CN117682087A - Profile compensation control method for composite reinforced wallboard - Google Patents
Profile compensation control method for composite reinforced wallboard Download PDFInfo
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- CN117682087A CN117682087A CN202311558303.0A CN202311558303A CN117682087A CN 117682087 A CN117682087 A CN 117682087A CN 202311558303 A CN202311558303 A CN 202311558303A CN 117682087 A CN117682087 A CN 117682087A
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- 239000002131 composite material Substances 0.000 title claims abstract description 42
- 238000000034 method Methods 0.000 title claims abstract description 31
- 238000012360 testing method Methods 0.000 claims abstract description 14
- 238000007711 solidification Methods 0.000 claims abstract description 12
- 230000008023 solidification Effects 0.000 claims abstract description 12
- 230000008439 repair process Effects 0.000 claims abstract description 9
- 230000008569 process Effects 0.000 claims description 8
- 230000004048 modification Effects 0.000 claims description 6
- 238000012986 modification Methods 0.000 claims description 6
- 238000012937 correction Methods 0.000 claims description 5
- 238000005520 cutting process Methods 0.000 claims description 2
- 238000004364 calculation method Methods 0.000 abstract description 2
- 238000005259 measurement Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 4
- 238000000465 moulding Methods 0.000 description 4
- 238000009966 trimming Methods 0.000 description 4
- 239000002313 adhesive film Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000001668 ameliorated effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 230000001739 rebound effect Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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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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- 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
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G16—INFORMATION AND COMMUNICATION TECHNOLOGY [ICT] SPECIALLY ADAPTED FOR SPECIFIC APPLICATION FIELDS
- G16C—COMPUTATIONAL CHEMISTRY; CHEMOINFORMATICS; COMPUTATIONAL MATERIALS SCIENCE
- G16C60/00—Computational materials science, i.e. ICT specially adapted for investigating the physical or chemical properties of materials or phenomena associated with their design, synthesis, processing, characterisation or utilisation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Theoretical Computer Science (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computing Systems (AREA)
- Composite Materials (AREA)
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Abstract
The invention discloses a profile compensation control method for a composite material reinforced wallboard. The invention controls the overall transverse solidification deformation of the wallboard by adjusting the strategy of the stringer profile compensation amount, and determines the main parameters of profile compensation by test and measurement as follows: the stringer compensation wallboard deformation repair angle is obtained through a deduction calculation method, so that the deformation problem of the reinforced wallboard is improved.
Description
Technical Field
The invention belongs to the technical field of aircraft composite material manufacturing, and particularly relates to a profile compensation control method for a composite material stringer and a reinforced wallboard.
Background
The composite material integrated reinforced wallboard is a reinforced wallboard assembly formed by bonding a plurality of T-shaped, I-shaped or J-shaped stringers and a skin together through an adhesive film, and is manufactured integrally by adopting a process of co-bonding the cured stringers and the uncured skin. The common structures of the T-shaped and J-shaped stringer parts made of the composite materials are two L-shaped prefabricated bodies, twisted sub-strips and stringer bottom edge bottom plates, and the common structures of the I-shaped stringer parts are two C-shaped prefabricated bodies, twisted sub-strips and stringer bottom edge bottom plates.
The non-uniform stresses generated internally during the molding process of the composite member cause the member to exhibit curing deformation after it is removed from the mold. The transverse solidification deformation trend of the stringer structure is relatively regular on the premise that the layering is integrally symmetrical, and the buckling deformation of the edge strips on the two sides of the stringer towards the web plate direction is achieved. After the stringers are combined with the skin, the reinforced wall plate as a whole can also transversely warp due to the L-shaped structure corner rebound effect, wherein the transverse warping is mainly influenced by factors such as the number of the stringers, the deformation of the stringers, the stringers and the thickness of the skin.
