SPACECRAFT ANTENNAS AND BEAM STEERING METHODS FOR SATELLITE COMMUNICATION SYSTEM

Abstract: The Spacecraft Antennas & Beam Steering Methods for Satellite Communication System comprises an advanced active element phased antenna array (10). The present invention utilizes electronic beam steering to provide extremely high gain signals. In one of the preferred embodiments of the invention, a satellite (S) includes an Earth-facing array (10) of hexagonal antenna facets (12) that are mated together along their six-sided boundaries to form a slightly flattened, hemispherical shell. The antenna array (10) is connected to two rectilinear, unfurled, solar panels (14) which trail the body of the spacecraft (S) and provide electrical power. The antenna array (10) is designed to transmit and receive signals from terrestrial units that are located within the footprints (20) produced by the electronically steered beams (19).

Description: Spacecraft Antennas and Beam Steering Methods for Satellite Communication System CROSS-REFERENCES TO RELATED PATENT APPLICAΗONS The present patent application is related to the following commonly-owned and commonly- assigned pending patent applications filed on October 28, 1991, November 8, 1991, June 6, 1992, July 16, 1992 and August 18, 1992: Satellite Communication System by Edward Fenton Tuck et al., assigned United States Serial Number 07/783,754; Method of Conducting a Telecommunications Business Implemented on a Computerby Edward Fenton Tuck, assigned United States Serial Number 07/895,295; Terrestrial Antennas for Satellite Communication System by Asu Ram Jha, assigned United States Serial Number 07/790,273; Switching Methods for Satellite Communication System by David Palmer Patterson and Moshe Lerner Liron, assigned United States Serial Number 07/790,805; Beam Compensation Methods for Satellite Communication System by David Palmer Patterson and Mark Alan Sturza, assigned United States Serial Number 07 790,318; Spacecrafi Designs for Satellite Communication System by James R. Stuart et al., assigned United States Serial Number 07/931,625. The specifications of the patent apphcations listed above are hereby incorporated by reference. DESCRIPTION OF THE INVENTION TECHNICAL FIELD The present invention relates to the field of satellite communications. More particularly, this invention provides an advanced, active element, phased array satellite antenna system which provides extremely high gain, but which also uses the available spectrum with great efficiency. The power supplied by the invention enables telephone users on the ground to communicate directly with a constellation of spacecraft in low Earth orbit using a compact, hand-held terminal which does not pose radiation hazards. BACKGROUND ART Existing public phone systems rely primarily on land lines and microwave repeaters to handle call traffic. Recent expansions of cellular networks have enhanced phone service by providing access to the land based system to customers using mobile phones in their vehicles or hand-held portable units. The increased capacity offered to the subscriber is relatively small compared to the number of subscribers using conventional fixed phones, since cellular service is limited to only those geographical regions that are densely populated. Cellular communication is often afflicted by poor performance when customers travel from one cell to another, or when they traverse the radio shadows projected by terrain or buildings. One previous attempt to bypass the limits of conventional communications networks utilizes a transportable telephone that employs a satellite dish several feet in diameter to communicate directly with satellites in 22,300 mile geostationary orbits. The transponders on board these satellites then connect the caller directly to the land-based system, which directs their call through switches on the ground. These devices are heavy, difficult to transport and are prohibitively expensive. Public phone companies do not currently offer continuous world-wide service to subscribers using a mobile or portable phone without the use of costly and large antenna systems. Commercial spacecraft and transponders that are presently on orbit do not generally possess the power capacity to communicate directly with terminals that are not coupled to an antenna dish that are at least a few feet in diameter. The service which is available is extremely limited and too expensive for use by all but a few. The problem of providing an economically viable network for voice, data and video which can be used by subscribers all over the world has presented a major challenge to the communications business. The development of a high power satellite system which can transmit and receive radio signals to portable, mobile and fixed terminals on the land and sea and in the air without the intermediate steps of routing traffic through land-based equipment would constitute a major technological advance and would satisfy a long felt need within the electronics and telephone industries. DISCLOSURE OF INVENΗON The Spacecraft Antennas & Beam Steering Methods for Satellite Communication System comprises an advanced active element phased array antenna. The present invention utilizes electronic beam steering to provide extremely high gain signals. By incorporating these novel antenna systems on a constellation of low Earth orbit spacecraft, phone customers across