CN114054939B - Efficient and precise processing method for composite material curled structure - Google Patents
Efficient and precise processing method for composite material curled structure Download PDFInfo
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- CN114054939B CN114054939B CN202111351615.5A CN202111351615A CN114054939B CN 114054939 B CN114054939 B CN 114054939B CN 202111351615 A CN202111351615 A CN 202111351615A CN 114054939 B CN114054939 B CN 114054939B
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- 238000003672 processing method Methods 0.000 title abstract description 17
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- 239000000463 material Substances 0.000 claims description 25
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- 150000002910 rare earth metals Chemical class 0.000 claims description 3
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 10
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/70—Auxiliary operations or equipment
- B23K26/702—Auxiliary equipment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2103/00—Materials to be soldered, welded or cut
- B23K2103/16—Composite materials, e.g. fibre reinforced
Abstract
The invention relates to a high-efficiency precise processing method of a composite material curling structure, which comprises the following steps: a. placing a protective backing plate on a ferromagnetic bearing and moving platform; b. flattening and attaching the coiled structure workpiece to be processed to the protective backing plate; c. placing a plurality of magnets on the surface of the flattened curled workpiece, and pressing the edge and the inner area of the flattened curled workpiece by utilizing the plurality of magnets in an adsorption mode; d. and processing the target area of the flattened curled workpiece by using a laser processing system. The processing method can solve the problems of high preparation period occupation ratio, low tool utilization rate, complex clamping process, outstanding processing damage and production efficiency, cost, precision and damage caused by the complex clamping process of the clamping tool in the existing processing method.
Description
Technical Field
The invention relates to the technical field of high-performance processing of composite material structures, in particular to a high-efficiency precise processing method of a composite material curled structure.
Background
The composite material is widely applied to the fields of military and civil equipment such as aviation, aerospace, weapons, rail trains and the like by virtue of excellent physical and chemical properties, and particularly the carbon fiber reinforced or toughened composite material is the most widely applied and important composite material in various composite materials by virtue of the advantages of low density, high strength, high modulus, low expansion, corrosion resistance and the like. Its level and scale of application has even been related to the success and failure of space weapon equipment crossover lifting and model development. With the maturation of new composite preparation technology and the advent of new composite, the depth and breadth of application of composite in the relevant fields is expected to be further deepened.
The honeycomb sandwich structure is one of the most important component forms of the bearing structure of the light, high-strength and high-rigidity products on satellites. The sandwich structure in the most widely used form of skin-honeycomb-skin is widely used for space vehicle structural panel products such as box-panel load cabins. Taking satellite carbon skin (with typical thickness less than or equal to 0.6 mm) as an example, although the satellite carbon skin is in a plane state in sandwich structures such as structural plates, most of the satellite carbon skin is prepared by asymmetric layering and heat curing, so that the satellite carbon skin is in a curled state in a free state (namely before being compounded with honeycomb into a planar structural plate). Before the coiled structure is assembled into a structural plate with a honeycomb, the coiled structure faces the unavoidable material reduction processing requirements of trimming, perforating and the like, has the characteristics of light weight, hardness, brittleness, high modulus, and simultaneously has the advantages of light weight, high rigidity, high strength and the like for sandwich structure products such as the structural plate and the like, and also has the problems of processing damage, processing tool consumables, clamping process, production efficiency, cost and the like for material reduction processing such as cutting, perforating and the like. For example, in terms of tooling consumables and production efficiency, based on the existing contact type material reduction processing method, a patterned metal drill jig prepared in advance is used as a flattening and positioning tool for subsequent manual material reduction processing (such as manual punching), or an upper layer and a lower layer of epoxy glass cloth plates are used as flattening and protection tools for subsequent machine tool material reduction processing. The development mode of various small batches of space aircrafts causes the metal drilling jig or the epoxy glass cloth plate to fall into a disposable tool. In particular, the metal drill jig used as a tool is required to undergo links such as cutting, deburring, detection and the like in the production process, so that the necessary time for producing the tool occupies a large proportion of the whole process manufacturing time of carbon skin manufacturing. In the aspect of the clamping process, the existing processing mode is to adopt a dry cutting method to process a sandwich structure of a cover plate tool, a carbon skin product and a bottom plate tool. Considering that the sandwich structure is processed (especially processed by a dry method) and has natural adverse factors such as large knife resistance, if a reliable mechanical clamping means is not adopted, the situation that the processed carbon skin product horizontally slides, the sandwich structure is separated when the knife is lifted, and the like is caused, and the problems of position deviation of the processed structure (such as a hole site) or damage to the edge of the structure are extremely easy to cause. The reliable clamping brings the problems of excessively high clamping time ratio and the like. In the aspect of processing damage, the nonmetallic composite material belongs to a strong and hard laminated structure, and the existing contact processing mode is extremely easy to cause the damage and defect problems of wiredrawing, layering and the like of the material surface skin, thereby influencing the structural precision and mechanical property of the product.
