US3742358A - Tethered airborne communications and information transfer system - Google Patents

Tethered airborne communications and information transfer system Download PDF

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Publication number
US3742358A
US3742358A US00102597A US3742358DA US3742358A US 3742358 A US3742358 A US 3742358A US 00102597 A US00102597 A US 00102597A US 3742358D A US3742358D A US 3742358DA US 3742358 A US3742358 A US 3742358A
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antenna
signal
coupled
ground station
shafts
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R Cesaro
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    • 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
    • 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

Definitions

  • a tethered balloon including means for controlling the height thereof is utilized as an airborne platform for transmitting and receiving apparatus including a multiple antenna assembly.
  • the antenna assembly is suspended from a gimbal or ball joint configuration attached to the balloon so that it is gravity stabilized in the vertical plane.
  • the antenna assembly itself is comprised of a plurality of independently rotatable coaxial shafts having respective antenna means coupled thereto.
  • each of the coaxial shafts are hung from a pendulum arm member which is freely moveable within a vertical cone angle limit of 45 and maintains vertical orientation to within :2.
  • the rotation of each of the coaxial shafts is independently controlled from a ground station by means of a control signal to selectively point each antenna means in a predetermined compass direction.
  • each coaxial shaft couples respective transmitter-receiver means to its antenna means in order to provide selective signal transfer between the ground station and/or other similar airborne systems.
  • the present invention is directed to an improved airborne radiating and receiving antenna system for communications and information transfer or radio, television, telephone, digital data signals, etc. for obtaining not only predetermined ground area coverage, but also a communication common carrier network relay capability over relatively long distances.
  • the subject invention is directed to tethered airborne apparatus utilized as a radiating and receiving platform and including means for controlling the height of the airborne apparatus for specific operational requirements.
  • the airborne apparatus is preferably comprised of a lighter than air device such as a balloon under which is mounted a gravity stabilized multiple antenna and transceiver assembly suspended from a universal ball joint subassembly which has a limited freedom of movement.
  • the antenna assembly comprises a plurality of independently rotatable coaxial shafts mounted on a base member attached to the ball joint subassembly, thereby forming a substantially vertically aligned pendulum arm which is adapted to maintainia vertical orientation by means of its own weight.
  • Respective transmitter-receiver means and antenna means are coupled to either end of selected coaxial shafts which additionally include transmission line means for coupling electrical signals therebetween.
  • Each of the selected coaxial shafts and attached antenna means is controlled in azimuth or horizontal plane by means of telemetry control from a ground station which radiates a compass heading signal via a flux gate transmitter to the antenna assembly.
  • a flux gate compass system controls a servo system coupled to each of the selected coaxial shafts to aim the respective antenna means in a predetermined compass direction.
  • FIG. 1 is a schematic representation of a system embodying the principles of the present invention
  • FIG. 2 is a schematic representation of a long distance communications network providing an air-to-air relay of electrical signals as well as ground station transfer at predetermined intervals;
  • FIG. 3 is a representation of a typical radiation pattern and network contemplated by the subject invention.
  • FIGS. 4A and 4B is an elevational view partially in vertical transverse section of a plurality of independently controlled coaxial shafts coupling respective transmitter-receiver means to antenna mounting pads located at the lower extremity thereof;
  • FIG. 5 is a view of one type of antenna means contemplated for use in combination with the subject invention.
  • FIG. 6 is a view of a second type of antenna means utilized by the subject invention.
  • FIG. 7 is a view of yet another type of antenna means utilized by the subject invention.
  • FIG. 8 is a block diagram of a ground based multiple channel communication transmitter utilized in combination with the subject invention.
  • FIG. 9 is a block diagram of a ground based multiple channel communication receiver adapted to receive signals from the antenna system contemplated by the subject invention.
  • FIG. 10 is a block diagram of a typical airborne relay subsystem
  • FIG. 1 l is a block diagram illustrative of one airborne receiver apparatus shown in FIG. 10;
  • FIG. 12 is a block diagram illustrative of one airborne transmitter apparatus shown in FIG. 10.
  • FIG. 13 is a block diagram illustrative of another receiver-transmitter apparatus shown in FIG. 10.
  • FIG. 1 discloses a pair of lighter than air free space aircraft consisting of tethered balloons 10. It should be observed, however, that this is shown by way of a preferred embodiment only since when desirable other types of tethered airborne apparatus may be utilized as well such as dirigibles, helicopters or even airplanes.
  • Each of the balloons 10 is connected to a tether line or cable 12 which is connected to a winch 14 located on the ground for providing selective altitude control of the balloon l0 and thus provides a variation in antenna platform heights as required for specific geographic locations and/or signal communication requirements.
  • a base member generally illustrated by reference numeral 16 is mounted on the underside of each balloon 10 from which is suspended at multiple antenna assembly 18 which is enclosed within a wind screen 20.
  • the base member 16 is also adapted to include transmitting and receiving apparatus not shown as well as suitable command and control circuitry and the necessary power supplies. Primary electrical power for this apparatus can either be obtained from a respective ground control station 22 coupling power to the airborne base 16 up the tether cable 12 or the balloon itself may additionally include a self-contained electrical power generating system.
  • Each balloon l and its respective transmitterreceiver apparatus which may be for example a plurality of transceivers adapted to provide an up-down communication link between itself and the control ground station 22 by means of one antenna assembly 26 as well as transmitting and/or receiving signals to and from one or more satellite ground stations 24 within the respective local area, for example area A defined by the radiation pattern of another antenna assembly 28.
  • the antenna system 18 is adapted to provide a direct air-to-air communication relay link between an adjacent airborne system similar to itself. This is provided by one or more still other antenna assemblies 29.
  • the ground station 22 is adapted to provide all interface functions with the respective airborne apparatus including directional control of the antenna elements, as well as controlling the overall operation of the receiving and transmission apparatus and the command and control circuitry. This will be considered in detail subsequently.
  • a balloon l0 tethered at a height h is adapted to electromagnetically radiate and receive information in a substantially circular area (FIG. 3) defined by A 'n'R Information can also be relayed by means of two balloon antenna systems separated by a distance 2R over a distance 4R. 1f the parameter R is considered the line of sight distance, a balloon having an altitude h 10,000 feet, will have a distance R which is in the order of 140 miles. Therefore, local area coverage within the order of 63,000 square miles will be provided while a long line transmission capability with two balloon antennas would be in the order of 550 miles.
