• 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:
    An aircraft antenna assembly (3) having a support member (6) having first and second surfaces (7, 8) on opposite sides thereof, at least an antenna element disposed on or in the support member (6) and a sealing device (15). The first surface (7) and the sealing device (15) are configured so that the antenna assembly (3) can be arranged on a portion (9) of the outer skin of an aircraft so as to in that the first surface (7) faces the portion (9) of the outer skin, that the sealing device (15) is located between the support member (6) and the portion (9) of the skin and at least one cavity (16) is defined by the sealing device (15), the portion (9) of the outer skin and the first surface (7). Figure for abstract: Figure 2
    公开号:FR3077684A1
    申请号:FR1901207
    申请日:2019-02-07
    公开日:2019-08-09
    发明作者:Christian Schaupmann；Markus Altmann
    申请人:Airbus Operations GmbH；
    IPC主号:
    专利说明:

    Description
    Title of the invention: Antenna assembly for aircraft [0001] The present application relates to an antenna assembly for aircraft which has a support element and at least one antenna element disposed on or in the support element, and an aircraft with such an antenna assembly.
    Planes typically have one or more antennas that establish a radio link between the plane and external devices or correspondents on the ground or in the air, for example other planes or satellites.
    In the prior art, these antennas have been mounted inter alia on the outside, on the fuselage of the aircraft, so that they extend well beyond the fuselage of the aircraft, in the air which surrounds the latter. As a result, not only does the airplane's resistance to air increase, but aerodynamic forces also act on the antennas and try to detach the antenna from the fuselage. Therefore, to ensure secure attachment of the antennas, important arrangements must be made which are often complicated and / or associated with heavy weight. Numerous antenna elements are for example fixed to the fuselage by means of a relatively heavy weight base plate which protrudes into the surrounding air at the same time as the antenna element itself.
    In other embodiments, elements of these antennas are integrated directly into the outer skin of the aircraft fuselage, being provided as a layer of a multilayer outer skin. Maintenance work on these antennas and replacement after manufacture are complicated.
    A problem underlying the present invention is therefore to provide an antenna assembly for aircraft which has a simple and economical structure, which is easy to install and maintain and whose weight is reduced, as well as a airplane with such an antenna assembly.
    This problem is solved with an antenna assembly for aircraft which has a support element provided with a first and a second surface located on opposite sides of the support element, at least one element of antenna disposed on or in the support member and a sealing device, in which the first surface and the sealing device are configured so that the antenna assembly can be disposed on a part of the outer skin of an aircraft so that the first surface faces the part of the outer skin, the sealing device is located between the support element and the part of the outer skin and that at least one cavity is defined by the sealing device, the part of the outer skin and the first surface. In addition, the support element or the sealing device has, for each of the cavities, at least one flow channel provided with a first and a second opening situated at opposite ends of the flow channel, which, after the placement of the antenna assembly on the part of the outer skin, mutually connects the corresponding cavity and the environment of the antenna assembly and which opens in the corresponding cavity at the level of the first opening and in the environment at the second opening.
    Advantageously, in the antenna assembly the second opening is formed by at least one of the flow channels on a guide part in which a part of the flow channel extends and which projects beyond the support element or sealing device in the environment after placing the antenna assembly on the part of the outer skin.
    Preferably, the second opening is formed by at least one of the flow channels in the second surface or in the sealing device.
    Additionally, the support element may be a flat and / or flexible element.
    Advantageously, the first surface has at least one recess, each of which defines one of the cavities after the placement of the antenna assembly on the part of the outer skin.
    Preferably, the support element has for each of the recesses a rigid lining which defines the recess concerned.
    Advantageously, each of the antenna element (s) is a panel antenna and / or a so-called KU or KA antenna.
    Advantageously, each of the antenna element (s) is printed on the support element or on a part of the latter.
    Preferably, the second surface has at least one enhancement in which is arranged at least one electrical conductor and / or at least one fixing element or which is formed by at least one electrical conductor and / or at least one fixing element , the second opening of at least one of the flow channels being disposed on the riser or in a position immediately adjacent to the riser.
    Advantageously, one or more elements conducting heat or electricity are provided on or in the support element, each of them forming a part of the first surface or projecting from the first surface so that the elements conducting heat or electricity are in contact with the outer skin portion after placing the support member on the outer skin portion.
