CN112762867A - Airplane engine blade three-dimensional imaging detection device and detection method - Google Patents
Airplane engine blade three-dimensional imaging detection device and detection method Download PDFInfo
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- CN112762867A CN112762867A CN202011592016.8A CN202011592016A CN112762867A CN 112762867 A CN112762867 A CN 112762867A CN 202011592016 A CN202011592016 A CN 202011592016A CN 112762867 A CN112762867 A CN 112762867A
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- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/30—Measuring arrangements characterised by the use of optical techniques for measuring roughness or irregularity of surfaces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
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Abstract
The invention discloses a three-dimensional imaging detection device and a detection method for an aircraft engine blade, and belongs to the technical field of aircraft engine blade detection. The three-dimensional imaging detection device and the detection method for the aircraft engine blade have the advantages that after the aircraft engine blade is conveyed into the detection port of the detection block, the engine blade is imaged by the camera light source in the detection port, the miniature hydraulic cylinders are controlled by the control cabinet, the length of the extension of the detection pipe is controlled along with the extension length of the aircraft engine blade, and the flatness of the surface of the aircraft engine blade is detected.
Description
Technical Field
The invention relates to the technical field of aircraft engine blade detection, in particular to a three-dimensional imaging detection device and a detection method for an aircraft engine blade.
Background
An aircraft engine is a highly complex and precise thermal machine and is used for providing power required by flying of an aircraft. The heart of the airplane is known as 'industrial flower', which directly affects the performance, reliability and economy of the airplane and is an important embodiment of national science and technology, industry and national defense strength. At present, only a few countries such as the united states, russia, the united kingdom, france and the like which can independently develop high-performance aircraft engines in the world have high technical thresholds, and the aircraft engines provide engines required by flight for aircrafts. The research and development work of the engine has the characteristics of high technical difficulty, high cost, long period, decisive influence on the performance of the aircraft and the success rate and progress of the aircraft development, and the engine technology has good dual-purpose characteristics of military and civil use and has important significance on national defense and national economy. The engine research and development work is characterized by large technical difficulty, high cost, long period, and decisive influence of the engine on the performance of the airplane and the success or failure and progress of the airplane development, and the engine technology has good dual-purpose characteristics of military and civil, and has important significance on national defense and national economy. Therefore, several countries in the world which can independently develop advanced aero-engines do not take the aero-engine with priority as the national policy, the engine technology is classified as the national and national defense key technology, a large amount of investment is given, the engines are guaranteed to develop relatively independently in advance, and the export of the key technology is strictly forbidden. Some aviation engines have also developed important technical development plans in later industrial countries, trying to establish the ability to independently develop or participate in international cooperation to develop advanced aviation engines;
the diameter of the fan blades is generally large, and varies from one meter to more than three meters. The fan blades mainly have the functions of primarily compressing air entering an engine, dividing the compressed air into two paths, enabling one path of the compressed air to enter the inner duct for continuous compression and enabling the other path of the compressed air to flow into the outer duct for direct high-speed discharge, and generating huge thrust. It may not be thought that more than 80% of the thrust of a turbofan engine is provided by the gas directly exiting the bypass, and the fan blades are typically made of titanium alloys and composites. The fan blades of the GE are generally carbon fiber composite materials. The specific strength of the composite material is very high, so that the engine rotating speed is high, and the composite material with high specific strength does not have the strength problem;
the air that current engine blade need get into the engine in the use carries out preliminary compression, the gas after the compression divides two the tunnel, get into interior duct all the way and continue the compression, flow into the direct high-speed discharge of outer duct all the way, produce huge thrust, consequently, the requirement to aircraft engine blade's surface smoothness is very high, after aircraft engine blade processing is accomplished, need detect the blade, current aircraft generator blade is mainly with artifical visual inspection when detecting more, but because work load is big, artifical final inspection is inefficient, long-time visual fatigue that easily looks at, very easily cause the missed measure, bury unpredictable potential safety hazard under the performance to follow-up equipment.
Disclosure of Invention
The invention provides a three-dimensional imaging detection device and a detection method for an aircraft engine blade, which are based on the technical problems that the existing aircraft engine blade is mainly subjected to manual visual inspection during detection, but due to large workload, the efficiency of manual final inspection is low, the omission is easily caused, and unpredictable potential safety hazards are buried in the service performance of subsequent equipment.
