Aircraft weighing scale with anti-deformation structure

Abstract

The utility model discloses an aircraft weighing scale with an anti-deformation structure, which relates to the technical field of airport ground service and comprises a protective shell, and the inner side and the outer side of the protective shell are jointly provided with a buffer protection mechanism. The buffer protection mechanism comprises a fixing frame, a buffer box is arranged in the protection shell, a honeycomb grid is arranged above the buffer box, two sets of hydraulic dampers are fixedly connected to the inner wall of the buffer box, the telescopic end of each hydraulic damper is fixedly connected with the bottom face of the honeycomb grid, and a bottom plate is fixedly connected to the inner bottom wall of the buffer box. A first fixed seat, a second fixed seat and two movable seats are fixedly connected to the upper surface of the bottom plate, a movable sliding plate is movably hinged to the inner wall of each movable seat, a bearing plate is arranged below the honeycomb-shaped grid, two movable plates are movably hinged to the inner wall of the bearing plate, and through the buffer protection mechanism, the aircraft weighing scale can be buffered and protected; and the problem of deformation of the weighing scale in the use process is avoided.

Description

TECHNICAL FIELD

[0001] The utility model relates to airport ground service technical field, concretely is a kind of aircraft weighing scale with anti-deformation structure. BACKGROUND

[0002] Airport ground service is an important additional service appearing in all levels of civil, military air station since the construction and operation of self-owned air transport service and major air station (airport), and is closely related to the operation of air station and indispensable, all civil, commercial and military aircraft need the service of ground service, from the moment when aircraft enters the apron to the moment when aircraft leaves the apron and enters the taxiway, all logistics services (fueling, water supply, passenger disembarking and boarding, luggage handling, aircraft meal loading, aircraft body cleaning, waste disposal, etc.) during parking are the work responsibility range of airport ground service personnel, and the measurement of the weight of aircraft also belongs to one of the tasks of airport ground service.

[0003] Airport ground service often involves the measurement of the weight of aircraft, and the weight of aircraft is generally measured by aircraft weighing scale, and the existing device generally moves the wheels of aircraft to the measuring equipment through slope to measure the weight of aircraft, which is not only time-consuming and laborious, but also the measuring equipment suddenly increases the vertical stress when moving from slope to the surface of measuring equipment, and the measuring equipment is easily deformed due to the sudden large pressure, thereby reducing the use effect of the device. UTILITY MODEL CONTENT

[0004] The utility model aims at making up for the deficiency of prior art, and provides an aircraft weighing scale with anti-deformation structure.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical scheme: an aircraft weighing scale with anti-deformation structure, comprising a protective shell, the inner side of the protective shell and the outer side of the protective shell are jointly provided with a buffer protection mechanism.

[0006] The buffer protection mechanism includes a fixed frame, the inside of the protection shell is provided with a buffer box, the upper part of the buffer box is provided with a honeycomb grid, the inner wall of the buffer box is fixedly connected with two groups of hydraulic dampers, the telescopic end of each hydraulic damper is fixedly connected with the bottom surface of the honeycomb grid, the inner bottom wall of the buffer box is fixedly connected with a bottom plate, the upper surface of the bottom plate is fixedly connected with a first fixed seat, a second fixed seat and two movable seats respectively, the inner wall of each movable seat is movably hinged with a movable sliding plate, the lower part of the honeycomb grid is provided with a receiving plate, the inner wall of the receiving plate is movably hinged with two movable plates, the inner wall of each movable sliding plate is movably hinged with the inner wall of the movable plate, the inner walls of the two movable plates are movably hinged with a threaded frame, the inner wall of the threaded frame is threadedly connected with a threaded rod, the outer side of the buffer box is provided with a servo motor, the inner bottom wall of the protection shell is fixedly connected with a pressure sensor, the inner wall of the protection shell is fixedly connected with a fixed baffle, and the front surface of the fixed baffle is fixedly connected with a controller main body.

[0007] Further, the outer surface of the threaded rod is fixedly connected with a bearing, the right end of the bearing is fixedly connected with the left side surface of the first fixed seat, the upper surface of the pressure sensor is in contact with the bottom surface of the buffer box, and the output end of the servo motor is fixedly connected with the left end of the threaded rod. The outer surface of each movable sliding plate is slidably connected with the inside of the receiving plate, and the outer surface of the threaded rod is rotatably connected with the second fixed seat and the first fixed seat respectively.

[0008] Further, the inner wall of one of the two fixed blocks is fixedly connected with the outer surface of the servo motor.

[0009] Further, the outer surface of the pressure sensor is fixedly connected with a fixed ring, and the bottom end of the fixed ring is fixedly connected with the inner wall of the protection shell.

[0010] Further, the outer surface of the controller main body is fixedly connected with a fixed frame, and the back surface of the fixed frame is fixedly connected with the front surface of the fixed baffle.