    Preferably, the assembly also has a part of the outer skin of an aircraft, the support element being arranged on the part of the outer skin so that the first surface is turned towards the part of the outer skin, that the sealing device is located between the support element and the portion of the outer skin and that the cavity or cavities are defined by the sealing device, the portion of the outer skin and the first surface.
    Advantageously, one or more bores through which cables have passed or can be passed are provided in the part of the outer skin, the bores being arranged outside the region of the part of the outer skin covered by the support element.
    Preferably, a hollow in which the antenna assembly is arranged is provided in the part of the outer skin.
    In a second aspect of the invention, an aircraft is provided with an outer skin and an antenna assembly as defined above in which the support element is disposed on a part of the skin outer such that the first surface faces the portion of the outer skin, the sealing device is located between the support element and the portion of the outer skin and the cavity or cavities are defined by the device sealing, the outer skin part and the first surface.
    An antenna assembly for an airplane or an airplane has a support element provided with a first and a second surface situated on opposite sides of the support element, one or more elements of antenna arranged on or in the support element and a sealing device.
    The first surface and the sealing device are configured so that the antenna assembly can be arranged on a part of the outer skin of an aircraft so that the first surface is turned towards the part of the outer skin, that the sealing device is located between the support element and the part of the outer skin and is for example in particular between the first surface and the part of the outer skin and that one or more several cavities are defined by the sealing device, the part of the outer skin and the first surface. Thus, the part of the outer skin may for example have a shape which corresponds to the first surface, so that the shape of the first surface defines the shape of the parts of the outer skin which are suitable for use with the element of particular support and the particular antenna assembly. As a variant or in addition, the sealing device also makes it possible to adapt the shape of the first surface to the shape of the part of the outer skin. In an advantageous embodiment to which we will extend still further, the support element and preferably the entire antenna assembly are however flexible and in particular in the form of a mat or film, so that they can adapt to different parts of the outer skin. Independently of this, the sealing device may for example have one or more sealing elements, an adhesive material and / or a part of the support element or be formed by them, and be adapted or intended to be installed on part of the outer skin.If more than one cavity is provided, they will be separated from each other after placing the support element on the part of the outer skin so that no air flow is possible between the different cavities. Sealing can for example be obtained by the sealing device.
    For each of the cavities, the support element or the sealing device has at least one flow channel provided with a first and a second opening situated at opposite ends of the flow channel, each of these flow channels preferably extending in the support element or in the sealing device. Each of the flow channels is configured and arranged so that after placing the antenna assembly on the part of the outer skin, it connects the corresponding cavity to the environment of the antenna assembly and opens in the corresponding cavity at the first opening and in the environment at the second opening. Thus, the first opening, which is preferably formed in the first surface, connects the corresponding cavity and the flow channel so that air from the cavity can flow into the flow channel through the first opening. . Similarly, the second opening connects the flow channel to the environment of the antenna assembly so that air from the flow channel can flow into the environment through the second opening. After placing the antenna assembly on the part of the outer skin, the sealing device seals the cavity or cavities so that a flow of air cannot escape from the cavity or cavities only through one of the flow channels associated with the cavity concerned.
    Thus, after the placement that has been described of the support element on a part of the outer skin of an airplane, when the airplane is flying, the second openings of the flow channels are scanned by the air and act as the suction openings of a jet pump, so that the corresponding flow channels act as suction channels through which a pressure below ambient pressure is established in the corresponding cavities and thus exerts a holding force which firmly holds the support element and the antenna assembly on the outer skin and which opposes the detachment forces which result from the aerodynamic forces. As these latter detachment forces are produced by the air flow which forms the depression and the depression is thus greater the greater the aerodynamic effects which lead to the detachment forces, it is advantageously obtained that the antenna assembly automatically and passively opposes the detachment forces. The holding force acts globally against a detachment or automatically prevents it. In the flexible configuration provided in a preferred embodiment of the support element, in particular in the form of a flexible mat or film, it is moreover advantageously possible to oppose or prevent the cleaning. Overall, it is advantageous that the flow channels and the second openings are arranged in such a way that when the antenna assembly is swept by the air in a predetermined direction after the placement described on a part of the outer skin, the flow takes place through the second openings of all the flow channels. The antenna assembly will then preferably be oriented on the part of the outer skin so that when the plane concerned flies, the antenna assembly is swept in the predetermined direction. The predetermined direction may in particular be opposite to the direction of flight.