the globe will be able communicate through a communication system whose switching intelligence resides on orbit. This unique configuration bypasses traditional land-based networks, and offers a revolutionary expansion of communications potential. The present invention is a vital element of a novel Satellite Communication System, which is referred to above. The innovative design of one of the preferred embodiments employs a hemispherical configuration of hexagonal antenna facets fabricated from ultra-light weight honeycomb materials and advanced composites. Gallium-arsenide (GaAs) millimeter wave integrated circuits (MMIC) coupled to each antenna panel handle call traffic. Each antenna simultaneously generates 256 beams which are electronically steered to 4,096 positions on the surface of the Earth. Each individual beam illuminates a region on the ground that measures roughly twenty kilometers by twenty kilometers. An appreciation of other aims and objectives of the present invention and a more complete and comprehensive understanding of this invention may be achieved by studying the following description of a preferred embodiment and by referring to the accompanying drawings. BRIEF DESCRIPΗON OF THE DRAWINGS Figure 1 is perspective view of a satellite that includes a hemispherical array of hexagonal antenna facets and fully extended rectangular solar panels. Figure 2 depicts a schematic diagram of the satellite similar to the one illustrated in Figure 1. Figure 2 also reveals three sets of electronically steered beams produced by the hexagonal antennas and the circular and elliptical footprints which the beams illuminate on the Earth's surface. Figure 3 presents a schematic depiction of the pattern of multiple beams generated by the satellite shown in Figures 1 and 2. Figures 4 and 5 are plots that reveal the geometric relationship of several spacecraft traveling in one of the many orbital planes in the satellite constellation. The pathways between neighboring sateUites that are not occluded by the Umb of the Earth provide communication Unks between spacecraft in the same orbit. Figure 6 reveals a schematic diagram of a GaAs MMIC time delay network. Figure 7 shows a schematic of the active lens, which includes a large number of the time delay networks shown in Figure 6. Figure 8 is a schematic iUustration of an active lens which incorporates a time delay steered antenna array. BEST MODE FOR CARRYING OUT THE INVENΗON Figure 1 depicts one of the preferred embodiments of the antennas. This perspective schematic view shows a sateUite S that includes an array 10 of generaUy hexagonal antenna Earth- facing facets 12 that are mated together along their six-sided boundaries to form a sUghtry flattened, hemispherical sheU. A space-facing array 16 that includes facets 18 is mated to the Earth facing array 10. The antenna sheU is connected to two generaUy rectilinear, unfurled, solar panels 14 which trail the body of the spacecraft S. Figure 2 depicts a schematic diagram of a similar satellite S, and also reveals three sets of electronically steered beams 19 produced by the hexagonal antennas 12 and the circular and eUiptical footprints 20 which the beams 19 Qluminate on the Earth's surface. The footprints 20 of the radio beams 19 are shown as regions of "fllumination" on various portions of the Earth's surface E. These beams provide communications services to subscribers using portable (P), mobfle (M) and fixed (F) terminals and gateways (G). The set of beams marked 19a travel the shortest possible distance from the spacecraft S to the Earth E because these beams 19a travel along a pathway which runs from the ground to the zenith Z and back. The area on the surface illuminated by this set of beams 19a results in a generally circular footprint 20a. Other sets of beams, like those marked 19b and 19c, are more inclined to the line that runs from the center of the Earth toward the zenith Z, and the areas 20b and 20c irradiated by these beams 19b and 19c become progressively more elliptical as the angle of inclination becomes larger. Figure 3 combines many sets of beams and portrays a complete set of line-of-sight radio waves 22 generated by one spacecraft. Figures 4 and 5 are geometric plots 24 and 26 which include sight lines between neighboring satellites that travel along the same orbit. These plots 24 and 26 reveal the geometric relationship of several spacecraft S traveling in one of the many orbital planes in the sateUite consteUation. The pathways between neighboring sateUites that are not occluded by the limb of the Earth provide communication links between spacecraft S in the same orbit. In one of the preferred embodiments of the invention, the sateUites shown in Figures 1 and 2 operate in a consteUation which includes 29 sets of spacecraft flying in 29 orbits. The entire fleet travels around the Earth at a height of 700 km (435 miles). In this embodiment, the antenna facets or surfaces 12 are designed to transmit and receive signals from terrestrial units that are located within the footprints 20 produced by the electronically steered beams 19. Onty those terrestrial units that are within the conical line-of-sight region that is defined by a minimum elevation angle, or "mask angle," of 40 degrees can be serviced by a particular spacecraft. The hexagonal antenna facets 12 and their related signal processing circuitry produce a hexagonal coverage