A manipulation system simulation foot pedal

Abstract

The utility model discloses a kind of operating system simulation footrests, including base, the base has two, the upper side of base is equipped with three horizontal bearing seats one of even distribution, two transversely distributed footrest uprights are rotatably connected between three horizontal bearing seats one of transversely adjacent, the upper end of footrest upright is rotatably connected with pedal by pivot two, still include footrest steering mechanism;Footrest steering mechanism: it includes pivot three, adjusting block, pivot four, main and auxiliary footrest connecting rod and adjusting assembly, this operating system simulation footrest, compatible multiple driving mode realizes aircraft footbrake and steering function, can satisfy the training demand of simulator, trainer, and device internal zero-gap design guarantees force feeling, stroke and installation aircraft keep consistent, while device itself selects healthy environmental protection, reliable device, equipment surface treatment, process method uses national military standard technology, environmental protection durable.

Description

Technical Field

[0001] This utility model relates to the field of aircraft control system simulation technology, specifically a control system simulation pedal. Background Technology

[0002] The rudder pedal is a foot control device in the aircraft cockpit used to operate the rudder. It is mainly used to control the aircraft's heading stability and correct yaw. Aircraft pilots need to undergo extensive simulation training to become familiar with the rudder pedal device. Current rudder pedal training partially relies on the following methods: 1. Theoretical teaching: explaining the sealing process through drawings and videos. This method lacks intuitive hands-on operation experience; 2. On-site training: conducting practical training directly on actual aircraft. This method has problems such as high cost (long aircraft occupation time), high risk (misoperation may damage original components), and low efficiency (requires coordination of aircraft resources). Therefore, we propose a control system simulation pedal. Utility Model Content

[0003] The technical problem to be solved by this utility model is to overcome the existing defects and provide a simulated foot pedal for a control system. This device is compatible with multiple drive methods to realize the foot pedal braking and steering functions of an aircraft, which can meet the training needs of simulators and trainers. The zero-gap design inside the device ensures force sensitivity, and the stroke is consistent with that of the actual aircraft. At the same time, the device itself selects healthy, environmentally friendly and reliable components, and the surface treatment and process methods of the equipment adopt national military standard technology, which is environmentally friendly and durable, and can effectively solve the problems in the background technology.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a simulated pedal for a control system, comprising a base, wherein there are two bases, and each base has three horizontally evenly distributed bearing seats 1 at its upper front end. The three horizontally adjacent bearing seats 1 are rotatably connected to two horizontally distributed pedal columns through a rotating shaft 1. The upper end of each pedal column is rotatably connected to a pedal through a rotating shaft 2. The invention also includes a pedal steering mechanism.

[0005] Foot pedal steering mechanism: It includes a third rotating shaft, an adjusting block, a fourth rotating shaft, a main and auxiliary foot pedal connecting rod, and an adjusting assembly. The adjusting blocks are rotatably connected to the upper side of the base through the third rotating shaft. The rear end of each adjusting block is rotatably connected to the fourth rotating shaft through a bearing. The main and auxiliary foot pedal connecting rods are provided between the fourth rotating shafts. Adjusting assemblies are provided between the adjusting blocks and the longitudinally adjacent foot pedal columns. This device is compatible with multiple drive methods to realize the foot pedal braking and steering functions of aircraft, which can meet the training needs of simulators and trainers. The zero-clearance design inside the device ensures force sensitivity, and the stroke is consistent with that of the actual aircraft. At the same time, the device itself selects healthy, environmentally friendly, and reliable components. The surface treatment and process methods of the equipment adopt national military standard technology, which is environmentally friendly and durable.

[0006] Furthermore, the adjustment assembly includes a linkage arm, a slide rod, a slider, a five-axis rotating shaft, a linkage connecting rod, an annular seat, and a rotating ball. The linkage arm is respectively set on the opposite surfaces of two horizontally adjacent foot pedal columns. Slide rods are provided at both ends of the adjustment block, and sliders are slidably connected to the outer sides of the slide rods. The sliders are all fitted with the horizontally adjacent adjustment blocks. An annular seat is rotatably connected to the middle of each slider via a five-axis rotating shaft. A rotating ball is provided on the outer side of each annular seat. A linkage connecting rod is rotatably connected to the outer side of each linkage arm via a three-axis bearing. A semicircular groove is provided at the rear end of each linkage connecting rod, and the semicircular groove is rotatably connected to the vertically adjacent rotating ball.

