A helicopter power shaft coaxiality inspection device

Abstract

The utility model relates to helicopter power shaft detection technical field especially is a kind of helicopter power shaft coaxality inspection equipment, including cylinder, the both ends of cylinder are fixedly connected with stainless steel method axle sleeve, located left stainless steel method axle sleeve is fixedly connected with process assembly in the one end away from cylinder, the left side fixedly connected with the process piece in process assembly of stainless steel method axle sleeve, the inside thread connection of process piece has target seat, the inside fixedly connected with target lens of target seat, the side fixedly connected with camera assembly of process assembly away from stainless steel method axle sleeve, in the utility model, laser beam is used as reference line, improves the stability and reliability of measurement, camera is used to identify the detection point of laser beam formed in target, replaces artificial visual observation, improves the objectivity and accuracy of measurement data, deviation coordinate is calculated by computer technology processing, is shown on monitor screen, measurement is fast, accurate, and precision is in ±0.05mm.

Description

Technical Field

[0001] This utility model relates to the field of helicopter power shaft detection technology, specifically a helicopter power shaft coaxiality inspection device. Background Technology

[0002] With the rapid development of my country's aircraft manufacturing industry, helicopters, as the second largest family of aircraft, have an increasingly wide range of applications compared to fixed-wing aircraft. They are characterized by their ability to perform low-altitude, low-speed maneuvering with a constant nose direction, and vertical take-off and landing in small areas. They play an irreplaceable role in many military and civilian fields such as transportation, patrol, combat, tourism, and rescue. However, in the process of helicopter manufacturing, use, and maintenance, the coaxiality requirements between the engine output shaft and the main gearbox input shaft are high. The engine's onboard installation accuracy affects flight safety, requiring the use of special equipment for adjustment to ensure that the engine coaxiality meets the assembly requirements.

[0003] Traditional measuring equipment, or the use of photoelectric technology, relies on visual observation of the relative position of the coaxial lines within an electron optical lens to determine whether the engine coaxiality is up to standard. This subjective judgment of position leads to discrepancies in measurement results among different personnel, especially when the measurement results are on the edge of the acceptable range, which can easily cause disputes about whether the engine mount needs to be adjusted.

[0004] Currently available equipment can only detect the coaxiality deviation between the engine and the main reducer power shaft. When the data exceeds the tolerance, it is difficult for on-site operators to determine how to adjust the engine mount based on the measurement results. They need to contact the helicopter manufacturer's after-sales professionals for on-site guidance and adjustment each time, which is very troublesome. Therefore, a helicopter power shaft coaxiality inspection device is proposed to address the above problems. Utility Model Content

[0005] The purpose of this invention is to provide a helicopter power shaft coaxiality inspection device to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] A helicopter power shaft coaxiality inspection device includes a cylinder. Stainless steel bushings are fixedly connected to both ends of the cylinder. A process component is fixedly connected to the left end of the stainless steel bushing, away from the cylinder. A process part from the process component is fixedly connected to the left side of the stainless steel bushing. A target seat is threadedly connected to the inner side of the process part. A target lens is fixedly connected to the inner side of the target seat. A camera assembly is fixedly connected to the side of the process component away from the stainless steel bushing. A first mounting base located in the camera assembly is fixedly connected to the left side of the process component. A camera is fixedly connected to the inner side of the first mounting base. A gigabit Ethernet interface is provided at the left end of the camera. A laser assembly is provided inside the cylinder. A laser generator from the laser assembly is located inside the cylinder. A second mounting base is fixedly connected to the right side of the laser generator. A monitor and an adapter are provided outside the cylinder.

[0008] Preferably, the cylinder is hollow and tubular, and a square operating groove penetrating the cylinder is provided at the top of the cylinder.

[0009] Preferably, the inner shape of the process component matches the shape of the target base, and the diameter at the left end of the target base is larger than the inner diameter of the process component.

[0010] Preferably, the three holes on the outer ring of the process component correspond to the three holes on the first mounting base, and their shapes and sizes are matched.

[0011] Preferably, the camera, monitor, and adapter are all provided with serial interfaces on their surfaces, and the models of the serial interfaces on the surfaces of the camera, monitor, and adapter are all matched.

[0012] Compared with the prior art, the beneficial effects of this utility model are:

[0013] 1. In this utility model, by setting up components such as a cylinder, stainless steel bushing, process components, camera components, laser components, monitor, and adapter, and using a laser beam as a reference line, the stability and reliability of the measurement are improved. A camera is used to identify the detection point where the laser beam forms on the target, replacing manual visual observation, thus improving the objectivity and accuracy of the measurement data. The deviation coordinates are calculated by computer technology and displayed on the monitor screen. The measurement is fast and accurate, with an accuracy of ±0.05mm. This solves the problem of traditional measuring equipment, or the technology of using photoelectric technology to judge whether the coaxiality of the engine is qualified by manually observing the relative position of the coaxial line inside the electronic optical lens. The position is judged subjectively by humans, and the measurement results of different people are different. Especially when the measurement results are on the edge of the qualified range, it is easy to cause disputes about whether the engine bracket needs to be adjusted.