  • the following table is more illustrative of typical values for a communication system illustrated in FIG. 1 as compared with a conventional TV transmission tower:
  • the ground station 22 provides an up-down" link with the airborne system and performs two functions: (1) controlling the airborne system and (2) transmitting and/or receiving communications signals therebetween. Accordingly, two transmitting and receiving antennas 30 and 32 are located at the particular ground station and are coupled to apparatus, not shown, housed in the station.
  • the satellite stations 24 may be, for example, automotive vehicles having two way mobile phone service,
  • any desired configuration of balloon locations can be utilized to configure the network either stretched out in length or for encompassing a predetermined closed ground area, both of which are illustrated in FIG. 3.
  • the ground station 22 comprising an end terminus 1 for example, can be adapted to couple up to 14 channels of one-way transmission plus the required telemetry and command signals to the balloon 10 which is then relayed to the relay 1 balloon 10 which is also coupled to its respective ground station 22 identified as a local drop insert station No. 1 wherein for example one channel may be dropped or inserted with the required telemetry command as well as including one local monitor channel.
  • the relay number No. 1 is then coupled to any number of relay balloons 10 shown as relay n which is similar in operation to relay number No. 1.
  • Relay n couples to a terminus number 2 balloon 10 at the end of the relay network which then is coupled to the ground station 22 included in terminus number 2 which is substantially identical to terminus number No. 1. Also, two-way transmission between terminus number 1 and terminus number 2 as well as the intermediate relay stations can be mechanized wherein 7 channels, for example, are transmitted in each direction.
  • a long line video network would include 7 channels transmitting in one direction (west) a band including 7925-81185 MHz while seven channels transmitted in the opposite (east) direction would cover a band of 8124.5 to 8318.0 MHz. Up to seven channels received from the east would cover the band 7300-74935 MHZ while up to seven channels received from the west would cover 74995-76930 MHz. All of these operations would be going on at the same time.
  • the local drop/insert at each balloon relay point would permit local insert in the 7699-77215 MHz range, local drop in the 8324-83465 MHz range, command in the 77275-77500 MHZ range, and monitor in 83525-83750 MHZ range.
  • each of the terminus balloon communications systems can be transformed into relay repeaters simply by reorienting the antenna structure and suitably interconnecting the electronics packages in the airborne equipment by means of the command and control radio link coupling the airborne system to the respective ground control station.
  • a typical ground station transmitting and receiving apparatus adapted for use in a network such as shown in FIG. 2 is disclosed in FIGS. 5 and 6, respectively, and will be treated subsequently.
  • the base 16 is secured to the underside of the balloon shown in FIG. 1 and additionally includes a universal ball joint assembly 34 comprised of a spherical member 36 mounted in a ball bearing assembly 38 secured to the vertical arms 40 and 42 which also form part of the base 16.
  • the center of the sphere 36 is located above the upper contact point of the roller bearing assembly 38 and a pendulum arm member 44 is coupled to the lower surface of the sphere 36 so that it is adapted to hang vertically therefrom due to its own weight as well as the apparatus to be described connected thereto.
  • the weighted pendulum arm 44 is adapted to point downward in the direction of local gravity.
  • a circular rubber damper member 46 is mounted on inwardly facing projections on the end of arms 40 and 42 which acts as a limit stop for the angle of sway of the pendulum arm 44.
  • the damper 46 is slightly angulated inwardly which in combination with the center of the sphere 36 defines a hypothetical cone having its apex at the center of the sphere.
  • the pendulum arm 44 and the assembly attached thereto is thus gravity stabilized vertically but having a limit determined by the rubber damper member 46 which permits the pendulum to sway within a 45 cone from the vertical which is more than enough motion to allow for continued changes in balloon orientationwith respect to varying wind conditions.
  • the wind screen 20 shown in FIG. 1 provides protection against weather, wind and wind gusts which would otherwise have a tendency to affect the pendulum action or motion of the assembly shown in FIG. 4A. All other forces acting on the pendulum arm 44 provide slow motion changes which are easily compensated as well as the continual changes in wind forces acting on the balloon l0 and its resulting directional motional changes.
  • the apparatus attached to the end of the pendulum arm 44 consists, inter alia, of a mounting ring 48 which is adapted to provide a mounting base for a plurality of concentric independently rotatable cylindrical shaft members.
  • a mounting ring 48 which is adapted to provide a mounting base for a plurality of concentric independently rotatable cylindrical shaft members.
  • four shafts 50, 52, 54 and 56 are illustrated; however, it should be noted that any desired number of concentric shafts may be utilized depending upon the desired configuration.
  • These shafts 50 56 moreover are attached to its respective adjacent shaft by means of an intermediate roller bearing assembly which permits independent rotation of each of the shafts about a common longitudinal axis which is in a substantially vertical plane.
  • the inner-most shaft 50 which could be considered the base shaft is also rotatable but is supported on a roller bearing assembly 58 by means of a collar 60 threaded onto the upper end of the shaft.
  • the collar 60 is secured to the upper race of the roller bearing assembly 58 while the lower race is secured to a cylindrical frame 62 attached to the mounting ring 48.
  • the frame 62 moreover, is adapted to provide a suspension for the entire multi-shaft assembly including the shafts 50 56.
  • a second roller bearing assembly 64 provides a support for the adjacent shaft 52.
  • the lower race thereof is secured to the shaft 50 while the upper race of the roller bearing assembly 64 is attached to the shaft 52.
  • a spacer ring 66 provides a necessary separation from the outer and inner surfaces of the shafts 50 and 52, respectively.
  • the inner-most shaft 50 is adapted to rotate around its central axis on the roller bearing assemblies 58 and 64 shown in FIG. 4A and 4B, respectively.
  • Rotation of the shaft 50 is provided by means of a drive motor 66 having its rotor attached to a bevel gear 68 which mates with a beveled ring gear 70 secured to an annular rib member 72 near the upper extremity of the shaft 50.
  • By suitably activating the drive motor 66 selective rotation of the shaft 50 can be provided.
  • the shaft 50 additionally includes a signal transmission line 78 within the cylindrical shaft wall which is adapted to terminate at one end in the antennas 76 and at the other end into an electrical slip ring assembly 80 which couples to an electronic transmitter-receiver apparatus which is shown schematically by reference numeral 82.
  • the second inner-most shaft 52 is located on the outside of the shaft 50 by means of the bearing assembly 84 and the roller bearing assembly 64 previously mentioned.
  • the inner race of the bearing assembly 84 is secured to the outer surface of the shaft 50 while the outer race is secured to the upper extremity of shaft 52 which comprises a flared portion to which is attached the beveled ring gear 86.
