CN108528755B - Digital installation method of acceleration sensor - Google Patents
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- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000009434 installation Methods 0.000 title claims abstract description 16
- 230000001133 acceleration Effects 0.000 title claims abstract description 15
- 238000005259 measurement Methods 0.000 claims abstract description 22
- 238000013519 translation Methods 0.000 claims abstract description 7
- 238000013461 design Methods 0.000 claims abstract description 6
- 238000004364 calculation method Methods 0.000 claims abstract description 4
- 238000005498 polishing Methods 0.000 claims description 4
- 238000003754 machining Methods 0.000 claims description 3
- 239000004570 mortar (masonry) Substances 0.000 claims description 3
- 239000003973 paint Substances 0.000 claims description 3
- PCTMTFRHKVHKIS-BMFZQQSSSA-N (1s,3r,4e,6e,8e,10e,12e,14e,16e,18s,19r,20r,21s,25r,27r,30r,31r,33s,35r,37s,38r)-3-[(2r,3s,4s,5s,6r)-4-amino-3,5-dihydroxy-6-methyloxan-2-yl]oxy-19,25,27,30,31,33,35,37-octahydroxy-18,20,21-trimethyl-23-oxo-22,39-dioxabicyclo[33.3.1]nonatriaconta-4,6,8,10 Chemical compound C1C=C2C[C@@H](OS(O)(=O)=O)CC[C@]2(C)[C@@H]2[C@@H]1[C@@H]1CC[C@H]([C@H](C)CCCC(C)C)[C@@]1(C)CC2.O[C@H]1[C@@H](N)[C@H](O)[C@@H](C)O[C@H]1O[C@H]1/C=C/C=C/C=C/C=C/C=C/C=C/C=C/[C@H](C)[C@@H](O)[C@@H](C)[C@H](C)OC(=O)C[C@H](O)C[C@H](O)CC[C@@H](O)[C@H](O)C[C@H](O)C[C@](O)(C[C@H](O)[C@H]2C(O)=O)O[C@H]2C1 PCTMTFRHKVHKIS-BMFZQQSSSA-N 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000003032 molecular docking Methods 0.000 abstract description 3
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- 238000011084 recovery Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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Abstract
A digital installation method of an acceleration sensor belongs to the field of aviation manufacturing engineering/airplane assembly, and comprises the following steps: firstly, after the airplane is docked by digital docking, the coordinate axes of the airplane coordinate system and the laser tracker space coordinate system are aligned and fitted through a ground ERS or TB common datum point. Secondly, the switching tool and the sensor support are connected with the machine body structure, the laser tracker is adopted to measure the measuring plate, the measuring result is led into a theoretical three-dimensional digital analog, and the space comparison between a theoretical plane and an actual measuring plane is established. And finally, obtaining the deflection angle of the measured plane relative to the theoretical plane through digital-analog measurement and calculation, obtaining the optimal compensation scheme of the body structure through integral translation along the X axis, and connecting retest according to the steps again after the body structure is compensated until the design requirements are met. The invention can improve the assembly technical level, shorten the assembly production period and improve the assembly efficiency, and has important significance on the assembly efficiency and quality of the machine body component.
Description
Technical Field
The invention belongs to the field of aviation manufacturing engineering/airplane assembly, and relates to an installation method of an airplane acceleration sensor based on digital measurement, which is used for accurately installing parts in a digital automatic docking process of large parts.
Background
The modern high-performance fighter generally adopts a fly-by-wire flight control system as an acceleration sensor which is one of main sensors of the system, and normal and lateral acceleration feedback is provided for the flight control system for function resolving such as control stability augmentation, boundary limitation and the like. The deviation of the installation position and the precision of the acceleration sensor can cause the deviation of feedback parameters in the flying process, thereby influencing the flying quality.
To avoid error accumulation, the acceleration sensor is typically installed at the end of the large component docking process. The acceleration sensor has strict installation requirements (parallelism is not more than +/-X' relative to a reference plane). The traditional installation method comprises a fixed tool installation method and a theodolite measurement installation method. The former has low efficiency and high cost; the latter is cumbersome to analyze and operate.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides an aircraft acceleration sensor installation method based on digital measurement.