[0011] Further, the inner wall of the fixed frame is threadedly connected with two bolts, and the outer surface of each bolt is connected with the fixed entity.

[0012] Compared with the prior art, the aircraft weighing scale with anti-deformation structure has the following advantages

[0013] Advantages:

[0014] The utility model discloses a buffer protection mechanism can be carried out to the airplane weighing scale buffering protection, avoid the problem that the deformation appears in the process of using the weighing scale, through the controller main part control servo motor works, and servo motor drives screw rod to rotate under the support of buffer tank, second fixed seat and first fixed seat, and screw rod rotation drives screw frame to move left and right, and the movement of screw frame is under the activity of movable seat activity and the activity of movable seat and movable board activity hinged effect, and movable slide plate is driven to move left and right along the inside of the receiving plate under the activity of receiving plate activity support effect, thereby adjusting the position height of receiving plate, is favorable to the back of receiving plate accurate with the bottom surface of honeycomb grid contact, thereby dispersing the surface force of honeycomb grid, reaches the purpose of device protection, through the hydraulic damper, can carry out the buffering to the pressure on the surface of honeycomb grid, avoids the problem that honeycomb grid and receiving plate surface are subjected to excessive pressure, and the use effect of device is further reduced. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 It is the structure schematic diagram of the utility model protection shell three-dimensional structure.

[0016] Figure 2 It is the utility model honeycomb grid section view.

[0017] Figure 3 It is the buffer tank section view of the utility model.

[0018] Figure 4 It is the fixed block section view of the utility model.

[0019] Figure 5 It is the structure schematic diagram of the utility model bottom plate three-dimensional structure.

[0020] Figure 6 It is the structure schematic diagram of the utility model first fixed seat three-dimensional structure.

[0021] In the drawing: 1, protection shell, 2, buffer protection mechanism, 201, fixed frame, 202, honeycomb grid, 203, controller main part, 204, buffer tank, 205, receiving plate, 206, servo motor, 207, pressure sensor, 208, hydraulic damper, 209, second fixed seat, 210, screw rod, 211, screw frame, 212, first fixed seat, 213, movable slide plate, 214, movable seat, 215, movable board, 216, fixed baffle, 217, bottom plate, 3, protection shell, 4, fixed block, 5, bolt, 6, bearing, 7, fixed ring. DETAILED DESCRIPTION

[0022] The principles and characteristics of the utility model are described below in conjunction with the drawings, and the examples are only used to explain the utility model and are not used to limit the scope of the utility model.

[0023] The embodiment provides an airplane weighing scale with an anti-deformation structure, which can protect the airplane weighing scale through a buffer protection mechanism, so that damage to the airplane weighing scale caused by excessive weight of the airplane can be avoided.

[0024] Referring to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 , an airplane weighing scale with an anti-deformation structure comprises a protective shell 1, the inner side of the protective shell 1 and the outer side of the protective shell 1 are provided with a buffer protection mechanism 2, the buffer protection mechanism 2 comprises a fixed frame 201, the inside of the protective shell 1 is provided with a buffer box 204, the upper side of the buffer box 204 is provided with a honeycomb grid 202, the inner wall of the buffer box 204 is fixedly connected with two groups of hydraulic dampers 208, the telescopic end of each hydraulic damper 208 is fixedly connected with the bottom surface of the honeycomb grid 202, the inner bottom wall of the buffer box 204 is fixedly connected with a bottom plate 217, the hydraulic damper 208 is a device for dissipating energy through fluid resistance, mainly used for inhibiting mechanical vibration or movement impact, and plays a role of buffering protection of the device, and the core principle is that when an external force drives the piston in the damper to move, the hydraulic oil enclosed in the cylinder is forced to pass through the small hole or valve on the piston, due to the fluid viscous resistance and throttling effect, the oil flow is limited to generate a reverse resistance, so as to convert kinetic energy into heat energy dissipation; at the same time, the one-way valve or adjustable valve designed inside can control the damping force, so as to realize the buffering effect at different speeds, the mechanism of "soft against hard" is widely used in automobile suspension damping, building anti-seismic structure, precision equipment anti-vibration and other fields, effectively improves the system stability and safety, the inner wall of the fixed frame 201 is screw-connected with two bolts 5, the outer surface of each bolt 5 is connected with a fixed entity, the bolts 5 are used for conveniently connecting the fixed frame 201 with the fixed entity by workers, so that the honeycomb grid 202 and the surface of the fixed block 4 are at the same level with the ground contacted by the airplane wheels, and then the device is convenient for measuring the weight of the airplane.