The invention provides an aircraft engine blade three-dimensional imaging detection device, which comprises an installation base and a control cabinet, wherein the upper surface of the installation base is fixedly connected with a guide block, a conveying device is arranged between the inner surfaces of the two ends of the installation base, the conveying device comprises a first chain wheel and a second chain wheel, the upper surface of the installation base, which is positioned between the two guide blocks, is fixedly connected with a detection device, the detection device comprises a detection block, the surface of one side of the installation base is fixedly connected with an installation block, the upper surface of the installation block is fixedly connected with a driving device, the driving device comprises a connecting seat, the guide block is positioned below the conveying device, the conveying device is controlled by the driving device, and the control cabinet respectively controls the conveying device, the driving device and the detection device;
a servo motor is fixedly arranged on the upper surface of the connecting seat;
the detection device is characterized in that a detection port is formed in the surface of one side of the detection block, a mounting hole is formed in the inner wall of the detection port, and a camera light source is fixedly connected to the inner wall of the detection port.
Preferably, the surface of first sprocket and second sprocket passes through chain drive and connects, the connecting axle of first sprocket and the connecting axle of second sprocket all pass through bearing and the both sides inner wall fixed connection of installation base, two the one end surface of second sprocket connecting axle all runs through and extends to one side surface and the first gear of fixedly connected with of installation base, the equal fixedly connected with backup pad of both ends surface of chain bucket axle.
Preferably, it is a plurality of the one end fixed surface of backup pad is connected with the conveying post, and is a plurality of first mounting groove and second mounting groove have all been seted up to the both sides surface of conveying post, the inner wall of first mounting groove and second mounting groove fixed mounting respectively has first infrared laser receiver and the infrared laser receiver of second.
Preferably, third mounting groove and fourth mounting groove have all been seted up to the both sides internal surface of installation base, the inner wall of third mounting groove and fourth mounting groove is fixed mounting respectively has first infrared laser emitter and second infrared laser emitter, and is a plurality of first infrared laser receiver's electrode all with first infrared laser emitter's electrode electric connection, it is a plurality of second infrared laser receiver's electrode all with second infrared laser emitter's electrode electric connection.
Preferably, the one end fixed surface of conveying post is connected with the sucking disc, one side fixed surface of conveying post is connected with the connecting pipe, the inner wall of connecting pipe and the inner wall fixed intercommunication of sucking disc, it is a plurality of the connecting pipe is located the equal fixedly connected with first solenoid valve of inner wall of conveying post inside.
Preferably, the ring channel has been seted up to one side internal surface of installation base, the inner wall of ring channel is the T shape, the rubber tube has been cup jointed in the inner wall activity of ring channel, the external fixed surface of rubber tube is connected with the support bar, and is a plurality of support bar evenly distributed is in the surface of rubber tube, the one end of connecting pipe and the fixed intercommunication of inner wall of rubber tube, the installation cavity has been seted up to the inner wall of installation base.
Preferably, the inner wall fixedly connected with transition dish of installation cavity, the fixed intercommunication of one side inner wall of transition dish has the connection pad, the connection pad surface cup joints with the inner wall rotation of rubber tube, the fixed intercommunication of the opposite side inner wall of transition dish has the breather pipe, the last fixed surface of installation piece installs the vacuum pump, the one end surface of breather pipe and the fixed intercommunication of the air exhaust end of vacuum pump.
Preferably, the output shaft of the servo motor is fixedly connected with a rotating shaft through a coupler, the outer surface of the rotating shaft is fixedly connected with a second gear, the outer surface of one side of the mounting base is fixedly connected with a connecting rod through a bearing, the outer surface of one end of the connecting rod is fixedly connected with a third gear, the second gear is respectively in meshing transmission with the first gear and the third gear, and the third gear is in meshing transmission with the other first gear.
Preferably, it is a plurality of the equal fixed mounting of inner wall of mounting hole has miniature pneumatic cylinder, miniature pneumatic cylinder includes piston and hydraulic stem, the one end external surface fixedly connected with detecting tube that the piston was kept away from to the hydraulic stem, the one end fixed surface of detecting tube is connected with circular rubber head, the inner wall fixed mounting of detecting tube has pressure sensor, the inner wall that the detecting tube is located between pressure sensor and the circular rubber head is provided with liquid.