[0007] Furthermore, the upper front end of the base is provided with horizontally symmetrical bearing seats two, and the middle of the rotating shaft two is provided with a connecting seat. The connecting seat and the vertically adjacent bearing seats two are rotatably connected to a brake reset cylinder through a rotating shaft six, so that the pedal in the control system simulation foot pedal can automatically reset after the foot is stepped on to simulate the aircraft brake.

[0008] Furthermore, the brake reset cylinder includes a cylinder shell, a piston rod, a piston, and a spring. The cylinder shells are respectively mounted on the rotating shaft six inside the bearing seat two. The piston rods are slidably connected inside the cylinder shells, and the lower ends of the piston rods are provided with pistons. The outer surfaces of the pistons are in slidable contact with the inner arc walls of the horizontally adjacent cylinder shells. Springs are provided between the top wall of the cylinder shells and the vertically adjacent pistons. The springs are movably sleeved on the outer arc surfaces of the horizontally adjacent piston rods. The spring reset force provides power to the self-reset of the pedal part after the simulated aircraft brakes.

[0009] Furthermore, the upper side of the base is provided with a shell, and the right rear end of the shell on the left side is provided with a fixing plate. A pedal reset cylinder is installed between the fixing plate and the horizontally adjacent rotating shaft four, so that the control system can automatically reset after simulating pedaling to turn.

[0010] Furthermore, a piston rod two is slidably connected inside the pedal reset cylinder. A circular seat is provided at the left end of the piston rod two. A rotating ball two is rotatably connected inside a semi-circular groove two on the left side of the circular seat. A connecting frame is provided on the spherical surface of the rotating ball two. The interior of the connecting frame is rotatably connected to a horizontally adjacent rotating shaft four through a bearing four. This allows the piston rod two to move synchronously through the semi-circular groove two and the rotating ball two as the adjusting block inside the simulated pedal of the control system rotates around the axis three.

[0011] Furthermore, it also includes angle sensors, which are respectively located on the upper middle part of the right adjustment block and on the left side of the rightmost connecting seat. The angle sensors are all bidirectionally electrically connected to an external microcontroller. The rightmost rotating shaft six and the rightmost rotating shaft three are both fixedly connected to the detection end of the horizontally adjacent angle sensor to detect and upload the steering angle corresponding to the pedaling of the control system.

[0012] Compared with the prior art, the beneficial effects of this utility model are: this control system simulates foot pedals, and has the following advantages:

[0013] 1. When using the control system to simulate foot pedals, the device uses components such as pedals, foot pedal steering mechanism and brake reset cylinder to realize the aircraft foot pedal braking and steering functions, which are compatible with multiple drive methods. It can meet the training needs of simulators and trainers, and the zero-gap design inside the device ensures force feel and the stroke is consistent with the actual aircraft.

[0014] 2. The control system features simulated foot pedals. The main body of the pedals is welded from steel, and the outer surface uses the same baking paint process as the cabin surface. The pedal surface is made of metal, making it sturdy and wear-resistant. The device itself selects healthy, environmentally friendly, and reliable components. The surface treatment and process methods of the equipment adopt national military standard technology, making it environmentally friendly and durable. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of this utility model;

[0016] Figure 2 This is a schematic diagram of the rear structure of this utility model;

[0017] Figure 3 This is a schematic diagram of the rear internal structure of this utility model;

[0018] Figure 4 This is a cross-sectional structural schematic diagram of the brake reset cylinder of this utility model;

[0019] Figure 5 This is an enlarged structural diagram of point A in this utility model;

[0020] Figure 6 This is an enlarged structural diagram of section B of the present invention.