  • the ring gear 86 couples to the bevel gear 88 which is connected to the shaft of a second drive motor 90.
  • the lower end of the shaft 52 is secured to the upper race of the bearing assembly 64 shown in FIG. 4B and constitutes an annular projection 92 forming an antenna pad to which one or more antennas 94 are adapted to be mounted.
  • a second independent signal transmission line 96 is lo cated within the side walls of the shaft 52 similar to the transmission lines 78 and terminates in a slip ring assembly 98 which couples into second transmitterreceiver apparatus 100.
  • the two outer-most shafts 54 and 56 are driven by respective drive motors 102 and 104 being independently rotated by the bevel and ring gear assemblies 105 and 106.
  • the concentric shaft assemblies including shafts 54 and 56 are mutually supported by the bearing assemblies 107, 108, and 112 in the manner previously noted.
  • the shaft 54 is relatively shorter than shaft 52 while longer than shaft 56. Its lower extremity terminates in an antenna mounting pad 114 and additionally includes a vertically oriented annular ring member 1116 which is adapted to support one or more antennas 118 which are shown in phantom view but are more fully disclosed in FIG. 7.
  • Shaft 54 also includes an electrical signal transmission line 120 incorporated in the wall thereof which is adapted'to be connected to the antennas 118 as well as terminating in the slip ring assembly 112 which in turn is coupled to a transmitterreceiver apparatus 122.
  • outer-most shaft 56 has its lower termination connected to a mounting pad 124 which includes the vertically oriented member 126. This is adapted to provide a mount for one or more antennas 128 which are similar to the antennas 118. Again, a signal transmission line 130 contained in the sidewall of the cylindrical shaft 56 is adapted to couple to the antennas 128 which connects to the slip ring assembly 132 at the upper end of the shaft as shown in FIG. 4A.
  • the slip ring assembly 132 couples into its respective transmitter-receiver apparatus 133 in the same manner that each of the other concentric cylindrical shaft members are adapted to couple respective signal transmission lines contained therein between the antennas mounted at the respective mounting pads to its transmitter-receiver apparatus.
  • 4A and 4B permit the antennas 76, 94, 118, and 128 to be selectively oriented in space independently of each other by means of the respective drive motors 66, 90, 102 and 104. Since the entire antenna assembly thus described is suspended from the mounting ring 48 attached to the pendulum arm 44, the weight of the assembly provides the required vertical stabilization while the drive motors produce aiming of the antenna members coupled to the shafts in the horizontal or azimuth direction.
  • FIGS. 5, 6 and 7, are typically illustrative of the antennas utilized in combination with the assembly shown in FIGS. 4A and 48.
  • FIG. is illustrative of the antenna configuration mounted on the lowermost pad 74 shown in FIG. 4B and which is part of the cylindrical shaft 50.
  • the antennas 76 comprise spiral antenna elements attached to the bottom surface of pad 74 by means of the antenna base elements 134 secured to the pad 74 by means of suitable hardware such as a nut and bolt.
  • Each of the spiral antenna elements 76 is commonly coupled to the transmission line 78 shown in FIG. 4B and are directed downward in a substantially vertical orientation. This is for purposes of being pointed directly at the ground station 22 shown in FIG. 1.
  • the antenna elements 76 form one element of an air-to-ground or up-down" link for electrical signals coupled between the ground station 22 and the electronic apparatus 82 shown in FIG. 4A.
  • Spiral antennas are preferred for the up-down or air-toground link because such antennas have wide beamwidth and permit the ground station command and control equipment to be located at a remote distance from the ground tethering point.
  • a high gain antenna is not required and the spiral antenna is very light in weight. The number of spiral antennas required depend upon the number of channels of communication being established between the ground station 22 and the airborne electronics system.
  • FIG. 6 there is disclosed the preferred embodiment of the antenna shown by reference numeral 94 in FIG. 4B and which constitutes the antenna assembly for local radiation coverage between the airborne system and the satellite stations 24 shown in FIG. 1.
  • the antenna configuration shown in FIG. 6 comprises the slightly tapered reflector element 138 secured to a swival base 140 attached to an arm 142 mechanically connected to the pad 92 by suitable hardware.
  • the swival connection between the base 140 and the arm 142 permits adjustment of the directivity of the reflector 138.
  • an antenna feed member 144 is included which is adapted to be connected to the transmission line 96 shown in FIG. 48.
  • Such an antenna provides a gain of approximately 2dbm and permits information transfer in a substantially circular downward hemispherical radiation pattern. Simultaneous multichannel wideband and narrow band information in both transmission and receiving modes can be handled by this type of an antenna.
  • FIG. 7 discloses such apparatus.
  • the antenna disclosed therein is typical of either of the antennas shown by reference numeral 118 or 128 shown in FIG. 4B and comprises a section of a parabolic cylinder shown by reference numeral 146 coupled to the respective vertical support element 116 or 126.
  • the parabolic cylinder design is preferred because the antenna gain and bandwidth are the same as a parabolic antenna of similar diameter, however its main purpose is that the main beam is not attenuated. There is a beamwidth reduction in the vertical plane; however, this disadvantage is disregarded since the antenna pointing direction will be substantially in the horizontal plane.
  • the parabolic cylinder antenna size in the parabolic dimension is determined by the beamwidth desired and the gain requirements of the system. An antenna having a gain in the 23-25dbm range is desirable.
  • Table II is illustrative of the power gain in the effective area of other types of antenna configurations which might be utilized when desired.
  • the ground station is intended to serve as the master command and control for the entire airborne system attached to the respective balloon. These functions include the necessary electrical, mechanical and opera tional control of the system which includes among other things, steering and directional control of each of the antenna mounts including the respective cylindrical coaxial shaft and the intercoupling of information between selective antennas and the respective transmitter-receiver apparatus coupled thereto.
  • the ground station selectively intercouples the airborne antenna structure according to the specific requirements of the respective location. More particularly, all signals directed to and from the ground station 22 are coupled to and from the transmitter-receiver apparatus, of predetermined type signals, 82 by means of the transmission line 78 and the slip ring assembly 80.
  • signals transmitted to the airborne system appear at circuit means 146 which is coupled to a command and control assembly 150 mounted on the base 16 by means of an input harness assembly shown by reference numeral 148.
  • the command and control assembly 150 as well as the electronics apparatus attached to the mount 48 is adapted to receive suitable power supply potentials from a power supply attached to the base 16.
  • the command and control assembly 150 is adapted to selectively interconnect the transmitterreceiver apparatus 82, 100, 122 and 133 by means of an output harness 149 as well as coupling directional control signals for each of the antenna shafts which have been received from the ground station 22 by means of the apparatus 82.