At present, there is a control method for predicting the deformation of the stringer and compensating the profile, see Chinese patent publication CN15107297a (a control method for compensating the profile of a T-shaped part made of composite material). The method only aims at the solidification prediction and the profile compensation of the independently solidified composite material T-shaped part, so that the self profile of the T-shaped structural part is closer to the design theoretical profile, the relation between the stringer profile compensation quantity and the integral solidification deformation of the reinforced wallboard is not considered, and the stringer profile compensation has no compensation effect on the integral solidification deformation of the wallboard.
If the problem of transverse solidification deformation of the panel is ameliorated by compensating the profile of the panel forming cementing jig with reference to the above method, the following risks exist. 1) The matching property between the molded surface of the molding cementing fixture and the cured stringer cementing surface is poor after the molded surface of the molding cementing fixture is compensated, and the internal quality risk exists; 2) Because the mold surface is changed, the stringers are difficult to accurately position on the skin, and key technical indexes such as the axiality of the stringers are difficult to reach the standard; 3) The shaping cementing fixture is a high-value tool with a thin-wall structure, the technical risk of tool profile compensation is extremely high, and the thin-wall structure does not have the feasibility of multiple compensation.
Therefore, for the problem of transverse solidification deformation of composite reinforced wallboard, there is an urgent need for a simple and reliable method for controlling the overall transverse solidification deformation of wallboard by adjusting the strategy of the stringer profile compensation.
Disclosure of Invention
The invention aims to provide a profile compensation control method for a composite material reinforced wallboard, which aims to solve the problems in the background technology. The composite material reinforced wallboard manufactured by the method has the advantages of high stringer cementing quality, accurate axis positioning, obvious improvement of transverse solidification deformation of the wallboard, higher numerical control milling precision and smaller integral assembly stress of the wallboard.
The invention mainly aims at the composite reinforced wallboard part bonded by the cured stringer and the uncured skin, and the integral transverse curing deformation of the wallboard is controlled by adjusting the compensation amount of the stringer profile.
A profile compensation control method for a composite material reinforced wallboard is characterized in that the composite material reinforced wallboard with the transverse bow height smaller than 200mm is used for the theoretical profile surface of a wallboard skin, and the profile of a stringer part is compensated, so that the integral transverse solidification deformation of the wallboard is controlled, and the concrete steps are as follows:
1, expanding a skin theoretical appearance surface in a composite material reinforced wallboard theoretical model into a skin theoretical plane;
dividing the composite material reinforced wallboard theoretical model into x typical characteristic sections along the transverse direction of the stringer, wherein the typical characteristic sections intersect with a skin theoretical plane to form x typical characteristic section lines;
3, along the transverse direction of the stringer, randomly cutting a section in the equal thickness area of the reinforced wallboard, forming two intersection points with the theoretical profile surface of the skin, and measuring the length L of the intersection point connecting line in the theoretical model of the reinforced wallboard made of the composite material 0 The number of stringers on the section is n, a composite material reinforced wallboard test piece containing the section is manufactured according to a theoretical model of the composite material reinforced wallboard, and the initial deformation tangent included angle alpha of the section in the test piece is measured 0 The width of the edge strip of any stringer cementing surface on the section is L i I=1, 2,3 …, n, panel skin thickness δ 0 The thickness of the stringer edge strip is delta i ，i＝1,2,3…,n；
4 according to L 0 、α 0 Constructing an arc line with the same diameter and taking the arc line as a typical deformation section line;
5 according to the formulaObtaining the deformation correction angle theta of the arbitrary stringer compensation wallboard i I=1, 2,3 …, n, wherein: k (k) i The deformation non-uniformity coefficient of the wallboard;
6 deformation modification angle theta of stringer compensation wallboard i The method is applied to the repair compensation process of the stringer mould.
Further, the wall plate deformation unevenness coefficient k i Is of the value of (2)In relation to, when->When k is i =1.05; when->When k is i =1; when->When k is i ＝0.95。
Further, when the number x of typical characteristic sections is greater than 1, the steps 3-6 can be repeated to perform multi-section modification compensation on the stringers.
Further, the mould included angle between any stringer web and edge strip on the stringer mould Wherein θ is Theory of Is the theoretical included angle theta between the stringer web and the edge strip 0 Compensating the angle for the stringer itself.
