CN113751569A - Airplane hatch cover skin liquid filling forming method - Google Patents
Airplane hatch cover skin liquid filling forming method Download PDFInfo
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- CN113751569A CN113751569A CN202110962639.8A CN202110962639A CN113751569A CN 113751569 A CN113751569 A CN 113751569A CN 202110962639 A CN202110962639 A CN 202110962639A CN 113751569 A CN113751569 A CN 113751569A
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- blank holder
- female die
- curved surface
- hemispherical curved
- edge
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
- B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
- B21D26/021—Deforming sheet bodies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
- B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
- B21D26/021—Deforming sheet bodies
- B21D26/031—Mould construction
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D53/00—Making other particular articles
- B21D53/92—Making other particular articles other parts for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
Abstract
A process model comprises two mirror-image-symmetric aircraft hatch cover skins, a process compensation surface and an annular process edge, wherein the two mirror-image-symmetric aircraft hatch cover skins are connected by the process compensation surface to form a hemispherical curved surface, and the annular process edge is positioned at the outer edge of the hemispherical curved surface; manufacturing a female die and a blank holder according to the process model, wherein the female die comprises a central molded surface and a flange edge, a protruding annular rolling rib is arranged on the flange edge, an annular sealing groove is arranged on the blank holder, a sealing ring is embedded in the sealing groove, and the sealing groove is correspondingly matched with the rolling rib on the female die; manufacturing an unfolded plate according to the process model; during forming, the unfolded sheet is placed between the blank holder and the female die, so that the sealing groove on the blank holder is correspondingly occluded with the calendering rib on the female die, liquid is filled between the blank holder and the sheet through the liquid filling pipeline on the blank holder, and the unfolded sheet is pressed to the central profile of the female die to form a hemispherical curved surface through hydraulic pressure; and cutting the formed hemispherical curved surface into two aircraft cabin cover skin parts.
Description
Technical Field
The invention relates to a sheet metal part forming technology in the field of aircraft manufacturing, in particular to a variable-curvature part hydro-forming method for an aluminum alloy sheet, and specifically relates to a skin hydro-forming method for an aircraft hatch cover.
Background
The hydro-forming is a novel forming method for manufacturing plane sheet metal parts, which is a forming method for tightly attaching a blank to a male die (or a female die) by using high-pressure liquid in a liquid chamber to generate relative pressure, and generating fluid lubrication between the female die and the lower surface of the blank sheet metal so as to obtain high-precision parts, reduce the generation of sheet metal forming local defects caused by the traditional deep drawing and greatly improve the sheet metal forming limit. In the forming process, liquid is not only a force transmission medium, but also plays a role of a half die, and the flexible manufacturing method for realizing the sheet forming is realized by gradually coating a rigid half die (male die) or filling a die cavity (female die) by utilizing the liquidity of the liquid in a high-pressure closed environment.
In the aircraft manufacturing, the outer shape size of a cabin cover skin part of an aircraft cockpit is large, the curvature of the top surface and the front edge of the cabin cover along the course is small and smooth, the curvature of two side surfaces of the cabin cover is large and steep, the deformation degree of the top surface and the front edge is different from the deformation degree of the two side surfaces when the cabin cover part is formed, the deformation requirements of the top surface and the front edge are difficult to be simultaneously coordinated by adopting the existing sheet metal forming process method, and the serious wrinkling quality problem exists. According to analysis of main reasons for generating the forming defects of the large cabin cover skin parts of the wide and flat type variable-curvature aircraft cockpit, the method has two aspects: firstly, the plate material is suspended in the air in the cavity, the front edge and the two side surfaces have different deformation degrees due to larger curvature difference, and the material of each point has uneven flowability and is easy to wrinkle; and secondly, the semi-closed cavity part is hollow, has large quenching deformation and large resilience and is easy to generate a bulging loose edge.
Disclosure of Invention
The invention aims to provide a hydro-forming method for an aircraft cabin cover skin aiming at the defects of the existing sheet metal forming technology, so as to eliminate the forming defects of wrinkling, swelling and the like in the part forming process and provide parts meeting the requirements of design drawings.