    The cavities can simply be sized, configured and arranged so as to cover a sufficient part of the first surface and appropriate parts of the first surfaces, so that the holding force is sufficient for the intended application. As the conditions prevailing in operation are essentially static and are conditions in which only the air which penetrates into the cavities through leaks is sucked in to maintain the vacuum in the cavities, the volume of the cavities is relatively small. important compared to the covering of the first surface by the cavities, their shape and their distribution.
    The antenna assembly which is described has the advantage of being able to be fixed in a reliable and simple manner on the outer skin of an aircraft, for example on the outer skin of the fuselage of the aircraft or of a other part of the structure, for example a wing or a rudder. In particular, one can do without a bonded bond or at least a bonded bond over a large area, as well as high-weight fixing mechanisms. The bonded connections have the disadvantage that the compatibility between the adhesive used and the material of the antenna assembly must be taken into account, which considerably limits the range of materials because the materials must also satisfy other requirements. , for example in terms of dielectric properties, aging of the material, thermal stability, elasticity and thermal conductivity. Large bonded connections are also difficult to maintain and repair, can prevent access for example to riveted connections located below the antenna assembly, favor the appearance of mechanical stresses in the assembly. antenna during deformations occurring during operation on the outer skin located below, can lead during normal air outlet through the outer skin to the formation of bubbles or local detachment forces and are difficult to achieve without inclusions d that can degrade their stability. The present antenna assembly eliminates these disadvantages.
    It is only necessary to connect the antenna assembly to the outer skin or to fix it on the latter by certain parts, that is to say only at one or more relatively small points or sections separated from each other. others, because the antenna assembly advantageously has a mechanism which opposes in flight the detachment forces produced in operation by the flow of air over the antenna assembly an opposite holding force which is also formed by this same air flow. Thus, the holding force increases when the flow speed and therefore the release force increases. The fixing can take place for example by holding clips which extend on the support element or on the outer skin, by a stiffening element or a stiffening structure of the aircraft which is located below the skin exterior or by a bonded bond which will not then extend over the entire surface.
    It is also possible to use flexible antenna elements and flexible antenna structures for which a solution with an adapter plate would lead to an unbearably high weight.
    Electrical conductors, electrical connection terminals, ground connection elements, shielding elements and / or waveguides are preferably arranged in or on the support element. They can for example be incorporated into a material of the support element, for example a flexible film material, and / or be arranged on the second surface.
    Thus, several separate cavities are provided so that if a leak occurs on a cavity and causes a decrease or failure of the holding force at this cavity, the other cavity (s) will not be concerned. As a variant or in addition, it is preferable to provide for each cavity several separate flow channels, so as to obtain for each cavity a redundancy in terms of flow channels and so that a vacuum can still be formed in case a flow channel becomes blocked.
    The second opening of one, more or all of the flow channels is formed on a guide section in which a part of the flow channel extends and which projects into the environment from the element. support after placing the antenna assembly on the part of the outer skin, and for example in particular from the second surface of the support element or of the sealing device. This embodiment has the advantage of allowing a particularly simple way to place the second opening in a controlled manner in a position and / or an orientation in which the aerodynamic effects which cause the suction effect are sufficiently large or maximum when the the antenna assembly is swept by air.
    Alternatively or additionally, the second opening of one, several or all of the flow channels is formed in the second surface or in the sealing device. In the case where it is formed in the second surface, the second opening opens in the environment adjacent to the second surface or the second surface connects the environment and the flow channel, so that the air in the channel flow can flow into the environment through the second opening. The support element may be a flat element. In other words, it has two opposite extended surfaces kept at a distance from each other in the thickness direction, the thickness being much smaller than the extension of the surfaces. The thickness can for example be from 1 to 5 cm. The support element can be configured for example in the form of a plate, carpet or film. Thanks to its flat configuration, the antenna assembly can advantageously be placed on the outer skin without greatly increasing the air resistance if the antenna element or the antenna elements are integrated in the support element or configured so that they do not protrude very much or not far from the second surface of the support member. This last result can be obtained for example by printing the antenna elements on the support element or by providing them as conductive tracks or conductive coatings on the support element.
