• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The design of a new type of device for carrying out accelerated aging tests of a coating, in particular an outer coating for an aircraft, making it possible in particular to test the durability of the coating after undergoing all kinds of stresses, is desired. The main object of the invention thus relates to such a device (1) comprising test chambers (2, 3) subjected to different test parameters and / or independently controllable, and comprising light means (6a, 6b ) for generating a photooxidation, the device (1) comprising a support (7) for a sample of the coating (R), movable between the chambers (2, 3) to generate mechanical stresses by thermal shock. The invention has applications in many fields of industry, and preferably in the field of aeronautics.
    公开号:FR3031181A1
    申请号:FR1463352
    申请日:2014-12-26
    公开日:2016-07-01
    发明作者:Stephane Rey；Florent Audoin；Pierre Heberle；Isabelle Multan
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to the field of devices intended for the performance of accelerated aging tests of a coating, and in particular to provide a method for carrying out accelerated aging tests. an aircraft outer coating, this accelerated aging being representative of the aging in service of the coating.
    [0002] The invention thus more specifically proposes a device for carrying out accelerated aging tests of a coating, as well as an associated method. It finds its application primarily in the field of aeronautics, particularly for the characterization of the durability of exterior coatings applied on aircraft. STATE OF THE PRIOR ART For purposes of illustrating the technical context of the invention, FIG. 1 shows, in plan view, an example of an aircraft 10 whose fuselage 11 has an outer covering R. Usually, the outer coatings used in the aircraft, for example a coating R of the type used for the fuselage 11 of the aircraft 10 shown in Figure 1, suffer damage in service. These can be grouped into two main categories, namely the impairments due to optical alteration and the impairments due to mechanical alteration. In the case of optical alteration, the degradations correspond to defects related to a change such as the gloss or the color of the coating. For example, it may be a yellowing and / or loss of gloss of the coating, among others.
    [0003] 3031181 2 In the case of mechanical alteration, the degradations correspond to physical defects of the coating. For example, it may be cracks and / or peeling, among others. The origin of these degradation of the coating can be explained by the combination of several stresses, in particular related to photooxidation, temperature and humidity, and mechanical appearance. Photooxidation is the chemical aging of the coating when it is exposed to solar radiation. The stresses due to temperature and humidity result from a large and rapid variation of temperature and humidity. Finally, the mechanical stresses correspond to the stresses induced by the structure of the aircraft, to which the coating is subjected. To study the degradation of the coating of an aircraft during its lifetime, it is conventional to carry out tests, in particular to characterize the durability of the coating. However, the tests usually performed are often long and take into account only one parameter, typically temperature, humidity or ultraviolet radiation. However, such an approach is not representative of the service behavior of the outer coating, and does not allow to find the damage observed on the coating. In addition, the prior art does not teach a solution for carrying out accelerated aging tests of a coating taking into account the combination or succession of the stresses at the origin of the deteriorations (photooxidation, temperature variation and humidity, mechanical constraints, ...) that it undergoes, and this in order to reproduce these degradations. In fact, there are currently, on the one hand, enclosures which allow for photooxidation on an aircraft coating sample to test its durability under accelerated aging conditions. FIG. 2 illustrates, in section, an exemplary accelerated photoaging chamber 12 according to the prior art for carrying out a photooxidation on an aircraft coating sample R.
