KR20100088632A

KR20100088632A - Apparatus and methods for satellite communication

Info

Publication number: KR20100088632A
Application number: KR1020107010715A
Authority: KR
Inventors: 그레고리 티. 와일러
Original assignee: 오쓰리비 네트웍스 리미티드
Priority date: 2007-10-18
Filing date: 2008-09-05
Publication date: 2010-08-09
Also published as: AU2008314537A1; EP2210289A4; WO2009051907A1; EP2210289A1

Abstract

A constellation consisting of a plurality of satellites operating in substantially equator, non-stop orbits; A plurality of ground stations configured to communicate with a satellite, wherein at least one designated ground station of the plurality of ground stations comprises: a ground station characterized by a lack of wired connection to any universal communication network; And one or more gateway stations connected to the general purpose communications network and one or more satellites, each satellite comprising one or more antennas having adjustable beams, the antennas for continuously transmitting focused point beams toward designated ground stations. It is characterized by controllable.

Description

Apparatus And Methods For Satellite Communication

The present invention relates generally to communication systems, and more particularly to systems and methods for satellite-based communication.

Satellite communication systems provide various benefits to consumers of telecommunication services such as telephony, internet communications, television communications, and the like. Various communication systems are currently available, which are described below.

Satellites using geostationary (GEO) orbits, in such systems, provide the convenience of having one or more satellites that maintain a fixed position relative to the earth as the earth rotates. However, at an altitude of the GEO orbit (which is about 36,000 km), the communication latency is about 600 milliseconds (ms). This latency leads to very slow communication performance and is particularly inefficient for internet communication. For example, the main page of "www.cnn.com" ® actually takes up to 24 seconds to load this latency interval.

For these and other reasons, satellites using non-geostationary orbits (NGSOs) (between 2000 and 36000 km) and low earth orbits (LEO) (less than 2000 km), such as medium earth orbits (MEOs), may Has been used. Existing LEO and MEO satellite systems typically use inclined orbits to enable such systems to meet the high interest of customers located in the northern and southern hemispheres. In this orbit, the satellite constantly moves about the various ground stations that communicate with the satellite. Furthermore, subsequent satellites of this constellation generally travel along different orbital planes. Thus, many of these systems use omnidirectional antennas at ground-based user terminals to allow continuous communication with various satellites in the constellations traveling through their relative orbits. However, such omni-directional antennas have very low gains, thereby limiting the communication performance (communication bandwidth) that can be obtained using this approach. One way to compensate for the low gain level of the antenna at the user terminal is to significantly increase the power used for satellite antenna transmission. However, these increased satellite transmit power levels may exceed the power currently available with satellite power generation technology and are therefore impractical.

In addition, satellites moving in NGSO orbit may cause interference between one or more entities in the GEO satellite communication system. Thus, when the NGSO satellite is too close to the communication path between the GEO satellite and the ground station in communication with the GEO satellite, transmission activity by the NGSO satellite is generally blocked. Such blocking would result in significant inconvenience and cost to the operation of the NGSO satellite system.

Therefore, there is a need in the related art for a satellite communication system that can provide an effective communication service at low cost and avoid interference with the current satellite system.

According to one aspect, the present invention relates to a communication system comprising a constellation of satellites operating in orbit on a non-stop orbit around the earth substantially at an equator, wherein the one or more satellites are delimited by one or more ground stations. A first antenna capable of controlling to transmit one concentrated point beam; And a second antenna controllable to transmit a second concentrated point beam to one or more gateway ground stations. Preferably one or more satellites operate to establish a communication path between the ground station and the gateway station along the first and second point beams. Preferably, at least one of the first and second antennas is mechanically steerable, such as a phased array antenna. Preferably, by communicating with a ground station on earth having a minimum latitudinal angular separation from the GEO sub-satellite point, one or more satellites prevent interference with the GEO satellite in communication with the GEO sub-satellite point on earth. Operable to operate. Preferably, the minimum latitude angular separation is about 5 degrees.

Preferably, by using a satellite located within the constellation of the satellite having a sub-satellite point having a minimum latitude angle separation from the GEO sub-satellite point, the system is in communication with the GEO satellite communicating with the GEO sub-satellite point on Earth. It is operable to prevent interference. Preferably, the minimum latitude angular separation is about 5 degrees. Preferably, the plurality of satellites in the constellation are within the communication range of the ground station at a given time, thereby providing several satellite communication options for the ground station. Preferably, in the event of an error of the first satellite, the ground station operates to hand off communication from the first satellite to the second satellite. Preferably, the constellation comprises at least 16 satellites, where at least three satellites are within range of the ground station at any given time. Preferably, the one or more ground stations lack a wired connection to any universal communication network, where the one or more gateway stations have a wired connection to the universal communication network.

Preferably, the general purpose communication network comprises the Internet. Preferably, the one or more satellites are operable to deliver the data packet signal to a destination in the communication system based on the frequency of transmission of the data packet signal. Preferably, the satellite constellation operates in orbit with an altitude between about 2,000 km and about 25,000 km. Preferably, the satellite constellation operates in orbit having an altitude between about 8,000 km and about 20,000 km.

According to another aspect, the present invention provides a method for moving a satellite constellation along a substantially equatorial, non-stop orbit; Controlling a first antenna mounted to one or more satellites to direct the first concentrated point beam to one or more ground stations; Controlling a second antenna on the one or more satellites to direct the second focused point beam to one or more gate stations. Preferably, the method further comprises establishing a communication path between the ground station and the gateway station along the first and second point beams. Preferably, controlling the first antenna comprises one or more of the following steps: a) mechanically adjusting the first antenna to direct the first concentrated point beam to one or more ground stations; And b) electrically adjusting the first concentrated point beam.

Advantageously, controlling the second antenna comprises one or more of the following steps: a) mechanically adjusting the second antenna to direct the second concentrated point beam to one or more ground stations; And b) electrically adjusting the second concentrated point beam. Preferably, at least one of the first antenna and the second antenna is a phased array antenna. Preferably, the method comprises one or more satellites that communicate only with ground stations on Earth having a minimum latitude angle separation from the GEO sub-satellite points, thereby providing for communication between the GEO satellites and their GEO sub-satellite points on the ground. Preventing the interference further.

Preferably, the minimum latitude angle separation is about 5 degrees. Preferably the method uses a satellite in the constellation of the satellite and a GEO satellite by using a satellite in the satellite constellation for communication with a ground station having a sub-satellite point having a minimum longitude angular separation from the GEO sub-satellite point. Preventing interference with the communication therebetween. Preferably, the minimum hardness angular separation is about 5 degrees.

According to another aspect, the present invention provides a system comprising: a constellation of a satellite operating in substantially equator, non-stop orbit; A plurality of ground stations configured to communicate with this constellation, wherein one or more designated ground stations of the ground station are characterized by no wireless connection to any universal communication network; And one or more gateway stations coupled to the universal communication network and one or more satellites, wherein each satellite comprises one or more antennas having adjustable beams that are controllable to continuously send a first concentrated point beam toward a designated ground station. . Preferably, at least one antenna comprises a mechanically adjustable antenna. Preferably at least one antenna is a phased array antenna. Preferably, each satellite is operable to communicate in real time with a designated ground station, with one or more gateway stations activating connectivity between the designated ground station and the universal communication network.

Preferably, the general purpose communication network comprises the Internet. Preferably, the designated ground station is configured to transmit a communication connection possibility from the first satellite of the constellation to a subsequent satellite of the satellite entering the communication range of the designated ground station, thereby providing substantial continuous communication connection possibility of the ground station designated as the universal communication network. do. Preferably, the orbit of the satellite constellation has an altitude between about 2,000 km and about 25,000 km. Preferably the orbit of the satellite constellation has an altitude between about 6,000 km and about 20,000 km. Preferably the orbit of the satellite constellation has an altitude between about 7,000 km and about 12,000 km.

If the preferred embodiment of the present invention is described in conjunction with the accompanying drawings in this specification, other aspects, features, advantages and the like will be clearly understood by those skilled in the art.

For the purpose of illustrating various aspects of the invention, preferred forms are shown in the drawings. It will be understood, however, that the intention is not to limit the invention to the precise arrangements and dimensions shown.
1 is a block diagram illustrating a communication system including a satellite system in accordance with one or more embodiments of the present invention.
2 is a block diagram illustrating a connection between the satellite system of FIG. 1 using a plurality of individual ground stations and individual groups of local subscribers, in accordance with one or more embodiments of the present invention.
3 is a block diagram illustrating a portion of a communication system, in accordance with one or more embodiments of the present invention.
3A is a block diagram illustrating a portion of a computer system that may be used to communicate with one or more ground stations of the system of FIG. 3.
4 is a perspective view of the constellation of a satellite located in the equator orbit with respect to the earth, in accordance with an embodiment of the invention.
5 is a plan view illustrating the constellations of satellites in orbit around the earth in accordance with one or more embodiments of the present invention.
6 is a plan view illustrating the constellations of satellites in orbit around the earth, illustrating self-healing performance in accordance with one or more embodiments of the present invention.
FIG. 7 is a schematic diagram illustrating a north-south section of the earth in which satellites and GEO satellites that form part of a non-GEO satellite system orbit around and in accordance with an embodiment of the present invention.
8 is a schematic diagram showing the equator plane of the earth orbiting around and a GEO satellite forming part of a non-GEO satellite system in accordance with an embodiment of the present invention.
9 is a schematic diagram showing an equator plane of the earth in which two satellites and a GEO satellite forming part of a non-GEO satellite system orbit around in accordance with the present invention.
FIG. 10 illustrates a range of longitudes along the perimeter of the earth as seen from satellites orbiting the earth in accordance with one or more embodiments of the present invention.
FIG. 11 illustrates a Mercator project for a portion of the earth representing the selection of satellites orbiting the earth in accordance with one or more embodiments of the present invention.
12 is a schematic top view of a satellite forming a portion of a constellation that moves along an equator orbit above North America, according to one embodiment of the invention.
FIG. 13 is a schematic top view of two satellites forming part of a constellation that moves along an equator orbit above North America, according to one embodiment of the invention.
FIG. 14 is a schematic plan view showing the two satellites of FIG. 13 traveling along their orbit according to one embodiment of the present invention.
15 is a functional block diagram illustrating hardware on a satellite in accordance with one or more embodiments of the present invention.
15A is a schematic diagram illustrating a device on a satellite in accordance with one or more embodiments of the present invention.
16 is a block diagram illustrating a plurality of communication antenna dishes on a satellite in accordance with one or more embodiments of the present invention.
17 is a schematic diagram illustrating a satellite having two mechanically adjustable antennas in accordance with one or more embodiments of the present invention.
18 is a schematic diagram illustrating a satellite having two electronically adjustable antennas in accordance with one or more embodiments of the present invention.
19 is a block diagram illustrating a computer system suitable for use with one or more embodiments of the present invention.

