Tool for simulating various states of airplane pedal

Abstract

The utility model provides a tool for simulating various states of an airplane pedal. Comprising a bearing bottom plate, a placing table fixed to the right side of the upper end face of the bearing bottom plate, two pedal angle adjusting assemblies symmetrically arranged on the two sides of the placing table, a supporting table fixed to the left side of the upper end face of the bearing bottom plate, and two pedal pressure applying units arranged on the supporting table in a front-back parallel mode. The placing table is used for placing an aircraft pedal to be tested; the pedal angle adjusting assembly is connected with the side faces of bases of a left pedal and a right pedal of a to-be-tested aircraft pedal respectively, and the overturning angles of the pedals are adjusted. The pedal pressure applying unit comprises a pressure applying rod and a regulation and control assembly for regulating the inclination angle and the telescopic distance of the pressure applying rod; the right ends of the pressure applying rods of the two pressure applying units abut against a left pedal and a right pedal of the to-be-tested airplane pedal respectively. The tool provided by the utility model can simulate the states of pedals at different angles in multiple directions in actual flight.

Description

Technical Field

[0001] The utility model belongs to the technical field of aerospace equipment detection, in particular to a tool for simulating multiple states of aircraft pedals. Background Art

[0002] Aircraft pedals primarily control aircraft yaw, nosewheel steering, and wheel braking, making them one of the aircraft's key primary control systems. During actual flight, these pedals are in multiple positions at different angles, requiring pilots to control the aircraft at various angles. To obtain experimental data on the pedals in various positions for research, a simulation of actual flight is required, simulating the pedals at various angles. Therefore, a tooling system is needed that can simulate the pedals in multiple positions during actual flight. Utility Model Content

[0003] In view of this, in order to solve the above technical problems, the utility model proposes a tooling for simulating multiple states of aircraft pedals, which can control the aircraft pedals to different angles and apply pressure to the pedals at the same time, simulating the state of the pilot controlling the pedals during actual flight, and providing assistance to researchers in obtaining corresponding experimental data.

[0004] In order to achieve the above-mentioned purpose, the technical solution of the utility model is achieved as follows:

[0005] A tool for simulating multiple states of aircraft pedals, comprising:

[0006] load-bearing base plate;

[0007] A placement platform, fixed to the right side of the upper end surface of the supporting base plate, for placing the aircraft pedal to be tested;

[0008] Pedal angle adjustment components, there are two pedal angle adjustment components, symmetrically arranged on both sides of the placement platform; the two pedal angle adjustment components are respectively connected to the base sides of the left and right pedals of the aircraft to be tested to adjust the flip angle of the pedals;

[0009] A support platform, the support platform is fixed to the left side of the upper end surface of the bearing base plate;

[0010] There are two pedal pressure units, which are arranged in parallel on the support platform in front and back; the pedal pressure unit includes a pressure rod and a control component for adjusting the inclination angle and telescopic distance of the pressure rod; the right ends of the pressure rods of the two pressure units are respectively abutted against the left and right pedals of the aircraft to be tested.

[0011] The aircraft pedal is equipped with left and right pedals. When simulating its various states, first place the aircraft pedal on the placement table, and then connect the base sides of the left and right pedals to the two pedal angle adjustment components. The pedal adjustment components can adjust the rotation angle of the aircraft pedal so that the left and right pedals are at different angles with the horizontal plane; the right ends of the two pressure rods are respectively in contact with the plate surfaces of the left and right pedals. Under the action of the control components, the pressure rods can be adjusted to an inclination angle consistent with the rotation angle of the aircraft pedal, and then under the action of the control components, they move toward the left and right pedals, thereby applying pressure to the left and right pedals to simulate the pressure state of the pilot's feet.

[0012] Furthermore, the bearing base plate includes a bearing mounting plate and supporting legs arranged at the bottom of the bearing mounting plate.

[0013] Furthermore, the placement platform includes a sliding execution base fixed on the supporting base, a vertical lifting base arranged on the sliding execution base for sliding along the left and right directions, and a pedal placement seat installed on the vertical lifting seat and capable of adjusting the height along the vertical direction; the two pedal angle adjustment components are symmetrically arranged on both sides of the pedal placement seat.

[0014] The pedal placement seat is used to place the aircraft pedals to be tested before the test, which is convenient for connecting the left and right pedals with the pedal angle adjustment assembly; the pedal placement seat can adjust the height by the lifting function of the lifting seat, and can adjust the position in the left and right directions by sliding the execution base.

