METHODS AND APPARATUS FOR AUGMENTING SATELLITE BROADCAST SYSTEM

Abstract: The present invention allows for reception of programming from both satellites (11) and local sources (L) using a single receiving antenna (32). Beams (18) emanating from a geosynchronous satellite (11) are collected using the main lobe (36) of a home receiving antenna (32), while a rebroadcast signal (26) generated by an airplane (20) circling above the home (H) is simultaneously sensed using a side lobe (38) of the receiving antenna (32).

Description: Methods & Apparatus for Augmenting Satellite Broadcast System DESCRIPTION OF THE INVENTION TECHNICAL FIELD The present invention relates to the field of satellite broadcast systems. More particularly, this invention comprises methods and apparatus for receiving direct satellite broadcasts and local programming delivered by an airborne platform using a single receiving antenna. BACKGROUND ART A growing portion of the television programming that is viewed by Americans is broadcast directly to home receivers by geosynchronous satellites. These satellites operate in orbits positioned above the Earth's Equator at an altitude of approximately 22,300 miles. Some consumers use relatively large satellite dishes that may be ten or more feet in diameter to receive television programming directly from satellites such as the Galaxy™ and Telstar™ series of spacecraft. In the past year, receivers that employ much smaller antennas that are only about two feet across have been introduced in the United States. These newer and smaller systems obtain signals from powerful new satellites operated by DirecTV™ and USSB™. One unfortunate consequence of relying on direct broadcast systems is that they rarely, if ever, provide programming from local stations. One possible solution to this problem would be to use high-altitude airplanes to rebroadcast local television stations in the same frequency band used for direct satellite television broadcasting. The satellites that supply direct broadcast signals move in orbits that are synchronized with the rotation of the Earth. A given geosynchronous satellite therefore appears to be in almost exactly the same elevation and azimuth for all viewers in even a large metropolitan area. In contrast, because the airplane is at a much lower altitude than the geosynchronous satellites used for television broadcasting, it cannot be at the same angle for all viewers. The problem with this approach is that two different antennas would then be required— one for signals emanating from the satellite, and a second oriented to the airplane's position for signals emitted from the aircraft. The viewer would not only be faced with the higher cost of purchasing two different antennas, but would also suffer the inconvenience of having to constantly switch between the two antennas each time he or she wishes to change channels that are not supplied solely by either the satellite or the aircraft. Other previous attempts to offer broadcast services from a variety of platforms have been met with mixed results. A number of systems are described in the U.S. Patents cited below. U.S. Patent No. 4,392,139, issued to Aoyama et al. in 1983, discloses an omni-directional VHF television antenna system for an aircraft. U.S. Patent No. 4,218,702, issued to Brocard et al. in 1980, describes a means for remote control of an aircraft video system for surveying ground activity. U.S. Patent No. 3,972,045, issued to Perret in 1976, pertains to an apparatus for transporting and entertaining passengers aboard an aircraft with a television system. U.S. Patent No. 3,778,007, issued to Kearney, II et al. in 1973, concerns a rod television-guided drone to perform reconnaissance and ordnance delivery. U.S. Patent No. 3,406,401, issued to Tillotson in 1968, discloses a synchronous satellite communication system for communicating simultaneously with a number of ground stations. U.S. Patent No. 2,748,266, issued to Boyd in 1956, describes a radiant energy relay system having mobile relay signaling stations moving in continuously progressing succession. U.S. Patent No. 2,626,348, issued to Nobles in 1953, relates to radio systems employing equipment mounted on aircraft for re-transmitting or relaying programs. U.S. Patent No. 2,598,064, issued to Lindenblad in 1952, discloses the transmission of radio signals between remote points. U.S. Patent No. 2,509,218, issued to Deloraine in 1950, pertains to a radio multi-channel communicating system adapted for association with predetermined routes. U.S. Patent No.4,253,190, issued to Csonka in 1981, describes a communications system using a mirror kept in outer space by electromagnetic radiation pressure. U.S. Patent No. 5,133,081, issued to Mayo in 1992, discloses