Disclosure of Invention
The invention provides an efficient and precise machining method for a composite material coiled structure, which aims to solve the problems of high preparation cycle ratio of a clamping tool, low tool utilization rate, complex clamping process before machining, outstanding mechanical damage in the machining process and the like of the conventional composite material coiled structure machining method and the problems of production efficiency, cost, precision and damage caused by the problems.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
the invention provides a high-efficiency precise processing method of a composite material curling structure, which comprises the following steps:
a. placing a protective backing plate on a ferromagnetic bearing and moving platform;
b. flattening and attaching the coiled structure workpiece to be processed to the protective backing plate;
c. placing a plurality of magnets on the surface of the flattened curled workpiece, and pressing the edge and the inner area of the flattened curled workpiece by utilizing the plurality of magnets in an adsorption mode;
d. and processing the target area of the flattened curled workpiece by using a laser processing system.
According to one aspect of the invention, after said step c and before said step d, said method further comprises:
measuring a flatness error of the target area of the flattened coiled structure workpiece;
evaluating the influence degree of the flatness error on the shape and the position of the flattened curled structure workpiece;
if the flatness error is insufficient to cause the relative position and absolute shape size of the target area to be out of tolerance when the flatness is sufficient, continuing to execute the step d, otherwise, adjusting the distribution positions and densities of the plurality of magnets in the step c.
According to one aspect of the invention, the flatness error of the target area of the flattened coiled structure workpiece is measured using the ranging optics of the laser machining system or an external photogrammetry optics.
According to one aspect of the invention, the protective pad has a dimension that is not less than the flattened dimension of the coiled work piece to be processed and is naturally planar.
According to one aspect of the invention, the protective backing plate is a material having a laser energy reflectivity of < 20% and a damage threshold of at least 3 times the damage threshold of the coiled work piece to be processed, the material comprising at least an asbestos rubber plate or an asbestos latex plate.
According to one aspect of the invention, the material of the coiled structure workpiece to be processed is a fiber composite material which is coiled in a free state and can be flattened.
According to one aspect of the invention, the convex surface of the coiled structure workpiece to be processed faces the processing light source of the laser processing system, the concave surface faces the protection backing plate, the concave surface of the coiled structure workpiece is attached to the protection backing plate, and the plurality of magnets are arranged on the convex surface of the coiled structure workpiece in a punctiform layout.
According to one aspect of the invention, the plurality of magnets are rare earth permanent magnets.
According to one aspect of the invention, the step d comprises:
in the laser processing system, parameters and track parameters of a pulse laser processing optical knife are selected based on acceptable damage degree and accuracy of the flattened coiled structure workpiece, and processing of a preset structure is performed on the target area.
According to one aspect of the invention, the pulse laser processing optical knife applies a pulse laser with a pulse width ranging from 7fs to 100ns.
The beneficial effects are that:
according to the scheme of the invention, the efficient and precise processing method of the composite material curled structure is a processing method for avoiding a one-time processing tool aiming at a composite material thin-wall structure in a curled state in a free state. Compared with the existing contact type machining, the requirement on a pressing tool is greatly reduced due to no contact stress during product machining, so that the preparation of the equal-amplitude metal drilling jig with the functions of leveling and positioning or the consumption of the equal-amplitude non-metal cover plate with the functions of leveling and scratch prevention is avoided. Therefore, the invention not only effectively shortens the process flow and shortens the production period of the product, but also realizes the great reduction of tooling processing cost or tooling consumable cost by avoiding the processing of the constant-amplitude metal drilling jig or the consumption of the constant-amplitude nonmetal cover plate.