[0014] 2. In this utility model, the real-time image transmitted from the camera via a gigabit Ethernet interface can be displayed through components such as a monitor and an adapter. The engine position can be adjusted by using the fitted circle center and punctuation points displayed on the monitor. By adjusting the addition or removal of shims in real time and observing the adjusted fitted circle center position and coordinate values, the engine mount can be adjusted automatically. This solves the problem that existing equipment can only detect the coaxiality deviation between the engine and the main reducer power shaft. When the data exceeds the tolerance, it is difficult for on-site operators to determine how to adjust the engine mount based on the measurement results. It requires contacting the helicopter manufacturer's after-sales professionals for on-site guidance and adjustment each time, which is very troublesome. Attached Figure Description

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

[0016] Figure 2 This is a top view of the overall structure of this utility model;

[0017] Figure 3 This is a schematic diagram of the overall left-side structure of this utility model;

[0018] Figure 4 This is a detailed structural diagram of the process components of this utility model;

[0019] Figure 5 This is a detailed structural diagram of the laser assembly of this utility model;

[0020] Figure 6 This is a detailed structural diagram of the camera assembly of this utility model;

[0021] Figure 7 This is a schematic diagram of the left-side structure of the camera assembly of this utility model.

[0022] In the diagram: 1. Cylinder; 2. Stainless steel bushing; 3. Process component; 31. Process part; 32. Target holder; 33. Target lens; 4. Camera assembly; 41. Camera; 42. First mounting base; 43. Gigabit Ethernet interface; 5. Laser assembly; 51. Laser generator; 52. Second mounting base; 6. Monitor; 7. Adapter. Detailed Implementation

[0023] 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.

[0024] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0025] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0026] Please see Figure 1-7 This utility model provides a technical solution:

[0027] A helicopter power shaft coaxiality inspection device includes a cylinder 1. Stainless steel bushings 2 are fixedly connected to both ends of the cylinder 1. A process component 3 is fixedly connected to the left end of the stainless steel bushing 2 away from the cylinder 1. A process component 31 in the process component 3 is fixedly connected to the left side of the stainless steel bushing 2. A target seat 32 is threadedly connected to the inner side of the process component 31. A target lens 33 is fixedly connected to the inner side of the target seat 32. A camera component 4 is fixedly connected to the side of the process component 3 away from the stainless steel bushing 2. A first mounting seat 42 located in the camera component 4 is fixedly connected to the left side of the process component 3. A camera 41 is fixedly connected to the inner side of the first mounting seat 42. A gigabit Ethernet interface 43 is opened at the left end of the camera 41. A laser component 5 is provided inside the cylinder 1. A laser generator 51 in the laser component 5 is provided inside the cylinder 1. A second mounting seat 52 is fixedly connected to the right side of the laser generator 51. A monitor 6 is provided outside the cylinder 1. An adapter 7 is provided outside the cylinder 1.

[0028] The cylinder 1 is hollow and tubular. A square operating groove is provided at the top of the cylinder 1, which facilitates laser irradiation and also enables the laser assembly 5 to be turned on. The inner shape of the process component 31 matches the shape of the target base 32, and the diameter of the left end of the target base 32 is larger than the inner diameter of the process component 31, which can stably fix the target lens 33 and effectively prevent the target base 32 and the target lens 33 from falling off. The three holes on the outer ring of the process component 31 correspond to the three holes on the first mounting base 42, and their shapes and sizes match each other, which can accurately fix and connect the process assembly 3 and the camera assembly 4. The surfaces of the camera 41, monitor 6 and adapter 7 are all provided with serial interfaces. The models of the serial interfaces on the surfaces of the camera 41, monitor 6 and adapter 7 are all matched, which facilitates the establishment of control communication between the camera assembly 4, monitor 6 and adapter 7.