a remotely controllable message broadcast system including central programming station, remote message transmitters and repeaters. U.S. Patent No. 3,378,837, issued to Graves in 1963, relates to a satellite synchronized precision timing system having an accuracy of a nanosecond for use in a tracking and guidance system capable of tracking space vehicles from a plurality of remote worldwide tracking stations. This problem of designing a system which provides programming from both satellites and local sources without utilizing two different antennas has presented a major challenge to the satellite business. The development of a home receiver that is capable of supplying both local and satellite signals but which is also relatively inexpensive and easy to use would constitute a major technological advance and would satisfy a long felt need within the television and communications industries. DISCLOSURE OF THE INVENTION The present invention is a system which provides programming from both satellites and local sources using a single antenna. According to a first aspect of the present invention, there is provided a radio communications system comprising a terrestrial receiver and/or transmitter located a the Earth's surface having a directional antenna with a main lobe and side lobes, and being in communication with a first transmitter and/or receiver and a second transmitter and/or receiver, characterized in that the first transmitter and/or receiver is on a substantially geosynchronous satellite located within said main lobe and the second transmitter and/or receiver is on an airborne platform arranged to be located within one of said side lobes. The references to receivers and transmitters incorporate devices relating reception and transmission signals. According to a second aspect of the present invention, there is provided a method of operating a radio communication system wherein a terrestrial receiver and/or transmitter located a the Earth's surface and having a directional antenna with a main lobe and side lobes is in communication with a first transmitter and/or receiver and a second transmitter and/or receiver, characterized in that said main lobe is directed at a substantially geosynchronous satellite having said first transmitter and/or receiver, and at least one of said side lobes is directed at an airborne platform having said second transmitter and/or receiver. A plurality of airborne platforms may be provided to receive and/or transmit different signals, the platforms being arranged in the same or different side lobes of the directional antenna. An airborne platform is positioned off-axis to the receiving antennas so as to transmit signals into the antennas' sidelobes. The invention allows immediate and inexpensive enhancement to existing geostationary broadcast services. In a preferred embodiment, beams emanating from a geosynchronous satellite are collected using the main lobe of a home receiving antenna, while a rebroadcast signal generated by an aiφlane circling above the home is simultaneously sensed using a side lobe of the receiving antenna. The aiφlane flies along a path which is a closed loop so that it is always positioned in a region where the aircraft antenna can supply signals to the receiving terminal using the side lobe. The present invention may be implemented using any form of airborne platform, whether it is manned or unmanned. This approach offers a convenience to the viewer, in that he or she does not need to disconnect his television receiver from the satellite receiver and connect it to a local antenna or cable system to receive local news and other local programming. If the airborne broadcast is provided by the satellite broadcast entity, the service provided would be indistinguishable from terrestrial cable service, except possibly for higher quality. The subscriber might also be able to avoid the additional cost of local terrestrial cable service, if his or her primary reception were poor. 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 DESCRIPTION OF THE DRA WINGS Figure 1 is a schematic diagram of geosynchronous satellites in Earth orbit. Figure 2 is a schematic diagram that illustrates a geosynchronous satellite transmitting signals to a receiving antenna mounted on the roof-top of a home. Figure 3 A is a schematic diagram which reveals the preferred embodiment of the present invention. The same receiving antenna shown in Figure 2 is used to receive both direct satellite broadcasts and signals transmitted from a local airborne platform. Figures 3B and 3C are schematic illustrations which show the relationships among the satellite, the airborne platform and receiving antennas. For the sake of simplicity of the drawing, the satellite and the airborne