a second rocker arm and a slider; an inner cavity is opened inside the pedal base, The slider is arranged in the inner cavity, and the middle part of the slider is slidably matched with a pin, which is fixedly connected to the pedal base, and the pin sleeve is provided with a return spring, one end of the return spring is in contact with the inner wall of the slider, and the other end is in contact with the inner wall of the slider; the second rocker arm is hinged on the pedal base and connected to the slider, the first rocker arm is hingedly connected to the pedal base, the first rocker arm and the second rocker arm are respectively arranged at two ends of the pedal base, the two ends of the second adjustment rod are respectively connected to the first rocker arm and the second rocker arm, the top of the first rocker arm is connected to a steel cable, and the adjustment handle is connected to the end of the steel cable.

[0007] Preferably, the parallel four-bar linkage transmission mechanism includes side arms, a main link and a front link; there are two groups of side arms and they are respectively arranged on both sides of the pedal base, the two ends of the main link are connected to the side arms, the middle part of the main link is connected to the two sides of the adjustment frame through a first adjustment rod, the front link is arranged at the front end of the pedal base, the middle part and both ends of the front link are respectively connected to the pedal adjustment mechanism and the side arms, and the side arms, the main link and the front link cooperate with the pedal base to form a parallel four-bar linkage transmission mechanism.

[0008] Preferably, a pedal pivot and an output rocker arm are also provided on the pedal base, and the pedal pivot is installed on the pedal base through a bearing, and the upper end of the pedal pivot is connected to the pedal adjustment mechanism, and the lower end is connected to the output rocker arm.

[0009] Preferably, brake sensor ears are provided at both ends of the side arm.

[0010] Preferably, two fixing ears are provided on the pedal base.

[0011] The aircraft pedal for coaxially and synchronously adjusting the pedal neutral position of the present application has the following advantages:

[0012] (a) The pedal neutral position adjustment mechanism adopts a central integrated design, integrating various transmission components together. When a pedal neutral position adjustment failure occurs, the adjustment mechanism can be replaced as a whole by directly removing it and replacing it. Even when the operating conditions around the pedals in the aircraft cabin are good, it can be replaced in situ without returning to the factory, which greatly reduces the difficulty of replacement and the workload of maintenance and support.

[0013] (b) This structure of pedals can meet the functional requirements of most mechanical / fly-by-wire flight control systems, with small space requirements, good versatility, and convenient maintenance and support for various types of aircraft. In addition, the simplification of the transmission link makes up for the disadvantages in transmission performance and reliability, greatly reducing system costs and installation and maintenance difficulties. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0015] Figure 1 It is a schematic diagram of a horizontal pedal structure in the background technology;

[0016] Figure 2 It is a schematic diagram of another horizontal pedal structure in the background technology;

[0017] Figure 3 This is a top view of the overall structure of this application;

[0018] Figure 4 This is the overall structure diagram of the pedal adjustment mechanism of this application;

[0019] Figure 5 This is the axonometric drawing of the overall structure of this application.

[0020] 1. Pedal base; 2. Pedal adjustment mechanism; 3. Side arm; 4. Main connecting rod; 5. Front connecting rod; 6. Pedal pedal; 7. First adjustment rod; 8. Pedal pivot; 9. Output rocker arm; 10. Fixed ear; 11. Brake sensor ear; 21. Adjustment handle; 22. Steel cable; 23. Second adjustment rod; 24. First rocker arm; 25. Second rocker arm; 26. Slider; 27. Return spring; 28. Adjustment frame. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0022] An aircraft pedal for coaxially and synchronously adjusting the neutral position of the pedal, such as Figure 3-5As shown, it includes a pedal base 1, a pedal pedal 6, a parallel four-bar linkage transmission mechanism and a pedal adjustment mechanism 2. There are two groups of pedal pedals 6 and they are symmetrically arranged on the pedal base 1, the parallel four-bar linkage transmission mechanism is arranged in front of the two groups of pedal pedals 6, the pedal adjustment mechanism 2 is arranged between the two groups of pedal pedals 6, and the middle part of the parallel four-bar linkage transmission mechanism is connected to the pedal adjustment mechanism 2.