    In particular, but not exclusively, when the support element is a flat element such as that described above, the support element and therefore preferably the entire antenna assembly are flexible. Flexibility can then be provided over the entire support element or over the entire antenna assembly or at least along at least one direction of the first surface. One can however also imagine that the support element or the antenna assembly is flexible in sections. The support element may preferably have a flexible material, for example a flexible plastic material, in the form of a film or a carpet, in which the antenna elements are incorporated or on which the antenna elements are fixed or printed. The support element is then preferably completely in the form of a carpet or film, is for example a film and in particular a film component or has a film and in particular a film component. It must be kept in mind that overall and also in this embodiment, a flexible configuration of the support element is possible while providing in the support element a reinforcing structure arranged so that the loads occurring in operation are conducted at predetermined points or parts of the support element which can then be used as fixing locations for fixing the support element on the outer skin or on a stiffening structure located below the latter. However, such a reinforcing structure need not be present.
    Alternatively or cumulatively with what has been described above, in particular when the support element is flexible and preferably flat, the first surface has one or more recesses, each of which defines at least in part but preferably completely one of the cavities after placing the antenna assembly on the part of the outer skin. The hollows define the cavities after placement on a part of the outer skin also when the first surface is located outside the hollows on the outer skin, but the sealing device can still be placed between the first surface and the skin. exterior. The antenna assembly can then also be defined independently of its placement on the outer skin, as follows: the antenna assembly for aircraft or an aircraft has a support element provided with a first and a a second surface located on opposite sides of the support element, one or more antenna elements arranged on or in the support element and a sealing device. The sealing device is in contact with the support element and preferably with the first surface or can be brought into contact with the latter. The first surface has the recess (s). For each of the recesses, the support element or the sealing device has at least one flow channel provided with a first and a second opening at the opposite ends of the flow channel, each of these channels flow preferably extending in the support member or in the sealing device. Each of the flow channels is configured and arranged so that it mutually connects the corresponding recess and the environment of the antenna assembly outside the recess or on another side of the support member and that it opens in the hollow corresponding to the level of the first opening and in the environment outside the hollow at the level of the second opening. Thus, the first opening, which is preferably formed in the first surface, connects each recess and the flow channel so that air from the recess can flow into the flow channel through the first opening. Similarly, the second opening connects the flow channel and the environment of the antenna assembly so that air from the flow channel can flow into the environment through the second opening even if the hollow concerned is covered or closed in an airtight manner. All the other structural configurations described here also remain valid for this description. The antenna assembly thus described can be arranged in the manner described on a part of the outer skin of an aircraft.
    In an antenna assembly, in which the support element is flexible as described and in which the support element has, as described, one or more recesses in the first surface, the support element defines for each of the hollows a rigid lining which defines the hollow. In other words, the wall of each hollow is formed by the lining. These linings ensure that the cavities or recesses also have predetermined shapes and dimensions in the lining despite the flexible configuration of the support element. This configuration is particularly advantageous for embodiments in which the support element has a flexible material in the form of a film or a carpet and in which the antenna elements are incorporated or on which the antenna elements are fixed.
    Each of the antenna elements can be a panel antenna and / or a so-called KU or KA antenna. On antennas working in the millimeter range, the present invention has the particular advantage of being able to reliably prevent local deformations or a ridge which could considerably degrade the operation of these antennas.
    In particular, when the support element is flat and flexible, but not exclusively, it is preferably a film or a film component or has these, the antenna element or each of the elements d antenna is printed on the support element or on a part of the latter.
    The second surface may have at least one enhancement in which at least one electrical conductor and / or at least one fixing element are arranged or by which at least one electrical conductor and / or at least one fixing element are formed. The second opening of at least one of the flow channels is disposed on the riser or is directly adjacent to the riser. For example, a guide section protruding from the second end of which the second opening is located can be arranged in the immediate vicinity of the raising or extend there. High local pressures occur in the direction of flow on these risers so that at the risers, the aerodynamic effects can be particularly high and positively influence the suction effect exerted on the second openings.
