• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an inter-satellite communication device for satellites operating within a constellation of satellites. The device comprises at least one dedicated optical terminal (51), at rated speed, to the orbital intra-plane communications links and at least one dedicated optical terminal, in nominal mode, to the orbital inter-plane communications links, each dedicated optical terminal. the orbital intra-plane communications being configured to transmit and receive optical signals with an optical terminal of the same satellite operating on the same orbital plane, each optical terminal dedicated to orbital inter-plane communications being configured to transmit and receive optical signals with an optical terminal of the same satellite of an adjacent orbital plane throughout its revolution on its orbital plane and each optical terminal dedicated to orbital interplanar communications having a field of view such that the half-angle at the apex of the latter is less than about 80 °.
    公开号:FR3051088A1
    申请号:FR1600741
    申请日:2016-05-04
    公开日:2017-11-10
    发明作者:Michel Sotom；Kernec Arnaud Le；Agnes Francastel；Dominique Potuaud；Gilles Fernandez
    申请人:Thales SA；
    IPC主号:
    专利说明:

    INTER SATELLITE COMMUNICATION DEVICE, SATELLITE AND CONSTELLATION OF ASSOCIATED SATELLITES
    The present invention relates to the field of satellite telecommunication. The invention more particularly relates to an inter-satellite communication device for satellites belonging to a satellite constellation. The invention may find application in satellite constellations requiring links between satellites of the same orbital plane and / or links between satellites belonging to different orbital planes. By way of illustration, FIG. 1 represents an example of satellite constellations 10 according to the invention as well as their inter-satellite links 11 (or ISL for * Inter Satellite Link * according to the English terminology). In a nonlimiting manner, it may be constellations of telecommunications satellites 10 in non-geostationary orbits such as low orbits (or LEO for <(Low Earth Orbit * according to English terminology) or medium orbit (also called MEO for * Medium Earth Orbit8) to provide high-speed, low-latency connections between ground users, which are built from multiple orbital planes, and in each orbital plane, several satellites move in near orbit. The satellite constellations may be polar or quasi-polar constellations whose orbital planes pass through or near the two poles.
    Figure 2 is an enlargement of Figure 1 illustrating links 11 between the satellites within the constellation. These links 11 may be between satellites 10 belonging to the same orbital plane 25, this being called intra-plane links 21 or between satellites 10 belonging to adjacent orbital planes 25 that are called inter-plane links 22. Each satellite is Thus, in connection with a maximum of four satellites 10. In FIG. 2, taking the direction of movement of the satellites as a reference, a satellite 10 may be connected with the two neighboring satellites moving in the same orbital plane in front of and behind it. and with the two neighboring satellites moving in orbital planes 25 adjacent to the right and left of the satellite 10.
    In order to establish links between them, some satellites 10 include inter-satellite communication terminals using radio frequency technologies. These satellites 10 use dedicated antennas for intra-plane orbital communications 21 and inter-orbital planes 22. By way of illustration, FIG. 3 represents an exemplary embodiment of a platform 30 of such a satellite known from FIG. prior art. This platform comprises two mobile antennas 32 for the inter-plane links 22 and two low mobility antennas 31 for the intra-plane links 21.
    These inter-satellite links 11, in radiofrequency technology, pose several problems in the case of use within a polar or quasi-polar constellation. Some problems arise from the fact that the azimuthal angle of an interplanar link 22 varies constantly with the latitude during the orbit and that the speed of variation of the azimuthal angle increases sharply as the two satellites approach pole. Other problems arise from the fact that it is necessary to avoid possible interference between all the beams present at the pole. In practice, inter-plane orbital links 22 can not be maintained for extreme latitudes, typically latitudes greater than about 60 ° and latitudes less than about -60 ° and must therefore be interrupted. The inter-satellite communication terminals are positioned and oriented so as to establish links with the right or left satellite (with respect to the direction of movement) and are capable of pointing in a given azimuth angular sector corresponding to these latitudes. Communications between satellites of neighboring orbital planes is therefore no longer available beyond these latitude values when the satellites pass through the pole regions.
