EP4000130A1 - Aérodyne avec antenne et procédé d'agencement associé - Google Patents
Aérodyne avec antenne et procédé d'agencement associéInfo
- Publication number
- EP4000130A1 EP4000130A1 EP20736744.2A EP20736744A EP4000130A1 EP 4000130 A1 EP4000130 A1 EP 4000130A1 EP 20736744 A EP20736744 A EP 20736744A EP 4000130 A1 EP4000130 A1 EP 4000130A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- antennas
- antenna
- aerodyne
- fuselage
- structural element
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/286—Adaptation for use in or on aircraft, missiles, satellites, or balloons substantially flush mounted with the skin of the craft
- H01Q1/287—Adaptation for use in or on aircraft, missiles, satellites, or balloons substantially flush mounted with the skin of the craft integrated in a wing or a stabiliser
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q21/00—Antenna arrays or systems
- H01Q21/06—Arrays of individually energised antenna units similarly polarised and spaced apart
- H01Q21/061—Two dimensional planar arrays
- H01Q21/065—Patch antenna array
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q21/00—Antenna arrays or systems
- H01Q21/28—Combinations of substantially independent non-interacting antenna units or systems
Definitions
- the present invention relates to an aerodyne comprising one or more antennas, as well as an external structural assembly and a method of arrangement thereof. It applies in particular to fixed-wing aerodynes, such as airplanes or gliders.
- An important aspect relating to antennas is their positioning. It is in particular known to have radome systems in the upper part of the aerodyne, on the fuselage. However, such arrangements have the drawback of increasing the drag of the aerodyne, and therefore the fuel consumption. In addition, substantial mechanical and aerodynamic tune-ups are required, at the cost of investment in time and budget. Typically, several days are thus required to install an antenna according to these solutions, relying on a highly qualified workforce. In addition, a flight authorization is only acquired under conditions of satisfactory analyzes and tests.
- Patent application CN 103887605 (inventors Zhou Jinzhu et al.) Describes an aircraft wing incorporating array antennas (also referred to as antenna arrays, "antenna arrays" in English terminology). More specifically, the wing has a central structure bounded by an upper skin and a lower skin defining its external surfaces, each of these coatings including a central radiofrequency circuit layer framed by thermally insulating honeycomb layers and by top and bottom panels.
- the core layer includes an array antenna.
- the object of the present description is in particular to overcome the difficulties and drawbacks mentioned above with the existing antenna systems for aerodynes.
- the invention makes possible a rapid and simplified installation, an economical realization, a reduced maintenance, a preservation of the aerodynamic properties of the aerodyne and / or a good reliability of communications by radio waves.
- an aerodyne comprising a fuselage and at least one external structural element with a lifting surface (called the "airfoil” type in English) mounted to the fuselage and configured to provide the aerodyne with aerodynamic properties.
- This outer structural element includes at least one outer shell and is provided with at least one antenna.
- the antenna (s) are arranged inside the external structural element while being structurally dissociated from the external shell (s).
- at least part of these external shells is substantially transparent to at least one range of radio frequencies, so that the antenna (s) can (s) perform an operation chosen from at least one reception and one transmission. of radio waves through this or these part (s) of the outer shell (s).
- the external structural element advantageously corresponds to a fixed part of the aerodyne, which makes it possible to facilitate antenna orientation stability.
- the aerodyne is therefore advantageously fixed-wing.
- the external structural element can however also consist of a fixed part of a rotary wing aerodyne, such as for example a tail or possibly a fixed wing of a helicopter.
- external structural element with a bearing surface is understood to mean a structural assembly forming an aerodynamic unit, whatever the composition or the multiplicity of the elements which constitute it.
- a structural element can optionally include a vertical fin comprising a main structure, as well as lower, longitudinal and upper cowls of this main structure.
- the outer shell can have common structural properties along its thickness, in the sense that independently in particular of stress gradients, deformations or temperatures along the thickness (variations in mechanical or thermal properties), movements or inclinations of the outer surface correspond substantially to corresponding movements or inclinations of the inner surface and of the whole of the intermediate part.
- the array antenna forms with the honeycomb layers and the lower and upper panels which border it a single structure of the outer shell. composite constituting the upper covering or the lower covering, and are inseparably linked structurally.
- changes in the curvature of one of the panels or of one of the honeycomb layers affect the shape, positioning and orientation of the array antenna sandwiched between the honeycomb layers. bee and signs.