    One or more elements conducting heat or electricity can be provided on or in the support element, each forming a part of the first surface or projecting from the first surface so that after the element support has been placed on the outer skin, the elements conducting heat or electricity are in contact with the outer skin. This allows heat and electricity to be exchanged between the outer skin and the antenna assembly.
    The antenna assembly may further have a part of the outer skin of an aircraft which therefore corresponds to the part of the outer skin described above. The support element is arranged on the part of the external skin so that the first surface faces the part of the external skin, so that the sealing device is located between the support element, for example in particular the first surface, and the part of the outer skin and at least one cavity is defined by the sealing device, the part of the outer skin and the first surface.
    Additionally, it is further preferable to provide in the outer skin one or more bores through which cables have passed or may be, the bores being arranged outside the region of the outer skin covered by the support element or antenna assembly. This embodiment has the advantage of being less demanding in terms of pressure sealing of the openings after the cables have passed through. In the arrangement below the support member, it had to be ensured that air could not enter one of the cavities through the openings.
    Alternatively or in addition, it is also preferable in this embodiment to provide in the part of the outer skin a hollow in which is disposed the antenna assembly. This can preferably be done by placing the second edge surface relative to parts of the outer skin on the edge of the hollow.
    In an aircraft having an outer skin and an antenna assembly as described above, the part of the outer skin described above is then a part of the outer skin of the aircraft. The support element is arranged there on the part of the outer skin so that the first surface faces the part of the outer skin, so that the sealing device is located between the support element, for example in particularly the first surface, and the part of the outer skin and that at least one cavity is defined by the sealing device, the part of the outer skin and the first surface. The antenna assembly is configured, arranged and oriented so that when the aircraft is in flight, the suction effect is achieved as described by air sweeping the antenna assembly at the second openings.
    The invention will now be explained in more detail with reference to the figures in which two exemplary embodiments have been shown.
    [Fig.l]
    FIG. 1 represents a schematic perspective view of the exterior skin of an aircraft provided with an antenna assembly according to the invention;
    [Fig.2]
    Figure 2 shows a schematic cross-sectional view of an antenna assembly according to a first embodiment of the present invention;
    [Fig.3]
    Figure 3 shows a schematic cross-sectional view of an antenna assembly according to a second embodiment of the present invention;
    [Fig.4]
    Figure 4 shows a schematic cross-sectional view of an antenna assembly according to a third embodiment of the present invention; and [fig. 5]
    FIG. 5 represents a schematic cross-sectional view of an antenna assembly according to a fourth embodiment of the present invention.
    The aircraft 1 shown in Figure 1 has a fuselage 2 and an antenna assembly 3 according to the invention. In addition to the antenna assembly 3, there has also been shown for illustrative purposes conventional sheet antennas 4 which are fixed from the outside to the fuselage 2 and project beyond the fuselage 2. However, the the antenna assembly 3 of the illustrated embodiment is configured as a flat and flexible film component and is arranged from the outside on a section of the outer skin 5 of the fuselage 2. In this way, the resistance to air of the fuselage 2 is not or not much increased by the antenna assembly 3. In FIG. 1, the antenna assembly 3 is arranged by way of example on the upper side of the fuselage 2. The antenna assembly may however also be located in any other location of the fuselage 2, for example on one side or on its underside, but also in other locations of the aircraft, for example a wing or a rudder .
    The antenna assembly 3, a first embodiment of which is shown in section in FIG. 2, has a support assembly 6 which is provided in the form of a flat and flexible film or of a component in flat and flexible film, which may for example have a thickness of 1 to 5 cm. In the figures, the support assembly 6 is shown at an exaggerated thickness, for reasons of representation. The support assembly 6 may have a layer of flexible material or several layers of one or more flexible materials arranged one above the other. The support assembly 6 has a first surface 7 and a second surface 8 provided on opposite sides of the support assembly 6 and which are kept at a mutual distance in the thickness direction of the support assembly 6. The first surface 7 and the second surface 8 are the two extended surfaces of the film or of the film component. The support assembly 6 is disposed and fixed on a part 9 of the outer skin 5 of an aircraft so that the first surface 7 faces the part 9 of the outer skin and the second surface 8 is not located on the side of part 9 of the outer skin. The fixing is carried out by means not shown, only at certain points distant from each other, for example by gluing or by retaining hooks which extend on the second surface 8 and on both sides of the support assembly 6 on part 9 of the outer skin or of a stiffening structure located below the latter.