platform are displayed close together on the same page, even though they are actually located at vastly disparate altitudes. These two schematic figures are intended to reveal the basic geometry of the main and side lobes of receiving antennas as they relate to the airborne platform and the satellite. Figures 3D, 3E and 3F present cross-sections of the main and side lobes of a receiving antenna at the altitude of the airborne platform. Figure 4 is a graph which plots antenna elevation pointing angle versus the geographical latitude of the receiving antenna. Figures 5 and 6 are schematic, unsealed drawings which depict geometrical relationships among a direct broadcast satellite, a local airborne platform and a receiving antenna on the Earth's surface. Figure 7 supplies a view of a receiving antenna pattern, and includes a depiction of both the main and side lobes of the antenna. Figures 8 A and 8B illustrate the geometry of the projection of the upper portion of the side lobe which lies in the plane of the altitude of the airborne platform. Figure 9A is a schematic view of a satellite that may be employed to practice the present invention. Figure 9B presents a schematic block diagram of a satellite-borne television transponder. Figure 10A is a schematic view of an aircraft that may be utilized to implement the present invention. Figure 1 OB is a schematic block diagram of an aircraft-borne television transponder. Figure 1 1 shows the aircraft depicted in Figure 10 flying in a generally circular flight path. Figure 12 is a schematic view of a direct broadcast satellite terminal, which includes a receiver and an antenna. Figure 13 is a perspective view of a receiving antenna. BEST MODE FOR CARRYING OUT THE INVENTION Geosynchronous Direct Broadcast Systems Figure 1 furnishes a schematic view 10 of satellites 1 1 operating in geosynchronous orbit 12 above the Earth E. Each satellite 11 travels along an orbit 12 which is positioned above the Equator, and emits signals that form a footprint F on the surface of the Earth. Figure 1 is not drawn to scale. For the sake of simplicity, none of the figures which accompany this Specification that portray the relative locations of satellites or aircraft are drawn to scale. Figure 2 is a schematic illustration 13 of a satellite 11 that includes a transponder 14 and antennas 16. Satellite beams of radiation 18 are emitted from the antennas 16 down to a home H and provide television programming to a terminal 28 which includes a receiver 30 and a paraboloidal reflector antenna 32. A Preferred Embodiment of the Invention Figure 3A is a third schematic view 33 that portrays a preferred embodiment of the present invention. An aircraft 20 flying over a home H is employed to rebroadcast local programming to a terminal 28 inside the home using the same receiver antenna 32 that is already utilized to acquire signals 18 from the satellite 1 1. In the preferred embodiment of the invention, the manned aircraft 20 includes a transponder 22 and antennas 24U & 24D which relay signals 26 to consumers. Like all antennas, the paraboloidal reflector antenna 32 has a "main lobe" in which almost all of the radio- frequency energy received or sent by the antenna is contained. This main lobe 36 is generally from one to a few degrees in diameter, is approximately circular in cross-section and is on or near the central axis 34 of the reflector antenna 32. As is also the case with all other antennas, the receiver antenna 32 has a series of unwanted responses, called "side lobes". These side lobes 38 are annular in cross-section, are centered roughly on the main lobe 36 and are separated from the main lobe 36 by angles that depend on the design of the antenna. There are several of these side lobes 38. In antennas used for receiving, the strongest response is in the side lobe nearest the main lobe (the "first side lobe"), and successively weaker responses occur in side lobes that are more widely separated from the main lobe. In a typical parabolic or paraboloidal-reflector antenna, the first side lobe is located at an angle to the main lobe of about four to six degrees, and its response is of the order of 20 to 30 decibels less than the main lobe. Figure 3B is a schematic drawing which shows a satellite 1 1 operating in a conical region of space that corresponds to the main lobe 36 of a receiving antenna 32. A rebroadcast signal 26 emitted by the aircraft is simultaneously sensed by the receiver antenna 32 using a side lobe, which is shown as a region of annular cross- section, labeled "38", coaxial to the main lobe 36. The response of the antenna to signals originating in the region of the annular cross-section between main lobe 36 and side lobe 38 is very slight. The aircraft 20 flies along a