In the following description, for purposes of explanation, specific numbers, materials, and configurations are set forth to provide a thorough understanding of the present invention. However, it is apparent to those skilled in the art that the present invention may be implemented without these specific details. In some cases, well known features may be omitted or simplified in order not to obscure the present invention. Further, reference to a specification for a phrase such as “one embodiment” or “one embodiment” means that a specific feature, structure, or characteristic described in connection with the embodiment is included in one or more embodiments of the present invention. do. The phrases such as "in one embodiment" or "in one embodiment" in various cases in this specification are not necessarily all referring to the same embodiment.

Those skilled in the art will appreciate that antennas (which may include beamformers or equipment for communicating over optical links communicating with other satellites or ground stations) may be similar in both transmit and receive modes. It is a reciprocal transducer showing its properties. For example, the antenna patterns for the transmit and receive modes are generally the same and can exhibit nearly the same gain. For convenience of explanation, it can be described in terms of transmitting or receiving a signal, on the understanding that the appropriate description can be applied in addition to two possible operations. Thus, it should be understood that antennas according to other embodiments described herein may be related to any of the transmit and receive operating modes. It will be apparent to those skilled in the art that the received and / or transmitted frequency may vary from high to low depending on the intended application of the system.

One or more embodiments of the present invention are directed to a satellite in a constellation that travels in substantial equator LEO or MEO orbital (which is a ground station not connected to any wired network and a gateway station that provides a primary link to entities in a wired, universal communications network). To solve the various limitations of existing systems. The contemplated communications will be used for internet services, mobile phone services, local fixed line telephone services, and / or satellite television, and the like.

In one embodiment, the density and distribution of the satellites in the constellation is preferably set such that the satellite constellations effectively perform the role of a public equatorial communication trunk line providing continuous band availability for all regions within the service range. Effectively, many of the areas most effectively serviced by embodiments of the present invention are located in various areas of the developing (tropical, equatorial) world that do not currently have wired connectivity to fiber optics or other wired or universal wired communications systems. do. Thus, for this currently unwired area, various embodiments of the present invention provide the only available solution to address the current absence of high speed communication. Still for less isolated regions, with substantially saturated wired connectivity, embodiments of the present invention provide a useful second source of high speed data connectivity.

Embodiments of the present invention provide much reduced communication latency when compared to GEO satellite systems. For ground stations located at the equator, the distance to the GEO satellite is 36,000 km, thus 3.6x10 ⁷ m (meters). In one embodiment, the distance from the ground station on the equator to the satellite within the equator mid-earth orbit (at an altitude of about 8,000 km) is clearly 8000 km (8 x 10 ⁶ m). Thus, for one round trip round (one move from earth to ante, and one move from satellite to earth), (3.6 x 10 ⁷ m / 3.0 x 10 ⁸ m / s) x 2 = .240 seconds Or 240 milliseconds (msec). Satellite round trip time (RTT) from a hub-based system requires two hops (up and down from the far terminal to the hub and back up and down from the hub to the far terminal), thus taking 480 msec transmission time. In the MEO satellite in the 8000 km orbit, one hop latency for the earth terminal is located on the equator (hop latency) the latency ^{(8 x 10 8/3 x} 10 8) x 2 = .053 seconds or 53 milliseconds (msec )to be. The total round trip time (travel from earth to satellite and back) is therefore 106 msec. Thus, the latency reduction for MEO satellites versus GEO satellites is significant.

For ground stations located at different latitudes from the equator, the same relationship is maintained. For example, the distance from the ground station at about 40 degrees N latitude to the GEO satellite is about 38,600 km, and the distance from this same ground station to the satellite in the equatorial MEO orbit is about 10,500 km. Applying the above equation, the RTT latency from the ground station at 40 degrees N latitude to the GEO satellite is 140 msec. Other factors may contribute to communication latency, such as processing time in a computer (at the ground station or at a satellite) or in a router. However, the main factor is the distance to / from the satellite. As above, it can be seen that the orbital altitude of various embodiments of the present invention can operate to substantially reduce communication latency.

Furthermore, at least the substantial equator orbits, contemplated by various embodiments of this specification, serve to simplify the process of orienting individual satellite antenna dishes towards each other in a section in which satellites and ground stations are in communication with each other. Moreover, a suitable choice of the number of constellations (one or more constellations may be used) with a center of gravity away from subsequent satellites in the constellation may prevent the trunk communication path between the GEO satellite and the ground station communicating with the GEO satellite. Can be.

1 is a block diagram of a communication system 10 including a satellite system 150 in accordance with one or more embodiments of the present invention. The communication system 10 may include a plurality of ground stations 100, which may be connected to a local subscriber 120, a satellite system 150, a single subscriber 500, a communication gateway (gateway station 700), And a communication network 400. Part of the system 10 shown above is further described below.

Communications network 400 may be a land-based network that may include the Internet. However, communication network 108 may be any communication network or system, which may utilize a satellite communication system to enable communication between network 400 and / or one or more ground stations 106 using each other. It can represent a combination of networks. Such systems may be used in place of or in addition to the Internet, telephone systems (terrestrial communications lines and / or wireless), radio communications (one-way broadcasts and / or two-way radios), television broadcasts, international warning system broadcasts (eg, weather emergency) Situations or other events), and / or other communication systems.

Gateway station 700 may serve as a communication relay between one or more satellites and one or more land-based communication networks (which may be wired or wireless). Here, the gateway 700 may function as an interface between the communication network 400 and the satellite system 150. Gateway station 700 may include one or more gateway stations or gateway terminals for data transmission and reception for retransmission to satellite system 150 and / or communication network 108. Gateway station 700 provides data format conversion and / or any necessary data communication routing necessary to facilitate communication between communication network 150 and satellite system 700. For example, by selecting one or more satellites from among a plurality of satellites for aquatic data communication, and / or by selecting one or more transponders distributed over a plurality of satellites or on one satellite to perform data communication. The station 700 may include a controller and / or other control means for controlling the location of the data communication path. In some cases, gateway station 700 may be considered to be a special-purpose ground station. In other cases, however, one or more gateway stations 700 may act as a relay transceiver station, between a) a satellite and a ground station, b) between two satellites, and / or c) between two ground stations. Can be.

In this specification, the terms "satellite system 150" and "satellite 150" are used interchangeably and generally between gateway station 700 and ground station 100, and / or sole subscribers 500. Refers to the entire satellite used as a communication relay between. Satellite system 150 may include one or more satellite constellations, and each constellation may include one or more satellites. Thus, satellite system 150 may include any number of satellites 200, from one to any desired number. Each satellite 200 of satellite system 150 may receive data from gateway 700, which data may be directly or via another satellite, one or more specific ground stations 100 within satellite system 150, any It may be retransmitted to another satellite 200, any independent subscriber 500. In contrast, satellite system 150 may receive data from one or more ground stations 106 and / or one or more single subscribers 500 and may retransmit the received data to one or more gateway stations 700.

The ground station 100 may be installed in a substantially permanently fixed location, as shown in FIG. 2, and may function as a communication hub for an individual group of networks consisting of local subscribers 120. In other embodiments, ground station 100 may be mobile. For example, ground station 100 may be implemented in a trunk, trailer, or other vehicle capable of carrying and powering an antenna system capable of communicating with one or more satellites. Alternatively, the mobile ground station may be a semi-permanent platform, which may nevertheless be mobile with suitable equipment if necessary. Mobile ground station 100 may be useful for providing information sources and communications, for example in schools, general hospitals, etc., where such facilities are difficult to afford permanent ground stations at their respective locations.

Each ground station 100 may be connected to one or more local subscribers 120, which may also be referred to as the customer side. Each subscriber may include one or more user terminals. Subscriber attributes and communication bandwidth requirements can vary widely. For example, each subscriber may include one or more telephone circuits, one or more Internet service providers, one or more Internet cafes, one or more individual telecommunications customers, and / or other forms of telecommunications providers, such as cable television providers, or a combination thereof. have.

The single subscriber 500 may be a subscriber that directly communicates with the satellite 200 of the satellite system 150 without using the ground station 100 as a relay. This approach would be appropriate if only the subscriber 500 was substantially isolated from other subscribers (eg, a plurality of subscribers 120), and the installation of a local network connected to the ground station 100 would not be cost effective. Here, the term user station may refer to either a ground station or a single subscriber (customer) of the district.

1 shows a configuration that can be used by satellites operating in any desired orbit of the Earth's state, which is a Geo-Stationary Orbit (GEO), Medium Earth Orbit (MEO), Highly Elliptical Orbit (HEO), or LEO (Low). Earth Orbit). GEO is located at an altitude of about 36,000 kilometers. An elliptical orbit refers to an orbit where the satellite altitude above the station surface changes as a function of each position of the satellite moving along its orbit. HEO refers to an elliptical orbit where the satellite's distance from Earth changes substantially as a function of time, or the progression of a satellite moving along its orbit. Further, system 10 may activate communication between different ground stations using single satellite 200 of satellite system 150 as a relay between ground stations. Alternatively, two or more satellites 200 of satellite system 150 may communicate with individual ground stations 100 that are in separate communication ranges of the two satellites. In this case, the gateway station 700 may communicate with two satellites to activate communication between two satellites and thus between two ground stations 106.

