CN118417448B

CN118417448B - Thermoforming mold for airplane parts and application method of thermoforming mold

Info

Publication number: CN118417448B
Application number: CN202410895580.9A
Authority: CN
Inventors: 刘昌根
Original assignee: Shenyang Baolong Aircraft Parts Co ltd
Current assignee: Shenyang Baolong Aircraft Parts Co ltd
Priority date: 2024-07-05
Filing date: 2024-07-05
Publication date: 2024-08-30
Anticipated expiration: 2044-07-05
Also published as: CN118417448A

Abstract

The invention belongs to the technical field of hot press forming, and provides a hot press forming die for an aircraft part and a use method thereof, wherein the hot press forming die for the aircraft part comprises a lower die assembly and an upper die assembly for lifting movement, the lower die assembly comprises a containing part for containing the part, an installation cavity is arranged in the lower die assembly, and a demoulding assembly is arranged in the installation cavity; the demolding assembly comprises a jacking mechanism, a lifting block, a connecting pipe and a jacking plate; the lifting block is connected with the connecting pipe, one end of the connecting pipe, which is far away from the lifting block, extends out of the mounting cavity and is in sliding connection with the upper wall of the mounting cavity, one end of the connecting pipe, which is far away from the lifting block, is connected with the lifting plate, and the side wall of the connecting pipe is provided with air outlets in annular equidistant arrangement. Air discharged by the air outlet of the connecting pipe is utilized to form air flow between the aircraft parts and the accommodating part, and the aircraft parts are demolded by means of the action of air power, so that friction and potential damage to the surfaces of the aircraft parts are obviously reduced.

Description

Thermoforming mold for airplane parts and application method of thermoforming mold

Technical Field

The invention belongs to the technical field of hot press forming, and particularly relates to a hot forming die for an aircraft part and a use method thereof.

Background

The manufacture of aircraft parts typically involves complex engineering techniques, with thermoforming being a critical manufacturing process. Thermoforming involves heating a metal or composite material to its plastic temperature and then shaping it into a precise part shape using a mold under specific pressure and temperature conditions. This technology is widely used because it can produce high strength, lightweight, and complex parts that meet stringent aviation standards. The thermal forming not only improves the utilization rate of materials, but also ensures the performance and reliability of parts by precisely controlling the forming conditions.

Although thermoforming techniques have been widely used in the manufacture of aircraft parts, existing thermoforming molds still present significant challenges in the demolding process. Currently, many mold designs rely on manual demolding, a process that is not only labor intensive, but also inefficient. In addition, some molds employ mechanical structures, such as a jacking mechanism or other linear motion mechanism, to assist in demolding. However, because of the extremely high precision requirements of aircraft parts and the large part area typically, with these mechanical aids, the parts may separate from the mold at some locations and still closely adhere to the mold at other locations, resulting in poor demolding. If an attempt is made to solve this problem by increasing the stroke of the jacking mechanism or the linear motion mechanism, deformation of the parts is easily caused, and the final performance and safety thereof are affected.

Disclosure of Invention

The invention provides a thermal forming die for aircraft parts and a use method thereof, and aims to solve the problems set forth in the background technology.

In a first aspect of the invention, there is provided an aircraft component thermoforming mold, comprising a lower mold assembly and an upper mold assembly for lifting movement, wherein the upper surface of the lower mold assembly is provided with a containing part for containing a component, the lower mold assembly is internally provided with a mounting cavity, the mounting cavity is internally provided with a demolding assembly, and the containing part is positioned on the top wall of the mounting cavity;

The demolding assembly comprises a jacking mechanism, a lifting block, a connecting pipe and a jacking plate; the lifting block is connected with the connecting pipe, one end of the connecting pipe, which is far away from the lifting block, stretches out of the installation cavity and is in sliding connection with the upper wall of the installation cavity, one end of the connecting pipe, which is far away from the lifting block, is connected with the lifting plate, the side wall of one end, which is close to the lifting plate, of the connecting pipe is provided with air outlets in annular equidistant arrangement, and the lifting mechanism is in contact with the lifting block and is used for driving the lifting block to move upwards.

Optionally, the jacking mechanism comprises a cylinder body, a piston, a valve core, a push rod, a driving piece and an air inlet pipe;

The air inlet pipe is connected with the cylinder body, the piston is arranged in the cylinder body, a first channel is arranged on the piston, the valve core is fixedly arranged in the cylinder body and used for sealing the first channel, the ejector rod is connected with the piston and extends out of the cylinder body, one end of the ejector rod, which is far away from the piston, is connected with the driving piece, a second channel is arranged in the driving piece, and a third channel communicated between the first channel and the second channel is arranged in the ejector rod; the driving piece is provided with a first inclined plane, the lifting block is provided with a second inclined plane matched with the first inclined plane, a fourth channel used for being communicated with the second channel is arranged in the lifting block, and the fourth channel is communicated with the connecting pipe.

Optionally, the jacking mechanism further comprises a first spring and an exhaust pipe, wherein the first spring is connected with the driving piece and is used for providing elastic force for the driving piece in the direction close to the cylinder body;

the driving piece is provided with a first limiting part, the air inlet pipe is provided with a one-way valve, the exhaust pipe is connected with the cylinder body, and the exhaust pipe is provided with an electromagnetic valve.