[0023] The pedal adjustment mechanism 2 comprises an adjustment frame 28, an adjustment handle 21, a second adjustment rod 23, a first rocker arm 24, a second rocker arm 25 and a slider 26. An inner cavity is provided inside the adjustment frame 28, and the slider 26 is arranged in the inner cavity. A latch is slidably matched in the middle of the slider 26, and the latch is fixedly connected to the adjustment frame 28. A return spring 27 is provided on the latch sleeve, and one end of the return spring 27 is in contact with the inner wall of the slider 26, and the other end is in contact with the inner wall of the slider 26; the second rocker arm 25 is hinged on the adjustment frame 28 and connected to the slider 26, the first rocker arm 24 is hingedly connected to the adjustment frame 28, the first rocker arm 24 and the second rocker arm 25 are respectively arranged at the two ends of the adjustment frame 28, the two ends of the second adjustment rod 23 are respectively connected to the first rocker arm 24 and the second rocker arm 25, the top of the first rocker arm 24 is connected to a steel cable 22, and the adjustment handle 21 is connected to the end of the steel cable 22.

[0024] When the left and right foot pedals are adjusted to the front and rear neutral position, the adjusting handle 21 drives the steel cable 22, the double-ear rocker arm, and the second adjusting rod 23 to rotate the rocker arm around the axis, pull out the pin stuck in the slider 26, and the slider 26 slides linearly back and forth in the adjustment structure under the left and right of the return spring 27, thereby driving the second adjusting rod 23 to move, and driving the main connecting rod 4 to rotate around the pivot. Under the action of the parallel four-bar transmission mechanism, the left and right foot pedals 6 move parallel to each other front and rear to achieve the front and rear adjustment of the neutral position of the left and right foot pedals.

[0025] Preferably, the parallel four-link transmission mechanism includes side arms 3, main links 4 and front links 5. There are two groups of side arms 3 and they are respectively arranged on both sides of the pedal base 1. The two ends of the main link 4 are connected to the side arms 3. The middle part of the main link 4 is connected to both sides of the adjustment frame 28 through the first adjustment rod 7. The front link 5 is arranged at the front end of the pedal base 1. The middle part and both ends of the front link 5 are respectively connected to the pedal adjustment mechanism 2 and the side arms 3. The side arms 3, the main link 4 and the front link 5 cooperate with the pedal base 1 to form a parallel four-link transmission mechanism. When the pedal adjustment mechanism 2 is working, the parallel four-link transmission mechanism stably supports the pedal adjustment mechanism 2 to prevent deviation.

[0026] Preferably, a pedal pivot 8 and an output rocker arm 9 are also provided on the pedal base 1. The pedal pivot 8 is installed on the pedal base 1 through a bearing. The upper end of the pedal pivot 8 is connected to the pedal adjustment mechanism 2, and the lower end is connected to the output rocker arm 9, forming the main shaft part of the pedal adjustment device.

[0027] Preferably, brake sensor ears 11 are provided at both ends of the side arm 3. The brake sensor ears 11 can be installed with brake command sensors as needed. When the foot pedal 6 rotates, the brake command sensor is stretched or compressed to output a brake command.

[0028] Preferably, two fixing ears 10 are provided on the pedal base 1, and the fixing ears 10 can be used for installing a human sensing system (load mechanism, damper) and a command sensor.

[0029] Through this design, the present application has the following advantages:

[0030] (a) The pedal neutral position adjustment mechanism adopts a central integrated design, integrating various transmission components together. When a pedal neutral position adjustment failure occurs, the adjustment mechanism can be replaced as a whole by directly removing it and replacing it. Even when the operating conditions around the pedals in the aircraft cabin are good, it can be replaced in situ without returning to the factory, which greatly reduces the difficulty of replacement and the workload of maintenance and support.