Alternatively, two dominances can function as a successive relay between two ground stations, and a single satellite can be used simultaneously with both ground stations and line-of-sight (transmit / receive). Does not have a straight line connection between the antennas. Thus, for example, referring to FIG. 2, the next link (connection) sequence from the first ground station to the second ground station can be implemented. In one embodiment, the link is from the first ground station 100-1 to the satellite 200 of the satellite system 150, to the second ground station 100-2, and to the final destination located at the local subscriber 120-2. Can lead to. In another embodiment, it may lead from the first ground station, to the first satellite, then to the second satellite, then to the second ground station, and then to the end point on the customer's side. In other embodiments, any number of satellites may be used as a relay between ground stations in communication with each other.

3 is a block diagram illustrating a portion of a communication system 10 in accordance with one or more embodiments of the present invention. A portion of the communication system 10 shown in FIG. 3 may include a satellite 200 and ground stations 100-1 and 100-2 on the earth 600. Since both the ground station 100-1 and the ground station 100-2 are connected to an equivalent set composed of a plurality of devices, only the devices connected to the ground station 100-1 will be described below for the sake of simplicity. Ground station 100-1 may include an antenna dish 102-1, a modem 104-1, and a computer system 110, which is shown in more detail in FIG. 3A. Further, ground station 100-1 may communicate with local subscribers 120-1-a, 120-1-b, and 120-1-c. The ground station 100-2 may include and communicate with the paralleled set of devices described above for the ground station 106-a as shown in FIG. 3. Antenna dish 102-1 may be any suitable telecommunicaitons dish (also known as satellite dish). O Antenna 102-1 may be configured to track satellite 200 as satellite 200 progresses along the orbit above ground station 100-1. Although only one antenna dish 102-1 is shown, any number of dish may be used at ground station 100-1, or other ground station within communication system 10. In one embodiment, two antenna dishes 102 are used at each ground station 100, operating in a round robin fashion, such that the first satellite 200 is out of range of the ground station 100 and the second satellite is As the ground station 106 gradually enters the range, it is possible for the ground station 100 to pass the communication with the satellite system (satellite constellation, 150) from one antenna dish 102 to the other in a round robin fashion. In another embodiment, there may be two satellites 200 that perform a continuous connection function along the data communication link between ground station 100-1 and ground station 100-2, where the signal path is two The data communication means passing through the satellite 200 and used between the two satellites may include optical transmission and / or radio frequency transmission.

FIG. 3A is a block diagram illustrating a portion of a computer system 110 that may be used in, or in communication with, a ground station 100-1 shown in FIG. Computer system 110 may include all the features necessary to control all parts of ground station 100-1, such as the computer components shown in FIG. However, for simplicity, only a subset of the portions of computer system 110 are shown in FIG. 3A. Computer system 110 may include a CPU 112 and a memory 114. The data table 116 may be stored in the memory 114 and may store the data related destination IP address of the digital data packet at a separate transmission frequency. For illustration purposes, FIG. 3A is a simplified version of data table 116. Data table 116 includes simplified IP addresses 1001 and 1002, which correspond to customer side 120-1-a and gateway station 700, respectively. In practical implementations, the IP address may be represented in any format suitable for a suitable application. Furthermore, any number of IP addresses and associated transmission frequencies and / or transmission frequency ranges may be stored in data table 116. Although the description herein describes enumerating destination IP addresses in table 116, in other embodiments, the address data stored in table 216 may be destination IP addresses, source IP addresses, data communication paths for data packets. And one or more IP address relay points, source MAC addresses and / or destination MAC addresses.

In one embodiment, computer system 110 of ground station 100-1 (and / or other equally configured ground stations in communication system 10) reads the destination IP address of each of digital data packets 120. The table 116 of the memory 214 is accessed, and a transmission frequency corresponding to the IP address read from the digital data packet 120 is retrieved. Thereafter, the ground station 106-a converts the digital data packet 120 into an analog data packet signal 130, and transmits the data packet signal 130 using the transmission frequency retrieved from the data table 216. Here, the term "packet" or "data packet" may refer to either the digital data packet 120 or the analog data packet signal 130. In this specification, analog data packet signal 130 is preferably an analog waveform or signal that includes digital data packet information of data packet 120 and is used to transmit digital packet information over an analog communication channel.

Data table 116 represents an example allowed frequency range that can be used for individual IP addresses. The ground station 100-1 can transmit each packet signal 130 using the transmission frequency anywhere within the transmission frequency range retrieved from the data table 116 for the particular IP address. In some embodiments, the transmission frequency range of table 216 may be sub-divided into smaller segments such that each segment of each range corresponds to a particular point of origin of each digital data packet 120.

Instead of a single frequency, a combination of specified IP addresses and frequency ranges may be useful for setting the frequency division threshold at the satellite 200 to activate the routing data packet signal 130 based on the transmission frequency of the signal 130. . This approach requires demodulating the signal 130 (in the satellite 200) and using expensive equipment on the satellite 200 to route the signal 130 based on the digital routing data contained in the signal. Can be effectively prevented.

Routing mechanisms, such as frequency dividers, may be used within satellite 200 to route analog packet signals 130 through satellite 200. Each packet, such as the one shown in table 116, transmits a frequency range corresponding to the respective IP address, before matching the data in table 116 and being transmitted from ground station 100-1 to satellite 200. It may be used to set thresholds in the frequency divider to implement routing decisions in satellite 200 that match the manner in which the transmission frequency is selected for signal 130. Thus, for example, in accordance with this embodiment, the packet signal 130 received at satellite 200 (see FIG. 2A) having a transmission frequency of 19.05 GHz is routed by satellite 200 to provide IP address 1002. In this case, the IP address corresponds to the gateway station 700.

In another example, the satellite 200 may serve as a relay for communication between the ground station 100-1 and the ground station 100-2 of FIG. 3. Thus, for example, the digital data packet 120 may be transmitted from the customer side 120-1 to the customer 120-2 via the ground station 100-2. Suitable equipment (eg, but not limited to modem 104-1 and / or computer system 110) of ground station 100-1 may then read the destination IP address of digital data packet 120 and The transmission frequency is selected based on the destination IP address of the data packet 120. Thereafter, the digital data packet 120 is modulated by the modem 104-1 to be analog data which is an analog version of the digital data packet 120. Packet signal 130. The analog data packet signal 130 may then be transmitted from the ground station 100-1 to the satellite 200 using the selected transmission frequency.

The satellite 200 preferably receives the data packet signal 130 and preferably determines the transmission frequency of the received signal (data table setting such correspondence is not shown). The satellite 200 then sends the data packet signal 130 to an output transponder (satellite antenna dish) on the selected satellite 200 based on the transmission frequency of the received data packet signal 130. It is desirable to transmit. The satellite 200 then preferably retransmits the data packet signal 130 from the transponder along the intended path, in which case the intended path leads to the ground station 100-2. In this example, it is assumed that the destination IP address points to the customer side 120-2-a as its final destination. Thus, when the data packet signal 130 is received at the ground station 100-2, it is desirable for the modem 104-2 to demodulate the signal back into the digital data packet 120 and identify the destination IP address. The ground station 100-2 then preferably transmits the digital data packet 120 to the customer side 120-2-a.

In the above example, satellite 200 functions as a relay between ground station 100-1 and ground station 100-2, each of which may be connected to several local subscribers. However, satellite 200 may communicate with two or more land-based communication stations of any suitable type. For example, in another embodiment, the satellite 200 may be a relay between a ground station and a gateway station, or between two gateway stations. Furthermore, each satellite 200 may communicate with one or more satellites and / or one or more ground stations.

4 is a perspective view illustrating the constellation 150 of the satellite 200 in the equator orbit 650 around the earth 600 in accordance with one embodiment of the present invention.

4 provides a perspective view of the earth 600 having an north pole 610, an south pole 620, an equator 630 (also denoted as “EQ”), a north latitude 30 degree line 710, and a south latitude 30 degree line 720. . This embodiment of the satellite constellation 150 includes sixteen satellites 200 moving along the orbit 650 (from left to right in FIG. 4), with the orbit preferably located near the equator. Since only about half of the earth 600 can be seen in FIG. 6, only eight satellites are shown in FIG. 6, although additional satellite portions can be seen. Here, the point on the earth 600 located vertically below the designated satellite is the sub-satellite point for that satellite.

Although one constellation of sixteen satellites is shown in FIG. 4, many other embodiments may be implemented. Specifically, any number of constellations can be used from one to infinity, where each constellation has any desired number of satellites. Although the embodiment of FIG. 4 includes sixteen satellites, in another embodiment, as few as five satellites may be used and may provide complete coverage for all service areas on the earth 600. In other embodiments, any number from five to any desired number of satellites may be included in satellite system 150.

4 shows a trajectory 650 near the equator. However, the present invention is not limited to these examples. Orbits with varying degrees of inclination may be used. Specifically, in one embodiment, the satellite 200 may move in an inclined orbit that varies from equator to latitude 0 to 10 degrees. In another example, a more inclined orbit may be used, in which case the satellite 200 moves farther than 10 degrees latitude from the equator.

In one or more embodiments, the satellite 200 moving substantially in the equator orbit 650 may provide communication coverage for an area on the earth 600 from 40 degrees north to 40 degrees south.

In one embodiment, each satellite 200 may include twelve customer antenna dishes and two gateway antenna dishes, each toward the surface of the earth 600 or to a communication destination on another satellite 600. Can point the adjustable point beam. In another example, note that satellite 200 may have fewer or more gateway antenna dishes and less than 12 customer antenna dishes.

