An aviation blade measuring device and method based on three-group line structured light sensors

Abstract

The application discloses an aviation blade measuring device and method based on three groups of line structure light sensors, and relates to the technical field of aviation blade measurement. The device comprises a platform unit, a rotary table unit and three groups of synchronous feeding adjusting units which are installed at 120 degrees to each other. The rotary table unit comprises a rotary table motor, a rotating shaft, a profiling wheel and a clamping mechanism. Each synchronous feeding adjusting unit has the same structure and comprises a synchronous wheel in contact with the profiling wheel, a synchronous assembly, an adjusting spring and a line structure light sensor. When the profiling wheel rotates, the synchronous wheel and the synchronous assembly are pushed to move linearly, and the adjusting spring resets them to adaptively adjust the measuring distance. The measuring method comprises the following steps: resetting the profiling wheel, clamping the blade, driving the rotation, acquiring the circumferential angle information, adaptively adjusting the distance measurement, acquiring the position information and measuring the longitudinal profile, fusing the data to output the three-dimensional point cloud after one rotation. The application can solve the problem of blade edge tracking measurement and realize high-speed and high-precision measurement of full information.

Description

Technical Field

[0001] This invention relates to the field of aircraft blade measurement technology, and more specifically to an aircraft blade measurement device and method based on three sets of line structured optical sensors. Background Technology

[0002] As a key component of aero-engines, the shape and dimensional accuracy of aero-engine turbine blades directly affect the performance of aero-engines and even flight safety. In actual production, the measurement of aero-engine blades has important guiding significance for blade manufacturing, blade maintenance and remanufacturing. When measuring aero-engine blades, the following requirements should generally be met: (1) Full information measurement: Aero-engine blades have complex curved surface geometry, so information loss should be avoided and complete contour measurement should be achieved. (2) High-speed measurement: Aero-engine blades are usually mass-produced, so measurement efficiency should be improved. (3) High-precision measurement: Higher measurement accuracy helps to improve the reliability of the engine.

[0003] Currently, aircraft blade measurement is mainly divided into contact measurement and non-contact measurement. Contact measurement is represented by coordinate measuring machines (CMMs). This device uses a Cartesian coordinate system as its core foundation, achieving precise positioning through three mutually perpendicular coordinate axes (X, Y, Z). Information is acquired on the blade surface by a measurement probe moving along a preset trajectory. The disadvantages are slow measurement speed and the direct contact of the measurement probe with the blade surface, potentially causing wear and affecting the measurement results. Non-contact measurement is represented by line structured light measurement devices. The invention patent with authorization announcement number CN120489007B uses four line structured light sensors and a computing module mounted on a CMM. Measurement can be completed with only one-dimensional movement along the Z-axis of the CMM. The disadvantage is that for aircraft blades with particularly complex curved surfaces, some blade edges may not fall within the measurement range of the line structured light sensors. The invention patent with authorization announcement number CN114427833B uses an external device based on line structured light sensors to assist the machine tool in closed-loop manufacturing of aircraft blades. The disadvantage is that the on-machine inspection results cannot be used as the basis for final inspection and judgment of the finished product.