Further, the stringer itself is trimmed to compensate for angle θ 0 In order to compensate the included angle between the web and the edge strip after the stringer is deformed to the angle of the theoretical profile, the stringer test piece can be manufactured.
Further, the theoretical angle of residual deformation after the deformation correction and compensation of the wallboard is as follows
The positioning device and the positioning method have the following advantages: 1) The method is simple, the complex problems are simplified, and the profile compensation repair operation is simple; 2) The process has strong adaptability, and is suitable for T-shaped, I-shaped and J-shaped stringers with different edge strip widths and different web and edge strip included angles; 3) The technical risk is low, the traditional repairing compensation thought of directly carrying out construction and decoration on the cured deformation molded surface is eliminated, the molded surface compensation amount is transferred to the secondary part to be glued, compared with the method of directly repairing the reinforced wallboard molding glue joint clamp, the total compensation amount is small, the repairing risk is low, the feasibility of multiple times of compensation is realized, and the technical risk of directly repairing the high-value tool is avoided; 4) The trimming effect is good, and the transverse solidification deformation of the reinforced wallboard can be improved by additionally compensating the profile of the stringer of the reinforced wallboard, so that the trimming process has no influence on the axiality of the stringer of the wallboard and the cementing quality of the stringer.
Drawings
FIG. 1 is a schematic diagram of a theoretical model of a T-shaped reinforced wallboard used in example 1 of the present invention
FIG. 2 is a cross-sectional view of a first characteristic cross-section of a T-stiffened panel used in example 1 of the invention
FIG. 3 is a schematic diagram showing the deformation geometry of a T-shaped reinforced wallboard according to embodiment 1 of the present invention
FIG. 4 is a schematic diagram of the compensation principle of the T-stringer mold according to embodiment 1 of the present invention
FIG. 5 is a schematic diagram showing the deformation geometry of an I-shaped stiffened wall panel according to embodiment 2 of the present invention
The numbering in the figures illustrates: 1-panel skin, 2-first stringer, 3-second stringer, 4-first typical characteristic section, 5-second typical characteristic section, 6-first typical characteristic section line, 7-skin theoretical plane, 8-first typical deformation section line, 9-initial deformation section line, 10-initial repair section line, 11-theoretical section line, 12-compensation panel deformation repair section line, 13-I-stringer, 14-I-panel typical deformation section line, 15-I-panel skin theoretical plane.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to fall within the scope of the invention.
Example 1
As shown in fig. 1-4, the composite T-stiffened panel part made using the co-cementing process in this example is made from 2 cured T-stringers: the first stringer 2, the second stringer 3 and the uncured skin are formed by glue bonding and combining by an adhesive film, and the transverse bow height of the theoretical profile surface of the panel skin is 5mm.
The skin theoretical appearance surface in the T-shaped reinforced wallboard theoretical model is unfolded to form a skin theoretical plane 7, and the T-shaped reinforced wallboard theoretical model is divided into a first typical characteristic section 4 and a second typical characteristic section 5 along the transverse direction of the stringer according to key influencing factors such as the skin size, the T-shaped stringer arrangement, the structural characteristics and the like of the T-shaped reinforced wallboard made of the composite material, and the typical characteristic section and the skin theoretical plane are intersected to form a first typical characteristic section line 6 and a second typical characteristic section line. Selecting a first typical characteristic section 4, forming two intersection points with a skin theoretical appearance surface, and measuring the length L of an intersection point connecting line in a composite material reinforced wallboard theoretical model 0 The number of stringers on a section of 2 was =600 mm, a composite stiffened panel test piece containing the section was made according to a T-stiffened panel theoretical model, and the initial deformation tangent angle α of the section in this test piece was measured 0 The width of the flanges of the first stringer 2 and the second stringer 3 on the cross section is L 1 =130 mm and L 2 =120 mm, panel skin 1 thickness δ 0 =4.5 mm, the cap thicknesses of the first stringer 2 and the second stringer 3 are δ 1 =3mm and δ 2 =3.75 mm. According to L 0 、α 0 Constructing an arc line with equal diameterAs a first typical deformed section line 8. Wherein:according to k i And->The correlation of (c) yields k 1 ＝1，k 2 ＝0.95。