path 40 such as a circle or a closed loop within the region of annular cross-section that defines the side lobe 38. In the preferred embodiment, the path 40 is a "racetrack" pattern. The aircraft 20 is always positioned in the region of annular cross-section where the aircraft downlink antenna 24D can supply signals to the terminal 28 using the side lobe 38. The present invention may be implemented using any form of airborne platform 20, whether it is manned or unmanned. Figure 3C is similar to Figure 3B, but reveals how the aircraft 20 flies in an "overlap" region that occupies a zone which corresponds to the intersected spaces of the side lobes 38 of more than one receiving antenna 32. In the preferred embodiment of the invention, the aiφlane 20 is positioned over a densely populated area so that it can provide signals to many receiving antennas 32. Figures 3D, 3E and 3F depict cross-sections of the main and side lobes 36 and 38 of the receiving antenna 32 at the altitude of the circling aircraft 20. Figure 3D is a picture of a single antenna pattern. The circular cross- section of the main lobe 36 is situated at the center of this single antenna pattern, while the annular cross-section of the side lobe 38 is located at the periphery of the pattern. Figure 3E supplies an illustration of three superimposed overlapping antenna patterns like the single pattern shown in Figure 3D. The two patterns shown in dashed lines in Figure 3E are slightly offset from the center pattern along an East-to-West axis. Figure 3F is similar to Figure 3E, but adds two more antenna patterns that are offset from the center pattern along the North-to-South axis. Figures 3E and 3F are intended to demonstrate how the side lobes 38 of a number of receiving antennas 32 form an overlapping region or zone in the atmosphere. This overlapping region is the space where the aircraft 20 flies its closed loop pattern 40, as indicated in Figure 3F. Geometrical Relationships Among Satellites. Aircraft & the Receiver Antenna Since the geosynchronous satellites 11 are of necessity directly above the Equator, and all receiving antennas 32 of terminals 28 which are intended to receive signals from a geosynchronous satellite must point their main lobes 36 at the satellite 11, it follows that all antennas aimed at a geosynchronous satellite must point their main lobes 36 upward at an angle θ which depends on the latitude L of the antenna 32. The main lobes 36 must also be pointed sideward an angle to the local meridian determined by the position of the satellite in its Equatorial orbit, which position is regulated by Government authorities, and which must remain fixed with respect to the Earth's surface. The latitude L(θ) of a particular elevation angle (θ) of the antenna is determined from the expression presented by Equation One: Z,(θ)=(arccos(0.1510 *cos(θ)))-Θ Equat i on 1 where θ is in degrees. Figure 4 presents a graph 42 which plots the antenna elevation pointing angle θ versus latitude L(θ). As an example, the United States of America lies between approximately 24 degrees north latitude and 48 degrees north latitude, resulting in antenna elevation angles of about 36 degrees, in the north of Maine, to about 63 degrees in South Texas. The aiφlane 20 can be flown in an area that is sufficiently distant from metropolitan areas, and at an appropriate azimuth and elevation from the main beams of the receivers in that metropolitan area, to intersect the first side lobes 38 of most of the receiver antennas 32 in the metropolitan area. The minimum horizontal distance from the aiφlane 20 to the receiver antenna 32 is given by the expression: D*h = a*cot(θ + α) Equation 2 where a is the altitude of the aiφlane. In a preferred embodiment of the invention, the aiφlane 20 flies at 50,000 feet above the surface, and its average horizontal distance from the receiving antennas 32 will range from 12 miles in Maine to 5.4 miles in South Texas. In this embodiment, the "top" of the first sidelobe 38 is utilized. The aircraft 20 may be flown in a region that is sufficiently distant from a metropolitan area, and at an appropriate azimuth from the main lobes 36 of the receiver antennas 32 in that metropolitan area, to intersect the first side lobes 38 of most of the receiving antennas 32 in the metropolitan area. The free-space attenuation of the received signal is proportional to the square of the path length. The slant range to a geostationary satellite varies with latitude, but is generally about 24,000 miles. Even if the aiφlane is as far as fifty miles from a receiver, the received signal from the aiφlane is 10 log (25,000/50) = 27 decibels stronger, other things being equal. This level of signal strength more than makes up for the lower sensitivity