CN113335553A - Airplane assembling and positioning method based on three-dimensional laser projection - Google Patents
Airplane assembling and positioning method based on three-dimensional laser projection Download PDFInfo
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- CN113335553A CN113335553A CN202010137621.XA CN202010137621A CN113335553A CN 113335553 A CN113335553 A CN 113335553A CN 202010137621 A CN202010137621 A CN 202010137621A CN 113335553 A CN113335553 A CN 113335553A
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- 238000000034 method Methods 0.000 title claims abstract description 23
- 238000013461 design Methods 0.000 claims abstract description 23
- 238000004088 simulation Methods 0.000 claims abstract description 3
- 238000009434 installation Methods 0.000 claims description 12
- 230000003287 optical effect Effects 0.000 claims description 4
- 238000007689 inspection Methods 0.000 abstract description 7
- 238000005553 drilling Methods 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 description 7
- 238000012360 testing method Methods 0.000 description 5
- 239000000047 product Substances 0.000 description 4
- 238000012827 research and development Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000006227 byproduct Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000002699 waste material Substances 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
The method is characterized in that design digital models of a first assembly part and a second assembly part are input into a control computer of projection equipment to establish a simulation assembly relation. In a coordinate system of the first assembly part, the three-dimensional profile or the center of the fastener hole of the second assembly part is projected on the assembly position of the first assembly part in the form of a laser line, a tooling positioner and a drilling template are replaced, a line drawing positioning mode is replaced, and part positioning, fastener hole position determination and assembly inspection are completed.
Description
Technical Field
The invention relates to an airplane manufacturing technology, belongs to the technical field of airplane digital assembly, and discloses an airplane assembly positioning method based on three-dimensional laser projection.
Background
The traditional airplane assembly positioning comprises methods such as line drawing positioning, assembly tool positioning, datum part positioning and the like, and the methods are singly or comprehensively used for positioning holes of parts and fasteners in the existing airplane manufacturing process. In the prior art, the problems of low efficiency and poor precision exist in line drawing positioning; the assembly tool can effectively solve the problem of positioning accuracy, but is influenced by factors such as operating space, economic cost and the like, various types of parts are generally not provided with positioning tools, such as mounting brackets of various systems of an airplane, connecting sheets at the butt joint of components and the like, the parts are generally positioned by depending on reference products and drawn lines, and the accuracy and the efficiency are low; for parts which are complex in connection relation and inconvenient to directly take guide holes, the traditional method adopts line drawing and hole making or template hole making, so that the hole making efficiency is low, the precision is poor, and if the product design is changed, the drilling template needs to be correspondingly changed, so that the repeated investment cost is high; in the aircraft assembly, the quality problems of the tool and the part are often difficult to find in time, and the inspection is carried out after the assembly problems occur, so that the greater quality loss is caused.
Disclosure of Invention
The invention aims to provide an aircraft assembly positioning method based on three-dimensional laser projection, aiming at solving the problems that line drawing positioning efficiency is low, precision is poor, tool positioning cost is high, tool repeated investment is generated by design change, and the quality of parts in a key assembly area cannot be found in time and the like in the prior art.
An aircraft assembly positioning method based on three-dimensional laser projection comprises a first assembly part and a second assembly part, wherein design digifax of the first assembly part and the second assembly part is known, and assembly positioning relation with the second assembly part is established on a first assembly part entity, and the method is characterized by comprising the following steps: 1) a projection device, wherein the projection device is associated with a control computer; 2) inputting the design digital model of the first assembly part and the design digital model of the second assembly part into a control computer to form a simulation assembly relation of the first assembly part and the second assembly part; 3) placing the projection equipment at a proper position near the first assembly part entity so that the projection equipment can acquire the characteristic points of the first assembly part entity; 4) acquiring feature points of a first assembly part entity by using projection equipment, and associating the feature points of the first assembly part entity with a design digital model of a first assembly part in a control computer to form a corresponding relation between the design digital models of the first assembly part and a second assembly part and the first assembly part entity; 5) according to the corresponding relation, projecting the three-dimensional outline of the second assembly part on the assembly position of the first assembly part entity through projection equipment, and establishing an assembly positioning relation of the first assembly part entity and the second assembly part entity in the three-dimensional outline projection; 6) and corresponding the three-dimensional contour projection of the second assembly part entity to the three-dimensional contour projection of the second assembly part according to the assembly positioning relation of the three-dimensional contour projection of the first assembly part entity and the second assembly part entity, so as to realize the assembly positioning relation of the second assembly part entity and the first assembly part entity.