The invention relates to a non-contact processing method by utilizing a scanning galvanometer and other remote laser modes. The non-contact processing characteristic reduces the clamping requirement. Therefore, compared with the existing product clamping process before contact machining and the product clamping process after machining, the method can realize reliable clamping and clamping removal only through strong magnet adsorption type compression (realizing dot-shaped layout similar to a chess playing mode) and magnet pulling-out, thereby avoiding the complex process of traditional screw thread-pressing plate type compression and decompression compression and realizing localized clamping flatness regulation and control according to the machining precision requirement. In addition, the non-contact processing characteristic avoids the defects of force-induced delamination, skin tearing, edge breakage and the like which are easily caused by the fact that the inherent characteristic of the traditional contact processing fiber composite material is lamination characteristic, so that the interlayer bonding force is weak, and the method is an efficient, flexible and low-damage processing method.
The invention uses mineral flat plate materials with low reflectivity, high damage threshold and low cost as protective backing plates of processed products. As the frock consumptive material, the existence of protection backing plate is not only in order to prevent the product by bearing and motion system platform scratch, also in order to prevent when needing to process thoroughly the product, for example cutting technology, need cut reliably and cut the protection backing plate that the product so is unavoidable to cut its below, and the cutter is damaged and is born and motion system platform. This is common to existing cutting processes and the process of the present invention. However, because the efficient and precise processing method of the composite material curling structure of the invention adopts a remote laser adding mode such as a scanning galvanometer and the like, macroscopic material reduction processing such as cutting and the like is realized through multipass reciprocating fine removal, namely the width and depth resolution of material removal is far higher than the cutting resolution of a traditional macroscopic cutter. On the other hand, the protective backing plate is made of a material with the laser energy reflectivity less than 20% and the damage threshold more than 3 times of the threshold of the material to be processed, so that the protective backing plate below the protective backing plate can be only processed without damage or only slightly damaged. Therefore, compared with the existing contact type processing, the invention can realize the effect of micro damage and even damage prevention on the protective backing plate. The method creates conditions for repeatedly utilizing the gasket material, thereby avoiding disposable consumption and frequent replacement of the gasket, being beneficial to reducing tool consumables and improving production efficiency.
Drawings
FIG. 1 schematically illustrates a flow chart of a method for efficient precision machining of a composite coiled structure in accordance with one embodiment of the present invention;
FIG. 2 schematically illustrates a flow chart of a method of efficient precision machining of a composite coiled structure in accordance with another embodiment of the present invention;
fig. 3 schematically illustrates a processing system of a method for efficient precision processing of a composite coiled structure according to an embodiment of the present invention.
Reference numerals illustrate:
1-pulsed laser source input; 2-a scanning laser processing head positionable in three directions X, Y, Z; 3-a load-bearing and motion system platform; 4-a protective backing plate; 5-blank; 6-neodymium magnet; relative positional relationship: along the plus z direction (i.e., the height direction), 3, 4, 5, 6 are sequentially arranged.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments will be briefly described below. It is apparent that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
The present invention will be described in detail below with reference to the drawings and the specific embodiments, which are not described in detail herein, but the embodiments of the present invention are not limited to the following embodiments.
FIG. 1 is a flow chart of a method of efficient precision machining of a composite coiled structure in accordance with one embodiment of the present invention. As shown in fig. 1, the efficient and precise machining method of the composite material curled structure comprises the following steps:
a. placing a protective backing plate on a ferromagnetic bearing and moving platform;
b. flattening and attaching the coiled structure workpiece to be processed to the protective backing plate;
c. placing a plurality of magnets on the surface of the flattened curled workpiece, and pressing the edge and the inner area of the flattened curled workpiece by utilizing the plurality of magnets in an adsorption mode;
d. and processing the target area of the flattened curled workpiece by using a laser processing system.
FIG. 2 is a flow chart of a method for efficient precision machining of composite coiled structures in accordance with another embodiment of the present invention. An embodiment of the present invention is described in detail below with reference to fig. 2.
As shown in fig. 2, the efficient and precise processing method of the composite material coiled structure of the present embodiment includes the following steps:
a. and (3) placing a protective backing plate with a size not smaller than the flattening size of the workpiece with the coiled structure to be processed and being in a plane naturally on a ferromagnetic bearing and moving platform, and naturally paving.
