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    • 专利摘要:
    system for reusing geo-allocated communications spectrum in a communications system based on the constellation of leo satellites, so that signals originating from leo satellite do not appear in the beamwidth of ground station antennas aimed at geo, and satellites configured to provide communications by manipulating their respective beam transmissions, which may include a forward beam and a backward beam whose angles are controlled to project the beam and reduce or eliminate the potential for interference with geo-pointed ground station antennas. the system and oil satellites can provide substantially 100% coverage of a ground station located at any point on the earth's surface, without coordination with geo satellites or geo-pointing ground stations. the system can also provide ground stations that are configured to enhance isolation between the geo communications system and the oil communications system using the same spectrum to reduce the potential for geo-pointed ground station antennas to pick up communication. of oil.
    公开号:BR112018072637B1
    申请号:R112018072637-0
    申请日:2017-05-03
    公开日:2021-06-01
    发明作者:Erlend Olson
    申请人:Theia Group, Incorporated；
    IPC主号:
    专利说明:

    1. FIELD OF THE INVENTION
    [0001] The present invention relates to the field of satellite communications and, more particularly, to systems, methods and devices for implementing a satellite communication system with low terrestrial orbit (LEO) satellites that provides reuse of reuse frequencies Geostationary Earth Orbiting (GEO) communication satellite. 2. BRIEF DESCRIPTION OF RELATED TECHNIQUE
    [0002] A large amount of microwave spectrum suitable for communications between earth stations and satellites is allocated by various national and international regulatory agencies for communications services involving geostationary earth orbiting (GEO) satellites. In the present situation, there is very little unallocated microwave spectrum remaining for allocation to new communications services that employ satellite-based communications systems as they are traditionally designed, built and operated. In addition, much of the existing spectrum allocated to GEO's satellite communications services is already consumed with existing applications, primarily for television distribution, existing telephony backhaul and government data movement. As such, it is unlikely that existing GEO satellite communications system operators will have the ability to retrofit any of their existing allocated spectrum to new applications as fast as such applications are growing.
    [0003] New industries with requirements for high volumes and high data rates are quickly emerging, and many applications within these industries require high data volume or high data rate global communications capabilities, and communications coverage outside the country. service areas of terrestrial-based networks. Some examples include remote sensing, remote control of unmanned aerial vehicles, video and image based communications (when contrasted with audio communications), video and image based machine for machine communications and control, and ultra high data transfers between two ground stations without transiting through a ground network. These applications are well suited for service by satellite communications systems built for that purpose. However, deployment of new satellite-based communications systems is largely limited by the lack of spectrum available for allocation.
    [0004] Today, satellite communications systems are well known and are responsible for many modern conveniences, which include the distribution of direct broadcast television to many parts of the world. Although there are currently some low terrestrial orbit (LEO) and medium terrestrial orbit (MEO) satellites and satellite constellations exclusive to communications functions, most communications satellites and systems today are of the geostationary terrestrial orbit (GEO) type.
    [0005] The International Telecommunications Union (ITU) as well as other government and regulatory bodies have recognized and allocated large swaths of radio frequency spectrum for use by GEO satellite for two-way communications between Earth and the satellite for a wide variety of purposes. The large number of GEO satellites in operation today has led to a situation where there is very little spectrum available for new satellite communications links. Most of the mobile earth station satellite communications can only be practically serviced by employing microwave frequencies, so that the antennas employed in the earth stations can be small and/or portable, and so the data rates that can transmitted with known data communications methods can be high. This imposes a practical lower limit on the frequencies of useful satellite-to-ground station communications, regardless of regulatory or assignment issues. Because of issues of atmospheric absorption and attenuation caused by rain, there is also a practical upper limit on the frequencies of useful satellite-to-ground station communications, regardless of regulatory or attribution issues. Between these practical limits, there is little unused spectrum available for new assignments, as most has already been allocated to ground-space communications with GEO satellite systems for fixed satellite services.
    [0006] Much of the spectrum in the so-called Ka and Ku bands is attributed to the uses of fixed satellite service, which employs a GEO satellite for the space segment, which, due to the fact that GEO satellites appear to an earth station at a fixed point in the sky, they are necessarily directional rather than omnidirectional. For example, the most popular use of spectrum associated with GEO at present is for direct broadcasting of television programs, which are received by small directional antennas at fixed-point earth stations, typically mounted in customer homes or buildings. The 3dB beamwidth of popular consumer grade direct scattering satellite antennas is on the order of 2-3 degrees, and they are highly directional. SUMMARY OF THE INVENTION
    [0007] This invention discloses a system to reuse communications spectrum allocated in GEO in a communications system based on the constellation of LEO satellites, in such a way that signals originating from the LEO satellite do not appear in the beamwidth of LEO antennas. earth station pointed to the GEO, however, the constellation of LEO satellites can have 100% coverage of an earth station located anywhere on the Earth's surface, at all times, without any coordination in any way with the satellites of GEO or ground stations that point to the GEO. Furthermore, this invention reveals the details of the ground stations associated with the LEO satellite communications constellation which intensifies the isolation between the GEO communications system and the LEO communications system using the same spectrum, taking measurements to prevent a GEO satellite from inadvertently picking up ground stations that intend to communicate with the revealed constellation of LEO satellites.
    [0008] Modalities of the invention provide a method for building and operating a low terrestrial orbit (LEO) satellite communications system that can reuse any existing spectrum allocated to GEO-based satellite communications services without causing interference to the communications system based on GEO. Among other parameters that the algorithm accepts as free variables, the present invention accepts a parameter within any practical range to create an angular guard band around any and all ground stations that are in a GEO-based communications system. The invention allows LEO-based communications simultaneously with a ground station (for LEO-based communications) located immediately next to a GEO-based ground station, at the same time, and over the same spectrum, without any need for the based system. in LEO to coordinate in any way, absolutely, with any GEO-based satellite or any GEO-based ground station. The system, method and devices are configured to simultaneously provide 100% global coverage, as revealed by the exemplary modalities of the LEO satellite constellation shown and described herein, to any ground station located anywhere, with no gaps or loss of contact at any time with any ground station.
    [0009] The system, devices, and method provide an array of low terrestrial orbit satellites that are configured to provide communications between communication devices and prevent energy radiated from a LEO satellite from appearing in the beamwidth of an antenna. ground station (ie, the ground station associated with the GEO satellite) pointed to a specific GEO satellite. The system, devices and method preferably implement LEO satellite-based communications while, however, communicating with a ground station associated with the LEO satellite communication services that is positioned immediately close to the ground station antenna (for example, from a ground station associated with the GEO satellite) aimed at a specific GEO satellite.
    [0010] According to preferred embodiments, the invention may be deployed with satellites, and preferably with LEO satellites, which are configured to manage communications by directing their respective communications beams away from interference with separate operating GEO satellites about ground stations aimed at the GEO and/or turning off transmission when the satellite beam (from the LEO satellite) would otherwise coincide with the beam from a GEO station antenna (eg a boresight from a LEO antenna GEO ground station). Modalities provide satellites configured with control mechanisms that direct the satellite antenna (or antennas) to control beam coverage to provide communications with ground-based devices such as a ground station, and/or telecommunications network that may be connected with one or more ground stations. Satellites are configured to handle communications such as, for example, communications between two ground stations, or between a ground station and a ground-based network. Satellites can be configured with antennas that direct communications to promote a controllable coverage beam or beams, which include a trail or trailing portion and a forward portion (relative to the direction of orbit). The beam angle from a satellite antenna preferably is adjusted as the satellite moves through its orbit. Under some embodiments, the satellite antenna is controlled to adjust the beam to maximize coverage without interfering with the GEO ground station antennas.
    [0011] According to some embodiments, the system can be deployed with a constellation of LEO satellites comprised of a plurality of LEO satellites configured with one or more controllable antennas that are used to manage the steering beam so as to avoid crossing or interference with GEO antennas, and, in particular, GEO antenna boresight. The satellites of the LEO constellation preferentially transfer communications with each other (for example, such as from an adjacent orbiting satellite to another adjacent orbiting satellite), such as, for example, when a LEO satellite beam from a satellite is turned off (in order to avoid a GEO antenna, and potential interference with it), another one of the LEO satellites picks up communication. Under some embodiments, an adjacent satellite may comprise an adjacent satellite in the same orbital plane as the transfer satellite, while under some other embodiments, the satellite receiving a communications transfer may be a satellite that is adjacent to the satellite. transfer, but in any other orbital plane (for example, where the satellite is in a different orbital plane with other satellites).
    [0012] The present invention provides benefits and advantages, a summary of which, without limitation to other benefits not listed, may include one or more of the following. The LEO satellite constellation can be configured to reuse any GEO communications spectrum without causing interference to GEO's mobile or fixed services under normal conditions. The LEO constellation can be designed to accept, as an independent variable, any practical parameter for a guard band angle around the GEO indicator vector of ground stations (GEO ground stations) with directional antennas that point toward a GEO satellite. The direction of the beam that is transmitted towards any ground station by the LEO satellite will preferably always be in a direction as opposed to the direction that a GEO satellite would be transmitting to the same ground station, with respect to the nadir at the ground station. Under some arrangements, the system can be deployed in which a simple directional antenna affixed to the ground station associated with the LEO system, which only has to be pointed towards both the north and south poles (depending on the ground station quadrant) , can provide additional isolation margin for the LEO communications link compared to a GEO communications link, both operating to ground stations placed at the same location and operating at the same time. In addition, the system can provide LEO communications that are deployed at the same frequencies as the GEO broadcast frequencies, but are controlled to avoid or minimize interference. The present system and satellites operating in combination with the system may spatially reuse GEO satellite broadcast frequencies for LEO satellite communications services.