[0004] Therefore, how to provide an aircraft blade measurement device and method that can achieve full information measurement of aircraft blades and has both high measurement efficiency and high measurement accuracy is a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] In view of this, the present invention provides an aircraft blade measurement device and method based on three sets of line structured optical sensors, aiming to solve the above-mentioned technical problems.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] An aircraft blade measurement device based on three sets of line structured light sensors, comprising: Platform unit; A turntable unit located at the center of the platform unit; and a first synchronous feed adjustment unit, a second synchronous feed adjustment unit, and a third synchronous feed adjustment unit installed above the platform unit at 120° to each other with the turntable unit as the center; The turntable unit includes a turntable motor, a rotating shaft driven by the turntable motor, a contour wheel connected to the rotating shaft, and a clamping mechanism coaxially connected to the contour wheel and used to clamp the aircraft blade. The contour of the contour wheel is the cross-sectional contour of the middle part of the aircraft blade. The first synchronous feed adjustment unit, the second synchronous feed adjustment unit, and the third synchronous feed adjustment unit have the same mechanical structure. The first synchronous feed adjustment unit includes a synchronous wheel that contacts the outer edge of the contour wheel, a synchronous component connected to the synchronous wheel, an adjustment spring that provides elastic restoring force to the synchronous component, and a first wire structured light sensor mounted on the synchronous component. When the contour wheel rotates, it pushes the synchronization wheel to drive the synchronization component to move linearly. The adjusting spring resets the synchronization component to adaptively adjust the measurement distance between the first line structured light sensor and the aircraft blade.

[0008] Through the above technical solution, this invention achieves real-time adaptive adjustment of the measurement distance between the line structured optical sensor and the aircraft blade by setting up a platform unit, a turntable unit, and three sets of synchronous feed adjustment units installed at 120° angles to each other, and by utilizing a linkage structure of a contour-following wheel with a profile resembling the middle section of an aircraft blade, a synchronous wheel, a synchronous component, and an adjusting spring. This structure ensures that the blade edge is always within the sensor's measurement range, effectively solving the problem of tracking and measuring the edge of thin, flat blades.

[0009] Preferably, in the above-mentioned aircraft blade measuring device based on three sets of line structured light sensors, the platform unit includes a platform support, a working platform mounted on the platform support, and a rotating platform welded to the center of the working platform, and the turntable motor is fixedly installed at the bottom of the rotating platform.

[0010] Preferably, in the above-mentioned aircraft blade measuring device based on three sets of line structured light sensors, the turntable unit further includes: A bearing for mounting the rotating shaft into the central through hole of the rotating platform; The measuring plate is fixed to the top of the rotating platform by bolts; A precision rotating wheel is connected to the rotating shaft via a first flange, and the precision rotating wheel is located above the measuring plate. A circular grating fixed on the precision rotating wheel; The circular grating reading head mounted on the measuring plate is used to synchronously acquire the circumferential rotation angle signal of the aircraft blade; The contour wheel is integrally formed with the base plate, which is connected to the top of the rotating shaft via the second flange; The clamping mechanism is connected to the support plate by bolts to the top surface of the contour wheel.

[0011] Preferably, in the above-mentioned aircraft blade measuring device based on three sets of line structured light sensors, the first synchronous feed adjustment unit further includes: Two sets of guiding mechanisms fixed to the working platform; Two sets of dovetail grooves are arranged vertically and horizontally inside the two sets of guide mechanisms. The synchronization component is arranged inside the two sets of dovetail grooves and is slidably connected to the dovetail grooves to form a sliding pair. A linear grating installed on the dovetail groove described below; A measurement connection plate is fixed to the synchronization component; a linear grating reading head is fixed to the measurement connection plate by bolts, the linear grating reading head is arranged opposite to the linear grating, and is used to synchronously acquire position signals along the X direction when the synchronization component moves linearly; An adjustment seat fixed to the working platform; An adjusting pusher is provided, wherein three protruding shafts of the adjusting pusher are inserted into the adjusting seat, the adjusting pusher is in contact with the surface opposite to the synchronization component, and the adjusting spring is connected between the adjusting pusher and the adjusting seat. The first sensor connector is installed at the upper end of the synchronization component, and the first line structured light sensor is fixed to the first sensor connector by bolts.

[0012] Preferably, in the above-mentioned aircraft blade measuring device based on three sets of line structured light sensors, the light plane emitted by the first line structured light sensor is projected onto the aircraft blade and located at the central axis of the rotation shaft, for measuring the lower part of the aircraft blade; the second synchronous feed adjustment unit includes a second sensor connector fixed by bolts and a second line structured light sensor fixed by bolts to the second sensor connector, the assembly height of the second sensor connector being such that the second line structured light sensor measures the middle part of the aircraft blade; the third synchronous feed adjustment unit includes a third sensor connector fixed by bolts and a third line structured light sensor fixed by bolts to the third sensor connector, the assembly height of the third sensor connector being such that the third line structured light sensor measures the upper part of the aircraft blade.