According to the formulaThe deformation correction angles of the two stringer compensation wall plates on the first typical characteristic section 4 are calculated as follows: θ 1 Approximately 0.13 DEG and theta 2 Approximately 0.09 deg.. Stringers θ with reference to the first representative section 4 described above i Performing profile compensation on the stringers on the second typical characteristic section 5 to obtain two stringer compensation wallboard deformation modification angles on the second typical characteristic section 5, wherein the deformation modification angles are respectively as follows: θ'. 1 And θ' 2 。
The stringer mold is trimmed to an initial trimming surface 10, a stringer test piece is manufactured, the test piece is cured, the edge strip is deformed and rebounded, the initial deformation surface 9 of the edge strip of the stringer can be compensated to a theoretical surface 11, and the self-trimming compensation angle theta of the stringer is obtained 0 =0.5°, known θ Theory of =89.5°. Using the formula The die included angle theta between the web plate and the edge strip of the first stringer 2 on the first typical characteristic section 4 can be calculated Mould 1-1 Approximately 90.07 DEG, and simultaneously obtaining a compensation wallboard deformation repair surface 12 of the first stringer 2, wherein the die included angle between the web plate and the edge strip of the second stringer 3 on the first typical characteristic section 4 is theta Mould 1-2 Approximately 90.05 °. Referring to the included angle theta between each stringer web and the cap die of the first representative feature section 4 Mould The calculation step of (a) yields a first stringer 2 and a second stringer on a second representative section 5Mould included angles of web plate and edge strip of truss 3 are respectively theta Mould 2-1 θ Mould 2-2 。
Carry-in theta Mould 1-1 θ Mould 2-1 Multi-section profile compensation of the first stringer 2 mold with θ Mould 1-2 θ Mould 2-2 The mould of the second stringer 3 is subjected to multi-section profile compensation.
According to the formulaThe theoretical angle of residual deformation of the first typical characteristic section 4 after compensation of the wall plate modification is calculated to be β=0.23°.
Example 2
As shown in fig. 5, the composite material i-shaped reinforced wallboard part manufactured by adopting the co-bonding process in the example is formed by combining 1 piece of cured type stringer 13 and an uncured skin through glue film bonding, and the transverse bow height of the theoretical profile surface of the wallboard skin is 150mm.
The skin theoretical appearance surface in the I-shaped reinforced wallboard theoretical model is unfolded to form an I-shaped wallboard skin theoretical plane 13, and the I-shaped reinforced wallboard theoretical model of the composite material is divided into 1 typical characteristic section along the transverse direction of the I-shaped stringer 13 according to key influencing factors such as the skin size of the I-shaped reinforced wallboard, the arrangement of the I-shaped stringers 13, structural characteristics and the like, wherein the typical characteristic section intersects with the I-shaped wallboard skin theoretical plane 15 to form a typical characteristic section line. The typical characteristic section and the skin theoretical appearance surface form two intersection points, and the length of the intersection point connecting line is measured to be L in the I-shaped reinforced wallboard theoretical model 0 The number of stringers on the section is 1, a composite material I-shaped reinforced wallboard test piece containing the section is manufactured according to a composite material I-shaped reinforced wallboard theoretical model, and the initial deformation tangent line included angle alpha of the section in the test piece is measured 0 The width of the edge strip of the I-shaped stringer 13 on the section is L 1 The thickness of the panel skin is delta 0 The thickness of the edge strip of the I-shaped stringer 13 is delta 1 . According to L 0 、α 0 An arc line with the same diameter is constructed and is used as a typical deformation section line 14 of the I-shaped wallboard, wherein:according to k i And->The correlation of (c) yields k 1 ＝1.05。
According to the formulaCalculating to obtain the deformation correction angle theta of the I-shaped stringer 13 compensation wallboard on the typical characteristic section 1 。
The self-repairing compensation angle theta of the I-shaped stringer 13 is obtained by manufacturing a stringer test piece 0 The theoretical included angle between the web plate and the edge strip of the known I-shaped stringer 13 is theta Theory of . Using the formulaThe die included angle theta between the web plate and the edge strip of the I-shaped stringer 13 on the typical characteristic section can be calculated Mould And can be according to theta Mould The mold of the i-stringer 13 is profile compensated.
