Aircraft manufacturing measurement positioning method

Abstract

The application belongs to the technical field of measurement positioning, and particularly relates to an aircraft manufacturing measurement positioning method, which deeply combines an interference networking measurement of a laser tracker and a spatial coordinate measurement method, uses an interference networking to construct a global coordinate system by using a small number of benchmark control TB points in an open space, carries out a complex system by using the benchmark control TB points in an effective ranging range, expands and enlarges benchmark ERS points, establishes a local enlarged benchmark system to measure and position a local measurement object, and clearly defines the order and limit of the global measurement and the local measurement in the measurement process according to the size chain superposition, and has high measurement precision.

Description

Technical Field

[0001] The present application belongs to the field of measurement and positioning technology, and specifically relates to a measurement and positioning method for aircraft manufacturing. Background Art

[0002] Currently, aircraft manufacturing mostly uses laser trackers for measurement and positioning. The measurement accuracy of laser trackers is usually 15μm+6ppm, and the ranging accuracy is 0.2mm, which can meet the 0.25mm accuracy requirement for aircraft manufacturing measurement and positioning within 30m.

[0003] However, as aircraft manufacturing quality requirements, especially symmetry requirements, become increasingly stringent, and the size of aircraft components becomes larger and larger, even reaching 80m, the accuracy requirements for measurement and positioning remain unchanged. In most cases, they still need to be maintained within 0.25mm. Relying solely on the measurement accuracy of laser trackers is difficult to meet the measurement and positioning accuracy requirements.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the Invention

[0005] The purpose of this application is to provide an aircraft manufacturing measurement and positioning method to overcome or alleviate at least one of the existing technical deficiencies.

[0006] The technical solution of this application is:

[0007] A method for measuring and positioning in aircraft manufacturing, comprising:

[0008] Step 1: Get the maximum outline length of the measured object ,width , and the highest measurement accuracy ;

[0009] Step 2: Construct a survey foundation covering the maximum outer contour range L×A of the survey object;

[0010] Step 3: According to the measurement accuracy of the laser tracker and the maximum measurement accuracy of the measured object , calculate the maximum measurement distance of the laser tracker ;

[0011] Step 4: On the measuring foundation, according to the maximum measuring distance of the laser tracker , determine the local measurement station within the length range;

[0012] Step 5: Arrange benchmark control TB points at each local measurement station;

[0013] Step 6: Arrange four laser trackers on the measurement foundation according to the global measurement station position;

[0014] Step 7: Based on the reference control TB point, use the laser tracker interferometry networking function to build a global coordinate system , calibrate the coordinate value of the benchmark control TB point;

[0015] Step 8: Divide the measurement object into multiple local measurement objects;

[0016] Step 9: For each local measurement object, in the global coordinate system Take multiple datum control TB points nearby to build a global coordinate system ;

[0017] Step 10: Arrange the expanded datum ERS points within the projection range of each local measurement object on the measurement foundation and outside the datum control TB point, and replicate them with the global coordinate system. As a benchmark, calibrate the coordinates of the expanded benchmark ERS points;

[0018] Step 11: Fit the coordinate values ​​of the datum control TB point and the expanded datum ERS point to construct the local expanded datum system of each local measurement object. , based on the local expanded benchmark system Measure and locate the local measurement object.

[0019] Optionally, in the above-mentioned aircraft manufacturing measurement and positioning method, in step 2, the stability of the constructed measurement foundation Not less than the highest measurement accuracy σ, measure the stability of the foundation Calculated as:

[0020] For a square measured foundation: ;

[0021] For rectangular survey foundations: ;

[0022] in,

[0023] To measure the foundation Spanwise non-uniform thermal expansion value;

[0024] To measure the foundation Spanwise non-uniform thermal expansion value;

[0025] To measure the uneven settlement of the foundation.

[0026] Optionally, in the above-mentioned aircraft manufacturing measurement and positioning method, in step 4, the number of local measurement stations determined is ,in, is the rounding function.

[0027] Optionally, in the above-mentioned aircraft manufacturing measurement and positioning method, in step five, at each local measurement station, the number of benchmark control TB points arranged is not less than 6, and the benchmark control TB points are arranged in not less than 5 rows in the length direction and not less than 3 columns in the width direction of the measurement foundation.

