METHOD FOR HOT-FORMING A THERMOPLASTIC MATERIAL AND IMPLEMENTATION FACILITY

Abstract

A method for shaping a preform made from thermoplastic material, and a facility for implementing the method, comprising the following steps: a) providing a preform made from thermoplastic material having a surface; b) supplying thermal energy to the preform by radiation in such a way as to make it ductile; and c) shaping the ductile preform inside a forming mould. Step b) further involves simultaneously spraying a gaseous fluid onto the surface of the preform in order to preserve the surface.

Claims

1. A method of forming a preform made of thermoplastic material, comprising the following steps: a) providing a preform made of thermoplastic material having a surface; b) providing heat energy by radiation to said preform such as to make it ductile; and, c) forming said ductile preform inside a forming die; wherein, at step a), a thermoplastic composite material is provided, and at step b), a gaseous fluid is simultaneously projected at the surface of said preform in order to protect said surface.

2. The forming method as claimed in claim 1, wherein, between step a) and step b), heat energy is further provided to said preform by conduction, such as to preheat said preform.

3. The forming method as claimed in claim 2, wherein said preform is brought into contact with heated plates in order to provide heat energy by conduction to said preform.

4. The forming method as claimed in claim 1, wherein said gaseous fluid is projected in a direction substantially perpendicular to the surface of said preform.

5. The forming method as claimed in claim 1, wherein, at step b), heat energy is provided by infrared radiation.

6. The forming method as claimed in claim 1, wherein, at step b), said gaseous fluid is air.

7. A facility for forming a preform made of thermoplastic material, comprising, firstly, a radiation heating enclosure for receiving a preform made of thermoplastic material such as to be able to provide heat energy by radiation to said preform to make it ductile, and, secondly, a forming die located downstream of said heating enclosure in order to be able to form said ductile preform; further comprising a gaseous fluid projecting device installed inside said radiation heating enclosure in order to be able to project said gaseous fluid at the surface of said preform, when said preform receives heat energy by radiation, such as to protect the surface of said preform.

8. The forming facility as claimed in claim 7, further comprising a conduction heating device located upstream of said radiation heating enclosure in order to be able to provide heat energy to said preform by conduction.

9. The forming facility as claimed in claim 8, wherein said conduction heating device comprises heated plates intended to come into contact with said preform in order to provide heat energy by conduction to said preform.

10. The forming facility as claimed in claim 7, wherein said radiation heating enclosure comprises infrared emission lamps.

Description

[0018] Other features and advantages of the invention will emerge upon reading the following description of a specific embodiment of the invention, which embodiment is given indicatively but in a nonlimiting manner, with reference to the appended drawings wherein:

[0019] FIG. 1A is a schematic view of a first station of a facility for forming a preform made of composite material in accordance with the invention;

[0020] FIG. 1B is a schematic view of a second station of the facility following the first station shown in FIG. 1A;

[0021] FIG. 1C is a schematic view of a third station of the facility following the second station shown in FIG. 1B; and,

[0022] FIG. 2 is a schematic view illustrating phenomena observed at the facility second station shown in FIG. 1B.

[0023] FIGS. 1A, 1B and 1C illustrate three successive stations for processing a preform made of thermoplastic material.

[0024] Reference will be made firstly to FIG. 1B schematically showing a heating enclosure 10, which forms an essential processing station of the method according to the invention. It comprises a processing space 12, which has an inlet 14 and an opposite outlet 16. Inside the processing space 12, a thermoplastic composite preform 15 is held horizontally in a fixed position. The preform 15 has, in this case, parts of various thicknesses. The heating enclosure 10 has, in the upper part thereof, upper infrared radians 18, located at the top of the processing space 12 and orientated towards the latter. It also has in the lower part thereof, below the processing space 12, lower infrared radians 20 also orientated towards the space. In addition, the heating enclosure 10 includes a gaseous fluid projecting device 22 for projecting the gaseous fluid through the infrared radians 18, 20 towards the inside of the processing space 12 in the direction of the preform 15. The projecting device 22 includes, for example, injection nozzles 24 extending between the elements of the infrared radians 20, 18. In this case, the gaseous fluid projected through the device 22 is air.

[0025] Downstream of the heating enclosure 10 is, shown schematically in FIG. 1C, a forming die 26 for receiving the preform 15 made of thermoplastic composite as will be explained hereafter.

[0026] Thus, the preform 15 made of thermoplastic composite has, for example, a polyamide 6, or polyamide 6.6, matrix, and textile reinforcing layers, for example, made of glass fiber or carbon fiber. The preform 15 is in the general shape of a plate, or a multi-thickness layered preform, which is not strengthened, and is held in a fixed position inside the processing space 12 on a perforated platform that is not shown. A multi-thickness preform has zones of various thicknesses.

[0027] In this manner, infrared radians 18, 20 provide heat energy by radiation to the preform 15 on the two opposite faces thereof.

[0028] As illustrated in greater detail in FIG. 2, the radiation penetrates through the surface 30 of the preform 15, into the surface layers thereof, over a thickness of approximately a few micrometers, or more, and then the heat energy is transmitted by conduction inside the preform 15 to reach the core of the material.