    One consequence is that a new interplanar connection 21 must be established after crossing the pole and that this connection is not made with the same satellite. In fact, with reference to FIG. 4, if a satellite 10 operating in the central orbital plane 25 is considered, this satellite 10 is in connection with two other satellites 10 placed in orbital planes 25 on either side of the plane. 25 central orbital. In the region of the poles, the orbital planes 25 intersect and the satellite 10 which was to the right of the satellite considered (taking as a reference direction, the direction of movement of the satellites and considering a view from above with respect to the Earth ) will end up on the left of the satellite considered after passing the pole. It is the same for the satellite 10 which was on the left before the passage of the pole. As soon as the satellite 10 has passed through the region of the poles, that is to say that its latitude is greater than about 60 ° or less than about -60 ° depending on the pole crossed, the inter-satellite communication terminals reacquire the links inter-orbital planes 22 with the satellites 10 of the neighboring orbital plane 25. However, each terminal reacquires the link 22 with a satellite 10 different from the time when said link 22 has been interrupted. For example, the inter-satellite communication terminal which was positioned on the platform to be connected with the satellite on the right before the passage of the pole will have to reacquire the inter-plane link 22 with the new satellite on its right which was to his left before. This complicates the procedure a little more, especially since these operations of interruption and reacquisition must be carried out twice in orbit.
    An object of the invention is in particular to correct all or part of the disadvantages of the prior art by proposing a solution to avoid interrupting orbital inter-plane links at the poles. For this purpose, the subject of the invention is a communication device for satellites configured to evolve within a constellation of satellites, a satellite comprising a satellite platform, said device comprising a group of at least one dedicated optical terminal, in nominal mode, to orbital intra-plane communications links and a group of at least one dedicated optical terminal, in rated mode, to the inter-plane orbital communications links, each optical terminal dedicated to orbital intra-plane communications being configured to transmit and receive optical signals with an optical terminal of the same satellite operating on the same orbital plane, each optical terminal dedicated to orbital inter-plane communications being configured to transmit and receive optical signals with an optical terminal of the same satellite of an adjacent orbital plane throughout its revolution on its orbital plane and each optic terminal e dedicated to orbital interplanar communications having a field of view such that the half-angle at the apex of the latter is less than about 80 °.
    According to one embodiment, the device comprises at least four inter-satellite optical connection terminals, a first group of two optical terminals being located in front of said satellite and a second group of two optical terminals being located behind said satellite. satellite, each group of optical terminals comprising a dedicated optical terminal, at rated speed, to the intra-plane orbital communications links and a dedicated optical terminal, in rated speed, to the orbital inter-plane communication links, the two optical connection terminals. inter-satellites of the same group being separated by a predetermined distance so that the optical beam of the inter-plane orbital communication link is never obscured by another optical terminal of the satellite platform during its evolution on the Orbital plane.
    According to one embodiment, the two optical terminals of each group are placed in a position symmetrical with respect to an axis parallel to the direction of the trajectory of the satellite.
    According to one embodiment, the optical terminals are identical and interchangeable.
    According to one embodiment, the intra-plane and inter-plane communication links are transmitted and received on a wavelength band divided into two sub-bands, the optical terminals of the first group emitting optical beams on the first sub-band. and -bande receiving optical beams on the second sub-band, the optical terminals of the second group emitting optical beams on the second sub-band and receiving optical beams on the first sub-band.
    According to one embodiment, the intra-plane and inter-plane communication links are transmitted and received with two different polarizations, the optical terminals of the first group emitting optical beams with a first polarization type and receiving optical beams with the second one. type of polarization, the optical terminals of the second group emitting optical beams with the second type of polarization and receiving optical beams with the first type of polarization.
    According to one embodiment, optical beams are emitted and received on the optical band C.
    According to one embodiment, optical beams are emitted and received on the optical strip L.
    According to one embodiment, the satellite evolves in a non-stationary orbit. The invention also relates to a satellite configured to evolve within a satellite constellation distributed over several orbital planes, said satellite comprising a satellite platform on which is disposed an inter-satellite communication device as described above. The invention also relates to a satellite constellation comprising a plurality of satellites as described above.
    In one embodiment, the satellites evolve in a non-stationary orbit.
    In one embodiment, the satellites move in a low orbit.