[0021] In the diagram: 1. Base, 2. Bearing seat 1, 3. Rotating shaft 1, 4. Foot pedal column, 5. Rotating shaft 2, 6. Pedal, 7. Foot pedal steering mechanism, 71. Rotating shaft 3, 72. Adjusting block, 73. Rotating shaft 4, 74. Main and auxiliary foot pedal linkage, 75. Adjustment assembly, 751. Linkage arm, 752. Slide rod, 753. Slider, 754. Rotating shaft 5, 755. Linkage linkage, 756. Ring seat, 757. Rotating ball 1, 8. Bearing seat 2, 9. Brake reset cylinder, 91. Cylinder shell, 92. Piston rod, 93. Piston, 94. Spring, 10. Connecting seat, 11. Rotating shaft 6, 12. Pedal reset cylinder, 13. Piston rod 2, 14. Round seat, 15. Rotating ball 2, 16. Connecting frame, 17. Outer shell, 18. Angle sensor. Detailed Implementation

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] Please see Figure 1-6 This embodiment provides a technical solution: a simulated foot pedal for a control system, including a base 1, of which there are two. Each base 1 has three horizontally evenly distributed bearing seats 2 on its upper front end. The three horizontally adjacent bearing seats 2 are rotatably connected to two horizontally distributed foot pedal columns 4 through a pivot 3. The upper end of each foot pedal column 4 is rotatably connected to a pedal 6 through a pivot 5. The simulated foot pedal of the device has two sets, left and right, to simulate the foot pedal operation of the pilot and co-pilot on an aircraft. The main and co-pilot foot pedal linkage 74 of the device deflects itself and transmits the deflection command to the rudder through a steel cable, hydraulic system or electric fly-by-wire system. The vertical tail deflection is controlled by the rudder. The foot pedal body is welded from steel material, and the outer surface is treated with the same baking paint process as the cabin surface. The pedal surface is made of metal material, which is sturdy and wear-resistant. The device itself selects healthy, environmentally friendly and reliable components. The surface treatment and process method of the equipment adopt the national military standard technology, which is environmentally friendly and durable. It also includes a foot pedal steering mechanism 7.

[0024] Foot pedal steering mechanism 7: It includes a third rotating shaft 71, an adjusting block 72, a fourth rotating shaft 73, a main and auxiliary foot pedal connecting rod 74, and an adjusting component 75. The adjusting blocks 72 are rotatably connected to the upper side of the base 1 through the third rotating shaft 71. The rear end of each adjusting block 72 is rotatably connected to the fourth rotating shaft 73 through a bearing. The main and auxiliary foot pedal connecting rod 74 is provided between the fourth rotating shaft 73. The adjusting block 72 and the longitudinally adjacent foot pedal column 4 are both provided with adjusting components 75.

[0025] The adjustment assembly 75 includes a linkage arm 751, a slide rod 752, a slider 753, a rotating shaft 754, a linkage connecting rod 755, an annular seat 756, and a rotating ball 757. The linkage arm 751 is respectively set on the opposite surfaces of two horizontally adjacent foot pedal columns 4. The left and right ends of the adjustment block 72 are provided with slide rods 752. The outer side of the slide rod 752 is slidably connected to a slider 753. The slider 753 is installed in cooperation with the horizontally adjacent adjustment block 72. The middle part of the slider 753 is rotatably connected to an annular seat 756 through a rotating shaft 754. The outer side of the annular seat 756 is provided with a rotating ball 757. The outer side of the linkage arm 751 is rotatably connected to the linkage connecting rod 755 through a bearing 3. The rear end of the linkage connecting rod 755 is provided with a semi-circular groove 1. The semi-circular groove 1 is rotatably connected to the vertically adjacent rotating ball 757.