    [0004] In this chamber 12, specimens 13 for sampling the coating R are fixed on a support 14 of specimens and subjected to exposure of a xenon lamp 15 inside the support 14, as shown on FIG. FIG. 2. The temperature of the enclosure 12 is, for example, of the order of 55.degree. C. in order to allow the exposure of the specimens 13 to photooxidation and to carry out the durability tests of the coating R after accelerated aging. In addition, there are also, on the other hand, enclosures which make it possible to perform mechanical stresses by thermal shocks on an aircraft coating sample in order to test its durability in an accelerated aging condition. FIG. 3 illustrates, in cross-section, an example of accelerated thermal shock aging chamber 12 according to the prior art for producing mechanical stresses on an aircraft coating sample R. In this type of enclosure 12 are provided two sub-enclosures 12a and 12b, 15 placed one above the other and separated by a wall 16 provided with an opening 16a. Furthermore, a support 14 of samples for sampling the coating R is provided in the enclosure 12. This support 14 is able to move vertically along the double arrow F between the sub-enclosures 12a and 12b in order to subject thermal shocks to the sample samples. The displacement of the support 14 then makes it possible to close the opening 16a of the wall 16 by one of its flanks, as in the case of its positioning shown in dotted lines in FIG. 3 within the sub-enclosure 12b. In order to be able to subject the specimens in the support 14 to thermal shock, the temperature T1 of the sub-enclosure 12a is clearly distinct from the temperature T2 of the sub-enclosure 12b. In particular, the temperature T1 can be chosen around 70 ° C while the temperature T2 can be chosen around -55 ° C. This considerable difference between the temperatures T1 and T2 makes it possible to obtain a thermal shock when the support 14 passes from one sub-enclosure to another. Thus, for example, it is possible to create a thermal shock, at the origin of mechanical stresses on the sample samples of the coating R, by placing the support 14 in the sub-enclosure 12a of temperature T1 equal to about 70 ° C, the lower side of the support 14 closing the opening 16a of the wall 16. Then, the support 14 is moved vertically to the sub-enclosure 12b by all types of means, for example such as inter alia by an articulated arm or by a cylinder pushing the support 14 upwards or downwards, which is at a temperature T2 equal to about -55 ° C., the opening 16a of the wall 16 then being closed by the upper side of the support 14 and the R-coating sampling specimens undergoing the thermal shock of the rapid transition from T1 to T2. Nevertheless, these two types of speakers described above are not entirely satisfactory for obtaining accelerated aging tests of aircraft outer coatings which are sufficiently representative of the actual wear undergone by these coatings. In particular, the prior art does not teach a solution for combining at least these two types of stresses (photooxidation and mechanical stresses by thermal shock) even though this combination of stresses is representative of the actual aging observed in service. SUMMARY OF THE INVENTION There is thus a need to design a new type of device for accelerated weathering of a coating, including an aircraft outer coating, to test the durability of the coating after suffered all kinds of solicitations. In particular, there is a need to provide such a device capable of generating stress on the coating to be tested of different types. The object of the invention is to at least partially overcome the above-mentioned needs and disadvantages relating to the embodiments of the prior art. The object of the invention is therefore, according to one of its aspects, a device for carrying out accelerated aging tests (also called accelerated aging device) of a coating, in particular an outer coating for an aircraft, characterized in that it comprises at least a first test chamber and a second test chamber separated by a movable partition, each chamber being subjected to accelerated aging test parameters, comprising at least the temperature and the reaction rate. humidity, said test parameters being different from one chamber to another and / or independently controllable from one chamber to another, each chamber further comprising light means for generating photooxidation, and in that the device further comprises a support for retaining at least one sample of said coating, the support being movable from the first chamber to the second chamber, and conversely after opening the movable partition between the first and second chambers to generate mechanical stresses by thermal shock. Thanks to the invention, it may be possible to have a device for carrying out accelerated aging tests of coatings which makes it possible to obtain more representative tests of the service behavior of the coatings, in particular decorative external coatings, and thus guaranteeing the durability of the coatings. The device according to the invention thus makes it possible to get as close as possible to the actual circumstances in which the coating is located. Indeed, in the case of an outer coating for aircraft on the ground, the aircraft is subjected to temperatures ranging between about -20 ° C and 50 ° C, and also to exposure to light. In flight, the aircraft is subjected to temperatures of about -55 ° C and also exposure to light.