    In one embodiment, the satellites evolve in a medium orbit. Other features and advantages of the present invention will appear more clearly on reading the following description, given for illustrative and non-limiting, and with reference to the accompanying drawings, in which: Figures 1 and 2, already presented respectively illustrate an example constellation of satellites and an enlargement of the latter; FIG. 3, already presented, represents an exemplary embodiment of a satellite platform known from the prior art; FIG. 4, already presented, represents an example of evolution of the inter-satellite links using inter-satellite radio frequency terminals, known from the prior art, in the vicinity of a pole; FIGS. 5a and 5b show exemplary embodiments of a satellite platform according to the invention; FIG. 5c is a graphical representation of the evolution of the amplitude of the field of view as a function of the distance between two optical terminals; FIG. 6a is a graphical representation of the evolution of the azimuth of an interplanar link as a function of time; Figure 6b illustrates the different angles between two satellites of the same constellation; FIG. 6c is a graphical representation of the evolution of the angle between an interplanar link and an intraplane link of the same satellite as a function of time; FIG. 7 illustrates an example of evolution of the inter-satellite links using inter-satellite link optical terminals during a half-orbit between a region around the south pole and a region around the north pole; FIG. 8 represents an exemplary embodiment of an inter-satellite link optical terminal with its associated electronics; FIGS. 9a and 9b respectively represent an example of spectral allocation and an example of use of the spectral band by the satellites of a constellation; FIG. 10 represents an exemplary embodiment of a satellite platform according to the invention.
    Subsequently, we will consider a view from above, with respect to the Earth, and we will take for reference the direction of movement of the satellites to designate the front and the rear of the latter as well as its right and left.
    An inter-satellite communication device comprises at least one dedicated optical terminal, in rated speed, to the intra-plane orbital communications links 21 and at least one dedicated optical terminal, in rated speed, to the orbital interplanar communication links 22. Each optical terminal dedicated to intra-plane orbital communications 21 is configured to transmit and receive optical signals with an optical terminal of the same satellite 10 operating on the same orbital plane 25 and each optical terminal dedicated to orbital interplanar communications 22 is configured to transmit and receive optical signals with an optical terminal of the same satellite 10 from an adjacent orbital plane 25 throughout its revolution on its orbital plane 25.
    FIGS. 5a and 5b show exemplary embodiments of an inter-satellite communication device according to the invention. This system can be installed on the platform 50 of a telecommunications satellite 10, that is to say the structure gathering the navigation and structure elements of the satellite, said satellite being configured to evolve within a constellation of satellites. This constellation can be a polar or quasi-polar constellation. The constellation comprises several orbital planes 25 and each orbital plane comprises several satellites 10.
    According to one embodiment, the inter-satellite communications device may comprise two groups G1, G2 of inter-satellite link optical terminals 51. A first group of two optical terminals 51 may be located at the front of the satellite platform 50. 10 and a second group of terminals 51 may be located at the rear of the platform 50 of the satellite. Each group G1, G2 of optical terminals 51 comprises an optical terminal 51 configured to establish, in nominal mode, an orbital intra-plane communication link 21 between the satellite 10 in question and another adjacent satellite 10 operating in the same orbital plane 25 as well as an inter-satellite link optical terminal 51 configured to establish, in nominal conditions, an orbital inter-plane communication link between the satellite 10 concerned and another neighboring satellite 10 operating in an adjacent orbital plane.
    The optical intra-plane link terminal 51 placed at the front of the platform of the satellite 10 in question is configured to establish a communication link with the optical terminal 51 of the adjacent satellite 10 operating in front of it. Similarly, the optical terminal 51 intra-plane link 21 placed at the rear of the platform of the satellite in question, to establish a communication link with the optical terminal 51 intra-plane link 21 of the adjacent satellite moving behind him.
    According to a preferred embodiment, the two inter-satellite link optical terminals 51 of each group G1, G2 are placed in a substantially symmetrical position with respect to an axis 52 parallel to the direction of the trajectory of the satellite 10 and passing through the center of the platform 50. Advantageously, this particular arrangement of the terminals 51 allows the latter to be redundant and thus perform the same functions. In addition, this allows the terminals 51 to have the same field of view 53.
    This redundancy can also be obtained for slightly asymmetrical positions of the terminals 51.
    In FIGS. 5a and 5b, the optical terminals 51 of the same group G1, G2 are aligned along an axis substantially perpendicular to the direction of movement of the satellite. This configuration is in no way limiting and these terminals can be offset with respect to an axis substantially perpendicular to the direction of movement of the satellite.
    The two terminals 51 of each group G1, G2 may be spaced a predetermined distance d. The value of this distance d is chosen so that the communication link between the inter-plane optical terminal 51 considered and the optical terminal 51 of the adjacent satellite with which it is connected is never masked and therefore never interrupted. whatever the position of said satellite 10 adjacent to the adjacent orbital plane.