Preferably, the detection method based on the detection device specifically includes the following steps:
firstly, a detection person places an aircraft engine blade to be detected on a guide block on the left side, the detection person controls a conveying device, a driving device and a detection device to start through a control cabinet, a servo motor drives a second gear to rotate through a rotating shaft, a second rack is meshed with an adjacent first gear and a third gear to further drive the adjacent first gear and the third gear to rotate, the third gear is meshed with another first gear to further drive another first gear to rotate, the two first gears drive two second chain wheels to rotate, and the second chain wheels drive the first chain wheels to rotate through chains;
step two, the transmission column moves along with the transmission of the chain, the transmission column drives the connecting pipe to move, the connecting pipe drives the rubber pipe to move along with the inner wall of the annular groove in the annular groove, the supporting bar supports the rubber pipe, the frame performance of the rubber pipe is increased through the supporting bar, the connecting pipe is convenient for driving the rubber pipe to move, the rubber pipe is rotatably sleeved with the connecting disc and further communicated with the inner wall of the transition disc, the vacuum pump is communicated with the transition disc through the vent pipe, after the first infrared laser transmitter is communicated with the first infrared laser receiver wire harness, the first electromagnetic valve connected with the first infrared laser receiver is conducted, the communication between the connecting pipe and the sucker is controlled, so that the vacuum pump can vacuumize the sucker at one end of the corresponding transmission column, and after the second infrared laser transmitter is communicated with the second infrared laser receiver wire harness, the first electromagnetic valve connected with the second infrared laser receiver is conducted, controlling the connection pipe and the sucker to be closed, so that the vacuum pump can not vacuumize the sucker at one end of the corresponding transmission column;
step three, after the aircraft engine blade is conveyed into the detection port of the detection block, the micro hydraulic cylinders are controlled by the control cabinet, the length of each micro hydraulic cylinder driven by the extension of the aircraft engine blade controls the extension length of the detection pipe, when the surface of the aircraft engine blade is provided with a convex part, the convex part extrudes the circular rubber head, liquid in the detection pipe extrudes the pressure sensor, when the pressure value detected by the pressure sensor reaches a certain value, the control cabinet controls the conveying device, the driving device and the detection device to stop, a detector can know the coordinates of the convex part of the aircraft engine blade on the control panel of the control cabinet to indicate that the aircraft engine blade is unqualified, the detector can take out the aircraft engine blade for marking, when the aircraft engine blade is qualified, the aircraft engine blade can smoothly pass through the detection port and move to the upper part of the right guide block, and conveying the blades of the aircraft engine through the conveying device on the right side, and normally blanking.
The beneficial effects of the invention are as follows:
1. by arranging the conveying devices between the inner surfaces of the two ends of the mounting base, the conveying devices comprise the first chain wheel and the second chain wheel, the purpose that the two first gears drive the two second chain wheels to rotate, the second chain wheels drive the first chain wheels to rotate through the chains, the conveying columns move along with the transmission of the chains is achieved, in the moving process, the rubber tube is driven by the connecting tube to move in the annular groove along with the inner wall of the annular groove, the supporting strip supports the rubber tube, the support bars increase the frame performance of the rubber tube, so that the connecting tube drives the rubber tube to move conveniently, the rubber tube is rotatably sleeved with the connecting disc, and then with the inner wall intercommunication of transition dish, the effect that the vacuum pump passes through breather pipe and transition dish intercommunication to solved current aircraft engine blade and needed the manual work to detect, because work load is big, the problem that manual work detection efficiency is low.
2. Be located the last fixed surface detection device between two guide blocks through setting up the installation base, detection device is including detecting the piece, reached when aircraft engine blade convey to the detection intraoral back that detects the piece, detect intraoral camera light source and image to engine blade, miniature pneumatic cylinder passes through switch board control, along with the length control every miniature pneumatic cylinder of aircraft engine blade stretching into drives the length that the test tube stretched out, detect the effect of the roughness on aircraft engine blade surface, thereby solved current aircraft engine blade and mainly examined when detecting with artifical visual inspection more, but because the work load is big, artifical final inspection inefficiency, very easily cause the missed measure, bury the problem of unpredictable potential safety hazard under the performance to follow-up equipment.
3. Through the last fixed surface who sets up the installation piece be connected with drive arrangement, drive arrangement includes the connecting seat, the guide block is located conveyer's below, it is rotatory to have reached to drive the second gear through the pivot through servo motor, second rack and adjacent a first gear and third gear engagement, and then drive adjacent first gear and third gear rotation, third gear and another first gear engagement, and then it is rotatory to drive another first gear, two first gears drive two second sprockets and carry out the pivoted effect, thereby the problem that servo motor can't drive two second sprockets simultaneously and carry out synchronous revolution has been solved.