[0028] Optionally, in the above-mentioned aircraft manufacturing measurement and positioning method, in step 6, four laser trackers are arranged on the measurement foundation in a rhombus or rectangle, and the distance between the center point of any laser tracker and the plane formed by the center points of the other three laser trackers is greater than , and not less than 300mm, of which, .

[0029] Optionally, in the above-mentioned aircraft manufacturing measurement and positioning method, in step seven, the coordinate value of the reference control TB point is compensated and adjusted according to the thermal expansion coefficient α, and the thermal expansion coefficient α is 、 、 The actual distance between the two farthest reference control TB points in the three directions, and the change ratio of the distance relative to the reference temperature;

[0030] For a square measured foundation:

[0031] ;

[0032] For rectangular survey foundations:

[0033] ;

[0034] in,

[0035] 、 、 They are 、 、 The two farthest reference control TB points are at the actual temperature The measuring distance below;

[0036] 、 、 They are 、 、 The two farthest reference control TB points are at the reference temperature The measured distance below.

[0037] Optionally, in the above-mentioned aircraft manufacturing measurement and positioning method, in step eight, the measurement object is divided into A local measurement object.

[0038] Optionally, in the above-mentioned aircraft manufacturing measurement and positioning method, in step nine, a global coordinate system complex is constructed for each local measurement object. When taking the benchmark control TB points, the number shall be no less than 4 and no less than two rows in the length direction of the measured foundation.

[0039] This application has at least the following beneficial technical effects:

[0040] Provides an aircraft manufacturing measurement and positioning method that deeply combines the interferometric network measurement of the laser tracker and the spatial coordinate measurement method, and uses interferometric networking to construct a global coordinate system with a small number of open space reference control TB points. , use the reference control TB point within the effective ranging range to carry out the complex system, expand the reference ERS point, and establish the local expanded reference system The measurement and positioning of the local measurement object are carried out, and the order and boundaries of the global measurement and local measurement superposition according to the dimension chain in the measurement process are clarified, which has higher measurement accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 is a schematic diagram of an aircraft manufacturing measurement and positioning method provided in an embodiment of the present application;

[0042] Figure 2 yes Figure 1 Schematic diagram at an angle;

[0043] Figure 3 is a top view of some structures involved in the aircraft manufacturing measurement and positioning method provided in an embodiment of the present application;

[0044] in:

[0045] 1-Measurement object; 2-Aircraft product; 3-Process equipment; 4-Measurement foundation; 5-Laser tracker; 6-Benchmark control TB point; 7-Expanded benchmark ERS point; 8-Local measurement object.

[0046] In order to better illustrate this embodiment, some contents of the drawings may be omitted, enlarged or reduced, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0047] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0048] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application shall have the ordinary meanings understood by those skilled in the art to which this application belongs. The term "include" as used in the description of this application means that the concepts preceding the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0049] In addition, the words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar words used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand their specific meanings in this application based on the specific circumstances.

[0050] A method for measuring and positioning in aircraft manufacturing, such as Figure 1 As shown:

[0051] Step 1: Get the maximum outline length of the measurement object 1 ,width , and the highest measurement accuracy .

[0052] The measurement object 1 includes aircraft products 2 and process equipment 3.

[0053] Step 2: Construct a measurement foundation 4 covering the maximum outer contour range L×A of the measurement object 1.

[0054] The process equipment 3 is arranged on a measurement foundation 4 , and the aircraft product 2 is arranged on the process equipment 3 .

[0055] Measuring the stability of foundation 4 Not less than the highest measurement accuracy σ.

[0056] For a square measurement foundation 4: ;

[0057] For rectangular measurement foundation 4: ;

[0058] in,

[0059] To measure the foundation 4 Spanwise non-uniform thermal expansion value;

[0060] To measure the foundation 4 Spanwise non-uniform thermal expansion value;

[0061] To measure the uneven settlement value of foundation 4.

[0062] Step 3: Based on the measurement accuracy of the laser tracker 5 and the maximum measurement accuracy of the measurement object 1 , calculate the maximum measurement distance of laser tracker 5 .

[0063] Step 4: On the measuring foundation 4, according to the maximum measuring distance of the laser tracker 5 , determine the local measurement station positions within the length range.

[0064] Considering the common overlapping area, the number of local measurement stations ,in, is the rounding function.