    [0013] The resources described in connection with the system, the method or satellites employed to implement the method, or modalities thereof, may be provided jointly or in combinations, with one or more resources that are combined with one or more other resources. BRIEF DESCRIPTION OF THE DRAWING FIGURES
    [0014] Figure 1 presents the nomenclature used throughout this disclosure.
    [0015] Figure 2 is a diagram of the Earth illustrating satellites and an orbit through the four quadrants.
    [0016] Figure 3 is a diagram representing the earth and showing a real elevation that points to the angle between a directional antenna and a geostationary satellite.
    [0017] Figure 4 is a diagram representing the earth and showing the geometry of two satellites in an orbital plane of LEO.
    [0018] Figure 5 is a diagram representing the earth and showing two sets of overlapping geometries, and indicating direction vectors for LEO satellite locations as an LEO satellite constellation orbits.
    [0019] Figure 6A is a diagram representing the earth and showing a final case situation near the maximum latitude at which any earth station can be practically anticipated to communicate with a GEO satellite.
    [0020] Figure 6B is an enlarged partial view of the diagram of Figure 6A, which shows the top portion thereof.
    [0021] Figure 7A is a diagram representing the earth and showing a final case situation at the equator in which any ground station can be practically anticipated to communicate with a GEO satellite.
    [0022] Figure 7B is an enlarged partial view of the diagram of Figure 7A, which shows the top portion thereof.
    [0023] Figure 8 is a diagram representing the earth showing a portion of a plane to illustrate the invention, and represents a constellation based on LEO for communications with earth stations anywhere in the world.
    [0024] Figure 9 is a diagram representing the earth and illustrating communications beams associated with two satellites, according to the invention, which are represented transiting the sky over the equator from north to south.
    [0025] Figure 10A is a diagram representing the earth and illustrating the latitude of a satellite at any particular point in its orbit, y.
    [0026] Figure 10B is an enlarged view of the diagram of Figure 10A.
    [0027] Figure 11 is an illustration representing the earth and showing a constellation of satellites (not to scale), according to the invention, which complies with the specifications in Table 1 (Figure 14).
    [0028] Figure 12 is a diagram representing a flat antenna pattern of a simple loop antenna.
    [0029] Figure 13 is an illustration representing the earth and showing an exemplary arrangement of satellites comprising part of a constellation of satellites, according to the invention, and showing antennas provided on the surface of the Earth with representations of indications of maximum gain.
    [0030] Figure 14 is a Table, referred to as Table 1, which shows tabulations of the various parameters for the input parameters of a=5 degrees, β=5 degrees and h=1,800 km.
    [0031] Figure 15 is a Table, referred to as Table 2, which is similar to Table 1, but for the limiting case where β=0, the posterior angle never turns negative and the posterior beam angle X at the equator is 0.
    [0032] Figure 16 is a Table, referred to as Table 3, which is similar to Table 1, but for input parameters of a=10 degrees, β=10 degrees and h=800 km.
    [0033] Figure 17 is a Table, referred to as Table 4, which shows in-plane free space path loss (FSPL) calculated for various angles from a LEO satellite in a constellation that orbits at an altitude to a station terrestrial, compared to FSPL to a GEO satellite, on the same communications frequency. DETAILED DESCRIPTION OF THE INVENTION
    [0034] Referring to Figure 1, nomenclature used throughout this disclosure and the Figures and Equations is presented. Furthermore, in order to effectively illustrate and explain the invention, the diagrams and Equations presented are for a two-dimensional view of the system, with diagrams that are illustrated in Figures 2 to 13, and with Equations (1 to 19) that are presented in this document and a listing at the end of this section. A feature of the invention is that the LEO communications satellites in the constellation are in polar orbits. Because the plane containing geosynchronous satellites for which frequencies are to be reused are in an orthogonal orthogonal to any plane of the revealed polar orbiting LEO communications satellite constellation, the 2D configuration revealed in the diagrams and equations is simple projection from any LEO orbital plane of a 3D configuration. Therefore, 3D diagrams and Equations are designed extensions of 2D representations that are well understood and simple to produce by those skilled in the technique of orbital mechanics and analysis.
    [0035] Furthermore, more complex equations than those presented in this document, which accommodate the slightly ellipsoid shape of the earth and other higher order factors, are well known to those skilled in the art of orbital mechanics. The assumption of the earth being perfectly spherical is used by this disclosure to illustrate the principles involved and the mechanics of the invention, but it is not meant to form a limitation on any matter disclosed herein. The principles disclosed herein and the invention can be extended to accommodate non-spherical earth and higher order orbital elements without departing from the scope of the disclosure.
    [0036] Figure 2 illustrates the situation and provides a foundation for subsequent Figures. In Figure 2, a single plane of multiple LEO satellite planes of a LEO satellite constellation in a polar orbit is represented, with two of many satellites that would be in the OP orbital plane shown as indicated in LEO1 and LEO2. As would be typical for a LEO communications constellation, and as indicated in the Figure as LEO1 BEAM and LEO2 BEAM, LEO satellites typically create overlapping coverage beams for both transmission to and reception of signals from radio stations. ground. Within each coverage beam of a single LEO satellite, there may be multiple sub-beams, which enable frequency reuse and polarization within a beam, in communications functions with ground stations. Furthermore, as is well understood by those skilled in the art, beams and/or sub-beams can be steered in real time to accommodate various orbital elements and practical ground station issues. By filling in completely in the orbital plane, and by placing multiple orbital planes in regular angular longitudinal spacing, the entire earth can be covered at all times with beams from at least one satellite in the LEO communications constellation. The Iridium Communications Satellite Constellation is an example of such a constellation, owned and operated by Iridium Satellite LLC. However, the iridium system, as well as other systems, employs spectrum that is not the same as that employed by GEO satellite communications systems, and no more of such spectrum is available. Examples of satellites and their operations are disclosed in U.S. Patents 5,410,728 and 5,604,920, the entire contents of which are incorporated herein by reference.
    [0037] Referring still to Figure 2, points on the Earth's surface in the northern hemisphere are indicated as P1NE at 70 degrees north latitude, through P8NE, which meets at the equator. For each point P, a vector is extracted that indicates the boresight of a directional antenna that would point to a geostationary satellite if located at that point. In addition, the LEO satellite OP orbit path shown orbits in a clockwise fashion, however this is simply for convention in the Figures and nomenclature in this disclosure and does not limit the generality of this disclosure. Under the convention used in this document, for any point P in Quadrant 1 or 2, LEO satellites in polar orbit ascend from North and descend towards the South (in the direction of travel indicated).
    [0038] Referring still to Figure 2, as can be seen, any time a LEO satellite using the same frequencies as a GEO satellite for communications with a ground station passes over a point P, there is a spot in the path of orbit in which the LEO satellite is directly in-line between the GEO satellite and the ground station. Therefore, at that point, if the LEO satellite was transmitting on the same frequency as the ground station is set to receive from the GEO satellite, then interference would result, and the GEO satellite signal could be interfered with the LEO satellite signal, since both signals on the same frequency would be simultaneously received by the ground station antenna and the front end RF, even with a highly directional ground station antenna specifically targeted at the GEO satellite.
    [0039] Referring now to Figure 3, the angle that points to the actual elevation between a directional antenna at any point P on the Earth's surface, which points to any geostationary satellite, is indicated. The angle pointing to the azimuth is not shown and is not relevant for illustrating the operating principles since any azimuth angle in 3D would have the same projection on the orthogonal polar plane shown in Figure 3. Governing equations 1 and 2 provide the solutions for computing g for any latitude Φ. Equations 1 and 2 are established in the Table of Equations and below (the equation number that appears next to the equation, in parentheses):

    [0040] By way of example, and without limitation, the Table in Figure 3 computes the approximate elevation angle for a directional antenna in increments of 10 degrees of latitude, starting with 80 degrees of latitude, which is approximately the highest latitude under the which ground station line-of-sight communication links to GEO could be sustainable, at 0 degree latitude, which is the equator.
    [0041] Next, referring to Figure 4, the geometry of two satellites in an orbital plane of LEO is presented. In this Figure 4 and including Equations 3 and 4, the relationship between the spacing, s, of the in-plane LEO satellites and the subtended angle θ as measured from a vertex at the geometric center of the earth, C, is indicated. In this Figure 4, P is indicated at the equator. Equations 3 and 4 are stated below (the equation number that appears next to the equation, in parentheses).

    [0042] Next, referring to Figure 5, the two sets of geometries are superimposed, with the strong blue lines indicating direction vectors for LEO satellite locations as the LEO satellite constellation orbits, as seen in from P1NE and P8NE. In the overlay in Figure 5 it can be seen that as an LEO satellite approaches any point P on Earth from the North, a directional antenna on P that points towards the GEO satellite is pointing south.
    [0043] However, as any specific LEO satellite passes over and then passes beyond any point P, if it continues to transmit back towards the ground station at P, at some point it would transmit down from the boresight of any antenna that points towards the GEO satellite.
    [0044] In order for a satellite constellation of LEO to provide continuous coverage to any place on Earth, at least one satellite may be in view at all times from any point P on Earth, and the direction indicating from that satellite to point P may not be along the same vector as the indicating direction between point P and a GEO satellite. Therefore, during the period when a first satellite in LEO orbit must stop transmitting to point P in order to avoid interference with GEO signals arriving at the same time and place on the same frequency, another second satellite in LEO orbit must be available in view from point P in order to porte in any communications may be taking place between the LEO communications satellite constellation and the ground station at point P. Figures 6 and 7, which include the “magnified” views of these diagrams, will be used to demonstrate two final case situations, first, in Figures 6A, 6B at the near maximum latitude at which any ground station can be practically anticipated to communicate with the GEO satellite (latitude of approximately 70 degrees) and, second, in Figures 7A, 7B at the equator.
