WO1998025412A1 - Methods and apparatus for augmenting satellite broadcast system - Google Patents
Methods and apparatus for augmenting satellite broadcast system Download PDFInfo
- Publication number
- WO1998025412A1 WO1998025412A1 PCT/US1996/019147 US9619147W WO9825412A1 WO 1998025412 A1 WO1998025412 A1 WO 1998025412A1 US 9619147 W US9619147 W US 9619147W WO 9825412 A1 WO9825412 A1 WO 9825412A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- antenna
- airborne platform
- receiver
- lobe
- satellite
- Prior art date
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Classifications
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N7/00—Television systems
- H04N7/20—Adaptations for transmission via a GHz frequency band, e.g. via satellite
Definitions
- 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.
- 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. 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.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.
- the present invention is a system which provides programming from both satellites and local sources using a single antenna.
- 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.
- receivers and transmitters incorporate devices relating reception and transmission signals.
- 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.
- beams emanating from a geosynchronous satellite are collected using the main lobe of a home receiving antenna, while a rebroadcast signal generated by an ai ⁇ lane circling above the home is simultaneously sensed using a side lobe of the receiving antenna.
- the ai ⁇ lane 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.
- 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.
- 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.
- Figure 1 furnishes a schematic view 10 of satellites 1 1 operating in geosynchronous orbit 12 above the
- FIG. 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.
- the manned aircraft 20 includes a transponder 22 and antennas 24U & 24D which relay signals 26 to consumers.
- 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.
- 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.
- 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.
- FIG. 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.
- 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.
- the ai ⁇ lane 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.
- Figure 4 presents a graph 42 which plots the antenna elevation pointing angle ⁇ versus latitude L( ⁇ ).
- 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 ai ⁇ lane 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 ai ⁇ lane 20 to the receiver antenna 32 is given by the expression:
- D*h a*cot( ⁇ + ⁇ ) Equation 2 where a is the altitude of the ai ⁇ lane.
- the ai ⁇ lane 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.
- 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.
- Figure 5 exhibits the geometrical relationships between a satellite 1 1 and a receiving antenna 32.
- the slant range d s and elevation (look angle) ⁇ as seen from the subscriber's antenna varies with the subscriber's latitude as follows:
- Equation 4 For latitudes ranging from thirty to fifty degrees, Equation 4 produces the values presented in Table One:
- Figure 6 depicts the geometrical relationships between the receiving antenna, the ai ⁇ lane and the satellite.
- Table Two presents the appropriate values of ⁇ , ⁇ , d sa and D a for the case when the ai ⁇ lane 20 is centered in the top of the first side lobe 38:
- Equations 8 and 9 are utilized to determine if the first side lobe 38 is large enough at the ai ⁇ lane's slant range so that the ai ⁇ lane can maneuver, and to ensure that the first side lobes 38 of receiving antennas 32 situated across a city can "see" the ai ⁇ lane.
- 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( ⁇ )
- Figures 8A and 8B illustrate the geometry of the projection of the receiving antenna side lobe 38 at the position of the ai ⁇ lane 20.
- the length and width of the area "seen" by the first sidelobe at the ai ⁇ lane's altitude must be calculated to determine whether the ai ⁇ lane 20 can stay within the sidelobe 38.
- the length £ of the projection of the sidelobe on the plane of the ai ⁇ lane's altitude is:
- Equations 10 and 1 1 may be used to generate the values contained in Table Four:
- 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 ai ⁇ lane 20 to fly a rather tight racetrack pattern 40 to stay in the optimum serving area.
- the best position for the ai ⁇ lane 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 pe ⁇ endicular to the long axis of the city.
- the turning radius of an ai ⁇ lane 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 ai ⁇ lane 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.
- 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
- TAS true airspeed
- the turning radius is, therefore:
- 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.
- FIG. 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.
- FIG 10A presents a schematic view of an aircraft 20 that may be used to practice the preferred embodiment of the present invention.