[0013] Preferably, in the above-mentioned aircraft blade measuring device based on three sets of line structured light sensors, the assembly heights of the first sensor connector in the first synchronous feed adjustment unit, the second sensor connector in the second synchronous feed adjustment unit, and the third sensor connector in the third synchronous feed adjustment unit are different from each other, so that the first line structured light sensor, the second line structured light sensor, and the third line structured light sensor mounted thereon respectively measure the lower, middle, and upper parts of the aircraft blade.

[0014] Preferably, in the above-mentioned aircraft blade measuring device based on a three-group linear structured optical sensor, the clamping mechanism uses a tenon-and-mortise connection structure to fix the aircraft blade.

[0015] This invention also discloses a method for measuring aircraft blades based on three sets of line structured light sensors, comprising the following steps: Step S1: Reset the contour wheel to its initial position; Step S2: The aircraft blade to be measured is clamped and fixed by the clamping mechanism; Step S3: Drive the turntable motor to rotate, so that the rotating shaft drives the contour wheel and the aircraft blade to rotate; Step S4: Obtain the circumferential rotation angle information of the aircraft blade; Step S5: The self-rotation of the contour wheel drives the feed adjustment of each synchronous wheel, thereby driving each synchronous component to move linearly. The compression and reset of each synchronous component are achieved by relying on the elastic restoring force of each adjusting spring, so that each line structured light sensor adaptively changes its measurement distance with the aircraft blade. Step S6: Obtain the position information of each line structured light sensor along the moving direction, and measure the longitudinal plane profile of the aircraft blade through each line structured light sensor; Step S7: The aircraft blade rotates once to acquire full surface information, fuses the acquired surface information data, and outputs three-dimensional coordinate point information.

[0016] Through the above technical solution, this invention achieves adaptive ranging by resetting the contour wheel, clamping the blade, driving its rotation, acquiring circumferential angle information, having the contour wheel drive the synchronous wheel to move the synchronous component linearly and relying on the adjusting spring to reset, acquiring position information and measuring the longitudinal contour, and fusion data to output three-dimensional coordinate points after one rotation. This method can adaptively adjust the measurement distance between the sensor and the blade in real time to ensure continuous and complete edge information; it only requires one rotation of the blade to acquire full surface information, resulting in fast measurement speed; through the collaborative fusion processing of angle and position information, it can obtain three-dimensional coordinate point cloud data with micron-level accuracy, while supporting repeatability verification after several rotations, thus simultaneously achieving high measurement efficiency, high measurement accuracy, and full information measurement.

[0017] Preferably, in the above-mentioned method for measuring aircraft blades based on three sets of line structured light sensors, step S7 further includes driving the aircraft blade to rotate several times and comparing the surface information data acquired in each rotation to verify repeatability.

[0018] Preferably, in the above-mentioned method for measuring aircraft blades based on three sets of line structured light sensors, the circumferential rotation angle information obtained in step S4 and the position information obtained in step S6 are fused together to obtain the three-dimensional coordinate point cloud data of the aircraft blade surface.

