CN105136048A - Method for detecting quality of airplane covering-riveting assembling surface - Google Patents
Method for detecting quality of airplane covering-riveting assembling surface Download PDFInfo
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- CN105136048A CN105136048A CN201510522567.XA CN201510522567A CN105136048A CN 105136048 A CN105136048 A CN 105136048A CN 201510522567 A CN201510522567 A CN 201510522567A CN 105136048 A CN105136048 A CN 105136048A
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Abstract
The invention discloses a method for detecting quality of an airplane covering-riveting assembling surface, comprising steps of adopting a 2D displacement sensor as a measurement member, arranging the 2D displacement sensor above a detected point during the measurement, enabling the distance between the 2D displacement sensor and the detected point to be in a center point in a measurement range of the 2D displacement sensor, receiving and processing the measurement data of the 2D displacement sensor by a measurement system, and calculating various technical index parameters of the airplane covering riveting surface quality according to various calculation methods. The invention is high in efficiency, good in reliability and easy in usage, and has many measurement functions, uses one measurement method to replace various measurement methods and multiple times of measurement, and improves the quality of the airplane covering-riveting assembly surface and production efficiency.
Description
Technical field
The present invention relates to aero-manufacturing technology field, be specifically related to a kind of method detecting aircraft skin riveted joint assembly surface quality.
Background technology
The effect of aircraft skin maintains aircraft configuration, makes it to have good aerodynamic characteristics.Covering to bear after aerodynamic effect by force transmission on the fuselage wing skeleton be connected, stressed complexity, and covering directly and extraneous contact in addition, so not only require that skin material intensity is high, plasticity good, also requires smooth surface, have higher resistance to corrosion.
In present generation aircraft riveted joint assembling process, aircraft skin quality control on the surface is the important technology index affecting riveting quality, aircraft skin surface quality mainly comprises the height of rivet top relative to aircraft skin, around rivet aircraft skin local deflection, covering docking time the technical indicator such as gap width, jump, and the quality of riveting quality will directly have influence on the aeroperformance of aircraft, fuel-economy type, fatigue lifetime and security.Concerning Modern fighter, the quality of aircraft skin riveted joint surface quality will have influence on the Stealth Fighter of aircraft, thus directly have influence on the operational performance of aircraft, and the riveting quality therefore improving aircraft skin just seems important especially in riveted joint assembling process.
In present stage, also do not have a kind of detection method effectively to detect each technical indicator of riveted joint surface quality, riveted joint ailhead is utilize triangle table to carry out measuring or utilize touch sensor to carry out two-sided measurement online to calculate height value relative to the height of aircraft skin simultaneously; Aircraft skin butt-joint clearance width and jump rely on manually to carry out measurement respectively and draw, above measuring method is all the contact type measurement adopted; That around rivet, the deformation of aircraft skin local relies on is artificial visually examine.
Summary of the invention
Instant invention overcomes in prior art and also do not have a kind of detection method can carry out the effective deficiency detected to each technical indicator of riveted joint surface quality simultaneously, there is provided a kind of and not only can detect the height value of rivet head relative to aircraft skin, and the deformation of the local of aircraft skin around rivet can also be detected and show with figure, thus judge the quality of riveting products surface quality according to the deformation of product local around every rivet.Also there is the method for the detection aircraft skin riveted joint assembly surface quality of the function of survey aircraft covering butt-joint clearance width and jump.
For achieving the above object, the present invention is by the following technical solutions:
Detect the method for aircraft skin riveted joint assembly surface quality, it comprises:
A, first 2D displacement transducer is installed to the side of boring upward pressure pin in riveting system;
B, when brill riveting system is after on rivet to aircraft skin, bore riveting system aircraft skin is moved, and rivet is moved to immediately below 2D displacement transducer, bore riveting system and send measurement instruction to measuring system, image data instruction is sent to 2D displacement transducer after measuring system receives measurement instruction, 2D displacement transducer sends measuring beam and is irradiated on rivet and aircraft skin after receiving image data instruction, measuring beam turns back to 2D displacement transducer and forms the first image data after diffuse reflection, first image data is fed back to measuring system by 2D displacement transducer,
C, by 2D displacement transducer 90-degree rotation, repeat step b obtain the second image data;
D, measuring system receive the first image data and second and gather and first to carry out being separated of valid data and interfering data after number, and then call processing module according to measurement demand and carry out process and obtain measurement data.
