US20030040273A1 - Sub-orbital, high altitude communications system - Google Patents

Sub-orbital, high altitude communications system Download PDF

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Publication number
US20030040273A1
US20030040273A1 US10/180,217 US18021702A US2003040273A1 US 20030040273 A1 US20030040273 A1 US 20030040273A1 US 18021702 A US18021702 A US 18021702A US 2003040273 A1 US2003040273 A1 US 2003040273A1
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relay station
energy
relay
stations
balloon
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US10/180,217
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English (en)
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Sherwin Seligsohn
Scott Seligsohn
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Individual
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Individual
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Application filed by Individual filed Critical Individual
Priority to US10/180,217 priority Critical patent/US20030040273A1/en
Priority to US10/307,116 priority patent/US8483120B2/en
Publication of US20030040273A1 publication Critical patent/US20030040273A1/en
Priority to US11/228,144 priority patent/US7567779B2/en
Assigned to KENYON & KENYON LLP reassignment KENYON & KENYON LLP ATTORNEY'S LIEN Assignors: WIRELESS UNIFIELD NETWORK SYSTEMS CORPORATION
Assigned to KENYON & KENYON LLP reassignment KENYON & KENYON LLP ATTORNEY'S LIEN Assignors: WIRELESS UNIFIED NETWORK SYSTEMS CORPORATION
Abandoned legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B64G1/1007—Communications satellites
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/40—Balloons
    • B64B1/44—Balloons adapted to maintain predetermined altitude
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/40—Balloons
    • B64B1/46—Balloons associated with apparatus to cause bursting
    • B64B1/48—Balloons associated with apparatus to cause bursting to enable load to be dropped by parachute
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/18502—Airborne stations
    • H04B7/18504—Aircraft used as relay or high altitude atmospheric platform

