Airplane cabin door sheet metal part forming device and method

Abstract

The invention provides an aircraft cabin door sheet metal part forming device and method.The device comprises a bottom plate and a top plate, a plurality of supporting columns are fixedly connected between the bottom plate and the top plate, a lower die is fixedly connected to the upper side of the bottom plate, a female die groove is formed in the upper side of the lower die, and a sound collecting device is arranged on the bottom side of the female die groove; an electric telescopic rod is fixedly connected to the bottom side wall of the top plate, an upper mold is fixedly connected to the bottom end of the electric telescopic rod, a convex mold block is fixedly connected to the bottom side wall of the upper mold, the convex mold block and the lower mold are both made of titanium alloy materials, and the convex mold block is matched with the concave mold groove in shape; a temperature sensor and a pressure sensor are arranged on the bottom side wall of the convex module; the control coefficient CY is constructed, the output power and the extension speed of the electric telescopic rod are dynamically adjusted in the stamping process, the output power of the electric heating plate is adjusted and controlled, then the stamping forming quality of the aircraft cabin door sheet metal part is improved, and cracks are avoided.

Description

Technical Field

[0001] The present application belongs to the field of aviation manufacturing technology, and specifically relates to a device and method for forming sheet metal parts for aircraft cabin doors. Background Art

[0002] Aircraft door sheet metal parts have the characteristics of large size, high precision, high surface quality and high fatigue resistance. In the manufacture of aircraft door sheet metal parts, they are generally prepared by metal sheet stamping. However, since the bottom of the door sheet metal parts has a small R step, it is difficult to control the stamping force and speed during stamping and bending, which easily causes the door sheet metal parts to break when bent. Therefore, a forming device and a forming method for aircraft door sheet metal parts are proposed. Summary of the invention

[0003] Purpose of the invention: Provide a forming device and a forming method for sheet metal parts of aircraft cabin doors to solve the problems raised in the above-mentioned background technology.

[0004] In a first aspect, the present application provides a sheet metal parts forming device for an aircraft cabin door, the device comprising a bottom plate 10 and a top plate 5;

[0005] A plurality of support columns 11 are fixedly connected between the bottom plate 10 and the top plate 5, a lower mold 6 is fixedly connected to the upper side of the bottom plate 10, a die groove 7 is provided on the upper side of the lower mold 6, a sound collection device is provided on the bottom side of the die groove 7, an electric telescopic rod 3 is fixedly connected to the bottom side wall of the top plate 5, an upper mold 1 is fixedly connected to the bottom end of the electric telescopic rod 3, a convex module 2 is fixedly connected to the bottom side wall of the upper mold 1, the convex module 2 and the lower mold 6 are both made of titanium alloy, the shape of the convex module 2 is matched with the die groove 7, a temperature sensor 13 and a pressure sensor 14 are provided on the bottom side wall of the convex module 2, and an electric heating plate 4 is provided inside the convex module 2.

[0006] Preferably, the sound collection device comprises an installation cavity 9, in which an acoustic emission detector 8 is installed, and a sound guide channel 12 is provided between the installation cavity 9 and the die groove 7, and the sound guide channel 12 is arranged in a cone shape.

[0007] Preferably, the device further comprises a control mechanism, which is used to improve the stamping quality of the sheet metal parts of the aircraft cabin door by regulating the output power and extension speed of the electric telescopic rod 3 and the output power of the electric heating plate 4.

[0008] Preferably, the control mechanism includes a control module, a detection module, and a processing module;

[0009] The control module is connected with the electric telescopic rod 3 and the electric heating plate 4 by electrical signals;

[0010] The detection module includes a temperature detection unit for detecting the stamping temperature of the surface of the convex module 2, a pressure detection unit for detecting the stamping intensity of the convex module 2, and a sound intensity detection unit for detecting the sound intensity of the bending deformation of the sheet metal parts during the stamping process of the convex module 2;

[0011] The processing module includes an evaluation unit and a judgment unit.

[0012] Preferably, the temperature detection unit is a temperature sensor 13 , and the pressure detection unit is a pressure sensor 14 .