Further technical scheme is, described measurement data comprises the deflection of aircraft skin around the rivet head distance height value of aircraft skin, butt-joint clearance width value, butt-joint clearance jump value or rivet.
Further technical scheme is, the model of described 2D displacement transducer is Ji Enshi LG-G030.
Further technical scheme is, described brill riveting system comprises boring and riveting machine matrix, described boring and riveting machine matrix one end is provided with opening, the other end is closed, and described riveter matrix entirety is c-shaped, the top being provided with open at one end at described boring and riveting machine matrix is provided with working head, described upper working head is provided with successively upward pressure pin, auger spindle milling spindle and the head that presses; The bottom being provided with open at one end at described boring and riveting machine matrix is provided with lower pressurized strut, and described upward pressure pin and lower pressurized strut are located along the same line.
Further technical scheme is, described in the first end that presses be provided with and send screw assembly.
Compared with prior art, the invention has the beneficial effects as follows:
Measurement function of the present invention is many, and efficiency is high, and simply, same measuring method just can substitute original many measuring methods and measurement repeatedly for good reliability, use, improves surface quality and the production efficiency of aircraft skin riveted joint assembling.
Accompanying drawing explanation
Fig. 1 is on-line measurement position view of the present invention.
Fig. 2 is the structural representation boring riveting system in the present invention.
Fig. 3 is the actual measured results display figure of aircraft skin local deformation around rivet head height of the present invention and rivet.
Reference numeral name corresponding in figure is called:
1 aircraft skin, 2 rivets, 3 upward pressure pin, 42D displacement transducer, 5 measuring beams, 6 boring and riveting machine matrixes, 7 times pressurized struts, 8 send screw assembly, and 9 press head, 10 milling spindles, 11 auger spindles, 12 riveting points.
Embodiment
Below in conjunction with accompanying drawing, the present invention is further elaborated.
The method of detection aircraft skin riveted joint assembly surface quality as shown in Figure 1-2, it comprises: a, first 2D displacement transducer 4 is installed to the side of boring upward pressure pin 3 in riveting system, b, when brill riveting system is riveted to rivet 2 after on aircraft skin 1, bore riveting system aircraft skin 1 is moved, and rivet 2 is moved to immediately below 2D displacement transducer 4, bore riveting system and send measurement instruction to measuring system, image data instruction is sent to 2D displacement transducer 4 after measuring system receives measurement instruction, 2D displacement transducer 4 sends measuring beam 5 and is irradiated on rivet 2 and aircraft skin 1 after receiving image data instruction, measuring beam 5 turns back to 2D displacement transducer 4 and forms the first image data after diffuse reflection, first image data is fed back to measuring system by 2D displacement transducer 4, c, by 2D displacement transducer 4 90-degree rotation, repeat step b obtain the second image data, d, measuring system receive the first image data and second and gather and first to carry out being separated of valid data and interfering data after number, and then call processing module according to measurement demand and carry out process and obtain measurement data, described measurement data comprises the deflection of aircraft skin around the height value of rivet head distance aircraft skin, butt-joint clearance width value, butt-joint clearance jump value or rivet, the model of described 2D displacement transducer 4 is Ji Enshi LG-G030, described brill riveting system comprises boring and riveting machine matrix 6, described boring and riveting machine matrix 6 one end is provided with opening, the other end is closed, and described riveter matrix 6 is overall c-shaped, the top being provided with open at one end at described boring and riveting machine matrix 6 is provided with working head, described upper working head is provided with successively upward pressure pin 3, auger spindle 11 milling spindle 10 and presses 9, the bottom that described boring and riveting machine matrix 6 is provided with open at one end is provided with lower pressurized strut 7, and described upward pressure pin 3 and lower pressurized strut 7 are located along the same line, described in 9 one end that press be provided with and send screw assembly 8.