- the configuration of the present description can be particularly advantageous, since it allows positioning and orientation of the antenna disconnected from the contours of the external structural element. This potentially offers great flexibility of implementation, which can prove to be invaluable in ensuring good radio connectivity with, in particular, satellites.
- the structural dissociation of the antenna and the outer shell is likely to greatly facilitate installation and maintenance operations.
- the arrangement of antennas within an outer structural element with a bearing surface and with structural dissociation from the outer shell may prove to be surprising for a person skilled in the art. It goes against the apparently antagonistic imperatives of good aerodynamic behavior of the airfoil and efficient transmission of waves. radio.
- the external structural elements with a bearing surface generally include parts that disrupt the circulation of waves, in particular metallic ones, so that the only feasible solutions for associating them with antennas could appear as external positioning or integration on the surface - at the price of the disadvantages mentioned above.
- the radio frequency range (s) to which the parts of the outer shells are substantially transparent include in some modes at least one of the Ku (typically 12-18 GHz) and Ka (typically 26.5-40 GHz) bands.
- the radio frequency range (s) at which the parts of the outer shells are substantially transparent include at least one cellular network frequency band, for example used for communications in 4G or 5G technology.
- the outer structural member is removably mounted to the fuselage.
- one or more parts of the external structural element are removable, and the antennas are accessible by removing this part or parts.
- hatches or flaps for accessing the antennas are provided in the external structural element.
- the external structural element comprises at least one free space between the antenna (s) and the external shell (s).
- Such free space can be used in particular to flexibly adjust the positioning or orientation of the antennas, during the installation of the latter or during maintenance operations.
- At least one of the antennas is separated from the inner surface of the outer shell by at least 3 times the thickness of the outer shell, and in more specific embodiments at least 5 times, at least 10 times or at least 20 times this thickness;
- At least one of the antennas is separated from the inner surface of the outer shell by at least 5 cm, and in more specific embodiments, at least 10 cm, at least 15 cm or at least 20 cm;
- the antennas has an inclination which differs by at least 10 ° from an inclination of the inner surface closest to the outer shell, and in more specific embodiments, at least 15 °, at least 20 ° or at least 30 °; the inclination of the internal surface is defined by a perpendicular to this surface, and the inclination of the antenna by the main line of sight of the antenna, or if the antenna is flat, by a perpendicular to the plane of this antenna.
- the aerodyne comprises at least one support structure carrying the antenna (s), this or these support structure (s) being arranged inside the external structural element while being structurally dissociated from the outer shell (s).
- the aerodyne comprises at least one modem cooperating with the antenna (s) and arranged inside the external structural element.
- the modem (s) and the antenna (s) can then be integrated on at least the same card.
- the modem is arranged apart from the antenna with which it cooperates, and can be used centrally for several antennas positioned at separate locations and with different orientations, if applicable.
- the aerodyne having a horizontal plane (which can be defined for example as a plane perpendicular to a vertical plane of symmetry with respect to the wings), the antenna considered is oriented with an angle of inclination between 45 ° and 70 ° relative to this horizontal plane, and in particular implementations between 67 ° and 68 °, and more specifically still between 67.4 ° and 67.6 °.
- the angle of inclination of the antenna is understood to mean the angle between a reference line of sight of the antenna and the vertical (an angle of 0 ° therefore corresponding to a horizontal positioning of a flat antenna).
- the antennas are at least two in number and the aerodyne comprises one or more multiplexer (s) configured to multiplex signals respectively obtained from these antennas.
- the antenna (s) includes (include) at least one transmission antenna and at least one reception antenna, these transmission and reception antennas being arranged on the same card and being spaced so as to avoid interference. full duplex cross interference.
- at least one of the antennas is an array antenna, the latter possibly being in particular phase-controlled.
- at least one of the antennas is a flat antenna.
- the antenna (s) are electronically steerable.
- the absence of a rotating mechanical part for the antennas makes it possible to reduce the risk of breakdowns and the need for maintenance.
- the external structural element is a dorsal fin and the antenna (s) are arranged in a lower part of this dorsal fin.
- antennas being able for example to be placed in the dorsal fin, in the upper and / or lower part, and / or other antennas being able to be placed in one. or two wings.
- the antennas distributed at different locations on the aerodyne and in different orientations are likely to provide additional information, or to secure communications through deliberate redundancies.