    The aircraft may in particular be the aircraft 1 shown in Figure 1 and the antenna assembly 3 is then oriented and positioned, for example in the position shown in Figure 1, so that when the airplane 1 is in flight, the air attacks the support assembly 6 and the antenna assembly 3 in the direction indicated by the arrow 10 and scans the latter in this direction 10. To obtain good flow conditions and keep as small as possible the aerodynamic effects which lead to the action on the support assembly 6 of forces which try to raise it or detach it from the part 9 of the outer skin, the front edge 11 of the assembly support 6 oriented in the direction opposite to the flow direction 10 is chamfered, as is the opposite rear edge 12. These detachment forces come not only from the incidence of flow at the level of the front edge 11 but and especially also by the flow air on the support assembly 6 which projects beyond the part 9 of the outer skin and which exerts on the support assembly 6 a suction effect which acts upwards in FIG. indicated in Figure 2 by the arrows 13, the thickness of which indicates the intensity of the force which acts on the support element due to the ambient pressure. It can be seen that these forces are much greater at the edge edge 11 than in the rest of the support assembly 6. At the edge edge 11, the pressure due to the deflection of the air flow towards the top is greater than the pressure of the environment and can represent for example 200% of the pressure of the environment, while in the rest of the support assembly 6, the pressure is less than the pressure of the environment and can be worth for example 50% of the pressure of the environment, so that a release force is applied to the support assembly 6.
    A recess 14 is formed in the first surface 7 and a seal 15 is disposed around the edge of the support assembly 6 between the first surface 7 and the part 9 of the outer skin. Therefore, a cavity 16 which essentially corresponds to the recess 14 is formed between the first surface 7, the part 9 of the outer skin and the seal 15. The seal 15 can be configured so that the first surface 7 rests on the part 9 of the outer skin outside the recess 14, so that the cavity 16 corresponds to the recess 14. In this case, the air leaving the cavity 16 or the recess 14 does not can reach the environment only through two flow channels 17 which extend in the thickness direction of the support assembly 6. Each of the flow channels 17 has at one of its ends a first opening 18 which opens in the hollow 14 or the cavity 16 and at its opposite end a second opening 19 which opens in the environment. The second opening 19 is provided on a rigid guide section 20 which projects from the second surface 8 and into which extends part of the corresponding flow channel 17.
    By sweeping the support assembly 6 and the antenna assembly 3 by air when the plane 1 is flying, a suction effect which sucks the air out of the recess 14 or the cavity 16 by the flow channels 17 and which in this way exerts a depression there between the first surface 7 and the part 9 of the outer skin is caused at the level of the second openings 19 in a similar manner to the principle of a jet pump of water. This depression is less than the pressure 13 which acts on the second surface 8, in the manner indicated by the arrows 21. As a result, a force, directed downwards in the region of the hollow 14 or the cavity 16 is obtained. Figure 2, which acts on the support assembly 6 to push the support assembly 6 and the antenna assembly 3 against the part 9 of the outer skin and which thus represents a holding force which opposes the peeling forces. This is produced by the same air flow as the detachment forces and increases for example in proportion to the latter. This significantly reduces what is required of another fixing of the support assembly 6 on the part 9 of the outer skin. It is thus possible to remove a bonding over the entire surface between the support assembly 6 and the part 9 of the outer skin.
    In the embodiment shown, the second opening 19 is oriented in the direction of flow 10 so that air vortices allow to obtain a particularly high suction effect on the support assembly 6 and on the guide section 20. The arrangement and orientation of the second openings 19 can be selected flexibly, so that for the intended application and a predetermined direction 10 of air sweeping, one obtains a suction effect of an appropriate level on the second openings 19.
    On the second surface 8 of the support element 6, several antenna elements 21 are printed in the form of panel antennas and electrical conductors 22 for the panel antennas 21 can be incorporated in the material of the support assembly 6 (not shown in Figure 2, see Figures 3 and 5).
    A second embodiment of the antenna assembly 3 has been shown in cross section in Figure 3. This embodiment is largely similar to the embodiment shown in Figure 2, so that the 'We will only expand on their differences.