of the receiver antenna 32 at the side lobe angle. Figure 5 exhibits the geometrical relationships between a satellite 1 1 and a receiving antenna 32. The constants and variables depicted in Figure 5 are specified below: r e = Earth's radius = 6378 kilometers h (geosynchronous) = 35860 kilometers h a = Aiφlane's altitude = 50,000 feet (15.24 km) β = First sidelobe offset : 4.5 degrees δ = Beamwidth = 3 degrees = Aiφlane's or satellite's lookdown angle d s = Slant range D = Surface distance from nadir λ = Latitude difference θ = Look angle For a geosynchronous satellite, the slant range d s and elevation (look angle) θ as seen from the subscriber's antenna varies with the subscriber's latitude as follows: From the law of cosines: Equation 3 ,2 2 d s =r a + (r a + hy-2r a (r a + )cosλ From the law of sines: Equation 4 θ =arccos( -(sinλ) *(h+r e )/dj For latitudes ranging from thirty to fifty degrees, Equation 4 produces the values presented in Table One: Table One Figure 6 depicts the geometrical relationships between the receiving antenna, the aiφlane and the satellite. For an aiφlane at an altitude h a , the slant range d sa and the surface distance D a from the subscriber to the aiφlane may be calculated as follows: Equation 5 =arcsin(r cι *sin(b+Q+90y(h a +r ι ) Equation 6 λ = 180-(α+β+θ+90) Equation 7 Z) =π *r *λ/180, approximately h a /tan(θ÷β) Table Two presents the appropriate values of α, λ, d sa and D a for the case when the aiφlane 20 is centered in the top of the first side lobe 38: Table Two Equations 8 and 9 are utilized to determine if the first side lobe 38 is large enough at the aiφlane's slant range so that the aiφlane can maneuver, and to ensure that the first side lobes 38 of receiving antennas 32 situated across a city can "see" the aiφlane. The height h sl and width w sh of the first side lobe are illustrated in Figure 7. The height h s , and width w sh of the first side lobe at a distance d sa are given by: Equation 8 h =d^ *tan(δ) Equation 9 w =2 *{(2h *d α -h 2 The values for h., and w„. are shown in Table Three: Table Three Figures 8A and 8B illustrate the geometry of the projection of the receiving antenna side lobe 38 at the position of the aiφlane 20. The length and width of the area "seen" by the first sidelobe at the aiφlane's altitude must be calculated to determine whether the aiφlane 20 can stay within the sidelobe 38. The length £ of the projection of the sidelobe on the plane of the aiφlane's altitude is: Equation 10 £=(A fl sin(θ+β-(δ/2))-(A fl sin(θ+β+(δ 2)) and the width is: Equation 1 1 W=w sι *hjsm(β +β-(δ/2))ld xι Equations 10 and 1 1 may be used to generate the values contained in Table Four: Table Four If the city being served has a radius of R c , the first sidelobes of subscribers at the edges of the city will be displaced from the center of the average volume "seen" by all sidelobes by the amount of their distance from the center of the city. The slight difference in pointing angle toward the very distant geosynchronous satellite 11 is negligible (a maximum of 0.0066 degrees at the altitudes considered here). This will constrain the aiφlane 20 to fly a rather tight racetrack pattern 40 to stay in the optimum serving area. The best position for the aiφlane 20 is as high as possible, and if the city is not circular but linear in shape (as is the case for many cities, especially coastal cities), the long axis of the racetrack pattern 40 should be on a line peφendicular to the long axis of the city. The turning radius of an aiφlane is determined by its speed and its angle of bank. A maximum angle of bank is about 60 degrees; this is a "two-gravity" turn, which results in a 360 degree turn in one minute. The speed of the aiφlane is ideally its maximum-endurance speed, about 1.2 times its stalling speed. Stalling speed, in turn, varies with weight, and decreases as fuel is burned. Stalling speed also varies considerably with the density of the air, which is a function of altitude and temperature. The temperature in the stratosphere is relatively constant at -55 degrees Celsius. A "Standard Atmosphere" temperature of T a = 217 degrees Kelvin and a sea-level stalling speed V s of 50 knots (92.6 km/hr) are employed to determine the turning radius. Because of Government Air Traffic Control regulations, the aiφlane will fly at a constant pressure altitude regardless of its geometric altitude; the density altitude is thus a function only of temperature. The Standard Atmosphere uses a seal-level temperature of 1 degrees Celsius. Other values that are utilized to calculate the turning radius are presented in Table Five. Table Five The true airspeed (TAS) is calculated in steps, as follows: Pressure ratio = R p = (((518.67-3.566* 10 "3 *h a )/518.56)) 5 R p = 0.109248 