Antenna assembly for an aircraft

Abstract

An aircraft antenna assembly has a support element having a first and a second surface on opposite sides, an antenna element arranged on or in the support element, and a sealing device. The first surface and the sealing device are configured such that the antenna assembly is arranged on an outer skin section of an aircraft such that the first surface faces the outer skin section, the sealing device is situated between the support element and the outer skin section, and a cavity is defined by the sealing device, the outer skin section and the first surface. The support element or the sealing device y has a flow channel having a first and a second opening at opposite ends, the flow channel connecting the cavity and the environment and opening into the cavity at the first opening and opening into the environment at the second opening.

Claims

1. An antenna assembly for an aircraft, comprising: a support element having a first and a second surface on opposite sides of the support element; at least one antenna element arranged on or in the support element; and a sealing device, wherein the first surface and the sealing device are configured in such a way that the antenna assembly is arranged in such a way on an outer skin section of an aircraft that the first surface faces the outer skin section, the sealing device is situated between the support element and the outer skin section, and at least one cavity is defined by the sealing device, the outer skin section and the first surface, and the support element or the sealing device for each of the cavities has at least one flow channel having a first and a second opening at opposite ends of the flow channel, the flow channel connecting the corresponding cavity and the environment of the antenna assembly to one another after the arrangement of the antenna assembly on the outer skin section and opening into the corresponding cavity at the first opening and opening into the environment at the second opening.

2. The antenna assembly according to claim 1, wherein the second opening of at least one of the flow channels is formed on a line section in which part of the flow channel extends and which projects from the support element or the sealing device into the environment after the arrangement of the antenna assembly on the outer skin section.

3. The antenna assembly according to claim 1, wherein the second opening of at least one of the flow channels is formed in the second surface or the sealing device.

4. The antenna assembly according to claim 1, wherein the support element is a sheet-like element.

5. The antenna assembly according to claim 1, wherein the support element is flexible.

6. The antenna assembly according to claim 5, wherein the support element has a rigid insert for each of the recesses, said insert defining the respective recess.

7. The antenna assembly according to claim 1, wherein the first surface has at least one recess, each of which defines one of the cavities after the arrangement of the antenna assembly on the outer skin section.

8. The antenna assembly according to claim 1, wherein each of the at least one antenna elements is a patch antenna and/or a Ku or Ka antenna.

9. The antenna assembly according to claim 1, wherein each of the at least one antenna elements is printed onto the support element or onto a part thereof.

10. The antenna assembly according to claim 1, wherein the second surface has at least one raised portion, in which at least one electric lead and/or at least one fastening element is arranged or which is formed by at least one electric lead and/or at least one fastening element, and wherein the second opening of at least one of the flow channels is arranged on the raised portion or directly adjacent to the raised portion.

11. The antenna assembly according to claim 1, wherein one or more thermally or electrically conductive elements, each of which forms part of the first surface or projects from the first surface, is/are provided on or in the support element, with the result that the thermally or electrically conductive elements are in contact with the outer skin section after the arrangement of the support element on the outer skin section.

12. The antenna assembly according to claim 1, further comprising an outer skin section of an aircraft, wherein the support element is arranged on the outer skin section in such a way that the first surface faces the outer skin section, the sealing device is situated between the support element and the outer skin section, and a cavity is defined by the sealing device, the outer skin section and the first surface.

13. The antenna assembly according to claim 12, wherein one or more holes, through which cables are passed or can be passed, is/are provided in the outer skin section, and wherein the holes are arranged outside that region of the outer skin section which is covered by the support element.

14. The antenna assembly according to claim 12, wherein a recess, in which the antenna assembly is arranged, is provided in the outer skin section.

15. An aircraft having an outer skin and an antenna assembly according to claim 1, wherein the support element is arranged in such a way on an outer skin section of the outer skin that the first surface faces the outer skin section, the sealing device is situated between the support element and the outer skin section, and the at least one cavity is defined by the sealing device, the outer skin section and the first surface.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The invention is explained in greater detail below with reference to the figures, in which two illustrative embodiments are illustrated.

(2) FIG. 1 shows a schematic perspective view of an aircraft having an antenna assembly according to the invention,

(3) FIG. 2 shows a schematic cross-sectional view of an antenna assembly according to a first illustrative embodiment of the present invention,

(4) FIG. 3 shows a schematic cross-sectional view of an antenna assembly according to a second illustrative embodiment of the present invention,

(5) FIG. 4 shows a schematic cross-sectional view of an antenna assembly according to a third illustrative embodiment of the present invention, and

(6) FIG. 5 shows a schematic cross-sectional view of an antenna assembly according to a fourth illustrative embodiment of the present invention.