[0026] When using the simulated pedals of the control system, the initial state of the device is that pedal 6 is in a neutral position, and the rudder surface on the external fuselage vertical tail is also in a neutral position. When the simulator pushes forward on the left pedal 6 of any set of simulated pedals and simultaneously pushes backward on the right pedal 6 of the same set of simulated pedals, the left pedal 6 of that set of simulated pedals causes the corresponding pedal column 4 to rotate backward around the axis of the corresponding pivot 3, and the right pedal 6 of that set of simulated pedals rotates forward around the axis of the corresponding pivot 3. During this process, the pedal column 4 inside the set of simulated pedals drives the adjusting block 72 to rotate in the opposite direction around the axis of pivot 71 through the corresponding adjusting component 75. The adjusting block 72 drives the main and auxiliary pedal linkage 7 through pivot 73. 4. Moving horizontally to the left causes the external rudder to control the vertical tail fin to deflect to the left. During this process, the front end of the linkage 755 adaptively rotates around the axis of the corresponding linkage arm 751, the rear end of the linkage 755 adaptively rotates through the semicircular groove and the corresponding rotating ball 757, the ring seat 756 adaptively rotates around the axis of the corresponding rotating shaft 754, and the slider 753 adaptively slides longitudinally along the outer arc surface of the corresponding slider 752 and the side of the laterally adjacent adjusting block 72. When the simulated person pushes the left pedal 6 of any set of simulated pedals backward and pushes the right pedal 6 of the same set of simulated pedals forward, the external rudder controls the vertical tail fin to deflect to the right through the same principle.

[0027] After the device has been used for a period of time, the brake reset cylinder 9 and the rudder reset cylinder 12 should be disassembled and replaced as a whole to avoid the aging of the corresponding springs 94 or 2 inside the brake reset cylinder 9 and the rudder reset cylinder 12. The device is compatible with multiple drive methods to realize the aircraft foot brake and steering functions, which can meet the training needs of simulators and trainers. The zero-gap design inside the device ensures the force feel and the stroke is consistent with the actual aircraft.

[0028] The upper front end of the base 1 is provided with horizontally symmetrical bearing seats 2 8. The middle part of the rotating shaft 2 5 is provided with a connecting seat 10. The connecting seat 10 and the vertically adjacent bearing seats 2 8 are rotatably connected to a brake reset cylinder 9 through a rotating shaft 6 11. The brake reset cylinder 9 includes a cylinder shell 91, a piston rod 92, a piston 93 and a spring 94. The cylinder shell 91 is respectively set on the rotating shaft 6 11 inside the bearing seat 2 8. The piston rod 92 is slidably connected inside the cylinder shell 91. The lower end of the piston rod 92 is provided with a piston 93. The outer side of the piston 93 is in sliding contact with the inner arc wall of the horizontally adjacent cylinder shell 91. The top wall of the cylinder shell 91 and the vertically adjacent piston 93 are provided with a spring 94. The spring 94 is movably sleeved on the outer arc surface of the horizontally adjacent piston rod 92.

[0029] When simulating braking of an aircraft using a simulated foot pedal, the simulator's toes press pedal 6, causing pedal 6 to rotate the connecting seat 10 around the axis of the corresponding rotating shaft 5. During the downward movement of the rear end of the connecting seat 10, downward pressure is applied to the piston rod 92 through the rotating shaft 11. The piston rod 92, under pressure, drives the piston 93 to move vertically downward along the inner wall of the cylinder 91, thereby squeezing the hydraulic oil inside the cylinder 91. The oil port on the bottom wall of the cylinder 91 is connected to the piston part on the aircraft wheel brake actuator through an oil supply line. The hydraulic oil squeezing force causes the piston on the actuator to apply the brake. The mechanical pressure of the brake disc causes the aircraft to decelerate. During this process, the spring 94 is gradually stretched. After the aircraft braking simulation is completed, the simulator releases the pedal 6. The stretching and restoring force of the spring 94 causes the piston 93 to move the piston rod 92 upward along the inner wall of the cylinder shell 91 to reset, thereby automatically resetting and controlling the pedal 6. During this process, the internal structure of the rudder pedal reset cylinder 12 is the same as that of the brake reset cylinder 9. The sliding friction between the corresponding piston inside the rudder pedal reset cylinder 12 and the inner wall of the rudder pedal reset cylinder 12, as well as the spring 2 inside the rudder pedal reset cylinder 12, prevent the pedal column 4 from rotating around the corresponding pivot 3.