[0019] As can be seen from the above technical solution, compared with the prior art, the present invention discloses an aircraft blade measurement device and method based on three sets of line structured light sensors, which has the following beneficial effects: 1. This invention designs a low-cost contour wheel structure, with the synchronous feed adjustment unit in stable contact with the contour wheel, enabling the line structured light sensor to accurately and continuously measure the edge information of aero-blades within the measurement range. This structure design can solve the problem of tracking and measuring thin, flat blades. 2. Through the design of the device structure, the present invention constructs a measurement field of view of the line structured light sensor, so that the circumferential measurement of the aircraft blade can be completed by the turntable motor driving the aircraft blade to rotate only one revolution, which effectively improves the measurement efficiency of the aircraft blade. 3. This invention designs a high-precision circular grating to obtain the circumferential rotation angle information of an aircraft blade, and obtains the longitudinal plane contour information of the aircraft blade by using a linear grating in conjunction with a line structured light sensor. By fusing the circumferential and longitudinal plane measurement data, micron-level three-dimensional coordinate point cloud data of the blade surface can be accurately obtained. 4. This invention designs three sets of line structured light sensors to implement a segmented detection method for different cross sections of aircraft blades, which can realize the full information measurement of aircraft blades. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0021] Figure 1 The attached figure is a schematic diagram of the structure of the aircraft blade measuring device based on three sets of line structure optical sensors provided by the present invention; Figure 2 The attached figure is a schematic diagram of the platform unit provided by the present invention; Figure 3 The attached figure is a partial structural schematic diagram of the turntable unit provided by the present invention. Figure 1 ; Figure 4 The attached figure is a partial structural schematic diagram of the turntable unit provided by the present invention. Figure 2 ; Figure 5 The attached figure is a partial enlarged view of the turntable unit provided by the present invention; Figure 6 The attached figure is a schematic diagram of the structure of the first synchronous feed adjustment unit provided by the present invention; Figure 7 The attached figure is a partial structural schematic diagram of the first synchronous feed adjustment unit, the second synchronous feed adjustment unit, and the third synchronous feed adjustment unit provided by the present invention; Figure 8 The attached figure is a flowchart of the aircraft blade measurement method provided by the present invention; Figure 9 The attached figure is a point cloud data diagram of an aircraft blade provided by the present invention.

[0022] in: 1-Platform unit; 2-Turntable unit; 3-First synchronous feed adjustment unit; 4-Second synchronous feed adjustment unit; 5-Third synchronous feed adjustment unit; 11-Platform support; 12-Working platform; 13-Rotating platform; 21-Turntable motor; 22-Rotating shaft; 23-Bearing; 24-Measuring plate; 25-Precision wheel; 26-Circular grating reading head; 27-Circular grating; 28-First flange; 29-Second flange; 210-Base plate; 211-Contouring wheel; 212-Support plate; 213-Clamping mechanism; 2 14-Aircraft blade; 31-Guide mechanism; 32-Dovetail groove; 33-Synchronization assembly; 34-Synchronization pulley; 35-Linear grating; 36-Measuring connection plate; 37-Linear grating reading head; 38-Adjustment seat; 39-Adjustment pusher; 310-Adjustment spring; 311-First sensor connector; 312-First linear structured light sensor; 313-Light plane; 411-Second sensor connector; 412-Second linear structured light sensor; 511-Third sensor connector; 512-Third linear structured light sensor. Detailed Implementation

[0023] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0024] Example 1: like Figure 1As shown, this embodiment provides an aircraft blade measuring device based on three sets of line structured light sensors, including: a platform unit 1, a turntable unit 2 disposed in the center of the platform unit 1, and a first synchronous feed adjustment unit 3, a second synchronous feed adjustment unit 4 and a third synchronous feed adjustment unit 5 installed above the platform unit 1 at 120° angles to each other with the turntable unit 2 as the center.

[0025] I. Specific structure of platform unit 1: like Figure 2 As shown, platform unit 1 includes platform support column 11, work platform 12 mounted on platform support column 11, and rotating platform 13 welded to the center of work platform 12. Platform support column 11 provides stable support for the entire device, work platform 12 is used to support other units, and rotating platform 13 provides the mounting foundation for turntable unit 2.