    The antenna assembly 3 of Figure 3 has a channel 23 which extends over at least part of the width of the support assembly 6 and part of which is part of the enhancement 24 which extends beyond the second surface 8. In the channel 23 may extend for example electrical conductors or a fixing bracket which extends over the entire width of the support assembly 6 and projects from the latter on both sides, in order to be able to these locations, be connected to the part 9 of the outer skin or to a stiffening structure of the airplane 1 located below the latter, to fix the support assembly 6 on the part 9 of the outer skin. The enhancement 24 constitutes a disturbance for the air flow which scans the support assembly 6 in the direction 10, and one of the guide parts 20 as well as the second opening 19 are arranged in position immediately adjacent to the fuselage 24 and behind the latter in the direction of air flow. This improves the suction effect on the second opening 19. The riser 24 can shrink downward in the direction opposite to the direction of air flow or have another suitable shape, at the times to keep the increase in air resistance small and improve the suction effect.
    In Figure 3, the panel antennas 21 are not printed but configured as antenna elements formed in the second surface 8. They are connected by electrical conductors 22 to electrical conductors placed in the channel 23. [ FIG. 4 represents an exemplary embodiment of the antenna assembly 3 which can be used inter alia in each of the exemplary embodiments of FIGS. 2, 3 and 5. It can be seen that not only antenna elements 21 and electrical conductors 22 are incorporated in the materials of the support assembly 6, but also elements 27 for ground connection. In addition, several recesses 14 which extend in channels perpendicular to the plane of the drawing and which are separated by seals 15 suitable both from each other and from the environment are provided in the first surface 7. thus obtains several cavities 16 separated from each other for the evacuation of each of which are provided flow channels 17. The walls of the recesses 14 are formed by rigid linings 26 which, even when the material of the support assembly 6 is very flexible, ensuring that the recesses 14 and the cavities 16 retain a defined shape and size. Despite this, sufficient flexibility remains guaranteed for the entire antenna assembly 3 to allow it to adapt to the curved surface of the part 9 of the outer skin which may, for example, be provided on a part 25 of the fuselage. from the plane 1.
    A fourth embodiment of the antenna assembly 3 has been shown in cross section in Figure 5. This embodiment is very largely similar to the embodiment shown in Figure 3 so that the 'We will only expand on their differences.
    In the antenna assembly 3 of Figure 5, the support member is arranged in a recess 29 of the part 9 of the outer skin so that the second surface 8 is flush or essentially flush with the surface of the part 9 of the outer skin on each side of the hollow 29. In addition, no hollow is provided in the first surface 7. On the contrary, the part 9 of the outer skin has in the hollow 29 another hollow 30 in which opens the first opening 18 of a flow channel 17 and into which a lower end of the channel 23 penetrates. The cavity 16 is formed mainly at the level of this other hollow 30 and to a lesser extent between the other parts of the first surface 7 and of the part 9 of the outer skin.
    In addition, the antenna assembly 3 has several metal elements 28 which are incorporated in the first surface 7 and partly extend beyond the latter. They are in electrical and thermal contact with the part 9 of the outer skin so as to allow an exchange of heat and electrical charges between the antenna assembly 3 and the part 9 of the outer skin.
    权利要求:
    Claims (1)
    [1" id="c-fr-0001]
    [Claim 1] [Claim 2] [Claim 3] [Claim 4]
    claims
    Antenna assembly for an aircraft (1), characterized in that it has
    - a support element (6) provided with first and second surfaces (7, 8) located on opposite sides of the support element (6),
    - at least one antenna element placed on or in the support element (6) and
    - a sealing device (15), in which
    - the first surface (7) and the sealing device (15) are configured so that the antenna assembly (3) can be disposed on a part (9) of the outer skin of an aircraft (1 ) so that the first surface (7) faces the part (9) of the outer skin, so that the sealing device (15) is located between the support element (6) and the part (9 ) of the outer skin and that at least one cavity (16) is defined by the sealing device (15), the part (9) of the outer skin and the first surface (7) and
    - the support element (6) or the sealing device (15) have for each of the cavities at least one flow channel (17) provided with a first and a second opening (18, 19) located at opposite ends of the flow channel (17), which, after placing the antenna assembly (3) on the part (9) of the outer skin, mutually connects the corresponding cavity (16) and the environment of the antenna assembly (3) and which opens in the cavity (16) corresponding to the level of the first opening (18) and in the environment at the level of the second opening (19).