Definitions

  • This invention relates to a long duration, high altitude communication system, and more particularly to a communications system in a sub-orbital plane that is well above any system which is physically connected to the ground, and whose components can stay aloft and on station for long periods.
  • Wireless telecommunications systems currently use either terrestrial (ground) based infrastructures or space (satellite) based infrastructures.
  • Terrestrial based systems include radio towers and antennae on tall buildings, mountains, and the like. Also, balloons that are tethered to the ground have been used.
  • Spaced based systems rely on satellites having telecommunications equipment.
  • Terrestrial based wireless telecommunications systems have been known since the early days of radio, almost a hundred years ago. Their configurations range from simple one-way and two-way radio hookups—to radio and television broadcast networks—to today's sophisticated cellular networks and proposed personal communications networks (PCN)
  • PCN personal communications networks
  • Relay stations are used to send and receive radio transmissions to and from other locations. Because they are on or close to the ground, their radio signals tend on the average to be closer to the horizontal than the vertical. Thus, each relay station can only send and receive signals from a limited distance. The distance that the radio signals can travel is limited because of horizon problems due to the curvature of the earth; line of sight problems due to uneven terrain, trees, and buildings; interference due to other signals or with reflections of the transmitted signal; and attenuation problems due to unwanted absorption of the transmitted signal. To increase the area of coverage, either more powerful equipment must be used, and/or the height of the relay stations must be increased.
  • Satellite systems in geosynchronous orbit (approximately 22,000 miles) have been used for may years with a high degree of reliability.
  • Their prime advantage is their high altitude which enables one satellite to send and receive signals from an area on the earth encompassing hundreds of thousands of square miles.
  • satellites are expensive to manufacture, launch and position, either initially or as replacements. Further, because of the cost associated with their manufacture and launch, and the great difficulty in servicing them, extraordinary care must be taken to assure their reliability.
  • the satellites will have to be programmed to permit this to happen. Thus, very complex routing features will need to be implemented.
  • members of the industry disagree amongst themselves over optimum altitudes, angles of signal propagation, and how to deal with the doppler shifts.
  • the satellites' orbits will decay at faster rates than the higher altitude satellites so that they and the equipment they carry will need to be replaced more often, again incurring substantial expense.
  • the invention relates generally to a telecommunications system that comprises at least two ground stations.
  • Each of the ground stations includes means for sending and means for receiving telecommunication signals.
  • At least one relay station is provided.
  • the relay station includes means for receiving and sending telecommunication signals from and to the ground stations and from and to other relay stations.
  • the relay stations are at an altitude of about 12 to 35 miles. Means are provided for controlling the lateral movement of the relay stations so that once a pre-determined altitude is reached, a predetermined location of each of the relay stations can be achieved and maintained.
  • the invention in another aspect relates to a telecommunications method comprising the steps of providing at least two ground stations and at least one relay station.
  • One of the relay stations is positioned at a predetermined location and at an altitude of about 12 to 35 miles.
  • a telecommunications signal is transmitted from one of the ground stations to one of the relay stations.
  • the relay station then transmits the telecommunications signal to the second ground station or to at least another of the relay stations and then to the second ground station.
  • Each of the relay stations is maintained at a predetermined altitude and location.
  • the invention in still another aspect relates to a relay station for a high altitude sub-orbital telecommunications system. It includes means for receiving and sending telecommunications signals from and to ground stations and/or from and to other relay stations. It also includes means for controlling the lateral and vertical movement of said relay station so that a predetermined altitude and location for the relay station can be achieved and maintained.
  • FIG. 1 is a schematic showing a communications system constructed in accordance with a presently preferred form of the invention.
  • FIG. 2 is a elevation view of one of the relay stations comprising the invention.
  • FIG. 3 is a view of a portion of FIG. 2 showing a propulsion system.
  • FIG. 4 is a view of a portion of FIG. 2 showing another form of propulsion system.
  • FIGS. 5A and 5B are a plan view and an elevation view, respectively, of another form of a part of the invention shown in FIG. 2.
  • FIG. 6A, 6B and 6 C are views of further forms of a part of the invention shown in FIG. 2.
  • FIG. 7 is a schematic showing an alternate arrangement of the communications system illustrated in FIG. 1.
  • FIG. 8 is a view of a portion of a relay station.
  • FIG. 9 is a view of a second embodiment of the portion of the relay station shown in FIG. 5.
  • FIG. 10 is a view of a relay station being recovered.
  • the system 10 comprises a ground based portion 12 and an air based portion 14 .
  • the ground based portion 12 may comprise conventional telephone networks 16 with branches that are connected to a ground station 18 having suitable long distance transmitting and receiving means such as antenna 20 .
  • the ground based portion 12 may also comprise mobile telephones of well known types such as cellular telephones that may be carried by individuals 22 or in vehicles 24 .
  • the microwave antennae 20 are operative to transmit and receive telecommunication signals to and from a sub-orbital, high altitude relay station 28 which is located at an altitude of between about 12 to 35 miles.
  • relay stations 28 there are a plurality of relay stations 28 ; each one being on station at a fixed location over the earth.
  • the relay stations are designed to stay aloft and on station at least 20 to 30 days.
  • Each relay station 28 contains means for receiving telecommunication signals from a ground station 20 , individual 22 or vehicle 24 and then transmitting them to another ground station 118 , individual 122 or vehicle 124 either directly or by way of another relay station 130 . Once the signals return to the ground based portion 12 of the system 10 , the telecommunication calls are completed in a conventional manner.
  • the relay station 28 may comprise a lifting device 32 .
  • a suitable lifting device could be an inflatable, lighter than air device such as a high altitude super-pressure balloon of the type developed by Winzen International, Inc. of San Antonio, Tex.
  • the super-pressure balloon 32 is configured so that it floats at a predetermined density altitude. The configuring is accomplished by balancing inflation pressure of the balloon and the weight of its payload against the expected air pressure and ambient temperatures at the desired density altitude. It has been observed that devices of this character maintain a high degree of vertical stability during the diurnal passage notwithstanding that they are subject to high degrees of temperature fluctuation.