- the external structural element (s) is (are) composed at least partially of a material selected from polymer reinforced with carbon fibers or CFRP (for Carbon Fiber Reinforced Polymer), polymer reinforced with Kevlar fibers or KFRP (for Kevlar Fiber Reinforced Polymer), and polymer reinforced with glass fibers or GFRP (for Glass Fiber Reinforced Polymer).
- CFRP Carbon Fiber Reinforced Polymer
- Kevlar fibers or KFRP for Kevlar Fiber Reinforced Polymer
- GFRP Glass Fiber Reinforced Polymer
- the description also relates to an external aerodyne structural assembly comprising an external structural element with a lifting surface adapted to be mounted to a fuselage of an aerodyne and configured to provide the aerodyne with aerodynamic properties.
- This external structural element comprises at least at least one external shell and is provided with at least one antenna.
- this or these antenna (s) is (are) arranged inside the external structural element while being structurally dissociated from this or these external shell (s).
- at least part of this or these outer shell (s) is substantially transparent to at least one range of radio frequencies, so that the antenna (s) can perform a chosen operation. among at least one reception and one emission of radio waves through this or these part (s) of the outer shell (s).
- Such an external structural assembly can thus be produced separately by integrating therein the desired antennas in an appropriate manner, and then be fixed to an aerodyne after, for example, packaging and transport.
- the specification also relates to a method of arranging at least one antenna in an aerodyne comprising a fuselage and at least one external structural element with an airfoil mounted to the fuselage and configured to provide the aerodyne with aerodynamic properties.
- This external structural element comprises at least one external shell.
- the method comprises arranging the antenna (s) inside the outer structural element in a manner structurally dissociated from the outer shell (s).
- at least part of this or these outer shell (s) is substantially transparent to at least one range of radiofrequencies, so that this or these antenna (s) can perform a selected operation. among at least one reception and one emission of radio waves through this or these part (s) of the outer shell (s).
- This method is advantageously suitable for producing an aerodyne conforming to any one of the embodiments above.
- the at least one dismantling component may be an aerodyne cowl.
- the installation step may include a step of fixing an antenna supporting structure on the fuselage.
- the reformation step may include a step of reassembling the dismantled component (s).
- FIG. 1 represents an airliner according to several embodiments making it possible to make it conform to an aerodyne according to the description
- FIG. 2 is a block diagram functionally illustrating an operation with satellite communications of an aerodyne in accordance with a particular embodiment (antennas in the lower part of the dorsal fin);
- FIG. 3 represents schematically and in a simplified manner an angular distribution of radiation from aerials in flight for an aerodyne of the type of FIG. 2;
- FIG. 4 illustrates more precisely in cross section and in partial view an example of an arrangement of flat antennas in the lower part of the dorsal fin, corresponding to the mode of FIGS. 2 and 3;
- FIG. 5 shows in longitudinal section and in partial view the example of FIG. 4;
- Figure 6 shows a side view of the components of a dorsal fin assembly, in which can be installed antennas according to the example shown in Figures 4 and 5;
- FIG. 7 shows a lower part of the dorsal fin cover at the fuselage level, called a shoe, the latter forming part of the dorsal fin assembly of FIG. 6 and being intended to place antennas in accordance with the example Figures 4 and 5;
- FIG. 8 shows in the absence of the shoe of Figure 7 a corresponding fuselage area
- Figure 10 shows in perspective a supporting structure configured for the positioning of antennas and intended to be installed in the fuselage area of Figures 8 and 9;
- Figure 1 1 shows the fuselage area of Figures 8 and 9 after installation of the supporting structure of Figure 10 fixed on the support legs of Figure 9;
- Figure 12 shows in perspective the fuselage area with supporting structure of Figure 1 1 after installation of panels for the attachment of flat antennas;
- FIG. 13 represents in side view the fuselage zone with supporting structure equipped with the panels of FIG. 12;
- Figure 15 is an exploded view of the array antenna block of Figure 14;
- Figure 17 is a block diagram illustrating connections between four array antenna blocks of the type of Figures 14 and 15 in position and processing modems which may form part of the functional architecture of Figure 16;
- FIG. 18 is a diagram of an electrical and electronic wiring harness within an aerodyne of the type of FIG. 2;
- FIG. 19 is a photo showing an installation for testing network antennas such as for example those of FIGS. 14 and 15 in position in a shoe such as that of FIG. 7;
- Figure 20 partially shows a variant of a supporting structure with network antenna blocks
- FIG. 22 is a schematic illustration in cross section of different methods of installing antenna panels inside a shoe, in relation for example to FIG. 13 or to FIGS. 20 and 21;
- Figure 23 shows schematically in cross section another method of installing antenna panels than those of Figure 22;
- FIG. 24 is a block diagram functionally showing an aerodyne according to the embodiment of FIG. 2, with a different type of array antennas than those of the previous figures;
- FIG. 25 is a block diagram functionally showing an aerodyne according to a particular embodiment distinct from that of FIG. 2 (antennas inside a wing on the fuselage side);
- FIG. 26 shows a flowchart for implementing an antenna arrangement method according to the present description, in the context of an adaptation or maintenance of an operational aerodyne
- FIG. 27 shows a flowchart for implementing an antenna arrangement method according to the present description, in the context of an aerodyne construction or transformation.