  • each antenna assembly including the antennas 76, 94, 118 and 128 is maintained by respective servo control systems shown diagrammatically by reference numerals 152, 154, 156 and 158 coupled to the drive motors 66, 90, 102 and 104.
  • Each of the servo systems 152 158 is coupled to a respective flux gate compass system and synchro control transformer shown generally by reference numerals 160, 162, 164 and166 attached to the mounting ring 48 and which receive inputs from respective flux gate transmitter apparatus shown schematically by reference numeral 49 located at the ground station 22.
  • a flux gate transmitter and compass system is well known to those skilled in the art, an example of which is the Bendix type 15026.
  • the flux gate transmitter on the ground provides the heading signal which is coupled to the flux gate compass by means of the transceiver 82 and the command and control assembly 150.
  • the desired respective headings are manually set on the ground. Deviations in heading relative to magnetic North develop a signal voltage proportional in level and phase to the deviation from the magnetic North.
  • These control signals actuate the servo system connected to its respective drive motor which will rotate the concentric shaft to which it is coupled to the proper heading in azimuth.
  • a system of this type is easily able to control the directivity within :2.
  • each of the concentric cylindrical shafts 50 56 are independently oriented by means of the flux gate compass system 160 166 which receive individual heading signals from the ground station.
  • the updown link sends telemetric control signals to the command and control assembly 150 for controlling the transmission and reception to and from the transmitterreceiver apparatus 82, 100, 122 and 133.
  • apparatus 122 and 133 may be interconnected such that the antennas 128 coupled to the apparatus 133 are adapted to receive signals which are then coupled to apparatus 122 for transmission from antennas 118 in a long-line" relay communications such as shown in FIG. 10.
  • FIGS. 11 13 A more detailed illustrative embodiment is shown in FIGS. 11 13.
  • a local area communication signal for the surrounding line of sight coverage of the airborne system is coupled to and from the apparatus 100 which is coupled to the antennas 94.
  • any desired combination of interconnections can be made under the control of the ground station 22 via the up-down link including the transmitter-receiver 82 and the command and control assembly 150.
  • the configuration shown in FIG. 4A and 45 provides a very flexible communications system having a multi-channel flexibility with diversity of operation as well as individual selective orientation of each antenna configuration of the assembly as controlled from the ground station.
  • FIGS. 8 and 9 are illustrative of a typical multi-channel communications transmitter and receiver, respectively, adapted for use in combination with the apparatus shown in FIGS. 4A and 4B.
  • the ground station transmitter shown in FIG. 8 discloses a seven channel configuration with means provided for transforming it into a fourteen channel configuration when desirable.
  • Each input signal is coupled to a respective input terminal 168-1 168-7.
  • the input signal is applied to a wide band modulator 170-1 such as a spread spectrum generator or a video frequency UHF transmitter which produces a modulated output signal of for example a 70MI-Iz.
  • This signal is immediately mixed with a local oscillator frequency of for example 544MHz applied from crystal oscillator 171 shown in FIG. 9 in a mixer 172-1 which produces a working IF frequency of for example, 614MHz.
  • the IF signal is applied to a narrow band filter 174-1 to reject the local oscillator frequency and the image frequencies.
  • the output of the narrow band filter 174-1 is next applied to an IF amplifier 176-1 which provides a gain of, for example, +l3db.
  • the amplifier IF signal is then mixed with a second local oscillator signal in the mixer 178-1 coupled from a synthesizer circuit 177 shown in FIG. 9 to transform the 614MHz IF signal to an X-band RF frequency desired for the specific channel i.e. channel 1.
  • the other channels 2 through 7 would provide a different X-band local oscillator RF frequency as determined by the synthesizer outputs.
  • the X-band output of the mixer 178-1 is passed through an isolator 180-1 which provides an impedance match between the mixer 178-1 and a second narrow band filter 182-1.
  • the narrow band filter 182-1 rejects the second local oscillator frequency and the image frequencies.
  • the channel 1 X-band signal is now fed to a power amplifier 184-1 which may be, for example, a traveling wave tube (TWT) amplifier which has an approximate net gain of +50db.
  • TWT traveling wave tube
  • the X-band signal is passed through a third narrow band filter 186-1 to reject noise amplified by the traveling wave tube 184-1.
  • an isolator 188-1 and low pass filter 190-1 couple into an antenna feed 192-1 of a parabolic cylindrical antenna 194. Since seven input feeds 192-1 192-7 are illustrated, a system configuration comprised of 14 channels would couple into the other seven input feeds by means of a circulator 196-1 196-7 coupled intermediate the narrow band filter 186 and the isolator 188. In either configuration, the isolator 188-1 reduces the cross coupling between antenna feeds and the low pass filter 190-1 rejects channel harmonics.
  • a seven or 14 channel X-band RF- transmitter which is adapted to radiate RF signals to the airborne system via the updown" link antennas 76 for distribution by the command and control assembly 150 for coupling to one or more of the transmitter-receive apparatus respectively associated with the antennas 94, 118 or 128, as shown in FIGS. 4A and 4B.
  • the frequency synthesizer 177 is additionally adapted to provide the local oscillator frequencies for the receiver circuitry shown therein.
  • FIG. 9 also discloses a second crystal oscillator 198 which is adapted to provide a fixed frequency of, for example, 684MHz, and which will be discussed subsequently.
  • a parabolic antenna 204 having a gain in the range of 28db and a beamwidth of 6 is adapted to receive, for example, 14 separate channel RF signals in the X-band range which are fed to a wideband filter 206 and then to a' low noise RF amplifier 208 having an approximate gain of 35db and a noise figure of 6.5db. These signals are then passed through a second wideband filter 210 which is adapted to reject the noise due to the image frequencies. Following the wideband filter 210 an isolator 212 couples the X-band signals into a mixer 214 which is adapted to receive an X-band to S-band local oscillator signal from the synthesizer 177.
  • the output of the mixer 214 comprises 14 channels of S-band frequencies which are fed into a 14 way power splitter 216. Seven of the outputs are terminated in substantially identical resistive load impedances 218 while the remaining 7 signals are fed to seven separate channel circuits.
  • Each receiver channel circuit for example channel 1, includes a narrow band filter 220-1 which is adapted to have a MI-Iz bandwidth for one channel of S-band frequency while rejecting the adjacent channel center frequency by not less than 35db.
  • the output of the narrow band filter 220-1 is fed to a 24db IF amplifier 222-1.