Optionally, the quantity of first spring is two, climbing mechanism still includes the mounting panel, fixed mounting has two first guide bars on the mounting panel, two first spring overlaps respectively and locates two on the first guide bar, be provided with two lugs on the driving piece, two first guide bar pass respectively two the lug and with lug sliding connection, two the first spring is kept away from the one end of mounting panel with the lug contact.

Optionally, the demolding assembly further comprises two fixing mechanisms, wherein each fixing mechanism comprises a bottom plate, two side plates, an electric push rod, a connecting block, two sliding rods, two driving arms, a connecting rod, two connecting sheets and a clamping plate;

The bottom plate is fixedly connected with the driving piece, the two side plates are fixedly connected with the bottom plate, sliding grooves are respectively formed in the two side plates, the electric push rod is fixedly installed on the bottom plate, the connecting block is connected with the output end of the electric push rod, the two sliding rods are respectively connected with the connecting block and respectively extend into the sliding grooves, the sliding rods are in sliding connection with the sliding grooves, the two driving arms are connected through the connecting rods, one ends, far away from the connecting rods, of the two driving arms are respectively connected with the two sliding rods in a rotating mode, the connecting rods penetrate through the two connecting pieces and are connected with the connecting pieces in a rotating mode, the two connecting pieces are triangular, the two connecting pieces are respectively connected with the two side plates in a rotating mode, and the clamping plate is fixedly connected with the two connecting pieces;

And the lifting block is connected with two clamping parts.

Optionally, the diapire in installation cavity is provided with the mount pad, be provided with the slide on the mount pad, the lower surface of driving piece be connected with slide matched's slider, the slider with slide sliding connection, cylinder body fixed mounting in the upper surface of mount pad.

Optionally, the driving piece is further provided with two second limiting parts, and the two second limiting parts and the first inclined surface form a groove for the lifting block to slide.

Optionally, the hot forming die for the aircraft parts further comprises a guide assembly, wherein the guide assembly is connected with the lower die assembly, and the upper die assembly is in sliding connection with the guide assembly;

The guide assembly comprises four second guide rods, four second springs, two guide rails, four linear bearings, two connecting pieces and two transverse plates; four second guide bars are respectively fixed on the upper surface of the lower die assembly, the upper ends of two adjacent second guide bars are fixed through the transverse plates, four linear bearings are respectively sleeved on the four second guide bars, four second springs are respectively sleeved on the four second guide bars, the second springs provide upward elastic force for the linear bearings, two guide rails are respectively fixedly connected with the lower die assembly, the upper ends of the guide rails are fixedly connected with the transverse plates, two connecting pieces are respectively in sliding connection with the two guide rails, the two connecting pieces are respectively fixedly connected with the linear bearings, and the upper die assembly is fixedly mounted between the two connecting pieces.

Optionally, the upper die assembly comprises a plate body, an upper die body and an electric heating wire; the upper die body is fixedly arranged on the lower surface of the plate body, and the electric heating wire is embedded into the upper die body.

In a second aspect of the present invention, there is also provided a method of using an aircraft part thermoforming mold, the method being performed in dependence on an aircraft part thermoforming mold as described above, comprising the steps of:

s1, arranging the aircraft parts in the accommodating part, controlling the upper die assembly to move downwards, and performing hot press molding on the aircraft parts.

S2, after the hot press molding is finished, controlling the upper die assembly to move upwards.

S3, driving the lifting block to move upwards by utilizing the jacking mechanism, driving the connecting pipe to move upwards by the lifting block, driving the jacking plate to move upwards by the connecting pipe, and further driving the connecting pipe and the jacking plate to move upwards so as to jack up the hot-pressed and molded aircraft parts. After the jacking operation is finished, air is introduced into the connecting pipe and discharged from the air outlet holes which are annularly and equidistantly arranged on the side wall of the connecting pipe, and the airplane parts are separated from the accommodating part by utilizing air pressure.

The invention has the beneficial effects that compressed air is conveyed into the cylinder body through the air inlet pipe, and the air pushes the piston to move along the cylinder body. This simple and efficient driving means uses air pressure as a power source, reduces mechanical wear and provides reliable movement capability. The linear motion between the ejector rod and the driving piece is converted into the upward movement of the lifting block through the interaction of the first inclined plane and the second inclined plane, so that the stability and the uniformity of the motion are ensured. While also providing a stable mechanical force.

The lifting block is driven to move upwards by the jacking mechanism, the lifting block drives the connecting pipe to move upwards, the connecting pipe drives the jacking plate to move upwards, and then the connecting pipe and the jacking plate are driven to move upwards, so that the hot-pressed aircraft parts are jacked. After the jacking operation is finished, air is introduced through the inside of the connecting pipe and is discharged from the air outlet holes which are annularly and equidistantly arranged on the side wall of the connecting pipe, and the airplane parts are gradually separated from the accommodating part by utilizing air pressure.

And air discharged by the air outlet hole of the connecting pipe is utilized to form air flow between the aircraft parts and the accommodating part, and the demolding of the aircraft parts is performed by means of the action of air power. Friction and potential damage to the surface of aircraft parts is significantly reduced, especially when handling aircraft parts of high precision and fragile materials, while maintaining their surface quality and structural integrity. As aircraft parts are often required to meet extremely high accuracy and material integrity requirements. Compared with the traditional mechanical lifting or pushing mode, the dynamic action of the gas is distributed more uniformly on the whole contact surface of the parts. Local stress concentrations are reduced, thereby significantly reducing the risk of deformation or damage to the component due to uneven forces. Meets the strict standard of the aviation industry on the quality control of parts, and effectively improves the reliability and the production efficiency of the manufacturing process.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the description of the embodiments will be briefly introduced below, it being obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

Fig. 1 is a schematic perspective view of a thermoforming mold for an aircraft component according to the present invention.