[0015] Furthermore, the vertical lifting seat includes a vertical frame, a vertical screw installed on the vertical frame, and a vertical screw rotating handwheel installed on the top of the vertical screw; the right end of the pedal placement seat is connected to the screw nut of the vertical screw.

[0016] The vertical screw rod rotates the hand wheel to rotate, driving the vertical screw to rotate, thereby causing the screw nut thereon to move in the vertical direction, and finally driving the vertical movement of the pedal placement seat.

[0017] Furthermore, the pedal angle adjustment assembly includes a sliding execution base 2 fixed on the bearing base, a mounting bracket slidingly arranged on the sliding execution base 2 along the front-rear direction, a flange installed on the mounting bracket facing the pedal placement seat, a fixed shaft fixed at the center position of the flange, a rotating sleeve sleeved on the fixed shaft, a rotating rod fixed at one end on the rotating sleeve, a connecting plate connected to the other end of the rotating rod at one end, and a pedal base connecting component fixed at the other end of the connecting plate; the rotating sleeve and the fixed shaft are fixed by a locking bolt, and the rotating sleeve can be rotated by loosening the locking bolt; the pedal base connecting component is used to connect the base side of the pedal.

[0018] The pedal base is connected to the pedal base connecting component. Loosening the locking bolt can rotate the rotating shaft sleeve, thereby causing the rotating rod, the connecting plate, and the pedal base connecting component to rotate with the flange as the center of the circle, and finally realizing the rotation of the aircraft pedal connected to the pedal base connecting component, thereby realizing angle adjustment; tightening the locking bolt fixes the rotating shaft sleeve, so that the pedal angle adjustment assembly stops rotating, and thus fixes the position of the aircraft pedal so that it is at the set rotation angle.

[0019] Furthermore, the sliding execution base 1 and the sliding execution base 2 both include a bottom mounting base installed on the bearing base plate, a screw installed on the bottom mounting base, a screw rotating handwheel connected to the head end of the screw, and slide rails arranged on both sides of the screw; the bottom of the vertical lifting base is connected to the screw nut on the screw of the sliding execution base 1, and the two ends of the bottom of the vertical lifting base are slidably connected to the corresponding slide rails; the bottom of the mounting frame is connected to the screw nut on the screw of the sliding execution base 2, and the two ends of the bottom of the mounting frame are slidably connected to the corresponding slide rails.

[0020] The screw is rotated by the hand wheel, which drives the screw to rotate, thereby causing the screw nut on it to move along the direction in which the screw is set, and finally drives the corresponding vertical lifting seat and mounting frame to move.

[0021] Furthermore, the regulating component includes a mounting plate, a permanent magnet table, and a lifting mechanism; a support mounting seat is fixed on the mounting plate, and the bottom of the permanent magnet table is rotatably connected to the support mounting seat through a pin shaft; the lifting mechanism is installed on the left side of the upper end surface of the mounting plate, and the lifting end of the lifting mechanism is connected to the left end of the permanent magnet table; a sliding plate that can slide in the left and right directions is provided on the permanent magnet table; the pressure rod is arranged parallel to the upper end surface of the permanent magnet table, the left end of the pressure rod is connected to the sliding plate, and the right end of the pressure rod is provided with a pedal connecting component, which abuts against the plate surface of the pedal.

[0022] The lifting and lowering adjustment of the lifting mechanism can control the tilt angle of the permanent magnetic table, thereby adjusting the tilt angle of the pressure rod so that the pressure direction of the pressure rod is consistent with the pedal of the aircraft to be tested; the permanent magnetic table can control the movement of the pressure rod in the tilt direction, so that the pressure rod applies force to the connected pedal, simulating the pedaling process.

[0023] Furthermore, a second support mounting seat is fixed to the left end of the mounting plate, and the fixing portion of the lifting mechanism is rotatably connected to the second support mounting seat via a pin.

[0024] Furthermore, the support platform includes a base, a screw 1 and a screw 2 arranged in the middle position of the base and along the front-to-back direction, a screw 1 rotating handwheel installed on the top of the screw 1, a screw 2 rotating handwheel installed on the top of the screw 2, and a slideway arranged at the left and right ends of the base and along the front-to-back direction; the bottom of the mounting plate of one of the regulating components is connected to the screw nut of the screw 1, and the bottom of the mounting plate of the other regulating component is connected to the screw nut of the screw 2; the left and right ends of the bottom of the two mounting plates are slidably connected to the slideways on both sides.

[0025] The hand wheel of screw rod 1 (2) rotates, driving screw rod 1 (2) to rotate, so that the screw nut on it moves along the setting direction of screw rod 1 (2), driving the connected regulating component to move along the front and rear direction, adjusting the position so that the pressure rod and the pedal can correspond.