Drawings
FIG. 1 is a schematic diagram of a three-dimensional imaging detection device and a detection method for an aircraft engine blade according to the present invention;
FIG. 2 is a side view of a mounting base structure of an aircraft engine blade stereo imaging detection device and detection method provided by the invention;
FIG. 3 is a front view of a third gear structure of the three-dimensional imaging detection device and the detection method for the blades of the aircraft engine according to the present invention;
FIG. 4 is a sectional view of a mounting base structure of an aircraft engine blade three-dimensional imaging detection device and a detection method according to the invention;
FIG. 5 is a structural cross-sectional view of a detection block of the three-dimensional imaging detection device and the detection method for the blades of the aircraft engine provided by the invention;
FIG. 6 is a perspective view of a chain structure of the three-dimensional imaging detection device and the detection method for the blades of the aircraft engine according to the present invention;
FIG. 7 is a perspective view of a detection block structure of the aircraft engine blade three-dimensional imaging detection apparatus and detection method according to the present invention;
FIG. 8 is a structural cross-sectional view of a micro hydraulic cylinder of the three-dimensional imaging detection device and the detection method for the blades of the aircraft engine, which are provided by the invention;
FIG. 9 is an enlarged view of the structure at the position A in FIG. 4 of the three-dimensional imaging detection device and the detection method for the blades of the aircraft engine according to the present invention;
fig. 10 is an enlarged view of a structure B in fig. 4 of a three-dimensional imaging detection device and a detection method for an aircraft engine blade according to the present invention.
In the figure: 1. installing a base; 2. a control cabinet; 3. a guide block; 4. a first sprocket; 401. a second sprocket; 402. a chain; 403. a first gear; 404. a transfer column; 405. a first infrared laser receiver; 406. a second infrared laser receiver; 407. a first infrared laser transmitter; 408. a second infrared laser transmitter; 409. a suction cup; 410. a connecting pipe; 411. a first solenoid valve; 412. an annular groove; 413. a rubber tube; 414. a supporting strip; 415. a transition disk; 416. a breather pipe; 417. a vacuum pump; 5. a detection block; 501. a detection port; 502. a micro hydraulic cylinder; 503. a detection tube; 504. a circular rubber head; 505. a pressure sensor; 6. mounting blocks; 601. a connecting seat; 602. a servo motor; 603. a second gear; 604. a third gear.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
Referring to fig. 1-10, an aircraft engine blade three-dimensional imaging detection device and detection method includes an installation base 1 and a control cabinet 2, a guide block 3 is fixedly connected to the upper surface of the installation base 1, a conveying device is arranged between the inner surfaces of the two ends of the installation base 1 and comprises a first chain wheel 4 and a second chain wheel 401, the outer surfaces of the first chain wheel 4 and the second chain wheel 401 are in transmission connection through a chain 402, a connecting shaft of the first chain wheel 4 and a connecting shaft of the second chain wheel 401 are fixedly connected with the inner walls of the two sides of the installation base 1 through bearings, the outer surfaces of one ends of the connecting shafts of the two second chain wheels 401 penetrate through and extend to the outer surface of one side of the installation base 1 and are fixedly connected with a first gear 403, and supporting plates are fixedly connected to the outer surfaces of the.
One end surface of the plurality of support plates is fixedly connected with a transmission column 404, the outer surfaces of two sides of the plurality of transmission columns 404 are respectively provided with a first installation groove and a second installation groove, the inner walls of the first installation groove and the second installation groove are respectively and fixedly provided with a first infrared laser receiver 405 and a second infrared laser receiver 406, the inner surfaces of two sides of the installation base 1 are respectively provided with a third installation groove and a fourth installation groove, the inner walls of the third installation groove and the fourth installation groove are respectively and fixedly provided with a first infrared laser emitter 407 and a second infrared laser emitter 408, the electrodes of the plurality of first infrared laser receivers 405 are respectively and electrically connected with the electrode of the first infrared laser emitter 407, the electrodes of the plurality of second infrared laser receivers 406 are respectively and electrically connected with the electrode of the second infrared laser emitter 408, one end surface of the transmission column 404 is fixedly connected with a suction cup 409, the outer surface of one side of the transmission column, the connecting pipe 410 is made of steel, the inner wall of the connecting pipe 410 is fixedly communicated with the inner wall of the suction cup 409, and the inner walls of the connecting pipes 410 inside the conveying column 404 are fixedly connected with first electromagnetic valves 411.