  • the output of the IF amplifier 222-1 is applied to the mixer 224-1 which receives a S-band to UHF local oscillator signal from the synthesizer 177, which produces a working IF frequency of for example, 614MHz.
  • This IF signal is passed through a 3db matching pad 226-1 and then to a second narrow band filter 228-1 which rejects the local oscillator frequencies.
  • the 614MHz UHF IF frequency is next amplifier by an IF amplifier 230-1 including automatic gain control (AGC).
  • AGC automatic gain control
  • the output of the IF amplifier 230-1 is next coupled to a second mixer 232-1 through a 6db matching pad 234-1.
  • the mixer 232-1 receives either a 544MHz signal from the crystal oscillator 171 or a 684MHz signal from the crystal oscillator 198 coupled thereto through a switch 200.
  • the 554MHz signal applied to the switch 200 is identified as the NOR or normal receive signal while the 684MHz signal is labeled the INV or invert signal, for purposes of which will be explained subsequently.
  • the output of the mixer 232 provides an IF signal which is in the range of 70MHz, which is applied to a suitable demodulator circuit 238-1 through a low pass filter 240-1.
  • the output of the demodulator 238 appears at terminal 242-1 and constitutes the desired output signal.
  • the two crystal oscillators 171 and 198 are utilized which are adapted to be 70MHz below and 70M Hz above respectively the working IF frequency of 614MHz.
  • the proper LO frequency is selected by means of the switch 236. It should be pointed out, however, that in signal transmission, this facility is not required and therefore only a single frequency, i.e.
  • 544MHz is applied to the apparatus shown in FIG. 8 from the crystal oscillator 171.
  • the additional receiving channels which are adapted to be coupled to the power splitter 216, rcplace the load resistors 218 shown.
  • the frequencies provided by the synthesizer 198 depend upon the desired system configuration. For example, 14 transmitters require one set of local oscillator frequencies while the 14 receiver circuits require a different set of local oscillator frequencies and an odd number of hops between terminus stations will require a different set of transmitter or receiver local oscillator frequencies.
  • FIG. 10 there is disclosed therein a typical airborne long-line relay subsystem incorporating the apparatus shown in FIGS. 4A and 4B which for example utilizes the antennas 128 as the receiving antennas and the antennas 118 as the transmitting antennas.
  • Each of the antennas respectively are coupled to the transmitter-receiver apparatus 134 and 122 each of which includes receiver apparatus shown more particularly in FIG. 11 and transmitter apparatus which is shown more particularly in FIG. 12 and wherein both apparatus includes up to fourteen channels.
  • the respective receiver and transmitter elements contained in each of the transmitter-receiver apparatus 122 and 133 is innerconnected through the command and control assembly so that proper innerconnection can be made for selectively utilizing either the receiver or the transmitter portions of the apparatus 133 and 122.
  • a synthesizer 202 is also included for providing at least five local oscillator frequencies for proper operation of the subsystem. Additionally, the up-down transmitter-receiver apparatus 82 connected to the spiral antenna means 76 is also coupled into the command and control assembly 150 and includes apparatus for providing one local drop channel, one or two insert channels plus one monitoring channel which is shown in more detail in FIG. 13.
  • the receiver portion of the airborne transmitterreceiver apparatus 122 and 133 shown in FIG. 11 is identical to the ground terminus receiver means shown in FIG. 9 from the wideband filter 206 up to the IF amplifier 230 having AGC for the channels 1 through 7.
  • the output of the IF amplifier 230-1 in FIG. 11 is fed into a two-way power splitter 242-1, the outputs of which are coupled to two identical matching pads 244-1 and 246-1.
  • the signal from the pads 244-1 is fed to the command and control assembly 150 for coupling to transmitter apparatus shown in FIG. 12 while the output from the pad 246-1 is adapted to be coupled to a l X 14 RF switch 248 coupled to the monitor and telemetry channel in the up-down" transmitter-receiver apparatus shown in FIG. 13.
  • the airborne transmitter apparatus shown in FIG. 12 is substantially identical to the ground based transmitter shown in FIG. 8 from the first IF amplifiers 176-1 176-7 to the low pass filters -1 190-7 which couple to the respective radiating antenna. It is to be noted that the input to the respective IF amplifiers 176-1, etc. are coupled back to the command and control assembly for innerconnection to the airborne receiver apparatus shown in FIG. 11 and briefly described above.
  • the synthesizer 202 is adapted to couple the required local oscillator frequencies as shown in FIGS. 11 and 12 so that multi-channel signal input and output translation occurs between the antenna 128 and 118 as shown in FIG. 10.
  • the airborne up-down transmitter-receiver apparatus 82 noted in FIG. as well as FIG. 4A. It includes circuit means for providing a local drop channel, a local insert channel, and a monitor and telemetry channel to the ground station via the spiral antenna means 76.
  • the local drop channel comprises apparatus substantially identical to the airborne transmitter apparatus shown in FIG. 12 and is shown comprising the elements 176' 190' which includes the apparatus from the IF amplifier to the low pass filter.
  • the input to the IF amplifier 176 is selectively coupled to one of the seven channel signals appearing at a selected output pad 246-1 246-7 which is coupled thereto through the command and control assembly 150.
  • the channel signal to be dropped to the ground station is coupled to the antenna means 76 from the low pass filter 190.
  • the local insert channel apparatus shown in FIG. 13 is substantially identical to the airborne receiver apparatus shown in FIG. 12 with the exception that the wideband filters 206 and 210 have been replaced by narrow band filters 207 and 209. Also in place of the 14 way power splitter 216 shown in FIG. 11 the apparatus shown in FIG. 13 employs a two way power splitter 215, one output of which is fed to the narrow band filter 220 while the other output is coupled to a narrow band filter 250 which couples into a mixer 252 which receives a command local oscillator frequency from the synthesizer 202. The output of the mixer 252 is fed into another narrow band filter 254 and then into an amplifier 256.
  • the output of the amplifier 256 is coupled into a limiter and discriminator 258 for obtaining command signals which are fed to a logic circuit 260 which couples into the command and control assembly150.
  • the insert signal which is fed to the amplifier 230 and the pad 246 is coupled into the command and control assembly 150 for selective coupling to one of the airborne transmitter inputs shown in FIG. 12.
  • the command information which is decoded in the logic 250 and fed into the command and control assembly 150 feeds back a control signal to the l X 14.
  • RF switch 248 by means of a circuit lead 262 which selectively controls the RF switch to select one of the channel inputs from the airborne receiver apparatus shown in FIG. 11.
