CN114998526A - Skin process net size unfolding method based on error compensation - Google Patents
Skin process net size unfolding method based on error compensation Download PDFInfo
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- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
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Abstract
The invention aims to provide an error compensation-based skin process net size unfolding method, which comprises the following steps of: determining the manufacturing tolerance delta of an assembly fixture f Determining the manufacturing error delta of the skeleton profile w Determining the assembly error delta in the assembly process of the framework a (ii) a Including assembly error delta of frame parts a1 Assembling error delta of truss type parts a2 (ii) a The parameters of the size of the unfolded outer contour of the skin containing error compensation are calculated according to the error transfer model, the skin unfolded by adopting an error compensation mechanism can directly guide the margin-free blanking of skin parts in the development stage, and the skin can be directly assembled according to the net size of the process in the assembly stage, so that the process of removing the margin by coordinating the skin is eliminated, and the assembly efficiency and the material utilization rate of the skin are improved. The skin which is unfolded after error compensation is adopted, the assembly stage can be directly applied to product development and production to improve the utilization rate of raw materials, the formula is simpler, and a secondary development set can be adoptedAnd (4) forming into three-dimensional software.
Description
Technical Field
The invention belongs to the field of aerospace digital manufacturing, and relates to an error compensation-based unfolding method for net dimension of skin process.
Background
Skin-like parts have numerous applications in the field of aerospace manufacturing, such as the cabin skin of launch vehicles and spacecraft. The skin parts belong to typical sheet metal parts, and the blanking size of the flat plate state of the skin parts is mainly calculated according to a theoretical assembly model of a cabin section framework and a theory that a neutral layer is unchanged.
At present, the net size of the skin process in the assembly stage is often different from the size of the theoretical model expansion under the influence of multiple factors such as the manufacturing error of the cabin assembly jig, the manufacturing error of the cabin skeleton, the assembly error of the cabin skeleton, the deformation of the skeleton in the cabin assembly process and the like. In the development stage, more allowance is reserved in the skin blanking stage, and in the to-be-assembled stage, the allowance is removed according to the actual shape of the framework in a coordinated mode, so that the net size of the skin process in the assembly stage is determined. The coordination method determines that the net size of the skin process is equivalent to secondary blanking, so that the assembly efficiency of the skin is greatly reduced. For batch products with stable states, the process net size of the skin can also be determined by an empirical method. Empirical methods are based on theoretical expansions to compensate for the proper empirical margin determination. However, the accumulated margin of empirical data often requires a long lead time. In addition, the cabin sections in the aerospace manufacturing field are mostly in multiple varieties and small batches, and the iterative modification speed of products is high. Once the product is modified, the experience data accumulated in the early stage cannot be directly transplanted and applied, and the effectiveness of guiding development and production is poor. Therefore, the coordination method and the experience method for determining the net size of the skin process are low in efficiency, cannot meet the development requirement of current model high-density emission, and are more unfavorable for digital manufacturing of aerospace products.
At present, the expansion calculation of three-dimensional modeling software such as Creo (PRO/E), CATIA (computer-aided three-dimensional interactive application) and the like on skin parts is mainly based on the expansion of a neutral layer of a part theoretical model, the influence of various error sources existing in an assembly stage on the net size of a skin process is not considered, the expanded contour is a theoretical outer contour, and the expansion calculation cannot be directly applied to the development and production in the assembly stage.
Therefore, if the source of the skin appearance error in the assembling process is quantized and compensated, the skin process net size can be determined at the initial development stage and the process design stage, so that the digital manufacturing of skin parts in the aerospace field is really realized, and the requirement of developing aerospace products in a short period is met.
Disclosure of Invention
The invention aims to provide a skin process net size unfolding method based on error compensation so as to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme:
an error compensation based skin process net size unfolding method comprises the following steps:
determining the manufacturing tolerance delta of an assembly fixture f ；
Determining the manufacturing error delta of the skeleton profile w
Determining an assembly error delta in a skeleton assembly process a (ii) a Including assembly error delta of frame parts a1 Assembling error delta of truss type parts a2 ；
And calculating parameters of the size of the unfolded outer contour of the skin with the error compensation according to the error transfer model.
As a further improvement of the invention: the method for calculating the parameters of the size of the unfolded outer contour of the skin with the error compensation according to the error transfer model comprises the following steps: the skin is a barrel-shaped cabin section skin,
the rectangular length l of the skin of the barrel-shaped cabin after being unfolded is defined by the following formula:
in the formula, h is the width of a rectangular outer contour of the cylindrical cabin section skin after being unfolded;
r is the theoretical radius of the skin on the neutral layer at the upper end or the lower end of the cylindrical cabin section;
theta is the included angle of the circle centers of the lower skin covering the cabin skeleton of the theoretical model.