In this manner, while satellite 200 moves along a designated segment of orbit 650 around earth 600, each satellite 200 is one or more user stations on earth 600 and one on earth 600. It is desirable to be able to continuously communicate with the gate station 700. In this way, the satellite 200 serves as a link between the ground stations 100 (FIGS. 1-3), and the ground stations have a gateway station having a wired connection to the universal communication network 400 (FIG. 1) and the network 400 (FIG. 700 may not have a wired connection. In some embodiments, the communication chain between ground station 100 and general purpose network 400 may include two or more satellites 200 in continuity instead of just one satellite 200. In this case, one or more satellite-to-satellite communication links may be used.

Adjusting the antenna dishes on one or more satellites, ground stations and gateway stations can be implemented by mechanical means, electronically (mechanisms such as phased array antennas), and / or combinations thereof. In embodiments utilizing substantial equator orbits for the satellite 200, the steering mechanism can be made more economical by simplifying and emphasizing the need for only one steering axis. More specifically, satellite 200 to satellite 200 maintains a line-of-site communication link with selected ground station 100 on earth 600 when satellite 200 moves along equatorial orbit 650. It may be sufficient to adjust the pitch angle of the adjustable light beam on. In the case where the satellite 200 travels along an inclined orbit, adjusting the orientation of the light beams to the satellites may result in two beams of adjustable beams to maintain line-of-site communication with the designated ground station 100. Adjusting the azimuth axis.

In one embodiment, a mechanically adjustable antenna dish may be used to continuously orient the communication beam between the satellite 200 and the corresponding ground station 100. In one embodiment, one-dimensional mechanically adjustable beams may be used to control the antenna dish orientation on the satellite 200 to maintain communication with the ground station 100. In this way, the communication between the designated ground station 100 and the designated satellite 200 can keep machine complexity to a minimum and maintain a minimum cost. Furthermore, a mechanically adjustable point beam can orient the beam with a high degree of accuracy and thus effectively concentrate radio frequency (RF) energy within a small, correctly positioned footprint at the surface of the earth 600.

Similarly, ground station 100 and / or gateway station 700 may use mechanical coordination and / or electronic (eg, phased array) coordination to keep track of satellites and thereby maintain communication connectivity between them. have. For ground station 100 located at the equator, there may be an option to use only one dimension in the adjustment. However, for ground stations 100 and / or gateway stations 700 located outside the equator, one or more dimensions may be implemented in the adjustment to ensure that there is sufficient adjustment capability to track the satellite 200.

Furthermore, in a system 10 where the satellite 200 is expected to move substantially in the equator orbit 650, the communications antenna dish orientation control at the ground station 100 and / or the single subscriber 500 is controlled by the satellite 200. A mechanically adjustable antenna dish may be used for many of the same reasons discussed above for the antenna dish on the top. Specifically, RF communication energy can be concentrated in a small, precisely placed footprint to obtain a high level of communication bandwidth per unit of energy consumption.

However, in alternative embodiments, electronic steering using a phased array antenna or other means may be used instead of the mechanical steering mechanism as discussed above. Such electronic coordination may be used for satellite 200, ground station 100 and / or single subscriber 500.

The satellite system 150 (which includes one constellation of 16 satellites in the embodiment shown in FIG. 6) may be implemented in a modular fashion with an additional satellite 200 and / or an additional constellation of satellites. The number of satellites 200 in the satellite system 150, the location of the added satellites in the satellite system 150, the communication facilities mounted on each satellite 200, and the communication between the designated satellite 200 and the designated ground station 100 It enables self-reasoning of failed communication links, coordination of scheduling, prevention of GEO satellites and edges, coordination of communication bandwidth, and / or power conservation. The foregoing is described in more detail below.

5 is a plan view illustrating the constellation of satellite 200 in orbit around earth 600 in accordance with one or more embodiments of the present invention. 5 shows a plan view from above the North Pole 610 of the Earth 600. A constellation 1500 consisting of 16 satellites 200 is shown in the equator orbit 650 around the earth, which travels from west to east as expected by LEO or MEO orbits. As previously mentioned, the satellite system 150 (which includes one constellation in this embodiment) may include fewer than six or more satellites 200.

FIG. 6 is a plan view illustrating the constellation 150 of satellite 200 in orbit around the earth 600 showing the self-healing capabilities of one or more embodiments of the present invention. In FIG. 6, S1, S2, S3, S4 correspond to individual customer ground stations 100. Unless otherwise noted, each satellite 200 is assumed to be in communication with one or more gateway stations (not shown) in addition to one of the ground stations S1, S2, S3 or S4.

In this embodiment, the satellite 200-4 normally communicates with the ground station S1 and a suitable gateway station 700 (not shown) at the stage of orbit of the satellite shown in FIG. 6. Otherwise, when performing its normal function, satellite 200-3 communicates with ground station S2 and a suitable gateway station. Thus, satellite 200-4 can communicate with ground stations S1 and S2 using separate individual customer antenna dishes for satellite 200-3 because of its proximity to S2, thereby allowing satellite ( Under the conditions mentioned for the failure of 200-3), it provides a beneficial level of redundancy. In such a situation, the satellite 200-4 is in addition to communication with the ground stations S1 and S2, and the one or more gateway stations 700 that enable communication between the ground stations S1 and S2 and the universal network 400. It is desirable to communicate with.

Other self-healing scenarios are shown for satellite 200-1 and satellite 200-2. Normally, S3 may communicate with S4 via satellite 200-2 (or other satellite 200 located where 200-2 is shown in FIG. 6). However, if there is an error in one customer antenna dish for satellite 200-2, FIG. 6 shows from ground station S3 to satellite 200-2, to satellite 200-1, and then to ground station ( An alternative path between S3 and S4 leading to S4) is shown. Thus, the angular range of each satellite 200 activated by the adjustable point light allows the communication system 10 to continue functioning fully, even if the satellite 200 or its components fail. It is desirable to provide redundancy in the system 150. Although FIG. 6 illustrates an embodiment of a satellite system 150 including sixteen satellites, the self-healing functionality discussed in connection with FIG. 6 may be implemented with fewer than sixteen satellites. In general, the number of satellites 200 required to provide a complete communication range decreases as the orbit 650 elevation increases. In sufficiently high-altitude MEO orbits, the overall coverage of the earth 600 may be provided by as few satellites 200 as there are four.

One advantage of the system disclosed in this specification is that even when the satellite system 150 is first deployed using six satellites that can be distributed substantially identically over a substantial equator orbit (as shown in FIG. 4). Additional satellite 200 can be easily added to satellite system 150 without distributing the operation of the first deployed satellite. Instead, the first deployed satellite and the newly added satellite can be easily controlled such that the angle range of the orbit 650 (that is, the center of gravity) in which each satellite communicates with the designated ground station is narrowed. Thus, additional satellites can be added as needed to accommodate the growing communication bandwidth requirements, thus distributing deployment costs.

One concern that continues for satellite systems is generally to avoid RF interference with other satellite systems. Since the various embodiments disclosed herein are concerned with satellites 200 moving in the equator, there is a need to address the problem of preventing interference with GEO satellites. This is because the GEO satellites are stationary in the Earth's geostationary orbit, and thus with respect to the ground stations that communicate with the GEO satellites, but lie within the equator plane. Thus, at various points of travel of satellite 200 along the LEO or MEO equator orbit, there is a risk of interference between communications between satellite 200 and its associated ground stations and communications between ground stations associated with GEO satellites and GEO satellites. In various embodiments of the present invention, the latitude and / or longitude bound of the ground station 100 and the gateway station 700 with which the designated satellite 200 communicates at any point along the orbit 650 of the satellite 700 ( bound) is made to avoid undesirable interference with GEO satellite RF reception and transmission energy. In order to prevent interference above acceptable levels, various standards have been used in the telecommunications industry. In one embodiment of this specification, each separation between communication beams separated by more than two degrees is considered sufficient to prevent interference above an acceptable level. However, those skilled in the art will appreciate that the principles discussed herein can be readily extended to accommodate the minimum light separation angle greater than or equal to 2 degrees.

FIG. 7 illustrates a north-south cross section of the earth 600 in which the GEO satellite 800 and the satellite 200 orbiting form a portion of the satellite system 150 in orbit, in accordance with an embodiment of the present invention. Earth 600 includes north pole 610, south pole 620 and equator 630. The dashed line 632 is a projection line from the center 680 (FIGS. 8-9) of the earth 600, through the equator 630, to the GEO satellite 800. Broken line 632 indicates that the GEO satellite 800 and satellite 200 are in line with the equator 630 in the arrangement of the entities shown in FIG. 7, indicating that a risk of interference is present.

However, by setting a bound on the latitude of the ground station with which the satellite 200 can communicate, interference can be effectively prevented. One set of example values is provided to illustrate this point. To use Earth 600 with a radius of 6,400 km, and satellite 200 at 8,000 km altitude, the ground station 100 should be 3.2 degrees or more (north) in order for the distinction angle α1 to be 2 degrees or more. Or anywhere in the south). Clearly, the larger the required angle of distinction, the larger the ground station 100 latitude angle will have to exist to prevent interference between satellite 200 and satellite 800.

In the example shown in FIG. 7, satellite 800 and satellite 200 both have ground station location “M” (position relative to Mexico City, located about 19 degrees north latitude), and satellites 800 and 200 at the equator. Even in line with 630, communication can be performed without causing interference.

Various ray separation angles α1, α2 and α3 are shown in FIG. 7, each corresponding to an angle separation between two separate communication beams. As already discussed above, interference beyond the acceptable limit can be prevented as long as the separation between rays acting on either the ground station or the satellite is separated by more than a minimum discrimination angle. This minimum distinct angle is between 2 degrees and 4 degrees. But. It may be below or above the range of 2-4 degrees. The minimum discrimination angle may vary as a function of the size or shape of the satellite dish, the processing equipment connected to the satellite dish, or as a function of the frequency, and / or power of each signal impinging the antenna dish at any given point in time. can be changed. In the embodiment of Fig. 7, the angular separation between light beams impinging any specified reception is clearly greater than the minimum distinct angular value described below. Furthermore, the principle of interference prevention can be extended to communication facilities having any distinct angular value. Thus, the exemplary arrangement of FIG. 7 is provided to illustrate one way in which embodiments of the present invention avoid interference. However, the present invention is not limited in this application to using the beam separation angle shown in FIG. 7 or the other figures.