The known design model of the aircraft cabin cover skin is characterized by comprising the following contents: 1) manufacturing a process model of the aircraft hatch cover skin according to a design model of the aircraft hatch cover skin, wherein the process model comprises two mirror-image aircraft hatch cover skins, a process compensation surface and an annular process edge, the two mirror-image aircraft hatch cover skins are connected by the process compensation surface to form a hemispherical curved surface, and the annular process edge is positioned at the outer edge of the hemispherical curved surface; 2) manufacturing a liquid filling forming die according to a process model, wherein the liquid filling forming die comprises a female die and a blank holder, the female die comprises a central profile and a flange edge, the central profile is matched with a hemispherical curved surface of the process model, the central profile is provided with an external exhaust hole, the flange edge corresponds to an annular process edge of the process model, a protruding annular rolling rib is arranged on the flange edge, the blank holder is of a flat plate structure, the blank holder is provided with a liquid filling pipeline communicated with the center of the upper surface of the blank holder, the blank holder is provided with an annular sealing groove, a sealing ring is embedded in the sealing groove, and the sealing groove is correspondingly matched with the rolling rib on the female die; 3) manufacturing an unfolded plate according to the process model; 4) during forming, the unfolded sheet is placed between the blank holder and the female die, so that the sealing groove on the blank holder is correspondingly occluded with the calendering rib on the female die, liquid is filled between the blank holder and the sheet through the liquid filling pipeline on the blank holder, and the unfolded sheet is pressed to the central profile of the female die to form a hemispherical curved surface through hydraulic pressure; 5) and cutting the formed hemispherical curved surface into two aircraft cabin cover skin parts.
The height of the rolled rib is gradually changed along with the curvature of the hemispherical curved surface in the process model, and the height of the rolled rib corresponding to the position with larger curvature of the hemispherical curved surface is lower than that of the rolled rib corresponding to the position with smaller curvature of the hemispherical curved surface.
The width of the sealing groove on the blank holder is larger than that of the rolled rib on the flange edge of the female die.
During forming, two-step progressive liquid-filling forming is adopted, the semi-spherical curved surface structure formed for the first time is quenched, then the semi-spherical curved surface structure after quenching treatment is placed between the blank holder and the female die, and liquid-filling forming is carried out to eliminate deformation and heat treatment stress of the semi-spherical curved surface structure.
The beneficial effect of this application lies in: the liquid filling forming die has simple structure and easy operation. And establishing a semi-closed hemispherical curved surface and a process model with an annular process edge for the aircraft hatch cover skin part so as to meet the structural sealing requirement of the liquid-filling forming tool. The curvature of the cabin cover skin along the top surface and the front edge of the heading cabin cover is small and smooth, the forming resistance is small, the material flow is fast and easy to wrinkle during liquid filling, the curvature of two side surfaces of the cabin cover is large and steep, the forming resistance is large, the material flow is slow and easy to pull and crack during liquid filling, the blank pressing force and the material flowability of the front edge and the two side surfaces of the cabin cover skin are controlled and balanced by using the heightening calendering ribs, the height of the part with the small curvature of the front edge of the cabin cover is high, the height of the part with the large curvature of the two side surfaces is low, and the generation of the forming wrinkling and the pull and crack of parts is effectively inhibited. The structural form of the blank holder and the inverted die of the female die is adopted, so that a large amount of liquid in the female die cavity can be naturally refluxed and recovered after liquid filling forming. And the hydro-forming is divided into two steps to be gradually formed, a quenching procedure is inserted between the two steps of forming, the bulging loose edge generated by quenching deformation of the cabin cover skin can be eliminated by utilizing the second step of hydro-forming, and finally, the qualified part meeting the technical requirements of the design and manufacture quality of the airplane is formed.
The application is described in further detail below with reference to the accompanying drawings of embodiments;
drawings
Fig. 1 is a schematic structural view of an aircraft hatch cover skin part.
FIG. 2 is a schematic view of a process model.
Fig. 3 is a schematic view of the structure of the female mold.
FIG. 4 is a schematic view of a binder ring configuration.
Fig. 5 is a schematic view of a forming and clamping structure.
FIG. 6 is a schematic view of a part being hydroformed.
The numbering in the figures illustrates: the method comprises the following steps of 1 covering a part, 2 process models, 3 process compensation surfaces, 4 annular process edges, 5 female dies, 6 central molded surfaces, 7 flange edges, 8 calendering ribs, 9 blank holders, 10 liquid filling pipelines, 11 sealing grooves, 12 sealing rings, 13 unfolding plates, 14 exhaust holes and 15 liquid.
Detailed Description
Referring to the drawings, the aircraft hatch cover skin part 1 related to the application is shown in the figures, the skin part 1 is of a circular arc-shaped variable-curvature curved-surface sheet metal structure, when in liquid-filling forming, the part with large curvature is pulled apart if the material flow is limited, and the part with small curvature is folded if the material flow is too fast.