[0013] Preferably, the sound intensity detection unit is an acoustic emission detector 8; the acoustic emission detector 8 is used to collect, analyze and process the sound signals generated by the bending deformation of the cabin door sheet metal parts during the stamping process, so as to obtain the sound intensity of the bending deformation of the sheet metal parts.

[0014] In a second aspect, the present application also provides a method for forming a sheet metal part of an aircraft cabin door, the method specifically comprising the following steps:

[0015] S1, placing the sheet metal part of the aircraft cabin door on the surface of the downward mold 6 and covering the die groove 7;

[0016] S2, control the electric heating plate 4 to start heating the male module 2, and then control the electric telescopic rod 3 to extend. The extension of the electric telescopic rod 3 will drive the male module 2 to descend through the upper mold 1 to extrude the sheet metal parts of the aircraft cabin door into the female die groove 7 for stamping;

[0017] S3, during the stamping process, the stamping temperature of the male module 2, the stamping intensity of the male module 2, and the sound intensity of the bending deformation of the sheet metal parts of the aircraft cabin door are respectively detected by the temperature detection unit, the pressure detection unit, and the sound intensity detection unit in the detection module to form temperature T, pressure N, and sound intensity R, and transmit them to the evaluation unit for evaluation. If at least one value among the temperature T, pressure N, and sound intensity R exceeds the range of the corresponding first preset threshold value, the value is adjusted to be within the range of the first preset threshold value;

[0018] S4. Summarize the acquired temperature T, pressure N, and sound intensity R to form detection condition information, build a data model and optimize and train it, perform regression analysis on the acquired temperature T, pressure N, and sound intensity R through analysis software, obtain the influence of temperature T, pressure N, and sound intensity R on the stamping quality of sheet metal parts of aircraft cabin doors, and output the temperature influence factor At, pressure influence factor An, and sound intensity influence factor Ar;

[0019] S5. The evaluation unit obtains the temperature T, pressure N, and sound intensity R, and performs dimensionless processing on them, and associates them to form a control coefficient CY. The association model is:

[0020]

[0021] Among them, At represents the temperature influence factor; An represents the pressure influence factor; Ar represents the solidification influence factor; L represents the metal elastic modulus of the sheet metal part of the aircraft cabin door;

[0022] S6. The acquired control coefficient CY is transmitted to the judgment unit for comparison with a preset second preset threshold value. If the control coefficient CY is not within the range of the second preset threshold value, a corresponding control instruction is generated to control the output power and extension speed of the electric telescopic rod 3 and the output power of the electric heating plate 4. At the same time, the control coefficient CY of the forming device is evaluated until the control coefficient CY is within the second preset threshold value, thereby ensuring the stamping quality of the sheet metal parts of the aircraft cabin door.

[0023] Preferably, when the sheet metal component of the aircraft door is made of aluminum alloy, the metal elastic modulus L is 70 GPa.

[0024] This application has the following technical effects:

[0025] The present invention is reasonably designed. By constructing the control coefficient CY, the output power and the extension speed of the electric telescopic rod and the output power of the electric heating plate can be dynamically adjusted during the stamping process, thereby improving the stamping quality of the sheet metal parts of the aircraft cabin door and avoiding the generation of cracks. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 A schematic diagram of the three-dimensional structure of a sheet metal parts forming device for an aircraft cabin door proposed by the present invention;

[0027] Figure 2 This is a front cross-sectional structural schematic diagram of a sheet metal parts forming device for aircraft cabin doors proposed by the present invention;

[0028] Figure 3 It is a front cross-sectional structural schematic diagram of the convex module and the lower mold in the present invention;

[0029] Among them: 1. upper mold; 2. convex module; 3. electric telescopic rod; 4. electric heating plate; 5. top plate; 6. lower mold; 7. concave mold groove; 8. acoustic emission detector; 9. installation cavity; 10. bottom plate; 11. support column; 12. sound guide channel; 13. temperature sensor; 14. pressure sensor. DETAILED DESCRIPTION