[0065] Step 5: Arrange benchmark control TB points 6 at each local measurement station.

[0066] At each local measurement station, the number of benchmark control TB points 6 arranged is not less than 6, and the benchmark control TB points 6 are arranged in not less than 5 rows in the length direction of the measurement foundation 4 and not less than 3 columns in the width direction.

[0067] Each reference control TB point 6 is arranged on the process equipment 3 , and there is no interference between the connection lines of each reference control TB point 6 .

[0068] Step 6: Arrange four laser trackers 5 on the measurement foundation 4 according to the global measurement positions.

[0069] Four laser trackers 5 are arranged on the measuring foundation 4 in a rhombus or rectangle shape. When arranged in a rhombus shape, two of the laser trackers 5 can be arranged at the midline position of 1 / 2 of the length of the measuring foundation 4, and the two laser trackers 5 are located at the edges on both sides of the width of the measuring foundation 4. The other two laser trackers 5 are arranged at the midline position of 1 / 2 of the width of the measuring foundation 4, and the distance between the two laser trackers 5 and the two ends of the length of the measuring foundation 4 is 1 / 4 of the length of the measuring foundation 4.

[0070] The distance between the center point of any laser tracker 5 and the plane formed by the center points of the other three laser trackers 5 should be greater than , and not less than 300mm, of which, .

[0071] Step 7: Based on the reference control TB point 6, use the interference networking function of the laser tracker 5 to build a global coordinate system , calibrate the coordinate value of the benchmark control TB point 6.

[0072] During the construction of the global coordinate system, each reference control TB point 6 is set with an optical target according to the direction of the laser tracker 5 station light. Each networked laser tracker 5 automatically illuminates each reference control TB point 6 one by one in the same period according to the measurement order for measurement.

[0073] The coordinate value of the reference control TB point 6 is compensated and adjusted according to the thermal expansion coefficient α. The thermal expansion coefficient α is 、 、 The actual distance between the two farthest reference control TB points 6 in the three directions, and the ratio of the distance change relative to the reference temperature.

[0074] For a square measurement foundation 4:

[0075] ;

[0076] For rectangular measurement foundation 4:

[0077] ;

[0078] in,

[0079] 、 、 They are 、 、 The two reference control TB points 6 in the farthest direction are at the actual temperature The measuring distance below;

[0080] 、 、 They are 、 、 The two reference control TB points 6 in the farthest direction are at the reference temperature The measured distance below.

[0081] Step 8: Divide the measurement object 1 into multiple local measurement objects 8, which can be divided into Local measurement objects8.

[0082] Step 9: For each local measurement object 8, in the global coordinate system Next, take multiple datum control TB points 6 nearby to build a global coordinate system complex .

[0083] Construct a global coordinate system complex for each local measurement object 8 When measuring, the number of benchmark control TB points 6 shall be no less than 4, and no less than two rows shall be taken in the length direction of the measuring foundation 4.

[0084] Step 10: Arrange the expanded ERS points 7 within the projection range of each local measurement object 8 on the measurement foundation 4 and outside the reference control TB points 6, and replicate them with the global coordinate system. As a benchmark, the coordinate value of the expanded benchmark ERS point 7 is calibrated.

[0085] The expanded reference ERS point 7 is arranged on the process equipment 3 or the measurement foundation 4 , and the measurement object 1 , the reference control TB point 6 , and the expanded reference ERS point 7 are all optically visible to the laser tracker 5 .

[0086] Step 11: Fit the coordinate values ​​of the reference control TB point 6 and the expanded reference ERS point 7 to construct the local expanded reference system of each local measurement object 8. , based on the local expanded benchmark system The local measurement object 8 is measured and positioned.

[0087] Locally expanded datum system Reconcile with the global coordinate system In the figure, the arrangement position of the laser tracker 5 is consistent.

[0088] Repeated measurement accuracy of each local measurement object 8 To expand the accuracy of the reference system , local ranging accuracy The sum of the global absolute measurement accuracy To expand the accuracy of the reference system , local ranging accuracy , global coordinate system accuracy The sum of the local ranging accuracy The maximum distance dimensional accuracy of the local measurement object 8 to the laser tracker 5 can be calculated based on the calculate.

[0089] In a specific example, an aircraft wing box is assembled, and the aircraft manufacturing measurement and positioning method disclosed in the above embodiment is specifically implemented as follows.