An annular groove 412 is formed in the inner surface of one side of the mounting base 1, the inner wall of the annular groove 412 is in a T shape, a rubber pipe 413 is movably sleeved on the inner wall of the annular groove 412, a supporting strip 414 is fixedly connected to the outer surface of the rubber pipe 413, the supporting strips 414 are uniformly distributed on the outer surface of the rubber pipe 413, one end of a connecting pipe 410 is fixedly communicated with the inner wall of the rubber pipe 413, a mounting cavity is formed in the inner wall of the mounting base 1, a transition disc 415 is fixedly connected to the inner wall of the mounting cavity, a connecting disc is fixedly communicated with the inner wall of one side of the transition disc 415, the outer surface of the connecting disc is rotatably sleeved with the inner wall of the rubber pipe 413, an air vent pipe 416 is fixedly communicated with the inner wall of the other side of the;
the two first gears 403 drive the two second sprockets 401 to rotate, the second sprockets 401 drive the first sprockets 4 to rotate through the chains 402, the conveying columns 404 move along with the transmission of the chains 402, the rubber pipes 413 are driven to move along with the inner walls of the annular grooves 412 in the annular grooves 412 through the connecting pipes 410 in the moving process, the rubber pipes 413 are supported by the supporting bars 414, the frame performance of the rubber pipes 413 is improved through the supporting bars 414, the connecting pipes 410 drive the rubber pipes 413 to move, the rubber pipes 413 are rotatably sleeved with the connecting discs and further communicated with the inner walls of the transition discs 415, and the vacuum pump 417 is communicated with the transition discs 415 through the vent pipes 416, so that the problem that the existing aircraft engine blades need manual detection due to large workload and low manual detection efficiency is solved;
the upper surface of the installation base 1, which is positioned between the two guide blocks 3, is fixedly connected with a detection device, the detection device comprises a detection block 5, the surface of one side of the installation base 1 is fixedly connected with an installation block 6, the upper surface of the installation block 6 is fixedly connected with a driving device, the driving device comprises a connecting seat 601, the guide blocks 3 are positioned below a conveying device, the conveying device is controlled by the driving device, and the control cabinet 2 respectively controls the conveying device, the driving device and the detection device;
the servo motor 602 is fixedly installed on the upper surface of the connecting seat 601, the output shaft of the servo motor 602 is fixedly connected with a rotating shaft through a coupler, the outer surface of the rotating shaft is fixedly connected with a second gear 603, the outer surface of one side of the installation base 1 is fixedly connected with a connecting rod through a bearing, the outer surface of one end of the connecting rod is fixedly connected with a third gear 604, the second gear 603 is respectively in meshing transmission with one first gear 403 and the third gear 604, the third gear 604 is in meshing transmission with the other first gear 403, the servo motor drives the second gear 603 to rotate through the rotating shaft, the second rack is meshed with the adjacent first gear 403 and the adjacent third gear 604 to further drive the adjacent first gear 403 and the adjacent third gear 604 to rotate, the third gear 604 is meshed with the other first gear 403 to further drive the other first gear 403 to rotate, and the two first gears 403 drive the two second chain wheels 401 to rotate, therefore, the problem that the servo motor 602 cannot simultaneously drive the two second chain wheels 401 to synchronously rotate is solved;
the detection block 5 is provided with a detection port 501 on one side surface, the detection port 501 is provided with mounting holes on the inner wall, the inner wall of the detection port 501 is fixedly connected with a camera light source, the inner walls of the mounting holes are fixedly provided with micro hydraulic cylinders 502, each micro hydraulic cylinder 502 comprises a piston and a hydraulic rod, the outer surface of one end of each hydraulic rod far away from the piston is fixedly connected with a detection tube 503, the surface of one end of each detection tube 503 is fixedly connected with a circular rubber head 504, the inner wall of each detection tube 503 is fixedly provided with a pressure sensor 505, the inner wall of each detection tube 503 between the pressure sensor 505 and the circular rubber head 504 is provided with liquid, after the aircraft engine blades are transmitted into the detection ports 501 of the detection block 5, the camera light source in the detection ports 501 images the engine blades, the micro hydraulic cylinders 502 are controlled by a control cabinet 2, the extension length of each micro hydraulic cylinder 502 which drives the detection tubes, the effect of detecting the flatness of the surface of the aircraft engine blade solves the problems that the existing aircraft engine blade is mainly manually and visually detected during detection, but due to large workload and low manual final detection efficiency, detection omission is easily caused, and unpredictable potential safety hazards are buried in the service performance of subsequent equipment.