Fig. 2 is an exploded view of the thermoforming mold for aircraft parts provided by the invention.

Fig. 3 is a schematic cross-sectional structural view of the thermoforming mold for aircraft parts provided by the invention.

Fig. 4 is a schematic perspective sectional structure view of a lower die assembly of a thermoforming die for aircraft parts provided by the invention.

Fig. 5 is a schematic perspective view of a demolding assembly of an aircraft part thermoforming mold provided by the invention.

Fig. 6 is an exploded view of a stripper assembly of a thermoforming mold for aircraft parts provided by the invention.

Fig. 7 is a schematic perspective view of a lifting block, a connecting pipe and a lifting plate of the thermoforming mold for aircraft parts.

Fig. 8 is a schematic perspective view of a driving member of the thermoforming mold for aircraft parts according to the present invention.

Fig. 9 is a schematic perspective view of a first view angle of a fixing mechanism of an aircraft part thermoforming mold provided by the invention.

Fig. 10 is a schematic perspective view of a second view angle of a fixing mechanism of an aircraft part thermoforming mold according to the present invention.

Fig. 11 is an exploded view of the fixing mechanism of the thermoforming mold of the aircraft component provided by the invention.

Fig. 12 is a schematic perspective view of a thermal forming mold for an aircraft component, which is provided by the invention, and is connected with an air supply device.

The reference numerals are as follows:

1-upper die assembly, 11-plate body, 12-upper die body, 13-heating wire, 2-lower die assembly, 21-receiving portion, 22-mounting cavity, 23-mounting seat, 24-slideway, 25-slide block, 3-demolding assembly, 31-jacking mechanism, 311-cylinder, 312-piston, 3121-first channel, 313-valve core, 3131-mounting frame, 314-ejector rod, 3141-third channel, 315-driving piece, 3151-second channel, 3152-first inclined surface, 3153-first limit portion, 3154-bump, 3155-second limit portion, 316-air inlet pipe, 3161-check valve, 317-first spring, 318-air outlet pipe 3181-electromagnetic valve, 319-mounting plate, 3191-first guide bar, 32-lifting block, 321-second inclined plane, 322-fourth channel, 323-clamping part, 33-connecting tube, 331-air outlet, 34-lifting plate, 35-fixing mechanism, 351-bottom plate, 352-side plate, 3521-chute, 353-electric push rod, 354-connecting block, 355-slide rod, 356-driving arm, 357-connecting rod, 358-connecting sheet, 359-clamping plate, 4-guide component, 41-second guide bar, 42-second spring, 43-guide rail, 44-linear bearing, 45-connecting piece, 46-transverse plate, 5-air supply device.

Detailed Description

The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to fall within the scope of the application.

The terms "first" and "second" and the like in this disclosure are used for distinguishing between different objects and not for describing a particular sequential order. Furthermore, the terms "comprise" and "have," as well as any variations thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, system, article, or apparatus that comprises a list of steps, operations, components, or modules is not limited to the particular steps, operations, components, or modules listed but may optionally include additional steps, operations, components, or modules inherent to such process, method, article, or apparatus.

Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the application. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Those of skill in the art will explicitly and implicitly appreciate that the embodiments described herein may be combined with other embodiments.

Example 1

As shown in fig. 1 to 12, a thermoforming mold for aircraft parts of an exemplary embodiment includes a lower mold assembly 2 and an upper mold assembly 1 for performing a lifting motion. The upper surface of the lower die assembly 2 is provided with a receiving portion 21 for receiving an aircraft part to be molded. A mounting cavity 22 is arranged in the lower die assembly 2, and the accommodating part 21 is positioned on the top wall of the mounting cavity 22; in which a stripper unit 3 is installed. The demolding assembly 3 is specially used for demolding the aircraft parts after hot press molding. In this embodiment, the shape of the press-fit portion of the upper die assembly 1 and the lower die assembly 2 is matched with the rib of the aircraft. In practical use, the shape of the press-fit part of the upper die assembly 1 and the lower die assembly 2 can be prepared according to the size and parameters of the parts to be actually processed, and the thermal forming die is mainly suitable for ribs of an airplane or other parts needing thermal forming.

In actual use, the die is mounted on an existing hot press and a hydraulic system is connected to the upper die assembly 1. The heated aircraft parts are placed in the receiving portion 21 of the lower die assembly 2. The upper die assembly 1 is controlled to move downwards by using a hydraulic system, so that the upper die assembly 1 presses the aircraft parts to the lower die assembly 2. After the pressing is finished, the hydraulic system controls the upper die assembly 1 to move upwards, and the pressing and demoulding processes are finished.