When the first assembly part is an airplane component and an assembly tool, the characteristic point selects an optical target point or an enhanced reference point on the tool.
When the first assembly part is an airplane component, the characteristic points are selected from datum planes or datum holes on the airplane component.
When the second assembly part is a part, the part digital-analog input control computer, the projection equipment projects the three-dimensional contour line of the part to the installation position in the form of a laser line, and the operator can realize the accurate positioning of the part by superposing each edge of the part real object with the projected laser contour line.
When the second assembly part is a fastener, a connecting hole of the fastener needs to be manufactured on the first assembly part, the design model of the second assembly part comprises a connecting position of the fastener on the first assembly part, the projection equipment projects the connecting position of the fastener on the first assembly part entity, and an operator performs hole manufacturing operation according to the projection of the connecting position.
When the assembly relationship between the second assembly entity and the first assembly entity needs to be checked, the design digital model of the second assembly to be checked is input into the control computer, assembly tolerance is set in the simulated assembly relationship between the first assembly and the second assembly, the mounting limit position relationship of the second assembly relative to the first assembly is formed, then the mounting limit position relationship of the second assembly relative to the first assembly is projected on the first assembly entity, and whether the assembly relationship between the second assembly entity and the first assembly entity is out of tolerance is checked.
The beneficial effect of this application lies in: 1) the fixture can replace the traditional fixture positioner within a certain range, simplify the fixture structure, avoid the fixture change caused by product change, and reduce the aircraft manufacturing cost. 2) The assembly efficiency is improved. Utilize laser to carry out the projection location, can avoid traditional setting-out location, the operator looks over the digifax, gets and take notes the size to reciprocate, carries out the lengthy operation process of setting-out on the aircraft again, effectively improves assembly efficiency. According to research and test of the applicant, the positioning efficiency of the system bracket parts can be improved by 60 percent, and the hole making efficiency of the joint and the angle piece is improved by 64 percent. 3) And the positioning precision is improved. The positioning method is adopted, and according to the research and test of the applicant, the positioning precision is improved from +/-2 mm to +/-0.4 mm. 4) Reducing mass loss. The laser projection positioning method is used for replacing line drawing positioning, so that the product quality problem caused by line drawing errors of an operator can be avoided. The assembly inspection of the key area can be carried out, so that quality problems can be avoided in advance, for example, hole site projection is carried out on the lap joint area before hole making, if the edge distance of the hole is out of tolerance, the arrangement of the fasteners can be adjusted in time, and product scrapping caused after hole making is avoided; for example, if the positioning of the second assembly is out of tolerance due to manufacturing quality problems, the hole forming operation with the first assembly is stopped, and further quality problems are avoided on the first assembly.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
Fig. 1 is a schematic view of the laser projection assembly positioning when the second assembly member is a part.
FIG. 2 is a schematic view of the laser projection assembly positioning when the second assembly member is a fastener.
The numbering in the figures illustrates: 1 control computer, 2 projection device, 3 target ball, 4 first assembly, 5 second assembly.
Detailed Description
Referring to the drawings, the airplane assembly positioning method based on three-dimensional laser projection is to input design figures of a first assembly part 4 and a second assembly part 5 into a control computer 1 of a projection device 2 to establish a simulated assembly relationship. In a coordinate system of the first assembly part 4, the three-dimensional profile or the center of a fastener hole of the second assembly part 5 is projected on an assembly position of the first assembly part 4 in the form of a laser line, a tool positioner and a drilling template are replaced, a line drawing positioning mode is replaced, and part positioning, fastener hole position determination and assembly inspection are completed.
The projection equipment 2 is connected to an airplane coordinate system after characteristic points on the entity of the first assembly part 4 are collected and associated with a design digital model of the first assembly part 4, then the second assembly part 5 is projected to a theoretical installation position on the entity of the first assembly part 4 in a laser line mode, and an operator is guided to install the entity of the second assembly part 5 in a manner of contrasting the laser line, or the laser line is used for checking the assembly relation of the installed entity of the second assembly part 5.
