CN112711795A - Reverse modeling method of control surface type honeycomb structural part suitable for remanufacturing and repairing - Google Patents
Reverse modeling method of control surface type honeycomb structural part suitable for remanufacturing and repairing Download PDFInfo
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- CN112711795A CN112711795A CN202011553579.6A CN202011553579A CN112711795A CN 112711795 A CN112711795 A CN 112711795A CN 202011553579 A CN202011553579 A CN 202011553579A CN 112711795 A CN112711795 A CN 112711795A
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- G06—COMPUTING; CALCULATING OR COUNTING
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- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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Abstract
The invention relates to a reverse modeling method of a control surface type honeycomb structural member suitable for remanufacturing and repairing, which comprises the following steps of S1: surveying and mapping the use state of the rudder surface honeycomb structural member on the machine body, and acquiring a first surface digital model; step S2: surveying and mapping a mounting seat for connecting a control surface type honeycomb structural member, and acquiring a second shape surface digital model; step S3: correcting the second topographic digital model and obtaining a third topographic digital model; step S4: surveying and mapping the rudder surface honeycomb structural part in a suspension state, and acquiring point cloud data with complete appearance of the rudder surface honeycomb structural part; step S5: and integrating the third shape surface digital model and the point cloud data to obtain an integral shape surface digital model of the control surface type honeycomb structural member. The shape information of the control surface type honeycomb structural part is mapped on the machine body, the point cloud data of the overall shape obtained by mapping in a suspension state are corrected, and the deviation of a reverse model and an actual model is reduced, so that the digital model of the overall shape of the control surface type honeycomb structural part is obtained.
Description
Technical Field
The invention relates to the technical field of reverse engineering of control surface honeycomb structural members, in particular to a reverse modeling method of a control surface honeycomb structural member suitable for remanufacturing and repairing.
Background
In the prior art, as shown in fig. 1, a control surface honeycomb structural member is generally formed by assembling and connecting 1 operating joint 1, a plurality of suspension joints 2 and a plurality of honeycomb unit bodies, and a typical structure of the honeycomb unit bodies is a wedge-shaped full-height honeycomb bonding structure which is formed by co-bonding an upper skin 3, a lower skin 4, a front beam 5, a rear edge strip 6, an end rib 7 and a honeycomb core 8 respectively; the joint is generally made of metal materials such as aluminum alloy, titanium alloy and the like, and the skin is generally a plane or small-curvature curved surface aluminum alloy or carbon fiber skin; for rudder surface honeycomb structural members used for a long time calendar, original design patterns cannot be obtained for some reasons, and a product digital model needs to be established through reverse engineering in the remanufacturing and repairing process so as to provide a manufacturing basis; for a control surface type honeycomb structural member, the shape surface and interface data of the structural member are generally obtained by combining photogrammetry with laser scanning at present, a product digital model is established according to surveying and mapping data, and finally, a manufacturing, gluing and assembling tool is designed according to the data, so that each remanufacturing and repairing process is completed.
The reverse modeling process of the control surface honeycomb structural member by adopting the prior art comprises the following steps: decomposing a to-be-painted product from a machine, cleaning to remove excess, freely placing the product, acquiring the shape and interface data of a structural member by adopting a photogrammetry and laser scanning combined method, establishing a digital model of the product according to the surveying and mapping data, smoothing the bulges and bulges in the modeling process, and taking the corrected digital model as a basis for designing the gluing and assembling tool.
Because the control surface type honeycomb structural part to be deeply repaired is generally used after a long-term calendar, a certain degree of internal stress is accumulated under the environmental action, after the control surface type honeycomb structural part is separated from a machine body, a certain degree of structural deformation exists in a free state compared with a new manufactured part, the shape surface and interface positions have larger deviation from an initial installation state, and the product in a free placement state is reversely modeled according to the prior art, so that the larger deviation exists between an obtained digital model and an actual model; on the other hand, in order to eliminate the deformation influence of the product after being separated from the machine, the machine can carry out surveying and mapping before the product is separated, but because the on-machine surveying and mapping is large in shading, the obtained information is too little, and a required digital model cannot be established, so the scheme is not adopted generally; it can be seen from the above that, the digital model and the actual model of the control surface honeycomb structural member obtained by the prior art have a certain deviation, and in the remanufacturing and repairing process, although the shape surface and the interface of the product can be guaranteed to fluctuate within the allowable range of the built model, the shape surface and the interface of the product may exceed the allowable range of the actual model, so that the problems that the step difference of the repaired product and the edge member exceeds the standard, the joint cannot be installed or harmful stress assembly is caused during the installation are caused.