[0029] The intensity of the infrared radians 18, 20 is adjusted such as to be able to bring the temperature of the material of the preform 15 substantially beyond the melting temperature thereof. At the same time, air is injected through the elements of infrared radians 20, 18 in a stream 28 orientated substantially perpendicular to the surface 30 of the preform 15. To achieve this, the facility according to the invention comprises air injection nozzles located between the radians. These air injection nozzles are orientated towards the preform 15, and they are fed using a compressed air network for example.

[0030] The projected air is initially at ambient temperature, and it makes it possible to cool the surface 30 of the composite preform 15 such as to reduce the oxidation of the material, without hindering the action of the infrared radiation through the surface layer. According to an alternative embodiment of the invention, the ambient air is not projected, but a nitrogen neutral gas, such as to expel the air and, as a result, eliminate the presence of oxygen at the surface 30 of the preform 15. In this manner, the possibilities for oxidation of the material are further reduced.

[0031] Thus, through the power of the infrared radians 18, 20, for transmitting the maximum possible heat energy to the composite material, and the action of the projected air that makes it possible to protect the surface 30 of the preform 15, the thermoplastic material is softened and made ductile within extremely short time periods without affecting the surface thereof.

[0032] Advantageously, in the case of a multi-thickness preform, the intensity of the infrared radians 18, 20 is regulated by measuring the surface 30 temperature of the preform 15 on the zone of lesser thickness. In this manner, it is possible to heat the thermoplastic material up to the melting temperature thereof without degradation thereof. Thus, it is possible to decrease by approximately 50% the heating times compared to the solutions according to prior art and it is possible to process composites having various thicknesses and particularly large thicknesses.

[0033] After the material of the preform 15 has been brought to a temperature greater than the melting temperature thereof, in a homogeneous manner, the preform is removed from the heating enclosure 10 through the outlet 16 so that it can be inserted directly inside the forming die 26. The preform 15 is then formed and subsequently cooled using a well-known implementation method, in order to provide a rigid composite piece.

[0034] According to a particularly advantageous method of implementing the invention, the preform 15 is preheated by conduction before being inserted inside the heating enclosure 10. Thus, the facility according to the invention comprises, upstream of the heating enclosure 10, as shown in FIG. 1A, a conduction heating device 32. The latter comprises two heating plates 34, 36 parallel and movable between a position of being spaced apart from one another and a position of being brought close to one another in which they sandwich the multi-thickness preform 15. The heating plates 34, 36 are made of metal and are, for example, provided with electric resistors. Furthermore, they can be preformed to closely fit the entire surface of the preform 15 and preheat it homogeneously.

[0035] In this conduction preheating stage for the preform 15, a large amount of heat energy is supplied throughout the material, and particularly when the preform has a large thickness, in particular with unstrengthened plies. Indeed, conduction is promoted by limiting the air spaces between plies, thanks to the slight pressure of the heating plates 34, 36. These are, of course, brought to a temperature less than the melting temperature of the thermoplastic material. This not only makes it possible to prevent adhesion, between the plates 34, 36 and the material of the preform 15, but moreover, to not promote the oxidation of the surface 30. For example, for a multi-thickness preform of a polyamide-based composite material and with a maximum thickness of 3.5 mm, thanks to the heating plates 34, 36, the preform 15 is preheated to a temperature of 180° C. in 60 seconds.

[0036] Although the preform 15 can have parts of various thicknesses, there is no need to have heating plates 34, 36 fitting the shape of the preform 15. This is indeed due to the fact that the heating plates 34, 36 are in contact with the parts of greater thickness, and consequently, will promote the preheating throughout these parts, while the parts of lesser thickness will be easily brought to core temperature later, and more particularly in the heating enclosure 10.

[0037] Thus, after having been preheated, the preform 15 is transferred inside the heating enclosure 10, in order to be softened in accordance with the arrangements indicated above. Although the temperature of the preform 15 tends to decrease during this transfer, only the surfaces are affected and the infrared radiation of the heating enclosure 10 makes it possible to heat them quickly again. At the end of passing inside the heating enclosure 10, the preform 15 has a temperature that is substantially higher than the melting temperature thereof and homogeneously distributed in all of the parts thereof despite possible differences in thickness.

[0038] Thus, for example, the preform 15 is brought from 180° C. to 250° C. inside the heating enclosure 10 during a period less than 60 seconds. The time spent inside the heating enclosure 10 is thus reduced as it is a matter of supplying heat energy such that the material of the preform 15 gains a few dozen additional degrees. As a result, the time of exposing the material to the infrared radiation is reduced and therefore, even more so, the risks of oxidation of the surface.

[0039] The preform 15 can then be transferred inside the forming die 26. Thus, thanks to the facility according to the invention, the thermoforming cycle times are decreased, for example for a multi-thickness preform of a polyamide-based composite material, with a maximum thickness of 3.5 mm and with a minimum thickness of 1 mm, and the cycle time can be approximately 60 seconds.

[0040] It will be observed that the method, in accordance with the invention, can also be used for forming thermoplastic materials in general.