According to the formulaCalculating the residual deformation theoretical angle of the typical characteristic section of the composite material I-shaped reinforced wallboard after repair compensation to be beta=alpha 0 -α 1 -α 2 。
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (6)
1. A profile compensation control method for a composite material reinforced wallboard is characterized in that the composite material reinforced wallboard with the transverse bow height smaller than 200mm is used for the theoretical profile surface of a wallboard skin, and the profile of a stringer part is compensated, so that the integral transverse solidification deformation of the wallboard is controlled, and the concrete steps are as follows:
1-1, expanding a skin theoretical appearance surface in a composite material reinforced wallboard theoretical model into a skin theoretical plane;
1-2 dividing a composite material reinforced wallboard theoretical model into x typical characteristic sections along the transverse direction of the stringer, wherein the typical characteristic sections intersect with a skin theoretical plane to form x typical characteristic section lines;
1-3, along the transverse direction of the stringer, randomly cutting a section in the equal thickness area of the reinforced wallboard, wherein the section and the theoretical external surface of the skin form two intersection points, and measuring the length L of the intersection point connecting line in the theoretical model of the reinforced wallboard made of the composite material 0 The number of stringers on the section is n, a composite material reinforced wallboard test piece containing the section is manufactured according to a theoretical model of the composite material reinforced wallboard, and the initial deformation tangent included angle alpha of the section in the test piece is measured 0 The width of the edge strip of any stringer cementing surface on the section is L i I=1, 2,3 …, n, panel skin thickness δ 0 The thickness of the stringer edge strip is delta i ，i＝1,2,3…,n；
1-4 according to L 0 、α 0 Constructing an arc line with the same diameter and taking the arc line as a typical deformation section line;
1-5 according to the formulaObtaining the deformation correction angle theta of the arbitrary stringer compensation wallboard i I=1, 2,3 …, n, wherein: k (k) i The deformation non-uniformity coefficient of the wallboard;
1-6 deformation modification of stringer compensation panel by an angle θ i The method is applied to the repair compensation process of the stringer mould.
2. The method of profile compensation control for a composite stiffened panel according to claim 1, wherein the panel has a deformation non-uniformity coefficient k i Is of the value of (2)In relation to, when->When k is i =1.05; when->When k is i =1; when->When k is i ＝0.95。
3. A method of profile compensation control for a composite stiffened panel according to claim 1, wherein steps 1-3 to 1-6 are repeated to provide multi-section profile compensation for stringers when the number of representative characteristic sections x > 1.
4. The method of profile compensation control for a composite stiffened panel according to claim 1, wherein the stringer mold includes a mold angle between any stringer web and a flange Wherein θ is Theory of Is the theoretical included angle theta between the stringer web and the edge strip 0 Compensating the angle for the stringer itself.
5. A method of profile compensation control for a composite stiffened panel according to claim 4, wherein the length isTruss self-repairing compensation angle theta 0 In order to compensate the included angle between the web and the edge strip after the stringer is deformed to the angle of the theoretical profile, the stringer test piece can be manufactured.
6. The method for compensating and controlling the profile of a reinforced composite wall panel according to claim 1, wherein the theoretical angle of residual deformation after deformation repair and compensation of the wall panel is
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311558303.0A CN117682087A (en) | 2023-11-21 | 2023-11-21 | Profile compensation control method for composite reinforced wallboard |
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| CN202311558303.0A CN117682087A (en) | 2023-11-21 | 2023-11-21 | Profile compensation control method for composite reinforced wallboard |
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