[0031] (b) This structure of pedals can meet the functional requirements of most mechanical / fly-by-wire flight control systems, with small space requirements, good versatility, and convenient maintenance and support for various types of aircraft. In addition, the simplification of the transmission link makes up for the disadvantages in transmission performance and reliability, greatly reducing system costs and installation and maintenance difficulties.

[0032] When the foot pedals are stepped on left and right, the main connecting rod, the foot pedal pivot, the foot pedal adjustment mechanism and the output rocker arm are pushed to rotate around the main axis, and the front connecting rod moves around the auxiliary axis to form a parallelogram motion, ensuring that the left and right foot pedals move parallel to each other front and back, and the output rocker arm outputs the corresponding mechanical displacement.

[0033] Finally, it should be noted that: the drawings of the embodiments disclosed in the present invention only involve structures related to the embodiments disclosed in the present invention, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0034] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft pedal for coaxially and synchronously adjusting the neutral position of the pedal, characterized in that: The pedal base (1) comprises a pedal pedal (6), a parallel four-bar linkage transmission mechanism and a pedal adjustment mechanism (2); the pedal pedals (6) are in total two groups and are symmetrically arranged on the pedal base (1); the parallel four-bar linkage transmission mechanism is arranged in front of the two groups of pedal pedals (6); the pedal adjustment mechanism (2) is arranged between the two groups of pedal pedals (6); the middle part of the parallel four-bar linkage transmission mechanism is connected to the pedal adjustment mechanism (2); the pedal adjustment mechanism (2) comprises an adjustment frame (28), an adjustment handle (21), a second adjustment pull rod (23), a first rocker arm (24), a second rocker arm (25) and a slider (26); an inner cavity is provided inside the adjustment frame (28), the slider (26) is arranged in the inner cavity, and the middle part of the slider (26) is slidingly coupled The adjusting frame (28) is provided with a latch, which is fixedly connected to the adjusting frame (28); the latch sleeve is provided with a reset spring (27); one end of the reset spring (27) is in contact with the inner wall of the slider (26), and the other end is in contact with the inner wall of the slider (26); the second rocker arm (25) is hinged on the adjusting frame (28) and connected to the slider (26); the first rocker arm (24) is hinged on the adjusting frame (28); the first rocker arm (24) and the second rocker arm (25) are respectively arranged at two ends of the adjusting frame (28); the two ends of the second adjusting rod (23) are respectively connected to the first rocker arm (24) and the second rocker arm (25); the top of the first rocker arm (24) is connected to a steel cable (22); the adjusting handle (21) is connected to the end of the steel cable (22).

2. The aircraft pedal for coaxially and synchronously adjusting the pedal neutral position as claimed in claim 1, characterized in that: The parallel four-bar linkage transmission mechanism comprises side arms (3), a main link (4) and a front link (5); the side arms (3) have two groups and are respectively arranged on both sides of the pedal base (1); the two ends of the main link (4) are connected to the side arms (3); the middle part of the main link (4) is connected to the two sides of the adjustment frame through a first adjustment rod (7); the front link (5) is arranged at the front end of the pedal base (1); the middle part and the two ends of the front link (5) are respectively connected to the pedal adjustment mechanism (2) and the side arms (3); the side arms (3), the main link (4) and the front link (5) cooperate with the pedal base (1) to form a parallel four-bar linkage transmission mechanism.

3. The aircraft pedal for coaxially and synchronously adjusting the pedal neutral position as claimed in claim 2, characterized in that: The pedal base (1) is also provided with a pedal pivot (8) and an output rocker arm (9); the pedal pivot (8) is mounted on the pedal base (1) via a bearing; the upper end of the pedal pivot (8) is connected to the pedal adjustment mechanism (2), and the lower end is connected to the output rocker arm (9).

4. The aircraft pedal for coaxially and synchronously adjusting the pedal neutral position as claimed in claim 1, characterized in that: Brake sensor ears (11) are provided at both ends of the side support arm (3).

5. The aircraft pedal for coaxially and synchronously adjusting the pedal neutral position as claimed in claim 1, characterized in that: Two fixing lugs (10) are arranged on the pedal base (1).

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