As a further improvement of the invention: the method for calculating the parameters of the size of the unfolded outer contour of the skin with the error compensation according to the error transfer model comprises the following steps: the skin is a conical cabin section skin,
the upper radius of the fan-shaped outer contour of the conical cabin section skin after being unfolded is R x Is defined by the following equation:
the lower radius R of the fan-shaped outer contour of the unfolded conical cabin section skin y Is defined by the following formula:
the sector central angle gamma of the unfolded conical cabin section skin is defined by the following formula:
in the formula:
r a the theoretical radius of the skin on the neutral layer at the upper end of the conical section cabin section;
r b the theoretical radius of the skin on a neutral layer at the lower end of the conical section cabin section;
alpha is the half cone angle of the conical cabin body;
beta is the included angle of the circle centers of the cabin skeletons covered by the skin under the theoretical model.
Compared with the prior art, the invention has the beneficial effects that:
the skin process net size unfolding method based on error compensation realizes skin process net size assembly, the skin unfolded by the error compensation mechanism can directly guide the margin-free blanking of skin parts in the development stage, and the skin can be directly assembled according to the process net size in the assembly stage, so that the skin coordination allowance removing process is omitted, and the assembly efficiency and the material utilization rate of the skin are improved. The skin which is unfolded after error compensation is adopted, the assembling stage can be directly applied to product development and production to improve the utilization rate of raw materials, and the formula is simpler and can be integrated into three-dimensional software through secondary development.
Drawings
FIG. 1 is a flow chart of a skin process net size deployment method based on error compensation;
FIG. 2 is a schematic view of a barrel bay in a theoretical assembled condition and associated parameters;
FIG. 3 is a fan-shaped state of blanking after flattening of the cylindrical cabin section skin and its profile description parameters;
FIG. 4 is a schematic view of a theoretical assembled state of a cone nacelle section and related parameters;
FIG. 5 is a fan-shaped state of blanking after the conical cabin section skin is flattened and profile description parameters thereof;
wherein: 1-schematic skin in theoretical state; 2-frame type part schematic diagram; 3-stringer part schematic; 4-maximum outer contour of skin with error compensation.
Detailed Description
To explain technical contents, structural features, and objects and effects of the technical solutions in detail, the following detailed description is given with reference to the accompanying drawings in conjunction with the embodiments.
Example one
Referring to fig. 1 to 3, in the present embodiment, an error compensation based skin process net size unfolding method is applied to calculating parameters related to an unfolded outer contour of a cylindrical cabin skin, and includes the following steps:
s1, determining the manufacturing error delta of the barrel cabin section assembling jig f Mainly the manufacturing error of the positioning element of the fixture where the upper frame (or the lower frame) of the skin is lapped is disclosed;
s2, determining the manufacturing error delta of the shape of the cylindrical cabin section framework w Mainly the manufacturing error of the upper frame (or the lower frame) assembled by the skin;
s3, determining an assembly error delta in the assembly process of the barrel cabin section framework a In which the frame-like parts are assembled into a complete frameAssembly error in stroke is delta a1 (ii) a The assembly error of the stringer parts in the process of assembling the framework is delta a2 ；
S4 according to the error delta determined in the steps S1-S3 f 、δ w And delta a Wherein δ a Including delta a1 And delta a2 Calculating the rectangular length l of the unfolded skin with the error compensation in the barrel-shaped cabin section according to the error transfer model, and recording the maximum rectangular outer contour width of the unfolded skin in the barrel-shaped cabin section as h, so that the rectangular length l of the unfolded skin with the error compensation in the barrel-shaped cabin section is calculated according to the following formula:
wherein:
r is the theoretical radius of the skin on the neutral layer at the upper end (or the lower end) of the cylindrical cabin section;
theta is the included angle of the circle centers of the lower skin covering the cabin skeleton of the theoretical model.
It needs to be reminded that the error source of the maximum rectangular outer contour width h after the skin is unfolded is mainly the errors of the height of the upper frame positioning plate and the lower frame positioning plate of the jig and the thickness of the product, the error is small, the development analysis is not needed, and h is only the theoretical value of the design model in the engineering application.