Accordingly, the inventors provide a reverse modeling method for a control surface-like honeycomb structure suitable for remanufacture repairs.
Disclosure of Invention
(1) Technical problem to be solved
The embodiment of the invention provides a reverse modeling method of a control surface type honeycomb structural member suitable for remanufacturing and repairing, solves the problems that full-coverage mapping cannot be carried out on a machine body and deformation of a reverse modeling sample is eliminated, and ensures the accuracy of a reverse digital model.
(2) Technical scheme
In a first aspect, an embodiment of the present invention provides a reverse modeling method for a control surface type honeycomb structural member suitable for remanufacturing and repairing, configured to obtain an overall shape surface digital model of the control surface type honeycomb structural member, where the control surface type honeycomb structural member includes a steering joint, a suspension joint, an upper skin, a lower skin, a front beam, a trailing edge strip, an end rib, and a honeycomb core, and includes: step S1: surveying and mapping the use state of the control surface type honeycomb structural part on the machine body, and acquiring a first surface digital model; step S2: surveying and mapping a mounting seat for connecting the control surface type honeycomb structural member, and acquiring a second shape surface digital model, wherein the mounting seat is fixedly connected to the machine body; step S3: correcting the second topographic digital model and obtaining a third topographic digital model; step S4: surveying and mapping the control surface type honeycomb structural part in a suspension state, and acquiring point cloud data with complete appearance of the control surface type honeycomb structural part; step S5: and integrating the third shape surface digital model and the point cloud data to obtain the integral shape surface digital model of the rudder surface honeycomb structural member.
Further, the step S1 includes a step S11: adjusting the rudder surface type honeycomb structural member and the adjacent structural member thereof to be in a use state on the machine body; step S12: adopting a supporting and fixing device to keep the machine body in a stable state; step S13: photogrammetry and laser scanning are carried out on the rudder surface type honeycomb structural part and the adjacent structural parts thereof, and first profile data of the rudder surface type honeycomb structural part and the external peripheral extension area thereof are obtained; step S14: and removing abnormal bulges and pits in the first profile data, and smoothing the curved surface in a millimeter-scale deviation range to obtain the first profile digital model.
Further, a step S121 of detecting whether the machine body is stable by using a first laser tracker is further included between the step S12 and the step S13, and if so, the process proceeds to a step S13; if not, the monitoring is continued until the body is confirmed to be in a stable state.
Further, the outer peripheral extension area is the area range of the peripheral extension of the control surface honeycomb structure outwards by 500mm-600 mm.
Further, the step S2 includes a step S21: loosening a connecting pin of the mounting seat and the control surface type honeycomb structural part, and separating the control surface type honeycomb structural part from the mounting seat; step S22: reinserting the pin into the pin hole of the mount; step S23: photogrammetry and laser scanning are carried out on the mounting seat, and mounting surface data of the mounting seat, mounting axis data of the pin and second shape surface data of the mounting seat extending outwards within the range of 500mm-600mm are obtained; step S24: removing abnormal bulges and pits in the shape surface in the second shape surface data, smoothing the shape surface in a millimeter-scale deviation range, and obtaining an edge region shape surface digital model of the region of the mounting seat extending outwards by 500mm-600 mm; step S25: establishing a mounting axis digital model of the operating joint and the suspension joint in the same coordinate system according to the mounting axis data of the pin; step S26: fitting a mounting plane according to the mounting surface data of the mounting seat, and establishing a mounting surface digital model of the operating joint and the suspension joint in the same coordinate system; step S27: and combining the first surface data by taking the edge surface digital model as a reference, and replacing the second surface data with the first surface data to obtain the second surface digital model.
Further, step S22 and step S23 include step S221 of detecting whether the machine body is stable by using a second laser tracker, and if so, go to step S23; if not, the monitoring is continued until the body is confirmed to be in a stable state.
Further, first laser tracker with the second laser tracker is same laser tracker for a plurality of monitoring points on the organism are located in the monitoring, before laser monitoring begins, monitor more than 30min in advance, monitor every time the position interval of monitoring point 5mm, after the survey and drawing begins, every interval 30-40mm accomplishes once monitoring.