Placing the projection device 2 in a suitable position physically adjacent the first assembly 4 ensures that the laser line of sight is not obscured. The target balls attached to the projection device 2 are physically mounted on the first assembly 4 according to the maximum envelope principle, and at least six target balls are required. When the first assembly part 4 comprises an airplane component and an assembly tool, the target ball can be installed on an optical characteristic point and an enhanced reference point of the assembly tool; when the first assembly part only comprises the airplane component, the target ball can be arranged on a reference surface or a reference hole of the airplane component, such as a non-deformable machining frame end surface, a precisely manufactured installation hole on a machining joint and the like. The theoretical coordinates of the installation point of each target ball are input into the software of the control computer 1, the projection equipment 2 is controlled to sequentially scan and collect the installation positions of the target point entities, the theoretical coordinates and the entity positions are calibrated one to one in the computer, the establishment of a projection positioning system coordinate system is completed, namely the projection equipment 2 is connected into an airplane coordinate system, and the corresponding relation between the design digifax of the first assembly part 4 and the second assembly part 5 and the entity of the first assembly part 4 is formed.
According to the corresponding relation, the three-dimensional contour of the second assembly part 5 is projected on the assembly position of the entity of the first assembly part 4 through the projection equipment 2, and the establishment of the assembly positioning relation between the entity of the first assembly part 4 and the second assembly part 5 is completed. And positioning and assembling the entity of the second assembly part 5 and the entity of the first assembly part 4 according to the three-dimensional contour projection of the second assembly part 5.
When the second assembly part 5 is a part, the part digital-analog input control computer, the projection equipment 2 projects the three-dimensional contour line of the part to the installation position in the form of a laser line, and the operator can realize accurate positioning in space with six degrees of freedom by superposing each edge of the part real object with the projected laser contour line. When the second assembly part 5 is a fastener, a digital-analog module containing the connecting position of the fastener is input into a control computer, the projection equipment 2 projects the hole position of the fastener on a part in a pattern in the form of a cross line and the like, and an operator performs hole making operation according to the projection.
In the aspect of assembly inspection, a digital-analog input of a second assembly part 5 to be inspected is input into the control computer 1, assembly tolerance is set, a theoretical installation limit position is projected on the first assembly part 4, and the position relation between the solid edge of the second assembly part 5 and a projection line is inspected to judge whether assembly is out of tolerance.
In the embodiment, a MA700 aircraft panel research and development test piece is taken as an example, assembly positioning is implemented according to the invention scheme of the application, the first assembly part 4 is an assembly tool of the MA700 aircraft panel research and development test piece, the second assembly part 5 is a system installation support, a shear slice, a stringer and other parts, and the specific steps are as follows:
1. device connection
Depending on the position of the first assembly 4, the projection device 2 is placed at a distance of 4m (which may vary depending on the device performance) from the first assembly 4, to check that the laser path is not blocked. The projection device 2 is connected to the power supply and is connected to the control computer 1 via a data line.
2. Input digital-to-analog
The design code for the first assembly 4 and the design code for the second assembly 5 are input into the control computer 1 of the projection device.
3. Accessing an aircraft coordinate system
The six target balls 3 attached to the projection equipment are installed on an assembly tool entity of a first assembly MA700 aircraft panel research and development test piece according to the maximum envelope principle, and are specifically installed on an optical characteristic point and an enhancement reference point of the assembly tool.
Inputting the theoretical coordinates of the six target ball mounting points into software of a control computer, controlling projection equipment to sequentially scan and collect the entity mounting positions of the target points, and calibrating the theoretical coordinates and the entity positions one by using the software to complete the establishment of a projection positioning system coordinate system, namely the projection equipment is accessed to an airplane coordinate system.
4. Projection positioning
When the second assembly part 5 is a system installation support, a shear blade, a stringer and other parts, the projection output of the three-dimensional outline of the second assembly part 5 on the entity of the first assembly part 4 can be realized by selecting the outline of the digital-analog of the second assembly part 5 on a control computer by a mouse; and guiding an operator to adjust and align the second assembly entity according to the projection contour line and then clamp the second assembly entity according to the projection contour line so as to finish positioning or carry out assembly inspection.
When the second assembly part 5 is a fastener, selecting the mounting point positions in the digifax of the second assembly part by using a mouse on a control computer, and sequentially clicking to realize the projection of the hole positions of the fastener on the entity of the first assembly part 4, wherein the projected hole positions can be displayed in a line shape such as a cross cursor, a hollow circle and the like through the setting of computer software; and guiding an operator to finish hole making or assembly inspection according to the hole position projection.
The second assembly part 5 of the present application is suitable for parts mainly including system brackets, connecting angle pieces, joint parts and fasteners which are small in structure and good in rigidity. The hole of the fastener is limited to the hole making by directly guiding an operator when the thickness of the interlayer is not large (less than or equal to 6mm is recommended).