    [0045] Referring now to Figures 6A, 6B, computation is shown to compute the maximum spacing of two satellites in a polar LEO orbit that are, or could be, in communication with point P1NE at 70 degrees latitude, of such that both (a) the ground station is never without line of sight to an adequately orbiting LEO satellite far enough above the local horizon to be available for reliable communications, and (b) during the period when any satellite of Orbiting LEO is within a guard band around the vector between the ground station and a GEO satellite, another LEO satellite is in view (and far enough above the local horizon) to assume any communications function with the ground station from the first LEO satellite (since the first LEO cannot transmit to the ground station when it is within the guard band, so it does not interfere with satellite communications from GEO to the ground station).
    [0046] In Figures 6A, 6B, s should be found (see Equations 3 and 4), which is used to compute θ (see Equation 5) and thus the number of satellites in the required LEO orbital plane, submitted to the limits that the satellite orbiting at altitude h must be at least an angle α above the local horizon and maintain a guardband angle of β around the vector between the ground station and a GEO at angle y. The cosine formula is employed, first with respect to triangle C-P1NE-D to compute d, then with respect to triangle C-P1NE-A to compute a, then finally with respect to triangle A-P1NE-D to compute s, the previously computed d, the previously computed a, and the known angle w1. (Although Equation 8 can provide two solutions, the significant solution is used for the distance d.) The relevant equations are denoted as Equations 5 to 8, 9 to 12 and 11 to 13 which are set out below (the equation number that appears next to the equation, in parentheses).

    [0047] How can this be by comparing Figures 6A, 6B and Figures 7A, 7B, as a satellite in the constellation LEO approaches the equator and covers a point P with its communications beam, the distance between when the satellite ascends above the horizon and when it must stop transmitting to point P, as P also approaches the equator, it is reduced. Unlike the northernmost positions of the satellite and points P, however, the point P at the equator can also be communicated with by an LEO satellite that is moving away from the equator, or descending into the southern sky.
    [0048] Figure 8 shows a portion of a plan of the invention, which comprises a constellation based on LEO for communications with ground stations anywhere in the world, and which can operate simultaneously in spectrum allocated for use by GEO to ground station, which includes an earth station at the same time and place, which operates as will be further described below. Figure 8 shows three satellites (represented by the circles designated 1, 2 and 3) in an orbital plane at two different conceptual times, designated T=1 and T=2, which operate close to the equator to maintain a ground station at the Ecuador. Satellites 1, 2 and 3 at time T=1 are represented by solid line circles and at time T=2 are represented by broken line circles. Operations close to the equator are the limiting case for the invention, and therefore are shown in detail and the focus of much of the disclosure. In Figure 8, one of the satellites identified as “2”’ approaches the equator at T=1 and then crosses the equator, with point P8NE below it. In this Figure, point P8SE is introduced, the point being almost identical to P8NE, except just south of the equator while P8NE is just north of the equator. The northern horizon is indicated as NH and the southern horizon as SH.
    [0049] In the disclosed invention, as satellite 3 rises above the northern horizon NH by a chosen angle α relative to a ground station at P8NE at the equator, satellite 3 has the ability to create a communications link with P8NE . At the same time T=1, except for a time required for transfer, satellite 2, which was previously serving communications with P8NE, interrupts its communications with P8NE as it enters the P8NE's GEO satellite guard band. As satellite 3 continues to ascend through the northern sky of the P8NE, it continues to serve any communications needs of the P8NE, which may be on the same frequency as that used with any GEO satellite, without interfering with any communications that may be. occurring with said GEO satellite, until it reaches the indicated position of satellite 2 at T=1. At that time, a satellite 4 (not shown) will begin to appear above the northern horizon with respect to the P8NE, so that satellite 3 can turn off its communications link with the P8NE while it transits along the GEO guard band of the P8NE.
    [0050] Meanwhile, as satellite 2 leaves the guard band of P8NE at T=2, it can start serving P8SE, which is assumed to be in the same place on the equator as P8NE, except south of the equator. Before satellite 2 began P8SE service, P8SE was served by satellite 3, which is moving south of P8SE. Likewise, each point around the globe is covered by a satellite in the constellation.
    [0051] Referring now to Figure 9, the communications beams associated with two satellites in the disclosed invention are depicted as they transit around the sky over the equator from north to south. As stated previously, the beams Described are antenna patterns created by real-time adjustable beam antennas on LEO satellites, such as can be created with phasing array antennas, which are well known and understood to those skilled in the art. As also stated above, the beam envelopes may have within each of them several sub-beams for specific frequency reuse, polarization reuse or accommodation of other orbital elements or ground station elements which are, however, within the scope of the invention.
    [0052] Still referring to Figure 9, the beam angle forward with respect to the satellite is indicated as angle Φ and the beam angle backward is indicated as angle X.
    [0053] As indicated in Figure 9, around the descending semicircle of the communications satellite's polar orbit, for that portion during which a satellite is in quadrant 1, the LEO projects its communications beam forward in the direction it is traveling. , continuously, at an angle of Φ, which can be as large as a reasonable or feasible angle for communications with ground stations until the satellite's latitude, a, reaches a so-called latitude limit as it approaches the equator . With respect to the forward portion of the beam, as it approaches the equator, the LEO satellite directional antenna control means begins to reduce the forward angle of its forward beam as indicated as the identified satellite SAT2 progresses from T=1 to T=6 towards the equator.
    [0054] Furthermore, in Figure 9, now noticing the identified satellite SAT1, as it progresses from T=1 to T=6, its beam is extinguished over the equator and no communication occurs with that satellite from any ground station as it transits along the GEO guard band at the equator. After crossing the equatorial guard band in quadrant 2, SAT1 then expands what is now the indicator portion to the rear of its communications beam as indicated, such as when the satellite has reached the latitude limit angle away from the equator , the backward beam covers a maximum region behind it, as an image symmetrical to the forward beam communications coverage area produced in quadrant 1.
    [0055] Each satellite also controls the angle, X, of a so-called backward beam as shown in Figures 10A, 10B. Figures 10A, 10B also indicate the satellite's latitude at any particular point in its orbit, a. The parameters and identifications α, β, y, A, P, C, a and d are as discussed above in relation to Figures 6 and 7, and Equations 5 to 15 are operative as described above in relation to Figures 6 and 7 to compute the angles relevant geometric shapes and lengths of triangles. Once the lengths a and d are found, Equations 17, 18 and 19 are used to calculate Φ at the latitude limit and X as a function of a, for a given β and y. Equations 14 to 19 are set out below (the equation number that appears next to the equation, in parentheses).

    [0056] The tabulations of the various parameters appear in Table 1 (Figure 14) for the input parameters of α=5 degrees, β= 5 degrees and h=1,800 km. For those parameters, the computations outlined in red define primary elements of the disclosed invention, and the implementation of the satellite antenna control mechanism that regulates the beam and/or sub-beam projection, which shows: that 11 satellites are needed in each orbital plane polar, that the maximum required beam forward angle is 50.96 degrees, which the forward beam should start to limit at a satellite latitude of 34.04 degrees (which keeps indicating just beyond the equator as the even approaches the equator), and that the rear beam angle X should track the values indicated in the columns titled X and o, where o to the left of the long black line is treated as a dependent variable based on the LEO satellite that communicates with an earth station P as indicated in the first column. Note that as the equator is reached, the rear beam angle becomes negative, which indicates that the rear beam must start pointing somehow towards the front of the satellite, rather than the back of it, as the satellite approaches the equator in order to avoid transmitting boresight from an antenna pointed at a GEO satellite. In the limiting case where β=0, the posterior angle never turns negative and the posterior beam angle À at the equator is 0 (this situation is shown in Table 2, Figure 15). The columns under y and Φ to the right of the long black line in Table 1 (Figure 14) compute forward beam angle as a function of satellite latitude, where satellite latitude is now treated as an independent variable.
    [0057] To show how the disclosed invention is applicable to other parameters, Table 3 (Figure 16) shows the computations for input parameters of a=10 degrees, β=10 degrees and h=800 km. For those parameters, computations show: that 21 satellites are needed in each polar orbital plane to implement the method, that the maximum required beam forward angle is 61.04 degrees, and that the forward beam should start to limit at one 18.96 degree satellite latitude (which keeps indicating just beyond the equator as it approaches the equator). For example, still referring to Table 3 (Figure 16), when one of the satellites in the constellation approaches the equator in Quadrant 1, when its latitude references to the center of the Earth are 8.06 degrees North, its posterior beam should be 0.05 degrees or less, which therefore actually then the posterior beam is pointing forward.
    [0058] As can be seen in Figure 9 and 10, since one of the satellites in the constellation approaches the equator, its general beamwidth declines by the general governing equations to zero. However, as the beamwidth approaches zero, there is some practical limit to achievable satellite antennas. This practical limit can change based on the deployment methods for the antenna and its associated control function, and at that limit the beam can simply be turned off (no longer transmitting). When the additional margin associated with such a minimum beamwidth can be accommodated by adjusting the guard band, β.