The working principle is as follows: a detection person places an aircraft engine blade to be detected on the guide block 3 on the left side, the detection person controls the transmission device, the driving device and the detection device to start through the control cabinet 2, the servo motor 602 drives the second gear 603 to rotate through the rotating shaft, the second rack is meshed with one adjacent first gear 403 and one adjacent third gear 604 to further drive the adjacent first gear 403 and the adjacent third gear 604 to rotate, the third gear 604 is meshed with the other first gear 403 to further drive the other first gear 403 to rotate, the two first gears 403 drive the two second chain wheels 401 to rotate, and the second chain wheels 401 drive the first chain wheels 4 to rotate through the chains 402;
the transmission column 404 moves along with the transmission of the chain 402, the transmission column 404 drives the connection pipe 410 to move, the connection pipe 410 drives the rubber pipe 413 to move along with the inner wall of the annular groove 412 in the annular groove 412, the support bar 414 supports the rubber pipe 413, the support bar 414 increases the frame of the rubber pipe 413, so that the connection pipe 410 drives the rubber pipe 413 to move, the rubber pipe 413 is rotatably sleeved with the connection disc and further communicated with the inner wall of the transition disc 415, the vacuum pump 417 is communicated with the transition disc 415 through the vent pipe 416, after the first infrared laser emitter 407 is communicated with the first infrared laser receiver 405, the first electromagnetic valve 411 connected with the first infrared laser receiver 405 is communicated, the connection pipe 410 is controlled to be communicated with the suction cup 409, so that the vacuum pump 417 can vacuumize the suction cup 409 at one end of the corresponding transmission column 404, and after the second infrared laser emitter 408 is communicated with the second infrared laser receiver 406, the first electromagnetic valve 411 connected with the second infrared laser receiver 406 is conducted to control the connection between the connection pipe 410 and the suction cup 409 to be closed, so that the vacuum pump 417 can not vacuumize the suction cup 409 at one end of the corresponding transmission column 404;
after the aircraft engine blade is conveyed into the detection port 501 of the detection block 5, the micro hydraulic cylinders 502 are controlled by the control cabinet 2, the length of each micro hydraulic cylinder 502 which drives the detection pipe 503 to extend is controlled along with the extending length of the aircraft engine blade, when the surface of the aircraft engine blade is provided with a convex part, the convex part extrudes the circular rubber head 504, liquid in the detection pipe 503 extrudes the pressure sensor 505, when the pressure value detected by the pressure sensor 505 reaches a certain value, the control cabinet 2 controls the conveying device, the driving device and the detection device to stop, a detector can know the coordinates of the convex part of the aircraft engine blade on the control panel of the control cabinet 2 to indicate that the aircraft engine blade is unqualified, the detector can take out the aircraft engine blade for identification, when the aircraft engine blade is qualified, the aircraft engine blade can smoothly pass through the detection port 501, and moving to the upper part of the right guide block 3, and conveying the aircraft engine blades through the right conveying device to perform normal blanking.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (10)
1. The utility model provides an aircraft engine blade stereoscopic imaging detection device, includes installation base (1) and switch board (2), its characterized in that: the upper surface of the mounting base (1) is fixedly connected with a guide block (3), conveying devices are arranged between the inner surfaces of two ends of the mounting base (1) and comprise a first chain wheel (4) and a second chain wheel (401), the upper surface of the mounting base (1) between the two guide blocks (3) is fixedly connected with a detection device, the detection device comprises a detection block (5), one side surface of the mounting base (1) is fixedly connected with a mounting block (6), the upper surface of the mounting block (6) is fixedly connected with a driving device, the driving device comprises a connecting seat (601), the guide blocks (3) are located below the conveying devices, the conveying devices are controlled by the driving devices, and the control cabinet (2) respectively controls the conveying devices, the driving devices and the detection devices;
a servo motor (602) is fixedly arranged on the upper surface of the connecting seat (601);
the detection device is characterized in that a detection port (501) is formed in the surface of one side of the detection block (5), a mounting hole is formed in the inner wall of the detection port (501), and a camera light source is fixedly connected to the inner wall of the detection port (501).