Further, the step S3 includes a step S31: analyzing the step difference between the periphery of the rudder surface honeycomb structural part to be mapped and the upper skin, and checking whether the body and the separated rudder surface honeycomb structural part have abnormal deviation or not in a contrast manner; step S32: removing abnormal data as abnormal deviation; and for normal deviation, continuously and respectively correcting the step difference of the peripheries of the upper skin and the control surface honeycomb structural member according to the priority flatness and curvature to obtain the third profile data model.
Further, the step S4 includes a step S41: designing and manufacturing a suspension tool according to the mounting surface digital model and the mounting axis digital model in the third shape digital model; step S42: respectively connecting the operating joint and the suspension joint of the control surface type honeycomb structural part with the suspension tool to enable the control surface type honeycomb structural part to be in a suspension state, and respectively fixing the operating joint and the suspension joint with the suspension connection point of the suspension tool by adopting glass cement; step S43: and carrying out photogrammetry and laser scanning on the control surface type honeycomb structural part in a suspension state to obtain point cloud data with complete appearance of the control surface type honeycomb structural part.
Further, the step S5 includes a step S51: integrating the point cloud data by taking the third geometric surface digital model as a reference; step S52: selecting the surface data of the upper skin in the point cloud data and the first surface data to fit, adjust and position the point cloud data; step S53: restoring appearance point cloud data related to the operating joint and the suspension joint in the point cloud data according to a rigid piece by taking the mounting surface digital model and the mounting axis digital model as references; step S54: restoring appearance point cloud data related to the front beam, the rear edge strip, the end ribs and the lower skin in the point cloud data according to elastic deformation by taking the first surface digital model as a reference; step S55: and continuously forming a plane or a curved surface according to the priority flatness and curvature, and correcting the shape surface of the front beam in the contact area between the operating joint and the suspension joint and the front beam respectively according to the recovered appearance point cloud data of the operating joint and the suspension joint, so as to obtain the integral shape surface digital model of the control surface honeycomb structural member.
(3) Advantageous effects
In conclusion, the invention obtains the first shape digital model by surveying and mapping the using state of the control surface honeycomb structural part on the machine body, removes the second shape digital model after surveying and mapping the mounting seat, and finally, integrating the third shape surface digital model and the point cloud data to obtain an integral shape surface digital model, acquiring a digital model of a mounting surface and a mounting axis of a mounting seat of the rudder surface honeycomb structural member to be remanufactured and repaired by adopting a hierarchical surveying and coordination type adjusting method, restoring an initial design principle of the deformed rudder surface honeycomb structural member, solving the deviation problem of conventional surveying and repairing in the prior art, realizing accurate restoration, and providing reliable design input for remanufacturing and repairing work.
According to the method, the surface information of the control surface honeycomb structural member is measured and drawn on the machine partially, the reverse digital model obtained by full-coverage measurement and drawing in a free placement state is corrected, and the deviation between the reverse model and an actual model is reduced, so that the control surface honeycomb structural digital model meeting the remanufacturing and repairing requirements is obtained.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a schematic structural view of a rudder surface type honeycomb structure of the prior art.
FIG. 2 is a flow diagram of the reverse modeling method of the present invention.
FIG. 3 is a schematic flow chart of the present invention for obtaining a first surface digital model.
FIG. 4 is a flow chart of the present invention for obtaining a second morphological digital model.
FIG. 5 is a flow chart of obtaining a third shape digital model according to the present invention.
Fig. 6 is a schematic flow chart of acquiring point cloud data according to the present invention.
FIG. 7 is a flow chart of obtaining the integer digital surface model according to the present invention.
Fig. 8 is a schematic structural view of a state of use of the control surface type honeycomb structure of the present invention on the machine body.
Fig. 9 is a schematic structural view of the suspension tool of the invention.
Fig. 10 is a schematic structural view of a suspended state of the rudder surface honeycomb structure according to the present invention.