[0026] II. Specific structure of turntable unit 2: like Figures 3 to 5 As shown, the turntable unit 2 includes a turntable motor 21, a rotating shaft 22, a bearing 23, a measuring plate 24, a precision rotating wheel 25, a circular grating reading head 26, a circular grating 27, a first flange 28, a second flange 29, a base plate 210, a contour wheel 211, a support plate 212, a clamping mechanism 213, and an aircraft blade to be tested 214.

[0027] The turntable motor 21 is bolted to the bottom of the rotating platform 13, and its output shaft is connected to the rotating shaft 22 via a coupling, providing rotational driving force to the rotating shaft 22. The rotating shaft 22 is mounted in the central through hole of the rotating platform 13 via a bearing 23, and can rotate freely.

[0028] The measuring plate 24 is bolted to the top of the rotating platform 13. The precision rotating wheel 25 is connected to the rotating shaft 22 via the first flange 28, and is positioned above the measuring plate 24. A circular grating 27 is fixed to the precision rotating wheel 25, and a circular grating reading head 26 is mounted on the measuring plate 24, positioned opposite to the circular grating 27. As the precision rotating wheel 25 rotates with the rotating shaft 22, the circular grating reading head 26 synchronously acquires the circumferential rotation angle signal of the aircraft blade 214.

[0029] The top end of the rotating shaft 22 is connected to the base plate 210 via the second flange 29, and the contour wheel 211 is integrally formed with the base plate 210. The contour of the contour wheel 211 is designed to resemble the cross-sectional contour of the middle part of the aircraft blade 214. The support plate 212 is connected to the top surface of the contour wheel 211 by bolts, and the clamping mechanism 213 is connected to the support plate 212 by bolts. The clamping mechanism 213 uses a tenon and mortise connection structure to fix the aircraft blade 214, so that the aircraft blade 214 and the contour wheel 211 are coaxial and rotate synchronously.

[0030] III. Specific structure of the synchronous feed adjustment unit: The first synchronous feed adjustment unit 3, the second synchronous feed adjustment unit 4, and the third synchronous feed adjustment unit 5 have identical mechanical structures, differing only in the assembly height of the sensor connectors, to achieve segmented measurement of the lower, middle, and upper parts of the aircraft blade 214. The following detailed description uses the first synchronous feed adjustment unit 3 as an example: like Figure 6 As shown, the first synchronous feed adjustment unit 3 includes: a guide mechanism 31, a dovetail groove 32, a synchronization component 33, a synchronization wheel 34, a linear grating 35, a measurement connecting plate 36, a linear grating reading head 37, an adjustment seat 38, an adjustment pusher 39, an adjustment spring 310, a first sensor connector 311, a first linear structured light sensor 312, and a light plane 313.

[0031] Two sets of guide mechanisms 31 are fixed on the working platform 12. Each set of guide mechanisms 31 has two sets of dovetail grooves 32 arranged vertically on its inner side. The synchronization component 33 is disposed inside the two sets of dovetail grooves 32 and is slidably connected with the dovetail grooves 32 to form a sliding pair. The synchronization wheel 34 is installed at the lower front of the synchronization component 33 and maintains stable contact with the outer edge of the contour wheel 211. When the contour wheel 211 rotates, its contour change pushes the synchronization wheel 34, thereby driving the synchronization component 33 to move linearly along the dovetail grooves 32.

[0032] A linear grating 35 is mounted on the lower dovetail groove 32. A measuring connection plate 36 is fixed to a synchronization assembly 33, and a linear grating reading head 37 is fixed to the measuring connection plate 36 by bolts and is positioned opposite to the linear grating 35. When the synchronization assembly 33 moves linearly, the linear grating reading head 37 synchronously acquires the position signal along the X direction (i.e., radial direction).