    With reference to FIG. 5b, if it is considered that the optical terminal 51 is defined by a cylindrical envelope, the apex half-angle α of the viewing field 53 of the optical terminal, with respect to a straight line parallel to the direction of the trajectory of the satellite 10, is given as a function of the distance d between the two optical terminals, their outer diameter D and the diameter φ of the optical beam by the expression:
    The value of the distance d separating the two optical terminals 51 is chosen in particular as a function of the orbit, the number of orbital planes 25 of the constellation and the number of satellites 10 per orbital plane 25. The value of this distance d can be determined so that the field of view 53 of the inter-plane optical terminal 51 is as wide as possible and so that said field of view 53 allows said optical terminal 51 to maintain its connection with the neighboring satellite, particularly in the region of poles when said satellite adjacent to the adjacent orbital plane 25 passes from one side to another of the satellite 10 considered.
    This particular position of the optical terminals 51 of inter-satellite link 11 makes it possible to maintain all the intra-plane links 21 and interplanar links 22 without interruption, especially when the satellites 10 cross the poles. This avoids having to reacquire the inter-plane link 22 after crossing the polar regions. This also avoids having to constantly update the connectivity of the constellation. Each satellite 10 remains connected to the same satellites by the same optical terminals 51 throughout its orbit.
    In addition, each satellite 10 of the constellation is always in relation to the same satellites 10 and thus the connectivity of the whole system remains the same. In addition, the fact of maintaining the inter-satellite links 11 without interruption always makes it possible to guarantee a maximum throughput for the traffic, the communications between the subscribers on the ground.
    Another advantage of the inter-satellite communication device 11 according to the invention lies in the fact that the two optical terminals 51 of inter-satellite link 11 of each group G1, G2 are identical and therefore interchangeable. Each of the two optical terminals 51 may be configured to function as well as an inter-plane link terminal 22 as an intra-plane link terminal 21. Thus, when one of the two optical terminals 51 fails, the optical terminal remaining can be reconfigured to replace the failed optical terminal 51 if the latter has a more critical function. In addition, since the two optical terminals 51 are identical, this change of function can be done in a software way and therefore without hardware reconfiguration. This allows a softer and lighter reconfiguration that can be performed by remote control from the ground. By way of illustration, FIG. 5c represents the evolution of the amplitude of the half-angle at the apex a of the field of view as a function of the distance between two optical terminals 51 for two particular configurations. In a first configuration, the outer diameter D of the optical terminal 51 is 20 cm and the diameter φ of the optical beam is 12.5 cm. According to a second configuration, the outer diameter D of the optical terminal 51 is 25 cm and the diameter φ of the optical beam is 15 cm.
    FIG. 6a is a graphical representation illustrating the evolution, as a function of time, of the azimuth of an interplanar link 22 for a given constellation having several orbital planes 25 and several satellites 10 per orbital plane 25, the angle azimuth is defined relative to the direction of movement of the satellites. In this example, each satellite 10 travels its orbit for a time interval T of about 110 minutes and the azimuth changes between about -75 ° and + 75 °. Thus, for this configuration, the field of view 53 of the optical terminal 51 inter-plane connection 22 must therefore at least cover this range of values. The azimuth of the interplanar link 22 goes to zero when the satellites 10 intersect at the poles and by extrema when the satellite 10 passes through the equator.
    With reference to FIG. 6b, in the case of satellites of the same constellation, being at the same altitude, on different planes, with an exactly polar inclination, it is possible to give an analytical expression of the maximum azimuthal angle.
    For this, we consider two satellites located at the positions A and B, in two consecutive planes separated by an angle, and we consider β / 2 the phasing angle between satellites. The reference point related to the orbit of the satellite A is defined by: O: Center Earth, X: direction of the Ascending Node A, Y: normal to the orbit, Z: normal to the plane (X, Y).
    If we define the plane (A, Va, Na), in which Va represents the speed of the satellite A and Na represents the normal to the orbit at A, and if we define B "as the projection of B in the plane ( A, Va, Na), the azimuth angle Az, between Va and (AB "), is then given by the following expression:
    In which a is the separation between the planes, β / 2 is the phasing angle between the first satellites of two consecutive planes, λ is the position in orbit of the satellite A.