In the figure:
1-an operating joint; 2-suspension joints; 3, covering the skin; 4-lower skin; 5-front beam; 6-a trailing edge strip; 7-end ribs; 8-a honeycomb core; 9-a mounting seat; 10-adjusting the gasket; 11-a pin; 20-an outer peripheral extension zone; 30-control surface honeycomb structural parts; 91-pinhole.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the invention and are not intended to limit the scope of the invention, i.e., the invention is not limited to the embodiments described, but covers any modifications, alterations, and improvements in the parts, components, and connections without departing from the spirit of the invention.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 2 is a schematic flow chart of a reverse modeling method of a rudder surface honeycomb structure suitable for remanufacturing and repairing, which is used for obtaining a digital model of the overall shape surface of the rudder surface honeycomb structure, as shown in fig. 1, 2, 9 and 10. As shown in fig. 1, the rudder surface-like honeycomb structure 30 includes a steering joint 1, a suspension joint 2, an upper skin 3, a lower skin 4, a front beam 5, a trailing edge strip 6, an end rib 7, and a honeycomb core 8, and has a length of 2m, as shown in fig. 2, the method includes the step S1: surveying and mapping the use state, namely the retracted state, of the rudder surface honeycomb structure on an airframe (not shown in the figure), wherein the rudder surface honeycomb structure is an airplane speed reduction plate, the airframe is a whole airplane, and the step S1 is to adjust the airplane speed reduction plate to the retracted state, arrange warning lines around a working area to prevent external interference and obtain a first surface digital model; step S2: surveying and mapping a mounting seat 9 (shown in fig. 9 and 10) for connecting the control surface type honeycomb structural part, obtaining a second shape surface digital model, and fixedly connecting the mounting seat 9 on the machine body; step S3: correcting the second topographic digital model and obtaining a third topographic digital model; step S4: surveying and mapping the rudder surface honeycomb structural part in a suspension state, and acquiring point cloud data with complete appearance of the rudder surface honeycomb structural part; step S5: and integrating the third shape surface digital model and the point cloud data to obtain the integral shape surface digital model of the rudder surface honeycomb structural member.
According to the method, a first shape face digital model is obtained by surveying and mapping the using state of the control surface type honeycomb structural part on the machine body, a second shape face digital model is removed after a mounting seat is surveyed and mapped, then the second shape face digital model is corrected to obtain a third shape face digital model, point cloud data is obtained by surveying and mapping the control surface type honeycomb structural part in a suspension state, finally the third shape face digital model and the point cloud data are integrated to obtain an integral shape face digital model, a hierarchical surveying and mapping and coordinated adjustment method is adopted, the mounting surface and the mounting axis digital model of the mounting seat of the control surface type honeycomb structural part to be remanufactured and repaired can be obtained, the initial design principle of the deformed control surface type honeycomb structural part is restored, the problem of deviation caused by conventional surveying and mapping in the prior art is solved, accurate restoration is realized, and reliable design input is provided for remanufacturing and repairing work.
As a preferred embodiment, as shown in fig. 3 and 8, the specific step of acquiring the first shape-face digital model includes step S11: adjusting the rudder surface type honeycomb structural member and the adjacent structural member thereof on the machine body to be in a use state, namely a retracted state; step S12: adopting a supporting and fixing device to keep the machine body in a stable state; step S13: photogrammetry and laser scanning are carried out on the control surface type honeycomb structural part and the adjacent structural parts thereof, and first profile data of the control surface type honeycomb structural part and the external peripheral extension area 20 thereof are obtained; step S14: removing abnormal bulges and pits in the profile in the first profile data, smoothing the profile in a millimeter-scale (1mm) deviation range, and obtaining a first profile digital model, wherein the first profile data is airfoil profile data on the whole airplane, and comprises profile data of a speed reduction plate and a wing trailing edge wall plate which are adjacent to two sides of the rudder-surface honeycomb structural member, and the first profile digital model is the whole airfoil profile digital model of the airplane.
As another preferred embodiment, as shown in fig. 2, a step S121 is further included between step S12 and step S13, that is, whether the machine body (not shown in the figure) is stable is detected by using the first laser tracker, and if yes, the process proceeds to step S13; if not, the monitoring is carried out until the body is confirmed to be in a stable state.
As other alternative embodiments.
Preferably, as shown in fig. 8, the outer peripheral extension area 20 is an area range where the periphery of the control surface type honeycomb structure 30 extends outwards 500mm-600mm, and the outer peripheral extension area comprises adjacent speed reduction plates and wing trailing edge wall plates on two sides of the control surface type honeycomb structure.