The demolding assembly 3 comprises a jacking mechanism 31, a lifting block 32, a connecting pipe 33 and a jacking plate 34. The lifting block 32 is connected to a connecting tube 33, and the connecting tube 33 extends out of the installation cavity 22 at an end away from the lifting block 32 and is slidably connected to an upper wall of the installation cavity 22. The other end of the connection pipe 33 is connected to the lift plate 34. The side wall of the connecting pipe 33 near one end of the jacking plate 34 is provided with air outlets 331 in annular equidistant arrangement. The lifting mechanism 31 contacts the lifting block 32, and the lifting mechanism 31 is used for driving the lifting block 32 to move upward.

The lifting block 32 is driven to move upwards by the jacking mechanism 31, the lifting block 32 drives the connecting pipe 33 to move upwards, the connecting pipe 33 drives the jacking plate 34 to move upwards, and then the connecting pipe 33 and the jacking plate 34 are driven to move upwards so as to jack up the hot-pressed aircraft parts. After the jacking operation is completed, air is introduced through the inside of the connection pipe 33 and discharged from the air outlet holes 331 annularly and equidistantly arranged on the side wall of the connection pipe 33, and the aircraft parts are gradually separated from the accommodating part 21 by using air pressure.

Further, the bottom of the accommodating portion 21 of the lower mold assembly 2 is provided with an accommodating groove (not shown) for accommodating the jacking plate 34. When the lifting plate 34 is at its lowest position, its upper surface completely coincides with the bottom wall of the receiving portion 21, forming a smooth surface. In the demolding process, the lifting plate 34 is moved up to a height which is sufficient to allow air to pass through, as long as a gap is formed between the lifting plate 34 and the bottom wall of the receiving portion 21. The problem that the aircraft parts deform due to the excessively high upward movement in the demolding process is avoided. And the air pressure provided by the air is utilized to separate the airplane parts from the accommodating part 21 of the lower die assembly 2, so that the contact between the mechanical structure and the airplane parts is avoided, and the damage to the airplane parts is avoided.

The air discharged from the air outlet 331 of the connection pipe 33 causes an air flow between the aircraft component and the housing 21, and the aircraft component is released by the action of the air power. Friction and potential damage to the surface of aircraft parts is significantly reduced, especially when handling aircraft parts of high precision and fragile materials, while maintaining their surface quality and structural integrity. As aircraft parts are often required to meet extremely high accuracy and material integrity requirements. Compared with the traditional mechanical lifting or pushing mode, the dynamic action of the gas is distributed more uniformly on the whole contact surface of the parts. Local stress concentrations are reduced, thereby significantly reducing the risk of deformation or damage to the component due to uneven forces. Meets the strict standard of the aviation industry on the quality control of parts, and effectively improves the reliability and the production efficiency of the manufacturing process.

Specifically, the jacking mechanism 31 is mainly composed of a cylinder 311, a piston 312, a valve element 313, a jack 314, a driving element 315, and an intake pipe 316.

The intake pipe 316 is connected to the cylinder 311, the piston 312 is mounted inside the cylinder 311, and the piston 312 is provided with a first passage 3121. The valve element 313 is cylindrical, and the valve element 313 is fixedly connected with the inner wall of the cylinder 311 through the mounting frame 3131, and one end of the valve element 313, which is far away from the mounting frame 3131, is hemispherical. The valve core 313 is used for closing the first channel 3121, the ejector rod 314 is connected with the piston 312 and extends out of the cylinder 311, one end of the ejector rod 314 away from the piston 312 is connected with the driving member 315, a second channel 3151 is arranged in the driving member 315, a third channel 3141 communicated between the first channel 3121 and the second channel 3151 is arranged in the ejector rod 314, and the second channel 3151 is curved as shown in fig. 3. The driving member 315 is provided with a first inclined surface 3152, and the elevating block 32 is provided with a second inclined surface 321 which is matched with the first inclined surface 3152. A fourth channel 322 for communicating with the second channel 3151 is provided in the elevation block 32, and the fourth channel 322 communicates with the connection pipe 33.

As shown in fig. 12, one end of the air inlet pipe 316 far away from the cylinder 311 is connected with the existing air supply device 5, air is supplied into the cylinder 311 by the air supply device 5, after the air enters the cylinder 311, the air pushes the piston 312 to move along with the continuous rising of the air pressure, at this time, the piston 312 moves relative to the valve core 313, the piston 312 drives the driving member 315 to perform linear motion through the ejector rod 314, the first inclined surface 3152 of the driving member 315 acts on the second inclined surface 321 of the lifting block 32, the lifting block 32 is driven to move upwards under the action of the first inclined surface 3152 and the second inclined surface 321, and meanwhile, the lifting block 32 also moves relative to the driving member 315. The lifting block 32 indirectly drives the lifting plate 34 to move upwards. When the piston 312 is completely separated from the valve element 313, the end of the second channel 3151 away from the ejector rod 314 corresponds to the fourth channel 322, and then air enters through the first channel 3121 of the piston 312, passes through the third channel 3141, the second channel 3151 and the fourth channel 322 in sequence, enters the connection pipe 33, and finally is discharged through the air outlet hole 331 of the connection pipe 33. The air flow is formed between the aircraft component and the housing 21, and the aircraft component is released by the action of the air power. In this embodiment, the power for moving up the lifting plate 34 and the input of air flow are provided by the air supply device 5, so that the design is ingenious.

Wherein the air supply means 5 may be, but is not limited to, the following existing devices:

a compressor: for generating compressed air;

gas cylinder: a high pressure gas cylinder filled with compressed air or nitrogen;

An air pump: an apparatus for providing a continuous flow of gas.