  • the lifting device 32 could be an improved zero pressure balloon of the type having means for controlling the extent to which the gas inside the balloon is heated during the day and is cooled at night.
  • controlling the heat of the gas reduces the amount of ballast that will need to be dropped each night.
  • the lifting device 32 could be an overpressure zero pressure balloon.
  • This is a conventional zero pressure balloon that is modified by closing its vents. It is allowed to pressurize within established limits in flight by the controlled release of gas through a valve. This reduces the amount of ballast that must be dropped when the gas cools at night as when a conventional zero pressure balloon would increase in density and lose altitude.
  • the amount of heat inside the balloon can be controlled by making the skin of the balloon, or portions of the skin, from a suitable transparent, electro-chromatic or photo-chromatic material.
  • the balloon skin will be substantially transparent at low light levels and at night. This will permit radiant heat energy to enter the balloon and heat its interior in a manner similar to a greenhouse. During the day, sunlight or a signal sent from the ground will cause the skin to become reflective or opaque. This will reduce the amount of radiant energy that will enter the balloon, thereby keeping the interior of the balloon relatively cool.
  • Another way to control altitude is to use a balloon that includes a central expansible chamber that is filled with a lighter that air gas that is surrounded by an outer substantially non-expansible chamber that is filled with air.
  • compressed air is forced into the outer chamber; to increase altitude, air is vented from the outer chamber.
  • Typical of this system is the Odyssey balloon project of Albuquerque, N. Mex. and described in the New York Times of Jun. 7, 1994, at section C, page 1 .
  • a plurality of tracking stations 36 are provided. They include well known means which can identify a particular relay station 28 without regard to whether it is in a cluster and detect its location and altitude.
  • a thrust system is provided for returning a relay station 28 to its preassigned station should a tracking station 36 detect that it has shifted.
  • the thrust system can be operated automatically to keep the relay stations on station by using control systems that rely on fuzzy logic.
  • each of the relay stations 28 comprises one equipment module 38 .
  • the equipment module comprises a platform.
  • the equipment module 38 can be of any convenient shape and size that is sufficient to support the equipment necessary to accomplish the purpose of the relay station.
  • the equipment module 38 includes a housing 40 which is supported by device 32
  • the housing 40 contains a telecommunication signal transmitter and receiver 44 and a ground link antenna 48 .
  • Antenna 48 is for receiving and sending telecommunications signals between ground stations 20 and the relay station 28 .
  • the relay station 28 also includes a plurality of antennas 52 which are adapted to receive and transmit telecommunications signals from and to other relay stations.
  • the housing 40 also contains a guidance module 56 that transmits the identity and location of the relay station to the tracking stations 36 . It receives instructions from the tracking station for energizing the thrust system.
  • a guidance antenna 58 is provided to enable communication between the tracking station 36 and the guidance module 56 .
  • a suitable re-energizable power supply 60 is mounted on housing 40 , the power supply 60 may comprise a plurality of solar panels 64 .
  • the solar panels capture the sun's light and convert it into electricity which can be used by the telecommunications equipment as well as for guidance and propulsion.
  • the power supply could also comprise a plurality of wind vanes 68 .
  • the wind vanes may be arranged to face in different directions so that at least some of them are always facing the prevailing winds.
  • the wind vanes 68 can be used to generate electric power in a well known manner which also can be used by the telecommunication equipment as well as for guidance and propulsion.
  • an alternate power supply 66 may be provided in the form of a microwave energy system similar to that which has been developed by Endosat, Inc of Rockville, Md.
  • the microwave energy system includes a ground based microwave generator (not shown) that creates a microwave energy beam of about 35 GHz. This beam is directed to receptors 80 on the relay station 28 and there converted to direct current. Further, the microwave energy could come from a source that is in orbit or from free space.
  • the microwave energy system could supply power sufficient to operate the telecommunications system on the relay station as well as provide power for guidance and propulsion.
  • the relay stations 28 may be provided with at least one microwave transmitter and suitable means for aiming the microwave transmitter at a microwave receiving means on another relay station 28 so that a source other than the ground based microwave generator is available to provide microwave energy to the relay stations.
  • the thrust system for the relay station 28 may comprise a plurality of rockets or jets 90 or propellers 94 .
  • the jets 90 and propellers 94 are arranged in a horizontal plane along mutually perpendicular axes which are supported by pods 100 on the housing 40 .
  • the relay station 28 can be directed to and maintained at a pre-determined location over the earth.
  • additional jets or rockets 108 or propellers 112 could be located on vertical axes to assist in bringing the relay station to its pre-determined altitude on launch or restoring it should its drift from that altitude be more than an acceptable amount.
  • Drifting of the relay stations 28 from their pre-determined locations will be detected by the tracking stations 36 .
  • the tracking stations 36 will then energize the thrust members on the relay stations 28 for selected intervals to return them to their pre-determined locations.
  • each relay station 28 can comprise a cluster of between two and four sections 34 .
  • Each section 34 comprises an equipment module 38 that is independently carried by its own lifting device 32 .
  • Some of the equipment modules 38 can carry telecommunications equipment while other equipment modules 38 can carry power generation and transmitting equipment. Thus, energy can be transmitted from the power generation modules by beaming microwave energy to antennae on the communications modules. Since there are several sections 34 comprising a relay station, each section 34 can be smaller and lighter than if there were only one equipment module comprising the relay station 28 . Further, the provision of a cluster of sections 34 creates a redundancy that will keep the relay station in service should the equipment on one of the sections 34 fail.
  • lightweight, unmanned airplanes 114 could be used in lieu of the balloons.
  • the airplanes 114 could be controlled from the ground in a well known manner. However, they are less desirable than balloons. This is because they are constantly changing position to remain aloft, and because their payloads are limited by the lightweight airframes required to reach high altitudes.
  • the airplane could be essentially a flying wing that is comprised of high efficiency solar panels 116 .
  • the solar panels in the wing could drive electric motors and an energy storage system.
  • hydrogen—oxygen regenerative fuel cells 118 could be used to achieve long periods of flight