[0090] Step 1: Get the maximum outline length of the measurement object 1 ,width , and the highest measurement accuracy .

[0091] Step 2: Construct a measurement foundation 4 that covers the maximum outer contour range of the measurement object 1.

[0092] The laser tracker 5 is used to measure the foundation 4 、 Spanwise non-uniform thermal expansion 、 , and measure the uneven settlement value of foundation 4 , calculate and measure the stability of foundation 4 ≤σ meets the use requirements.

[0093] Step 3: The measurement accuracy of the laser tracker 5 is 15μm+6ppm, and the highest measurement accuracy is taken. Four-fifths of the maximum measurement distance of the laser tracker 5 is calculated according to the distance measurement error calculation method of the laser tracker 5. .

[0094] Step 4: Calculate the number of local measurement stations , on the measuring foundation 4, determine the local measuring stations within the length range, and completely envelop and divide the length of the measuring foundation 4.

[0095] Step 5: Arrange benchmark control TB points 6 at each local measurement station. At each local measurement station, the number of benchmark control TB points 6 arranged is not less than 6, and the benchmark control TB points 6 are arranged in not less than 5 rows in the length direction of the measurement foundation 4 and not less than 3 columns in the width direction.

[0096] Step 6: Arrange four laser trackers 5 on the measurement foundation 4 according to the global measurement station. The four laser trackers 5 are arranged on the measurement foundation 4 in a diamond or rectangle shape. Two laser trackers 5 are arranged in the length direction of the measurement foundation 4. =17.5m, at the edge of the width of the measuring foundation 4 on both sides, and the other two laser trackers 5 are arranged in the width direction of the measuring foundation 4 At the end of the measuring foundation 4 .

[0097] Calculate the distance between the center point of any laser tracker 5 and the plane formed by the center points of the other three laser trackers 5 and be greater than , and not less than 300mm.

[0098] Step 7: Based on the reference control TB point 6, use the interference networking function of the laser tracker 5 to build a global coordinate system , calibrate the coordinate value of the reference control TB point 6, and according to the thermal expansion coefficient Compensate and adjust the coordinate value of the reference control TB point 6.

[0099] The measurement foundation 4 is an elongated rectangle, and the two farthest reference control TB points 6 are in the X direction. The actual temperature is measured Down, The measurement distance between the two farthest reference control TB points 6 , at the reference temperature Measuring distance under , then the thermal expansion coefficient is calculated .

[0100] Step 8: Divide the measurement object 1 into four local measurement objects 8.

[0101] Step 9: For each local measurement object 8, in the global coordinate system Next, take the nearest datum control TB points 6 with no less than two rows and no less than four in the length direction of the measurement foundation 4 to construct the global coordinate system complex .

[0102] Step 10: Arrange the expanded ERS points 7 within the projection range of each local measurement object 8 on the measurement foundation 4 and outside the reference control TB points 6, and replicate them with the global coordinate system. As a benchmark, the coordinate value of the expanded benchmark ERS point 7 is calibrated.

[0103] Step 11: Fit the coordinate values ​​of the reference control TB point 6 and the expanded reference ERS point 7 to construct the local expanded reference system of each local measurement object 8. , based on the local expanded benchmark system The local measurement object 8 is measured and positioned.

[0104] According to the manufacturer's expanded reference system and complex system accuracy , the maximum measurement distance of the laser tracker 5 , the ranging accuracy is 15μm+6ppm, calculate the local ranging accuracy , measured global coordinate system accuracy , then the repeatability of the local measurement object 8 is , global absolute measurement accuracy .

[0105] The aircraft manufacturing measurement and positioning method disclosed in the above embodiment deeply combines the interference network measurement of the laser tracker and the spatial coordinate measurement method, and uses the interference network to construct the global coordinate system with a small amount of open space reference control TB point 6 , use the reference control TB point 6 within the effective ranging range to perform the complex system, expand the reference ERS point, and establish the local expanded reference system The local measurement object 8 is measured and positioned, and the order and boundaries of global measurement and local measurement in the measurement process according to the superposition of dimension chains are clarified. It has high measurement accuracy and can meet the measurement and positioning requirements of 0.25mm accuracy for the manufacturing of 80m large aircraft.