- FIG. 1 An airplane 1 (FIG. 1), which may for example be an airliner such as that marketed under the brand A321 by the company Airbus, has an airframe including a fuselage 10 and wings 13 provided with covers 131 at their root for fixing to the fuselage 10, these cowls 1 31 being for example made of polymer reinforced with Kevlar fibers (KFRP) and contributing to the aerodynamic fairing of the wings 13 in addition to a main part 130, metallic.
- KFRP Kevlar fibers
- the aircraft 1 also comprises a tail unit including a dorsal fin 1 1 and horizontal stabilizers 12, the dorsal fin 1 1 being provided with cowls such as a lower cowl 1 1 1 at its zone of attachment to the fuselage 10, said shoe cover ("shoe cover” in English) a cover 1 12 at the upper end of the fin 1 1, called a "hood cover” in English, and an elongated cover in the upper part of the fin 1 1 and connecting the shoe 1 1 1 and the cap 1 12, said longitudinal cowl (“roof cover” in English), these cowls 1 1 1, 1 12 and 1 13 contributing to the aerodynamic fairing of the fin 1 1 in addition to a main part 1 10, metallic.
- the shoe 1 1 1 and the cap 1 13 are for example made of glass fiber reinforced polymer (GFRP).
- the aircraft 1 is particularized by the presence of one or more antennas inside the fin 11 and / or at least one of the wings 13, and more precisely inside at least one of their parts consisting of the shoe 1 1 1 and the fin cover 1 12 and the wing covers 131, as detailed below.
- antennas can be placed for example inside the longitudinal cover 1 12 made of GFRP.
- antennas are present at various locations of the aircraft 1 and are operated jointly, for example by combined processing of signals obtained from these antennas and / or of transmitted signals. by these antennas. It is thus possible to enrich the transmission and reception capacities, in particular in terms of range, directional coverage and / or gain.
- an antenna 2 inside the shoe 1 1 1 of the fin 1 1 in the aircraft 1 is for example carried out as explained below in relation to FIG. 2 (multiple antennas of the type antenna 2 which can be jointly active in the shoe 1 1 1).
- the antenna 2 is integrated in an on-board communication system 5 also comprising a modem 6, an electronic and electrical network 51 1 of the aircraft 1, and a local wireless network (called LAN for “Local Area Network”) 512.
- LAN Local Area Network
- the aircraft 1 communicates with a satellite 31 in reception (downlink 31 1, for example at 10 Gbit / s) and in transmission (up link 312, for example at 1 Gbit / s) , the satellite 31 being in radio link with a gateway parabolic antenna 321 on the ground, which is connected to a processing center 322 and via the latter to computer resources 323 (for example of the cloud or cloud type) and associated interfaces.
- the possible bandwidth depends above all on the capacities of the satellite (s) in connection with the aircraft.
- Communications between aircraft 1 and satellite 31, a block diagram of which can be seen in Figure 3, is based on the transmission capacities via antenna 2 through the shoe 1 1 1 of the fin 1 1.
- the location of the antenna 2 can provide right 313A or left 313B sight lines (right and left being defined with respect to the direction of navigation) substantially perpendicular to the axis of the fuselage 10, and relatively wide angular radiation apertures.
- 314A or 314B respectively on the right and on the left (the representations of the radiation being purely of principle and not accounting for effective radiation patterns).
- a selection of active antennas can thus be carried out in particular as a function of a spatial positioning and directional of the airplane 1 with respect to communication satellites (in particular taking into account the azimuthal positions of these satellites with respect to the airplane 1).