When 2D displacement transducer 4 is installed in the present invention, its center of slotted line can be allowed parallel with a reference axis of brill riveting system with two lines boring riveting point 12, its measuring basis line and the bottom surface of upward pressure pin 3 is made to be positioned at same level, control owing to first will carry out normal direction adjustment when carrying out brill riveting, therefore, bore riveting point 12 position and be in normal direction state, and with brill riveting point 12 central shaft the overlap calculating that can simplify measurement data and improve measuring accuracy, efficiency parallel with reference axis of the slotted line of 2D displacement transducer 4; It is in order to working depth position when ensureing that the measurement baseline of 2D displacement transducer 4 and part bore riveting overlaps that measuring basis line and the ground of upward pressure pin 3 are positioned at same level, this is that near the position owing to measuring baseline at 2D displacement transducer 4, its measuring accuracy is the highest, measurement range is maximum, position height change when 2D displacement transducer 4 moves to measurement point would not too greatly, the number this ensures that thering effective measurement data is maximum, measures just more accurate.
The principle of work of riveting drill system is as follows:
When carrying out brill riveting, first bracket locating device navigates to the position of boring riveting point 12 with aircraft skin 1, namely immediately below upward pressure pin 3, then pressurized strut 7 is descended to rise, upward pressure pin 3 declines, aircraft skin 1 is clamped, upper working head moving handle auger spindle 11 is transformed into brill riveting point 12 and then holes to aircraft skin 1 to lower feeding, return after being fed into the position of setting, glue filling device is to injecting glue in hole, upper working head is transformed into the position of boring riveting point 12 the head that presses and the Kong Zhonghou that the rivet 2 pressed on head inserts aircraft skin 1 is pressed, until the power of pressing is return after reaching setting value, original position, upper working head conversion work position, now send screw assembly 8 to the rivet 2 of loading on the head that presses, upward pressure pin 3 rises simultaneously, lower pressurized strut 7 declines, complete one and bore riveting circulation.And then bracket locating device positions motion, and system carries out next one circulation.
When needing to detect the riveted joint surface quality of aircraft skin 1, the below that bracket locating device moves to 2D displacement transducer 4 is measured, and has measured tail-bracket locating device and again aircraft skin 1 has been moved to the next riveting point that bores.
The actual measured results of aircraft skin local deformation around nail ailhead height as shown in Figure 3 and rivet, what in figure, the left side represented be rivet head superelevation and around rivet aircraft skin local deformation overproof, intermediate representation be rivet head sink and around rivet aircraft skin local deformation overproof, what the right represented is rivet head height qualified and around rivet aircraft skin local without the overproof figure of distortion.
Rivet head of the present invention has relative to the height measurement function of product surface measures the high feature of efficiency, and measuring method originally at least needs to carry out twice measurement just can draw measurement result, and this method only needs one-shot measurement just can obtain a result; The problem directly measured can not be carried out before solving to rivet deformation amount, ensure that riveting quality; Measurement efficiency is high, and anti-interference is good, and measurement function is many, and measurement result accurately and reliably.
Above embodiment is described in detail to essence of the present invention; but can not limit protection scope of the present invention; apparently; under enlightenment of the present invention; the art those of ordinary skill can also carry out many improvement and modification; it should be noted that these improve and modify all to drop within claims of the present invention.
Claims (5)
1. detect a method for aircraft skin riveted joint assembly surface quality, it is characterized in that, it comprises:
A, first 2D displacement transducer (4) is installed to the side of boring upward pressure pin (3) in riveting system;
B, when brill riveting system is riveted to rivet (2) after on aircraft skin (1), bore riveting system aircraft skin (1) is mobile, and rivet (2) is moved to immediately below 2D displacement transducer (4), bore riveting system and send measurement instruction to measuring system, image data instruction is sent to 2D displacement transducer (4) after measuring system receives measurement instruction, sending measuring beam (5) after 2D displacement transducer (4) receives image data instruction is irradiated on rivet (2) and aircraft skin (1), measuring beam (5) turns back to 2D displacement transducer (4) and forms the first image data after diffuse reflection, first image data is fed back to measuring system by 2D displacement transducer (4),
C, by 2D displacement transducer (4) 90-degree rotation, repeat step b obtain the second image data;
D, measuring system receive the first image data and second and gather and first to carry out being separated of valid data and interfering data after number, and then call processing module according to measurement demand and carry out process and obtain measurement data.