Mach number=M = {(5*((l/R p )*((l+0.2(V L /661.5) 2 ) 3 5 -l)+l) 02857 -l)} M = 0.272168 V Lha = 38.96*M* (T a *(C τ ((l/(l+o.2*M 2 ))-l)+l)) V Lha = 155.3 The turning radius is, therefore: (V Lha * 180/T R )/(2*60*60*π)=R τ = 0.21 Nmi., or 0.38 kilometers which is adequate for the objectives of the preferred embodiment, since it is within the service volume specified above. Satellites Utilized in the Preferred Embodiment Figure 9A is a schematic illustration of a geosynchronous satellite 1 1 that may be used to implement the present invention. The satellite includes a transponder 14 and antennas 16D and 16U. Figure 9B offers a schematic block diagram of a satellite-borne television transponder 14. Solar arrays 42 generate electrical power which is fed to power conditioning equipment 44. A terrestrial uplink transmitter 46 feeds video programming 48 to a satellite uplink antenna 16U via uplink transmitter beams 50. Signals from the uplink antenna 16U are processed by a band-pass filter 52, a low noise amplifier 54 and a mixer 56 which is also connected to a local oscillator 58. A second band-pass filter 60 conveys signals from the mixer 56 to a power amplifier 62 and then to a downlink antenna 16D. Satellite beams 18 are collected by receiving antenna 32 and are then processed by receiver 30 and converter 64 before they are finally passed to a television TV. Aircraft Utilized in the Preferred Embodiment Figure 10A presents a schematic view of an aircraft 20 that may be used to practice the preferred embodiment of the present invention. The aiφlane 20 includes a transponder 22 and uplink and downlink antennas 24U & 24D that relay signals from a local ground transmitter L to home receiving antennas 32. The details of the aircraft-borne transponder 22 are revealed in Figure 10B. Local video programming 66 is relayed to an aircraft uplink antenna 24U via a local uplink transmitter L which emits uplink transmitter beams 68. A generator 70, which may be driven by the aircraft's engine, furnishes electrical power to power conditioning equipment 72 aboard the aiφlane 20. Signals from the uplink antenna 24U are delivered to a band-pass filter 74, a low noise amplifier 76 and a mixer 78 that is linked to a local oscillator 80. The output of the mixer 78 is fed to a second band-pass filter 82 and a power amplifier 84 which, in turn, forwards signals to an airborne downlink antenna 24D. Beams 26 from the aiφlane 20 are sensed by receiving antenna 32, which is coupled to receiver 30, converter 64 and television TV. Figure 1 1 shows the aiφlane 20 flying in a generally closed loop pattern 40. Although the preferred embodiment of the invention is implemented using a manned aiφlane, alternative embodiments of the invention may be practiced using a blimp, a dirigible, a helicopter, both free and untethered balloons, aerostats or any other airborne platform that will serve as a reliable source for providing signals to receiver antennas 32. Home Receiving Antennas Figure 12 illustrates a receiving antenna 32 mounted on the rooftop of a home H. A terminal 28 includes a direct broadcast receiver 30 connected to the antenna 32, a converter 64 and a television TV. Figure 13 offers a perspective view of a receiving antenna 32. Various methods may be employed to deliberately enhance the gain of the side lobe 38 of the receiving antenna 32. In a conventional paraboloidal reflector, the antenna surface 35 is carefully contoured to approximate shape of a true paraboloid to maximize the gain of the main lobe 36. In one embodiment of the invention, the antenna surface 35 may be deliberately distorted to augment the gain of the side lobe 38. Another technique which strengthens the sensitivity of the side lobe 38 is to decrease the taper of the radiation emitted by the feedhorn structure 37 so that it illuminates the edges of the reflector 32 more strongly. Another alternative that exaggerates the action of the side lobe 38 is to reduce the size of the receiver antenna 32, or to reduce the radius of the antenna 32 in the direction in which the side lobe 38 is to be enhanced. The side lobe 38 may also be effectively boosted by distorting the shape of the energy radiated from the feedhorn structure 37 so that the reflector 32 is illuminated mor-axis direction. Yet another method of improving side lobe 38 sensitivity is to move the feedhorn structure 37 slightly closer to the reflector relative to its normal position. This alteration defocuses the beam slightly, and makes the first side lobe 38 stronger and the main lobe 36 very slightly weaker. Another alternative method involves forming a small dimple in the feedhorn structure 37 or a by making a small dent in the reflector 32. The present invention may also be implemented using