- Such an arrangement uses for example eight blocks of antennas including on the left four blocks of flat array antennas 21 1 B, 212B, 213B and 214B, and symmetrically on the right four blocks of array antennas plates not shown. These antennas are close in their upper part to a vertical plane of symmetry of the shoe 1 1 1, and are inclined by approximately 72 ° with respect to a horizontal plane ( Figure 4), so that they have lines of sight elevated by about 18 ° relative to the horizontal of airplane 1 perpendicular to the axis of the fuselage 10.
- the antenna blocks 21 1 B, 212B, 213B and 214B on the left and the corresponding ones on the right are carried two by two by panels 41 1 B and 412B on the left, and symmetrically on the right 41 1 A and 412A, which give the antennas the desired inclinations ( Figure 5), and are articulated by means of hinges 42 to one or more structures not shown.
- the panels 41 1 A, 412A, 41 1 B and 412B have dimensions in height and width of the order of 50 cm, and the antenna blocks of the right panels 41 1 A and 412A are spaced horizontally by a distance of between 45 and 50 cm (for example 47 cm, the same for the antenna blocks of the left panels 41 1 B and 412B).
- a partition can be made between antennas for reception and transmission, the antenna blocks 21 1 B and 212B being for example used for transmission and the antenna blocks 213B and 214B for reception.
- the distance between the antenna blocks can then make it possible to operate in full duplex mode (called "full duplex" in English terminology), avoiding interference between reception and transmission.
- the number and / or the size of the antenna blocks can be adapted as a function of the needs and of the available space, the examples presented in the present application not being limiting.
- a method of installing such antennas 2 inside the shoe 11 1 of an existing aircraft can be carried out for example as follows, with reference to Figures 6 to 13.
- the shoe 1 1 1 is removably attached to the fuselage 10 and borders the main part 1 10, metal, of the dorsal fin 1 1, the longitudinal cover 1 13 being positioned on the main part 1 10 in the extension shoe 1 1 1 (figure 6).
- the shoe has, for example, a length of about 1.20 m (along the axis of the fuselage), and is mainly made of GFRP, adhesive film and honeycomb structure.
- the longitudinal cover 1 13 (figure 7) is removed, then the shoe 11 1 (figure 8) is removed, before fixing on the fuselage 10 (figure 9) support legs 421 ("brackets" in English, three in number in a triangle in the example shown), which will be used to fix a supporting structure 40 (FIG. 10).
- a simple gluing of the feet 421, as shown, may prove to be satisfactory for this purpose.
- the supporting structure 40 is configured to be fixed to the fuselage 10 on the one hand by countersunk parts 422 and on the other hand to the legs 421 respectively by fixing elements 423, and to receive panels which hold flat antennas, such as for example the panels 41 1 A, 412A, 41 1 B and 41 2B above.
- a block of antennas 20, as shown in Figures 14 and 15, for example comprises two sub-networks 221 and 222 of 256 elements ("patches" in English), and is identical in reception or transmission.
- This antenna block 20 can take the form of a printed circuit board or PCB (for "Printed Circuit Board”).
- PCB for "Printed Circuit Board”
- modem functionality is reduced to controller boards.
- 206 for antenna control and traceability
- the antenna block 20 also includes connectors 205, a ventilation assembly 207 (for cooling a passive metal plate) and a DC power supply brick 208.
- the antenna block 20, and its two sub-networks 221 and 222 are multibeam, and are for example suitable for satellite communications both with satellites in geostationary earth orbit or GEO (for “Geostationary Earth Orbit”) and in low earth orbit or LEO (for "Low Earth Orbit”).
- the block of antennas 20 has for example a length (in the direction traversing the two sub-arrays 221 and 222) of between 46 and 47 cm, a width of between 42 and 43 cm, and a depth of the order of 5 , 5 cm.
- the assembly formed by the supporting structure 40 provided with the panels 41 1 A, 412A, 41 1 B and 412B and the antenna blocks 20 may have a relatively limited weight, for example of the order of 50 kg.
- a radio communication system 50 cooperating with the antenna blocks such as the antenna block 20 above and installed inside the fuselage 10, for example mainly comprises the following elements, with reference to the architecture of principle shown in figure 16.