In order to achieve the purpose, the technical scheme of the invention is as follows:
a digital installation method of an acceleration sensor is realized based on a switching tool 3, and the switching tool 3 is provided with a support 9, a self-made bolt 5, a threaded plate 6, a measuring plate 7 and a measuring ball 8. The switching tool 3 is in an inverted L shape and comprises a cross beam and a longitudinal beam, and a support 9 is arranged between the cross beam and the longitudinal beam; one end of the beam is provided with a threaded plate 6, the threaded plate 6 is connected with the sensor support 2, and the sensor support 2 is provided with a compensation block; the other end of the cross beam is fixedly connected with the top end of the longitudinal beam. The bottom of the longitudinal beam is connected with a measuring plate 7. The measuring plate 7 is of a square structure, and any three end corners of the measuring plate 7 are provided with measuring balls 8 through machining. And the transverse beam and the longitudinal beam are respectively provided with a measuring ball 8 for calibrating the relative positions of the transverse beam and the longitudinal beam. In order to facilitate the selection and measurement of the datum point, the measuring plate 7 and the sensor positioning surface form a spatial 90-degree included angle, the relative position precision of the measuring plate 7 and the sensor positioning surface is guaranteed through the calibration of the measuring ball 8 and the compensation of the mortar, and the position tolerance of the measuring ball 8 is +/-0.08 mm.
The digital installation method comprises the following steps:
(1) after the airplane is butted by digital involution, 4 laser trackers are arranged in the range of 10M of the switching tool, and a space coordinate system is constructed by the laser trackers. And aligning and fitting coordinate axes of the airplane coordinate system and the space coordinate system of the laser tracker 4 through more than 4 ERS or TB common reference points on the ground. The X, Y, Z axis fitting tolerance of the constructed space coordinate system is required to be not more than +/-0.08 mm, otherwise, the datum point needs to be selected again.
(2) Through four self-control bolts 5 and thread plate 6 with switching frock 3, sensor support 2 with organism structure 1 be connected, adopt micrometer inspection three laminating clearance, require the laminating clearance to be less than 0.1 mm. A measuring ball 8 with an R of 6.35mm is selected and the measuring ball 8 on the measuring plate 7 guided out of the machine body structure 1 is measured with the laser tracker 4. And (3) importing the measurement result into a theoretical three-dimensional digital analog, and establishing a space comparison between a theoretical plane and an actually measured plane, as shown in figure 3.
(3) Let face ABCD be the theoretical plane of measuring plate 7, face a ' ″ B ' ″ D ' be its measured plane, obtain through digifax measurement and calculation that the measured plane is respectively for theoretical plane around X, Y, Z deflection angle alpha, beta, gamma. Three angles of alpha, beta and gamma are calculated:
firstly, a certain point of a measuring plane is selected, and the certain point is coincided with a certain point of a theoretical point through integral translation, such as points A and A'. And (4) making a normal line of the theoretical surface at the C ' point, wherein the normal line and the theoretical surface intersect at the C ' point and are connected with the AC ' point. The angle between AC and AC "is measured, and the angle α is the angle of deflection of the measured plane about the Y axis relative to the theoretical plane. And rotating the measured plane around the Y axis in the opposite direction by an alpha through a rotation instruction, and measuring the included angle between the CD and the C 'D', wherein the angle beta is the deflection angle between the measured plane and the theoretical plane around the X axis. The angle between AC and a 'C' is measured and is the angle of deflection of the measured plane about the Z axis relative to the theoretical plane.
And then, rotating the positioning theoretical surface of the sensor support 2 around X, Y, Z coordinate axes by alpha, beta and gamma to obtain the actual space position of the positioning surface of the sensor support, and obtaining the interference amount and the clearance value of the base compensation block of the sensor support 2 through comparison measurement.