Aiming at the steps S1-S4, specifically, a skin unfolding case with error compensation in a cylindrical cabin section is known, the theoretical radius r of a neutral layer of the skin at the upper end of the cylindrical cabin section is 1125mm, the included angle theta of the center of a circle of a skeleton of a cabin covered by the skin under a theoretical model is 90 degrees, and the skin assembly height h is 1000mm, the method comprises the following steps:
s1, manufacturing error delta of positioning element of skin assembly frame is determined f : the cabin assembly type frame is positioned by a positioning plate, the manufacturing error of the positioning plate is according to GB/T1804-m, the linear dimension tolerance of the positioning plate is 1.2mm, the installation coaxiality error of the positioning plate is 0.3mm, and the sum of the two terms is delta f ＝1.5mm；
S2, manufacturing error delta of skin assembly frame is determined w : the assembly frame is a section bar half frame, according to QJ 262A-2005 determination of roundness linear dimension tolerance as delta w ＝1.5mm；
S3, determining the assembly error delta in the assembly process of the framework a1 : if the upper frame and the lower frame adopt the assembly error in the process of assembling the section bar half frames into the whole frame, the maximum single gap in the process of splicing the two half frames is 1mm, and the difference is converted into the difference of the theoretical radius subtracted from the corresponding radius in the state of the maximum gap, namely delta a1 0.3 mm; determining assembly error delta in process of assembling stringer parts into framework a2 Is 0.5 mm;
s4: according to the error delta determined in the steps S1-S3 f 、δ w And delta a Wherein δ a Including delta a1 And delta a2 Substituting into a calculation formula of the rectangular length l of the unfolded skin with error compensation in the cylindrical cabin section:
i.e. l 1773.33 mm.
Example two
Referring to fig. 1, 4 and 5, in the present embodiment, an error compensation based skin process net size unfolding method is applied to calculating parameters related to an unfolded outer contour of a cone-shaped cabin skin, and includes the following steps:
s1, determining the manufacturing error delta of the conical cabin section assembling jig f Mainly the manufacturing error of the positioning element of the fixture where the upper frame (or the lower frame) of the skin is lapped is disclosed;
s2, determining the manufacturing error delta of the shape of the conical cabin section framework w Mainly the manufacturing error of the upper frame (or the lower frame) assembled by the skin;
s3, determining an assembly error delta in the assembly process of the cone cabin section framework a The assembling error of the middle frame parts in the whole frame assembling process is delta a1 (ii) a The assembly error of the stringer parts in the process of assembling the framework is delta a2 ；
S4 according to the error delta determined in the steps S1-S3 f 、δ w And delta a Wherein δ a Including delta a1 And delta a2 Calculating the key parameter R of the maximum outer contour of the skin with the error compensation in the conical cabin section according to the error transfer model x 、R y And gamma is calculated as follows:
wherein:
r a the theoretical radius of the skin on the neutral layer at the upper end of the conical section cabin section;
r b the theoretical radius of the skin at the neutral layer at the lower end of the conical section cabin section;
alpha is the half cone angle of the conical cabin body;
beta is the included angle of the circle centers of the cabin skeletons covered by the skin under the theoretical model.
Aiming at the steps S1-S4, specifically, a skin unfolding case with error compensation in a cone-shaped cabin section is known, and the theoretical radius r of a neutral layer of the skin at the upper end of the cone-shaped cabin section is known a 1125mm, the theoretical radius r of the lower neutral layer b 1525mm, the included angle beta of the circle center of the skeleton of the cabin covered by the skin under the theoretical model is 120 degrees, alpha is the half cone angle of the conical cabin body is 15 degrees, and the method comprises the following steps:
s1, manufacturing error delta of positioning element of skin assembly frame is determined f : the cabin assembly type frame is positioned by a positioning plate, and the manufacturing error of the positioning plate is in accordance with GB/T1804-m. Therefore, the linear dimension tolerance of the positioning plate is 1.2mm, the mounting coaxiality error of the positioning plate is 0.3mm, and the sum of the two terms is delta f ＝1.5mm；
S2, manufacturing error delta of skin assembly frame is determined w (ii) a The assembly frame adopts a section bar half frame, and the roundness linear dimension tolerance is determined according to QJ 262A-2005Is delta w ＝1.5mm；
S3, determining the assembly error delta in the assembly process of the framework a1 : if the upper frame and the lower frame adopt the assembly error in the process of assembling the section bar half frames into the whole frame, the maximum single gap in the process of splicing the two half frames is 1mm, and the difference is converted into the difference of the theoretical radius subtracted from the corresponding radius in the state of the maximum gap, namely delta a1 0.3 mm; determining assembly error delta in process of assembling stringer parts into framework a2 Is 0.5 mm;
s4: according to the error delta determined in the steps S1-S3 f 、δ w And delta a Wherein δ a Including delta a1 And delta a2 Substituting into the key parameter R of the maximum outer contour of the skin with error compensation in the conical cabin section x 、R y The calculation formula of γ is as follows:
namely R x ＝4359.42mm；R y ＝5904.90mm；γ＝31.07°。
The skin process net size unfolding method based on the error compensation realizes skin process net size assembly, the skin unfolded by the error compensation mechanism can directly guide the zero-allowance blanking of skin parts in the development stage, and the skin can be directly assembled according to the process net size in the assembly stage, so that the skin coordination allowance removing process is omitted, and the assembly efficiency and the material utilization rate of the skin are improved. The skin which is unfolded after error compensation is adopted, the assembling stage can be directly applied to product development and production to improve the utilization rate of raw materials, and the formula is simpler and can be integrated into three-dimensional software through secondary development.
