WO2023078736A1 - Plateforme satellite et procédé de reconfiguration du faisceau électromagnétique d'une telle plateforme satellite - Google Patents
Plateforme satellite et procédé de reconfiguration du faisceau électromagnétique d'une telle plateforme satellite Download PDFInfo
- Publication number
- WO2023078736A1 WO2023078736A1 PCT/EP2022/079794 EP2022079794W WO2023078736A1 WO 2023078736 A1 WO2023078736 A1 WO 2023078736A1 EP 2022079794 W EP2022079794 W EP 2022079794W WO 2023078736 A1 WO2023078736 A1 WO 2023078736A1
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- WO
- WIPO (PCT)
- Prior art keywords
- satellite
- wall
- antenna
- strand
- strands
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims description 14
- 230000010287 polarization Effects 0.000 claims abstract description 29
- 239000002184 metal Substances 0.000 claims abstract description 23
- 230000010363 phase shift Effects 0.000 claims abstract description 20
- 230000005540 biological transmission Effects 0.000 claims description 15
- 230000005670 electromagnetic radiation Effects 0.000 claims description 7
- 230000017105 transposition Effects 0.000 claims description 5
- 238000005516 engineering process Methods 0.000 claims description 3
- 238000004364 calculation method Methods 0.000 claims description 2
- 230000005855 radiation Effects 0.000 description 39
- 238000010586 diagram Methods 0.000 description 6
- 238000013459 approach Methods 0.000 description 4
- 230000005404 monopole Effects 0.000 description 4
- 108091092919 Minisatellite Proteins 0.000 description 3
- 238000004891 communication Methods 0.000 description 3
- 230000000295 complement effect Effects 0.000 description 3
- 230000006978 adaptation Effects 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000008034 disappearance Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005684 electric field Effects 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000003071 parasitic effect Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
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
- H01Q1/288—Satellite antennas
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/08—Means for collapsing antennas or parts thereof
- H01Q1/085—Flexible aerials; Whip aerials with a resilient base
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/44—Details of, or arrangements associated with, antennas using equipment having another main function to serve additionally as an antenna, e.g. means for giving an antenna an aesthetic aspect
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q21/00—Antenna arrays or systems
- H01Q21/24—Combinations of antenna units polarised in different directions for transmitting or receiving circularly and elliptically polarised waves or waves linearly polarised in any direction
- H01Q21/245—Combinations of antenna units polarised in different directions for transmitting or receiving circularly and elliptically polarised waves or waves linearly polarised in any direction provided with means for varying the polarisation
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q9/00—Electrically-short antennas having dimensions not more than twice the operating wavelength and consisting of conductive active radiating elements
- H01Q9/04—Resonant antennas
- H01Q9/16—Resonant antennas with feed intermediate between the extremities of the antenna, e.g. centre-fed dipole
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/26—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture
Definitions
- the invention lies in the field of antennas arranged on satellites, for HF, VHF, UHF radiocommunications: the antennas usually used are dipole or monopole antennas, each dimension of the size of the satellite being smaller than the wave length.
- a dipole antenna consists of the combination of two metal strands. It is powered in its middle and intended to transmit or receive electromagnetic energy.
- the strands are usually aligned along the same axis, which defines the linear polarization of the transmitted or received wave.
- a dipole antenna is usually used when the length of each of its two strands corresponds to a quarter wavelength. The resonance of the mode which is established there makes it possible to simply adapt the antenna to the traditional transmission lines.
- the intensity of the field produced is maximum in the plane orthogonal to the dipole.
- the two pairs of strands are excited in their center with two electromagnetic signals, making it possible to radiate two independent signals in the two orthogonal linear polarizations.
- the maximum radiation directions corresponding to each dipole will however be located in orthogonal planes.
- the plane where the field radiated by a dipole is maximum corresponds to a zero intensity field for the dipole arranged orthogonally with respect to the first.
- Such dipole antennas have already been fitted to nanosatellites.
- a nano satellite or a mini satellite has dimensions comparable to a fraction of a wavelength: it interferes significantly with a dipole antenna, which significantly affects its own radiation.
- the first approaches followed in the scientific community favored a symmetrical positioning of the dipole with respect to the nano satellite in order to avoid the excitation of parasitic resonances on the body of the satellite, and to reduce its diffraction or even a remote positioning of the body of the satellite. satellite.
- layout constraints which are added to all the other specifications (diversity of direction of radiation, diversity of polarization).
- beam formation is applied in a known manner to identical radiating elements, the individual radiation of which covers the entire specified angular sector. Beamforming then makes it possible to increase the gain of the antenna, and to produce a more directional beam, which can be oriented in a more specific direction within this angular sector, using a beamformer which distributes to the different elements the same signal assigned a phase weighting.