As a flexible positioning mode, when the airplane parts and the connection arrangement positions are changed, only the latest digital-analog input control computer needs to be re-projected. The method avoids the problem that in the traditional positioning method, the part positioner is physically changed, or a new sample plate is manufactured by reporting the waste hole-making sample plate according to a new connecting and arranging position. The period of the production line for implementing design change can be greatly shortened, and the manufacturing cost of the airplane is effectively reduced.
Claims (6)
1. An aircraft assembly positioning method based on three-dimensional laser projection comprises a first assembly part and a second assembly part, wherein design digifax of the first assembly part and the second assembly part is known, and assembly positioning relation with the second assembly part is established on a first assembly part entity, and the method is characterized by comprising the following steps: 1) a projection device, wherein the projection device is associated with a control computer; 2) inputting the design digital model of the first assembly part and the design digital model of the second assembly part into a control computer to form a simulation assembly relation of the first assembly part and the second assembly part; 3) placing the projection equipment at a proper position near the first assembly part entity so that the projection equipment can acquire the characteristic points of the first assembly part entity; 4) acquiring feature points of a first assembly part entity by using projection equipment, and associating the feature points of the first assembly part entity with a design digital model of a first assembly part in a control computer to form a corresponding relation between the design digital models of the first assembly part and a second assembly part and the first assembly part entity; 5) according to the corresponding relation, projecting the three-dimensional outline of the second assembly part on the assembly position of the first assembly part entity through projection equipment, and establishing an assembly positioning relation of the first assembly part entity and the second assembly part entity in the three-dimensional outline projection; 6) and corresponding the three-dimensional contour projection of the second assembly part entity to the three-dimensional contour projection of the second assembly part according to the assembly positioning relation of the three-dimensional contour projection of the first assembly part entity and the second assembly part entity, so as to realize the assembly positioning relation of the second assembly part entity and the first assembly part entity.
2. The aircraft assembly positioning method based on three-dimensional laser projection of claim 1, wherein when the first assembly part is an aircraft component and an assembly tool, the characteristic point is an optical target point or an enhanced reference point on the tool.
3. The method as claimed in claim 1, wherein when the first assembly is an aircraft component, the feature points are selected from datum planes or datum holes on the aircraft component.
4. The three-dimensional laser projection-based airplane assembly positioning method as claimed in claim 1, wherein when the second assembly part is a part, the part digital-analog is input into the control computer, the projection device projects the three-dimensional contour line of the part to the installation position in the form of laser line, and the operator can accurately position the part by overlapping each edge of the part real object with the projected laser contour line.
5. The three-dimensional laser projection-based aircraft assembly positioning method as claimed in claim 1, wherein when the second assembly member is a fastener, a connecting hole of the fastener needs to be formed in the first assembly member, the design digifax of the second assembly member comprises a connecting position of the fastener on the first assembly member, the projection device projects the connecting position of the fastener on the first assembly member entity, and an operator performs hole forming operation according to the connecting position projection.
6. The three-dimensional laser projection-based aircraft assembly positioning method as claimed in claim 1, wherein when the assembly relationship between the second assembly entity and the first assembly entity needs to be checked, the second assembly design digital model to be checked is input into the control computer, an assembly tolerance is set in the simulated assembly relationship between the first assembly entity and the second assembly entity, an installation limit position relationship of the second assembly entity relative to the first assembly entity is formed, then the installation limit position relationship of the second assembly entity relative to the first assembly entity is projected on the first assembly entity, and whether the assembly relationship between the second assembly entity and the first assembly entity is out of tolerance is checked.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010137621.XA CN113335553A (en) | 2020-03-02 | 2020-03-02 | Airplane assembling and positioning method based on three-dimensional laser projection |
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| CN202010137621.XA CN113335553A (en) | 2020-03-02 | 2020-03-02 | Airplane assembling and positioning method based on three-dimensional laser projection |
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Cited By (2)
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| CN117647964A (en) * | 2024-01-29 | 2024-03-05 | 中航西飞民用飞机有限责任公司 | Collaborative following mobile transfer platform control system and method for aircraft assembly |
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| CN117647964A (en) * | 2024-01-29 | 2024-03-05 | 中航西飞民用飞机有限责任公司 | Collaborative following mobile transfer platform control system and method for aircraft assembly |
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