In the embodiment of FIG. 7, the separation angle α1 between (a) the communication path between point M and satellite 800 and (b) the communication path between point M and satellite 200 is point (M). Since it is sufficient to protect these two rays from interference with each other at the ground station 100 of the non-interferece, it is possible to prevent interference between the various communication rays. Preferably, in this embodiment, the light beam separation angles α2 and α3 exceed the minimum distinct angle for satellite 200 and satellite 800, respectively.

Preferably, the beam splitting angles discussed above serve to prevent interference between the beams facing the common point even when the two beams use the same frequency. Although a detailed equation is not provided herein, by selecting a ground station 100 for communication with the satellite 200 that is greater than a predetermined minimum angular distance (measured in latitude units) north or south from the equator 630. It can be seen that the separation angle between the GEO satellite 800 for the M ray and the satellite 200 for the M ray can be maintained above the maximum separation angle.

Since the latitude has been described, interference between satellite 200 and GEO satellite 800 within satellite system 150 is next when the GEO and non-GEO satellites communicate with ground stations located at or very close to the equator. To avoid that.

8 illustrates the equator plane of the earth 600 orbiting the satellite 200-n, which forms part of the GEO satellite 800 and the non-GEO satellite system 150, in orbit, according to one embodiment of the invention. It is a figure which shows. 8 shows the point E on the equator and on the surface of the earth where the ground station 100 is located. The satellite system 150 may operate in an orbit located below or above the altitude of the orbit described as connected to FIGS. 8 and 9.

In this embodiment, the satellite system communicates with the ground station 100 at position E on the equator 630 in the region where another station receives and transmits RF energy along the path 802 to the GEO satellite 800. If detected by 150, the interference between satellites 200 and GEO satellite 800 communications of satellite system 150 may be affected by a satellite system (e.g., outside the specific forbidden angle range 640 in which the risk of interference exists). Can be prevented using satellite 200 within 150. The placement of the adjustable beam relative to the satellite 200 does not cause interference with communication between the GEO satellite 800 and the GEO satellite associated ground station located at or adjacent to the point E, and the equator 630 of the earth 600. It is preferable that the ground station and the satellite 200 located at the point E to be activated to activate communication.

In the embodiment of FIG. 8, satellite 200-n of satellite system 150 is in the MEO orbit at an altitude of about 6,000 km. The satellite system 150 is outside the forbidden angle range 640 but within the communication range 660 of the point E on the equator 630 to communicate with the ground station 100 at point E. It is desirable to activate 200. In this embodiment, the ground station 100 located at point E is at a topographic angle (an angle as seen from the surface of the earth 600) which is an elevation of at least 5 degrees above the east and west horizons. It may communicate with any satellite 200. The above constraint allows the ground station located at point E to communicate with satellite 200 in most communication range 660. In this example, at the above-mentioned altitudes and where there are constraints mentioned for elevation above the horizon, about 110 degrees for ground station 100 where communication range 660 is located at point E. to be.

More specifically, non-interfering communication between ground stations 100 located at point E may occur at all communication ranges 660 other than segments of the trajectory 650 within the forbidden range 640. More specific examples of the trajectory / constellation configurations discussed above are considered in connection with FIG. 9.

FIG. 9 illustrates an Earth 600 orbiting a GEO satellite 800 and two satellites 200-1 and 200-2 that form part of a non-GEO satellite system 150, according to an example of the present invention. A diagram showing the equator plane of. As in FIG. 8, point E corresponds to the position of ground station 100 located at equator 630. The scheme for interference prevention proposed in this specification works in the same way, regardless of the hardness of point E. Therefore, the hardness of the points E and 100 is not specified.

9 shows satellites 200-1 and satellites 200-2 continuous within satellite system 150 in the equator orbit at an altitude of about 6,000 km above the surface of Earth 600. The angular separation between the satellites 200-1 and 200-2 is the center angle 22 (separation angle as measured from the center 680 of the earth 600) and / or the ground angle 224 ( A separation angle known from the point E on the surface of the earth 600). In the embodiment of FIG. 9, the satellite system 150 preferably includes 16 satellites spaced equally along the orbit 650 (FIGS. 4-5). In 16 equally spaced satellites, each distance between successive satellites 200-1 and 200-2 is 22.5 degrees. Thus, the continuous communication connectivity between the satellite system 150 and the ground station 100 at point E maintains communication over a range of motion along the orbit 650 of 22.5 degrees. However, in alternative embodiments, the connectivity between the designated satellite 200 and the ground station 100 may be changed as desired, within the limits for communication connections of the various satellites 200. As previously mentioned, using an altitude of 6,000 km, if the constellation of 16 satellites 200 is equally distributed over orbit 650, up to 5 satellites will be pointed at any given point in time. It may have a line-of-site communication capability with the ground station 100 located at (E). Accordingly, it will be appreciated that many possible variations of the above connectivity schemes may be implemented.

In the embodiment of FIG. 9, communication range 660 is about 110 degrees (when using 6,000 km altitude and the condition that satellite 100 is at least 5 degrees above the east and west horizons for communication). Having a centerline 802 and edges 642, 644 and pointing towards the GEO satellite 800 at the center 680 of the earth 600, as can be seen at ground station 100 located at point E. By setting the prohibition range of the indicator angle range of 2 degrees, interference prevention with the GEO satellite 800 can be achieved. However, the angular magnitude of the prohibition range 640 may be increased or decreased depending on the sensitivity of one or more communication devices to interference. The present invention is not limited to the use of any specific size prohibition range. In one embodiment, forbidden ranges greater than or less than two degrees may be used where equipment characteristics permit.

In the following, one specific approach to interference is described. It will be appreciated that many communication devices are capable of providing continuous connectivity to ground station 100 and satellite system 150 while preventing interference with GEO satellite 800, so that the present invention is not limited to this approach. .

In summary, the various aspects of satellite orbits, satellite constellation design, and the nature of RF communications produce varying results within the scope of which various communication options or schemes are available. More specifically, design aspects such as orbit 650 altitude above the earth 600, the number and distance of satellites 200 in the satellite system 150 (in this case a single constellation 150) determine the following results: do:

(a) a minimum topocentric elevation angle (here, 0 degrees elevation elevation angle) for the satellite 200 above the horizon enabling communication with the ground station 100;

(b) a communication range 660 corresponding to the portion of the orbit 650 where the designated ground station has a line-of-site communication connection with the satellite 200 of the satellite system 150;

(c) a range of longitude ω at which the ground station can be deployed, in communication with the designated satellite 200 located at the designated point along the orbit 650; And

(d) The total number of satellites in the satellite system 150 having line-of-site communication capability with the designated ground station 100 at the designated time.

Separately, sensitivity to interference of the GEO satellite 800 and associated ground stations may determine the angular value of the prohibition range 640.

Some specific values are now described for example embodiments. In this example, an altitude of about 6,400 km (approximately equal to the radius of the earth) and 16 satellites evenly spaced within the orbit 650, negligible elevation, about 110 degrees of communication range 660, about Communication longitude range (ω) for the designated satellite 200 at 120 degrees (FIG. 10), and all five satellites 200 that are visible (i.e., likely to communicate with the designated ground station) at the designated ground station at the specified time point. Use The range of longitudes seen by the designated satellite 200 at the designated time point is shown as an angle ω in FIG. 10. The range of longitude generally increases as the altitude of the trajectory 650 increases. The angle θ of FIG. 10 corresponds to a right angle and may be adjusted such that light rays acting on the satellite 200 can communicate with ground stations located on the surface of the earth 600 within the longitude range ω.

The above condition involving the negligible elevation angle mentioned satisfies the communication longitude range ω of about 120 degrees. The need for a minimum topocentric elevation angle at ground station 100 will reduce the communication hardness range ω. Furthermore, for a given satellite at a given altitude, the communication longitude range ω will decrease as the minimum surface elevation angle increases. For example, at an altitude of 6,000 km, with a minimum elevation angle of 5 degrees, each satellite 200 has been determined to have a longitude range ω of about 108 degrees. At this same altitude (6,000 km), in a system using satellites spaced at 16 equal angular distances and thus arranged at a center angular interval of 22.5 degrees with respect to orbit 650, at point E (FIG. 9) The satellite of the ground station 100 located rotates over an angle range of about 45.5 degrees.

It is contemplated to apply a prohibition range 640 value of 2 degrees to this example. However, this value may vary depending on the situation. Those skilled in the art will appreciate that changing the design aspects of the orbit 650 and constellation 150 will likewise change the results listed above. Further, it will be appreciated that the present invention is not limited to the above-mentioned design aspects or the results listed above.

The flexibility and redundancy possible by the embodiment of FIG. 9 does not affect the communication reception or transmission of the GEO satellite 800, but the ground station located at the continuous satellite 200 and the point E of the satellite system 150. Activate various options to enable communication. One such option is described below. However, other options may be implemented.

At an altitude of 6,000 km, an example is considered in which the satellite 200-1 and satellite 200-2 and the ground station 100 at point E communicate over each segment of the 22.5 degree indicator of the orbit 650. 9 shows points in a series of stages in which a handoff (escalation) is made between satellite 200-1 and satellite 200-2. Preferably, the ground station 100 communicates with each satellite 200 starting at a location where satellites 200-2 are shown in FIG. Terminate the communication session when 200 arrives. The geometry of these locations is best described using a combination of indices and centroid angles.