[0025] Referring to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6The upper surface of the bottom plate 217 is respectively fixedly connected with the first fixed seat 212, the second fixed seat 209 and the two movable seats 214, the inner wall of each movable seat 214 is movably hinged with the movable sliding plate 213, the lower part of the honeycomb grid 202 is provided with the receiving plate 205, the inner wall of the receiving plate 205 is movably hinged with the two movable plates 215, the inner wall of each movable sliding plate 213 is movably hinged with the inner wall of the movable plate 215, the inner walls of the two movable plates 215 are movably hinged with the threaded frame 211, the inner wall of the threaded frame 211 is threadedly connected with the threaded rod 210, the outer side of the buffer box 204 is provided with the servo motor 206, the inner wall of the protective shell 1 is fixedly connected with the two fixed blocks 4, the inner wall of one of the fixed blocks 4 is fixedly connected with the outer surface of the servo motor 206, the servo motor 206 can be fixed by the fixed block 4, so that the problem of fluctuation of the servo motor 206 during use is avoided, and the lifting of the device is further affected.

[0026] Referring to Figure 3 The inner bottom wall of the protective shell 1 is fixedly connected with the pressure sensor 207, the outer surface of the pressure sensor 207 is fixedly connected with the fixed ring 7, the bottom end of the fixed ring 7 is fixedly connected with the inner wall of the protective shell 1, the pressure sensor 207 can be fixed by the fixed ring 7, so that the problem of movement and falling of the pressure sensor 207 during use is avoided, and the accuracy of the device for measuring the weight of the aircraft is further affected.

[0027] Referring to Figure 1The inner wall of the protective shell 1 is fixedly connected with a fixed baffle 216, the front surface of the fixed baffle 216 is fixedly connected with a controller body 203, the outer surface of the controller body 203 is fixedly connected with a fixed frame 3, the back surface of the fixed frame 3 is fixedly connected with the front surface of the fixed baffle 216, the controller body 203 can be fixed by the fixed frame 3, so as to avoid the problem that the controller body 203 falls during use, thereby affecting the stability of the line connection of the controller body 203. The composition of the controller includes two parts of hardware and software: the hardware mainly includes a central processing unit CPU responsible for calculation, an input / output I / O interface connected with a sensor and an actuator, a memory storing programs and data, a power supply, a communication module and the like; the software covers a control algorithm program, a real-time operating system such as RTOS and a man-machine interface, which together ensure accurate and efficient system control, and is widely used in industrial automation, smart home, automobile electronics and the like. The controller is a core device for adjusting system operation by processing input signals in real time and generating control instructions. Its working principle can be summarized as follows: first, collect the signals input by sensors or externally, such as temperature and speed, and compare them with the preset target value to calculate the deviation; then use the built-in algorithm such as PID control to analyze the deviation and generate adjustment instructions; finally, drive the actuator such as a motor or a valve through the output interface to adjust the system state, while continuously monitoring the effect through closed-loop feedback to achieve dynamic stability. The electrical components of the technical solution can be controlled by the controller.

[0028] Referring to Figure 5 and Figure 6 The outer surface of the threaded rod 210 is fixedly connected with a bearing 6, the right end of the bearing 6 is fixedly connected with the left side surface of the first fixed seat 212, the upper surface of the pressure sensor 207 is in contact with the bottom surface of the buffer box 204, and the output end of the servo motor 206 is fixedly connected with the left end of the threaded rod 210. The outer surface of each movable sliding plate 213 is slidably connected with the inner part of the supporting plate 205, and the outer surface of the threaded rod 210 is rotatably connected with the second fixed seat 209 and the first fixed seat 212 respectively. The threaded rod 210 can be fixed by the bearing 6 to avoid the problem of shaking of the threaded rod 210 during rotation, thereby affecting the stability of the device.