- the ai ⁇ lane 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 ai ⁇ lane 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 ai ⁇ lane 20 are sensed by receiving antenna 32, which is coupled to receiver 30, converter 64 and television TV.
- Figure 1 1 shows the ai ⁇ lane 20 flying in a generally closed loop pattern 40.
- the preferred embodiment of the invention is implemented using a manned ai ⁇ lane, 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.
- 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.
- the antenna surface 35 is carefully contoured to approximate shape of a true paraboloid to maximize the gain of the main lobe 36.
- 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 ai ⁇ lane 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.
- 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.
Abstract
Description
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Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/US1996/019147 WO1998025412A1 (en) | 1996-12-06 | 1996-12-06 | Methods and apparatus for augmenting satellite broadcast system |
CA002273898A CA2273898A1 (en) | 1996-12-06 | 1996-12-06 | Methods and apparatus for augmenting satellite broadcast system |
EP96944742A EP0943207A1 (en) | 1996-12-06 | 1996-12-06 | Methods and apparatus for augmenting satellite broadcast system |
AU13283/97A AU1328397A (en) | 1996-12-06 | 1996-12-06 | Methods and apparatus for augmenting satellite broadcast system |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/US1996/019147 WO1998025412A1 (en) | 1996-12-06 | 1996-12-06 | Methods and apparatus for augmenting satellite broadcast system |
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Publication Number | Publication Date |
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WO1998025412A1 true WO1998025412A1 (en) | 1998-06-11 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/US1996/019147 WO1998025412A1 (en) | 1996-12-06 | 1996-12-06 | Methods and apparatus for augmenting satellite broadcast system |
Country Status (4)
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EP (1) | EP0943207A1 (en) |
AU (1) | AU1328397A (en) |
CA (1) | CA2273898A1 (en) |
WO (1) | WO1998025412A1 (en) |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH03226689A (en) * | 1990-01-31 | 1991-10-07 | Nec Corp | Antenna control apparatus |
WO1995027373A1 (en) * | 1994-04-05 | 1995-10-12 | Diversified Communication Engineering, Inc. | System for providing local originating signals with direct broadcast satellite television signals |
US5584047A (en) * | 1995-05-25 | 1996-12-10 | Tuck; Edward F. | Methods and apparatus for augmenting satellite broadcast system |
-
1996
- 1996-12-06 AU AU13283/97A patent/AU1328397A/en not_active Abandoned
- 1996-12-06 EP EP96944742A patent/EP0943207A1/en not_active Withdrawn
- 1996-12-06 WO PCT/US1996/019147 patent/WO1998025412A1/en not_active Application Discontinuation
- 1996-12-06 CA CA002273898A patent/CA2273898A1/en not_active Abandoned
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH03226689A (en) * | 1990-01-31 | 1991-10-07 | Nec Corp | Antenna control apparatus |
WO1995027373A1 (en) * | 1994-04-05 | 1995-10-12 | Diversified Communication Engineering, Inc. | System for providing local originating signals with direct broadcast satellite television signals |
US5584047A (en) * | 1995-05-25 | 1996-12-10 | Tuck; Edward F. | Methods and apparatus for augmenting satellite broadcast system |
Non-Patent Citations (3)
Title |
---|
"Fesselballons tragen Fernsehsender", FUNKSCHAU, vol. 52, no. 11, 23 May 1980 (1980-05-23), DE, pages 51 - 53, XP002036712 * |
OTTO H J: "MEHR PROGRAMME MIT EINER SAT-ANTENNE ASTRA, KOPERNIKUS UND EUTELSAT", FUNKSCHAU, vol. 65, no. 6, 5 March 1993 (1993-03-05), pages 42 - 44, XP000346205 * |
PATENT ABSTRACTS OF JAPAN vol. 016, no. 005 (P - 1295) 8 January 1992 (1992-01-08) * |
Also Published As
Publication number | Publication date |
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AU1328397A (en) | 1998-06-29 |
EP0943207A1 (en) | 1999-09-22 |
CA2273898A1 (en) | 1998-06-11 |
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