[0030] The present invention discloses a sheet metal parts forming device for aircraft cabin door, comprising a bottom plate and a top plate, a plurality of support columns are fixedly connected between the bottom plate and the top plate, a lower mold is fixedly connected to the upper side of the bottom plate, a concave mold groove is provided on the upper side of the lower mold, a sound collection device is provided on the bottom side of the concave mold groove, an electric telescopic rod is fixedly connected to the bottom side wall of the top plate, an upper mold is fixedly connected to the bottom end of the electric telescopic rod, a convex module is fixedly connected to the bottom side wall of the upper mold, the convex module and the bottom mold are both made of titanium alloy, the shape of the convex module is adapted to the concave mold groove, and a temperature sensor and a pressure sensor are provided on the bottom side wall of the convex module. The present invention can dynamically adjust the output power and elongation speed of the electric telescopic rod and the output power of the electric heating plate during the stamping process by constructing a control coefficient CY, thereby improving the stamping quality of the sheet metal parts of the aircraft cabin door and avoiding cracks.

[0031] The present application provides a sheet metal parts forming device for aircraft cabin doors, comprising a bottom plate and a top plate, wherein a plurality of support columns are fixedly connected between the bottom plate and the top plate, a lower mold is fixedly connected to the upper side of the bottom plate, a die groove is provided on the upper side of the lower mold, a sound collection device is provided on the bottom side of the die groove, an electric telescopic rod is fixedly connected to the bottom side wall of the top plate, an upper mold is fixedly connected to the bottom end of the electric telescopic rod, a convex module is fixedly connected to the bottom side wall of the upper mold, the convex module and the lower mold are both made of titanium alloy, the shape of the convex module is matched with the die groove, a temperature sensor and a pressure sensor are provided on the bottom side wall of the convex module, and an electric heating plate is provided inside the convex module.

[0032] Preferably, the sound collection device comprises an installation cavity, in which an acoustic emission detector is installed, and a sound guide channel is provided between the installation cavity and the die groove, and the sound guide channel is arranged in a cone shape.

[0033] Preferably, a control mechanism is further included, wherein the control mechanism is used to improve the stamping quality of the sheet metal parts of the aircraft cabin door by regulating the output power and extension speed of the electric telescopic rod and the output power of the electric heating plate.

[0034] Preferably, the control mechanism includes a control module, a detection module, and a processing module;

[0035] The control module is connected with the electric telescopic rod and the electric heating plate by electrical signals;

[0036] The detection module includes a temperature detection unit for detecting the stamping temperature of the convex module surface, a pressure detection unit for detecting the stamping intensity of the convex module, and a sound intensity detection unit for detecting the sound intensity of the bending deformation of the sheet metal parts during the stamping process of the convex module;

[0037] The processing module includes an evaluation unit and a judgment unit.

[0038] Preferably, the temperature detection unit is a temperature sensor, and the pressure detection unit is a pressure sensor.

[0039] Preferably, the sound intensity detection unit is an acoustic emission detector; the acoustic emission detector is used to collect, analyze and process the sound signals generated by the bending deformation of the cabin door sheet metal parts during the stamping process, so as to obtain the sound intensity of the bending deformation of the sheet metal parts.

[0040] In other embodiments of the present application, a forming method of a sheet metal part forming device for an aircraft cabin door proposed by the present invention uses any one of the sheet metal part forming devices for an aircraft cabin door described above, and the forming method specifically comprises the following steps:

[0041] S1. Place the sheet metal part of the aircraft cabin door on the surface of the downward mold and cover the die groove;

[0042] S2, control the electric heating plate to start heating the male module, and then control the electric telescopic rod to extend. The extension of the electric telescopic rod will drive the male module to descend through the upper die to extrude the sheet metal parts of the aircraft cabin door into the female die groove for stamping;

[0043] S3, during the stamping process, the stamping temperature of the convex module, the stamping intensity of the convex module, and the sound intensity of the bending deformation of the sheet metal parts of the aircraft cabin door are respectively detected by the temperature detection unit, the pressure detection unit and the sound intensity detection unit in the detection module to form temperature T, pressure N, and sound intensity R, and transmit them to the evaluation unit for evaluation. If at least one of them exceeds the corresponding first preset threshold, judgment information is formed; the range of the first preset threshold is obtained based on experience;