- the radio communication system 50 includes:
- a processing unit 71 comprising a digital signal processor or DSP (for “Digital Signal Processor”) subsystem, a processor or CPU (for “Central Processing Unit”) subsystem, a direct access controller to the memory or DMA (for "Direct Memory Access”) and an external memory controller,
- DSP Digital Signal Processor
- CPU for “Central Processing Unit”
- DMA Direct Memory Access
- MAC layer for "Medium Access Control”
- MAC layer for "Medium Access Control”
- buses 74 interconnecting all the elements of the radio communication system 50.
- the modem part 60 more specifically comprises a demodulation sub-part 601 (with parallel demodulation units) and a modulation sub-part 602, the demodulation being associated in reception upstream with analog-to-digital converters 603 and downstream with modules 605. for extracting data from transport trains by, in particular, decapsulation, and the modulation being associated in transmission upstream with modules 606 for preparing transport trains by, in particular, encapsulation and downstream with digital-to-analog converters 604.
- the signals transmitted and received by the radio communication system 50 via the modem part 60 are for example satellite signals conforming to the DVB-S2 standard (standing for “Digital Video Broadcasting” - second generation for satellite broadcasting).
- the antenna blocks 20 and the modem part 60 can in particular be configured for transmissions in Ku and / or Ka bands.
- the antenna blocks 20 are configured to receive and transmit in the Ku band, between 10.7 and 12.7 GHz in reception and between 14 and 14.5 GHz in transmission, with a transmission efficiency of around 80%.
- these antenna blocks 20 have in transmission an equivalent effective radiated power or EIRP (for "Effective Isotropy Radiated Power") of 32 dBW and in reception have a performance factor G / T (gain over noise temperature). of 3 db / K.
- EIRP effective radiated power
- antenna blocks 20 and modem part 60 can be configured to perform beamforming (also called beamforming) with phase and gain adjustment for each path, thereby providing multibeam capabilities. For example, up to 32 separate beams can be generated and up to 32 separate beams can be processed (32 signal inputs and 32 signal outputs), with a simultaneously processed signal bandwidth of 880 MHz (split between channels) . In other examples, up to 16 beams, or up to 8 beams can be processed.
- beamforming also called beamforming
- phase and gain adjustment for each path thereby providing multibeam capabilities.
- up to 32 separate beams can be generated and up to 32 separate beams can be processed (32 signal inputs and 32 signal outputs), with a simultaneously processed signal bandwidth of 880 MHz (split between channels) .
- up to 16 beams, or up to 8 beams can be processed.
- the antenna blocks 20 can use components developed by the company SatixFy such as a specialized integrated circuit or ASIC (for “Application Specifies Integrated Circuit”) for an active flat array antenna, marketed under the trademark “ PRIME ”, and an integrated component for radio frequencies or RFIC (for“ Radio Frequency Integrated Circuit ”), interfaced between a phased array antenna and a“ PRIME ”ASIC and acting as a front module, marketed under the brand“ BEAT ” .
- ASIC Application Specifies Integrated Circuit
- PRIME Radio Frequency Integrated Circuit
- the antenna blocks 20 provided to be arranged inside the shoe 1 1 1 are connected in series to two modems 621 and 622 provided to be placed inside the fuselage 10.
- an electronic and electrical wiring harness between the antennas 2 arranged inside the shoe 1 1 1 and the functions present inside the fuselage 10 may for example, as in figure 18, comprise an electronic path 51 for routing to one or more modems 62 (for example modems 621 and 622 above) and an electrical path 52 to a power supply electric 53 on the front of the device.
- the wiring path can for example pass through ceilings.
- the power supply can be divided into several cables (for example four) in order to avoid too high amperage. Maximum values of around 12.5 A for amperage and 28 V direct current for voltage are, for example, observed.
- FIG. 20 and 21 and referenced 43 Another embodiment of a supporting structure than that explained above, shown schematically in Figures 20 and 21 and referenced 43, comprises two tilted right 431 A and left 431 B panels, joined in their upper part and arranged symmetrically with respect to a plane vertical in the axis of the fuselage 10.
- the supporting structure 43 is designed to receive four blocks of antennas of the type 20 described above, including two blocks of antennas 215A and 216A on the right panel 431 A, and two blocks of '215B and 216B antennas on the left panel 431 B.
- a supporting structure of this type can be produced according to the present description, depending on the angles of inclination of such panels 431 A and 431 B with respect to the horizontal.
- principle illustrations show in Figure 22, in position inside the shoe 1 1 1, a supporting structure 441 with tilt angles of 45 °, a supporting structure 442 with tilt angles of 60 °, and suggest various intermediate inclinations of 48 °, 50 °, 52 °, 54 °, 56 ° and 58 ° respectively.