In this example, communication between each satellite 200 and ground station 100 begins when the satellite 200 is five degrees above the horizon. This location is shown in FIG. 9, where line 228 is drawn from ground station 100 at location E toward the horizon in the west direction. The smallest elevation (where this is 5 degrees from the horizon) is shown at angle 226. Satellite 200-2 is shown at this minimum elevation position in FIG. 9. Thus, once the satellite 200 reaches the minimum elevation angle 226, the connection between the satellite 200 and the ground station 100 may begin. This connection continues as the satellite 200 progresses along the orbit 650 (where the satellite proceeds counterclockwise in FIG. 9). In this embodiment, the satellite 200 advances 22.5 degrees (center angle) along the orbit 650 during a connection session with the ground station 100, preferably as shown by the center angle 222. This 22.5 degree angular distance corresponds to 1/16 of one complete orbit of the Earth 600 state, and thus the above description of the constellation of satellite system 150 comprising 16 satellites spaced at equal even angular distances. Matches.

As described above, when satellite 200 completes its progression over an orbital segment of 22. 5 degrees, it reaches the position where satellite 200-1 is shown in FIG. In this step, the ground station 100 connection to the satellite system 150 is transferred to the next satellite 200 (the satellite in the next constellation in the clockwise direction). With respect to the satellite numbered specifically in FIG. 9, when satellite 200-1 completes the 22.5 degree orbit segment indicated by angle 222, the connection of ground station 100 is terminated at satellite 200-1. It is preferable to transfer to -2). Thereafter, the sequence described above is repeated for satellite 200-2, and then for satellite 200-3 (not shown), satellite 200-4 (not shown), and the like. In the case of using a satellite system 150 having constellations comprising 16 satellites spaced at equal angular distances along the orbit 650, located at a stated altitude of 6,000 km, the satellite system 150 (and thus Continuous connection of the ground station 100 to the general purpose network 400 may be accomplished by repeating the above steps of communicating with the satellite 200 via the orbital segment 222, and then the connection is next in constellation. Escalated to satellite. It will be appreciated that constellation system 150 may include fewer or more than sixteen satellites. Changing the number of satellites in satellite system 150 may require the use of orbit segments having an angular range that differs from the altitude of orbit 650 and / or other parameters of communication system 10 discussed above. have. In various embodiments of the present invention, the flexibility of the communication device and the desired redundancy of the satellite system 150 will increase as the number of satellites in the satellite system 150 increases.

As the satellite 200 moves along the orbit segment 222, the surface angle (indicated by the angle 224) of the satellite visible by the ground station 100 located at point E is represented by the angle 222. It may vary substantially more than the 22.5 degree value. However, angle 224 is mostly related to the adjustment of the orientation of the tracking equipment located on the communication antenna dish and / or other ground station 100 and / or satellite 200. As the satellite 200 moves through each of the designated ear guide segments 222, the ground angle 224 as the tracking equipment rotates increases as the altitude of the orbit 650 decreases. For representation, for a very low altitude 650, in order to track the satellite 200 along a relatively small orbital angular segment 222, the angle 224 must rotate rapidly from the west horizon to the east horizon.

From the above, if the communication range 660 is much larger than the orbit segment 222 required for each satellite, the distance that the connection "session" of the ground station 1000 with each satellite is safe from the prohibition range 640 It can be performed in. As previously discussed in this specification, this effectively avoids interference with the receive / transmit RF energy for the GEO satellite 800. While one such anti-interference scheme is presented above, the geometric arrangement of the orbit 650 and satellite constellation 150 enables many other such schemes. For example, from FIG. 9, it is readily understood that significant angular space may exist within the communication range 660 (FIG. 8) of the ground station 1000 outside the orbit segment 222 used in the embodiments described above. Can be.

To provide an overview of the geometrical arrangement of the orbit 650 and the placement of the ground station 100 and the gateway station 700, from now on in more detail the operation of the embodiment according to the invention on top of a portion of the earth 600. Provide an example.

The following example illustrates an embodiment that includes an equator orbit 650 for illustration. However, the present invention is not limited to having a satellite purely along the equator orbit. If satellites in the satellite system 150 are needed, they can move along an inclined orbit. This inclined trajectory may fall away from the equator by any desired range, for example, one or less latitudes, five or less latitudes, or ten or less latitudes.

The various figures in this specification show some earth stations, such as those present at ground station 100 and other gateway stations 700. In some embodiments, ground station 100 is an earth station that does not have a wired connection to universal network 400, and gateway station 700 is an earth station that has this wired connection to universal network 400. However, the present invention is not limited to the apparatus described above. Some district stations may perform functions such as ground station 100 and gateway station 700. Some ground stations 100 communicate via satellite system 150 for specific purposes, but may have a wired connection to a general purpose network. Furthermore, some gateway stations 700, having connections to the general purpose network 400, provide one or more gate stations 700 when providing more convenient and / or faster communication over a particular segment of the earth 600. ) Can be communicated with. Unless stated otherwise, one or more ground stations 100 and one or more gateway stations 700 may have interchangeable functions. In either case, the communication connections available to the designated district station may change over time.

Thus, a ground station 100 located within a tropical area that does not currently have a wireless connection to the universal network 400 and thus exclusively relies on satellite communications for the universal connection will eventually end this wired connection to the universal network 400. Can be obtained. In the case of using such a wired connection, the satellite system 150 according to the invention can provide valuable additional bandwidth for the currently-wired ground station 100.

FIG. 11 shows a Mercator projection map of a portion of the earth 600 showing the selection of a satellite 200 orbiting the earth 600 in accordance with one or more embodiments of the present invention.

11 shows satellites 200-1, 200-2 and 200-3 adjacent to South America, Africa and Asia, respectively. Ground station 100-1 adjacent to Venezuela Caracas; Ground station 100-2 adjacent to Brazil Brasilia; Satellites 100-3 adjacent to Zaire Kinshasa; Ground station 1004 adjacent to Kuala Lumpur, Malaysia; And various district stations including ground stations 100-5 adjacent to Bangkok, Thailand. FIG. 11 further shows a gateway station 700-1 adjacent to Buenos Aires, Argentina; Gateway station 700-2 adjacent to Johannesburg, South Africa; Shown is Gateway Station 700-3, adjacent to Perth, Australia. In this embodiment, a plurality of satellites 200-1, 200-2, and 200-3 are shown moving along the equator 630. For this discussion, assume that a plurality of ground stations 100-1, 100-2, 100-3, 100-4, and 100-5 do not have a wireless connection to the general purpose network 400.

FIG. 11 is a simplified diagram of various satellites 200, ground stations 100 and gateway stations 700 capable of providing backhaul services for ground stations 100 that do not have a wired connection to general purpose network 400. to provide. Indications (or identifiers) for ground stations, gateway stations and cities are provided for illustrative purposes and do not necessarily reflect the connections currently available at any particular location.

For the purpose of explanation in FIG. 11, a plurality of ground stations 100-1, 100-2, 100-3, 100-4 and 100-5 are arranged adjacent to Caracas, Brasilia, Kinshasa, Kuala Lumpur, and Bangkok, respectively. ) Is treated as lacking a wired connection to the rest of the world, and therefore a satellite system 150 is needed to provide connectivity to the universal network 400 for various above listed ground station locations. Although the constellations of the satellites 200 move along their orbits, the position shown in FIG. 11 is described as being stationary for convenience of description.

In this embodiment, the satellite 200-3 preferably communicates with the ground station 100-1 and the ground station 100-2, and the gateway station 700-1. In an environment where the gateway station 700-1 (adjacent to Buenos Aires) has a wired connection to the universal network 400, the satellite 200-3 may be connected to the ground station (100-1, adjacent to Caracas) and the ground station (100-). 2, it is desirable to be able to extend this universal connection to Brasilia, which is treated as having no wired connection to the universal network 400 for this example (embodiment). Thus, in this embodiment, satellite system 150 may provide a unique low-latency communication solution for ground station 100-1 and ground station 100-2.

In this embodiment, a similar situation exists for satellite 200-2, which is shown disposed adjacent to the African continent. In this embodiment, the ground station 100-3 located adjacent to Zaire, Kinshasa is treated as lacking a wired connection to the universal network 400. Meanwhile, the gateway station 700-2 adjacent to Johannesburg and the gateway station 700-3 adjacent to Tel Aviv are treated as having a wired connection to the general-purpose network 400. Thus, at least, in this embodiment, satellite system 150 (indicated at points in time shown in FIG. 10 by satellite 200-2) is gateway station 700-3 and / or gateway station 700. -2) to connect the ground station 100-3 to operate the low-latency (high speed) backhaul communication service to the ground station 100-3.

However, the present invention is not limited to providing only the functions listed above. In a preferred case, satellite 200-2 also provides a useful communication link directly between gateway station 700-2 and gateway station 700-3. In some cases, a wired connection to the general purpose network 400 available at the gateway station 700-2 and the gateway station 700-3 is a direct communication between the station 700-2 and the station 700-3. Use of satellite system 150 is unnecessary for this purpose. In other cases, however, satellite system 150 may still function as a useful additional link providing low-latency, high-bandwidth communication services between gateway station 700-2 and gateway station 700-3. have. Further, in special cases, such as when a wired link fails, satellite system 150 may function as a valuable backup communication option between gateway station 700-2 and gateway station 700-3.

Similar to the above, satellite 200-1 may have a communication link to gateway station 700-4, ground station 100-4, and / or ground station 100-5. For this discussion, ground station 100-4 and ground station 100-5 are treated as having no wired link to general purpose network 400. Thus, in this case, the satellite 200-1 is backhaul communication service from the ground station (100-4, adjacent to Kuala Lumpur) and / or the ground station (100-5, adjacent to Bangkok) to the gateway station 700-4. Can be operated to provide.

Selection of particular cities in certain selected latitudes and longitudes has been used to describe certain aspects of one or more embodiments of the invention. However, it will be apparent to those skilled in the art that the principles described herein can be readily extended to any ground station at any longitude on Earth 600 or in any adjacent city. Furthermore, embodiments of the present invention may deliver the services described above within a range from north to south from 40 degrees north to 40 degrees south.