pattern. In one embodiment of this invention, the radius to the center of each of the six sides of each facet 12 is 6.2 degrees, whUe the radius to the six corners of the hexagon subtends 7.16 degrees. A spacing of 12.41 degrees aUows for 29 hexagonal coverage patterns in each orbital plane. A similar spacing along the equator results in 29 orbital planes. This configuration of hexagonal facets 12 offers double coverage in the equatorial regions and up to eight-fold coverage at higher latitudes, where larger numbers of subscribers are located. By selecting an odd number of sateUites and planes, the center of the descending patterns wiU faU on the seams of the ascending patterns. This selection insures that virtuaUy every region on the surface between the latitudes of 70 degrees North and South wiU be serviced by the consteUation. In general, and aUowing for the somewhat inaccurate assumption that the Earth is spherical, the coverage angle of each sateUite is given by the expression: 2 a =2arcsin(^) r+h where a is the half angle of the cone of Earth coverage in radians; θ is the user antenna mask angle in radians; r is the radius of the Earth (6378 km); and d is the height of the orbit (700 km). Orbits of 700 km and a 40 degree user antenna mask angle yield a coverage of 87.3 degrees. The slant range at the edge of the Earth coverage cone is determined by the equation: d = ((r +Λ) 2 -r 2 )coβ 2 θ) -rsinθ =1022J n The Earth coverage area of the cone is: A =ιt(d 2 +h--2dhcos(a)) = l,568,000i n - This quantity represents the Earth coverage area of each sateUite if the entire circular footprint is utilized. As described above in the copending patent application that describes Beam Compensation Methods, this area is divided into 256 superceUs and each superceU is further divided into 16 smaUer individual cells. The total number of ceUs created by each spacecraft is then 256 x 16, or 4,096. Each of these 4,096 cells has an area of 383 km 2 . If each ceU is square, they measure approximately 19.6 km on a side. Although the preferred embodiment of the invention utilizes circular footprints 20, the footprints created by the sateUites need not be circular. Any regular polygon inscribed in the circle may be effectively employed. Other alternative embodiments employ inscribed squares and inscribed hexagons. The area of the square is 63.7% of the total area, while the area of the hexagon is 82.7% of the total area. If the ceU size is maintained constant, then the resulting numbers of ceUs are 2,609 for the square and 3,387 for the hexagon. The spaceborne antenna facets or surfaces 12 are capable of providing a gain of 45 dB at the periphery of each footprint and 42 dB at the nadir position. Because the beams generated by the spaceborne antenna facets 12 are so powerful, Earth-based terminals can incorporate low power antenna designs which substantially eliminate any radiation hazards that might otherwise harm the user. Each antenna uses a combination of the 20 and 30 Ghz frequency bands for sateUite to ground communications, and propagates 256 simultaneous beams, which are multiplexed to 4,096 positions. Beams aimed at the horizon possess an eUiptical, as opposed to a circular or polygonal, shape to compensate for the low grazing angle, so that a constant Earth coverage footprint is maintained. Uncorrected beams have an eUiptical ground pattern which degrades spectral reuse efficiency. Electronic beam steering also permits the independent control of directivity gain and power gain. The beam steering provides a convenient method of correcting power levels during rain fades. The transmitted power gain from the sateUite can be increased on transmit to overcome downlink fading. SateUite receive power gain can be increased during receive to overcome uplink fading. The use of these two techniques overcomes possibly poor communication performance during rainy weather conditions. Signal processing components residing in the spacecraft include GaAs MMIC filters and are responsible for electronicalty steering active antenna arrays on board each sateUite. Figure 6 reveals a schematic diagram of a GaAs MMIC time delay network 28. Figure 7 shows a schematic of the active lens 30, which includes a large number of the time delay networks 28 coupled to radiating elements 32. In the preferred embodiment of the present invention, a circuit Model No. TD101 produced by Pacific MonoHthics, Inc. in California is employed as the time delay network. Other more conventional time delay networks may also be employed. The electronic steering is accomplished by using these time delay networks 28 to create an active lens 30. The focal point of the lens 30 is related to the directivity gain of the antenna facet 12 and can be controlled electronically. The ability to control the directivity gain is important for communications satellites in low Earth orbit because less gain is needed when a cell is addressed at the sateUite Nadir than when a cett is addressed at the periphery of the sateUite footprint 20. It is also desirable to increase the directivity gain in the elevation plane when addressing a ceU at the satellite footprint periphery. The active lens 30 incorporated in the antenna facets 12 aUows these variable directivity gains to be implemented without the reduction in efficiency that is associated with conventional antenna arrays. The active lens 30 Ulustrated in Figure 7 is