a receiving antenna 32 which is specially built to have an adjustable shaped beam that is specifically suited to detect signals from the aiφlane 20. The present invention exploits an inherent weakness in receiving antennas, and also exploits the fact that antennas manufactured at the time this Patent Application is being filed which are used to receive broadcasts from geosynchronous broadcast satellites using newly-occupied K u -band (about 14 GHz) are of identical design. INDUSTRIAL APPLICABILITY The present invention will provide simultaneous sources of programming from both satellites and local broadcasters using a single antenna. The invention allows immediate and inexpensive enhancement to existing geostationary broadcast services. CONCLUSION Although the present invention has been described in detail with reference to particular preferred and alternative embodiments, persons possessing ordinary skill in the art to which this invention pertains will appreciate that various modifications and enhancements may be made without departing from the spirit and scope of the Claims that follow. The various satellites, aircraft and antennas that have been disclosed above are intended to educate the reader about particular embodiments, and are not intended to constrain the limits of the invention or the scope of the Claims. The List of Reference Characters which follows 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. LIST OF REFERENCE CHARACTERS 10 Schematic diagram of geosynchronous satellites in Earth orbit 1 1 Satellites 12 Earth orbit 13 Schematic diagram showing direct satellite broadcast to home 14 Satellite transponder 16D Satellite downlink antenna 16U Satellite uplink antenna 18 Satellite beams of radiation 20 Airborne platform 22 Airborne platform transponder 24D Airborne platform downlink antenna 4U Airborne platform uplink antenna 6 Airborne platform beams of radiation 8 Terminal 0 Receiver 2 Receiver antenna 33 Schematic diagram showing preferred embodiment of present invention 34 Central axis of antenna 5 Surface of receiver antenna 6 Main antenna lobe 37 Feedhorn structure 38 Side antenna lobe 0 Flight path 42 Solar array 4 Power conditioning equipment 6 Uplink transmitter 48 Video programming 50 Uplink transmitter beams 52 Band-pass filter 54 Low noise amplifier 56 Mixer 58 Local oscillator 60 Band-pass filter 62 Power amplifier 64 Converter 66 Local video programming 68 Local uplink transmitter beams 70 Engine-driven generator 72 Power conditioning equipment 74 Band-pass filter 76 Low noise amplifier 78 Mixer 80 Local oscillator 82 Band-pass filter 84 Power amplifier E Earth F Footprint H Home L Local ground television transmitter

Claims: CLAIMS What is claimed is: 1. A radio communications system comprising a terrestrial receiver and/or transmitter (28) located at the Earth's surface having a directional antenna (32) with a main lobe (36) and side lobes (38), and being in communication with a first transmitter and/or receiver and a second transmitter and/or receiver, characterised in that the first transmitter and/or receiver (14) is on a substantially geosynchronous satellite (11) located within said main lobe and the second transmitter and/or receiver (22) is on an airborne platform (20) arranged to be located within one of said side lobes. 2. A system according to Claim 1, wherein the airborne platform (20) is arranged to move within said side lobe (38). 3. A system according to Claim 2, wherein the airborne platform (20) executes substantially closed loops within said side lobe (38). 4. A system according to Claim 2 or 3, wherein the airborne platform (20) is an aeroplane. 5. A system according to Claim 1, wherein the airborne platform (20) is arranged to be substantially static. 6. A system according to Claim 1, wherein the airborne platform (20) is a blimp, a dirigible, a helicopter, a free balloon, a tethered balloon or an aerostat. 7. A system according to any preceding claim, wherein the airborne platform (20) operates at a height from 15,000 m to 25,000 m. 8. A system according to any preceding claim, wherein the directional antenna (32) comprises a feed structure (37) and a reflector surface (35), said surface being of distorted paraboloidal shape whereby to enhance side lobe gain. 9. A system according to Claim 8, wherein the paraboloidal shape has a reduced radius in the direction of enhancement of side lobe gain. 10. A system according to Claim 8, wherein the reflector surface (35) has a dent therein. 