- This approach could not be applied in the application cases of the dipole or monopole type of the prior art described above, because due to the constraints of installing the antennas to reduce diffraction, it is not possible to produce several radiating elements having the same radiation pattern.
- the present invention describes a satellite platform comprising:
- the second idea then consists in having, on the contrary, radiating elements which have complementary radiation diagrams, making it possible to cover by adds the entire specified angular region, ideally for each of the principal polarization components.
- said satellite platform will include one and/or other of the following characteristics:
- the strands are attached to the periphery of the first or second wall in the plane from which they extend, said strands further extending outwards from said wall;
- the strands are made using tape measure technology
- the present invention describes a method for implementing an electromagnetic beam of a satellite platform comprising:
- said satellite platform will include one and/or other of the following characteristics:
- the strands are attached to the periphery of the first or second wall in the plane from which they extend, said strands further extending outwards from said wall;
- Figure 1 is an illustration of the radiation of a dipole antenna, as known from the prior art
- Figure 2 is a representation of a satellite platform in one embodiment of the invention.
- Figure 3 is a schematic representation of beamforming in one embodiment of the invention.
- Figure 4 illustrates the connection between the strands and the satellite in one embodiment of the invention
- Figure 5 is a representation of unit radiation patterns in polarization for each of 6 antennas in one embodiment of the invention.
- FIG. 6 is a representation of the unitary radiation patterns in polarization E e for each of 6 antennas in one embodiment of the invention
- FIG. 7 is a representation of a radiation pattern in E ⁇ p polarization obtained by forming beams in one embodiment of the invention
- FIG. 8 is a representation of a radiation diagram in E e polarization obtained by forming beams in one embodiment of the invention.
- FIG. 2 schematically represents a satellite platform 10 in one embodiment of the invention, in orbital trajectory at a distance d from the earth T 20, d between 500 and 1000 km.
- the satellite platform 10 comprises a satellite 13 delimited by its metal satellite envelope 11, describing here substantially a parallelepiped (generally, of dimensions at least 12 or
- the satellite platform 10 further includes solar panels 16 deployed around the satellite casing 11 .
- the metal casing 11 comprises a wall 12, arranged facing the earth 25, a wall 14 facing the wall 12, in the direction opposite to the earth 25 and four side walls 15 extending from one to the other of the walls 12, 14 and thus closing the casing 11.
- the wall 12 will be referred to below as the earth facing wall and the wall 14 as the anti-earth facing wall.
- the satellite platform 10 comprises an antenna system 17 comprising N antennas A1, A2, ..., AN, with N greater than or equal to 2.
- the antenna system 17 comprises N antennas A1, A2, ..., AN, with N greater than or equal to 2.
- the 17 operates in HF, VHF or UHF frequency bands, the length of which wave is between 0.5 and 5 meters.
- the dimensions of the satellite 13 are of the order of several tenths of a wavelength; the width D1, the length D2, the height D3 are each less than the wavelength, for example between a wavelength and a wavelength.
- the antenna system 17 is in the VHF band, operating at 150 MHz, corresponding to a wavelength of 2 meters, and is fixed to the envelope 11 of the satellite 13, of dimensions D1 ⁇ D2 ⁇ D3 equal to 20 cm ⁇ 20 cm ⁇ 40 cm (the satellite 13 in other embodiments is a mini-satellite, the dimensions of which are comparable to the wavelength).
- the length of each metal strand is a quarter wavelength. Such a length allows the establishment of a quarter-wave mode on the metal strand, which facilitates the adaptation of the antenna (it will be noted that it is also possible to have a length corresponding to a half-wave; a higher mode would be established on the antenna, which would also allow its adaptation, with radiation from each different radiating element).
- each antenna Ai comprises a metal strand, (the strand n°i) and the metal casing 11 of the satellite 13.
- Each antenna Ai is powered by an electrical connector adapted to inject a useful electrical signal to the strand i at one end of the latter and for the also inject into the satellite envelope 11. Electric currents are established on the walls of the satellite. A global resonance can then be established on the metal strand - satellite assembly.
- each strand extends in the plane of the wall 12 facing the earth or in that of the wall 14 facing the anti-earth.
- the direction of the strands (defined by the vector starting from the end of the strand connected to the electrical connector towards the other end) is distributed spatially, so as to obtain complementary maximum radiation directions (also called preferential directions of complementary radiation).
- the strand power connectors are located on the periphery of the earth facing wall 12 (or anti-earth facing wall 14), the strands then extending mainly outside the wall. This makes it possible to establish primarily vertical currents (along the Oz axis) on the side walls 15 of the satellite.
- N 6 and the 6 strands, referenced 1, 2, 3, 4, 5, 6 anchored to the periphery of the wall 12 extend mainly outside the wall 12, in the plane of the wall 12 facing the earth, corresponding here to the small side of the satellite. Any two adjacent strands are spaced apart by +2TT/N (here TT/3).