[0026] Compared with the prior art, the tooling for simulating multiple states of aircraft pedals described in the present invention has the following advantages:

[0027] The tooling for simulating various states of aircraft pedals disclosed in the utility model adjusts the angle of the aircraft pedals through a pedal angle adjustment component to simulate the various angle states of the aircraft pedals in actual flight; and applies pressure to the left and right pedals of the aircraft pedals through a pedal pressure unit to simulate the state of footsteps stepping on the pedals when the aircraft pedals are at various angles. The structural design is reasonable. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The accompanying drawings, which constitute part of the present invention, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0029] Figure 1 This is a schematic structural diagram of a tool for simulating multiple states of aircraft pedals according to an embodiment of the present utility model;

[0030] Figure 2 This is a schematic structural diagram from another angle of the tooling for simulating multiple states of aircraft pedals according to an embodiment of the present utility model;

[0031] Figure 3 This is a structural diagram of another angle of the tooling for simulating multiple states of aircraft pedals according to an embodiment of the utility model

[0032] Figure 4 This is a structural schematic diagram of the rear angle of the tooling for simulating various states of aircraft pedals according to an embodiment of the present utility model.

[0033] Description of reference numerals:

[0034] 1-Bearing base, 2-Placing table, 3-Pedal angle adjustment assembly, 4-Support platform, 5-Pedal pressure unit, 6-Sliding execution base 1, 7-Vertical lifting seat, 8-Pedal placement seat, 9-Vertical frame, 10-Vertical screw, 11-Vertical screw rotating handwheel, 12-Sliding execution base 2, 13-Mounting frame, 14-Flange, 15-Fixed shaft, 16-Rotating sleeve, 17-Rotating rod, 18-Connecting plate, 19-Pedal bottom Seat connecting component, 20-bottom mounting seat, 21-screw, 22-screw rotating handwheel, 23-slide rail, 24-base, 25-screw one, 26-screw two, 27-screw one rotating handwheel, 28-screw two rotating handwheel, 29-slide, 30-pressure rod, 31-mounting plate, 32-permanent magnet table, 33-lifting mechanism, 34-support mounting seat one, 35-support mounting seat two, 36-sliding plate, 37-pedal connecting component. DETAILED DESCRIPTION

[0035] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features therein can be combined with each other.

[0036] In the description of the present invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limiting the present invention. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0037] In the description of this utility model, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; mechanical connections, electrical connections; direct connections, indirect connections through an intermediate medium, and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on specific circumstances.

[0038] The present invention will be described in detail below with reference to the accompanying drawings and in combination with embodiments.

[0039] As shown in the figure, a tool for simulating various states of aircraft pedals includes a load-bearing base plate 1, a placement table 2, a pedal angle adjustment assembly 3, a support table 4, and a pedal pressure unit 5;

[0040] The load-bearing base plate 1 includes a load-bearing mounting plate and a support leg provided at the bottom of the load-bearing mounting plate;

[0041] The placement platform 2 is fixed to the right side of the upper end surface of the load-bearing base plate 1 and is used to place the pedals of the aircraft to be tested. The placement platform 2 includes a sliding execution base 6 fixed to the load-bearing base plate 1, a vertical lifting seat 7 that slides on the sliding execution base 6 in the left-right direction, and a pedal placement seat 8 mounted on the vertical lifting seat 7 and adjustable in height in the vertical direction. The vertical lifting seat 7 includes a vertical frame 9, a vertical screw 10 mounted on the vertical frame 9, and a vertical screw rotation handwheel 11 mounted on the top of the vertical screw 10. The right end of the pedal placement seat 8 is connected to the screw nut of the vertical screw 10.

[0042] There are two pedal angle adjustment assemblies 3, which are symmetrically arranged on both sides of the pedal placement seat 8; the two pedal angle adjustment assemblies 3 are respectively connected to the base sides of the left and right pedals of the aircraft to be tested to adjust the flip angle of the pedal; the pedal angle adjustment assembly 3 includes a sliding execution base 2 12 fixed on the bearing base 1, a mounting bracket 13 slidably arranged on the sliding execution base 2 12 along the front and rear directions, a flange 14 mounted on the mounting bracket 13 facing the pedal placement seat, a fixed shaft 15 fixed at the center position of the flange 14, a rotating shaft sleeve 16 sleeved on the fixed shaft 15, a rotating rod 17 fixed at one end to the rotating shaft sleeve 16, a connecting plate 18 connected at one end to the other end of the rotating rod 17, and a pedal base connecting member 19 fixed at the other end of the connecting plate 18; the rotating shaft sleeve 16 and the fixed shaft 15 are fixed by a locking bolt, and the rotating shaft sleeve 16 can be rotated by loosening the locking bolt; the pedal base connecting member 19 is used to connect the base side of the pedal;