In order to form a qualified aircraft hatch cover skin part, the method specifically comprises the following steps:
according to the design model of the aircraft hatch cover skin part 1, a process model 2 of the aircraft hatch cover skin is manufactured, wherein the process model 2 comprises two mirror-symmetrical aircraft hatch cover skin parts 1, a process compensation surface 3 and an annular process edge 4, as shown in FIG. 2. The two mirror-symmetrical aircraft cabin cover skin parts 1 are connected by the process compensation surface 3 to form a hemispherical curved surface, and the annular process edge 4 is positioned at the outer edge of the hemispherical curved surface;
the hydro-forming die is manufactured according to the process model 2, the hydro-forming die comprises a female die 5 and a blank holder 9, the female die comprises a central molded surface 6 and a flange edge 7, the central molded surface 6 is matched with the hemispherical curved surface of the process model 2, the central molded surface 6 is provided with an outward exhaust hole 14, in implementation, the exhaust hole 14 on the central molded surface 6 of the female die is preferably arranged at the position of the maximum curvature of the central molded surface 6, and the central molded surface 6 can be provided with a plurality of exhaust holes according to requirements.
The flange edge 7 around the female die 5 corresponds to the annular process edge 4 of the process model 2, a convex annular rolled rib 8 is arranged on the flange edge 7, the convex height of the rolled rib 8 gradually changes along with the curvature change of the central profile 6, and the height of the rolled rib corresponding to the position with the larger curvature of the central profile is lower than that of the rolled rib corresponding to the position with the smaller curvature of the central profile.
The blank holder 9 is of a flat plate structure, a liquid filling pipeline 10 communicated with the center of the upper surface of the blank holder is arranged on the blank holder 9, an annular sealing groove 11 is arranged on the upper surface of the blank holder 9, a sealing ring 12 is embedded in the sealing groove 11, and the sealing groove 11 is correspondingly matched with the rolling rib 8 on the female die 5; in order to ensure the sealing performance, the width of the sealing groove 11 is larger than that of the rolled rib 8 on the flange edge of the female die.
Before forming parts, manufacturing an unfolded plate 13 according to the process model 2; during forming, the blank holder 9 and the female die 5 are arranged on a liquid-filled forming device. The sealing groove 11 of the blank holder 9 is filled with a rubber sealing ring 12, and the rubber sealing ring 12 must form a complete closed loop. Placing the unfolded sheet material 13 between the blank holder 9 and the female die 5, closing the die, pressing the blank holder 9 and the female die 5 tightly, enabling the sealing groove 11 on the blank holder 9 to be correspondingly occluded with the calendering rib 8 on the female die, filling liquid between the blank holder 9 and the unfolded sheet material 13 through the liquid filling pipeline 10 on the blank holder 9, and when the blank holder 9 and the female die 5 are pressed tightly, forming a closed cavity by the blank holder 9, the unfolded sheet material 13 and the rubber sealing ring 12. High-pressure liquid 15 is gradually filled between the blank holder 9 and the unfolded sheet 13 through a supercharger and liquid filling pipeline 10, along with the continuous injection of the high-pressure liquid 15, air in the cavity of the female die 5 is exhausted out of the die along the female die exhaust hole 14, and the unfolded sheet 13 gradually expands, deforms and covers the central molded surface 6 of the female die 5.
In the liquid filling process, the blank holder force and the material flow of each point in the front edge area and the two side surface areas of the cabin cover skin part 1 are adjusted and balanced through the variable-height rolling ribs 8, and the wrinkling and the tensile crack of the suspended area in the forming process of the unfolded plate 13 are inhibited.
The unfolded plate 13 is pressed to the central molded surface 6 of the female die 5 to form a hemispherical curved surface by hydraulic pressure, in order to improve the forming quality of the skin part, two-step liquid filling forming is preferably adopted to eliminate the bulging generated by the forming of the skin part 1 in the implementation, namely, after the first forming, the formed hemispherical curved surface structure is separated from a forming die to be quenched, then the quenched hemispherical curved surface structure is placed between the blank holder 9 and the female die 5 for the second time, and the liquid filling forming is repeatedly carried out to eliminate the deformation and the heat treatment stress of the hemispherical curved surface structure.
And finally, cutting the formed hemispherical curved surface into two aircraft cabin cover skin parts.
The utility model provides a covering part 1 is along course cabin cover top surface, the less mild of front edge camber, the shaping resistance is little, the material flow is easy to wrinkle fast during the topping up, consequently, it is higher relatively to need the calendering muscle height that corresponds, the speed of restriction material flow, prevent wrinkling, and covering part 1 is great precipitous along the camber of course cabin cover both sides face, the shaping resistance is big, the material flow is easy to the stretch-breaking slowly during the topping up, consequently, it is lower relatively to need the calendering muscle height that corresponds, accelerate the speed that the material flows, prevent the stretch-breaking, so this application utilizes the calendering muscle that becomes high to adjust and control balanced cabin cover covering front edge and both sides face each point blank pressing power and material mobility.