    It is thus possible to choose the characteristic parameters defined above, that is to say the distance d separating the two optical terminals, their outside diameter D and the diameter of the optical beam by the expression φ, so that the half angle at the top of the field of view is always greater than the maximum azimuthal angle. Thus, each optical terminal 51 dedicated to orbital interplanar communications 22 has a field of view such that the half-angle at the aperture α of the latter, with respect to a straight line parallel to the direction of the trajectory of the satellite 10, is greater than at the maximum azimuthal angle but less than about 80 °.
    FIG. 6c illustrates the evolution, as a function of time, of the angle between the optical beam of an intra-plane link and that of an inter-plane link for the same satellite 10 in a configuration identical to the previous configuration . This angle has a maximum value when the satellite 10 is at the equator and has a minimum value when the satellite 10 of the neighboring orbital plane crosses the relevant satellite in the pole region. The graph shows that for this configuration, regardless of the position of the satellite 10 considered in its orbit, the measurement of the angle between an intra-plane link 21 and an interplanar link 22 is never less than a value between 5 ° and 10 °. Given the divergence of the optical beams of the terminals 51 inter-satellite link 11, which is of the order of a few microradians to a few tens of microradians, this difference is sufficient for the optical beams are not collinear and therefore n ' do not interfere with each other. Thus, the two links 21, 22 can be held together in the regions around the poles without the intra-plane and inter-plane links interfering with each other.
    FIG. 7 illustrates an example of the evolution of the inter-satellite links 11 using inter-satellite optical terminals 51 according to the invention during a half-orbit between a region around the south pole and a region around the North Pole.
    Advantageously, when the satellite 10 passes through a pole, the inter-satellite links 11 are always maintained. Thus, it is not necessary to interrupt the orbital inter-plane connection when the satellite approaches the region of a pole and then reacquires it when it leaves this region. Thus, it avoids having to conduct a pointing and acquisition phase that can be long, with a probability of failure during the restoration of the link which is not zero, which can further lengthen the procedure. We also avoid having to exchange information such as the relative position of satellites, ephemeris etc ...
    There is no need to permanently update the connectivity of the constellation at each passage of a pole and each optical terminal 51 is always connected to the same optical terminal 51 of the neighboring satellite 10. This can simplify the architecture of the optical terminal 51 and / or equipment associated with it and thus reduce their cost.
    Similarly, the fact that the inter-satellite links 11 are maintained regardless of the position of the satellite 10 in its orbit allows the constellation to always provide a maximum rate for communications between subscribers on the ground.
    FIG. 8 is a possible functional representation of an inter-satellite link optical terminal 51 according to the invention as well as electronic equipment with which it cooperates. The set may comprise a telecommunication processor 81 (or OBP for * 0/7 Edge Processor * according to the English terminology) configured to deliver the telecommunication signals to be transmitted by the inter-satellite link optical terminal 51 11 and receive the signals received by said optical terminal 51. This processor 81 may be connected with a laser communication unit 82 configured to transfer the signals in optical form. This unit 82 may comprise optical transmission and reception elements, amplification, pre-amplification, detection, modulation, demodulation, multiplexing and demultiplexing elements. Is the laser communication unit the same even connected to the optical terminal 51 inter-satellite link. The terminal 51 comprises the optical head and the beam pointing, deflection and orientation subassemblies for acquisition and tracking (or PAT for * Pointing, Acquisition and Tracking * according to English terminology) of the optical terminal. 51 with which he communicates. To drive the laser communication unit 82 and the optical terminal 51 the assembly comprises a control unit 83. This control unit 83 is configured to interface between these units and the on-board computer, to manage the power supplies and coordinate the actions of the different units. In addition, there are different ways to organize these functions into hardware units. For example, the control unit may be common to several optical terminals and thus control several optical heads and several laser communication units.
    FIG. 9a represents an example of wavelength spectral allocation for the optical terminals of an inter-satellite communication device according to the invention. The optical terminals 51 can use the optical bands C or L. Each optical terminal 51 of inter-satellite link 11 providing bidirectional links, the spectral band used can be split into two parts, in two sub-bands 91, 92. A guard band 93 is left free between the two subbands to avoid interference.
    According to an implementation variant, the two sub-bands 91, 92 can use different polarizations. For example, a first subband can use a right bias and the second subband a left bias or a horizontal bias and a vertical bias.