Claims (3)
1. An error compensation based skin process net size unfolding method is characterized by comprising the following steps: the method comprises the following steps:
determining the manufacturing tolerance delta of an assembly fixture f ；
Determining manufacturing tolerances delta of skeleton profile w
Determining an assembly error delta in a skeleton assembly process a (ii) a Including assembly error delta of frame parts a1 Assembling error delta of truss type parts a2 ；
And calculating parameters of the size of the unfolded outer contour of the skin with error compensation according to the error transfer model.
2. The skin process net size unfolding method based on error compensation is characterized by comprising the following steps of: the method for calculating the parameters of the size of the unfolded outer contour of the skin with the error compensation according to the error transfer model comprises the following steps: the skin is a barrel-shaped cabin section skin,
the rectangular length l of the skin of the barrel-shaped cabin after being unfolded is defined by the following formula:
in the formula, h is the width of a rectangular outer contour of the cylindrical cabin section skin after being unfolded;
r is the theoretical radius of the skin on the neutral layer at the upper end or the lower end of the cylindrical cabin section;
theta is the included angle of the circle centers of the lower skin covering the cabin skeleton of the theoretical model.
3. The skin process net size unfolding method based on error compensation is characterized by comprising the following steps of: the method for calculating the parameters of the size of the unfolded outer contour of the skin with the error compensation according to the error transfer model comprises the following steps: the skin is a conical cabin section skin,
the upper radius of the fan-shaped outer contour of the unfolded conical cabin section skin is R x Is defined by the following equation:
the lower radius R of the fan-shaped outer contour of the unfolded conical cabin section skin y Is defined by the following formula:
the sector central angle gamma of the unfolded conical cabin section skin is defined by the following formula:
in the formula:
r a the theoretical radius of the skin on the neutral layer at the upper end of the conical section cabin section;
r b the theoretical radius of the skin on a neutral layer at the lower end of the conical section cabin section;
alpha is the half cone angle of the conical cabin body;
beta is the included angle of the circle centers of the cabin skeletons covered by the skin under the theoretical model.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104972282A (en) * | 2015-07-15 | 2015-10-14 | 江西洪都航空工业集团有限责任公司 | Method for machining aircraft skin part |
| CN110116510A (en) * | 2019-05-28 | 2019-08-13 | 湖北三江航天万峰科技发展有限公司 | A kind of integrated molding method of composite material cabin |
| CN112829337A (en) * | 2020-12-31 | 2021-05-25 | 湖北三江航天红阳机电有限公司 | Cabin net size forming method, forming tool and cabin |
| CN113857795A (en) * | 2021-11-11 | 2021-12-31 | 湖北三江航天红阳机电有限公司 | Cabin section machining method |
| CN114313300A (en) * | 2022-02-22 | 2022-04-12 | 成都飞机工业（集团）有限责任公司 | Method for predicting and improving installation qualification rate of aircraft part and aircraft surface connecting piece |
-
2022
- 2022-06-23 CN CN202210714867.8A patent/CN114998526B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104972282A (en) * | 2015-07-15 | 2015-10-14 | 江西洪都航空工业集团有限责任公司 | Method for machining aircraft skin part |
| CN110116510A (en) * | 2019-05-28 | 2019-08-13 | 湖北三江航天万峰科技发展有限公司 | A kind of integrated molding method of composite material cabin |
| CN112829337A (en) * | 2020-12-31 | 2021-05-25 | 湖北三江航天红阳机电有限公司 | Cabin net size forming method, forming tool and cabin |
| CN113857795A (en) * | 2021-11-11 | 2021-12-31 | 湖北三江航天红阳机电有限公司 | Cabin section machining method |
| CN114313300A (en) * | 2022-02-22 | 2022-04-12 | 成都飞机工业（集团）有限责任公司 | Method for predicting and improving installation qualification rate of aircraft part and aircraft surface connecting piece |
Non-Patent Citations (2)
| Title |
|---|
| 刘宇;龚集响;皮兴来;: "一种阵列式柔性夹具的工件定位方法", 机械科学与技术, no. 04, 16 July 2019 (2019-07-16) * |
| 申丽娟;杨军;赵宇;: "基于方差传递模型的飞机蒙皮拉形工艺稳健设计", 机械工程学报, no. 01, 5 January 2011 (2011-01-05) * |
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