[0106] The aircraft manufacturing measurement and positioning method disclosed in the above embodiment can be used for measurement and positioning of processes such as full aircraft leveling, assembly of large aircraft components, fuselage docking assembly, wing box assembly, and mold benchmark leveling exceeding 30m.

[0107] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A method for measuring and positioning in aircraft manufacturing, characterized in that: include: Step 1: Obtain the maximum outline length of the measurement object (1) ,width , and the highest measurement accuracy ; Step 2: construct a measurement foundation (4) covering the maximum outer contour range L×A of the measurement object (1); Step 3: Based on the measurement accuracy of the laser tracker (5) and the maximum measurement accuracy of the measurement object (1), , calculate the maximum measurement distance of the laser tracker (5) ; Step 4: On the measuring foundation (4), according to the maximum measuring distance of the laser tracker (5) , determine the local measurement station within the length range; Step 5: Arrange the benchmark control TB points (6) at each local measurement station; Step 6: Arrange four laser trackers (5) on the measurement foundation (4) according to the global measurement station; Step 7: Based on the reference control TB point (6), use the laser tracker (5) interferometric networking function to construct the global coordinate system , calibrate the coordinate value of the benchmark control TB point (6); Step 8: Divide the measurement object (1) into a plurality of local measurement objects (8); Step 9: For each local measurement object (8), in the global coordinate system Next, take multiple datum control TB points (6) nearby to construct a global coordinate system complex ; Step 10: Arrange the expanded datum ERS point (7) within the projection range of each local measurement object (8) on the measurement foundation (4) and outside the datum control TB point (6) to replicate the global coordinate system. As a benchmark, calibrate the coordinate value of the expanded benchmark ERS point (7); Step 11: Fit the coordinate values ​​of the datum control TB point (6) and the expanded datum ERS point (7) to construct the local expanded datum system of each local measurement object (8). , based on the local expanded benchmark system The local measurement object (8) is measured and positioned.

2. The aircraft manufacturing measurement and positioning method according to claim 1, characterized in that: In step 2, the stability of the constructed measurement foundation (4) Not less than the highest measurement accuracy σ, measure the stability of the foundation (4) Calculated as: For a square measurement foundation (4): ; For a rectangular survey foundation (4): ; in, To measure the foundation (4) Spanwise non-uniform thermal expansion value; To measure the foundation (4) Spanwise non-uniform thermal expansion value; To measure the uneven settlement value of the foundation (4).

3. The aircraft manufacturing measurement and positioning method according to claim 2, characterized in that: In step 4, the number of local measurement stations determined ,in, is the rounding function.

4. The aircraft manufacturing measurement and positioning method according to claim 3, characterized in that: In step 5, at each local measurement station, the number of the benchmark control TB points (6) is not less than 6, and the benchmark control TB points (6) are arranged in not less than 5 rows in the length direction and not less than 3 columns in the width direction of the measurement foundation (4).

5. The aircraft manufacturing measurement and positioning method according to claim 4, characterized in that: In step 6, four laser trackers (5) are arranged on the measurement foundation (4) in a rhombus or rectangle shape, and the distance between the center point of any laser tracker (5) and the plane formed by the center points of the other three laser trackers (5) is greater than , and not less than 300mm, of which, .

6. The aircraft manufacturing measurement and positioning method according to claim 5, characterized in that: In step 7, the coordinate value of the reference control TB point (6) is compensated and adjusted according to the thermal expansion coefficient α. The thermal expansion coefficient α is 、 、 The actual distance between the two farthest reference control TB points (6) in the three directions, and the change ratio of the distance relative to the reference temperature; For a square measurement foundation (4): ； For a rectangular survey foundation (4): ； in, 、 、 They are 、 、 The two farthest reference control TB points (6) in the actual temperature The measuring distance below; 、 、 They are 、 、 The two farthest reference control TB points (6) are at the reference temperature The measured distance below.

7. The aircraft manufacturing measurement and positioning method according to claim 6, characterized in that: In step 8, the measurement object (1) is divided into local measurement objects (8).

8. The aircraft manufacturing measurement and positioning method according to claim 7, characterized in that: In step nine, a global coordinate system is constructed for each local measurement object (8) When measuring, the number of the benchmark control TB points (6) shall be no less than 4 and no less than two rows in the longitudinal direction of the measuring foundation (4).

Images