    [0005] Thus, the aircraft passes from one environment to another, in particular the time of take-off and / or landing. The device according to the invention can reproduce this environment of the aircraft for carrying out accelerated aging tests. The device according to the invention may further comprise one or more of the following features taken singly or in any possible technical combinations. The movable partition between the first and second chambers is advantageously full, that is to say devoid of opening. The absence of opening in the movable partition can provide a better temperature seal between the first and second chambers, and a gain in consumption. Indeed, in this case, no sidewall of the support is subjected to a different temperature.
    [0006] At least one of the luminous means, in particular each luminous means, can be mounted in translation along an axis so as to be able to move towards and away from said at least one sample of said outer coating located in the support.
    [0007] Such an axis may for example be a central axis, or any other type of axis, in particular vertical or not. However, the displacement in translation of each luminous means along its associated axis is advantageously a displacement in a direction perpendicular to the direction of movement of the support between the first and second chambers, in particular a vertical displacement relative to the horizontal plane on which device is placed. Each luminous means advantageously comprises a lamp, in particular a lamp of the xenon or mercury type. The operating system, and in particular the movement system, of one of the luminous means is moreover advantageously independent of the other of the luminous means. In other words, the light means are advantageously controllable independently of each other. The operating system of each light means preferably comprises motorized means for moving the light means 20. The support advantageously comprises an opening, in particular an upper opening, to allow the passage of each light means, namely the movement of each light means from the inside to the outside of the support and vice versa.
    [0008] Furthermore, the device may comprise at least one compartment external to the first and second chambers, in particular a first compartment external to the first chamber and a second compartment external to the second chamber, in which at least one of the luminous means is suitable. to be housed in case of non-use of the light medium. In particular, the device may comprise a first compartment 30 external to the first chamber and a second compartment external to the second chamber, the first luminous means of the first chamber being able to be housed in the first external compartment in case of no use of the first light means, and the second light means of the second chamber being adapted to be housed in the second external compartment in case of non-use of the second light means.
    [0009] Moreover, the possible temperature ranges in the first and second chambers are advantageously different and chosen to generate thermal shocks when passing between the two chambers, the possible temperature range for one of the chambers being in particular between 0 and 250. ° C and the possible temperature range for the other of the chambers being in particular between -70 and 250 ° C. The range of possible humidity levels in the first and second chambers may be identical for both chambers, being in particular between 0 and 100%. Advantageously, the humidity ranges of the first and second chambers can be controlled independently of each other in each chamber. The walls of the movable partition and / or the walls of the first and second chambers may be preferentially thermally insulated to allow the simultaneous operation of the two chambers at different temperatures. On the other hand, at least one of the first and second chambers may include a liquid spray system within the carrier. In addition, the support may include a first support portion and a second support portion, the first support portion for retaining said at least one sample of said coating and being rotatably mounted relative to the second support portion.
    [0010] The second support portion may further comprise support displacement elements, in particular notched wheels cooperating with a displacement rail, in particular a notched rail, the device extending continuously between the first and second chambers. Moving the carrier between the first and second chambers can prevent handling of the carrier in an ambient temperature environment, which would prevent thermal shock. In fact, the time of passage from one chamber to another and the time that the support takes to take the new temperature of the room to which it was moved are equivalent to the time of takeoff and / or landing.