[0030] The upper side of the base 1 is provided with a shell 17. The right rear end of the shell 17 on the left side is provided with a fixing plate. A rudder reset cylinder 12 is installed between the fixing plate and the horizontally adjacent rotating shaft 73. A piston rod 13 is slidably connected inside the rudder reset cylinder 12. A circular seat 14 is provided at the left end of the piston rod 13. A rotating ball 15 is rotatably connected inside a semi-circular groove 2 on the left side of the circular seat 14. A connecting frame 16 is provided on the spherical surface of the rotating ball 15. The interior of the connecting frame 16 is rotatably connected to the horizontally adjacent rotating shaft 73 through a bearing 4. During the simulation of the vertical tail steering of the aircraft by the control system simulates the pedals, as the adjusting block 72 rotates around the axis of the corresponding rotating shaft 71, At this time, the piston rod 13 of the pedal reset cylinder 12 slides adaptively along the inner wall of the pedal reset cylinder 12 through the corresponding round seat 14, rotating ball 15, connecting frame 16 and rotating shaft 73. The connecting frame 16 rotates adaptively around the axis of rotating shaft 73 on the left side. The rotating ball 15 rotates adaptively with the semicircular groove 1 inside the round seat 14. The internal structure of the pedal reset cylinder 12 is the same as that of the brake reset cylinder 9. When the simulated person releases the forward or backward pedaling force applied to the pedal 6 later, the piston rod 13 inside the pedal reset cylinder 12 is automatically reset by the tension or compression force of the corresponding spring 2 inside the pedal reset cylinder 12, thereby automatically resetting the pedal 6 to the initial state.

[0031] It also includes angle sensors 18, which are respectively located on the upper middle part of the right adjustment block 72 and on the left side of the rightmost connecting seat 10. The angle sensors 18 are all bidirectionally electrically connected to the external microcontroller. The rightmost rotating shaft 11 and the rightmost rotating shaft 71 are both fixedly connected to the detection end of the horizontally adjacent angle sensors 18. When using the control system to simulate pedals, the angle sensors 18 are activated by the external microcontroller. The upper angle sensor 18 adopts a high-performance integrated magnetic sensitive element. It uses the non-contact characteristic of magnetic signal sensing to measure the rotation angle of the connecting seat 10 around the axis of the rotating shaft 11, and measures the pedal 6 braking angle. The measurement result is transmitted to the external microcontroller in the form of an electrical signal, so that the simulator can understand the toe pressing depth of the pedal part of the device through the external microcontroller. Through the lower angle sensor 18, the simulator can understand the deflection angle of the pedal part when the vertical tail wing is adjusted by the external microcontroller using the same principle.