DETAILED DESCRIPTION

(7) The aircraft 1 shown in FIG. 1 has a fuselage 2 and an antenna assembly 3 according to an embodiment of the invention. In addition to the antenna assembly 3, conventional blade antennas 4, which are secured externally on the fuselage 2 and project outwards from the fuselage 2, are also shown for purposes of illustration. In contrast, the antenna assembly 3 in the illustrative embodiment shown is configured as a sheet-like 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 air resistance of the fuselage 2 is increased insignificantly or not at all by the antenna assembly 3. In FIG. 1, the antenna assembly 3 is arranged on the upper side of the fuselage 2, by way of example. However, it is also possible for the antenna assembly to be situated at any other point on the fuselage 2, e.g. on one side or on the underside or, alternatively, at other points on the aircraft, e.g. a wing or a tailplane.

(8) The antenna assembly 3, of which a first illustrative embodiment is shown in cross section in FIG. 2, has a support element 6 which is provided in the form of a sheet-like, flexible film or of a sheet-like, flexible film component, which can have a thickness of 1 to 5 cm, for example. In the figures, the support element 6 is in each case illustrated with an exaggerated thickness for reasons of illustration. The support element 6 can comprise a layer composed of a flexible material or a plurality of layers composed of one or more flexible materials arranged one on top of the other. The support element 6 has a first surface 7 and a second surface 8, which are provided on opposite sides of the support element 6 and are spaced apart in the thickness direction of the support element 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 element 6 is arranged and secured on a section 9 of the outer skin 5 of an aircraft in such a way that the first surface 7 faces the outer skin section 9 and the second surface 8 faces away from the outer skin section 9. In this case, securing is accomplished by means that are not illustrated, only at individual interspaced points, e.g. by adhesive bonding or by means of retaining clips, which extend over the second surface 8 and are secured on both sides of the support element 6 on the outer skin section 9 or on a reinforcing structure situated thereunder.

(9) In particular, the aircraft can be the aircraft 1 which is shown in FIG. 1, and the antenna assembly 3 is then oriented and positioned in such a way, e.g. in the position shown in FIG. 1, that air acts on the support element 6 and the antenna assembly 3 in the direction denoted by the arrow 10 during the flight of the aircraft 1 and flows over these in said direction 10. The leading edge 11 of the support element 6, which faces counter to the direction of flow 10, is bevelled, as is the opposite trailing edge 12 in precisely the same way, in order to achieve favourable flow conditions and to keep to a minimum aerodynamic effects leading to forces on the support element 6 that tend to lift or detach it from the outer skin section 9. Such lifting forces are caused not only by the impact of the flow in the region of the leading edge 11 but especially also by the flow of air over the support element 6 projecting from the outer skin section 9, which exerts a suction effect on the support element 6, said effect acting upwards in FIG. 2. This is indicated in FIG. 2 by the arrows 13, the respective thickness of which indicates the strength of the force exerted on the support element by the ambient pressure. It can be seen that these forces are very much higher in the region of the leading edge 11 than in the remaining area of the support element 6. In the region of the leading edge 11, the upward pressure is greater than the ambient pressure owing to the deflection of the air flow and can amount to 200% of the ambient pressure, for example, while the pressure in the remaining area of the support element 6 is lower than the ambient pressure and can amount to 50% of the ambient pressure, for example, with the result that a lifting force is exerted on the support element 6.

(10) A recess 14 is formed in the first surface 7, and an encircling sealing ring 15 is arranged in the edge region of the support element 6, between the first surface 7 and the outer skin section 9. A cavity 16 corresponding substantially to the recess 14 is thereby formed between the first surface 7, the outer skin section 9 and the sealing ring 15. The sealing ring 15 can be configured in such a way that the first surface 7 rests against the outer skin section 9 outside the recess 14, with the result that the cavity 16 corresponds to the recess 14. In all cases, air can escape from the cavity 16 or recess 14 into the environment only via two flow channels 17, which extend through the support element 6 in the thickness direction. At one end, each of the flow channels 17 has a first opening 18, which opens into the recess 14 or cavity 16 and, at the opposite end, has a second opening 19, which opens into the environment. Here, the second opening 19 is provided on a rigid line section 20, which projects from the second surface 8 and in which part of the corresponding flow channel 17 runs.

(11) As with the principle of a water jet pump, the flow of air over the support element 6 and the antenna assembly 3 during the flight of the aircraft 1 causes a suction effect at the second openings 19, sucking air out of the recess 14 or cavity 16 through the flow channels 17 and in this way producing a reduced pressure there between the second surface 7 and the outer skin section 9. This reduced pressure is lower than the pressure 13 acting on the first surface 8, as indicated by the arrows 21. As a result, a force on the support element 6 acting downwards overall in FIG. 2 arises in the region of the recess 14 or cavity 16, pressing the support element 6 and the antenna assembly 3 against the outer skin section 9 and thus representing a retaining force counteracting the lifting forces. This retaining force is produced by the same flow as the lifting forces and increases proportionally thereto, for example. The requirements on any other fastening of the support element 6 on the outer skin section 9 are therefore significantly reduced. Thus, for example, it is possible to dispense with full-area adhesive bonding between the support element 6 and the outer skin section 9.