  • the output is then coupled into transmitter circuitry 176" 190" which is substantially identical to the airborne transmitter apparatus shown in FIG. 12 with the exception that a coupler 262 is adapted to insert a telemetry signal coupled thereto from telemetry logic circuitry contained in the command and control assembly 150.
  • This signal is applied through a modulator circuit 264, a mixer 266 which receives a telemetry local oscillator frequency from the synthesizer 202 and an IF amplifier 268.
  • the monitor and telemetry channel'apparatus is adapted to couple information from the low pass filter 190" to the spiral antenna means 76 for transmission to the ground station.
  • the system disclosed is adapted to operate in any desired mode or frequency range of electromagnetic signal transmission and reception.
  • the system adapted to handle multi-channel X-band signal transmission as shown in FIGS. 8 13, but is also adapted to handle standard AM and FM radio broadcasting as well as television transmission wherein amplitude modulation of one carrier is utilized for video transmission while the audio transmission occurs as FM modulation of a second carrier.
  • amplitude modulation of one carrier is utilized for video transmission while the audio transmission occurs as FM modulation of a second carrier.
  • UHF and VHF operation can also be mechanized.
  • Other types of information handling are also contemplated e.g., telegraphy, telephony, facsimile, multichannel multiplex voice frequency telegraphy, and analog/digital computer data, etc.
  • the present system can tie into any existing conventional network or information distribution system.
  • the present invention is particularly useful in that it permits an advance modern complex information handling and distribution network system to be provided in a very short time and at a very low cost.
  • simple conventional low cost electrical elements can be utilized in assembling of a ground satellite station such that equipment costs are comparable to normal high quality roof top mounted and driven antennas or a receiver elements in home use at present.
  • airborne apparatus for providing a mounting platform for electronic transmitting and receiving apparatus
  • a gravity stabilized antenna assembly suspended from said airborne apparatus, said antenna assembly being comprised of (a) a mounting base attached to the underside of said airborne apparatus including a ball-joint housing depending therefrom, said housing having a downwardly depending side portion and a lower end portion having a circular means, and (3) a communication air-toair relay link along a substantially horizontal direction by at least one-of yet another of said antenna means.
  • said side portion also including an inwardly projecting ball bearing mount intermediate its length and a tapered race type ball bearing assembly having a concave bearing surface affixed thereto, a spherical member of predetermined di- 4.
  • directional control means includesaflux gate transmitsaid diameter being of such a magnitude that the ter at said ground station for providing a compass headcenter of the sphere is located above the uppering signal for each of said antenna means via said upmost contact point between the spherical member down link and wherein each of said selected coaxial and the ball bearing assembly, said opening addishafts is coupled to a flux gate compass system and adtionally having an inwardly angulated circular ditionally including means responsive to the output of damper member affixed thereto the outer surface said compass system to rotate said shaft in a predeterof which defines a hypothetical cone having an mined direction in accordance with said
  • pendulum arm member attached to one extremity 5.
  • said to said spherical member and projecting through last-recited means comprises an electrical drive motor said damper member and being suspended there- 29 and an electrical servo system coupled between said from in substantially vertical alignment, (c) a supflux gate compass system and said drive motor for conport member attached to the other extremity of trolling the operation of said drive motor.
  • said arm member and (d) a plurality of coaxial cy- 6.
  • said lindrical shafts which are independently rotatable signal transmitter-receiver apparatus includes means about the central longitudinal axis thereof mounted for multi-channel electrical signal communications. on said support member and wherein selected 7.
  • selected 7. In an electromagnetic signal communication sysshafts of said plurality of shafts each additionally tem,
  • independent transmitter-receiver means and slip ring coupling means integral with said selected shafts coupled to the respective transmission line means at the other end of the respective shaft for receiving or transmitting signals to the respective antenna means;
  • circuit means located on each said aircraft being responsive to said second control signal transmitted from said ground station to selectively operate each said transmitter-receiver means to relay communication signals between adjacent tethered aircraft and 'to provide communication signal transfer between the respective ground stations and aircraft.
  • said plurality of aircraft are comprised of lighter than air balloons and wherein said ground station additionally includes means for controlling the height of the respective balloons as well as means for monitoring the condition thereof.
  • said first recited means comprises a tether cable and wherein said tether cable includes means for coupling electrical power from said ground station to said antenna platform.
  • said at least one of said antenna means comprises a first type antenna
  • said at least one other antenna means comprises a second type antenna
  • said at least one yet another antenna means comprises a third type antenna.
  • said first type antenna comprises a spiral antenna
  • said second type antenna comprises a dish type antenna
  • said third type antenna comprises a parabolic cylindrical type antenna
  • said means for transmitting and receiving a plurality of electrical signals comprises a multi-channel transmitter and a multichannel receiver of microwave signals.