2. The aircraft engine blade stereo imaging detection device of claim 1, wherein: the surface of first sprocket (4) and second sprocket (401) passes through chain (402) transmission and connects, the connecting axle of first sprocket (4) and the connecting axle of second sprocket (401) all through the both sides inner wall fixed connection of bearing and installation base (1), two the one end surface of second sprocket (401) connecting axle all runs through and extends to one side surface and the first gear of fixedly connected with (403) of installation base (1), the equal fixedly connected with backup pad of both ends surface of chain (402) bucket axle.
3. The aircraft engine blade stereo imaging detection device according to claim 2, characterized in that: a plurality of the one end fixed surface of backup pad is connected with conveying post (404), and is a plurality of first mounting groove and second mounting groove have all been seted up to the both sides surface of conveying post (404), the inner wall of first mounting groove and second mounting groove fixed mounting respectively has first infrared laser receiver (405) and second infrared laser receiver (406).
4. An aircraft engine blade stereo imaging detection device according to claim 3, characterized in that: third mounting groove and fourth mounting groove have all been seted up to the both sides internal surface of installation base (1), the inner wall of third mounting groove and fourth mounting groove respectively fixed mounting have first infrared laser emitter (407) and second infrared laser emitter (408), and is a plurality of the electrode of first infrared laser receiver (405) all with the electrode electric connection of first infrared laser emitter (407), it is a plurality of the electrode of second infrared laser receiver (406) all with the electrode electric connection of second infrared laser emitter (408).
5. An aircraft engine blade stereo imaging detection device according to claim 3, characterized in that: one end fixed surface of conveying post (404) is connected with sucking disc (409), one side outer fixed surface of conveying post (404) is connected with connecting pipe (410), the inner wall of connecting pipe (410) and the fixed intercommunication of inner wall of sucking disc (409), it is a plurality of connecting pipe (410) are located the equal fixedly connected with first solenoid valve (411) of inner wall of conveying post (404) inside.
6. The aircraft engine blade stereo imaging detection device of claim 1, wherein: annular groove (412) have been seted up to one side internal surface of installation base (1), the inner wall of annular groove (412) is the T shape, rubber tube (413) have been cup jointed in the inner wall activity of annular groove (412), the external fixed surface of rubber tube (413) is connected with support bar (414), and is a plurality of support bar (414) evenly distributed is in the surface of rubber tube (413), the one end of connecting pipe (410) and the fixed intercommunication of inner wall of rubber tube (413), the installation cavity has been seted up to the inner wall of installation base (1).
7. The aircraft engine blade stereo imaging detection device of claim 6, wherein: the inner wall fixedly connected with transition dish (415) of installation cavity, the fixed intercommunication of one side inner wall of transition dish (415) has the connection pad, the connection pad surface cup joints with the inner wall rotation of rubber tube (413), the fixed intercommunication of the opposite side inner wall of transition dish (415) has breather pipe (416), the last fixed surface of installation piece (6) installs vacuum pump (417), the one end surface of breather pipe (416) and the fixed intercommunication of the bleed end of vacuum pump (417).
8. The aircraft engine blade stereo imaging detection device according to claim 2, characterized in that: the output shaft of servo motor (602) passes through shaft coupling fixedly connected with pivot, the outer fixed surface of pivot is connected with second gear (603), one side surface of installation base (1) passes through bearing fixedly connected with connecting rod, the one end outer fixed surface of connecting rod is connected with third gear (604), second gear (603) respectively with one first gear (403) with third gear (604) meshing transmission, third gear (604) and another first gear (403) meshing transmission.
9. The aircraft engine blade stereo imaging detection device of claim 1, wherein: a plurality of the equal fixed mounting of inner wall of mounting hole has miniature pneumatic cylinder (502), miniature pneumatic cylinder (502) include piston and hydraulic stem, the one end external surface fixed connection that the piston was kept away from to the hydraulic stem has detecting tube (503), the one end fixed surface of detecting tube (503) is connected with circular rubber head (504), the inner wall fixed mounting of detecting tube (503) has pressure sensor (505), the inner wall that detecting tube (503) are located between pressure sensor (505) and circular rubber head (504) is provided with liquid.