[0033] The adjustment seat 38 is fixed on the working platform 12. The three convex shafts of the adjustment pusher 39 are inserted into the adjustment seat 38, and the main body of the adjustment pusher 39 is in contact with the surface opposite to the synchronization component 33. The adjustment spring 310 is connected between the adjustment pusher 39 and the adjustment seat 38. When the synchronization component 33 is pushed outward by the contour wheel 211, the adjustment spring 310 is compressed; when the contour of the contour wheel 211 retracts, the elastic restoring force of the adjustment spring 310 pushes the adjustment pusher 39, so that the synchronization component 33 is reset, thereby ensuring that the measurement distance between the first-line structured light sensor 312 and the aircraft blade 214 can be adaptively adjusted in real time, ensuring that the blade edge is always within the measurement range of the sensor.

[0034] The first sensor connector 311 is mounted on the upper end of the synchronization assembly 33, and the first line structured light sensor 312 is fixed to the first sensor connector 311 by bolts. The light plane 313 emitted by the first line structured light sensor 312 is projected onto the aircraft blade 214 and is located at the central axis of the rotation shaft 22 (i.e., the central axis surface of the blade), and is used to measure the lower part of the aircraft blade 214.

[0035] The structure of the second synchronous feed adjustment unit 4 is exactly the same as that of the first synchronous feed adjustment unit 3, except that the assembly height of its second sensor connector 411 is different, so that the second line structured light sensor 412 mounted on it is aligned with the middle of the aircraft blade 214 for measurement. The assembly height of the third sensor connector 511 of the third synchronous feed adjustment unit 5 is the highest, so that the third line structured light sensor 512 is aligned with the upper part of the aircraft blade 214 for measurement. Figure 7 As shown, the heights of the first sensor connector 311, the second sensor connector 411, and the third sensor connector 511 increase sequentially, thereby achieving full-coverage segmented measurement of the blade from top to bottom.

[0036] Example 2: When using the above-mentioned device to measure aircraft blades, according to Figure 8 The flowchart shown illustrates the following steps: Step S1: Reset and Initialization: Reset the contour wheel 211 driven by the turntable motor 21 to the initial position (grating zero position), and at the same time ensure that each linear grating reading head 37 returns to the zero point.

[0037] Step S2: Clamping the blade: The aviation blade 214 to be measured is fixed by the clamping mechanism 213 (mortise and tenon structure) to ensure that the aviation blade 214 and the contour wheel 211 are concentric and rotate on the same axis.

[0038] Step S3: Drive rotation: Start the turntable motor 21, so that the rotating shaft 22 drives the precision rotating wheel 25, the contour wheel 211 and the aircraft blade 214 to rotate together.

[0039] Step S4: Obtain angle information: The precision rotating wheel 25 rotates, driving the circular grating 27 to rotate. The circular grating reading head 26 collects the circumferential rotation angle signal of the aircraft blade 214 in real time and transmits the angle data to the data processing module.

[0040] Step S5: Adaptive Feed Adjustment: During its rotation, the contour curve of the contour wheel 211 pushes each synchronous wheel 34, thereby driving each synchronous component 33 to move linearly along the dovetail groove 32. Each adjustment pusher 39 contacts the synchronous component 33, and the elastic restoring force of the adjustment spring 310 realizes the compression and reset of the synchronous component 33, so that the measurement distance between the first sensor connector 311, the second sensor connector 411, the third sensor connector 511 and the aircraft blade 214 changes adaptively in real time, ensuring that the blade edge always falls within the measurement range of the sensor.

[0041] Step S6: Acquire longitudinal profile information: While the online structured light sensor is performing measurements, each linear grating reading head 37 synchronously acquires the position signal of each sensor along the X direction. Each linear structured light sensor scans and measures the longitudinal plane profile of the aircraft blade 214 to obtain accurate profile data of the blade surface in the XOZ plane.