In the step a, the protective backing plate is made of a material with the laser energy reflectivity less than 20% and the damage threshold value at least 3 times that of the coiled structure workpiece to be processed, and the material at least comprises an asbestos rubber plate or an asbestos latex plate. It is possible to achieve a protective pad under which only the product is processed without damage or only slight damage.
b. The method comprises the steps of flattening a coiled structure workpiece to be processed by using a convex surface of the coiled structure workpiece to be processed towards a light source to be processed and a concave surface towards a protective backing plate, enabling the concave surface of the coiled structure workpiece to be flattened, enabling the concave surface to be attached to the protective backing plate, placing a plurality of magnets with soft materials wrapped on the surface on the convex surface of the coiled structure workpiece at corresponding distribution positions and densities, and firstly pressing the flattened edge of the coiled structure workpiece by using the magnets in an adsorption mode and then fixing an inner area. The magnet point distribution position is suitable for the position of optical processing under the condition of not interfering laser, and the point distribution density is judged by the required flattening degree: the denser is generally flatter. Preferably, the magnets are rare earth permanent magnets, such as neodymium magnets 6.
In step b, the material of the workpiece with the curled structure to be processed is a fiber composite material which is curled in a free state and can be flattened in an elastic range.
c. And measuring the flatness error of the flattened structure target area by adopting an optical method such as a ranging optical system of a laser processing system or external photogrammetry and the like.
d. The degree of influence of the flatness error on the shape and position of the flattened structure is evaluated. And (c) for the target area, if the flatness error is insufficient to cause the relative position and the absolute shape size of the target area to be out of tolerance when the flatness error is sufficient to be flattened, continuing to execute the following steps, otherwise, adjusting the distribution position and the density of the magnet in the step b until the flatness requirement is met.
e. And according to the acceptable damage degree and accuracy of material processing, a laser processing head mode is used, corresponding pulse laser processing optical knife parameters and track parameters are selected, a block splicing process is adopted, and trimming, perforating or other operation requirements are carried out on a target area of a flattened structure until the processing of all preset structures of the workpiece with the curled structure is completed. The pulse width range of the pulse laser applied by the pulse laser processing optical knife is 7 fs-100 ns.
In the present embodiment, a piece of asbestos rubber material protection pad 4 with the dimensions of 2500mm×2000mm×2mm is placed on a machine tool carrying and moving system platform 3 with ferromagnetism, and is naturally laid flat.
The blank of the workpiece with the coiled structure to be processed is a high-modulus carbon fiber reinforced resin-based skin blank 5 with a coiled state, the convex surface of the blank faces the light source to be processed, the concave surface of the blank faces and is attached to the protective backing plate 4, and a plurality of neodymium magnets 6 with soft materials are wrapped on the surface of the blank, and the blank is placed on the convex surface of the blank 3 at corresponding distribution positions and densities, so that the position of the blank 5 is consolidated by positive pressure generated by adsorption of the neodymium magnets 6 and horizontal friction force generated by the positive pressure.
A high-precision laser ranging system of the laser processing system is adopted to evaluate the flatness error of the target area of the flattened blank 5 and evaluate the influence degree of the flatness error on the shape and the position of an ideal flattened structure. For the target area of the curled blank 5, the flatness error after clamping is only 0.15mm, so when the curled blank 5 is ideally flattened (i.e. the flatness error tends to zero), the hole pitch error and the shape error caused by the flatness error of clamping are still within the design tolerance range allowed by the processed product, and therefore, the distribution position and the density of each neodymium magnet 6 do not need to be adjusted.
The scanning galvanometer type laser processing head 2 and the energy of the pulse laser transmitted by the scanning galvanometer type laser processing head are adopted to carry out corresponding trimming and perforating processing on the target area of the spread blank 5 through a mode of 'reciprocating etching and block splicing', and the processing of all structures is completed.
According to the processing system shown in fig. 3 and the processing flow shown in fig. 2, the coiled carbon skin with the mark of M55/BS-4 and the thickness of 0.40mm is cut, so that the integral processing of the cut straight edge and the internal hole structure is realized, and the thickness of the expected thermal deterioration layer of the processed edge is not more than 20 mu M.