    [0011] In another aspect, the subject of the invention is also a method for carrying out accelerated aging tests on a coating, in particular an outer coating for an aircraft, characterized in that it is implemented by means of a device as defined above, and in that it comprises the realization, one or more times, of a step i) optical stresses by photooxidation and / or a step ii) of mechanical stresses by thermal shock, as described below: i) submission of at least one sample of said coating, retained by the support located in the first chamber or in the second chamber, closed by the movable partition, at the exposure a first luminous means of the first chamber or a second luminous means of the second chamber; ii) the subject of at least one sample of said coating retained by the support located in the first chamber; or in the second chamber, closed by the movable partition, at first accelerated aging test parameters comprising at least a first temperature and a first humidity level, or respectively at second accelerated aging test parameters. comprising at least a second temperature and a second humidity level; then opening the movable partition to allow the support to move from the first chamber to the second chamber, respectively from the second chamber to the first chamber, and closing the movable partition when the support is located in the second chamber, respectively in the first room; and subjecting the second chamber to second accelerated aging test parameters comprising at least a second temperature and a second humidity rate, respectively subjecting the first chamber to first accelerated aging test parameters comprising at least one first temperature and a first humidity level, at least the first and second temperatures being different so as to generate thermal shocks, the temperature difference between the first and second temperatures being in particular greater than or equal to 100 ° C. preferably 120 ° C, more preferably 130 ° C. Moreover, the method may comprise the realization successively of at least one step i) optical stresses by photooxidation and then at least one step ii) mechanical stresses by thermal shock, or vice versa. In addition, the method may optionally comprise, during at least one step i) of optical stresses by photooxidation, the spraying of a liquid in the first chamber or in the second chamber by means of a first system of Spraying liquid, respectively by means of a second liquid spraying system, in particular during a rotation of a first support portion relative to a second support portion of the support. In addition, the method may optionally comprise, during at least one step ii) of mechanical stressing by thermal shock, the subjection of said at least one sample of said coating, retained by the support located in the first chamber or in the second chamber, closed by the movable partition, the light exposure of a first light means of the first chamber, respectively a second light means of the second chamber. The method may also comprise the repetition, in a number n greater than or equal to 2, of all the previously described steps of an accelerated aging cycle so that the process comprises as many accelerated aging cycles as necessary for the definition given for accelerated aging tests of the coating. The device and method according to the invention may comprise any of the previously mentioned features, taken alone or in any technically possible combination with other features.
    [0012] BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood on reading the following detailed description of an example of non-limiting implementation thereof, as well as on examining the figures, diagrams and partial, of the appended drawing, in which: - Figure 1 shows, in plan view, an example of an aircraft whose fuselage comprises an outer coating, - Figure 2 illustrates, in section, an example of an enclosure of photo-aging accelerated by photooxidation according to the prior art for carrying out optical stresses on an aircraft coating sample; FIG. 3 illustrates, in section, an example of thermal shock accelerated aging enclosure according to the prior art for producing mechanical stresses on an aircraft coating sample, and - Figure 4 illustrates, in section, an embodiment of a device according to the invention for the realization of accelerated aging test of an aircraft outer coating. In all of these figures, identical references may designate identical or similar elements. In addition, the different parts shown in the figures are not necessarily in a uniform scale, to make the figures more readable.
    [0013] DETAILED DESCRIPTION OF A PARTICULAR EMBODIMENT An example of implementation of the invention is described below with reference to FIG. 4. FIGS. 1 to 3, relating to the technical context of the invention and to FIG. prior art, have been previously described. FIG. 4 illustrates an exemplary embodiment of a device 1 according to the invention for carrying out accelerated aging tests of an outer coating R for an aircraft. The device 1 is in the form of a test bench comprising a first test chamber 2 and a second test chamber 3 separated by a movable partition 4, movable vertically along the double arrow F1.