  • the lightweight airplane 114 could achieve its power from microwave energy that is beamed to antennae 126 on the airplane from a transmitting dish 128 on the ground as described above, or is collected from microwave energy in free space.
  • the telecommunications signal will be conveyed from the caller's telephone by way of a conventional network to the ground station 18 associated with that location.
  • the microwave antenna 20 will then beam a telecommunications signal corresponding to that telephone call to the nearest relay station 28 .
  • Switching circuity of a well known type will direct the signal to another ground station 120 near the recipient. If the recipient is further, the signal will be sent to a further relay station 130 from which it will be directed to a mobile telephone carried by an individual 122 or in a vehicle 124 or to a ground station 140 near the recipient.
  • the signal received by the ground station 120 or 140 will be transmitted to the recipient's telephone by way of a conventional telephone network.
  • the relay stations are at an altitude of about 12-35 miles they are above adverse weather. None-the-less, at that altitude telecommunications power requirements are low enough to enable the use of frequencies that are the same as those used for terrestrial transmission. This means that existing allocated telecommunications frequencies can be used. Since much of the engineering has been done for those telecommunications frequencies, the costs of implementing this system are reduced. Further, maximum use of the existing frequencies can be achieved by currently known digital multiple access technologies such as frequency division multiple access (FDMA), time division multiple access (TDMA), code division multiple access (CDMA) or combinations of them.
  • FDMA frequency division multiple access
  • TDMA time division multiple access
  • CDMA code division multiple access
  • the signals generated in the communications system of the invention can be relatively weak since they travel a shorter distance. This is particularly advantageous since the ability to use a weaker signal results in transmitters and receivers that are smaller, lighter, and which require less power to operate.
  • This aspect of the telecommunications system could be enhanced by having the relay stations 28 stationed over more densely populated areas 132 operate at lower altitudes and/or with more narrowly focused angles of reception and propagation 142 than other relay stations 28 that are over less densely populated areas 134 that will operate at higher altitudes and/or with broadly focused angles of reception and propagation 144 as seen in FIGS. 7A and 7B.
  • a substantial unbalance in the volume of traffic handled by the various relay stations comprising the telecommunications system can be reduced.
  • the relay stations 28 that are designated for the more densely populated areas 132 may operate with lower power. This can result in a lower cost of operation.
  • This is another advantage over a satellite based system since in such a system a reduction in the height of the orbit for a particular satellite will increase its decay rate and shorten its life.
  • a recovery system 150 for the relay stations 28 is provided.
  • the recovery system includes a deflation device 152 and a remote controlled recovery parachute 154 .
  • one embodiment of the deflation device 152 includes a housing 160 that is formed integrally with the suitable lighter than air device 32 .
  • the housing 160 includes an outwardly extending and radially directed flange 164 that is integrally connected to the device 32 as by welding or by adhesive.
  • the flange 164 supports a downwardly directed, and generally cylindrical wall 168 that supports a bottom wall 172 .
  • the bottom wall 172 is defined by an open lattice so that the housing 160 is connected to the interior of the device 32 and is at the same pressure.
  • the cylindrical wall 168 supports an inwardly directed flange 176 .
  • a frangible cover 184 is connected to the flange in airtight relation. This can be accomplished by connecting the cover to the flange by an adhesive, or with a suitable gasket between them, or by fabricating the cover as an integral part of the housing 160 .
  • the cylindrical wall 168 , bottom wall 172 and cover 18 define a chamber that contains the remote control recovery parachute 154 .
  • a small chamber 190 is formed on the underside of the cover 184 by a wall 192 .
  • a small explosive pack 194 which is contained within the chamber 190 is responsive to a signal received by antenna 196 .
  • the parachute 154 has its control lines 198 connected to a radio controlled drive member 200 that is contained within the housing 160 .
  • the drive member 200 may include electric motors that are driven in response to signals from the ground to vary the length of the control lines in a well known manner to thereby provide directional control to the parachute.
  • a coded signal is sent to the device where it is received by antenna 196 . This results in the explosive charge 194 being detonated and the frangible cover 184 being removed.
  • the cover 184 is designed to break, the explosive charge can be relatively light so that it does not damage the parachute 154 .
  • the wall 192 helps to direct the explosive force upwardly against the cover rather than toward the device 32 .
  • the parachute 154 will support the device 32 by way of its control lines 198 .
  • the relay station 28 can be directed to a predetermined location on the ground.
  • flange 164 supports cover 204 with an annular airtight gasket between them.
  • the cover 204 is held against the flange 164 by a plurality of circumferentially spaced clamping brackets 210 .
  • the clamping brackets are retractably held in engagement with the cover 204 by electrically driven motors 212 .
  • the motors are energized in response to signals from the ground to retract the brackets 210 .
  • brackets 210 When the brackets 210 are retracted, the pressure of the gases escaping from the device 32 will dislodge the cover and permit the parachute to be deployed.
  • the recovery system 150 can be replaced and the device 32 can be re-inflated and returned to their respective stations.
  • relay stations comprise remotely controlled airplanes 114 , they can be recovered in a well known manner for service and returned to their respective stations.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
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  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Combustion & Propulsion (AREA)
  • Signal Processing (AREA)
  • Chemical & Material Sciences (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Radio Relay Systems (AREA)
  • Mobile Radio Communication Systems (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
  • Polyesters Or Polycarbonates (AREA)
  • Absorbent Articles And Supports Therefor (AREA)
  • Measurement And Recording Of Electrical Phenomena And Electrical Characteristics Of The Living Body (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Selective Calling Equipment (AREA)
  • Vehicle Body Suspensions (AREA)
  • Reduction Or Emphasis Of Bandwidth Of Signals (AREA)
US10/180,217 1993-07-30 2002-06-25 Sub-orbital, high altitude communications system Abandoned US20030040273A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US10/180,217 US20030040273A1 (en) 1993-07-30 2002-06-25 Sub-orbital, high altitude communications system
US10/307,116 US8483120B2 (en) 1993-07-30 2002-11-26 High efficiency sub-orbital high altitude telecommunications system
US11/228,144 US7567779B2 (en) 1993-07-30 2005-09-16 Sub-orbital, high altitude communications system