Preferably, as shown in fig. 4, the specific step of acquiring the second shape digital model includes step S21: loosening the connecting pin 11 of the mounting seat 9 and the control surface honeycomb structural part, taking down the adjusting gasket 10, and separating the control surface honeycomb structural part from the mounting seat 9; step S22: reinserting the pin 11 into the pin hole 91 of the mount 9; step S23: photogrammetry and laser scanning are carried out on the mounting seat 9, and mounting surface data of the mounting seat 9, mounting axis data of the pin 11 and second shape surface data of the periphery of the mounting seat 9, which extends outwards within the range of 500mm-600mm, are obtained, wherein the second shape surface data remove the airfoil surface shape surface data of the whole aircraft behind the control surface type honeycomb structural part; step S24: removing abnormal bulges and pits in the profile in the second profile data, smoothing the curved surface in the millimeter-scale (1mm) deviation range, and obtaining an edge profile digital model of the region of 500mm-600mm extending outwards from the periphery of the mounting seat 9; step S25: according to the installation axis data of the pin 11, an installation axis digital model of the operation joint 1 and the suspension joint 2 is established in the same coordinate system; step S26: fitting an installation plane according to the installation surface data of the installation seat 9, and establishing an installation surface digital model of the operation joint 1 and the suspension joint 2 in the same coordinate system; step S27: and taking the marginal area shape surface digital model as a reference, combining the first shape surface data, replacing the first shape surface data with the second shape surface data, and acquiring a second shape surface digital model, wherein the second shape surface digital model is a digital model of the airfoil surface data of the whole airplane with the installation surface and the installation axis of the installation seat and the control surface honeycomb structural member removed.
Preferably, as shown in fig. 4, the steps S22 and S23 further include step S221 of detecting whether the machine body (not shown) is stable by using the second laser tracker, and if so, the process goes to step S23; if not, the monitoring is carried out until the body is confirmed to be in a stable state.
Preferably, the first laser tracker and the second laser tracker are the same laser tracker and are used for monitoring a plurality of monitoring points (not shown in the figure) arranged on the airplane body, the monitoring is carried out for more than 30min in advance before laser monitoring is started, the position interval of each monitoring point is 5mm, and after surveying and mapping are started, the monitoring is completed once at the interval of 30-40 mm.
Preferably, as shown in fig. 1 and 5, the specific step of acquiring the third shape-face digital model includes step S31: analyzing the step difference between the periphery of the control surface type honeycomb structural part to be mapped and the upper skin 3, specifically, checking whether an abnormal deviation exists between the machine body (not shown in the figure) and a separated control surface type honeycomb structural part real object (not shown in the figure) or not by comparing the control surface type honeycomb structural part to be mapped and the left adjacent control surface type honeycomb structural part with the step difference of 2 mm; step S32: removing abnormal data as abnormal deviation; and for normal deviation, continuously and respectively correcting the step difference of the peripheries of the upper skin 3 and the control surface type honeycomb structural part according to the priority flatness and the curvature, specifically, performing flattening treatment and filling in a periphery normal area, continuously correcting the adjacent edges of the control surface type honeycomb structural part to be drawn and the left and right adjacent control surface type honeycomb structural parts according to the curvature until the maximum step difference of the digital models of the upper skin 3 and the periphery area is 0.08mm, and obtaining a third shape data model, wherein the third shape data model is an airfoil shape digital model comprising the installation surface and the installation axis of the installation seat. According to the method, the surface information of the control surface honeycomb structural member is measured and drawn on the machine partially, the reverse digital model obtained by full-coverage measurement and drawing in a free placement state is corrected, and the deviation between the reverse model and an actual model is reduced, so that the control surface honeycomb structural digital model meeting the remanufacturing and repairing requirements is obtained.
Preferably, as shown in fig. 6, 9 and 10, the specific step of acquiring the point cloud data includes step S41: designing and manufacturing a suspension tool according to an installation surface digital model and an installation axis digital model in the third shape digital model; step S42: respectively connecting an operating joint 1 and a suspension joint 2 of the control surface type honeycomb structural part 30 with a suspension tool to enable the control surface type honeycomb structural part 30 to be in a suspension state, and respectively fixing the operating joint 1 and the suspension joint 2 with a suspension connection point of the suspension tool by adopting glass cement; step S43: photogrammetry and laser scanning are carried out on the control surface type honeycomb structural part 30 in a suspension state, and point cloud data with complete appearance of the control surface type honeycomb structural part are obtained.