Specifically, the jacking mechanism 31 further includes a first spring 317 and an exhaust pipe 318, where the first spring 317 is connected to the driving member 315, and is configured to provide the driving member 315 with an elastic force in a direction approaching the cylinder 311. When the piston 312 moves and drives the driving member 315 to move, the driving member 315 compresses the first spring 317, and the first spring 317 is used to provide a restoring force to the driving member 315.

The driving member 315 is provided with a first limiting portion 3153, when the first limiting portion 3153 of the driving member 315 moves to contact with the lifting block 32, the driving member 315 moves in place, and along with the continuous input of air pressure, the driving member 315 cannot move in a direction away from the cylinder 311, and meanwhile, the piston 312 is separated from the valve element 313. The intake pipe 316 is provided with a check valve 3161, the exhaust pipe 318 is connected to the cylinder 311, and the exhaust pipe 318 is provided with a solenoid valve 3181.

When the air is filled into the air intake pipe 316, the air passes through the check valve 3161, and the check valve 3161 serves to prevent the air in the cylinder 311 from flowing back from the air intake pipe 316. The lifting block 32 is driven and the aircraft parts are demolded by filling air into the cylinder 311, after the demolding is completed, the electromagnetic valve 3181 is controlled to be opened, the piston 312 is driven to perform reset motion under the action of the elastic force of the first spring 317, the air in the cylinder 311 is extruded to flow out of the exhaust pipe 318, meanwhile, the driving piece 315 also performs reset motion, and then the lifting block 32, the connecting pipe 33 and the lifting plate 34 descend under the action of gravity, and the lifting plate 34 returns to the accommodating groove for accommodating the lifting plate 34 to wait for the next demolding motion.

Among them, the check valve 3161 and the solenoid valve 3181 are set so as to prevent the air in the cylinder 311 from leaking out; when the air supply device 5 stops supplying air, the elastic force of the first spring 317 indirectly drives the piston 312 to perform the reset motion, and when the valve element 313 stretches into the first channel 3121 again, the air in the cylinder 311 cannot be discharged, so that the piston 312 is effectively prevented from resetting under the elastic force of the first spring 317. The structure is designed to prevent the piston 312 from resetting when the air supply device 5 is in an unexpected condition of insufficient air pressure or stopping air supply, so as to prevent the lifting plate 34 from falling back into the accommodating groove when the air supply device 5 is in an unexpected condition of insufficient air pressure or stopping air supply.

Specifically, the number of the first springs 317 is two, the jacking mechanism 31 further includes a mounting plate 319, two first guide rods 3191 are fixedly mounted on the mounting plate 319, the two first springs 317 are respectively sleeved on the two first guide rods 3191, two protruding blocks 3154 are arranged on the driving member 315, the two first guide rods 3191 respectively penetrate through the two protruding blocks 3154 and are in sliding connection with the protruding blocks 3154, and one ends, far away from the mounting plate 319, of the two first springs 317 are in contact with the protruding blocks 3154. The two first guide rods 3191 are configured to improve the stability and smoothness of the linear motion of the driving member 315, and two first springs 317 are provided to guide the driving member 315 to ensure the balance of the force applied to the driving member 315.

Example two

To ensure the stability of the interface of the second channel 3151 with the fourth channel 322. The difference between this embodiment and the first embodiment is that the demolding assembly 3 further includes two fixing mechanisms 35, and the fixing mechanisms 35 include a bottom plate 351, two side plates 352, an electric push rod 353, a connecting block 354, two slide bars 355, two driving arms 356, a connecting rod 357, two connecting pieces 358, and a clamping plate 359.

Bottom plate 351 and driving piece 315 fixed connection, two curb plates 352 and bottom plate 351 fixed connection, the spout 3521 has been seted up respectively on two curb plates 352, electric putter 353 fixed mounting is on bottom plate 351, connecting block 354 is connected with the output of electric putter 353, two slide bars 355 are connected with connecting block 354 respectively and stretch into in spout 3521 respectively, slide bar 355 and spout 3521 sliding connection, two drive arms 356 pass through connecting rod 357 to be connected, the one end that connecting rod 357 was kept away from to two drive arms 356 rotates with two slide bars 355 respectively to be connected, connecting rod 357 passes two connection pieces 358 and rotates with connection piece 358 to be connected, two connection pieces 358 are triangle-shaped, two connection pieces 358 rotate with two curb plates 352 respectively to be connected, grip block 359 and two connection piece 358 fixed connection. Two clamping portions 323 are connected to the lifting block 32.

When the lifting block 32 is not in contact with the first stopper 3153, the output end of the electric putter 353 is in a retracted state. When the lifting block 32 contacts with the first limiting part 3153, the electric push rod 353 is started, the output end of the electric push rod 353 drives the connecting block 354 to move, the sliding rod 355 is in sliding connection with the sliding groove 3521, stable linear motion of the connecting block 354 is guaranteed, meanwhile, the sliding rod 355 drives the driving arm 356 to move, the driving arm 356 drives the two connecting sheets 358 to rotate relative to the side plate 352 through the connecting rod 357 until the two connecting sheets 358 drive the clamping plate 359 to contact with the clamping part 323, at the moment, the lifting block 32 is fixed by the clamping plate 359 and the first limiting part 3153, at the moment, the second channel 3151 is in complete butt joint with the fourth channel 322, further the butt joint stability of the second channel 3151 and the fourth channel 322 is guaranteed, the air flow conveying stability is guaranteed, and the air leakage is reduced.