    The optical terminals 51 of the inter-satellite communication device according to the invention can transmit and receive the optical beams in different ways. By way of example, the optical terminals 51 of a first group G1, G2 of terminals may use a first subband 91, 92 in transmission and the second subband in reception. The terminals of the second group for their part use the second subband 92 in transmission and the first subband 91 in reception.
    According to one embodiment, the optical terminals 51 of the first group G1 of terminals use a first type of transmission polarization and a second type of reception polarization, the terminals of the second group G2 using the second type of transmission polarization and the first type of polarization in reception.
    FIG. 9b illustrates an example of use of the sub-bands 91, 92 by the satellites inside a constellation. Considering, for example, the number 35 satellite, the optical terminals placed at the front of the platform transmit using the first sub-band 91 and those of the group placed at the rear of the platform transmit using the second sub-band. 92. At the reception, the optical terminals placed at the front use the second sub-band 92 and those located at the rear use the first sub-band 91. The subject of the invention is also a satellite 10, for example telecommunication, comprising a satellite platform 50 on which is disposed an inter-satellite communication device as described above. By way of illustration, FIG. 10 represents an exemplary embodiment of a platform of such a satellite according to the invention. In this non-limiting example, the four inter-satellite link terminals are placed at the four corners of the platform 30 so as to maximize the field of view 53 of the terminals configured for the inter-plane orbital links.
    These satellites can be configured to evolve in a non-geostationary orbit. It may be for example a low orbit, typically an orbit less than about 2,000 kilometers in altitude, or a medium orbit that is to say an orbit of between 2,000 and 36,000 kilometers. 'altitude.
    Another object of the invention is a satellite constellation 10 according to the invention. This polar or quasi-polar constellation comprises several orbital planes 25 intersecting in the region of the poles, each plane comprising several satellites 10 interconnected by intra-plane optical links 21 and / or interplanar links 22.
    权利要求:
    Claims (14)
    [1" id="c-fr-0001]
    An inter-satellite communication device for satellites (10) configured to evolve within a satellite constellation, a satellite (10) comprising a satellite platform (50), said device being characterized in that it comprises a group of at least one optical terminal (51) dedicated, in rated speed, to the intra-plane orbital communications links (21) and a group of at least one dedicated optical terminal (51), in nominal mode, to the links of orbital interplanar communications (22), each optical terminal (51) dedicated to orbital intraplane communications (21) being configured to transmit and receive optical signals with an optical terminal (51) of the same satellite (10) evolving on the same orbital plane (25), each optical terminal (51) dedicated to inter-plane orbital communications (22) being configured to transmit and receive optical signals with an optical terminal (51) of the same satellite (10) d an orbi plan adjacent orbital plane (25) and each optical terminal (51) dedicated to the orbital interplanar communications (22) having a field of view such that the half-angle at the apex has the latter is less than about 80 °.
    [2" id="c-fr-0002]
    2. Device according to the preceding claim wherein said device comprises at least four optical terminals (51) intersatellite link (11), a first group (G1) of two optical terminals (51) being located in front of said satellite (10). ) and a second group (G2) of two optical terminals (51) being situated behind said satellite (10), each group (G1, G2) of optical terminals comprising a dedicated optical terminal (51), in nominal mode, the orbital intra-plane communication links (21) and a dedicated optical terminal (51), at nominal speed, to the orbital interplanar communication links (22), the two inter-satellite optical connection terminals (51) (11). ) of the same group (G1, G2) being separated by a predetermined distance (d) so that the optical beam of the interplanar orbital communication link (22) is never obscured by another optical terminal (51). ) of the satellite platform (50) during the its evolution on the orbital plane (25).
    [3" id="c-fr-0003]
    3. Device according to one of the preceding claims wherein the two optical terminals (51) of each group (G1, G2) are placed in a symmetrical position with respect to an axis (52) parallel to the direction of the trajectory of the satellite (10). ) and passing through the center of the platform (50).
    [4" id="c-fr-0004]
    4. Device according to one of the preceding claims wherein the optical terminals (51) are identical and interchangeable.
    [5" id="c-fr-0005]
    5. Device according to one of the preceding claims wherein the intra-plane (21) and inter-plane (22) communication links are transmitted and received on a wavelength band divided into two sub-bands (91, 92). , the optical terminals (51) of the first group (G1) emitting optical beams on the first sub-band (91) and receiving optical beams on the second sub-band (92), the optical terminals (51) of the second group (G2) emitting optical beams on the second subband (92) and receiving optical beams on the first subband (91).