    [0059] Satellites may be configured with a satellite control mechanism that controls satellite operations. For example, the control engine can determine the satellite's position, which includes its latitude, and can use the latitude position to regulate the projected beam that forms the satellite. Under some embodiments, the satellite control mechanism preferably includes computing components that are loaded by the satellite. The computing components preferably include a computer that is provided with software that includes instructions to monitor the satellite's positions along its orbit and regulate beams projected by the satellite's antennas. Any suitable mechanism for directing the antenna beam can be employed, which includes mechanical or electronic controls that limit, expand, direct or combine these methods to regulate the beam angle. The beam can also be formed from sub-beams. The satellite may be provided with one or more real-time adjustable beam antennas, such as, for example, a phasing array antenna, or other antennas that are known in the art. Satellite antennas can generate beam envelopes that can comprise multiple sub-beams for specific frequency reuse and/or polarization reuse. Under some embodiment, the beam envelope sub-beams can be configured to accommodate other orbital elements and/or ground station elements. According to preferred embodiments, the satellite is configured to produce one or more beams and, preferably, a beam may be provided with one or more forward portions, and one or more backward portions (e.g., in which a forward portion beam may comprise a first beam, and a trailing portion of beam may comprise a second beam). The beam portion can be regulated (eg, turning on or off) to limit the beam field or projection. According to some arrangements, the satellite control mechanism can be powered using the satellite power supply. Under some arrangements, system components can be powered with solar panels that can be deployed to the satellite for these and other purposes. The satellite beam control mechanism preferably includes computing components configured to process the satellite location information, and determine the beam angle to be provided by an antenna, such as, for example, a transmit satellite antenna. . The control mechanism preferably manipulates the beam angle, according to determinations from the satellite location information and the application of the positioning as established in this document, and, in particular, according to the modalities provided represented by the Equations in the present document (see for example, Equations 5 to 13). Satellites can be equipped with antennas suitable for communications with ground stations. For example, phasing array antennas, helical antennas or other suitable antennas can be provided. Additionally, satellites can be configured to communicate with other satellites. Suitable antennas such as lenses for satellite cross-link communications can be provided. For example, adjacent satellites can communicate with each other. Satellites can also be provided with devices for routing signals such as communications and data. For example, the satellite can be configured with one or more switching units that process information such as the communication destination, and route the communication through an appropriate satellite. Under some embodiments, satellites are configured to route communications to a ground station within the satellite's leave range, and the ground station may be connected to a network that routes communication to a designated destination. Similarly, transitions from a ground station can be received by a satellite, and the satellite can route that communication to a destination, such as a device. For example, under some embodiments, the satellites and the satellite system can preferably carry datagrams between any satellite and a ground-based terrestrial network. Ground stations, which can be configured as or in association with a gateway station, can receive and transmit signals, such as datagrams, between a satellite. This can be carried by means of immediate retransmission of the datagram to a gateway station in view of the same satellite (i.e., left pipe), where data is transmitted to the satellite from a ground station or gateway, and the satellite sends it back again. In some embodiments, the signal or data may be sent unmodified, other than processing to retransmit the signal back (which may involve one or more of the signal amplification, changing the uplink/downlink frequency for retransmission. according to other embodiments, the satellite can be configured with equipment that can be used to perform on-board signal processing, such as, for example, to demodulate, decode, recode and/or modulate the signal (for example, via a transponder Under some preferred modalities, transport of datagrams between any satellite and a ground-based terrestrial network can be performed by means of a cross-link to one or more other satellites in the satellite constellation and then from those other satellites to a communication port. For example, the intended communication port may not be in view of the first satellite at any particular time, however, it may be in view of one of the other satellites in the satellite constellation. A satellite in view of the gateway can receive a datagram routed from another satellite (for example, the first satellite). The constellation satellites can preferably be configured to crosslink, and route transmissions through their respective crosslinks.
    [0060] The equations and tables can be rearranged with direct mathematical manipulations well known to those skilled in mathematical techniques, to enable any particular parameter shown to be a free variable, which enables the rest of the satellite constellation orbital elements and arrays of indication of satellite antenna to be computed thereafter, without departing from the scope of the present invention.
    [0061] It is readily understood from the symmetry of the invention revealed that satellites operate in symmetrical image of each other in each quadrant. That is, the geometry, antenna patterns and operation of the satellites in a plane in quadrant 1 are mirrored around the equator to generate quadrant 2, which is then mirrored around the north-south geometric axis of the earth to generate quadrant 3 and then mirrored around the equator to generate quadrant 4. The details of a satellite that crosses the equator were presented in detail as this is the highest potential place for interference, and this, how far it crosses the equator , the most effective interference avoidance technique is to simply have the equator bypass satellite interrupt that transmits to ground stations when within the guard band around the GEO indicator vector. This also allows the satellite enough time to reorient the antenna system to the subsequent quadrant. When a satellite is over the poles, its antenna indicator system must also be reoriented, however the mechanics of that can be performed in an unlimited manner in any way properly designated by those skilled in the art, in that there is no geostationary communications possible at the poles, as the geostationary satellite may be in view from the poles.
    [0062] It should be noted that the drawings in Figures 8, 9 and 10 imply that the LEO communications beam intersects the ground exactly at the equator. In practical deployment, the beam would extend forward beyond the equator as the satellite reaches the equator, to an extent necessary to accommodate various uncertainties in orbit and antenna patterns, as well as to accommodate the time needed to transmit from the other. satellite of LEO as it enters the guard zone over the equator. This practical matter is easily accommodated without departing from the scope of the invention.
    [0063] An option that complicates the design of the satellite antenna and antenna control system is as follows, but remains within the scope of this invention. The beam envelope that was revealed above is typically composed of many sub-beams. Certain sub-beams can be turned off or redirected as the satellite passes over or near the equator, which enables additional communications support for areas above and below the equator, without causing the satellite to interrupt all transmissions to ground stations. This option, however, requires careful control of standard satellite antenna sidelobes, which can add expense and may not be technically possible for certain antenna deployment methods.
    [0064] Because the orbit of the revealed satellite constellation is polar, the azimuth plane of the LEO satellite constellation can be operated independently of the elevation plane that has been thoroughly described in this document. As such, the number of planes to complete global coverage can be designated as an independent variable in relation to the operation of satellites and their antenna patterns in a plane. For example, the LEO-based communications system can be designed to cover 30 degrees of longitude to the right or left of the orbit plane, while operating simultaneously as provided in this disclosure, and as above, in relation to Table 1 (Figure 14) , for example, within the orbit plane.
    [0065] Figure 11 shows a complete satellite constellation (not to scale) that conforms to the specifications in Table 1 (Figure 14), with 11 satellites per plane and 6 planes (only three being represented in the Figure), at one height of orbit of 1800 km in the required polar orbit. As seen in Figure 11, each plane can be filled such that the satellite within the plane has the equator crossing time of each satellite slightly offset from the neighboring plane, which, depending on the selected plane spacing, can provide assistance added to cover ground stations near the equator that are closer to a neighboring orbital plane.
    [0066] The method of subsequent communications between the class of communications constellations of LEO disclosed in this document and an additional terrestrial terminal or terrestrial communication port is flexible and can be either by means of a terrestrial communication port within the view of each satellite in a so-called bent-pipe architecture, or it can be through a cross-connected architecture such as that deployed by the iridium satellite constellation. Both deployments are possible with the disclosed invention, and both can be implemented to complete a communications link between a ground station, a satellite operated within a satellite constellation as disclosed herein, and another ground station, or other ground data or communications network.
    [0067] In addition to the isolation provided between the GEO communications satellites, ground stations involved with GEO and the LEO-based communications system disclosed in this document which is provided by the operations geometry and antenna system, there are additional features of the system revealed in relation to ground stations that communicate with the LEO satellites that can now be described. When a ground station transmits to a LEO satellite in the revealed system, the transmission must only bridge the distance to the LEO satellite, which requires considerably less signal energy than that required to bridge the distance to a GEO satellite on the same frequency. This situation is shown in Table 4 of Figure 17, which shows the in-plane free space path loss (FSPL) calculated for various angles from a LEO satellite in a constellation that orbits at an altitude of 800 km to a station terrestrial, compared to FSPL to a GEO satellite, on the same communications frequency of 12 GHz (Ku Band). Calculations show a minimal difference in path loss of 33dB. The difference in path loss provides a significant link margin to further reduce the possibility that a signal transmitted by a ground station with an omnidirectional antenna that is intending to transmit only to a LEO satellite is, however, recognized by a GEO satellite which listens on the same frequency, which thereby causes an interference with GEO's satellite communications system.
    [0068] Still referring to Table 4 shown in Figure 17, the same path loss data provides the basis for the ability of a ground station associated with the LEO satellite communications constellation that has an omnidirectional antenna to prevent the interference thereto from a GEO-based communications signal. Because the LEO satellite is isolated from GEO-based receiving stations by geometry, the LEO satellite can transmit at energies such that the ground signal energy received by stations associated with the LEO system can be much more than the same energy received by an omnidirectional antenna at the same frequency from a GEO system, which thus provides the ability for the ground station associated with the LEO to reject the much weaker signal from the GEO satellite. GEO, by means commonly known to those skilled in the art of receiver design.
    [0069] Notwithstanding the previous paragraph, additional binding margin may be desired to accommodate wider operating envelopes in a given system design. Therefore, the revealed LEO system can be paired with ground stations that are designed to communicate exclusively with the LEO satellites, even though they are communicating on the same frequency as a ground station that communicate with a GEO satellite well to your side. An additional optional element of the LEO satellite based on the disclosed communications system is to add a directional antenna to the ground station. Although a full azimuth and elevation directional antenna with a small beamwidth is an option, such an antenna is often prohibited in cost, size, weight or energy for certain applications. However, with the LEO satellite operating as described above it provides a communications direction that is always pointing north in the northern hemisphere, and pointing south in the southern hemisphere. This fact allows for a dramatically simpler directional antenna to be employed by the ground station. The flat antenna pattern of a single loop antenna, which is oriented perpendicular to the ground, is shown in Figure 12. Even this single antenna provides as much as 12 dB of additional link margin at a point P on the equator, and even more to higher latitudes. The only requirement on the earth station is that the antenna's highest gain direction be pointed generally south if the earth station is in the southern hemisphere, or generally north if the earth station is in the northern hemisphere.