- a supporting structure comprises a mechanism, for example based on notches or hooks, which makes it possible to adjust the inclination of the panels at different angles.
- This embodiment can be particularly advantageous for use in series of the same model of supporting structure, because it allows flexible adaptation of the configuration of this structure with several types of aerodynes, external structural elements chosen for the positioning of the antennas, categories of antennas, or radio communications applications.
- a supporting structure 45 has for its right panel 451 A and its left panel 451 B inclination angles of 70 °.
- a block of antennas 23 comprises on the right a flat array antenna 231 extended to the right, and to the left, a substantially square flat array antenna 232 and smaller in size than the array antenna 231 and spaced therefrom.
- the network antennas 231 and 232 are provided respectively for the reception and the transmission of radio waves, the reception being more demanding in performance than the transmission.
- the space between the antennas 231 and 232 helps prevent interference between transmission and reception in full duplex operation.
- antennas 2 are arranged inside 'at least one of the cowls 131 of the wings 13 in the vicinity of the fuselage 10.
- the antennas 2 are connected to one or more modems 6 dedicated to the combined processing of the corresponding signals.
- the antennas operated in this configuration are advantageously small in size, compared to those that can be installed inside a fin as discussed above.
- the radio communication systems 50 cooperating with the antenna blocks 2 can take any suitable form known to a person skilled in the art to perform the functions mentioned and produce the effects or results mentioned. They may in particular include devices, components, or physical parts of device (s) or component (s), which these parts be grouped together in the same machine or in separate machines, which can be separated within the aerodyne considered. Furthermore, the signal processing functionalities can be performed in the form of hardware, software, firmware (also called firmware), or any mixed form thereof.
- the antennas 2 can for their part be arranged in any relevant area of the aircraft or in several of them, and the corresponding signals can be processed separately or jointly by means of the radio communication systems 50 in all technically feasible ways to achieve the functions mentioned and to produce the effects or results mentioned.
- a method of arranging 81 a set of antennas in an existing aerodyne can be implemented either during an initial installation operation or in a subsequent maintenance or updating operation.
- Such a method 81 comprises for example the following steps, illustrated in FIG. 26:
- step 811 disassembly of at least one component (such as a cover) from an external structural element with a bearing surface;
- step 812 placing the set of antennas in an area cleared by the dismantling of step 81 1, for example by fixing an antenna supporting structure on the fuselage;
- step 813 of an electronic and electrical harness connecting the antenna assembly to a radio communication system and to a power supply inside the fuselage;
- step 814 of the external structural element, for example by reassembling the dismantled component (s), so as to cover the set of antennas in place.
- a method of arranging 82 a set of antennas in an aerodyne under construction can be implemented separately in an external structural element with an airfoil before connection to the fuselage.
- Such a method 82 comprises for example the following steps, illustrated in FIG. 27:
- step 821 clearing a placement area within the outer structural member, configured to receive at least one component (such as a cover) of that member;
- step 822 placement of the set of antennas in this open area, for example by fixing an antenna supporting structure, and covering the set of antennas by placing the one or more components;
- step 824 of the outer structural member to a fuselage, during aerodyne construction operations
- Such an installation of antennas upstream in elements intended for the construction of aerodynes is particularly advantageous, because it makes it possible to implement mass productions, for example of wings or fins, which can then be the subject of distribution or export to remote locations. It is thus possible to rationalize manufacturing and reduce fixed costs, while centralizing corresponding expertise.
- antennas radio communication systems, and placement configurations in external airfoil airfoil structural elements can also be developed while preserving the functionality discussed.
- the selection of these entities is advantageously carried out jointly, taking into account their interactions and the desired purposes.
- positioning and the orientation of the antennas can be determined by means of supporting structures as a function of the number, capacities and types of operation, and of the possibly combined processing (in transmission and / or in reception) of these antennas.
- the antennas and radio communication systems described in the description are dedicated to satellite transmissions, they can also consist of antennas of radio communication systems configured for terrestrial transmissions, for example provided for receptions and transmissions. in 4G and / or 5G, particularly useful in particular when the aerodyne is on a tarmac.
- the joint presence of antennas intended for satellite and terrestrial transmissions in an aerodyne can be of particular interest.
- Other types of antennas than flat antennas and / or arrays can also be used.