(12) In the illustrative embodiment shown, the second opening 19 is oriented in such a way in the direction of flow 10 that a particularly high suction effect can be achieved by means of air turbulence at the support element 6 and the line section 20. The arrangement and orientation of the second openings 19 can be selected in a flexible manner in such a way that a suitable high suction effect for the envisaged use and for a predetermined direction of overflow 10 is achieved at the second openings 19.

(13) A multiplicity of antenna elements 21 in the form of patch antennas is printed onto the second surface 8 of the support element 6, and electric feed lines 22 for the patch antennas 21 can be embedded in the material of the support element 6 (not shown in FIG. 2 but see FIGS. 3 and 5).

(14) A second illustrative embodiment of the antenna assembly 3 is shown in cross section in FIG. 3. This illustrative embodiment is very largely identical to the illustrative embodiment shown in FIG. 2, and therefore only differences will be explained.

(15) The antenna assembly 3 in FIG. 3 has a channel 23, which extends over at least part of the width of the support element 6 and of which one part forms a raised portion 24 projecting from the second surface 8. In the channel 23, it is possible, for example, for there to be electric leads or a fastening clamp, which extends over the entire width of the support element 6 and extends beyond the latter on both sides and can be connected there to the outer skin section 9 or to a reinforcing structure, situated underneath the latter, of the aircraft 1 in order to secure the support element 6 on the outer skin section 9. The raised portion 24 forms an obstacle to the flow flowing over the support element 6 in direction 10, and one of the line sections 20 and the second opening 19 are arranged directly adjacent to and, in the direction of flow 10, behind the raised portion 24. It is thereby possible to improve the suction effect at the second opening 19. The raised portion 24 can have a downward slope in a direction counter to the direction of flow 10 or can have some other suitable shape in order both to keep down an increase in air resistance and to achieve an improvement in the suction effect.

(16) In FIG. 3, the patch antennas 21 are not printed on but are designed as antenna elements let into the second surface 8. They are connected to electric leads in the channel 23 by electric leads 22.

(17) FIG. 4 shows an illustrative embodiment of the antenna assembly 3 which can be used inter alia in each of the illustrative embodiments in FIGS. 2, 3 and 5. It can be seen that not only antenna elements 21 and electric leads 22 but also earthing elements 27 are embedded in the material of the support element 6. Moreover, a multiplicity of recesses 14 is provided in the first surface 7, each extending in the form of channels perpendicularly to the plane of the drawing and being separated both from one another and from the environment by suitable seals 15. This gives rise to a plurality of mutually separated cavities 16, for each of which dedicated flow channels 17 for the evacuation thereof are provided. The walls of the recesses 14 are formed by stiff or rigid inserts 26 which, even in the case of very flexible material for the support element 6, ensure that the recesses 14 and the cavities 16 have a defined shape and size. It is nevertheless possible to ensure a flexibility of the overall antenna assembly 3 sufficient to allow adaptation to the curved surface of the outer skin section 9, which can be provided on a fuselage section 25 of the aircraft 1, for example.

(18) A fourth illustrative embodiment of the antenna assembly 3 is shown in cross section in FIG. 5. This illustrative embodiment is a very largely identical to the illustrative embodiment shown in FIG. 3, and therefore only differences will be explained.

(19) In the antenna assembly 3 in FIG. 5, the support element is arranged in a recess 29 in the outer skin section 9, more specifically in such a way that the second surface 8 is flush or substantially flush with the surface of the outer skin section 9 beyond the recess 29. Moreover, no recesses are provided in the first surface 7. On the contrary, the outer skin section 9 has, in recess 29, a further recess 30, into which the first opening 18 of a flow channel 17 opens and into which a lower end of the channel 23 projects. The cavity 16 is formed primarily in the region of this further recess 30 and, to a lesser extent, between the remaining regions of the first surface 7 and the outer skin section 9.

(20) Furthermore, the antenna assembly 3 has a multiplicity of metallic elements 28, which are embedded in the first surface 7 and partially project therefrom. They are in electric and thermal contact with the outer skin section 9, allowing an exchange of heat and electric charge between the antenna assembly 3 and the outer skin section 9.

(21) While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms comprise or comprising do not exclude other elements or steps, the terms a or one do not exclude a plural number, and the term or means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.