    [0014] The two chambers 2 and 3 may be similar in size. Each of the chambers 2, 3 is subjected to accelerated aging test parameters determined according to the production conditions chosen for the tests. These parameters are different for the two chambers 2, 3 and are controllable independently during the tests. In addition, these parameters comprise both the temperature Ta, Tb and the moisture content Rha, Rhb of the two chambers 2, 3. Specifically, the first chamber 2 is subjected to a first temperature Ta high, between 0 and 250 ° C, and in particular of the order of 60 ° C. Meanwhile, the second chamber 3 is subjected to a second low temperature Tb, between -70 and 250 ° C, and in particular of the order of -70 ° C. The important difference in temperature between the first 2 and second 3 chambers aims to create the mechanical stresses through thermal shocks. Moreover, the hygrometry conditions in each of the two chambers 2, 15 3 are such that the first chamber 2 is subjected to a moisture level Rha and that the second chamber 3 is subjected to a moisture level Rhb, which are included 0 and 100%. In addition, in order to ensure the correct operation of the two chambers 2, 3 at different temperatures, the walls of the movable partition 4 and the walls of the first 2 and second 3 chambers are thermally insulated. In addition, as can be seen in FIG. 4, each chamber 2, 3 comprises a light means 6a, 6b for generating the photooxidation on the outer coating sample R. The first 6a and second 6b light means of the first 2 and Secondly, three chambers are in particular constituted by lamps, in particular of the xenon or mercury type. These first 6a and second 6b lamps operate independently, and are particularly controlled in their movements independently. As can be seen in FIG. 4, the first lamp 6a is mounted in translation along a first central axis Xa to allow its vertical movement 3031181 12 from top to bottom, and from bottom to top, according to the double arrow F2. In this way, the first lamp 6a can be moved towards and away from the sample of the coating R. Similarly, the second lamp 6b is mounted in translation along a second central axis Xb to allow its vertical displacement from above at the bottom, and from bottom to top, according to the double arrow F3. In this way, the second lamp 6b can be moved towards and away from the sample of the coating R. To ensure vertical displacements of the first 6a and second 6b lamps, they are associated with a motorized operating system. In addition, the device 1 comprises a first compartment 17a external to the first chamber 2 and a second compartment 17b external to the second chamber 3. These two compartments 17a and 17b are located respectively on the upper surfaces of the first 2 and second 3 chambers . These two compartments 17a and 17b are of smaller size than the first 2 and second 3 chambers. The two compartments 17a and 17b are, for example, each in the form of a rectangular tube. They are respectively connected with the first 2 and second 3 chambers through their opening, respectively to the upper surfaces of the first 2 and second 3 chambers. However, the two compartments 17a and 17b make it possible to close respectively the first 2 and second 3 chambers in a sealed manner.
    [0015] When the first compartment 17a, or the second compartment 17b, communicates with the first chamber 2, respectively the second chamber 3, through its opening, the first compartment 17a and the first chamber 2, respectively the second compartment 17b and the second chamber 3, form a single enclosure.
    [0016] The presence of the first 17a and second 17b compartments makes it possible to bring the first 6a and second 6b lamps closer to the coating R inside the support 7 described below. Thus, the first lamp 6a of the first chamber 2 is adapted to be housed in the first external compartment 17a in case of non-use thereof. Similarly, the second lamp 6b of the second chamber 3 is adapted to be housed in the second compartment 17b external in case of non-use thereof. Furthermore, to ensure the displacement of the first 6a and second 6b lamps from their compartment 17a, 17b respective to the coating sample R, the support 7 of the coating sample R, described below, has an opening 7c upper allowing the passage of each lamp 6a, 6b. Indeed, in order to have the coating sample R intended to undergo accelerated aging to know the durability under the effect of several stresses, the device 1 comprises a support 7 for retaining this sample, for example comparable to a carousel. This support 7 is movable from the first chamber 2 to the second chamber 3, and vice versa, when the movable partition is moved upwards along the arrow F1. In this way, the passage of the support 7 from the first chamber 2 to the second chamber 3 generates mechanical stresses by thermal shock.
    [0017] As can be seen in FIG. 4, the support 7 comprises a first support portion 7a and a second support portion 7b. The first support portion 7a allows the retention of the coating sample R. It is further mounted in rotation along the arrow Ro relative to the second support portion 7b. The first support part 7a is for example in the form of a hollow enclosure provided with a single opening corresponding to the upper opening 7c of the support 7. This first support part 7a can comprise a plurality of internal walls, including a lower inner wall, preferably substantially horizontal, for receiving the coating sample R. These inner walls may further have any type of shape.