    [6" id="c-fr-0006]
    6. Device according to one of claims 1 to 4 wherein the intra-plane communication links (21) and inter-planes (22) are transmitted and received with two different polarizations, the optical terminals (51) of the first group (G1). emitting optical beams with a first type of polarization and receiving optical beams with the second type of polarization, the optical terminals (51) of the second group (G2) emitting optical beams with the second type of polarization and receiving optical beams with the first type of polarization.
    [7" id="c-fr-0007]
    7. Device according to one of the preceding claims wherein optical beams are emitted and received on the optical band C.
    [8" id="c-fr-0008]
    8. Device according to one of claims 1 to 6 wherein optical beams are emitted and received on the optical tape L.
    [9" id="c-fr-0009]
    9. Device according to one of the preceding claims wherein the satellite evolves in a non-stationary orbit.
    [10" id="c-fr-0010]
    10. A satellite (10) configured to evolve within a satellite constellation (10) distributed over several orbital planes, characterized in that it comprises a satellite platform (50) on which an inter-satellite communication device is arranged. according to one of the preceding claims.
    [11" id="c-fr-0011]
    11. Constellation of satellites characterized in that it comprises a plurality of satellites (10) according to the preceding claim.
    [12" id="c-fr-0012]
    12. Constellation according to the preceding claim wherein said satellites (10) evolve in a non-stationary orbit.
    [13" id="c-fr-0013]
    13. Constellation according to one of claims 11 or 12 wherein said satellites (10) evolve in a low orbit.
    [14" id="c-fr-0014]
    14. Constellation according to one of claims 11 or 12 wherein said satellites (10) evolve in a medium orbit.
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    同族专利:
    公开号 | 公开日
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    FR3051088B1|2018-05-25|
    EP3242417A1|2017-11-08|
    EP3242417B1|2019-03-06|
    引用文献:
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    FR3051088B1|2016-05-04|2018-05-25|Thales|INTER SATELLITE, SATELLITE AND SATELLITE CONSTELLATION COMMUNICATION DEVICE|FR3051088B1|2016-05-04|2018-05-25|Thales|INTER SATELLITE, SATELLITE AND SATELLITE CONSTELLATION COMMUNICATION DEVICE|
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    US10742311B2|2017-03-02|2020-08-11|Lynk Global, Inc.|Simplified inter-satellite link communications using orbital plane crossing to optimize inter-satellite data transfers|
    US10084535B1|2017-04-26|2018-09-25|UbiquitiLink, Inc.|Method and apparatus for handling communications between spacecraft operating in an orbital environment and terrestrial telecommunications devices that use terrestrial base station communications|
    US10951305B2|2018-04-26|2021-03-16|Lynk Global, Inc.|Orbital base station filtering of interference from terrestrial-terrestrial communications of devices that use protocols in common with orbital-terrestrial communications|
    CN111786716A|2020-06-08|2020-10-16|东方红卫星移动通信有限公司|Low-earth-orbit communication satellite constellation networking structure and inter-satellite communication method|
    法律状态:
    2017-04-27| PLFP| Fee payment|Year of fee payment: 2 |
    2017-11-10| PLSC| Publication of the preliminary search report|Effective date: 20171110 |
    2018-05-01| PLFP| Fee payment|Year of fee payment: 3 |
    2019-04-29| PLFP| Fee payment|Year of fee payment: 4 |
    2020-05-05| PLFP| Fee payment|Year of fee payment: 5 |
    2022-02-11| ST| Notification of lapse|Effective date: 20220105 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1600741A|FR3051088B1|2016-05-04|2016-05-04|INTER SATELLITE, SATELLITE AND SATELLITE CONSTELLATION COMMUNICATION DEVICE|
    FR1600741|2016-05-04|FR1600741A| FR3051088B1|2016-05-04|2016-05-04|INTER SATELLITE, SATELLITE AND SATELLITE CONSTELLATION COMMUNICATION DEVICE|
    ES17169499T| ES2728744T3|2016-05-04|2017-05-04|Inter-satellite communication device, satellite and constellation of associated satellites|
    US15/586,862| US10003400B2|2016-05-04|2017-05-04|Inter-satellite communication device, associated satellite and associated constellation of satellites|
    EP17169499.5A| EP3242417B1|2016-05-04|2017-05-04|Inter-satellite communication device, associated satellite and satellite constellation|
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