[0042] Step S7: Data Fusion and Output: After the aircraft blade 214 rotates once, the circumferential angle information and longitudinal contour information of the entire blade surface can be obtained. The circumferential rotation angle information obtained in Step S4 is fused with the position information and light knife data obtained in Step S6 to obtain three-dimensional coordinate point cloud data of the aircraft blade 214 surface. To verify the repeatability and reliability of the data, the aircraft blade 214 can be driven to rotate several more times, and the surface information data obtained in each rotation can be compared. Finally, three-dimensional point cloud data with micron-level precision is output, such as... Figure 9 As shown, the measurement is now complete.

[0043] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to the method section.

[0044] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An aircraft blade measuring device based on three sets of line structured optical sensors, characterized in that, include: Platform Unit (1); A turntable unit (2) is located in the center of the platform unit (1); and a first synchronous feed adjustment unit (3), a second synchronous feed adjustment unit (4) and a third synchronous feed adjustment unit (5) are installed above the platform unit (1) at 120° angles to each other with the turntable unit (2) as the center. The turntable unit (2) includes a turntable motor (21), a rotating shaft (22) driven by the turntable motor (21), a contour wheel (211) connected to the rotating shaft (22), and a clamping mechanism (213) coaxially connected to the contour wheel (211) and used to clamp the aircraft blade (214). The contour of the contour wheel (211) is the cross-sectional contour of the middle part of the aircraft blade (214). The first synchronous feed adjustment unit (3), the second synchronous feed adjustment unit (4) and the third synchronous feed adjustment unit (5) have the same mechanical structure. The first synchronous feed adjustment unit (3) includes a synchronous wheel (34) that contacts the outer edge of the contour wheel (211), a synchronous component (33) connected to the synchronous wheel (34), an adjustment spring (310) that provides elastic restoring force to the synchronous component (33), and a first line structured light sensor (312) mounted on the synchronous component (33). When the contour wheel (211) rotates, it pushes the synchronous wheel (34) to drive the synchronous component (33) to move linearly. The adjusting spring (310) resets the synchronous component (33) to adaptively adjust the measurement distance between the first line structured light sensor (312) and the aircraft blade (214).

2. The aircraft blade measuring device based on three sets of line structured optical sensors according to claim 1, characterized in that, The platform unit (1) includes a platform support (11), a working platform (12) installed on the platform support (11), and a rotating platform (13) welded to the center of the working platform (12). The turntable motor (21) is fixedly installed at the bottom of the rotating platform (13).

3. The aircraft blade measuring device based on three sets of line structured optical sensors according to claim 2, characterized in that, The turntable unit (2) also includes: A bearing (23) for mounting the rotating shaft (22) in the central through hole of the rotating platform (13); The measuring plate (24) is fixed to the top of the rotating platform (13) by bolts. A precision rotating wheel (25) is connected to the rotating shaft (22) via a first flange (28), and the precision rotating wheel (25) is located above the measuring plate (24); A circular grating (27) is fixed on the precision rotating wheel (25); The circular grating reading head (26) installed on the measuring plate (24) is used to synchronously acquire the circumferential rotation angle signal of the aircraft blade (214); The contour wheel (211) is integrally formed with the base plate (210) which is connected to the top of the rotating shaft (22) via the second flange (29); The clamping mechanism (213) is connected to the support plate (212) by bolts to the top surface of the contour wheel (211).

4. The aircraft blade measuring device based on three sets of line structured optical sensors according to claim 3, characterized in that, The first synchronous feed adjustment unit (3) further includes: Two sets of guide mechanisms (31) are fixed on the working platform (12); Two sets of dovetail grooves (32) are arranged inside the two sets of guide mechanisms (31) and arranged vertically. The synchronization component (33) is arranged inside the two sets of dovetail grooves (32) and is slidably connected to the dovetail grooves (32) to form a sliding pair. Linear grating (35) installed on the dovetail groove (32) in the lower part; A measurement connection plate (36) is fixed on the synchronization component (33); a linear grating reading head (37) is fixed on the measurement connection plate (36) by bolts. The linear grating reading head (37) is arranged opposite to the linear grating (35) and is used to synchronously collect position signals along the X direction when the synchronization component (33) moves linearly. Adjustment seat (38) fixed on the working platform (12); An adjusting pusher (39) is provided, the three protruding shafts of which are inserted into the adjusting seat (38). The adjusting pusher (39) is in contact with the surface opposite to the synchronizing component (33). The adjusting spring (310) is connected between the adjusting pusher (39) and the adjusting seat (38). The first sensor connector (311) is installed on the upper end of the synchronization component (33), and the first line structured light sensor (312) is fixed to the first sensor connector (311) by bolts.