- antennas in addition to the installation of antennas inside a shoe or a fin cap, or a wing cover at the level of their root for attachment to the fuselage, those- these can also be installed, for example (exclusively or in combination with some of the above arrangements) inside other parts of external structural elements having the desired transparency to the radio waves to be received or transmitted (longitudinal fin cover , horizontal stabilizer cowl, etc.). It may then be appropriate to provide an appropriate harness for electronic and electrical connections, or other means fulfilling similar functions.
- the antenna blocks are provided with a set of processing capabilities, particularly in terms of modems, which significantly reduce or make unnecessary additional processing performed remotely inside the fuselage.
- antenna-carrying structures have been detailed in the description. However, all kinds of other supporting structures can be used, including mobile structures which can give the antennas orientations and / or positions that vary over time, in particular by remote control or prior programming.
- the supporting structures offer advantageously the possibility of applying to the antennas positions and / or orientations inside the external structural element with a supporting surface, without these positions and / or orientations being dictated by the external shell of the external structural element.
- Such a configuration can be implemented during the initial installation and / or during maintenance operations.
- the supporting structures are fixed to the fuselage and have no direct structural link with the external structural element which surrounds them.
- the supporting structures have at least one connection with this external structural element, which can in particular form one or more complete links and / or pivot links.
- the supporting structures can be fixed and have adjustable flaps or panels, arms and / or fixing notches, making it possible to flexibly decide the position and orientation of the carried antennas, for example according to the capacities and the number of these and the missions to be carried out.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Mechanical Engineering (AREA)
- Details Of Aerials (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1908260A FR3099001A1 (fr) | 2019-07-19 | 2019-07-19 | Aérodyne avec antenne et procédé d’agencement associé |
PCT/EP2020/069643 WO2021013589A1 (fr) | 2019-07-19 | 2020-07-10 | Aérodyne avec antenne et procédé d'agencement associé |
Publications (1)
Publication Number | Publication Date |
---|---|
EP4000130A1 true EP4000130A1 (fr) | 2022-05-25 |
Family
ID=68806941
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20736744.2A Withdrawn EP4000130A1 (fr) | 2019-07-19 | 2020-07-10 | Aérodyne avec antenne et procédé d'agencement associé |
Country Status (4)
Country | Link |
---|---|
US (1) | US20220320719A1 (fr) |
EP (1) | EP4000130A1 (fr) |
FR (1) | FR3099001A1 (fr) |
WO (1) | WO2021013589A1 (fr) |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2169866A (en) | 1985-01-23 | 1986-07-23 | Gec Avionics | Aircraft-mounted radome pod |
EP0600699B1 (fr) * | 1992-11-30 | 1999-05-06 | All Nippon Airways Co. Ltd. | Récepteur mobile pour signaux satellites radio diffusés |
US6844855B2 (en) * | 2002-01-25 | 2005-01-18 | The Boeing Company | Aircraft phased array antenna structure including adjacently supported equipment |
US8228248B1 (en) * | 2010-01-25 | 2012-07-24 | The Boeing Company | Dorsal high frequency antenna |
EP2782190A1 (fr) * | 2013-03-20 | 2014-09-24 | EADS Construcciones Aeronauticas S.A. | Ensemble antenne pour aéronef |
CN103887605B (zh) | 2014-04-04 | 2016-08-24 | 西安电子科技大学 | 结构功能一体化机翼天线 |
US10483630B2 (en) * | 2017-11-13 | 2019-11-19 | The Boeing Company | Wing leading edge antenna system |
US10435134B2 (en) * | 2017-12-12 | 2019-10-08 | The Boeing Company | Core structures for composite panels of an aircraft, composite panels and aircraft including the core structures, and methods of manufacturing the composite panels |
-
2019
- 2019-07-19 FR FR1908260A patent/FR3099001A1/fr active Pending
-
2020
- 2020-07-10 US US17/628,108 patent/US20220320719A1/en not_active Abandoned
- 2020-07-10 EP EP20736744.2A patent/EP4000130A1/fr not_active Withdrawn
- 2020-07-10 WO PCT/EP2020/069643 patent/WO2021013589A1/fr unknown
Also Published As
Publication number | Publication date |
---|---|
FR3099001A1 (fr) | 2021-01-22 |
WO2021013589A9 (fr) | 2021-03-18 |
WO2021013589A1 (fr) | 2021-01-28 |
US20220320719A1 (en) | 2022-10-06 |
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