The electric push rod 353 is a currently available linear motion mechanism, and the specific control principle and the use method thereof are not described in detail herein. In the implementation of this embodiment, an existing contact switch may be applied and installed on the lifting block 32 or the first limiting portion 3153, so as to monitor whether the lifting block 32 contacts the first limiting portion 3153, and when the lifting block 32 contacts the first limiting portion 3153, the contact switch is triggered, and the electric push rod 353 is started. After the demolding is completed, the output end of the electric push rod 353 can be controlled to retract by using an existing switch or a controller or the like, and the fixing of the lifting block 32 is canceled. Meanwhile, an existing position monitoring sensor can be used for monitoring the position of the lifting block 32, so as to control the start and stop and the action of the electric push rod 353. In summary, the specific triggering manner and control method of the fixing mechanism 35 are well known to those skilled in the art, and can be flexibly set according to actual situations, and detailed descriptions thereof are omitted herein.

Specifically, the bottom wall of the mounting cavity 22 is provided with a mounting seat 23, a slide 24 is provided on the mounting seat 23, a slider 25 matched with the slide 24 is connected to the lower surface of the driving member 315, the slider 25 is slidably connected with the slide 24, and the cylinder 311 is fixedly mounted on the upper surface of the mounting seat 23. The setting of the slide 25 and slide 24 serves to improve the smoothness of the motion of the driving member 315.

Specifically, the driving member 315 is further provided with two second limiting portions 3155, and the two second limiting portions 3155 and the first inclined surface 3152 form a groove for the lifting block 32 to slide. The two second stopper portions 3155 are set to guide the movement of the lifting block 32.

Example III

The difference between this embodiment and the second embodiment is that the thermoforming mold for the aircraft component further includes a guide assembly 4, the guide assembly 4 is connected with the lower die assembly 2, and the upper die assembly 1 is slidably connected with the guide assembly 4.

The guide assembly 4 comprises four second guide bars 41, four second springs 42, two guide rails 43, four linear bearings 44, two connectors 45 and two cross plates 46. As shown in fig. 1, the lower die assembly 2 has a rectangular structure in plan view, and four guide bars 41 are respectively provided at four corners of the upper surface of the lower die assembly 2; the upper ends of two adjacent second guide rods 41 are fixed through a transverse plate 46, four linear bearings 44 are respectively sleeved on the four second guide rods 41, four second springs 42 are respectively sleeved on the four second guide rods 41, the second springs 42 provide upward elastic force for the linear bearings 44, two guide rails 43 are respectively fixedly connected with the lower die assembly 2, the upper ends of the two guide rails 43 are fixedly connected with the transverse plate 46, two connecting pieces 45 are respectively slidably connected with the two guide rails 43, the two connecting pieces 45 are respectively fixedly connected with the linear bearings 44, and the upper die assembly 1 is fixedly installed between the two connecting pieces 45. The adjacent two guide bars 41 are two guide bars 41 that are adjacent to each other in a direction perpendicular to the moving direction of the driving member 315.

When the hydraulic mechanism/system provides downward pressure to the upper die assembly 1 to perform hot press molding on the aircraft parts, the upper die assembly 1 moves downward, and simultaneously drives the two connecting pieces 45 to move downward, the two connecting pieces 45 slide on the two guide rails 43, and the linear bearings 44 also follow the two connecting pieces 45 to slide on the second guide rods 41. The guide rail 43 and the second guide rod 41 are utilized to have an accurate guide effect on the movement of the upper die assembly 1, meanwhile, the second spring 42 is compressed, and when the hydraulic mechanism/system drives the upper die assembly 1 to move upwards, the second spring 42 provides auxiliary upward force for the hydraulic mechanism/system.

Specifically, the design of the upper die assembly 1 takes into account the stringent requirements for temperature control during thermoforming to ensure the quality and accuracy of the aircraft parts. The upper die assembly 1 includes a plate body 11, an upper die body 12, and heating wires 13. The upper die body 12 is fixedly installed at the lower surface of the plate body 11, and the heating wire 13 is embedded inside the upper die body 12.

The embedding of the heating wire 13 enables the upper die body 12 to provide uniform and controlled heat during the hot press molding process. So as to be suitable for thermoforming processes requiring precise temperature control, in particular for the production of aircraft parts. By the thermal effect of the heating wire 13, the upper die body 12 can maintain a constant temperature throughout the molding process, thereby ensuring the heat treatment effect and molding quality of the material and preventing the material from being degraded due to uneven or insufficient temperature.

In addition, the temperature of the heating wire 13 can be precisely adjusted by an external existing control system to adapt to the molding temperature requirements of different materials. Such precise control of temperature is critical to achieving high standard aircraft component production, as any minor temperature variation may affect the structural integrity and final performance of the component. Meanwhile, in the actual implementation, the heating wire 13 may be optionally embedded in the accommodating portion 21 as well.

The invention also provides a method for using the thermoforming mould of the aircraft part, the implementation of the method depends on the thermoforming mould of the aircraft part, and the method comprises the following steps:

S1, arranging the aircraft parts in the accommodating part 21, controlling the upper die assembly 1 to move downwards, and performing hot press molding on the aircraft parts.