5. The aircraft blade measuring device based on three sets of line structured optical sensors according to claim 4, characterized in that, The light plane (313) emitted by the first line structured light sensor (312) is projected onto the aircraft blade (214) and located at the central axis of the rotation shaft (22), and is used to measure the lower part of the aircraft blade (214); the second synchronous feed adjustment unit (4) includes a second sensor connector (411) fixed by bolts and a second line structured light sensor (412) fixed by bolts on the second sensor connector (411), the assembly height of the second sensor connector (411) is such that the second line structured light sensor (412) measures the middle part of the aircraft blade (214); the third synchronous feed adjustment unit (5) includes a third sensor connector (511) fixed by bolts and a third line structured light sensor (512) fixed by bolts on the third sensor connector (511), the assembly height of the third sensor connector (511) is such that the third line structured light sensor (512) measures the upper part of the aircraft blade (214).

6. The aircraft blade measuring device based on three sets of line structured optical sensors according to claim 5, characterized in that, The first sensor connector (311) in the first synchronous feed adjustment unit (3), the second sensor connector (411) in the second synchronous feed adjustment unit (4), and the third sensor connector (511) in the third synchronous feed adjustment unit (5) have different assembly heights, so that the first line structured light sensor (312), the second line structured light sensor (412), and the third line structured light sensor (512) mounted thereon respectively measure the lower, middle, and upper parts of the aircraft blade (214).

7. The aircraft blade measuring device based on three sets of line structured optical sensors according to claim 1, characterized in that, The clamping mechanism (213) uses a tenon and mortise connection structure to fix the aircraft blade (214).

8. A method for measuring aircraft blades based on three sets of line structured optical sensors, using the apparatus described in any one of claims 1 to 7, characterized in that, Includes the following steps: Step S1: Reset the contour wheel (211) to its initial position; Step S2: The aircraft blade (214) to be measured is clamped and fixed by the clamping mechanism (213). Step S3: Drive the turntable motor (21) to rotate, so that the rotating shaft (22) drives the contour wheel (211) and the aircraft blade (214) to rotate; Step S4: Obtain the circumferential rotation angle information of the aircraft blade (214); Step S5: The contour wheel (211) rotates to drive the feed adjustment of each synchronous wheel (34), thereby driving each synchronous component (33) to move linearly. The compression and reset of each synchronous component (33) are achieved by relying on the elastic restoring force of each adjusting spring (310), so that each line structure light sensor adaptively changes its measurement distance with the aircraft blade (214). Step S6: Obtain the position information of each line structured light sensor along the moving direction, and measure the longitudinal plane profile of the aircraft blade (214) through each line structured light sensor; Step S7: The aircraft blade (214) rotates once to acquire full surface information, fuses the acquired surface information data, and outputs three-dimensional coordinate point information.

9. The method for measuring aircraft blades based on three sets of line structured optical sensors according to claim 8, characterized in that, Step S7 also includes driving the aircraft blade (214) to rotate several times, and comparing the surface information data acquired in each rotation to verify repeatability.

10. The method for measuring aircraft blades based on three sets of line structured optical sensors according to claim 8, characterized in that, The circumferential rotation angle information obtained in step S4 and the position information obtained in step S6 are fused together to obtain the three-dimensional coordinate point cloud data of the surface of the aircraft blade (214).

Images