[0044] S4. Summarize the acquired temperature T, pressure N, and sound intensity R to form detection condition information, build a data model and optimize and train it, perform regression analysis on the acquired temperature T, pressure N, and sound intensity R through analysis software, obtain the influence of temperature T, pressure N, and sound intensity R on the stamping quality of sheet metal parts of aircraft cabin doors, and output the temperature influence factor At, pressure influence factor An, and sound intensity influence factor Ar;

[0045] S5. The evaluation unit obtains the temperature T, pressure N, and sound intensity R, and performs dimensionless processing on them, and associates them to form a control coefficient CY. The association model is:

[0046]

[0047] Among them, At represents the temperature influence factor, 0.37≤At≤0.69; An represents the pressure influence factor, 0.47≤An≤0.76; Ar represents the solidification influence factor, 0.24≤Ar≤0.95; L represents the metal elastic modulus of the sheet metal part of the aircraft cabin door;

[0048] S6, transmitting the acquired control coefficient CY to the judgment unit for comparison with the preset second preset threshold value, if the control coefficient CY is not within the range of the second preset threshold value, then forming a corresponding control instruction, regulating the output power and extension speed of the electric telescopic rod, and the output power of the electric heating plate, and evaluating the control coefficient CY of the forming device at the same time, until the control coefficient CY is within the second preset threshold value, thereby ensuring the stamping quality of the sheet metal parts of the aircraft cabin door. The range of the second preset threshold value is determined according to the part forming quality after multiple tests.

[0049] Preferably, when the sheet metal component of the aircraft door is made of aluminum alloy, the metal elastic modulus L is 70 GPa.

[0050] For other embodiments of the present invention, please refer to Figure 1 to Figure 3 , a sheet metal parts forming device for an aircraft cabin door is provided, comprising a bottom plate 10 and a top plate 5, a plurality of support columns 11 are fixedly connected between the bottom plate 10 and the top plate 5, a lower mold 6 is fixedly connected to the upper side of the bottom plate 10, a die groove 7 is provided on the upper side of the lower mold 6, a sound collection device is provided on the bottom side of the die groove 7, an electric telescopic rod 3 is fixedly connected to the bottom side wall of the top plate 5, an upper mold 1 is fixedly connected to the bottom end of the electric telescopic rod 3, a convex module 2 is fixedly connected to the bottom side wall of the upper mold 1, the convex module 2 and the lower mold 6 are both made of titanium alloy, the shape of the convex module 2 is adapted to the die groove 7, a temperature sensor 13 and a pressure sensor 14 are provided on the bottom side wall of the convex module 2, and an electric heating plate 4 is provided inside the convex module 2.

[0051] Specifically, the sound collection device includes an installation cavity 9, in which an acoustic emission detector 8 is installed. A sound guide channel 12 is opened between the installation cavity 9 and the die groove 7. The sound guide channel 12 is arranged in a cone shape. When the cabin door sheet metal parts are in the stamping process, the sound signal generated by the bending deformation of the cabin door sheet metal parts in the die groove 7 will be collected by the acoustic emission detector 8 through the convex module 2, and then the sound intensity of the bending deformation of the sheet metal parts is obtained. When the sheet metal parts are stamped faster or more, the bending deformation of the sheet metal parts is more likely to produce cracks, and at this time the sheet metal parts will produce a larger bending deformation sound intensity.