the microwave analog of an optical lens. By increasing the time delay for the signal paths in the center of the lens with respect to the edge of the lens, the focal length of the lens can be changed electronically, which, in turn, changes the directivity gain of the antenna facets 12. The antenna facets 12 provide electronic steering which is sufficiently accurate to implement a practical gain variation in the 42 dB to 45 dB regime. For example, changing the radius of a radiation pattern by 200 meters at a range of 1200 kilometers requires a time delay control of 4 picoseconds for a 45 dB gain antenna array with dimensions of 1.2 meters on a side. Active lens control for the 42 to 45 dB range (in a 20/30 GHz system) requires time delays on the order of 4 picoseconds to 35 picoseconds. The active lens 30 can be constructed using one of two techniques. The first, which is depicted in Figure 7, utilizes a conventional lens that includes many pairs of receive and transmit antennas that are each connected in series with an active time delay network. The second technique, which comprises the preferred embodiment of the invention, is a time delay circuit 34 exhibited in Figure 8. This circuit 34 includes a feed 36 coupled to a time delay steered array 37 which comprises a series of switches 38, time delay paths 40, transmission lines 42 and amplifiers 44. The time delay steered array 37 is connected to the time delay active lens 30 and to radiating elements 32. The switched time delay networks 28 in the corporate feed accomplish beam steering functions. The time delay networks 28 can be adjusted for either fine gain beam steering (a few degrees) or for changing the directivity gain of the antenna (focal length of the lens). Every sateUite S controls the assignment of channels to terminals requesting services. When a terminal has more than one sateUite in view, the sateUites monitor the signal quality and select which one is best suited to handle the caU to the terminal. The receive beam from the ground terminal lags the transmit beam emitted from the sateUite by a fixed interval. The terminal transmits its data to the sateUite at a delay specified by the sateUite in its preceding scan. This method is used to compensate for delay differences caused by variations in path lengths. The scan pattern among beams is coordinated to insure that aU cells being scanned at one instant are separated by sufficient distance to eliminate interference among many closely-spaced customers. An electronic pushbroom carries the beams through one beam position in the direction of sateUite travel, and then performs a flyback. Each beam carries a pUot tone which identifies each beam for terrestrial terminals. Components on board each sateUite measure time delay and Doppler shift of each subscriber signal to determine the location of the subscriber within a particular beam footprint. Because the sateUite antennas operate at a relatively high gain, the footprints on the ground are relatively smaU. Since the cells are smaU and the sateUite footprint moves rapidly over the Earth's surface, any particular terminal remains in the same ceU for onty a few seconds. To avoid the rapid handoff from sateUite to satellite every few seconds, the innovative logical/physical cell mapping scheme described in the copending patent application on Beam Compensation is utilized in conjunction with the present invention. Several spacecraft in a single orbital plane can communicate with each other if they are located above the horizon of the Earth. Satellites communicate among one another using a 60 Ghz inter-satellite frequency band. In one of the preferred embodiments, a 1.5 foot antenna provides approximately 45 Db of gain which supports a practical inter-sateHite link (ISL). Four fixed and two electronicalty steerable antennas are used on each sateUite for ISL links. Optional links in the orbital plane may increase the number of ISL antennas to ten, eight of which would be fixed and two of which would be steerable. A second preferred embodiment comprises sateUites circling in 21 orbital planes with 40 sateUites S in each orbit. This 21 x 40 embodiment can be implemented using the same antenna facets 12 which may be modified to account for the increased population of the consteUation. CONCLUSION Although the present invention has been described in detail with reference to a particular preferred embodiment, persons possessing ordinary skiU in the art to which this invention pertains wfl appreciate that various modifications and enhancements may be made without departing from the spirit and scope of the claims that foUow. The various orbital parameters and sateUite population and configuration statistics that have been disclosed above are intended to educate the reader about one preferred embodiment, and are not intended to constrain the limits of the invention or the scope of the claims. The List of Reference Characters which foUows is intended to provide the reader with a convenient means of identifying elements of the invention in the specification and drawings. This list is not intended to delineate or narrow the scope of the claims. INDUSTRIAL APPLICABILITY The Spacecraft Antennas and Beam Steering Methods for SateUite Communication System described above wfll help to overcome the limits that circumscribe the performance and potential of existing telephone systems. The present invention is