[0029] Workflow: When a helicopter power shaft coaxiality inspection device is required, the entire device is powered externally. Taking a helicopter main reducer as an example, the laser generator 51 is fixed to the input drive shaft of the main reducer using pins and nuts. The laser generator 51 is then fixed to the power shaft of the main reducer via the second mounting base 52. The cylinder 1 is fitted over the drive shaft and the laser generator 51 and connected to the main reducer. The right side of the cylinder 1 is fixed to the front bushing of the main reducer housing via connecting pins, washers, and a stainless steel bushing 2. Then, the process component 31 is placed tightly against the end face of the cylinder 1. On the stainless steel bushing 2, the process component 31 is kept parallel and in contact with the end face of the cylinder 1, and the cylinder 1 and the process component 31 are connected using quick-connect pins. The process component 31 is fixed to the existing engine mounting bracket by connecting pins. The laser target is fixed at the center of the process component, ensuring that the target lens 33 is concentric with the engine axis (at the mounting bracket). Next, the camera assembly 4 is connected to the monitor 6 and adapter 7 through the calibration device wiring harness. The power switch of the laser assembly 5 is turned on, and the laser assembly 5 emits a red laser. The power switch of the monitor 6 is turned on, and the calibration system interface is entered. The laser spot can be observed in the interface. Click the "Start Processing" button on the interface to start rotating the reducer spindle. The laser assembly 5 rotates with the reducer shaft, and the laser spot is projected onto the translucent target lens 33. The rear camera 41 uses visual recognition technology to locate and record the position of the laser spot on the target. The embedded computer can quickly calculate the engine coaxiality deviation through the center of gravity algorithm. At the same time, if the measurement result is out of tolerance, the user is guided to adjust the position and adjustment amount of the engine bracket according to the deviation position coordinates displayed in real time on the monitor 6 screen. The interface can see the laser spot moving with the reducer. The system rotates and records its trajectory. After the reducer has rotated more than one revolution, it stops rotating. Simultaneously, clicking "End Processing" will cause the system to fit a circle based on the trajectory and calculate the center of the circle (which is the reducer shaft center). The offset (in mm) between the fitted circle center and the center of process part 31 (which is the engine center) will be displayed in the upper right corner of the interface. If the fitted center position exceeds the 2.5mm diameter circle centered on the center point of process part 31, shims need to be added or removed between the engine mounting bracket and the structure to bring the fitted circle center within the required 2.5mm circle range. The position and coordinate values ​​of the fitted circle center can be observed, and the shims can be adjusted in real time. The adjusted fitted circle center position and coordinate values ​​can then be observed again. This process is repeated until the fitted circle center and the coordinate point coincide.

[0030] Contents not described in detail in this specification are existing technologies known to those skilled in the art. Standard parts used in this invention can all be purchased commercially, and irregularly shaped parts can be custom-made according to the description and drawings. The specific connection methods for each part all employ conventional methods such as bolts, rivets, and welding, which are already mature technologies. The machinery, parts, and equipment all use conventional models from the prior art, and the circuit connections also employ conventional connection methods from the prior art, which will not be detailed here.

[0031] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A helicopter power shaft coaxiality inspection device, comprising a cylinder (1), characterized in that: Stainless steel bushings (2) are fixedly connected to both ends of the cylinder (1). A process component (3) is fixedly connected to the end of the stainless steel bushing (2) on the left side away from the cylinder (1). A process component (31) in the process component (3) is fixedly connected to the left side of the stainless steel bushing (2). A target seat (32) is threadedly connected to the inner side of the process component (31). A target lens (33) is fixedly connected to the inner side of the target seat (32). A camera component (4) is fixedly connected to the side of the process component (3) away from the stainless steel bushing (2). The left side of the process component (3) A first mounting base (42) is fixedly connected to the camera assembly (4). A camera (41) is fixedly connected to the inner side of the first mounting base (42). A gigabit Ethernet interface (43) is provided on the left end of the camera (41). A laser assembly (5) is provided on the inner side of the cylinder (1). A laser generator (51) in the laser assembly (5) is provided inside the cylinder (1). A second mounting base (52) is fixedly connected to the right side of the laser generator (51). A monitor (6) is provided on the outside of the cylinder (1). An adapter (7) is provided on the outside of the cylinder (1).

2. The helicopter power shaft coaxiality inspection device according to claim 1, characterized in that: The cylinder (1) is hollow and tubular, and a square operating groove is provided at the top of the cylinder (1) that penetrates the cylinder (1).

3. The helicopter power shaft coaxiality inspection device according to claim 1, characterized in that: The inner shape of the process component (31) matches the shape of the target seat (32), and the diameter at the left end of the target seat (32) is greater than the inner diameter of the process component (31).

4. The helicopter power shaft coaxiality inspection device according to claim 1, characterized in that: The three holes of the process component (31) located around the target base (32) correspond to the three holes on the first mounting base (42), and their shapes and sizes are matched.

5. The helicopter power shaft coaxiality inspection device according to claim 1, characterized in that: The camera (41), monitor (6) and adapter (7) are all provided with serial interfaces on their surfaces, and the models of the serial interfaces on the surfaces of the camera (41), monitor (6) and adapter (7) are all matched.

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