S2, after the hot press molding is finished, controlling the upper die assembly 1 to move upwards.

S3, the lifting block 32 is driven to move upwards by the jacking mechanism 31, the lifting block 32 drives the connecting pipe 33 to move upwards, the connecting pipe 33 drives the jacking plate 34 to move upwards, and then the connecting pipe 33 and the jacking plate 34 are driven to move upwards so as to jack up the hot-pressed aircraft parts. After the jacking operation is completed, air is introduced through the inside of the connection pipe 33 and discharged from the air outlet holes 331 annularly and equidistantly arranged on the side wall of the connection pipe 33, and the aircraft parts are separated from the accommodating part 21 by air pressure.

Further, before thermoforming begins, it is ensured that the aircraft parts have been preheated to an appropriate temperature to facilitate the forming effect.

The preheated aircraft parts are accurately placed in the accommodating part 21 of the lower die assembly 2, so that the parts are ensured to be positioned correctly, and the molding precision and quality are ensured. The upper die assembly 1 is controlled to slowly move down. The upper die body 12 is heated by the electric heating wire 13, so that a constant temperature is maintained in the molding process, and the aircraft parts are subjected to hot press molding. Accurate control of pressure and temperature is critical to ensure molding quality. After the molding is completed, the hydraulic system is activated to move the upper die assembly 1 upward. And preparation is made for demolding of the aircraft parts.

The lifting mechanism 31 is activated, wherein the lifting block 32 is driven to start moving upward. The lifting block 32 drives the connecting pipe 33 and the lifting plate 34 thereon to move upwards synchronously through mechanical connection.

With the upward movement of the jacking plate 34, the hot-press molded aircraft parts start to be gradually jacked up from the accommodating portion 21 of the lower die assembly 2. In this process, the lift plate 34 needs to maintain smooth contact with the components to avoid damage or deformation of the components.

When the lifting operation is about to be completed, compressed air is introduced into the connection pipe 33 through the air inlet pipe 316. The air is uniformly discharged from the air outlet holes 331 formed in the side wall of the connection pipe 33 to form a stable air cushion layer, and the aircraft parts are smoothly and completely separated from the accommodating part 21 by using air pressure. This gas-assisted demolding helps to reduce physical contact and reduce the risk of mechanical damage.

According to the method, the lifting mechanism 31 and airflow are utilized to demould the aircraft parts, the electric heating wires 13 are integrated to ensure uniform heating of materials in the forming process, and unstable material performance caused by uneven temperature is avoided. Moreover, the risk of damage to formed parts is greatly reduced by utilizing airflow demolding, and particularly for complex or fine aircraft parts, the method can keep high quality standard and dimensional accuracy, and remarkably improves production efficiency and product quality, so that the method has higher practical value in the aviation manufacturing industry.

The exemplary embodiments of the present application may be combined with each other, and exemplary embodiments obtained by combining also fall within the scope of the present application.

The principles and embodiments of the present application have been described with reference to specific examples, which are provided to facilitate understanding of the method and core ideas of the present application; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in light of the ideas of the present application, the present description should not be construed as limiting the present application.

Claims

1. The hot forming die for the aircraft parts comprises a lower die assembly (2) and an upper die assembly (1) for lifting, wherein a containing part (21) for containing the parts is arranged on the upper surface of the lower die assembly (2), and the hot forming die is characterized in that an installation cavity (22) is arranged in the lower die assembly (2), a demolding assembly (3) is arranged in the installation cavity (22), and the containing part (21) is positioned on the top wall of the installation cavity (22);

The demolding assembly (3) comprises a jacking mechanism (31), a lifting block (32), a connecting pipe (33) and a jacking plate (34); the lifting block (32) is connected with the connecting pipe (33), one end of the connecting pipe (33) far away from the lifting block (32) extends out of the mounting cavity (22) and is in sliding connection with the upper wall of the mounting cavity (22), one end of the connecting pipe (33) far away from the lifting block (32) is connected with the lifting plate (34), the side wall of one end of the connecting pipe (33) near the lifting plate (34) is provided with air outlet holes (331) in annular equidistant arrangement, and the lifting mechanism (31) is in contact with the lifting block (32) and is used for driving the lifting block (32) to move upwards;

The jacking mechanism (31) comprises a cylinder body (311), a piston (312), a valve core (313), an ejector rod (314), a driving piece (315) and an air inlet pipe (316);

The air inlet pipe (316) is connected with the cylinder body (311), the piston (312) is installed in the cylinder body (311), a first channel (3121) is arranged on the piston (312), the valve core (313) is fixedly installed in the cylinder body (311) and is used for sealing the first channel (3121), the ejector rod (314) is connected with the piston (312) and extends out of the cylinder body (311), one end of the ejector rod (314) far away from the piston (312) is connected with the driving piece (315), a second channel (3151) is arranged in the driving piece (315), and a third channel (3141) communicated between the first channel (3121) and the second channel (3151) is arranged in the ejector rod (314); the driving piece (315) is provided with a first inclined surface (3152), the lifting block (32) is provided with a second inclined surface (321) matched with the first inclined surface (3152), the lifting block (32) is internally provided with a fourth channel (322) communicated with the second channel (3151), and the fourth channel (322) is communicated with the connecting pipe (33);

The jacking mechanism (31) further comprises a first spring (317) and an exhaust pipe (318), wherein the first spring (317) is connected with the driving piece (315) and is used for providing elastic force for the driving piece (315) in the direction close to the cylinder body (311);

Be provided with first spacing portion (3153) on driving piece (315), be provided with check valve (3161) on intake pipe (316), blast pipe (318) with cylinder body (311) are connected, be provided with solenoid valve (3181) on blast pipe (318).