[0029] Working principle: in use, first connect the pressure sensor 207, controller body 203 and servo motor 206 with the power supply, when the device is used to measure the weight of the aircraft, the staff first find a suitable position for the weight measurement of the aircraft, the measuring device needs to be built in the entity, that is, the protective shell 1 is connected with the fixed entity by bolt 5, the surface of the fixed frame 201 is flat with the ground, then the staff controls the servo motor 206 to work by the controller body 203, the servo motor 206 drives the threaded rod 210 to rotate under the support of the buffer tank 204, the threaded rod 210 rotates under the support and fixation of the second fixed seat 209 and the first fixed seat 212, because the threaded rod 210 is screwed with the threaded frame 211, the rotation of the threaded rod 210 drives the threaded frame 211 to move left and right along the surface of the threaded rod 210, the movement of the threaded frame 211 before and after drives the movable slide plate 213 to move forward and backward along the inside of the bearing plate 205 under the activity support of the movable plate 215 and the movable seat 214, so as to adjust the position height of the bearing plate 205, adjust the position height of the surface of the bearing plate 205 to contact with the bottom surface of the honeycomb grid 202, at the same time, the staff observes the current reading by the controller body 203, and records the current reading as the original data, then the staff drives the aircraft wheels to move stably to the surface of the honeycomb grid 202 by the tractor, the aircraft wheels move to the surface of the honeycomb grid 202, at this time the weight of the aircraft is applied to the surface of the honeycomb grid 202 through the wheels, the honeycomb grid 202 can decompose the concentrated load into distributed stress field, so as to reduce the local pressure, the pressure of the aircraft wheels is distributed on the bottom surface of the honeycomb grid 202, the honeycomb grid 202 contacts with the surface of the bearing plate 205 and the hydraulic damper 208, the pressure of the honeycomb grid 202 is transferred to the surface of the bearing plate 205 and the hydraulic damper 208, which is distributed and dispersed, so as to protect the device and avoid the problem of damage to the device when measuring the weight of the aircraft, the wheels of the aircraft apply downward force to the contacted surface of the honeycomb grid 202, the force is distributed and dispersed and acts on the bottom surface of the buffer tank 204 under the support of the surface of the honeycomb grid 202 and the buffer of the hydraulic damper 208, the bottom surface of the buffer tank 204 contacts with the surface of the pressure sensor 207, the buffer tank 204 gives the downward pressure to the pressure sensor 207, so as to realize the measurement of the weight on the surface of the buffer tank 204, that is, the weight of the aircraft, through the device, the weight of the aircraft can be uniformly distributed through the buffer protection mechanism 2, so as to protect the device and improve the use effect of the device.

[0030] The above merely describes preferred embodiments of the present application and is not intended to limit the present application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An aircraft weighing scale with an anti-deformation structure, comprising a protective casing (1), characterized in that: The inner side of the protective shell (1) and the outer side of the protective shell (1) are jointly provided with a buffer protection mechanism (2); The buffer protection mechanism (2) comprises a fixed frame (201), the inside of the protective shell (1) is provided with a buffer box (204), the upper side of the buffer box (204) is provided with a honeycomb grid (202), the inner wall of the buffer box (204) is fixedly connected with two groups of hydraulic dampers (208), the telescopic end of each hydraulic damper (208) is fixedly connected with the bottom surface of the honeycomb grid (202), the inner bottom wall of the buffer box (204) is fixedly connected with a bottom plate (217), the upper surface of the bottom plate (217) is fixedly connected with a first fixed seat (212), a second fixed seat (209) and two movable seats (214) respectively, the inner wall of each movable seat (214) is movably hinged with a movable sliding plate (213), the lower side of the honeycomb grid (202) is provided with a receiving plate (205), the inner wall of the receiving plate (205) is movably hinged with two movable plates (215), the inner wall of each movable sliding plate (213) is movably hinged with the inner wall of the movable plate (215), the inner walls of the two movable plates (215) are movably hinged with a threaded frame (211), the inner wall of the threaded frame (211) is threadedly connected with a threaded rod (210), the outer side of the buffer box (204) is provided with a servo motor (206), the inner bottom wall of the protective shell (1) is fixedly connected with a pressure sensor (207), the inner wall of the protective shell (1) is fixedly connected with a fixed baffle (216), the front surface of the fixed baffle (216) is fixedly connected with a controller main body (203).

2. The aircraft weighing scale with anti-deformation structure according to claim 1, characterized in that: The outer surface of the threaded rod (210) is fixedly connected with a bearing (6), the right end of the bearing (6) is fixedly connected with the left side surface of the first fixed seat (212), the upper surface of the pressure sensor (207) is in contact with the bottom surface of the buffer box (204), the output end of the servo motor (206) is fixedly connected with the left end of the threaded rod (210), the outer surface of each movable sliding plate (213) is slidably connected with the inside of the receiving plate (205), the outer surface of the threaded rod (210) is rotatably connected with the second fixed seat (209) and the first fixed seat (212) respectively.

3. The aircraft weighing scale with anti-deformation structure according to claim 1, characterized in that: The inner wall of the protective shell (1) is fixedly connected with two fixed blocks (4), the inner wall of one of the fixed blocks (4) is fixedly connected with the outer surface of the servo motor (206).

4. The aircraft weighing scale with anti-deformation structure according to claim 1, characterized in that: The outer surface of the pressure sensor (207) is fixedly connected with a fixed ring (7), the bottom end of the fixed ring (7) is fixedly connected with the inner wall of the protective shell (1).

5. The aircraft weighing scale having a deformation resistant structure according to claim 1, characterized in that: The outer surface of the controller main body (203) is fixedly connected with a fixed frame (3), the back surface of the fixed frame (3) is fixedly connected with the front surface of the fixed baffle (216).

6. The aircraft weighing scale having a deformation resistant structure according to claim 1, characterized in that: The inner wall of the fixed frame (201) is threadedly connected with two bolts (5), the outer surface of each bolt (5) is connected with a fixed entity.

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