[0052] The present invention also includes a control mechanism, which is used to improve the stamping quality of the sheet metal parts of the aircraft cabin door by regulating the output power and extension speed of the electric telescopic rod 3 and the output power of the electric heating plate 4;

[0053] The control mechanism includes a control module, a detection module, and a processing module;

[0054] The control module is connected with the electric telescopic rod 3 and the electric heating plate 4 by electrical signals;

[0055] The detection module includes a temperature detection unit for detecting the stamping temperature of the surface of the convex module 2, a pressure detection unit for detecting the stamping intensity of the convex module 2, and a sound intensity detection unit for detecting the sound intensity of the bending deformation of the sheet metal parts during the stamping process of the convex module 2, wherein the temperature detection unit is a temperature sensor 13, and the pressure detection unit is a pressure sensor 14; the sound intensity detection unit is an acoustic emission detector 8; the acoustic emission detector 8 is used to collect, analyze and process the sound signals generated by the bending deformation of the sheet metal parts of the cabin door during the stamping process of the sheet metal parts of the cabin door, so as to obtain the sound intensity of the bending deformation of the sheet metal parts;

[0056] The processing module includes an evaluation unit and a judgment unit.

[0057] In other embodiments of the present application, a molding method is also provided, which specifically includes the following steps:

[0058] S1, placing the sheet metal part of the aircraft cabin door on the surface of the downward mold 6 and covering the die groove 7;

[0059] S2, control the electric heating plate 4 to start heating the male module 2, which can make the sheet to be stamped more ductile and less likely to crack, and then control the electric telescopic rod 3 to extend, which will drive the male module 2 to descend through the upper mold 1 to extrude the sheet metal part of the aircraft cabin door into the female die groove 7 for stamping;

[0060] S3, during the stamping process, the stamping temperature of the male module 2, the stamping intensity of the male module 2, and the sound intensity of the bending deformation of the sheet metal parts of the aircraft cabin door are respectively detected by the temperature detection unit, the pressure detection unit, and the sound intensity detection unit in the detection module to form temperature T, pressure N, and sound intensity R, and transmit them to the evaluation unit for evaluation. If at least one of them exceeds the corresponding first preset threshold, judgment information is formed;

[0061] S4. Summarize the acquired temperature T, pressure N, and sound intensity R to form detection condition information, build a data model and optimize and train it, perform regression analysis on the acquired temperature T, pressure N, and sound intensity R through analysis software, obtain the influence of temperature T, pressure N, and sound intensity R on the stamping quality of sheet metal parts of aircraft cabin doors, and output the temperature influence factor At, pressure influence factor An, and sound intensity influence factor Ar;

[0062] S5. The evaluation unit obtains the temperature T, pressure N, and sound intensity R, and performs dimensionless processing on them, and associates them to form a control coefficient CY. The association model is:

[0063]

[0064] Wherein, At represents the temperature influence factor, 0.37≤At≤0.69; An represents the pressure influence factor, 0.47≤An≤0.76; Ar represents the solidification influence factor, 0.24≤Ar≤0.95; L represents the metal elastic modulus of the sheet metal part of the aircraft cabin door. When the sheet metal part of the aircraft cabin door is made of aluminum alloy, the metal elastic modulus L is 70GPa;

[0065] S6. The acquired control coefficient CY is transmitted to the judgment unit for comparison with a preset second preset threshold value. If the control coefficient CY is not within the range of the second preset threshold value, a corresponding control instruction is generated to control the output power and extension speed of the electric telescopic rod 3 and the output power of the electric heating plate 4. At the same time, the control coefficient CY of the forming device is evaluated until the control coefficient CY is within the second preset threshold value, thereby ensuring the stamping quality of the sheet metal parts of the aircraft cabin door.

Claims

1. A sheet metal parts forming device for aircraft cabin doors, characterized in that: The device comprises a bottom plate (10) and a top plate (5); A plurality of support columns (11) are fixedly connected between the bottom plate (10) and the top plate (5); a lower mold (6) is fixedly connected to the upper side of the bottom plate (10); a die groove (7) is provided on the upper side of the lower mold (6); a sound collection device is provided on the bottom side of the die groove (7); an electric telescopic rod (3) is fixedly connected to the bottom side wall of the top plate (5); an upper mold (1) is fixedly connected to the bottom end of the electric telescopic rod (3); a convex module (2) is fixedly connected to the bottom side wall of the upper mold (1); the convex module (2) and the lower mold (6) are both made of titanium alloy; the shape of the convex module (2) matches the die groove (7); a temperature sensor (13) and a pressure sensor (14) are provided on the bottom side wall of the convex module (2); and an electric heating plate (4) is provided inside the convex module (2).