    [0070] Referring now to Figure 13, it is shown that by pointing the maximum antenna gain away from the direction of the GEO satellite, and towards the direction of the LEO satellite, additional margin is obtained to assist in minimizing the possibility of transmissions from the LEO ground station are received with sufficient power by a GEO satellite system to be recognized. This requirement of being generally pointing north or south, depending just on which hemisphere the ground station is in, is a much simpler requirement in a ground station directional antenna than the requirement to be fully azimuth and elevation direction capable, which, in this way, it makes the LEO-based system revealed more cost-effective for mass deployment. Other similar patterns from other types of antennas can be created that are well known to those skilled in the art of directional antennas that can provide the same or additional larger margins with economical deployments, without departing from the scope of the disclosure.
    [0071] References are made to a ground station that receives and transmits communications between it and the LEO satellite. The ground station may include antennas that are located on the ground to receive transmissions from and/or send transmissions to LEO satellites. The earth station antennas can be any suitable antennas and in particular RF frequencies to and from LEO satellites. Each LEO satellite can be configured with, and preferably, a plurality of antennas. For example, an LEO satellite may have a first antenna that transmits a forward beam in a forward direction and a second antenna that transmits a backward beam in a backward direction (for example, relative to the satellite's orbit direction. ), in which the antennas can be independently controlled, and can limit or expand their respective beams or extinguish them. Satellite antennas can comprise one or more phasing array antennas. For example, the phasing array antenna can be configured with a number of individual radiating elements that are controllable to control beam coverage and, in particular, beam configuration and angle. A computer on the satellite, which, in some embodiments, may comprise a dedicated computer programmed with instructions for manipulating the beam angle (which, for example, may include software stored on a chip or other circuitry component that contains the instructions), can be used to control the antenna array to generate a beam projection that can be increased or decreased and conformance to satellite orbit, and that can be performed to maximize coverage for an antenna. The computer is preferably configured with software that contains instructions for regulating the operation of the antenna to eliminate transmissions that might otherwise interfere with GEO satellite communications (which includes where LEO satellite and GEO satellite transmissions use the same spectrum). This can be accomplished by controlling the beam angles of the projections from the antennas as well as turning the antennas off as needed (eg when within the guardband range of a GEO ground station antenna). According to some preferred embodiments, the computer can be configured to manipulate the beam projections in accordance with the provisions set forth herein. The satellite beams are preferably manipulated mechanically, electronically, or both, to generate a desired coverage beam and avoid transmissions within the guardband of a GEO satellite antenna (e.g., from a GEO ground station).
    [0072] These and other advantages can be realized with the present invention. While the invention has been described with reference to specific embodiments, the description is illustrative and should not be construed as limiting the scope of the invention. Various modifications and changes may occur to those skilled in the art without departing from the spirit and scope of the invention described herein and as defined by the appended claims.

    权利要求:
    Claims (93)
    [0001]
    1. Constellation of low terrestrial orbital communications satellites characterized in that it comprises a) a plurality of satellites in a polar orbit around the Earth; b) wherein the satellites are arranged in a sufficient number of orbital planes to provide substantially coverage for each point on Earth for communications and substantially at all times, and c) where the number of satellites in each orbital plane is sufficient to provide communications in the range of the orbital plane; d) where each satellite has an antenna to receive and transmit to ground stations, and wherein the satellite antenna is controlled to prevent transmission below the boresight of a GEO aiming antenna at any point on Earth; e) wherein the satellite orbital plane comprises an orbital plane defining an orbit polar around the four quadrants of the Earth, where the satellite has a pointing control, and where the pointing control in the first quadrant follows a algorithm for targeting satellite broadcasts to maximize coverage and avoid transmission below boresight of a GEO aiming antenna; f) where the satellite targeting control directs satellite broadcast coverage in each quadrant of the orbit plane to mirror the satellite transmission coverage of the backwards beam projected in the anterior quadrant of the satellite orbit; g) where the transition between quadrants at the equator includes the satellite turning off its transmitter to Earth in order to avoid transmission below boresight an antenna that points to a GEO satellite; and h) in which the transmission between satellites and a ground station is carried out using spectrum also used by GEO communications satellites that communicate in the same region.
    [0002]
    2. Constellation according to claim 1, characterized in that the means of transporting datagrams between any satellite and a ground terrestrial network occurs by means of immediate retransmission of the datagram to a gateway station that is located at the view from the same satellite.
    [0003]
    3. Constellation according to claim 1, characterized in that the means of transporting datagrams between any satellite and a ground-based terrestrial network occurs by means of a cross-link to one or more other satellites in said constellation and then to the said other satellites to a communication port, wherein the communication port is not in view of the first satellite at any particular time.
    [0004]
    4. Constellation according to claim 3, characterized in that said satellites comprise switching means for switching the transport of datagrams between satellites, wherein the switching means associated with a satellite is configured to transfer datagram transmission to the switching means associated with another satellite.
    [0005]
    5. Constellation according to claim 1, characterized in that the associated ground station for transmitting datagrams between the ground station and a satellite employs an omnidirectional antenna.
    [0006]
    6. Constellation according to claim 1, characterized in that the associated ground station to transmit datagrams between the ground station and the satellite employs a directional antenna that is directional north or south in relation to the orbital plane of the satellite constellation.
    [0007]
    7. Constellation according to claim 5, characterized in that the antenna is directional both in elevation and in azimuth.
    [0008]
    8. Constellation according to claim 1, characterized in that the satellites are arranged in a sufficient number of orbital planes to provide coverage for every point on Earth.
    [0009]
    9. Constellation according to claim 1, characterized in that the number of satellites in each orbital plane is selected according to the maximum transmission and reception coverage for the altitude elevation angle and satellite horizon.
    [0010]
    10. Constellation according to claim 1, characterized in that said satellite pointing control comprises a control mechanism, and in which the control mechanism controls the beam from one or more satellite antennas to direct satellite broadcasts (1) according to a beam projection in the backward direction that is projected at a backward beam angle of angle X, which for an acute angle y between the horizon and the vector at a location of a point on the Earth where a GEO earth station points to a geostationary satellite, and a GEO guard band angle β around the vector between the GEO earth station and the GEO satellite it points to, which is at angle Y to the horizon, is determined by the expression:
    [0011]
    11. Constellation according to claim 10, characterized in that the satellite projections are controlled to maximize coverage, and that the satellite projections are controlled to prevent transmission below the boresight of a GEO aiming antenna .
    [0012]
    12. Constellation according to claim 1, characterized in that the satellite has a control mechanism that controls the satellite transmitter, and that the satellite antenna is controlled to prevent transmission below the boresight of a satellite antenna. pointing to GEO with said control mechanism at any point on Earth by the control mechanism, said control mechanism being configured to turn off the transmitter in locations where transmissions from the transmitter would coincide with the boresight of a ground station antenna of GEO pointing to a GEO satellite.
    [0013]
    13. Constellation according to claim 12, characterized in that each satellite is configured to turn off its transmitter that transmits to Earth in the transition between quadrants at the equator, in order to avoid transmission below the boresight of an antenna that points for a GEO satellite.
    [0014]
    14. Constellation according to claim 1, characterized in that the LEO satellites provide communications links, and in which a satellite of the LEO satellite constellation approaches a boresight of an antenna of a satellite earth station of GEO or a GEO satellite guardband that is within the orbital plane of the oncoming satellite is configured to transfer communications to another of the LEO satellites that is not within the boresight of an antenna of a GEO satellite.
    [0015]
    15. Constellation according to claim 1, characterized in that said LEO satellite antenna for receiving and transmitting to ground stations comprises a real-time adjustable beam antenna.
    [0016]
    16. Constellation according to claim 1, characterized in that the satellite transmits a beam that is projected from the antenna, said beam having a forward direction and a backward direction in relation to the movement of the satellite within the orbit.
    [0017]
    17. Constellation according to claim 1, characterized in that the satellite transmits a beam that is projected from the antenna, and wherein said beam has a forward pointing portion and a backward pointing portion.
    [0018]
    18. Constellation according to claim 16, characterized in that the satellite antenna comprises the directional antenna; wherein the satellite beam in the forward direction is projected at a forward beam angle of ^, and where the satellite beam in the backward direction is projected at a backward beam angle of X; wherein said directional satellite antenna is manipulated to reduce the forward beam angle of Φ as the LEO satellite moves to a limit of latitude.
    [0019]
    19. Constellation according to claim 18, characterized in that the satellite directional antenna is manipulated to decrease the forward beam angle of de as the LEO satellite moves as the satellite moves to a limiting latitude angle away from the equator.
    [0020]
    20. The constellation of claim 18, wherein the directional satellite antenna is manipulated to increase the backward pointing beam angle of X as the satellite moves away from the equator.
    [0021]
    21. Constellation according to claim 18, characterized in that the satellite directional antenna is manipulated to increase the backward pointing beam angle of X as the satellite moves in the opposite direction to a guard band of GEO ground station.
    [0022]
    22. Constellation according to claim 18, characterized in that the satellite directional antenna is manipulated to increase the backward pointing beam angle of X as the satellite moves in the opposite direction to a station's boresight terrestrial from GEO.
    [0023]
    23. The constellation of claim 17, wherein the satellite communication beam forward portion of a satellite beam has a forward beam angle which is adjusted as a function of the satellite's latitude.
    [0024]
    24. A low-earth orbiting satellite constellation communications system characterized by the fact that it comprises: a) a plurality of low-earth orbiting satellites in a polar orbit, the polar orbit covering four quadrants of the Earth; b) communications processing equipment provided on each satellite, said communications processing equipment comprising a processor and circuitry for receiving and transmitting signals between a ground station and one or more satellites of the satellite constellation; c) in that each satellite has at least one antenna to receive and transmit to ground stations; d) wherein said antenna is controllable to turn off its communication link to prevent transmission below the boresight of a GEO pointing antenna at any point on Earth ; and e) wherein each satellite has a beam control mechanism that includes computing components configured to process the satellite's location information and determine the beam angle to be provided by the satellite antenna, so that the beam angle provides coverage. which prevents transmission below the boresight of a GEO aiming antenna at any point on Earth.