[0032] The working principle of the simulated foot pedal of the control system provided by this utility model is as follows: The simulated foot pedal of the device has two sets, left and right, to simulate the foot pedal operation of the main and co-pilots on the aircraft. The main and co-pilot foot pedal linkage 74 of the device deflects itself and transmits the deflection command to the rudder through the steel cable, hydraulic system or electric fly-by-wire system. The rudder controls the deflection of the vertical tail. When the simulated foot pedal is used to simulate braking of the aircraft flight, the simulated person presses the pedal 6 with their toes, causing the pedal 6 to drive the connecting seat 10 to rotate around the axis of the corresponding rotating shaft 5. During the downward movement of the rear end of the connecting seat 10, the piston rod 92 is subjected to downward pressure through the rotating shaft 6 11. The piston rod 92 is compressed and drives the piston 93 to move vertically downward along the inner wall of the cylinder shell 91, thereby controlling the piston 93 to move downward. The hydraulic oil inside the cylinder shell 91 is squeezed. The oil port on the bottom wall of the cylinder shell 91 is connected to the piston part on the aircraft wheel brake actuator through the oil supply pipeline. The hydraulic oil squeezing force causes the piston on the actuator to mechanically squeeze the brake pads onto the brake disc, thereby decelerating the aircraft. During this process, the spring 94 is gradually stretched. After the aircraft braking simulation is completed, the simulator releases the pedal 6. The stretching and restoring force of the spring 94 causes the piston 93 to move the piston rod 92 upward along the inner wall of the cylinder shell 91 to reset, thereby automatically resetting and controlling the pedal 6. During this process, the internal structure of the rudder pedal reset cylinder 12 is the same as that of the brake reset cylinder 9. The sliding friction between the corresponding piston inside the rudder pedal reset cylinder 12 and the inner wall of the rudder pedal reset cylinder 12, as well as the internal structure of the rudder pedal reset cylinder 12, are controlled. Spring 2 prevents the pedal column 4 from rotating around the corresponding pivot 3. When using the control system to simulate pedals, the initial state of the device is that pedal 6 is in a neutral position, and the rudder surface on the external fuselage vertical tail is also in a neutral position. When the simulated person pushes forward on the left pedal 6 of any set of simulated pedals and simultaneously pushes backward on the right pedal 6 of the same set of simulated pedals, the left pedal 6 of the set of simulated pedals causes the corresponding pedal column 4 to rotate backward around the corresponding pivot 3, and the right pedal 6 of the set of simulated pedals rotates forward around the corresponding pivot 3. During this process, the pedal column 4 inside the set of simulated pedals drives the adjusting block 72 to rotate in the opposite direction around the pivot 3 71 through the corresponding adjusting component 75. The adjusting block 72 rotates through the pivot 71. Axis 4 73 drives the main and auxiliary foot pedal linkage 74 to move horizontally to the left, causing the external rudder to control the vertical tail fin to deflect to the left. During this process, the front ends of the linkage linkage 755 adaptively rotate around the axis of the corresponding linkage arm 751, the rear ends of the linkage linkage 755 adaptively rotate through the semicircular groove and the corresponding rotating ball 757, the annular seat 756 adaptively rotates around the axis of the corresponding rotating shaft 754, and the slider 753 adaptively slides longitudinally along the outer arc surface of the corresponding slider 752 and the side of the laterally adjacent adjusting block 72. When the simulated person pushes the left pedal 6 of any set of simulated foot pedals backward and simultaneously pushes the right pedal 6 of the same set of simulated foot pedals forward, the external rudder controls the vertical tail fin to deflect to the right through the same principle.Simultaneously, during the simulation of the vertical tail steering of the aircraft using the control system's simulated pedals, as the adjusting block 72 rotates around the corresponding pivot 71, the piston rod 13 of the rudder reset cylinder 12 adaptively slides along the inner wall of the rudder reset cylinder 12 via the corresponding circular seat 14, rotating ball 15, connecting frame 16, and pivot 73. The connecting frame 16 adaptively rotates around the pivot 73 on the left side, and the rotating ball 15 adaptively rotates with the semicircular groove 1 inside the circular seat 14. The rudder reset cylinder 12 has the same internal structure as the brake reset cylinder 9. Later, when the simulated user releases the forward or backward pressing force applied to the pedal 6, the piston rod 13 inside the rudder reset cylinder 12 automatically resets due to the tension or compression force of the corresponding spring 2 inside the rudder reset cylinder 12, thereby automatically resetting the pedal 6 to its initial state. After the device has been used for a period of time, The brake reset cylinder 9 and the rudder reset cylinder 12 are disassembled and replaced as a whole to prevent the corresponding springs 94 or 2 inside the brake reset cylinder 9 and rudder reset cylinder 12 from aging. Simultaneously, when using the control system to simulate pedals, the external microcontroller activates the angle sensor 18. The upper angle sensor 18 uses a high-performance integrated magnetic sensitive element, utilizing the non-contact characteristic of magnetic signal induction to measure the rotation angle of the connecting seat 10 around the axis of the rotating shaft 11, and to measure the braking angle of the brake pedal 6. The measurement results are transmitted to the external microcontroller as electrical signals, allowing the simulator user to understand the toe-pressing depth of the pedals. Similarly, the lower angle sensor 18, using the same principle, allows the simulator user to understand the corresponding deflection angle of the pedals when adjusting the vertical tail fin.

[0033] It is worth noting that the angle sensor 18 disclosed in the above embodiments can be an HSM22M multi-turn non-contact magnetic potentiometer, and the external microcontroller controls the operation of the angle sensor 18 using methods commonly used in the prior art.

[0034] The above description is merely an embodiment of this utility model and does not limit the patent scope of this utility model. Any equivalent structural or procedural transformations made based on the content of this utility model specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this utility model.