Preferably, as shown in fig. 1 and 7, the specific step of acquiring the overall shape face digital model includes step S51: integrating point cloud data by taking the third geometric surface digital model as a reference; step S52: selecting surface data of an upper skin 3 in the point cloud data and fitting the first surface data to adjust and position the point cloud data; step S53: restoring appearance point cloud data related to the operating joint 1 and the suspension joint 2 in the point cloud data according to the rigid part by taking the mounting surface digital model and the mounting axis digital model as references; step S54: restoring appearance point cloud data related to a front beam 5, a rear edge strip 6, an end rib 7 and a lower skin 4 in the point cloud data according to the elastic deformation by taking the first surface digital model as a reference; step S55: and continuously forming a plane or a curved surface according to the priority flatness and curvature, and correcting the shape surface of the front beam 5 in the contact area of the operating joint 1 and the suspension joint 2 and the front beam 5 respectively according to the recovered appearance point cloud data of the operating joint 1 and the suspension joint 2, so as to obtain the integral shape surface digital model of the control surface honeycomb structural member.
It should be clear that the embodiments in this specification are described in a progressive manner, and the same or similar parts in the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known process techniques is omitted herein for the sake of brevity.
The above description is only an example of the present application and is not limited to the present application. Various modifications and alterations to this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.
Claims (10)
1. Reverse modeling method suitable for rudder face class honeycomb structure of refabrication repair for obtain the whole shape face digital model of rudder face class honeycomb structure, rudder face class honeycomb structure includes manipulation joint (1), suspension joint (2), goes up covering (3), covering (4), front-axle beam (5), trailing edge strip (6), end rib (7) and honeycomb core (8) down, its characterized in that includes:
step S1: surveying and mapping the use state of the control surface type honeycomb structural part on the machine body, and acquiring a first surface digital model;
step S2: surveying and mapping a mounting seat (9) for connecting the control surface type honeycomb structural part, and acquiring a second shape surface digital model, wherein the mounting seat (9) is fixedly connected to the machine body;
step S3: correcting the second topographic digital model and obtaining a third topographic digital model;
step S4: surveying and mapping the control surface type honeycomb structural part in a suspension state, and acquiring point cloud data with complete appearance of the control surface type honeycomb structural part;
step S5: and integrating the third shape surface digital model and the point cloud data to obtain the integral shape surface digital model of the rudder surface honeycomb structural member.
2. The reverse modeling method for a rudder surface-like honeycomb structure suitable for remanufacturing and repairing according to claim 1, wherein the step S1 includes:
step S11: adjusting the rudder surface type honeycomb structural member and the adjacent structural member thereof to be in a use state on the machine body;
step S12: adopting a supporting and fixing device to keep the machine body in a stable state;
step S13: photogrammetry and laser scanning are carried out on the rudder surface type honeycomb structural part and the adjacent structural parts thereof, and first profile data of the rudder surface type honeycomb structural part and the external peripheral extension area (20) thereof are obtained;
step S14: and removing abnormal bulges and pits in the first profile data, and smoothing the curved surface in a millimeter-scale deviation range to obtain the first profile digital model.
3. The reverse modeling method for the rudder surface honeycomb structure suitable for remanufacturing and repairing according to claim 2, wherein between the step S12 and the step S13, the method further comprises a step S121 of detecting whether the machine body is stable by using a first laser tracker, and if so, the method goes to a step S13; if not, the monitoring is continued until the body is confirmed to be in a stable state.
4. The reverse modeling method of a rudder surface-like honeycomb structure suitable for remanufacturing and repairing according to claim 2, characterized in that the outer peripheral extension area (20) is an area range where the periphery of the rudder surface-like honeycomb structure extends outward 500mm to 600 mm.