[0043] The sliding execution base 1 6 and the sliding execution base 2 12 both include a bottom mounting base 20 mounted on the bearing base 1, a lead screw 21 mounted on the bottom mounting base 20, a lead screw rotating handwheel 22 connected to the head end of the lead screw 21, and slide rails 23 provided on both sides of the lead screw 21; the bottom of the vertical lifting base 7 is connected to the lead screw nut on the lead screw 21 of the sliding execution base 1 6, and the two ends of the bottom of the vertical lifting base 7 are slidably connected to the corresponding slide rails 23; the bottom of the mounting frame 13 is connected to the lead screw nut on the lead screw 21 of the sliding execution base 2 12, and the two ends of the bottom of the mounting frame 13 are slidably connected to the corresponding slide rails 23;

[0044] The support platform 4 is fixed to the left side of the upper end surface of the supporting base plate 1; the support platform 2 includes a base 24, a screw 1 25 provided in the middle position of the base 24 and arranged in the front-to-back direction, a screw 2 26, a screw 1 rotation handwheel 27 installed on the top of the screw 1 25, a screw 2 rotation handwheel 28 installed on the top of the screw 2 26, and a slide 29 provided at the left and right ends of the base 24 and arranged in the front-to-back direction;

[0045] There are two pedal pressure units 5, which are arranged on the support platform 4 in parallel front and back; the pedal pressure unit 6 includes a pressure rod 30 and a regulating component for adjusting the tilt angle and telescopic distance of the pressure rod 30; the regulating component includes a mounting plate 31, a permanent magnet table 32, and a lifting mechanism 33; a support mounting seat 1 34 is fixed on the mounting plate 31, and the bottom of the permanent magnet table 32 is rotatably connected to the support mounting seat 1 34 through a pin; a support mounting seat 2 35 is fixed to the left end of the mounting plate 31, and the fixed part of the lifting mechanism 33 is rotatably connected to the support mounting seat 2 35 through a pin; the lifting end of the lifting mechanism 33 is connected to the left end of the permanent magnet table 32; the permanent magnet table 32 is provided with a support mounting seat 34 along the support mounting seat 34; A sliding plate 36 that can slide in the left and right directions; a pressure rod 30 is arranged parallel to the upper end surface of the permanent magnet table 32, the left end of the pressure rod 30 is connected to the sliding plate 36, and the right end of the pressure rod 30 is provided with a pedal connecting component 37, and the pedal connecting component 37 abuts against the plate surface of the pedal; the right ends of the pressure rods 30 of the two pedal pressure units 5 respectively abut against the left and right pedals of the aircraft to be tested; the bottom of the mounting plate 31 of one regulating component is connected to the screw nut of screw one 25, and the bottom of the mounting plate 31 of the other regulating component is connected to the screw nut of screw two 26; the left and right ends of the bottom of the two mounting plates 31 are slidably connected to the slideways 29 on both sides.

[0046] The working process of the tooling for simulating multiple states of aircraft pedals described in the utility model is as follows:

[0047] Adjust the height of the placement table 2 and place the aircraft pedal to be tested on the placement table 2; adjust the positions of the two pedal angle adjustment assemblies 3 to correspond to the two pedal bases of the aircraft pedal, and connect the base sides of the left and right pedals to the two pedal angle adjustment assemblies 3; loosen the locking bolt and rotate the rotating shaft sleeve 16 to adjust the rotation angle of the aircraft pedal, tighten the locking bolt to fix the rotating shaft sleeve 16 so that the pedal angle adjustment assembly 3 stops rotating and the position of the aircraft pedal is fixed; adjust the inclination angle of the permanent magnetic platform 32 through the lifting mechanism 33, thereby adjusting the inclination angle of the pressure rod 30, so that the pressure direction of the pressure rod 30 is consistent with the pedal of the aircraft pedal to be tested, and the right ends of the two pressure rods 30 are respectively abutted against the plate surfaces of the left and right pedals. The permanent magnetic platform 32 controls the movement of the pressure rod 30 in the inclination direction, so that the pressure rod 30 applies force to the connected pedals to simulate the pedaling process.