    [0025]
    25. System according to claim 24, characterized in that each of said satellites of the satellite constellation has a control mechanism to control their respective antennas.
    [0026]
    26. System according to claim 25, characterized in that the control mechanism controls at least one antenna to direct the beam interfering with the boresight of a GEO satellite earth station antenna pointing to a GEO satellite GEO.
    [0027]
    27. System according to claim 26, characterized in that the control mechanism controls one or more antennas of a satellite to produce a beam in the forward direction projected at a forward beam angle and to produce a beam in the backward direction projected at a backward beam angle.
    [0028]
    28. System according to claim 27, characterized in that the satellite beam in the backward direction is projected at a backward beam angle that decreases as the satellite moves forward in its directional orbit.
    [0029]
    29. System according to claim 27, characterized in that the satellite beam in the forward direction is projected at a forward beam angle that increases as the satellite moves forward in its directional orbit.
    [0030]
    30. System according to claim 28, characterized in that the satellite beam in the forward direction is projected at a forward beam angle that increases as the satellite moves forward in its directional orbit.
    [0031]
    31. System according to claim 28, characterized in that the satellite beam in the backward direction is projected at a backward beam angle of X, which for an acute angle Y between the horizon and the vector in a location of a point on Earth where a GEO ground station points to a geostationary satellite, and a GEO guard band angle β around the vector between the GEO ground station and the GEO satellite to which the same point, which is at angle Y to the horizon, is determined by the expression:
    [0032]
    32. System according to claim 29, characterized in that the satellite beam in the forward direction is projected at a forward beam angle of ^ and wherein, for a given latitude position in the satellite's orbit, the projected forward beam angle ^ is determined by the expression:
    [0033]
    33. System according to claim 32, characterized in that the horizon elevation angle consists of the minimum angle between (1) the horizon and (2) the satellite in which the satellite and a ground station to which the satellite can communicate as viewed from the ground station location.
    [0034]
    34. System according to claim 30, characterized in that the satellite beam in the backward direction is projected at a backward beam angle of angle X, wherein, for a given latitude position in the satellite's orbit , the X projected backward beam angle is determined by the expression:
    [0035]
    35. System according to claim 27, characterized in that the beam produced in the forward direction is comprised of a plurality of sub-beams.
    [0036]
    36. System according to claim 27, characterized in that the beam produced in the backward direction is comprised of a plurality of sub-beams.
    [0037]
    37. System according to claim 27, characterized in that at least one of the beam produced in the forward direction and the beam produced in the backward direction is comprised of a plurality of sub-beams, and in which said sub-beams are controllable for controlling the projection of the communication beam from said satellite antenna.
    [0038]
    38. System according to claim 27, characterized in that the beam produced in the forward direction is comprised of a plurality of sub-beams, wherein the beam produced in the backward direction is comprised of a plurality of sub-beams, and in that said sub-beams are controllable to control the projection of the communication beam from said satellite antenna.
    [0039]
    39. System according to claim 37, characterized in that a sub-beam is controllable by positioning said antenna that supplies the sub-beam.
    [0040]
    40. System according to claim 37, characterized in that at least one of said forward beam and said backward beam is controllable by activating or deactivating a sub-beam comprising the respective forward beam or beam back.
    [0041]
    41. System according to claim 37, characterized in that said forward beam is controllable by activating or deactivating a subbeam comprising the forward beam, and wherein said backward beam is controllable by activating yourself or by disabling the subbeam that comprises the beam backwards.
    [0042]
    42. System according to claim 24, characterized in that the satellite antenna comprises a real-time adjustable beam antenna.
    [0043]
    43. System according to claim 42, characterized in that the real-time adjustable beam antenna comprises a phasic array antenna.
    [0044]
    44. System according to claim 42, characterized in that the antenna provides a beam envelope that is comprised of sub-beams configured for specific frequency reuse, polarization reuse, or accommodation of other orbital elements or ground station elements .
    [0045]
    45. System according to claim 43, characterized in that the antenna provides a beam envelope that is comprised of sub-beams configured for specific frequency reuse, polarization reuse, or accommodation of other orbital elements or ground station elements .
    [0046]
    46. System according to claim 24, characterized in that said satellite constellation is provided so that at least one satellite of the satellite constellation is in view at all times from any point P on Earth.
    [0047]
    47. System according to claim 26, characterized in that the satellite beam in the forward direction is projected at a forward beam angle ^; where the backward-direction satellite beam is projected at a backward-beam angle of X; wherein the at least one satellite antenna comprises the directional antenna that projects the beam forward, and wherein the at least one directional antenna that projects the beam forward is manipulated to reduce the forward beam angle Φ as the satellite of LEO moves to a limit of latitude, where at least one satellite antenna comprises the directional antenna that projects the beam backwards, where the at least one directional satellite antenna projects the beam backwards is manipulated to increase the angle backward beam X as the LEO satellite moves to a limit of latitude.
    [0048]
    48. System according to claim 47, characterized in that each directional antenna has an associated transmitter that provides a signal to the antenna, and in that each satellite is configured to turn off an associated transmitter in locations where the transmission of its transmitter would coincide with the boresight of an antenna pointing to a GEO satellite.
    [0049]
    49. System according to claim 24, characterized in that said at least one antenna for receiving and transmitting to ground stations comprises the directional antenna and in that there is at least one transmitter associated with the directional antenna that provides a signal to the antenna, and where each satellite is configured to turn off its associated transmitter at locations where its transmitter's transmission would coincide with the boresight of an antenna pointing to a GEO satellite.
    [0050]
    50. System according to claim 49, characterized in that the satellite constellation is in a plane of orbit by the four quadrants of the Earth that define four respective quadrants of the orbit plane, and in which the equator defines a transition between quadrants of the orbit plane.
    [0051]
    51. System according to claim 50, characterized in that each satellite is configured to turn off its transmitter that transmits to Earth in the transition between quadrants at the equator, in order to avoid transmission below the boresight of an antenna that points for a GEO satellite.
    [0052]
    52. System according to claim 51, characterized in that each second, third and fourth quadrant of the orbit plane is an operating mirror of the first quadrant, in which a satellite of the satellite constellation in an orbit mirrors the projections angle beam for each successive quadrant.
    [0053]
    53. System according to claim 24, characterized in that said satellites operate using spectrum also used by GEO communications satellites in the same region.
    [0054]
    54. System according to claim 52, characterized in that said satellites operate using spectrum also used by GEO communications satellites in the same region.
    [0055]
    55. System according to claim 47, characterized in that the forward beam angle Φ and the backward beam angle X are determined at the limit of latitude as a function of the limit of latitude o for a given angle of guard band β around the vector between the GEO ground station and a GEO satellite at an angle y, and where the satellite is in orbit at an altitude h which is at least an angle α above the local horizon.
    [0056]
    56. System according to claim 30, characterized in that each satellite includes a computer that has a hardware processor, and software that contain instructions to instruct the computer to manipulate the beam from the satellite in the forward and backwards, said instructions comprising instructing the computer to: determine the forward beam angle Φ by monitoring the satellite altitude and location coordinates for the satellite, where the forward beam angle Φ is the angle of beam relative to a vector defined by the center of the Earth and the satellite location that projects forward from the satellite in the direction of the satellite's orbit; determine the backward beam angle X by monitoring the satellite location and altitude coordinates for a satellite, where the backward beam angle X is the beam angle relative to a vector defined by the center of the Earth and the location of the satellite that projects to the rear of the satellite at d. opposite direction to that of the satellite orbit; identify locations of ground GEO stations that are in the line of sight of the satellite orbit; and control the forward beam angle Φ and backward beam angle X to maximize coverage and to prevent transmission below the boresight of a GEO ground station antenna.
    [0057]
    57. System according to claim 24, characterized in that the LEO satellites of the satellite constellation are distributed in orbital planes above the earth's surface; wherein a LEO satellite of the satellite constellation is distributed in orbit relative to an adjacent LEO satellite of the satellite constellation such that the LEO satellite and the satellite adjacent thereto are within line-of-sight distance of each other .
    [0058]
    58. System according to claim 24, characterized in that the satellites are spaced within their orbital plane at a line-of-sight distance, s, spacing adjacent satellites.
    [0059]
    59. System according to claim 57, characterized in that the maximum line-of-sight distance spacing between satellites of the satellite constellation is determined by the minimum angle between the horizon and a satellite on which that satellite can communicate with an earth station located at a point on Earth.
    [0060]
    60. System according to claim 59, characterized in that the maximum spacing distance between adjacent satellites is determined by an angle θ of a vector defined by the respective latitude positions of each respective adjacent satellite in a respective orbital plane, where the vertex of angle is the center of the Earth.
    [0061]
    61. System according to claim 60, characterized in that said angle θ is determined by the expression θ = 2 arcsen(S/2n_), where S is the spacing distance between adjacent satellites and is represented by the expression S = 2 rL sin(θ/2).
    [0062]
    62. The system of claim 57, characterized in that at least one first orbiting LEO satellite of the satellite constellation is far enough above the local horizon to be within the line of sight of a LEO ground station that receives broadcasts from the satellite constellation to be available for reliable communications; wherein during the period when the at least one orbiting first LEO satellite of the satellite constellation is within a guard band around the vector between the GEO earth station and a GEO satellite, at least one second satellite of LEO is within sight and far enough above the local horizon, and assumes any communications function with the ground station from the first LEO satellite within the guardband vector.