Finally, the optimal compensation scheme of the machine body structure 1 is obtained through integral translation along the X axis, and is ensured by adding a cushion for the first time and is polished by a small amount in principle. And (4) connecting and retesting the machine body structure 1 according to the steps after compensation until the design requirements are met, and then performing paint recovery layer and final connection to obtain a qualified product.
The invention has the beneficial effects that: by applying the invention, the assembly technical level can be improved, the assembly production period can be shortened, and the problems of the mounting precision and efficiency of precision parts such as an acceleration sensor and the like can be solved. Under the monitoring of a digital measuring system, the assembly precision of the mounting bracket of the acceleration sensor is improved by 20%, and the mounting efficiency is improved by 50% compared with that of the traditional mounting method. The real-time online measurement of the key positioning characteristics of the assembly of the machine body components is realized through digital measurement, and the method has important significance on the assembly efficiency and quality of the machine body components.
Drawings
FIG. 1 is a schematic view of a measurement; the coordinate system of the X, Y, Z axis is a space coordinate system of the laser tracker 4, P is a measurement point in space, d is a distance between an origin of the laser tracker and the point P, the angle a is an angle formed by a directed line segment and the positive direction of the z axis, and the angle b is an angle from the positive z axis to the directed line segment in the clockwise direction from the y axis.
FIG. 2 is a schematic view of a structure of the transfer tool;
FIG. 3 is a diagram of a spatial comparison between a theoretical plane and an actual measurement plane;
in the figure: 01 a machine body structure; 02 a sensor holder; 03 transferring a tool; 04 laser tracker; 05 self-made bolts; 06 thread plate; 07 measuring the plate; 08 a measuring ball; 09 and (b) a bracket.
Detailed Description
The present invention is further illustrated by the following specific examples.
In order to guide the information of the key matching surface to the outer surface of the machine body and facilitate measurement, the invention provides a digital installation method of an acceleration sensor, which is realized based on a designed switching tool 3. The switching tool 3 is composed of five parts, namely a bracket 9, a self-made bolt 5, a thread plate 6, a measuring plate 7 and a measuring ball 8, as shown in fig. 1 and 2. The switching tool 3 is in an inverted L shape and comprises a cross beam and a longitudinal beam, and a support 9 is arranged between the cross beam and the longitudinal beam; one end of the beam is provided with a threaded plate 6, the threaded plate 6 is connected with the sensor support 2, and the sensor support 2 is provided with a compensation block; the other end of the cross beam is fixedly connected with the top end of the longitudinal beam. The bottom of the longitudinal beam is connected with a measuring plate 7. The measuring plate 7 is of a square structure, and any three end corners of the measuring plate 7 are provided with measuring balls 8 through machining. And the transverse beam and the longitudinal beam are respectively provided with a measuring ball 8 for calibrating the relative positions of the transverse beam and the longitudinal beam. In order to facilitate the selection and measurement of the datum point, the measuring plate 7 and the sensor positioning surface form a spatial 90-degree included angle, the relative position precision of the measuring plate 7 and the sensor positioning surface is guaranteed through the calibration of the measuring ball 8 and the compensation of the mortar, and the position tolerance of the measuring ball 8 is +/-0.08 mm.
And in the measurement process, most parts are selected to align to station ERS or TB points, and a space coordinate system is constructed by using the laser tracker 4. Switching frock 3 one end is connected with sensor holder 2, organism structure 1 through self-control bolt 5 and thread plate 6, and laser tracker 4 is measured the measuring plate 7 of being guided out the organism outside. And importing the measured data into a three-dimensional digital-analog, and comparing the measured data with a theoretical value. Obtaining a product meeting design requirements according to a measurement and calculation method: the actual space position of the positioning surface of the sensor support is obtained by deflecting the positioning surface of the sensor support by angles alpha, beta and gamma around an axis X, Y, Z, and the polishing or padding values of the four base compensation blocks of the sensor support A, B, C, D are obtained through comparison measurement. And (4) carrying out retest after polishing and cushioning until the design requirements are met.