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  • Engineering & Computer Science (AREA)
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  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Signal Processing (AREA)
  • Radio Relay Systems (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
US00102597A 1970-12-30 1970-12-30 Tethered airborne communications and information transfer system Expired - Lifetime US3742358A (en)

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Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4491846A (en) * 1981-02-25 1985-01-01 Salzgitter Maschinen Und Anlagen Aktiengesellschaft Arrangement for holding a plurality of vertically superimposed antennas for rotary adjustment
US4607389A (en) * 1984-02-03 1986-08-19 Amoco Corporation Communication system for transmitting an electrical signal
US5645248A (en) * 1994-08-15 1997-07-08 Campbell; J. Scott Lighter than air sphere or spheroid having an aperture and pathway
US5734716A (en) * 1995-09-29 1998-03-31 Qualcomm Incorporated Magnetically driven vertically correcting antenna for portable telephones
WO1998051568A1 (en) * 1997-05-16 1998-11-19 Spherecore, Inc. Aerial communications network
US5844985A (en) * 1995-09-22 1998-12-01 Qualcomm Incorporated Vertically correcting antenna for portable telephone handsets
US5949766A (en) * 1996-12-30 1999-09-07 Motorola, Inc. Ground device for communicating with an elevated communication hub and method of operation thereof
US6018659A (en) * 1996-10-17 2000-01-25 The Boeing Company Airborne broadband communication network
US6072524A (en) * 1997-04-07 2000-06-06 The Boeing Company Electronic observation post with communications relay
US6151308A (en) * 1996-12-30 2000-11-21 Motorola, Inc. Elevated communication hub and method of operation therefor
EP1058409A1 (de) * 1999-06-03 2000-12-06 Contraves Space AG Netz und Verfahren zur drahtlosen Datenkommunikation mittels Flugrelaissationen
US6396233B1 (en) * 2000-09-05 2002-05-28 The United States Of America As Represented By The Secretary Of The Navy Ball joint gimbal system
WO2002061971A1 (en) * 2001-02-01 2002-08-08 Skylinc Limited Communication system using an aerostat tethered above the earth surface and linked to a base station by an optical fibre
US20030040273A1 (en) * 1993-07-30 2003-02-27 Seligsohn Sherwin I. Sub-orbital, high altitude communications system
US20030109281A1 (en) * 2001-04-18 2003-06-12 Knoblach Gerald M. Unmanned lighter-than-air safe termination and recovery methods
US6628941B2 (en) 1999-06-29 2003-09-30 Space Data Corporation Airborne constellation of communications platforms and method
US20030236070A1 (en) * 2002-06-25 2003-12-25 Seligsohn Sherwin I. Sub-orbital, high altitude communications system
US20040008637A1 (en) * 1993-07-30 2004-01-15 Seligsohn Sherwin I. High efficiency sub-orbital high altitude telecommunications system
US20040198346A1 (en) * 2003-04-02 2004-10-07 The Boeing Company Aircraft based cellular system
US20040253951A1 (en) * 2003-04-02 2004-12-16 The Boeing Company Induced cellular communications handover
US20040253949A1 (en) * 2003-04-02 2004-12-16 The Boeing Company Platform-associated visitor location registers (VLR) for cellular communications
US20050014499A1 (en) * 1999-06-29 2005-01-20 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US20060009262A1 (en) * 2004-07-09 2006-01-12 The Boeing Company Avionic base station controller (ABSC) for aircraft-based cellular communications
US20090232337A1 (en) * 2008-03-17 2009-09-17 Chia-Lun Tang Method for improving compatibility of hearing aid with antenna
US20110175604A1 (en) * 2010-01-15 2011-07-21 Vale S.A. Stabilization system for sensors on moving platforms
US20130175391A1 (en) * 2012-01-09 2013-07-11 Google Inc. Relative Positioning of Balloons with Altitude Control and Wind Data
US9281554B1 (en) * 2013-04-16 2016-03-08 Google Inc. Balloon with pressure mechanism to passively steer antenna
US9632503B2 (en) 2001-04-18 2017-04-25 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US9643706B2 (en) 2001-04-18 2017-05-09 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
WO2017105657A1 (en) * 2015-12-16 2017-06-22 Skycom Corporation Lighter-than-air platform
US9692497B2 (en) * 2015-02-12 2017-06-27 Sharper Shape Oy Tethered airborne device
US9908608B2 (en) 2001-04-18 2018-03-06 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US10059421B2 (en) 2014-12-30 2018-08-28 Space Data Corporation Multifunctional balloon membrane
US10207802B2 (en) 2014-12-24 2019-02-19 Space Data Corporation Breaking apart a platform upon pending collision
US10403160B2 (en) 2014-12-24 2019-09-03 Space Data Corporation Techniques for intelligent balloon/airship launch and recovery window location
WO2019199182A1 (en) * 2018-04-11 2019-10-17 Sultan Qaboos University System and method for automatically controlling communication sector of antennas configured with tethered balloon
US10574341B1 (en) * 2015-10-13 2020-02-25 Loon Llc Channel reconfigurable millimeter-wave RF system

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3224183A1 (de) * 1982-06-29 1984-01-12 Siemens AG, 1000 Berlin und 8000 München Schaltungsanordnung zur durchfuehrung einer selektiven nachrichtenuebermittlung
ES2137887B1 (es) * 1995-06-07 2000-08-16 Int Multi Media Corp Sistema de comunicacion sub-orbital de gran altitud.
RU2176852C2 (ru) * 2000-01-06 2001-12-10 Прушковский Олег Владимирович Система передачи информации (варианты)
RU2208296C2 (ru) * 2001-02-07 2003-07-10 Открытое акционерное общество "Научно-производственное объединение "Алмаз" им. акад. А.А.Расплетина" Кластерная телекоммуникационная система
RU2238613C2 (ru) * 2002-06-05 2004-10-20 Федеральное государственное унитарное предприятие "Научно-исследовательский институт микроэлектронной аппаратуры "Прогресс" Устройство приема и передачи асинхронных последовательных данных
RU2247472C2 (ru) * 2002-10-25 2005-02-27 Хусаинов Владимир Римович Способ радиосвязи между подвижными объектами, маршруты движения которых имеют общий начальный пункт
RU2244379C2 (ru) * 2002-10-25 2005-01-10 Хусаинов Владимир Римович Способ радиосвязи между подвижными объектами, маршруты движения которых имеют общий начальный пункт
RU2239947C2 (ru) * 2002-10-25 2004-11-10 Хусаинов Владимир Римович Способ радиосвязи между подвижным объектом и неподвижным объектом, находящимся в начальном пункте маршрута движения подвижного объекта
RU2240654C2 (ru) * 2002-10-25 2004-11-20 Хусаинов Владимир Римович Способ радиосвязи между подвижным объектом и неподвижным объектом, находящимся в начальном пункте маршрута движения подвижного объекта
RU2244376C2 (ru) * 2002-10-25 2005-01-10 Хусаинов Владимир Римович Способ радиосвязи между подвижными объектами, маршруты движения которых имеют общий начальный пункт
RU2244377C2 (ru) * 2002-10-25 2005-01-10 Хусаинов Владимир Римович Способ радиосвязи между подвижным объектом и неподвижным объектом, находящимся в начальном пункте маршрута движения подвижного объекта
RU2250568C2 (ru) * 2002-10-25 2005-04-20 Хусаинов Владимир Римович Способ радиосвязи между подвижным объектом и неподвижным объектом, находящимся в начальном пункте маршрута движения подвижного объекта