Taking into consideration Gaussian pulse sequence with a central wavelength of 532nm, a single pulse duration of 12ps and a repetition frequency of 1MHz, inputting a pulse laser source of the Gaussian pulse sequence into 1 by adopting an energy transmission mode of a scanning galvanometer, and projecting the pulse laser source onto the surface of a curled carbon skin pressed by a flattened magnet to generate a peak flux of 10-20J/cm 2 And adjusting the galvanometer control to generate proper scanning speed so as to lead the light spot overlapping rate to be about 80 percent. And (3) carrying out corresponding trimming and perforating processing on the target area of the spread blank 5 by utilizing the pulse laser processing optical knife parameter and the track parameter through a mode of 'reciprocating etching and block splicing', and finishing the processing of all structures. Compared with the traditional method, the method does not need to develop a constant-amplitude metal drilling jig or use a constant-amplitude nonmetal cover plate as a positioning or flattening tool of a machined workpiece. Therefore, the process flow is effectively shortened, the production period of the product is shortened, and the tooling processing cost or the tooling consumable cost is greatly reduced. Generally, for the production of the constant-width metal drilling jig tool in the existing processing mode, even if the necessary management processes such as transferring and handing over after the production are not considered (but only the net time of the technical links such as laser cutting, quality inspection and the like is counted), the consumed necessary time is not lower than the subsequent product processing time, so if the production link of the constant-width metal drilling jig tool can be omitted, the curling carbon mask can be greatly improvedThe production efficiency of the skin product. In addition, the characteristic of non-contact processing reduces the clamping requirement, so that the quick clamping before processing and the quick clamping removal after processing can be finished only by using a powerful magnet for distribution in a chess-like manner, and compared with the traditional thread-pressing plate type processing manner, the processing method can obviously greatly compress the clamping and clamping removal preparation time before and after processing of the material, and further improves the production efficiency. Meanwhile, the characteristics of ultrashort pulse laser non-contact processing and the inherent advantages of low heat input avoid the defects of delamination, surface tearing, edge breakage and the like caused by processing force which are easy to occur in the existing contact processing fiber composite material (the inherent characteristic is lamination characteristic, and therefore the interlayer bonding force is weak). In summary, the efficient and precise processing method of the composite material coiled structure of the embodiment is an efficient, high-quality and low-cost processing method.
The above description is only one embodiment of the present invention and is not intended to limit the present invention, and various modifications and variations of the present invention will be apparent to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A high-efficiency precise machining method of a composite material curled structure comprises the following steps:
a. placing a protective backing plate on a ferromagnetic bearing and moving platform;
b. flattening and attaching the coiled structure workpiece to be processed to the protective backing plate;
c. placing a plurality of magnets on the surface of the flattened curled workpiece, and pressing the edge and the inner area of the flattened curled workpiece by utilizing the plurality of magnets in an adsorption mode;
d. processing a target area of the flattened coiled structure workpiece by using a laser processing system;
after step c and before step d, the method further comprises:
measuring a flatness error of the target area of the flattened coiled structure workpiece;
evaluating the influence degree of the flatness error on the shape and the position of the flattened curled structure workpiece;
if the flatness error is insufficient to cause the relative position and absolute shape size of the target area to be out of tolerance when the flatness error is sufficient, continuing to execute the step d, otherwise, adjusting the distribution positions and densities of the plurality of magnets in the step c;
the protective backing plate is made of a material with the laser energy reflectivity less than 20% and the damage threshold value at least 3 times of that of the coiled structure workpiece to be processed, and the material at least comprises an asbestos rubber plate or an asbestos latex plate;
the convex surface of the coiled structure workpiece to be processed faces the processing light source of the laser processing system, the concave surface faces the protection backing plate, the concave surface of the coiled structure workpiece is attached to the protection backing plate, and the magnets are arranged on the convex surface of the coiled structure workpiece in a punctiform layout.
2. The method of claim 1, wherein a ranging optical system of the laser machining system or an external photogrammetry optical system is employed to measure flatness error of the target area of the flattened coiled structure workpiece.
3. The method of claim 1, wherein the protective pad has a dimension that is not less than a flattened dimension of the coiled work piece to be processed and is naturally planar.
4. The method according to claim 1, characterized in that the material of the curled work piece to be processed is a fiber composite material which is curled in a free state and can be flattened in an elastic range.
5. The method of claim 1, wherein the plurality of magnets are rare earth permanent magnets.
6. The method according to claim 1, wherein said step d comprises:
in the laser processing system, parameters and track parameters of a pulse laser processing optical knife are selected based on acceptable damage degree and accuracy of the flattened coiled structure workpiece, and processing of a preset structure is performed on the target area.
7. The method of claim 6, wherein the pulse laser machining optical knife applies a pulse laser having a pulse width in the range of 7fs to 100ns.
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