    [0018] In addition, the second support portion 7b comprises displacement elements 8 of the support 7, in the form of toothed wheels 8, which cooperate with a notched displacement rail 9 of the device 1. This notched rail 9 can extend between the first 2 and second 3 bedrooms. Furthermore, the first 2 and second 3 chambers also each comprise a spraying system 5a, 5b of liquid inside the support 7, for example water or any other liquid. The spraying of this liquid can be programmed. Finally, the device 1 comprises sensors, particularly thermal and / or hygrometry, for regulating accelerated aging test parameters of the first 2 and second 3 chambers, in particular such as those described below. We will now describe the steps of a method for carrying out accelerated aging tests of an R coating for an aircraft 10, implemented by means of the device 1 described above with reference to FIG. 4. In particular, it is presented below the steps of an aging cycle. Of course, such an aging cycle can be repeated n times according to the definition of the tests to be performed on the coating R. In addition, this repetition of the aging cycle will reproduce the aging in service of the outer coating R with greater accuracy . Moreover, the order of the steps described below can be reversed if necessary.
    [0019] First of all, the method comprises step i) of performing optical stresses by photooxidation. To do this, the sample of the coating R is placed on the support 7, which is located inside the first chamber 2, closed by the movable partition 4. The first lamp 6a is a lamp of the xenon or mercury type, adapted to go up or down along its central axis Xa, the movement being transmitted by a motorized system. The carrying out of the photooxidation then comprises the submission of the sample of the coating R to the light exposure of the first lamp 6a. During this exposure, the first chamber 2 is subjected to the first accelerated aging test parameters, namely a first temperature Ta of between 0 and 250 ° C., and for example of the order of 70 ° C., and first moisture content Rha between 0 and 100%. These first accelerated aging test parameters are regulated by means of sensors of the device 1. Moreover, during the rotation of the first support portion 7a of the support 7 with respect to the second support portion 7b forming a base, that is, during the rotation of the first support portion 7a around the first lamp 6a, a liquid spray is performed by means of the first liquid spraying system 5a of the first chamber 2. At the end of the first exposing the sample of the coating R to the first lamp 6a, this first lamp 6a automatically rises upwards to go to the first compartment 17a. Then, the method comprises opening the movable partition 4 to allow the support 7 to move from the first chamber 2 to the second chamber 3. To do this, the second support part 7b moves via its wheels notch 8 on the notched rail 9 extending from the first chamber 2 to the second chamber 3. The method then comprises closing the movable partition 4 when the support 7 is located in the second chamber 3. In this way, the two rooms 2, 3 are isolated from each other. It should be noted that, in this example, the opening and closing of the movable partition 4 are made by vertical displacement of the movable partition 4. However, alternatively, the movable partition 4 could be moved laterally. It is therefore possible to perform step ii) of the method according to the invention consisting in producing mechanical stresses by thermal shock. To do this, step ii) comprises subjecting the second chamber 3 to 20 of the second accelerated aging test parameters, namely a second temperature Tb of between -70 and 250 ° C., and for example of order of -70 ° C, and a second Rhb moisture content between 0 and 100%. These second accelerated aging test parameters are regulated by means of sensors of the device 1.
    [0020] As can be seen, the second temperature Tb is significantly lower than the first temperature Ta so as to generate mechanical stresses by means of thermal shocks. Furthermore, the sample of the coating R can also be subjected to the light exposure of the second lamp 6b of the second chamber 3 closed by the movable partition 4. This second lamp 6b can also be a lamp of the type 3031181 16 xenon or mercury. It is able to move vertically, to go up and / or down, along its central axis Xb, the movement being transmitted by a motorized system. A liquid spray can also be performed using a second liquid spray system 5b located in the second chamber 3. At the end of the exposure of the sample of the coating R in the light of the second 6b lamp, the lamp 6b is moved upwards to be housed in the second compartment 17b automatically. The aging cycle is thus finalized and can be repeated a multitude of times in order to accurately reproduce aging in service. Thus, advantageously, the exposure of the outer coating sample (s) R is feasible both in the first chamber 2 and in the second chamber 3. Advantageously, the method according to the invention described above may allow to reproduce on at least one surface coating sample R for aircraft 10 the photooxidation of the coating R and the mechanical stresses to which the coating R is subjected thanks to the test parameters such as the temperature Ta, Tb and the moisture content Rha, Rhb, exposure to lamps 6a, 6b, liquid exposure of spray systems 5a, 5b, and the important differences between these parameters, especially between the two temperatures Ta and Tb, to create thermal shocks.