    An antenna assembly according to claim 1, wherein the second opening (19) is formed by at least one of the flow channels (17) on a guide portion (20) in which a portion of the flow channel (17) extends and which projects beyond the support element (6) or the sealing device (15) into the environment after the placement of the antenna assembly (3) on the part (9) of the outer skin. An antenna assembly according to claim 1 or claim 2, wherein the second opening (19) is formed by at least one of the flow channels (17) in the second surface (8) or in the device sealing (15).
    An antenna assembly according to one of the preceding claims, in which the support element (6) is a flat element.
    [Claim 5] [Claim 6] [Claim 7] [Claim 8] [Claim 9] [Claim 10] [Claim 11] [Claim 12]
    An antenna assembly according to one of the preceding claims, in which the support element (6) is flexible.
    Antenna assembly according to one of the preceding claims, in which the first surface (7) has at least one hollow (14), each of which defines one of the cavities after the placement of the antenna assembly (3) on the part (9) of the outer skin.
    An antenna assembly according to claim 5 and claim 6, in which the support element (6) has, for each of the recesses (14), a rigid lining (26) which defines the recess (14) concerned.
    An antenna assembly according to one of the preceding claims, in which each of the antenna element (s) is a panel antenna and / or a so-called KU or KA antenna.
    An antenna assembly according to one of the preceding claims, in which each of the antenna element (s) is printed on the support element (6) or on a part of the latter.
    An antenna assembly according to one of the preceding claims, in which the second surface (8) has at least one raising (24) in which is arranged at least one electrical conductor (22) and / or at least one fixing element or which is formed by at least one electrical conductor (22) and / or at least one fixing element, the second opening (19) of at least one of the flow channels (17) being disposed on the riser (24 ) or in a position immediately adjacent to the raising (24).
    An antenna assembly according to one of the preceding claims, in which one or more elements (28) conducting heat or electricity are provided on or in the support element (6), each of them forming a part of the first surface (7) or projecting from the first surface (7) so that the elements (28) conducting the heat or the electricity are in contact with the part (9) of the outer skin after the placement of the support element (6) on the part (9) of the outer skin.
    An antenna assembly according to one of the preceding claims, which further has a part (9) of the outer skin of an aircraft (1), the support element (6) being arranged on the part (9) of the outer skin so that the first surface (7) faces the part (9) of the outer skin, so that the sealing device (15) is located between the support element (6) and the part ( 9) of the outer skin and that the cavity or cavities (16) are defined by the sealing device [Claim 13] [Claim 14] [Claim 15] (15), the part (9) of the outer skin and the first surface (7). An antenna assembly according to claim 12, in which one or more bores through which cables pass or can pass are provided in the part (9) of the outer skin, the bores being arranged outside the region of the part (9) of the outer skin covered by the support element (6).
    An antenna assembly according to claim 12 or claim 13, wherein a recess (29) in which the antenna assembly (3) is disposed is provided in the portion (9) of the outer skin.
    Airplane with an outer skin (5) characterized in that it is further provided with an antenna assembly (3) according to one of the preceding claims, the support element (6) being arranged on a part (9) of the outer skin (5) so that the first surface (7) faces the part (9) of the outer skin, so that the sealing device (15) is located between the element support (6) and the part (9) of the outer skin and that the cavity or cavities (16) are defined by the sealing device (15), the part (9) of the outer skin and the first surface (7 ).
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    同族专利:
    公开号 | 公开日
    CN110120579A|2019-08-13|
    US20190245264A1|2019-08-08|
    GB2572476A|2019-10-02|
    GB201901402D0|2019-03-20|
    US10923805B2|2021-02-16|
    DE102018102765A1|2019-08-08|
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    法律状态:
    2020-02-19| PLFP| Fee payment|Year of fee payment: 2 |
    2021-02-24| PLFP| Fee payment|Year of fee payment: 3 |
    2021-08-13| PLSC| Publication of the preliminary search report|Effective date: 20210813 |
    2022-02-16| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018102765.6|2018-02-07|
    DE102018102765.6A|DE102018102765A1|2018-02-07|2018-02-07|Antenna arrangement for an aircraft|
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