2. The device according to claim 1, characterized in that The sound collection device comprises an installation cavity (9), an acoustic emission detector (8) is installed in the installation cavity (9), a sound guide channel (12) is provided between the installation cavity (9) and the die groove (7), and the sound guide channel (12) is arranged in a cone shape.

3. The device according to claim 2, characterized in that The device also includes a control mechanism, which is used to improve the stamping quality of the sheet metal parts of the aircraft cabin door by regulating the output power and extension speed of the electric telescopic rod (3) and the output power of the electric heating plate (4).

4. The device according to claim 3, characterized in that The control mechanism includes a control module, a detection module, and a processing module; The control module is connected to the electric telescopic rod (3) and the electric heating plate (4) via electrical signals; The detection module comprises a temperature detection unit for detecting the stamping temperature of the surface of the convex module (2), a pressure detection unit for detecting the stamping intensity of the convex module (2), and a sound intensity detection unit for detecting the sound intensity of the bending deformation of the sheet metal parts during the stamping process of the convex module (2); The processing module includes an evaluation unit and a judgment unit.

5. The device according to claim 4, characterized in that The temperature detection unit is a temperature sensor (13), and the pressure detection unit is a pressure sensor (14).

6. The device according to claim 5, characterized in that The sound intensity detection unit is an acoustic emission detector (8); the acoustic emission detector (8) is used to collect, analyze and process the sound signals generated by the bending deformation of the cabin door sheet metal parts during the stamping process, so as to obtain the sound intensity of the bending deformation of the sheet metal parts.

7. A method for forming sheet metal parts of aircraft cabin doors, characterized in that: The method specifically comprises the following steps: S1, placing the sheet metal component of the aircraft cabin door on the surface of the downward mold (6) and covering the concave mold groove (7); S2, controlling the electric heating plate (4) to start heating the male module (2), and then controlling the electric telescopic rod (3) to extend. The extension of the electric telescopic rod (3) drives the male module (2) to descend through the upper mold (1) to extrude the sheet metal parts of the aircraft cabin door into the female mold groove (7) for stamping; S3, during the stamping process, the stamping temperature of the male module (2), the stamping intensity of the male module (2), and the sound intensity of the bending deformation of the sheet metal parts of the aircraft cabin door are respectively detected by the temperature detection unit, the pressure detection unit, and the sound intensity detection unit in the detection module to form temperature T, pressure N, and sound intensity R, which are transmitted to the evaluation unit for evaluation. If at least one value among the temperature T, pressure N, and sound intensity R exceeds the range of the corresponding first preset threshold value, the value is adjusted to be within the range of the first preset threshold value; S4. Summarize the acquired temperature T, pressure N, and sound intensity R to form detection condition information, build a data model and optimize and train it, perform regression analysis on the acquired temperature T, pressure N, and sound intensity R through analysis software, obtain the influence of temperature T, pressure N, and sound intensity R on the stamping quality of sheet metal parts of aircraft cabin doors, and output the temperature influence factor At, pressure influence factor An, and sound intensity influence factor Ar; S5. The evaluation unit obtains the temperature T, pressure N, and sound intensity R, and performs dimensionless processing on them, and associates them to form a control coefficient CY. The association model is: Among them, At represents the temperature influence factor; An represents the pressure influence factor; Ar represents the solidification influence factor; L represents the metal elastic modulus of the sheet metal part of the aircraft cabin door; S6, transmitting the acquired control coefficient CY to the judgment unit for comparison with a preset second preset threshold value; if the control coefficient CY is not within the range of the second preset threshold value, generating a corresponding control instruction to control the output power and extension speed of the electric telescopic rod (3) and the output power of the electric heating plate (4); and at the same time evaluating the control coefficient CY of the forming device until the control coefficient CY is within the second preset threshold value, thereby ensuring the stamping quality of the sheet metal parts of the aircraft cabin door.

8. The method according to claim 7, characterized in that When the sheet metal parts of aircraft cabin doors are made of aluminum alloy, the metal elastic modulus L is 70GPa.

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