The measuring and calculating method comprises the following steps:
(1) after the airplane is butted by digital involution, the laser tracker 4 is arranged in the range of the switching tool 10M. And carrying out alignment fitting on the airplane coordinate system and the laser tracker coordinate system through more than 4 ERS or TB common datum points on the ground. The fitting tolerance of the established system X, Y, Z axis is required to be not more than +/-0.08 mm, otherwise, the datum point needs to be selected again.
(2) Switching frock 3, sensor support 2 are connected with organism structure 1 through four self-control bolts 5 and thread plate 6. And (5) checking the fit clearance of the three by using a micrometer, wherein the fit clearance is required to be less than 0.1 mm. A measuring ball 8 with an R of 6.35mm is selected and the measuring ball 8 on the measuring plate 7 is measured with the laser tracker 4. And importing the measurement result into a theoretical three-dimensional digital-analog. A spatial comparison of the theoretical plane and the measured plane is established as in fig. 3. The actual measurement plane is obtained by rotating the theoretical plane around X, Y, Z coordinate axes by alpha, beta and gamma.
(3) Calculating three angles of alpha, beta and gamma, firstly selecting a certain point of a measuring plane, and coinciding the certain point with a theoretical point, such as points A and A' through integral translation. The point of passing C' is taken as the normal of the theoretical plane. The normal line intersects the theoretical plane at the C "" point, connecting the AC "" points. The angle between AC and AC "is measured. The angle α is the angle of deflection of the measured plane relative to the theoretical plane about the Y-axis. And rotating the measured plane in the opposite direction around the Y axis by alpha through a rotation command. The angle between CD and C 'D' is measured. The angle beta is the angle of deflection of the measured plane relative to the theoretical plane about the X-axis. The angle between AC and a 'C' is measured. The angle γ is the angle of deflection of the measured plane relative to the theoretical plane about the Z-axis. And then, rotating the positioning theoretical surface of the sensor support around X, Y, Z coordinate axes by alpha, beta and gamma to obtain the actual space position of the positioning surface of the sensor support. Finally, the interference amount and the clearance value of the compensation blocks at four positions of the support A, B, C, D are measured. And obtaining an on-board optimal compensation scheme by integral translation along the X axis. The principle is that the polishing is firstly guaranteed by adding a cushion as much as possible and is slightly polished. And after on-board compensation, re-testing according to the previous preparation condition until the design requirement is met. And (5) after the product is qualified, performing restoring paint layer and final connection.
The above-mentioned embodiments only express the embodiments of the present invention, but not should be understood as the limitation of the scope of the invention patent, it should be noted that, for those skilled in the art, many variations and modifications can be made without departing from the concept of the present invention, and these all fall into the protection scope of the present invention.
Claims (1)
1. The digital installation method of the acceleration sensor is characterized in that the digital installation method is realized based on a switching tool (3), and a support (9), a self-made bolt (5), a threaded plate (6), a measuring plate (7) and a measuring ball (8) are arranged on the switching tool (3); the switching tool (3) is in an inverted L shape and comprises a cross beam and a longitudinal beam, and a support (9) is arranged between the cross beam and the longitudinal beam; one end of the beam is provided with a threaded plate (6), the threaded plate (6) is connected with the sensor bracket (2), and the sensor bracket (2) is provided with a compensation block; the other end of the cross beam is fixedly connected with the top end of the longitudinal beam; the bottom of the longitudinal beam is connected with a measuring plate (7); the measuring plate (7) is of a square structure and is manufactured by machining, and measuring balls (8) are arranged at any three corners of the measuring plate (7); the transverse beam and the longitudinal beam are respectively provided with a measuring ball (8) for calibrating the relative position of the transverse beam and the longitudinal beam; the measuring plate (7) and the positioning surface of the sensor support form a spatial 90-degree included angle, the relative position precision of the measuring plate (7) and the positioning surface of the sensor support is ensured by calibration of the measuring ball (8) and mortar compensation, and the position tolerance of the measuring ball (8) is +/-0.08 mm; the digital installation method comprises the following steps:
1) after the airplane is butted by digital involution, the laser tracker (4) is arranged in the range of 10M of the switching tool, and a space coordinate system is constructed by the laser tracker; aligning and fitting coordinate axes of an airplane coordinate system and a space coordinate system of the laser tracker (4) through more than 4 ERS or TB common datum points on the ground; requiring that the fitting tolerance of X, Y, Z axes of the constructed space coordinate system is not more than +/-0.08 mm, otherwise, reselecting the reference point;
2) the switching tool (3) and the sensor bracket (2) are connected with the machine body structure (1) through a self-made bolt (5) and a threaded plate (6), and a micrometer is adopted to check the fit clearance of the switching tool and the sensor bracket, wherein the fit clearance is required to be less than 0.1 mm; selecting a measuring ball (8) with the R being 6.35mm, and measuring the measuring ball (8) on a measuring plate (7) guided out of the machine body structure (1) by using a laser tracker (4); importing the measurement result into a theoretical three-dimensional digital analog, and establishing a space comparison between a theoretical plane and an actually measured plane;
3) setting the face ABCD as a theoretical plane of the measuring plate (7), setting the faces A ', B', C 'and D' as measured planes of the measuring plate, and obtaining deflection angles alpha, beta and gamma of the measured planes relative to the theoretical plane respectively around an X, Y, Z axis through digital-analog measurement and calculation; three angles of alpha, beta and gamma are calculated:
firstly, selecting a certain point of an actually measured plane, coinciding the certain point with a certain point of a theoretical plane through integral translation, such as points A and A ', making a normal line of the theoretical plane through a point C', intersecting the normal line with the theoretical plane at the point C ', and connecting an AC'; measuring the included angle between AC and AC', wherein the included angle alpha is the deflection angle of the measured plane relative to the theoretical plane around the Y axis; rotating the measured plane in the opposite direction around the Y axis by an alpha through a rotation instruction, and measuring an included angle between the CD and the C 'D', wherein the included angle beta is a deflection angle between the measured plane and a theoretical plane around the X axis; measuring an included angle between AC and A 'C', wherein the included angle gamma is a deflection angle of an actually measured plane relative to a theoretical plane around a Z axis;
then, rotating the theoretical positioning surface of the sensor bracket (2) around an X, Y, Z axis by alpha, beta and gamma to obtain the actual space position of the positioning surface of the sensor bracket, and obtaining the interference amount and the clearance value of the base compensation block of the sensor bracket (2) through comparison and measurement;
finally, obtaining an optimal compensation scheme of the machine body structure (1) by integral translation along the X axis, and ensuring the optimal compensation scheme by adding a cushion for the first time and polishing a small amount in principle; and (4) connecting and retesting the machine body structure (1) according to the steps after compensation until the design requirements are met, and then recovering the paint layer and finally connecting to obtain a qualified product.
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| CN111422374B (en) * | 2020-04-01 | 2022-04-29 | 中国航空制造技术研究院 | Coordination and compensation method suitable for welded part and machine body structure |
| CN111891382B (en) * | 2020-06-30 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Spherical hinge center calibration method for adjusting attitude of large part of airplane |
| CN112623262B (en) * | 2020-12-30 | 2023-02-28 | 中航贵州飞机有限责任公司 | Assembling tool installation and maintenance method |
| CN114986929B (en) * | 2022-06-01 | 2024-06-18 | 沈阳飞机工业（集团）有限公司 | Method for improving secondary cementing quality and efficiency of composite material air inlet channel |
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| CN101746510B (en) * | 2010-02-03 | 2012-12-19 | 北京航空航天大学 | Assembly method of leading edge flap based on laser measuring technique |
| CN103292748B (en) * | 2013-01-05 | 2015-12-02 | 中国航空工业集团公司西安飞机设计研究所 | A kind of split of many substrates based on laser measurement detection method |
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