capable of offering continuous voice, data and video service to customers across the globe on the land, on the sea, or in the air. Instead of merety improving upon or expanding existmg land-based systems, the present invention bypasses centralized terrestrial switching hardware by placing aU the intelligence of the network in orbit. Unlike conventional hierarchical systems, which are linked together by a complex web of wires, cables, glass fibers, and microwave repeaters that are very expensive to build and maintain, the present invention liberates the true communications potential of existing land-based networks by routing signals through spacecraft in low Earth orbit. The present invention wfll revolutionize the telecommunications industry, and offer a wide spectrum of services and industrial opportunities around the world. LIST OF REFERENCE CHARACTERS 10 Earth-facing antenna array 12 Hexagonal antenna surfaces 14 Solar panels 16 Space facing array 8 Space-facing facets 9 Electronicalty steered beams 0 Footprints 2 Line-of-sight radio waves 4&26 Geometric plots 8 GaAs MMIC time delay network 0 Time delay active lens 2 Radiating elements

Claims: CLAIMS What is claimed is: 1. An apparatus traveling in Earth orbit for communicating directly with a pluraUty of portable (P), mobile (M), fixed (F) terminals, gateways (G) and sateUites (S) comprising: a pluraUty of antenna surfaces (10); said antenna surfaces (10) being coupled and arranged in a generaUy contiguous pattern; each of said pluraUty of antenna surfaces (10) being capable generating a pluraUty of radiated beams (19) which are electronicalty steered to footprint regions (20) on the surface of the Earth (E); each of said pluraUty of antenna surfaces (10) being capable generating a pluraUty of radiated beams (19) using a time delay circuit (34); said time delay circuit (34) including a time delay network (28), said time delay circuit (34) being coupled to each of said pluraUfy of antenna surfaces (10). 2. An apparatus as claimed in Claim 1, in which said pluraUfy of antenna surfaces (10) are substantially hexagonal in shape. 3. An apparatus as claimed in Claim 1, in which said pluraUfy of antenna surfaces (10) are coupled and arranged in a generally contiguous pattern which approximates the contour of a partially oblate hemisphere. 4. An apparatus as claimed in Claim 1, in which said pluraUfy of antenna surfaces (10) are capable of simultaneously generating at least 256 of said pluraUty of radiated beams (19) which are electronically steered to approximately 4,096 positions on the surface of the Earth (E). 5. An apparatus as claimed in Claim 1, in which said pluraUty of radiated beams (19) each iUuminate a footprint (20) on the Earth (E) that measures approximately 20 kUometers by 20 kilometers. 6. An apparatus as claimed in Claim 1, in which said plurality of radiated beams (19) are generated at a gain of at least 40 dB. 7. An apparatus as claimed in Claim 1, in which said pluraUfy of antenna surfaces (10) are each capable of emitting and receiving said pluraUfy of radiated beams (19) over a cone measuring at least 25 degrees measured from each of said pluraUfy of antenna surfaces (10). 8. An apparatus as claimed in Claim 1, in which said pluraUfy of antenna surfaces (10) includes at least 14 surfaces. 9. An apparatus as claimed in Claim 1, in which said time delay circuit (34) includes a pluraUty of GaUium Arsenide MMIC time delay networks (28). 10. An apparatus for providing a pluraUty of radiated beams (19) directed toward the Earth's surface; said apparatus being capable of communicating directty with a pluraUty of portable (P), mobUe (M), and fixed (F) terminals, gateways (G) and sateUites (S) comprising: a pluraUty of substantiaUy hexagonal radiating facets (12); said substantiaUy hexagonal radiating facets (12) being coupled and arranged in a generaUy contiguous pattern which approximates the contour of a partially oblate hemisphere; each of said pluraUty of substantiaUy hexagonal radiating facets (12) being capable of simultaneously generating at least 256 of said pluraUty of radiated beams (19) which are electronicalty steered to approximately 4,096 positions on the surface of the Earth (E); each of said pluraUty of radiated beams (19) Uluminating a footprint (20) on the Earth that measures approximately 20 kilometers by 20 kilometers at a gain of at least 40 dB; each of said pluraUfy of substantialty hexagonal radiating facets (12) being capable of emitting and receiving said pluraUfy of radiated beams (19) over a cone measuring at least 25 degrees measured from each of said pluraUty of substantiaUy hexagonal radiating facets (12); said pluraUty of substantialty hexagonal radiating facets (12) including at least fourteen facets (12); and a time delay circuit (34); said time delay circuit (34) including a GaAs MMIC time delay network (28), said time delay circuit (34) being coupled to each of said pluraUty of substantialty hexagonal radiating facets (12); each of said pluraUty of substantialty hexagonal radiating facets (12) including a pluraUty of matched pairs of surfaces for separatety transmitting and receiving each of said pluraUty of radiated beams (19).

Inventors: LOCKIE DOUGLAS GENE, LOCKIE, DOUGLAS, GENE
Applicants: CALLING COMMUNICATIONS CORP, CALLING COMMUNICATIONS CORPORATION
Application year: 1992
Main classification: H01Q1
IPC codes: B64G1, H01Q1, H01Q25, H04B7