    [0021] Of course, the invention is not limited to the embodiment which has just been described. Various modifications may be made by the skilled person.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. Device (1) for carrying out accelerated aging tests of a coating (R), in particular an outer coating (R) for an aircraft (10), characterized in that it comprises at least a first test chamber ( 2) and a second test chamber (3) separated by a movable partition (4), each chamber (2, 3) being subjected to accelerated aging test parameters, comprising at least the temperature (Ta, Tb) and the humidity level (Rha, Rhb), said test parameters being different from one chamber to another and / or independently controllable from one chamber to another, each chamber (2, 3) comprising in addition to a light means (6a, 6b) for generating a photooxidation, and in that the device (1) further comprises a support (7) for retaining at least one sample of said coating (R), the support (7) being movable from the first chamber (2) to the second chamber (3), and vice versa, after opening the partition wall island (4) between the first (2) and second (3) chambers to generate mechanical stresses by thermal shock.
    [0002]
    2. Device according to claim 1, characterized in that at least one of the light means (6a, 6b), in particular each light means (6a, 6b), is mounted in translation along an axis (Xa, Xb) so as to be able to move towards and away from said at least one sample of said outer coating (R) located in the support (7).
    [0003]
    3. Device according to claim 1 or 2, characterized in that each light means (6a, 6b) comprises a lamp, in particular a lamp of the xenon or mercury type.
    [0004]
    4. Device according to one of the preceding claims, characterized in that it comprises a first outer compartment (17a) to the first chamber (2) and a second outer compartment (17b) to the second chamber (3), the first luminous means (6a) of the first chamber (2) being adapted to be housed in the first external compartment (17a) in case of non-use of the first light means (6a), and the second light means (6b) of the second chamber (3) being adapted to be housed in the second outer compartment (17b) in case of non-use of the second light means (6b). 5
    [0005]
    5. Device according to any one of the preceding claims, characterized in that the light means (6a, 6b) are controllable independently of each other.
    [0006]
    6. Device according to any one of the preceding claims, characterized in that the temperature ranges (Ta, Tb) possible in the first (2) and second (3) chambers are different and chosen to generate thermal shocks in passing. between the two chambers (2, 3), the temperature range (Ta) possible for one (2) of the chambers (2, 3) being in particular between 0 and 250 ° C and the temperature range (Tb) possible for the other (3) of the chambers (2, 3) being in particular between -70 and 250 ° C.
    [0007]
    7. Device according to any one of the preceding claims, characterized in that the range of humidity levels (Rha, Rhb) possible in the first (2) and second (3) chambers is identical for the two chambers (2, 3) being in particular between 0 and 100%.
    [0008]
    8. Device according to any one of the preceding claims, characterized in that the walls of the movable partition (4) and / or the walls of the first (2) and second (3) chambers are thermally insulated to allow simultaneous operation. two chambers (2, 3) at different temperatures.
    [0009]
    9. Device according to any one of the preceding claims, characterized in that the support (7) comprises a first support portion (7a) and a second support portion (7b), the first support portion (7a) allowing the Retaining said at least one sample of said coating (R) and being rotated relative to the second support portion (7b).