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10003793A 1993-07-30 1993-07-30
US10/180,217 US20030040273A1 (en) 1993-07-30 2002-06-25 Sub-orbital, high altitude communications system

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
US10003793A Continuation-In-Part 1993-07-30 1993-07-30
US15770198A Continuation 1993-07-30 1998-09-21

Related Child Applications (2)

Application Number Title Priority Date Filing Date
US10/307,116 Continuation-In-Part US8483120B2 (en) 1993-07-30 2002-11-26 High efficiency sub-orbital high altitude telecommunications system
US11/228,144 Continuation US7567779B2 (en) 1993-07-30 2005-09-16 Sub-orbital, high altitude communications system

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US20030040273A1 true US20030040273A1 (en) 2003-02-27

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US10/180,217 Abandoned US20030040273A1 (en) 1993-07-30 2002-06-25 Sub-orbital, high altitude communications system
US11/228,144 Expired - Lifetime US7567779B2 (en) 1993-07-30 2005-09-16 Sub-orbital, high altitude communications system

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US11/228,144 Expired - Lifetime US7567779B2 (en) 1993-07-30 2005-09-16 Sub-orbital, high altitude communications system

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EP (1) EP0711476B1 (ja)
JP (1) JPH09503892A (ja)
KR (1) KR100442209B1 (ja)
CN (1) CN1073311C (ja)
AT (1) ATE185659T1 (ja)
AU (1) AU685149B2 (ja)
BR (1) BR9407157A (ja)
CA (1) CA2168353C (ja)
DE (2) DE4495639T1 (ja)
ES (2) ES2113814B1 (ja)
FR (1) FR2712128B1 (ja)
GB (1) GB2296634B (ja)
GR (1) GR3032336T3 (ja)
HK (1) HK1013180A1 (ja)
IT (1) IT1290878B1 (ja)
PL (1) PL180378B1 (ja)
PT (1) PT711476E (ja)
RU (1) RU2185026C2 (ja)
UA (1) UA43849C2 (ja)
WO (1) WO1995004407A1 (ja)

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