    [0063]
    63. System according to claim 60, characterized in that the at least one second LEO satellite that assumes the communications function assumes the communications functions from the at least one first satellite before the first satellite turns off its transmission function in guard band vector.
    [0064]
    64. System according to claim 63, characterized in that said at least one first satellite ceases transmission when it is within the guard band vector by turning off one or more sub-beams of its transmission beam.
    [0065]
    65. System according to claim 62, characterized in that the backward beam projection of the first satellite can communicate with the ground station after the forward beam has passed the boresight vector.
    [0066]
    66. System according to claim 26, characterized in that the constellation of plane orbit satellites has four quadrants, each corresponding to a quadrant of the Earth over which the orbit passes; in which a satellite controls the angle of beam forward of beam projected forward changing the projection angle as the satellite moves through its orbit in one quadrant; where the backward beam of the satellite of the satellite constellation in the next quadrant of its orbit is projected to mirror the forward beam projected by the satellite in the previous quadrant.
    [0067]
    67. The system of claim 66, characterized in that said backward projection mirroring provides a maximum region of coverage behind the satellite as the satellite moves through the quadrant.
    [0068]
    68. System according to claim 24, characterized in that the beam transmitted by a LEO satellite of the satellite constellation is in a direction opposite to the direction that a GEO satellite would transmit to the same ground station.
    [0069]
    69. System according to claim 24, characterized in that, when a transmitting satellite needs to cease transmitting to a ground station located at a point on Earth to avoid the boresight vector of a GEO ground station antenna , another satellite in the LEO satellite constellation takes over the broadcast from the broadcast satellite.
    [0070]
    70. System according to claim 24, characterized in that it includes a plurality of earth stations configured to receive transmissions from LEO satellites and send transmissions to LEO satellites, wherein at least some of the plurality of earth stations have omnidirectional antennas.
    [0071]
    71. System according to claim 24, characterized in that it includes a plurality of earth stations configured to receive transmissions from LEO satellites and send transmissions to LEO satellites, wherein at least some of the plurality of earth stations have directional antennas.
    [0072]
    72. System according to claim 71, characterized in that said directional antennas are directional to the north or south in relation to the orbital plane of the satellite constellation.
    [0073]
    73. System according to claim 72, characterized in that said antennas directed north or south are steerable in elevation and azimuth.
    [0074]
    74. System according to claim 24, characterized in that said satellites operate using spectrum also used by GEO communications satellites in the same region.
    [0075]
    75. System according to claim 24, characterized in that the satellites of the satellite constellation are arranged in a sufficient number of orbital planes to provide coverage substantially to every point on Earth for communications and substantially at all times.
    [0076]
    76. System according to claim 75, characterized in that the satellites of the satellite constellation are positioned in multiple orbital planes in regular angular longitudinal spacing.
    [0077]
    77. System according to claim 61, characterized in that the number of satellites provided in an orbital plane is determined by the distance between satellites in the orbit that are at an altitude h and at least one angle α above the horizon, and maintain a guardband angle of β around the vector between a GEO ground station and a GEO at an angle Y.
    [0078]
    78. System according to claim 24, characterized in that each satellite has a plurality of antennas.
    [0079]
    79. System according to claim 78, characterized in that each satellite plurality of antennas includes antennas for up/down links with ground stations and antennas for cross links with other satellites.
    [0080]
    80. System according to claim 79, characterized in that said uplink/downlinks comprise helical antennas, and wherein said crosslink antennas comprise lenses.
    [0081]
    81. System according to claim 24, characterized in that the number of satellites is the minimum number of satellites and that the distance between satellites is the maximum distance between satellites.
    [0082]
    82. System according to claim 24, characterized in that it further includes a plurality of ground stations having at least one directional antenna, wherein the greatest gain of the directional antenna is directed to substantially point south to a ground station located in the southeast hemisphere, and where the greatest gain of the directional antenna is directed to point substantially north to an earth station located in the northeast hemisphere.
    [0083]
    83. System according to claim 82, characterized in that the directional earth station antenna is directed to point its maximum antenna gain in the direction opposite to the direction of a GEO satellite and facing the direction of a GEO satellite. LEO
    [0084]
    84. Method for deploying communications through a satellite communication system with low orbiting (LEO) satellites providing reuse of geostationary terrestrial orbiting (GEO) communication satellite reuse frequencies, the method characterized by comprising: a) disposing a plurality of LEO satellites in a plurality of orbital planes around the Earth; wherein each satellite includes equipment to transmit RF transmissions that have frequencies suitable for reception by a ground station located on Earth; b) provide a control mechanism that controls satellite RF transmissions; c) transmit from a LEO satellite to transmission to a ground station; d) control the transmission satellite to turn off its communication link to prevent transmission below the boresight of an antenna pointing towards a GEO satellite; and e) in which transmission from a LEO satellite a transmission to a ground station is carried out using spectrum also employed by GEO communications satellites communicating in the same region.
    [0085]
    85. The method of claim 84, wherein controlling the transmitting satellite includes controlling with a control mechanism the operation of one or more satellite antennas to produce a transmit beam in the forward direction projected at an angle beam forward and to produce a transmit beam in the backward direction projected at a backward beam angle.
    [0086]
    86. The method of claim 85, characterized in that controlling the beam angle comprises projecting a transmit beam in the forward direction at a forward beam angle of ^ and wherein, for a given latitude position in the orbit of the satellite, the forward beam angle ^ at which the beam is projected is determined by the expression:
    [0087]
    87. Method according to claim 85, characterized in that controlling the beam angle comprises projecting the transmission beam in the backward direction at a backward beam angle of angle X where, for a given latitude position in the satellite orbit, the backward beam angle X at which the beam is projected is determined by the expression:
    [0088]
    88. Method according to claim 85, characterized in that controlling the beam angle comprises projecting a transmission beam in the forward direction at a forward beam angle of ^ and wherein, for a given latitude position in the orbit of the satellite, the forward beam angle ^ at which the beam is projected is determined by the expression:
    [0089]
    89. Low Earth Orbiting Satellite (LEO) characterized by the fact that it comprises: a) communications equipment, said communications equipment comprising equipment for transmitting RF transmissions that have frequencies suitable for reception by a terrestrial station located on Earth , and communications equipment to communicate with other satellites; b) a control mechanism that includes a processing and software component with instructions for controlling RF transmissions from the LEO satellite to a ground station; c) a transmitter for transmitting transmissions from RF; d) at least one antenna for projecting RF transmissions from the LEO satellite; e) wherein said control mechanism controls the satellite transmissions to turn off its communication link to prevent transmission below the boresight of a antenna that points to a GEO satellite; and f) where RF transmissions from the LEO satellite to a ground station are carried out using spectrum also employed by GEO communications satellites that communicate in the same region.
    [0090]
    90. Satellite according to claim 89, characterized in that the control mechanism controls the operation of one or more antennas of the satellite to produce a transmit beam in the forward direction projected at a forward and forward beam angle. produce a backward transmission beam projected at a backward beam angle.
    [0091]
    91. Satellite according to claim 90, characterized in that the control mechanism controls the beam angle to project a transmit beam in the forward direction at a forward beam angle of ^ and in which, for a given latitude position in the satellite's orbit, the forward beam angle Φ is determined by the expression:
    [0092]
    92. Satellite according to claim 90, characterized in that the control mechanism controls the beam angle to project a transmission beam in the backward direction at a backward beam angle of angle X, wherein for a given latitude position in the satellite's orbit, the backward beam angle X is determined by the expression:
    [0093]
    93. Satellite according to claim 90, characterized in that the control mechanism controls the beam angle to project a transmit beam in the forward direction at a forward beam angle of ^ and in which, for a given latitude position in the satellite's orbit, the forward beam angle Φ is determined by the expression: where rE represents the radius of the Earth, where α represents the horizon elevation angle, and where rL represents the radius of the satellite orbit; and wherein the control mechanism controls the beam angle to project a transmit beam in a backward direction at a backward beam angle of angle X, where, for a given latitude position in the satellite's orbit, the beam angle to behind X is determined by the expression: where rE represents the radius of the Earth, where rL represents the radius of the satellite orbit where y represents an acute angle between the horizon and the vector at a location of a point on Earth where a GEO ground station points to a geostationary satellite, and where β represents a GEO guard-band angle around the vector between the GEO ground station and the GEO satellite it points to, which is at angle Y to the horizon, and at that rL represents the radius of the satellite's orbit.