Claims

1. A simulated pedal for a control system, comprising a base (1), wherein there are two bases (1), each base (1) having three horizontally evenly distributed bearing seats (2) at its upper front end, and two horizontally distributed pedal columns (4) rotatably connected between the three horizontally adjacent bearing seats (2) via a pivot (3), and a pedal (6) rotatably connected to the upper end of each pedal column (4) via a pivot (5), characterized in that: It also includes a foot pedal steering mechanism (7); The pedal steering mechanism (7) includes a rotating shaft three (71), an adjusting block (72), a rotating shaft four (73), a main and auxiliary pedal connecting rod (74), and an adjusting component (75). The adjusting blocks (72) are rotatably connected to the upper side of the base (1) through the rotating shaft three (71). The rear end of the adjusting blocks (72) is rotatably connected to the rotating shaft four (73) through a bearing one. The main and auxiliary pedal connecting rods (74) are provided between the rotating shafts four (73). The adjusting blocks (72) and the longitudinally adjacent pedal uprights (4) are provided with adjusting components (75).

2. The simulated pedal of the control system according to claim 1, characterized in that: The adjustment assembly (75) includes a linkage arm (751), a slide rod (752), a slider (753), a rotating shaft (754), a linkage link (755), an annular seat (756), and a rotating ball (757). The linkage arm (751) is respectively set on the opposite surfaces of two horizontally adjacent foot pedal columns (4). The left and right ends of the adjustment block (72) are provided with slide rods (752), and sliders (753) are slidably connected to the outer sides of the slide rods (752). 753) are all installed in conjunction with the horizontally adjacent adjustment block (72). The middle part of the slider (753) is rotatably connected to the ring seat (756) through the rotating shaft five (754). The outer side of the ring seat (756) is provided with the rotating ball one (757). The outer side of the linkage arm (751) is rotatably connected to the linkage rod (755) through the bearing three. The rear end of the linkage rod (755) is provided with the semi-circular groove one. The semi-circular groove one is rotatably connected to the vertically adjacent rotating ball one (757).

3. The simulated foot pedal of the control system according to claim 1, characterized in that: The upper front end of the base (1) is provided with horizontally symmetrical bearing seats (8), and the middle part of the rotating shaft (5) is provided with a connecting seat (10). The connecting seat (10) and the vertically adjacent bearing seats (8) are rotatably connected to the brake reset cylinder (9) through the rotating shaft (11).

4. The simulated pedal of the control system according to claim 3, characterized in that: The brake reset cylinder (9) includes a cylinder shell (91), a piston rod (92), a piston (93), and a spring (94). The cylinder shell (91) is respectively set on the rotating shaft six (11) in the bearing seat two (8). The piston rod (92) is slidably connected inside the cylinder shell (91). The lower end of the piston rod (92) is provided with a piston (93). The outer side of the piston (93) is in sliding contact with the inner arc wall of the horizontally adjacent cylinder shell (91). The top wall of the cylinder shell (91) is provided with a spring (94) between it and the vertically adjacent piston (93). The spring (94) is movably sleeved on the outer arc surface of the horizontally adjacent piston rod (92).

5. The simulated pedal of the control system according to claim 1, characterized in that: The upper side of the base (1) is provided with a shell (17). The right rear end of the shell (17) on the left side is provided with a fixing plate. The fixing plate and the horizontally adjacent rotating shaft four (73) are equipped with a rudder reset cylinder (12).

6. The simulated foot pedal of the control system according to claim 5, characterized in that: The piston rod 2 (13) is slidably connected inside the rudder reset cylinder (12). A round seat (14) is provided at the left end of the piston rod 2 (13). A rotating ball 2 (15) is rotatably connected inside the semi-circular groove 2 on the left side of the round seat (14). A connecting frame (16) is provided on the spherical surface of the rotating ball 2 (15). The interior of the connecting frame (16) is rotatably connected to the horizontally adjacent rotating shaft 4 (73) through the bearing 4.

7. The simulated foot pedal of the control system according to claim 1, characterized in that: It also includes an angle sensor (18), which is respectively located on the upper middle part of the right adjustment block (72) and the left side of the rightmost connecting seat (10). The angle sensors (18) are all bidirectionally electrically connected to an external microcontroller. The rightmost rotating shaft six (11) and the rightmost rotating shaft three (71) are both fixedly connected to the detection end of the horizontally adjacent angle sensor (18).

Images