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DE102009036504A1 (de) * 2009-08-07 2011-02-17 Rheinmetall Defence Electronics Gmbh Relaiseinheit

Cited By (71)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4491846A (en) * 1981-02-25 1985-01-01 Salzgitter Maschinen Und Anlagen Aktiengesellschaft Arrangement for holding a plurality of vertically superimposed antennas for rotary adjustment
US4607389A (en) * 1984-02-03 1986-08-19 Amoco Corporation Communication system for transmitting an electrical signal
US8483120B2 (en) 1993-07-30 2013-07-09 Sherwin I. Seligsohn High efficiency sub-orbital high altitude telecommunications system
US7567779B2 (en) 1993-07-30 2009-07-28 International Multi-Media Corporation Sub-orbital, high altitude communications system
US20060063529A1 (en) * 1993-07-30 2006-03-23 Seligsohn Sherwin I Sub-orbital, high altitude communications system
US7844218B2 (en) * 1993-07-30 2010-11-30 International Multi-Media Corporation Sub-orbital, high altitude communications system
US20030040273A1 (en) * 1993-07-30 2003-02-27 Seligsohn Sherwin I. Sub-orbital, high altitude communications system
US20060003698A1 (en) * 1993-07-30 2006-01-05 Seligsohn Sherwin I Sub-orbital, high altitude communications system
US20040008637A1 (en) * 1993-07-30 2004-01-15 Seligsohn Sherwin I. High efficiency sub-orbital high altitude telecommunications system
US5645248A (en) * 1994-08-15 1997-07-08 Campbell; J. Scott Lighter than air sphere or spheroid having an aperture and pathway
US5844985A (en) * 1995-09-22 1998-12-01 Qualcomm Incorporated Vertically correcting antenna for portable telephone handsets
US5734716A (en) * 1995-09-29 1998-03-31 Qualcomm Incorporated Magnetically driven vertically correcting antenna for portable telephones
US6018659A (en) * 1996-10-17 2000-01-25 The Boeing Company Airborne broadband communication network
US6151308A (en) * 1996-12-30 2000-11-21 Motorola, Inc. Elevated communication hub and method of operation therefor
US5949766A (en) * 1996-12-30 1999-09-07 Motorola, Inc. Ground device for communicating with an elevated communication hub and method of operation thereof
US6072524A (en) * 1997-04-07 2000-06-06 The Boeing Company Electronic observation post with communications relay
WO1998051568A1 (en) * 1997-05-16 1998-11-19 Spherecore, Inc. Aerial communications network
US6167263A (en) * 1997-05-16 2000-12-26 Spherecore, Inc. Aerial communications network including a plurality of aerial platforms
EP1058409A1 (de) * 1999-06-03 2000-12-06 Contraves Space AG Netz und Verfahren zur drahtlosen Datenkommunikation mittels Flugrelaissationen
US9964629B2 (en) 1999-06-29 2018-05-08 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US8825232B2 (en) 1999-06-29 2014-09-02 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US20080299990A1 (en) * 1999-06-29 2008-12-04 Space Data Corporation Systems and applications of lighter-than-air (lta) platforms
US20050014499A1 (en) * 1999-06-29 2005-01-20 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US9519045B2 (en) 1999-06-29 2016-12-13 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US6628941B2 (en) 1999-06-29 2003-09-30 Space Data Corporation Airborne constellation of communications platforms and method
US10429489B2 (en) 1999-06-29 2019-10-01 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US7356390B2 (en) 1999-06-29 2008-04-08 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US6396233B1 (en) * 2000-09-05 2002-05-28 The United States Of America As Represented By The Secretary Of The Navy Ball joint gimbal system
WO2002061971A1 (en) * 2001-02-01 2002-08-08 Skylinc Limited Communication system using an aerostat tethered above the earth surface and linked to a base station by an optical fibre
US7801522B2 (en) 2001-04-18 2010-09-21 Space Data Corporation Unmanned lighter-than-air safe termination and recovery methods
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US7203491B2 (en) 2001-04-18 2007-04-10 Space Data Corporation Unmanned lighter-than-air safe termination and recovery methods
US9643706B2 (en) 2001-04-18 2017-05-09 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US9632503B2 (en) 2001-04-18 2017-04-25 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US20030109281A1 (en) * 2001-04-18 2003-06-12 Knoblach Gerald M. Unmanned lighter-than-air safe termination and recovery methods
US10710695B2 (en) 2001-04-18 2020-07-14 Space Data Corporation Systems and applications of lighter-than-air (LTA) platforms
US9823663B2 (en) 2001-04-18 2017-11-21 Space Data Corporation Unmanned lighter-than-air-safe termination and recovery methods
US8644789B2 (en) 2001-04-18 2014-02-04 Space Data Corporation Unmanned lighter-than-air-safe termination and recovery methods
US20030236070A1 (en) * 2002-06-25 2003-12-25 Seligsohn Sherwin I. Sub-orbital, high altitude communications system
US7558569B2 (en) 2003-04-02 2009-07-07 The Boeing Company Induced cellular communications handover
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US8325955B2 (en) * 2008-03-17 2012-12-04 Auden Techno Corp. Method for improving compatibility of hearing aid with antenna
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US8456159B2 (en) * 2010-01-15 2013-06-04 Vale S.A. Stabilization system for sensors on moving platforms
US20110175604A1 (en) * 2010-01-15 2011-07-21 Vale S.A. Stabilization system for sensors on moving platforms
US20130175391A1 (en) * 2012-01-09 2013-07-11 Google Inc. Relative Positioning of Balloons with Altitude Control and Wind Data
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US9281554B1 (en) * 2013-04-16 2016-03-08 Google Inc. Balloon with pressure mechanism to passively steer antenna
US10403160B2 (en) 2014-12-24 2019-09-03 Space Data Corporation Techniques for intelligent balloon/airship launch and recovery window location
US10696400B2 (en) 2014-12-24 2020-06-30 Space Data Corporation Breaking apart a platform upon pending collision
US10207802B2 (en) 2014-12-24 2019-02-19 Space Data Corporation Breaking apart a platform upon pending collision
US10059421B2 (en) 2014-12-30 2018-08-28 Space Data Corporation Multifunctional balloon membrane
US10689084B2 (en) 2014-12-30 2020-06-23 Space Data Corporation Multifunctional balloon membrane
US9692497B2 (en) * 2015-02-12 2017-06-27 Sharper Shape Oy Tethered airborne device
US10574341B1 (en) * 2015-10-13 2020-02-25 Loon Llc Channel reconfigurable millimeter-wave RF system
US10367447B2 (en) 2015-12-16 2019-07-30 Skycom Corporation Lighter-than-air aircraft and method to reduce leakage within a flexible bladder
EA035059B1 (ru) * 2015-12-16 2020-04-22 Скайком Корпорейшн Аэростатический летательный аппарат
CN108473190A (zh) * 2015-12-16 2018-08-31 天空通讯公司 轻于空气的平台
WO2017105657A1 (en) * 2015-12-16 2017-06-22 Skycom Corporation Lighter-than-air platform
WO2019199182A1 (en) * 2018-04-11 2019-10-17 Sultan Qaboos University System and method for automatically controlling communication sector of antennas configured with tethered balloon

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DE2327498A1 (de) 1974-12-12
DE2327498C2 (de) 1982-06-09
GB1431485A (en) 1976-04-07
FR2234719A1 (enExample) 1975-01-17

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