[0048] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A tool for simulating multiple states of aircraft pedals, characterized in that: include: load-bearing base plate; A placement platform, fixed to the right side of the upper end surface of the supporting base plate, for placing the aircraft pedal to be tested; Pedal angle adjustment components, there are two pedal angle adjustment components, symmetrically arranged on both sides of the placement table; The two pedal angle adjustment assemblies are respectively connected to the base sides of the left and right pedals of the aircraft to be tested to adjust the flip angle of the pedals; A support platform, the support platform is fixed to the left side of the upper end surface of the bearing base plate; There are two pedal pressure units, which are arranged in parallel on the support platform in front and back; the pedal pressure unit includes a pressure rod and a control component for adjusting the inclination angle and telescopic distance of the pressure rod; the right ends of the pressure rods of the two pressure units are respectively abutted against the left and right pedals of the aircraft to be tested.

2. The tool for simulating multiple states of aircraft pedals according to claim 1, characterized in that: The bearing base plate includes a bearing mounting plate and supporting legs arranged at the bottom of the bearing mounting plate.

3. The tool for simulating multiple states of aircraft pedals according to claim 1, characterized in that: The placement platform includes a sliding execution base fixed on the bearing base, a vertical lifting base that slides on the sliding execution base along the left and right directions, and a pedal placement base installed on the vertical lifting base and capable of adjusting the height along the vertical direction; the two pedal angle adjustment components are symmetrically arranged on both sides of the pedal placement base.

4. The tool for simulating multiple states of aircraft pedals according to claim 3, characterized in that: The vertical lifting seat includes a vertical frame, a vertical screw installed on the vertical frame, and a vertical screw rotating handwheel installed on the top of the vertical screw; the right end of the pedal placement seat is connected to the screw nut of the vertical screw.

5. The tool for simulating multiple states of aircraft pedals according to claim 3, characterized in that: The pedal angle adjustment assembly includes a sliding execution base 2 fixed on the bearing base, a mounting bracket slidably arranged on the sliding execution base 2 along the front-rear direction, a flange installed on the mounting bracket facing the pedal placement seat, a fixed shaft fixed at the center position of the flange, a rotating sleeve sleeved on the fixed shaft, a rotating rod fixed at one end on the rotating sleeve, a connecting plate connected at one end to the other end of the rotating rod, and a pedal base connecting member fixed at the other end of the connecting plate; the rotating sleeve and the fixed shaft are fixed by a locking bolt, and the rotating sleeve can be rotated by loosening the locking bolt; the pedal base connecting member is used to connect the base side of the pedal.

6. The tool for simulating multiple states of aircraft pedals according to claim 5, characterized in that: The sliding execution base 1 and the sliding execution base 2 both include a bottom mounting base mounted on the bearing base, a lead screw mounted on the bottom mounting base, a lead screw rotating handwheel connected to the head end of the lead screw, and slide rails arranged on both sides of the lead screw; the bottom of the vertical lifting base is connected to the lead screw nut on the lead screw of the sliding execution base 1, and the two ends of the bottom of the vertical lifting base are slidably connected to the corresponding slide rails; the bottom of the mounting frame is connected to the lead screw nut on the lead screw of the sliding execution base 2, and the two ends of the bottom of the mounting frame are slidably connected to the corresponding slide rails.

7. The tool for simulating multiple states of aircraft pedals according to claim 1, characterized in that: The regulating component includes a mounting plate, a permanent magnet table, and a lifting mechanism; a support mounting seat is fixed to the mounting plate, and the bottom of the permanent magnet table is rotatably connected to the support mounting seat through a pin shaft; the lifting mechanism is installed on the left side of the upper end surface of the mounting plate, and the lifting end of the lifting mechanism is connected to the left end of the permanent magnet table; a sliding plate that can slide in the left and right directions is provided on the permanent magnet table; the pressure rod is arranged parallel to the upper end surface of the permanent magnet table, the left end of the pressure rod is connected to the sliding plate, and the right end of the pressure rod is provided with a pedal connecting component.

8. The tool for simulating multiple states of aircraft pedals according to claim 7, characterized in that: A second support mounting seat is fixed to the left end of the mounting plate, and the fixing portion of the lifting mechanism is rotatably connected to the second support mounting seat via a pin shaft.

9. The tool for simulating multiple states of aircraft pedals according to claim 7, characterized in that: The support platform includes a base, a lead screw 1 and a lead screw 2 which are arranged in the middle position of the base and along the front-to-back direction, and a slideway which is arranged at the left and right ends of the base and along the front-to-back direction; the bottom of the mounting plate of one regulating component is connected to the lead screw nut of the lead screw 1, and the bottom of the mounting plate of the other regulating component is connected to the lead screw nut of the lead screw 2; the left and right ends of the bottom of the two mounting plates are slidably connected to the slideways on both sides.

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