In Figures 12-14, a sequence of communication sessions performed by two consecutive satellites in orbital motion above South America is described. This description uses a sequence of static figures to help explain the dynamic operation of embodiments of the present invention. Although only two satellites 200-1 and 200-2 and three ground stations located in three separate cities are shown, any number of locations within the latitude range of satellite system 150 may be included in one or more embodiments of the present invention. It can be clearly served by.

Figure 12 is a plan view showing a constellation (satellite 200-1 forming part of satellite system 150) that moves along an equator orbit 650 in upper South America in accordance with an embodiment of the present invention. Continental continent, equator 630, satellite 200-1 moving along the equator. Looking back at the device described above in connection with Figure 11, satellite 200-1 is a ground station (100-1, adjacent to Caracas). Communication with the ground station 100-2 (adjacent to Brasilia) and the gateway station 700-1 (adjacent to Buenos Aires), in one embodiment, the satellite 200-1 is connected to the ground stations 100-1 and 100. -2) may provide backhaul communication to gateway station 700-1 (which has no wired connection to general purpose network 400), which preferably has a wireless connection to general purpose network 400 .

FIG. 13 shows the system of FIG. 12, where the satellite 200-1 travels east along its orbit 650, but with the ground station 100-1 and the ground station 100-2 and the gateway station. Maintain communication with (700-1). Furthermore, satellite 200-2 of satellite system 150 has entered into FIG.

A further progression step is shown in FIG. 14, where communication from two ground stations 100-1 and 100-2 and gateway station 700-1 has been transferred from satellite 200-1 to satellite 200-2. . The dashed line extending north-west from satellite 200-1 attempts to represent an initial stage where the communication path between satellite 200-1 and the earth station is further established along orbit 650, as in the west coast of Africa. will be. The exact location of this earth station is not central to this discussion and therefore nothing is specified.

Preferably, since the constellation of satellite 200 continues to move along orbit 650, infinitely continuous satellite 200, which forms part of satellite system 150, is the earth station 100-1, from the west. It continues to enter the communication range, shown in FIGS. 12-14 for 100-2 and 700-1. As satellite 200-2 operates as shown in FIG. 14, it advances along orbit 650 within South America, followed by several Earth stations 100-1, with each satellite facing east from South America. , Leaving the communication area for 100-2, 700-1). And satellite 200-1 operates as shown in FIG. In this manner, the satellite system 150 can be configured to provide the ground stations 100-1 and 100-2 and the gateway station 700-1 even when individual satellites 200 enter and leave the communication range of such earth stations. You can keep your connection with you.

15 is a functional block diagram illustrating hardware 300 mounted on satellite 200 in accordance with one or more embodiments of the present invention. Satellite hardware 300 may include a processor 302, data path control 304, gateway antenna dish tracking system 306, customer antenna dish tracking system 308, gateway antenna dish 316, and / or customer antenna dish 318. ) May be included.

Processor 302 may be a multi-purpose process with connections to volatile and / or nonvolatile memory. Processor 302 may be operable to coordinate data flow between gateway antenna dish 316 and customer antenna dish 318. The data path control device 304 preferably operates to control data flow from various transponder inputs, along the waveguide and to various transponder outputs within the satellite 200. Data path control 304 may be implemented by the processor 302 using one or more MUX frequency splitters, using other devices, or by a combination of one or more of these devices.

The gateway antenna dish tracking system 306 preferably operates such that the counterpart antenna dish and the gateway antenna dish 316 in communication maintain a communication path, where the counterpart antenna dish is the earth 600 or other satellite. May be present on the surface of the. The operation of the tracking system 306 depends on the type of antenna dish and the light beam used by the antenna dish 316. The above description can also be applied to customer antenna dish tracking system 308 and customer antenna dish 318, respectively. In the following, two types of antennas are described with a tracking system corresponding to each antenna type.

In one embodiment, the gateway antenna dish 316 and / or the customer antenna dish may comprise one or more reflectors suitable for directing the point light beam in the desired direction with the supply. In such an embodiment, the set light direction may mechanically adjust the antenna assembly to control the orientation of the antenna dish along one or more angular dimensions. A tracking system suitable for interacting with a mechanically adjustable antenna is described next.

Mechanically adjustable antennas (eg, in FIG. 17) where the gateway antenna dish 316 or customer antenna dish 318 continually adjusts the orientation of the point beams for transmission and reception by the antenna dish 316, 318. Tracking system 306 or 308 operates to control the orientation of the antenna dish according to the pitch dimension or the pitch and roll angular size, thereby providing the antenna dish 316 or 318. Ensure that the communication target (where the communication target is a ground station or other satellite) communicates with it. Suitable light intensity sensing equipment and motors may be implemented to properly adjust the orientation of the antenna dishes 316, 318 to maintain a communication path at or above an acceptable power level.

If the gateway or customer antenna dish 316, 318 uses a phased array antenna (eg, as described in connection with FIG. 18), the tracking system 316 and / or the tracking system 318 may be the antenna dish 316. And / or light sensing equipment and light control equipment suitable for forming a communication light beam for 318. This forming step preferably includes controlling the direction and communication power of the communication path to the antenna dish 316 and / or antenna dish 318. In one or more embodiments, controlling the direction and communication power of the phased array antenna may be achieved by adjusting the antenna level of the array of antenna elements within each antenna such that the combination of the contributions of the individual antenna array elements to the designated antenna is desired and Generating a single beam having a desired communication power.

The customer antenna dish 318 and the gateway antenna dish 316 may be any one of several types of satellite communication antenna dishes capable of bidirectional communication with one or more ground stations, one or more other satellites, and / or a combination of ground stations and other satellites. It may include. Satellite 200 may include any number of customer antenna dishes 318 and any number of gateway dishes 316.

15A is a diagram illustrating equipment on satellite 200 in accordance with one or more embodiments of the present invention. Processor 302 and data path control device 304 of FIG. 15A preferably correspond to the same numbered entities described above with respect to FIG. Therefore, the description of these items is not repeated in this section. The satellite 200 equipment includes a processor 302, data path control equipment 304, low noise amplifier 403, multiplexer (mux) 404, demultiplexer (demux) 410, traveling wave tube amplifier 412). Satellite 200 may receive customer light 406 and gateway light 408 and may transmit customer light 416 and gateway light 418.

Satellite 200 may receive customer light 406 and gateway light 408. The received light travels through a low-noise amplifier (LNA) 402. The received gateway beam 408 proceeds to the demux 410 and controls the data path control device 403 and processor 302 along one or more of the customer beams 416 or along the gate beam 418. Underneath, it is transmitted outside of the satellite 200. In either of the above paths, outbound light is amplified in one or more TWTAs 412 prior to transmission of the satellite 200.

After amplification, the received customer light beam 406 may travel towards the multiplexer 404, after which the light beam 406 transmits toward the gateway light beam 418 and / or out of the satellite 200. It may be transmitted toward the demux 410 facing the light beam 416. In either case, the outbound light passes through the TWTA 412 before being transmitted outside the satellite 200.

The number of gateway rays and customer rays in FIG. 15A is for illustration purposes. In other embodiments, fewer or more than three inbound and outbound customer beams may be used. Furthermore, in other embodiments, two or more gateway rays may be received and transmitted from the satellite 200.

For illustrative purposes, the customer receive light beam 406 and the customer transmit light beam 416 are shown separately, such as the receive light beam 408 and the transmit light beam 418 for the gateway. However, in one or more embodiments, separate antennas may be used for both receiving and transmitting data. In other embodiments, data transmission and data reception operations may be performed by separate antennas for one or more customer and / or gateway communication paths.

16 is a block diagram illustrating a plurality of communication antenna dishes on satellite 200 in accordance with one or more embodiments of the present invention. In this embodiment, each antenna dish can both transmit and receive radio frequency communications.

Satellite 200 may include gateway transponders GW1 and GW2 for communication with two separate gateway stations on Earth. In other embodiments, satellite 200 may include fewer or more than two gateway transponders. The satellite 200 further includes twelve antenna dishes (each with the desired or preferably associated transponders) for communication with ground stations in communication with the customer, which are transponders C11, C12, C13. , C14, C21, C22, C23, C24, C31, C32, C33, C34). Twelve communication antenna dishes for customer communication are shown in FIG. 1, but fewer or more than twelve communication antenna dishes may be included in the satellite 200. One or more of the antenna dishes on satellite 200 may be mechanically and / or electronically adjusted to track a fixed location on Earth, a moving target on Earth, and / or another satellite as the satellite travels along orbit 65. Can be. The adjustment capability may be provided in one or more orientation dimensions as desired or as desired for a given application. In one embodiment, one or more customer communication antenna dishes and / or one or more gateway antenna dishes may be economically configured to track earth stations in only one direction. In other embodiments, one or more customer antenna dishes and / or one or more gateway antenna dishes may serve individual communication targets (static earth stations, moving earth stations, and / or other satellites) in two angular dimensions. Can be configured to track.

In one embodiment, the data received at the input of any one of the transponders of the satellite 200 shown in FIG. 7 will be routed to be output from any one of fourteen transponders including the transponder from which the data was received. Can be. In other embodiments, a more limited set of signal transmission routing options may be used within one or more satellites 200 within the top of such satellites to gain greater economic benefit.

FIG. 17 is a schematic diagram illustrating a satellite 200 having two mechanically adjustable antennas 252, 254 in accordance with one or more embodiments of the present invention. Antenna 252 preferably rotates about axis 252-a, and preferably antenna 254 rotates about axis 254-a. Axis 252-a and 254-a extend into and out of the page in FIG. 17. Antenna 252 and antenna 254 move along orbit 650 to maintain their respective communication path relative to the individual earth-based (or satellite-based) antenna with which satellite 200-1 communicates with it. As such, it can rotate about an individual axis 252-a and an axis 254-a. Rotation about axis 252-a and axis 254-a enables satellite 200-1 to communicate with ground station 100, which has a wide range of longitude above the surface of earth 600. . In some embodiments, antennas 252 and 254 also preferably allow satellite 200-1 to communicate with ground stations 100 located at different latitude ranges on the surface of earth 600. Rotation about axis 256 corresponds to adjustment of the axis of rotation of antennas 252 and 254. It is clear that the rotation about the axes 252-a / 254-a, and 256 corresponds only to adjustments for longitude and latitude, respectively. Stated differently, in some embodiments, rotation of antenna 252 about axis 256 may change both the latitude and longitude of the location on earth 600 with which antenna 252 communicates. Likewise, in some embodiments, rotation of antenna 252 about axis 252-a can change both the latitude and longitude of a location on earth 600 with which antenna 252 communicates.