- the strands, all positioned in the plane of the earth facing wall 12 or all positioned in the plane of the anti-earth facing wall 14 are spaced angularly by 90 °.
- N is the total number of antennas on the platform, each comprising said satellite casing and a respective metal strand extending in the plane of the first or second wall.
- these metal strands are made with tape measure technology.
- Tape measures are flexible tapes having an arcuate cross-section, the radius of curvature of which is convex on a first side of the tape and concave on a second side of the tape.
- the strand can thus be in the rolled-up configuration, occupying a limited volume, before the commissioning of the antenna and be deployed, and rigid, as soon as it is put into service, the ribbons being able to pass from the rolled-up state to the deployed state essentially thanks to their own elastic energy.
- Measuring tapes are therefore well suited for the manufacture of deployable wire antennas and for minimizing the mass of the antenna.
- the injection of the electrical signal into each antenna Ai between the strand and the satellite envelope is carried out by means of a connector 60, here a coaxial cable, arranged between the electronic module adapted to supply this signal in transmission (and/or to process this signal in reception; in one embodiment,
- the central core 61 of a connector 60 is connected to the end of the satellite strand n anchored on the satellite.
- the peripheral crown 62 of the connector 60 is placed in direct contact with the wall
- the mass of the coaxial cable 60 is transferred to the metal mandrel 25 directly in contact with the wall 12 of the satellite (the mandrel 25 is attached to the wall 12 by tabs 26) (in another embodiment, the mass could be transferred of the coaxial cable directly on the earth face, at the level of the excitation of the metal strands).
- the end of the strands which is anchored to the wall 12 is anchored at the level of a mandrel 25 around which they were wound before the operational commissioning of the antenna system 17 for example (the deployment measuring tapes along their respective axis is ensured for example in an autonomous manner by their spontaneous unwinding following a step of releasing the tapes by the disappearance of fuse wires during the triggering of a high intensity current).
- the resulting radiation pattern for the antenna Ai would be very similar to that of a half-wave dipole as represented in FIG. very low (-45 dB in a simulated example).
- each radiating element (defined by a horizontal strand i and the nanosatellite) contributes on privileged angular zones
- the angular zones corresponding to two radiating elements with adjacent strands evolve by a rotation of 2TT/N, if there are N radiating elements.
- Figure 5 (respectively Figure 6) highlights these angular sectors, representing, as a function of the angles A, B, the radiation according to the component Eq, (respectively Ee) in the configuration considered in Figure 2 for each antenna A1 , ..., A6, represented in gray levels from -20 dBi, in steps of two.
- the preferential angular sectors corresponding to the two components Eq,, Ee are orthogonal. Radiating elements having metal strands oriented in opposite directions (such as strands 1 and 4, or links 2 and 5, or links 3 and 6) contribute to the same angular sectors. This effect is particularly marked for the radiation in Eq polarization, which is mainly produced by the metallic strand and the currents on the earth-facing wall 12 of the satellite.
- the radiation patterns in Ee polarization, for which the side walls 15 of the satellite contribute, are less symmetrical, probably due to stronger currents on the side faces 15 located on the metal strand side.
- the satellite platform 10 comprises an electronic beam-forming device 50 represented schematically in FIG.
- the attenuator 31 J is adapted to apply an attenuation gain to the signal from the processing chain i qi supplied to it as input and the phase shifter 32_i is adapted to apply a phase shift to the signal from the processing chain i supplied to it entrance.
- the values of the gains and the phase shifts for each chain n°i are controlled by the controller 40 according to the specified privileged direction and the specified polarization for the radiation of the antenna system 17.
- an electrical signal S carrying the useful information to be transmitted by the antenna system 17 is divided into N signals, one of these signals being provided at the input of each processing chain.
- the electrical signals delivered by the antenna connectors A1, ..., AN are each phase shifted, then attenuated, with on each chain i, an attenuation and a phase shift of values determined by the controller selectively for each chain i, depending on the direction specified and the polarization specified for the radiation picked up by the antenna system 17.
- the beam forming can be done in analog or after frequency transposition, in digital.
- the values of the attenuation and phase shift coefficients for each chain i, depending on the direction specified and the polarization specified for the radiation from the antenna system 17, are determined, in a phase of prior calibration, by a "conjugate matching" process, maximizes the gain in a given direction, or an MMSE processing process ("minimum mean squared error") which maximizes the gain in a given direction, while minimizing interference in the other directions.
- the ‘Conjugate Matching’ process calculates the weighting applied to the different radiating elements to maximize the gain in a direction 6, cp, and for a given polarization. It calculates the attenuation and phase shift coefficients so that they are the combined coefficients of the illumination law of the various radiating elements, illuminated by a plane wave with the considered polarization, and incident in a direction 0, cp.