It should be noted that, because the large-scale cabin cover skin of the wide and flat aircraft is an open part, the process supplementary modification needs to be performed on the open part of the skin part 1, and then the semi-closed shape process model is symmetrically established to form a semi-closed structure, so that the hydro-forming can be smoothly performed. In order to eliminate the edge bulging loose edge of the part after the hydro-forming, the contour of the circumference of the skin part 1 after the symmetric compensation needs to be extended to form a bell-mouth-shaped annular technical edge 4 so as to keep the shape and the size of the molded surface of the skin part stable.
Claims (5)
1. The known design model of the aircraft cabin cover skin is characterized by comprising the following contents: 1) manufacturing a process model of the aircraft hatch cover skin according to a design model of the aircraft hatch cover skin, wherein the process model comprises two mirror-image aircraft hatch cover skins, a process compensation surface and an annular process edge, the two mirror-image aircraft hatch cover skins are connected by the process compensation surface to form a hemispherical curved surface, and the annular process edge is positioned at the outer edge of the hemispherical curved surface; 2) manufacturing a liquid filling forming die according to a process model, wherein the liquid filling forming die comprises a female die and a blank holder, the female die comprises a central profile and a flange edge, the central profile is matched with a hemispherical curved surface of the process model, the central profile is provided with an external exhaust hole, the flange edge corresponds to an annular process edge of the process model, a protruding annular rolling rib is arranged on the flange edge, the blank holder is of a flat plate structure, the blank holder is provided with a liquid filling pipeline communicated with the center of the upper surface of the blank holder, the blank holder is provided with an annular sealing groove, a sealing ring is embedded in the sealing groove, and the sealing groove is correspondingly matched with the rolling rib on the female die; 3) manufacturing an unfolded plate according to the process model; 4) during forming, the unfolded sheet is placed between the blank holder and the female die, so that the sealing groove on the blank holder is correspondingly occluded with the calendering rib on the female die, liquid is filled between the blank holder and the sheet through the liquid filling pipeline on the blank holder, and the unfolded sheet is pressed to the central profile of the female die to form a hemispherical curved surface through hydraulic pressure; 5) and cutting the formed hemispherical curved surface into two aircraft cabin cover skin parts.
2. The aircraft hatch skin hydroforming method according to claim 1, wherein the height of said ribs varies progressively with the curvature of the central profile, the height of the ribs corresponding to the locations of greater curvature of the central profile being less than the height of the ribs corresponding to the locations of lesser curvature of the central profile.
3. The aircraft hatch skin hydroforming method according to claim 1 or 2, wherein the width of the sealing groove on the binder ring is greater than the width of the bead on the flange of the female die.
4. The aircraft hatch cover skin hydro-forming method according to claim 1, characterized in that after the step 4) is completed, the formed hemispherical curved surface structure is quenched, then the quenched hemispherical curved surface structure is placed between the blank holder and the female die, and the step 4) is repeated to carry out hydro-forming again, so that the deformation and the heat treatment stress of the hemispherical curved surface structure are eliminated.
5. The method of hydroforming an aircraft hatch skin according to claim 1 wherein the vent holes in the central profile of the female mold are positioned at the locations of maximum curvature of the central profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110962639.8A CN113751569A (en) | 2021-08-20 | 2021-08-20 | Airplane hatch cover skin liquid filling forming method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110962639.8A CN113751569A (en) | 2021-08-20 | 2021-08-20 | Airplane hatch cover skin liquid filling forming method |
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| CN113751569A true CN113751569A (en) | 2021-12-07 |
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| CN202110962639.8A Pending CN113751569A (en) | 2021-08-20 | 2021-08-20 | Airplane hatch cover skin liquid filling forming method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114425582A (en) * | 2022-01-28 | 2022-05-03 | 东北林业大学 | Internal high-pressure forming device and method for pipe with flange edge |
| CN117483533A (en) * | 2024-01-03 | 2024-02-02 | 天津天锻航空科技有限公司 | Forming method of airplane oil transportation half pipe parts |
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2021
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| CN114425582A (en) * | 2022-01-28 | 2022-05-03 | 东北林业大学 | Internal high-pressure forming device and method for pipe with flange edge |
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| CN117483533A (en) * | 2024-01-03 | 2024-02-02 | 天津天锻航空科技有限公司 | Forming method of airplane oil transportation half pipe parts |
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Application publication date: 20211207 |