In one embodiment, antenna 252 may communicate with ground station 100 and antenna 254 may communicate with gateway station 700, thereby connecting ground station 100 with a general purpose communication network. However, in other examples, this arrangement can be changed. Although only two adjustable antennas 252, 254 are shown in FIG. 17, any desired number of antennas may be used in the designated satellite 200-1. For example, the embodiment of FIG. 16 shows a satellite 200 with twelve customer antenna dishes and two gateway antenna dishes. In one embodiment, all fourteen antenna dishes shown in FIG. 16 may be adjustable antennas. In one embodiment, all fourteen antennas may be mechanically adjustable. In another embodiment, all fourteen antennas may be electrically adjustable. In another embodiment, a combination of a mechanically adjustable antenna and an electronically adjustable antenna may be included between the fourteen antennas shown in FIG. Furthermore, it is apparent that less than or more than 14 antennas may be included in one or more satellites 200 in satellite system 15.

18 is a diagram illustrating a satellite having two electrically adjustable antennas 262, 264 in accordance with one or more embodiments of the present invention. In the embodiment of FIG. 18, antennas 262 and 264 communicate with individual ground stations and / or other satellites on the surface of Earth 600 as satellite 200-1 travels along orbit 650. It can be continuously controlled to maintain the path. In one embodiment, antenna 262 may communicate with ground station 100 on the surface of earth 600, and antenna 264 may communicate with gateway station 700. While two phased array antennas are shown in FIG. 18, any number of antennas may be used. The satellite 200-1 is not limited to having only one type of antenna. Specifically, satellite 200-1 may include one or more mechanically adjustable antennas and / or one or more electrically adjustable antennas (eg, a phased array antenna). As described with respect to FIG. 17, the satellite 200 of FIG. 18 may include, for example, fourteen antennas as shown in FIG. 16, combining a mechanically adjustable antenna and an electrically adjustable antenna. Including use.

In operation with a suitable tracking system (described in connection with FIG. 15), it is desirable for the antenna 262 to operate to orient the communication path along one or more angular dimensions. Specifically, the antenna 262 may adjust the pitch angle and / or rotation angle (both described with respect to FIG. 17) of the communication beam as needed.

19 is a block diagram of a computer system 199 adapted for use with one or more embodiments of the present invention. For example, one or more portions of computer system 1900 may be computer functions 110 of FIGS. 3 and 3A, processor 302 of FIG. 15 and / or functions of data path control device 304, as described herein. It may be used to perform the functions of the gateway station 700 and / or one or more processing entities in the communication system 10 of FIG. 1.

In one or more embodiments, a central processing unit (CPU) 1902 may be coupled to the bus 1904. In addition, bus 1904 may include random access memory (RAM) 1906, read only memory (ROM) 1908, input / output (I / O) adapter 1910, communication adapter 1922, user interface adapter 1906, and the like. May be connected to the display adapter 1918.

In one embodiment, RAM 1906 and / or ROM 1908 may store user data, system data, and / or programs. I / O adapter 1910 may connect hard drive 1912, CD-ROM (not shown), or other mass storage device to computer system 1900. The communication adapter 1922 may connect the computer system 1900 to a local, wide area or general purpose network 1924. User interface adapter 1916 may connect user input devices, such as keyboard 1926 and / or pointing device 1914, to computer system 1900. Further, display adapter 1918 may be driven by CPU 1902 to control the display on display device 1920. CPU 1902 can be any versatile CPU.

Any known processor, programmable digital device or system, programmable array logic device that the methods and apparatus described previously and / or later in this document execute standard digital circuits, analog circuits, software and / or firmware programs. Note that the present invention may be implemented using any one of the known techniques such as a combination thereof. One or more embodiments of the invention may also be implemented as a software program for storage on a suitable storage medium and for execution by a process unit.

Although the present invention has been described with reference to specific embodiments, it should be understood that this embodiment is only for expressing the principles and applications of the present invention. Accordingly, it will be understood that various modifications may be made to the practical embodiments and that other arrangements may be implemented without departing from the spirit and scope of the invention as defined by the appended claims.

Claims

At the equator, a constellation consisting of a plurality of satellites operating in a non-stop orbit around the earth, wherein at least one of the plurality of satellites is:
A first antenna controllable to transmit a first point beam concentrated at one or more ground stations; And
A second antenna controllable to transmit a second point beam focused to one or more gateway stations
Satellite communication system comprising a.

The method of claim 1,
And the at least one satellite is operable to establish a communication path between the ground station and the gateway station along the first and second point beams.

The method of claim 1,
At least one of the first and second antennas is mechanically adjustable.

The method of claim 1,
And at least one of said first and second antennas is a phased array antenna.

The method of claim 1,
The at least one satellite is operable to prevent interference with GEO satellite communications with a GEO sub-satellite point on the earth by communicating with a ground station on earth having a minimum longitude angular separation from the GEO sub-satellite point. Satellite communication system.

The method of claim 5, wherein
The minimum latitude angle separation is 5 degrees.

The method of claim 1,
The system utilizes one satellite in a constellation consisting of a plurality of satellites, with a sub-satellite point having a minimum longitude angular separation from the GEO sub-satellite point, thereby providing for GEO satellite communication with the GEO sub-satellite point on Earth. And a satellite communication system operable to prevent interference.

The method of claim 7, wherein
And said minimum longitudinal angular separation is 5 degrees.

The method of claim 1,
And said plurality of satellites in said constellation are within communication range of said ground station at any specified time, thereby providing a redundant satellite communication option for said ground station.

The method of claim 9,
And wherein the ground station is operative to migrate communication from the first satellite to the second satellite in the event of a failure of the first satellite.

The method of claim 1,
The constellation comprises at least 16 satellites, wherein at least three satellites are present within the communication range of the ground station at any given time.

The method of claim 1,
Wherein said at least one ground station lacks a wired connection to any universal communication network, and said at least one gateway station has a wireless connection to a general purpose communication network.

The method of claim 12,
And said general purpose communication network comprises the Internet.

The method of claim 1,
Wherein said at least one satellite is operative to route the data packet signal to a destination in a communication system based on a transmission frequency of the data packet signal.

The method of claim 1,
And the constellation of the satellite operates in orbit having an altitude between 2,000 km and 25,000 km.

The method of claim 1,
And the satellite constellation operates in orbit having an altitude between 8,000 km and 20,000 km.

Causing a constellation of a plurality of satellites to move along an equator, non-stop orbit;
Controlling a first antenna on at least one of the plurality of satellites to transmit a first point beam concentrated at one or more ground stations; And
Controlling a second antenna on one or more of the plurality of satellites to transmit a concentrated second point beam to one or more gateway stations
Communication method comprising a.

The method of claim 17,
Establishing a communication path between the ground station and the gateway station along the first and second point beams.

The method of claim 17,
Controlling the first antenna includes:
a) mechanically adjusting the first antenna to transmit a first point beam concentrated at one or more ground stations; And
b) electrically adjusting the concentrated first point beam
A communication method comprising at least one of.

The method of claim 17,
Controlling the second antenna includes:
a) mechanically adjusting the second antenna to transmit a second point beam concentrated at one or more ground stations; And
b) electrically adjusting the concentrated second point beam
A communication method comprising at least one of.

The method of claim 17,
At least one of the first and second antennas is a phased array antenna

The method of claim 17,
Preventing one or more satellites from communicating with the GEO satellites and the GEO sub-satellite points on the earth only by allowing the one or more satellites to communicate only with earth stations on the earth having a minimum latitude angle separation from the GEO sub-satellite points. A communication method characterized by the above.

The method of claim 21,
And wherein said minimum latitude angle separation is 5 degrees.

The method of claim 21,
Between the GEO satellites with the sub-satellite points of the GEO satellites by using satellites in the constellation of plural satellites for communication with the ground station having sub-satellite points with minimum longitude angular separation from the GEO sub-satellite points Satellite communication method characterized in that to prevent the interference to the communication.

The method of claim 24,
And said minimum longitudinal angular separation is 5 degrees.

A constellation of plural satellites operating in an equator, non-stop orbit;
A plurality of ground stations in communication with the constellation, wherein one or more designated ground stations of the plurality of ground stations lack a wired connection to any universal communication network; And
At least one gateway station connected to a universal communication network and at least one of said plurality of satellites,
Wherein said at least one satellite comprises at least one antenna utilizing adjustable beams that can be controlled to transmit a continuously focused first point beam towards said designated ground station.

The method of claim 26,
Wherein said at least one antenna comprises a mechanically adjustable antenna.

The method of claim 26,
Wherein said at least one antenna comprises a satellite array antenna.

The method of claim 26,
Wherein said at least one antenna communicates with a designated ground station in real time, said at least one gateway station activating a connection between said designated ground station and said universal communication network.

The method of claim 29,
Wherein said universal communication network comprises the Internet.

The method of claim 26,
The designated ground station delegates a communication connection from the first satellite of the constellation to subsequent satellites entering the communication range of the designated ground station, thereby providing a continuous communication connection of the designated ground station to the universal communication network. Communication system.

The method of claim 26,
Orbit the satellite constellation has an altitude between 2,000 km and 25,000 km.

The method of claim 26,
Orbit the satellite constellation has an altitude between 6,000 km and 20,000 km.

The method of claim 26,
Orbit the satellite constellation has an altitude between 7,000 km and 12,000 km.