5. The reverse modeling method for the control surface-type honeycomb structural member suitable for remanufacturing and repairing according to claim 2, wherein the step S2 includes:
step S21: loosening a connecting pin (11) of the mounting seat (9) and the control surface honeycomb structural part, and separating the control surface honeycomb structural part from the mounting seat (9);
step S22: reinserting the pin (11) into the pin hole (91) of the mounting seat (9);
step S23: photogrammetry and laser scanning are carried out on the mounting seat (9), and mounting surface data of the mounting seat (9), mounting axis data of the pin (11) and second shape surface data of the mounting seat (9) extending outwards within the range of 500mm-600mm are obtained;
step S24: removing abnormal bulges and pits in the shape surface in the second shape surface data, smoothing the curved surface in a millimeter-scale deviation range, and obtaining an edge region shape surface digital model of the region of 500mm-600mm extending outwards from the periphery of the mounting seat (9);
step S25: establishing a digital model of the installation axis of the steering joint (1) and the suspension joint (2) in the same coordinate system according to the installation axis data of the pin (11);
step S26: fitting an installation plane according to the installation surface data of the installation seat (9), and establishing an installation surface digital model of the operation joint (1) and the suspension joint (2) in the same coordinate system;
step S27: and combining the first surface data by taking the edge surface digital model as a reference, and replacing the second surface data with the first surface data to obtain the second surface digital model.
6. The reverse modeling method for the rudder surface honeycomb structure suitable for remanufacturing and repairing according to claim 5, wherein the steps S22 and S23 further include a step S221 of detecting whether the machine body is stable by using a second laser tracker, and if so, the method goes to a step S23; if not, the monitoring is continued until the body is confirmed to be in a stable state.
7. The reverse modeling method for the control surface honeycomb structural member suitable for remanufacturing and repairing according to claim 3 or 5, wherein the first laser tracker and the second laser tracker are the same laser tracker and are used for monitoring a plurality of monitoring points arranged on the machine body, the monitoring is performed for more than 30min in advance before laser monitoring is started, the position interval of each monitoring point is 5mm, and after surveying and mapping are started, the monitoring is performed once every 30-40 mm.
8. The reverse modeling method for a control surface-like honeycomb structure suitable for remanufacturing and repairing according to claim 1 or 5, wherein the step S3 includes:
step S31: analyzing the step difference between the periphery of the rudder surface honeycomb structural part to be mapped and the upper skin (3), and checking whether the abnormal deviation exists between the body and the separated rudder surface honeycomb structural part in a contrast manner;
step S32: removing abnormal data as abnormal deviation; and for normal deviation, continuously and respectively correcting the step difference of the peripheries of the upper skin (3) and the control surface honeycomb structural member according to the priority flatness and curvature to obtain the third profile data model.
9. The reverse modeling method for a rudder surface-like honeycomb structure suitable for remanufacturing and repairing according to claim 8, wherein the step S4 includes:
step S41: designing and manufacturing a suspension tool according to the mounting surface digital model and the mounting axis digital model in the third shape digital model;
step S42: respectively connecting the operating joint (1) and the suspension joint (2) of the control surface type honeycomb structural member with the suspension tool, so that the control surface type honeycomb structural member is in a suspension state, and respectively fixing the operating joint (1) and the suspension joint (2) with the suspension connection point of the suspension tool by adopting glass cement;
step S43: and carrying out photogrammetry and laser scanning on the control surface type honeycomb structural part in a suspension state to obtain point cloud data with complete appearance of the control surface type honeycomb structural part.
10. The reverse modeling method for a rudder surface-like honeycomb structure suitable for remanufacturing and repairing according to claim 9, wherein the step S5 includes:
step S51: integrating the point cloud data by taking the third geometric surface digital model as a reference;
step S52: selecting the surface data of the upper skin (3) in the point cloud data and fitting the first surface data to adjust and position the point cloud data;
step S53: restoring appearance point cloud data related to the operating joint (1) and the suspension joint (2) in the point cloud data according to a rigid piece by taking the mounting surface digital model and the mounting axis digital model as references;
step S54: restoring appearance point cloud data related to the front beam (5), the rear edge strip (6), the end ribs (7) and the lower skin (4) in the point cloud data according to elastic deformation by taking the first surface digital model as a reference;
step S55: and continuously forming a plane or a curved surface according to the priority flatness and curvature, and correcting the shape surface of the front beam (5) in the contact area of the operating joint (1) and the suspension joint (2) and the front beam (5) respectively according to the recovered appearance point cloud data of the operating joint (1) and the suspension joint (2), thereby obtaining the integral shape surface digital model of the control surface honeycomb structural member.
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