10. The detection method based on the aircraft engine blade stereo imaging detection device according to any one of claims 1 to 9, is characterized by comprising the following steps:
firstly, a detection person places an aircraft engine blade to be detected on a guide block (3) on the left side, the detection person controls a conveying device, a driving device and a detection device to start through a control cabinet (2), a servo motor (602) drives a second gear (603) to rotate through a rotating shaft, a second rack is meshed with an adjacent first gear (403) and a third gear (604) to further drive the adjacent first gear (403) and the third gear (604) to rotate, the third gear (604) is meshed with another first gear (403) to further drive another first gear (403) to rotate, the two first gears (403) drive two second chain wheels (401) to rotate, and the second chain wheels (401) drive first chain wheels (4) to operate through chains (402);
step two, the transmission column (404) moves along with the transmission of the chain (402), the transmission column (404) drives the connecting pipe (410) to move, the connecting pipe (410) drives the rubber pipe (413) to move along with the inner wall of the annular groove (412) in the annular groove (412), the supporting strip (414) supports the rubber pipe (413), the frame performance of the rubber pipe (413) is improved through the supporting strip (414), the connecting pipe (410) drives the rubber pipe (413) to move conveniently, the rubber pipe (413) is rotatably sleeved with the connecting disc and further communicated with the inner wall of the transition disc (415), the vacuum pump (417) is communicated with the transition disc (415) through the vent pipe (416), when the first infrared laser emitter (407) is communicated with the first infrared laser receiver (405) through a wiring harness, the first electromagnetic valve (411) connected with the first infrared laser receiver (405) is conducted, and the connection between the connecting pipe (410) and the sucking disc (409) is controlled, enabling a vacuum pump (417) to vacuumize the suction cup (409) at one end of the corresponding conveying column (404), and after the second infrared laser transmitter (408) is in wire harness communication with the second infrared laser receiver (406), conducting a first electromagnetic valve (411) connected with the second infrared laser receiver (406), controlling the connection between the connecting pipe (410) and the suction cup (409) to be closed, so that the vacuum pump (417) cannot vacuumize the suction cup (409) at one end of the corresponding conveying column (404);
step three, after the aircraft engine blade is conveyed into a detection port (501) of a detection block (5), a camera light source in the detection port (501) images the engine blade, the micro hydraulic cylinders (502) are controlled by the control cabinet (2), the length of the extension of each micro hydraulic cylinder (502) driving a detection pipe (503) along with the extension length of the aircraft engine blade is controlled, when a raised part is arranged on the surface of the aircraft engine blade, the raised part extrudes a circular rubber head (504), liquid in the detection pipe (503) extrudes a pressure sensor (505), when a pressure value detected by the pressure sensor (505) reaches a certain value, the control cabinet (2) controls the conveying device, the driving device and the detection device to stop, and a detection person can know the coordinates of the raised part of the aircraft engine blade on a control panel of the control cabinet (2), the aircraft engine blade is unqualified, and the inspector can take out the aircraft engine blade to be identified, and when the aircraft engine blade is qualified, the aircraft engine blade can smoothly pass through the detection port (501), moves to the upper part of the right guide block (3), and is conveyed through the conveying device on the right side to perform normal blanking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011592016.8A CN112762867A (en) | 2020-12-29 | 2020-12-29 | Airplane engine blade three-dimensional imaging detection device and detection method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011592016.8A CN112762867A (en) | 2020-12-29 | 2020-12-29 | Airplane engine blade three-dimensional imaging detection device and detection method |
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| Publication Number | Publication Date |
|---|---|
| CN112762867A true CN112762867A (en) | 2021-05-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011592016.8A Withdrawn CN112762867A (en) | 2020-12-29 | 2020-12-29 | Airplane engine blade three-dimensional imaging detection device and detection method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114384090A (en) * | 2021-12-30 | 2022-04-22 | 中国飞机强度研究所 | Device and method for detecting damage to barrel section of machine body in strength test |
-
2020
- 2020-12-29 CN CN202011592016.8A patent/CN112762867A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114384090A (en) * | 2021-12-30 | 2022-04-22 | 中国飞机强度研究所 | Device and method for detecting damage to barrel section of machine body in strength test |
| CN114384090B (en) * | 2021-12-30 | 2023-12-22 | 中国飞机强度研究所 | Device and method for detecting damage of fuselage barrel section in strength test |
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Application publication date: 20210507 |