- the diagrams of the individual radiating elements give their responses in incidence. Therefore, the amplitude coefficients vary in the range of values between 0 and -20dB, and the phase law in the range of values between 0 and 360°.
- the controller 40 in embodiments, is adapted to, in response to a command received, control the switching between a beamforming and a basic configuration simply summing the individual diagrams (without beamforming), or even a minimal configuration by feeding for example only a few antennas.
- the size of satellite 13 determines the surface current distributions established there.
- Longer side walls 15 (larger D3) for example could be the support of a higher order mode for the vertical currents being established along these side walls.
- a satellite with larger walls 12, 14 will increase the radiation according to the component Eq,.
- the mode of operation remains the same, as regards the complementarity of the angular sectors associated with the components Ee and Eq i .
- Commercial electromagnetic simulation tools now make it possible to predict this global operation with precision, by modeling the antenna system and its satellite environment.
- the satellite platform 10 further comprises a ground plane 22 orthogonal to the side walls 15 of the satellite (ground plane 22 in the plane of the anti-earth wall 14 or parallel to this wall and located just under this wall 14 for example).
- This large ground plane 22 can be a very heavily perforated grid, the size of the openings of which is of the order of X/10; each side of this plane is at least 5 A. It could be deployed simultaneously with 16 solar generators.
- ground plane 22 makes it possible to significantly increase the gain in the upper half-space. It does not alter the operation of the antenna system 17 which is always reconfigurable in pointing and in polarization.
- the present invention thus proposes, in a manner compatible with the constraints inherent in small satellite platforms, a deployable antenna, reconfigurable in pointing direction and in polarization, making it possible to produce a beam whose gain is greater than that of an antenna omnidirectional, typically 2-5 dBi, in any direction within a wide angular sector (typically ⁇ 60°).
- the solution therefore responds particularly well to the constraints encountered in communications with terminals on land and which can move in very varied geographical sectors and have difficulty controlling the polarization of the transmitted signal, which is also affected by the propagation conditions in the atmosphere.
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- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA3237080A CA3237080A1 (fr) | 2021-11-04 | 2022-10-25 | Plateforme satellite et procede de reconfiguration du faisceau electromagnetique d'une telle plateforme satellite |
KR1020247018664A KR20240097917A (ko) | 2021-11-04 | 2022-10-25 | 위성 플랫폼 및 그러한 위성 플랫폼의 전자기 빔을 재구성하기 위한 방법 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2111690A FR3128830B1 (fr) | 2021-11-04 | 2021-11-04 | Plateforme satellite et procédé de reconfiguration du faisceau électromagnétique d'une telle plateforme satellite |
FRFR2111690 | 2021-11-04 |
Publications (1)
Publication Number | Publication Date |
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WO2023078736A1 true WO2023078736A1 (fr) | 2023-05-11 |
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ID=80787203
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/EP2022/079794 WO2023078736A1 (fr) | 2021-11-04 | 2022-10-25 | Plateforme satellite et procédé de reconfiguration du faisceau électromagnétique d'une telle plateforme satellite |
Country Status (4)
Country | Link |
---|---|
KR (1) | KR20240097917A (fr) |
CA (1) | CA3237080A1 (fr) |
FR (1) | FR3128830B1 (fr) |
WO (1) | WO2023078736A1 (fr) |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10347974B1 (en) * | 2018-01-26 | 2019-07-09 | Eagle Technology, Llc | Deployable biconical radio frequency (RF) satellite antenna and related methods |
US11152987B1 (en) * | 2019-09-25 | 2021-10-19 | United States Of America As Represented By The Administrator Of Nasa | Direction-of-arrival estimation for signal-of-opportunity receiver |
-
2021
- 2021-11-04 FR FR2111690A patent/FR3128830B1/fr active Active
-
2022
- 2022-10-25 KR KR1020247018664A patent/KR20240097917A/ko unknown
- 2022-10-25 WO PCT/EP2022/079794 patent/WO2023078736A1/fr active Application Filing
- 2022-10-25 CA CA3237080A patent/CA3237080A1/fr active Pending
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10347974B1 (en) * | 2018-01-26 | 2019-07-09 | Eagle Technology, Llc | Deployable biconical radio frequency (RF) satellite antenna and related methods |
US11152987B1 (en) * | 2019-09-25 | 2021-10-19 | United States Of America As Represented By The Administrator Of Nasa | Direction-of-arrival estimation for signal-of-opportunity receiver |
Also Published As
Publication number | Publication date |
---|---|
FR3128830A1 (fr) | 2023-05-05 |
CA3237080A1 (fr) | 2023-05-11 |
KR20240097917A (ko) | 2024-06-27 |
FR3128830B1 (fr) | 2023-11-03 |
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