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    同族专利:
    公开号 | 公开日
    SG11201809489WA|2018-11-29|
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    BR112018072637A2|2019-02-26|
    JP2019520729A|2019-07-18|
    CA3022513A1|2017-11-09|
    AU2017260347A1|2018-12-13|
    RU2018140570A3|2020-06-17|
    KR20190002672A|2019-01-08|
    IL262694A|2021-04-29|
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    CN109417827A|2019-03-01|
    RU2018140570A|2020-06-03|
    IL262694D0|2018-12-31|
    EP3453223B1|2021-10-06|
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    EP3453223A4|2019-12-18|
    DK3453223T3|2022-01-10|
    US10348396B2|2019-07-09|
    RU2730169C2|2020-08-19|
    CN109417827B|2020-08-14|
    AU2017260347B2|2021-10-21|
    PT3453223T|2021-12-29|
    EP3453223A1|2019-03-13|
    WO2017192727A1|2017-11-09|
    MX2018013489A|2019-10-30|
    JP6896982B2|2021-06-30|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    IL91529D0|1988-10-28|1990-04-29|Motorola Inc|Satellite cellular telephone and data communication system|
    US5604920A|1993-04-21|1997-02-18|Motorola, Inc.|Satellite cellular telephone and data communication system|
    US5439190A|1991-04-22|1995-08-08|Trw Inc.|Medium-earth-altitude satellite-based cellular telecommunications|
    US8442519B2|2003-12-07|2013-05-14|Gogo Llc|Spectrum sharing between an aircraft-based air-to-ground communication system and existing geostationary satellite services|
    US5367304A|1992-07-06|1994-11-22|Motorola, Inc.|Communication system employing spectrum reuse on a spherical surface|
    US6236834B1|1993-12-15|2001-05-22|International Mobile Satellite Organization|Method and apparatus for limiting interference between satellite systems|
    US5566354A|1994-09-26|1996-10-15|Sehloemer; Jerry R.|System and method for channel assignment in a satellite telephone system|
    US5930679A|1994-10-03|1999-07-27|Motorola, Inc.|Satellite-based ring alert apparatus and method of use|
    US5552920A|1995-06-07|1996-09-03|Glynn; Thomas W.|Optically crosslinked communication system |
    US6019318A|1997-06-16|2000-02-01|Hugehs Electronics Corporation|Coordinatable system of inclined geosynchronous satellite orbits|
    US6175340B1|1998-05-04|2001-01-16|Motorola, Inc.|Hybrid geostationary and low earth orbit satellite ground station antenna|
    US20020150060A1|1998-09-01|2002-10-17|Marie-Jose Montpetit|Asymmetric formatting system and method for low-earth-orbit satellite data communication|
    US6678520B1|1999-01-07|2004-01-13|Hughes Electronics Corporation|Method and apparatus for providing wideband services using medium and low earth orbit satellites|
    US6195037B1|1999-06-01|2001-02-27|Motorola, Inc.|Method and apparatus for increased system capacity using antenna beamforming|
    US6556828B1|1999-08-31|2003-04-29|Loral Spacecom Corp.|Network architectures for LEO/GEO satellite-based communications systems|
    US7184761B1|2000-03-27|2007-02-27|The Directv Group, Inc.|Satellite communications system|
    US20020041328A1|2000-03-29|2002-04-11|Astrovision International, Inc.|Direct broadcast imaging satellite system apparatus and method for providing real-time, continuous monitoring of earth from geostationary earth orbit and related services|
    US7200360B1|2000-06-15|2007-04-03|The Directv Group, Inc.|Communication system as a secondary platform with frequency reuse|
    US7369847B1|2000-09-14|2008-05-06|The Directv Group, Inc.|Fixed cell communication system with reduced interference|
    US6701126B1|2000-11-13|2004-03-02|Space Resource International Ltd.|System and method for implementing a constellation of non-geostationary satellites that does not interfere with the geostationary satellite ring|
    US6714521B2|2000-12-29|2004-03-30|Space Resources International Ltd.|System and method for implementing a constellation of non-geostationary satellites that provides simplified satellite tracking|
    US6940452B2|2003-09-29|2005-09-06|Northrop Grumman Corporation|Reducing co-channel interference in satellite communications systems by antenna re-pointing|
    AU2004319490B8|2003-12-29|2011-06-23|Peersat Llc|Inter-satellite crosslink communications system, apparatus, method and computer program product|
    US7669803B2|2004-12-07|2010-03-02|Lockheed Martin Corporation|Optimized land mobile satellite system for north american coverage|
    US7624948B2|2004-12-07|2009-12-01|Lockheed Martin Corporation|Optimized land mobile satellite configuration and steering method|
    WO2006091605A2|2005-02-22|2006-08-31|Atc Technologies, Llc|Reusing frequencies of a fixed and/or mobile communications system|
    US8107875B2|2006-09-26|2012-01-31|Viasat, Inc.|Placement of gateways near service beams|
    CN101573922A|2006-10-06|2009-11-04|维尔塞特公司|Dynamic feedback for outbound link rate adjustment in multi-rate downstream|
    EP3726744A1|2007-10-09|2020-10-21|ViaSat Inc.|Non-interfering utilization of non-geostationary satellite frequency band for geostationary satellite communication|
    US20110169688A1|2007-10-18|2011-07-14|Gregory Thane Wyler|Apparatus and methods for satelite communication|
    US8193975B2|2008-11-12|2012-06-05|Atc Technologies|Iterative antenna beam forming systems/methods|
    US20110032143A1|2009-08-05|2011-02-10|Yulan Sun|Fixed User Terminal for Inclined Orbit Satellite Operation|
    WO2011038378A1|2009-09-28|2011-03-31|Atc Technologies, Llc|Systems and methods for adaptive interference cancellation beamforming|
    FR2954635B1|2009-12-17|2016-03-11|Astrium Sas|HYBRID SPATIAL SYSTEM BASED ON A CONSTELLATION OF SATELLITES IN LOW ORBIT ACTING AS SPACE REPEATERS TO IMPROVE THE EMISSION AND RECEPTION OF GEOSTATIONARY SIGNALS|
    US10511379B2|2010-05-02|2019-12-17|Viasat, Inc.|Flexible beamforming for satellite communications|
    FR2976749B1|2011-06-16|2013-06-28|Astrium Sas|DEVICE AND METHOD FOR OPTIMIZING THE FLOOR COVERAGE OF A HYBRID SPATIAL SYSTEM.|
    FR2976750B1|2011-06-16|2013-07-19|Astrium Sas|USEFUL SATELLITE REPEATER CHARGE, SYSTEM AND METHOD FOR SATELLITE TELECOMMUNICATIONS.|
    US10110463B2|2012-09-11|2018-10-23|Higher Ground Llc|Personal communications device for multiple communications systems|
    US20140113681A1|2012-10-18|2014-04-24|Robert S. Reis|Personal communications device with cross router|
    EP2735883A1|2012-11-27|2014-05-28|Eutelsat S.A.|Method of geo localization of a terminal sending a single signal to a satellite|
    RU2530223C1|2013-03-12|2014-10-10|Арий Борисович Ляско|Method for conversion in open space of two linearly polarised multiharmonic flows of electromagnetic waves, which are directed to one side, to directed de broglie wave flow|
    EP3175647B1|2014-08-03|2018-12-12|Hughes Network Systems, LLC|Centralized ground-based route determination and traffic engineering for software defined satellite communications networks|
    US9859927B2|2014-11-24|2018-01-02|Worldvu Satellites Limited|Communication-satellite system that causes reduced interference|
    EP3048745A1|2015-01-20|2016-07-27|Airbus Defence and Space Limited|Space network node receiving data from terrestrial and space nodes.|
    US9585150B2|2015-03-20|2017-02-28|Qualcomm Incorporated|EPFD coverage for NGSO satellites|
    US10084531B2|2015-08-31|2018-09-25|The Boeing Company|System and method for allocating resources within a communication network|
    US9942082B2|2015-09-23|2018-04-10|Hughes Network Systems, Llc|Modulation and coding for a high altitude platform|WO2018037404A1|2016-08-21|2018-03-01|Nsl Comm Ltd|Method for calibrating and commissioning communication satellites using leo satellites|
    WO2019078348A1|2017-10-20|2019-04-25|三菱電機株式会社|Communication device and communication method|
    US11063661B2|2018-06-06|2021-07-13|Kymeta Corporation|Beam splitting hand off systems architecture|
    US10903900B2|2018-07-26|2021-01-26|Gilat Satellite Networks Ltd.|Non-geosynchronous orbit satellite constellations|
    CN110034817B|2019-04-29|2020-06-19|北京邮电大学|Low-orbit satellite network routing method and device based on software defined network|
    CN110011725B|2019-05-07|2020-10-23|中国人民解放军32039部队|Relay satellite tracking method and device|
    US10637562B1|2019-05-15|2020-04-28|Lockheed Martin Corporation|Geosynchronous broadcast of data to low-earth orbit|
    CN110224741A|2019-06-06|2019-09-10|航天科工空间工程发展有限公司|NGSO satellite constellation and GSO satellite communication system frequency spectrum coexistence method|
    CN110212971B|2019-06-17|2020-06-02|航天科工空间工程发展有限公司|Method for acquiring frequency interference of low-orbit constellation system to geostationary orbit satellite system|
    CN110417453B|2019-07-12|2021-12-07|中国空间技术研究院|Beam constant bias sharable radio spectrum method and low-orbit communication satellite system|
    CN110838866B|2019-10-09|2022-03-04|中国空间技术研究院|Method for sharing same frequency of NGSO satellite system and GSO satellite system|
    CN110838867B|2019-10-23|2022-02-01|西安空间无线电技术研究所|Medium-low orbit satellite constellation and beam design method thereof|
    KR102134894B1|2020-01-10|2020-07-20|국방과학연구소|Scale-down modeling appratus and operating method thereof|
    US11012147B1|2020-01-16|2021-05-18|M2SL Corporation|Multi-mode communication adapter system with smartphone protector mechanism and method of operation thereof|
    RU2744941C1|2020-01-17|2021-03-17|Федеральное государственное автономное учреждение "Военный инновационный технополис "ЭРА"|Optical communication system|
    CN111585635B|2020-04-17|2021-09-10|中国人民解放军国防科技大学|Satellite internet system design method based on space-frequency hybrid multiple access mode|
    CN112468207B|2020-10-21|2021-11-05|北京大学|Multi-layer low-earth orbit satellite constellation deployment method and system|
    CN112803989B|2021-03-09|2021-06-29|北京航空航天大学|Method and device for uniformly covering geographical partition by inscribed polygon of low-earth-orbit satellite network|
    法律状态:
    2020-08-18| B07A| Application suspended after technical examination (opinion) [chapter 7.1 patent gazette]|
    2021-03-16| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-06-01| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 03/05/2017, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US201662331245P| true| 2016-05-03|2016-05-03|
    US62/331,245|2016-05-03|
    PCT/US2017/030847|WO2017192727A1|2016-05-03|2017-05-03|Low earth orbit satellite constellation system for communications with re-use of geostationary satellite spectrum|
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