1 1. A system according to any of Claims 1 to 7, wherein the directional antenna (32) comprises a feed structure (37) and a reflector surface (35) of substantially paraboloidal shape, the directional sensitivity of said feed structure (37) being such that it interacts with the edges of the surface (35) more strongly than with a central region thereof or interacts more strongly in an off-axis direction, whereby to enhance side lobe gain. 12. A system according to any of Claims 1 to 7, wherein the directional antenna (32) comprises a feed structure (37) and a reflector surface (35) of substantially paraboloidal shape, the feed structure (37) being arranged closer than the focal point to the reflector surface (35), whereby to enhance side lobe gain. 13. A system according to any of Claims 1 to 7, wherein the directional antenna (32) comprises a feed structure (37) and a reflector surface (35) of substantially paraboloidal shape, the feed structure (37) having a dimple therein, whereby to enhance side lobe gain. 14. A method of operating a radio communication system wherein a terrestrial receiver and/or transmitter (28) located at the Earth's surface and having a directional antenna (32) with a main lobe (36) and side lobes (38) is in communication with a first transmitter and/or receiver and a second transmitter and/or receiver, characterised in that said main lobe (36) is directed at a substantially geosynchronous satellite (11) having said first transmitter and/or receiver (14), and at least one of said side lobes (38) is directed at an airborne platform (20) having said second transmitter and/or receiver (22). 15. A method according to Claim 14, wherein said airborne platform (20) moves relative to the ground. 16. A method according to Claim 14, wherein said airborne platform (20) is substantially static relative to the ground. 17. A method according to any of Claims 14 to 16, wherein the side lobe gain of the terrestrial receiver and/or transmitter (28) is enhanced. 18. A communications apparatus comprising: a satellite (11) in Earth orbit (12); said satellite (11) including a satellite transponder (14) and a satellite antenna (16) for conveying a set of satellite beams of radiation (18) toward the surface of the Earth (E); an airborne platform (20); said airborne platform (20) including an airborne platform transponder (22) and an airborne platform antenna (24D, 24U) for conveying a set of airborne platform beams of radiation (26) toward the surface of the Earth (E); and a terminal (28); said terminal (28) including a receiver (30) and a receiver antenna (32); said receiver antenna (32) having a central axis (34) and a main antenna lobe (36); said main antenna lobe (36) being generally coaxial with said central axis (34); said main antenna lobe (36) being pointed toward said satellite (1 1) and being used to receive said set of satellite beams of radiation (18); said receiver antenna (32) also having an antenna surface (35) and a feed structure (37); said receiver antenna (32) further having a side antenna lobe (38); said side antenna lobe (38) being generally coaxial to said central axis (34); said side antenna lobe (38) being used to receive said set of airborne platform beams of radiation (26); said airborne platform (20) being flown along a flight path (40) which permits said airborne platform (20) to transmit said set of airborne platform beams of radiation (26) to said receiver antenna (32) using said side antenna lobe (38) while said central axis (34) of said receiver antenna (32) is pointed toward said satellite (11). 19. An apparatus as claimed in Claim 18, in which said airborne platform (20) operates at high altitudes. 20. An apparatus as claimed in Claim 18, in which said airborne platform (20) operates in a generally closed loop pattern (40). 21. An apparatus as claimed in Claim 18, in which said surface (35) of said receiver antenna (32) is deliberately distorted to augment the gain of said side lobe (38). 22. An apparatus as claimed in Claim 1, in which said airborne platform (20) is an aiφlane. 23. A method of augmenting a satellite broadcast system comprising the steps of: operating a receiving antenna (32); said receiving antenna (32) having a main lobe (36) and a side lobe (38); sensing a set of satellite beams of radiation (18) transmitted from a satellite (1 1) in Earth orbit (12) using said main lobe (36) of said receiving antenna (32); operating an airborne platform (20) over the surface of the Earth; said airborne platform (20) including an airborne platform transponder (22) and an airborne platform antenna (24D & 24U); conveying a set of airborne platform beams of radiation (26) toward the surface of the Earth (E) to said receiving antenna (32); and simultaneously sensing said set of airborne platform beams of radiation (26) using said side lobe (38) of said receiving antenna (32).

Inventors: TUCK EDWARD F, TUCK, EDWARD, F.
Applicants: TUCK EDWARD F, TUCK, EDWARD, F.
Application year: 1996
Main classification: H04N7
IPC codes: H04N7