2. the method for detection aircraft skin according to claim 1 riveted joint assembly surface quality, is characterized in that described measurement data comprises the deflection of aircraft skin around the height value of rivet head distance aircraft skin, butt-joint clearance width value, butt-joint clearance jump value or rivet.
3. the method for detection aircraft skin riveted joint assembly surface quality according to claim 1, is characterized in that the model of described 2D displacement transducer (4) is Ji Enshi LG-G030.
4. the method for detection aircraft skin riveted joint assembly surface quality according to claim 1, it is characterized in that described brill riveting system comprises boring and riveting machine matrix (6), described boring and riveting machine matrix (6) one end is provided with opening, the other end is closed, and described riveter matrix (6) is overall c-shaped, the top being provided with open at one end described boring and riveting machine matrix (6) is provided with upper working head, described upper working head is provided with successively upward pressure pin (3), auger spindle (11) milling spindle (10) and the head that presses (9); The bottom being provided with open at one end described boring and riveting machine matrix (6) is provided with lower pressurized strut (7), and described upward pressure pin (3) and lower pressurized strut (7) are located along the same line.
5. the method for detection aircraft skin riveted joint assembly surface quality according to claim 4, head (9) one end that presses described in it is characterized in that is provided with send screw assembly (8).
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| CN201510522567.XA CN105136048A (en) | 2015-08-24 | 2015-08-24 | Method for detecting quality of airplane covering-riveting assembling surface |
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| CN201510522567.XA CN105136048A (en) | 2015-08-24 | 2015-08-24 | Method for detecting quality of airplane covering-riveting assembling surface |
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| CN107576275A (en) * | 2017-08-11 | 2018-01-12 | 哈尔滨工业大学 | A kind of method for carrying out straining field measurement to inflatable structure using photogrammetric technology |
| CN109596059A (en) * | 2019-01-07 | 2019-04-09 | 南京航空航天大学 | A kind of aircraft skin gap based on parallel lines structure light and scale measurement method |
| CN111050945A (en) * | 2017-07-28 | 2020-04-21 | 赛峰集团 | Riveting method of airplane |
| CN112161587A (en) * | 2020-09-27 | 2021-01-01 | 西北工业大学 | Robot intelligent drilling and riveting operation online quality detection system and method |
| CN114777651A (en) * | 2022-05-05 | 2022-07-22 | 东北大学 | Airplane surface assembly quality detection method based on digital twinning |
| US11556732B2 (en) | 2020-10-15 | 2023-01-17 | Nanjing University Of Aeronautics And Astronautics | Method for extracting rivet points in large scale three-dimensional point cloud base on deep learning |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111050945A (en) * | 2017-07-28 | 2020-04-21 | 赛峰集团 | Riveting method of airplane |
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| CN109596059A (en) * | 2019-01-07 | 2019-04-09 | 南京航空航天大学 | A kind of aircraft skin gap based on parallel lines structure light and scale measurement method |
| CN109596059B (en) * | 2019-01-07 | 2021-03-05 | 南京航空航天大学 | Aircraft skin gap and step difference measuring method based on parallel line structured light |
| CN112161587A (en) * | 2020-09-27 | 2021-01-01 | 西北工业大学 | Robot intelligent drilling and riveting operation online quality detection system and method |
| US11556732B2 (en) | 2020-10-15 | 2023-01-17 | Nanjing University Of Aeronautics And Astronautics | Method for extracting rivet points in large scale three-dimensional point cloud base on deep learning |
| CN114777651A (en) * | 2022-05-05 | 2022-07-22 | 东北大学 | Airplane surface assembly quality detection method based on digital twinning |
| CN114777651B (en) * | 2022-05-05 | 2024-01-26 | 东北大学 | Digital twinning-based aircraft surface assembly quality detection method |
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