2. The aircraft part thermoforming mold according to claim 1, wherein the number of the first springs (317) is two, the jacking mechanism (31) further comprises a mounting plate (319), two first guide rods (3191) are fixedly mounted on the mounting plate (319), the two first springs (317) are respectively sleeved on the two first guide rods (3191), two protruding blocks (3154) are arranged on the driving member (315), the two first guide rods (3191) respectively penetrate through the two protruding blocks (3154) and are in sliding connection with the protruding blocks (3154), and one ends, away from the mounting plate (319), of the two first springs (317) are in contact with the protruding blocks (3154).

3. The aircraft part thermoforming mold of claim 1, wherein the demolding assembly (3) further comprises two fixing mechanisms (35), the fixing mechanisms (35) comprising a bottom plate (351), two side plates (352), an electric push rod (353), a connecting block (354), two slide bars (355), two driving arms (356), a connecting rod (357), two connecting pieces (358) and a clamping plate (359);

The bottom plate (351) is fixedly connected with the driving piece (315), two side plates (352) are fixedly connected with the bottom plate (351), sliding grooves (3521) are respectively formed in the two side plates (352), the electric push rod (353) is fixedly installed on the bottom plate (351), the connecting blocks (354) are connected with the output ends of the electric push rod (353), two sliding rods (355) are respectively connected with the connecting blocks (354) and respectively extend into the sliding grooves (3521), the sliding rods (355) are in sliding connection with the sliding grooves (3521), two driving arms (356) are connected through the connecting rods (357), one ends, far away from the connecting rods (357), of the two driving arms (356) are respectively connected with the two sliding rods (355) in a rotating mode, the connecting rods (357) penetrate through the two connecting pieces (358) and are connected with the output ends of the electric push rod (353) in a triangular mode, the two connecting pieces (358) are respectively connected with the two connecting pieces (358) in a rotating mode, and the two connecting pieces (358) are fixedly connected with the two connecting pieces (359).

Two clamping parts (323) are connected to the lifting block (32).

4. The aircraft part thermoforming mold according to claim 1, wherein the bottom wall of the mounting cavity (22) is provided with a mounting seat (23), a slide way (24) is provided on the mounting seat (23), a sliding block (25) matched with the slide way (24) is connected to the lower surface of the driving piece (315), the sliding block (25) is in sliding connection with the slide way (24), and the cylinder body (311) is fixedly mounted on the upper surface of the mounting seat (23).

5. The aircraft part thermoforming mold according to claim 1, wherein the driving member (315) is further provided with two second limiting portions (3155), and the two second limiting portions (3155) and the first inclined surface (3152) form a groove for sliding the lifting block (32).

6. The aircraft part thermoforming mold according to claim 1, further comprising a guide assembly (4), the guide assembly (4) being connected to the lower mold assembly (2), the upper mold assembly (1) being slidingly connected to the guide assembly (4);

The guide assembly (4) comprises four second guide rods (41), four second springs (42), two guide rails (43), four linear bearings (44), two connecting pieces (45) and two transverse plates (46); four second guide bars (41) respectively fixed mounting in the upper surface of lower module (2), two adjacent upper ends of second guide bars (41) pass through diaphragm (46) are fixed, four linear bearing (44) are respectively overlapped and are located four on second guide bars (41), four second spring (42) are respectively overlapped and are located four on second guide bars (41), second spring (42) are for linear bearing (44) provides ascending elasticity, two guide rail (43) respectively with lower module (2) fixed connection, two the upper end of guide rail (43) with diaphragm (46) fixed connection, two connecting piece (45) respectively with two guide rail (43) sliding connection, two connecting piece (45) respectively with linear bearing (44) fixed connection, go up module (1) fixed mounting in between two connecting piece (45).

7. The aircraft part thermoforming mold according to claim 1, wherein the upper mold assembly (1) comprises a plate body (11), an upper mold body (12) and a heating wire (13); the upper die body (12) is fixedly arranged on the lower surface of the plate body (11), and the electric heating wire (13) is embedded into the upper die body (12).

8. A method of using an aircraft part thermoforming mould, the method being carried out in dependence on an aircraft part thermoforming mould as claimed in any of claims 1 to 7, the method comprising the steps of:

the aircraft parts are arranged in the accommodating part (21), the upper die assembly (1) is controlled to move downwards, and hot press molding is carried out on the aircraft parts;

After the hot press molding is finished, the upper die assembly (1) is controlled to move upwards;

The lifting block (32) is driven to move upwards by the jacking mechanism (31), the lifting block (32) drives the connecting pipe (33) to move upwards, the connecting pipe (33) drives the jacking plate (34) to move upwards, and then the connecting pipe (33) and the jacking plate (34) are driven to move upwards so as to jack up the hot-pressed aircraft parts; after the jacking operation is finished, air is introduced through the inside of the connecting pipe (33) and is discharged from the air outlet holes (331) which are annularly and equidistantly arranged on the side wall of the connecting pipe (33), and the airplane parts are separated from the accommodating part (21) by utilizing air pressure.