    [0010]
    10. Device according to claim 9, characterized in that the second support portion (7b) comprises displacement elements (8) of the support (7), in particular toothed wheels cooperating with a displacement rail (9), in particular a notched rail, the device (1) extending continuously between the first two (2) and second (3) chambers. 10
    [0011]
    11. A method for carrying out accelerated aging tests of a coating (R), in particular an outer coating (R) for an aircraft (10), characterized in that it is implemented by means of a device ( 1) according to any one of the preceding claims, and in that it comprises the realization, one or more times, of a step i) optical stresses by photooxidation and / or a step ii) of 15 mechanical stresses by thermal shocks, as described below: i) subjecting at least one sample of said coating (R) retained by the support (7) located in the first chamber (2) or in the second chamber (3), closed by the movable partition (4), at the luminous exposure of a first luminous means (6a) of the first chamber (2), or respectively of a second luminous means (6b) of the second chamber (3) , ii) subjecting at least one sample of said coating (R) retained by the support (7) located in the first chamber (2) or in the second chamber (3), closed by the movable partition (4), at first accelerated aging test parameters comprising at least a first temperature (Ta) and a first humidity level 25 (Rha), or respectively to second accelerated aging test parameters comprising at least a second temperature (Tb) and a second humidity level (Rhb); then opening the movable partition (4) to allow the support (7) to move from the first chamber (2) to the second chamber (3), respectively from the second chamber (3) to the first chamber (2), and closing the movable partition (4) when the support (7) is located in the second chamber (3), respectively in the first chamber (2); and subjecting the second chamber (3) to second accelerated aging test parameters comprising at least a second temperature (Tb) and a second humidity level (Rhb), respectively subjecting the first chamber (2) to first accelerated aging test parameters comprising at least a first temperature (Ta) and a first humidity level (Rha), at least the first (Ta) and second (Tb) temperatures being different so as to cause shocks thermal.
    [0012]
    12. Method according to claim 11, characterized in that, in step ii) 10 of mechanical stresses by thermal shock, the temperature difference between the first (Ta) and second (Tb) temperatures is greater than or equal to 100 ° C, preferably 120 ° C, more preferably 130 ° C.
    [0013]
    13. The method of claim 11 or 12, characterized in that it comprises the realization successively of at least one step i) optical stresses by photooxidation then at least one step ii) mechanical stresses by thermal shock, Or vice versa.
    [0014]
    14. Method according to one of claims 11 to 13, characterized in that it comprises, during at least one step i) optical stresses by photooxidation, the spraying of a liquid in the first chamber (2 ) or in the second chamber (3) by means of a first spraying system (5a) of liquid, respectively by means of a second spraying system (5b) of liquid, in particular during a rotation of a first support portion (7a) relative to a second support portion (7b) of the support (7).
    [0015]
    15. Method according to any one of claims 11 to 14, characterized in that it comprises, during at least one step ii) of mechanical stresses by thermal shock, the subject of said at least one sample of said coating (R ), Retained by the support (7) located in the first chamber (2) or in the second chamber (3), closed by the movable partition (4), to the light exposure of a first light means ( 6a) of the first chamber (2), respectively a second light means (6b) of the second chamber (3).
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    同族专利:
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    US20160187247A1|2016-06-30|
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    法律状态:
    2015-12-21| PLFP| Fee payment|Year of fee payment: 2 |
    2016-07-01| PLSC| Publication of the preliminary search report|Effective date: 20160701 |
    2016-12-22| PLFP| Fee payment|Year of fee payment: 3 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 4 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-12-23| PLFP| Fee payment|Year of fee payment: 7 |
    2021-12-24| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1463352A|FR3031181B1|2014-12-26|2014-12-26|DEVICE FOR REALIZING AN ACCELERATED AGING TEST OF A COATING BY MULTIPLE TYPES OF SOLICITATIONS|FR1463352A| FR3031181B1|2014-12-26|2014-12-26|DEVICE FOR REALIZING AN ACCELERATED AGING TEST OF A COATING BY MULTIPLE TYPES OF SOLICITATIONS|
    US14/977,963| US10180391B2|2014-12-26|2015-12-22|Devices and methods for conducting accelerated aging tests of a coating with several types of stresses|
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