CN1422447A - Mobile radio communication system - Google Patents
Mobile radio communication system Download PDFInfo
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- CN1422447A CN1422447A CN01807848A CN01807848A CN1422447A CN 1422447 A CN1422447 A CN 1422447A CN 01807848 A CN01807848 A CN 01807848A CN 01807848 A CN01807848 A CN 01807848A CN 1422447 A CN1422447 A CN 1422447A
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- antenna
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- earth station
- ground
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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
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/12—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems
- H01Q3/16—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems for varying relative position of primary active element and a reflecting device
- H01Q3/18—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems for varying relative position of primary active element and a reflecting device wherein the primary active element is movable and the reflecting device is fixed
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/22—Supports; Mounting means by structural association with other equipment or articles
- H01Q1/24—Supports; Mounting means by structural association with other equipment or articles with receiving set
- H01Q1/241—Supports; Mounting means by structural association with other equipment or articles with receiving set used in mobile communications, e.g. GSM
- H01Q1/246—Supports; Mounting means by structural association with other equipment or articles with receiving set used in mobile communications, e.g. GSM specially adapted for base stations
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/12—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems
- H01Q3/16—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems for varying relative position of primary active element and a reflecting device
- H01Q3/20—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems for varying relative position of primary active element and a reflecting device wherein the primary active element is fixed and the reflecting device is movable
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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
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04W—WIRELESS COMMUNICATION NETWORKS
- H04W16/00—Network planning, e.g. coverage or traffic planning tools; Network deployment, e.g. resource partitioning or cells structures
- H04W16/24—Cell structures
- H04W16/28—Cell structures using beam steering
Abstract
This disclosure provides a communication system using a high-altitude aircraft traveling at relatively slow speeds, which can remain airborne for long periods of time. The communication system uses the airplane as a long term high altitude platform that relays signals between one or more ground-stations and/or satellites, aircraft, and the like. The ground-stations have narrow-beam antennas that are aimable, permitting the aircraft to maintain a larger station than would otherwise be possible using the narrow-beam antennas. The ground-stations adjust their aim based on information either gained by tracking the aircraft's signal, or transmitted by the aircraft to the ground-station.
Description
The application requires the U.S. Provisional Patent Application of application on April 14th, 2000, the priority of sequence number 60/197,799, and it is incorporated in herein as a reference for general purpose.
Technical field
The present invention relates to wireless communication system, relate in particular to the wireless communication system that a kind of use has the aircraft of one or more ground stations.
Background technology
The needs that to high bandwidth, closely connect voice-and-data string terminal use promptly increase for a long time.This needs that communication capacity is increased both had been present in the urban area with solid communication infrastructure, were present in the zone of the less exploitation that lacks above-mentioned foundation structure again.Signal of communication can be transmitted to the terminal use by the communication system of number of different types.Wired, land system usually provides high-speed communication for very big bandwidth signal.But the foundation structure that is used for said system is expensive, and builds, safeguards and upgrading is time-consuming, with and can not support mobile communication individually.Use the wireless system that transmits tower to provide the quite communication of high speed for each available more limited in fact bandwidth in area.
Geostationary Earth's orbit (GEO) satellite (being in about 36,000 kilometers height) also can provide radio communication to the terminal use, but because it is highly very high, is limited as bandwidth efficiency.Even the narrow beam antenna that is installed in above-mentioned distance has very big land surface.Therefore, the GEO satellite is restricted with the ability that high-bandwidth communication of providing need be provided in most of zones for it, especially for densely populated areas.And the GEO satellite must be in the equatorial orbit, and this has limited its practical use for position, area, equator.
In and Low Earth Orbit (MEO and LEO) satellite system (respectively 10,000 kilometers and 700-1500 kilometer height) be actually complicated because the terminal use need have the equipment that tracking satellite is crossed the relative motion of sky.Asynchronous satellite needs intricately, adjusts directional antenna continuously,, can fixedly run through very big angle by enough gimbals that is.These antenna not only aloft but also had on the ground needed, and typically because ground-plane antenna has the auxiliary antenna system, was suitable for transmitting satellite from one and switched signal of communication to the next one.Certainly, above-described satellite neither one is to regain easily, for example, is used for maintenance.
Aircraft uses in application miscellaneous, comprises travelling, transportation, fire fighting, survelillance and fight.Aircraft can be used for relaying signal of communication.Being used for the ground station of such use will be typically or need arrowband, omnidirectional antenna or big universal angular properties (being similar to the ground station that is used for MEO or LEO satellite), even because make circular motion, and the above-mentioned aircraft real distance of will moving.
Unfortunately, the gimbal-mounted earth station equipment of standard is expensive, is damaged easily and weares and teares.Use wide-angle or omnidirectional antenna can avoid using gimbals.But big broadcast angle needs secondary power, the more important thing is the repeated use that has limited near ground station and/or near aircraft frequency.Therefore, to utilize wide-angle or omnidirectional antenna be restricted to this wide bandwidth systems.
Above-described have or the exception of the requirement of the gimbals of wide broadcast angle or wide-angle is for antenna, this aircraft can be very little aloft the position for holding position for a long time, that is, as a long duration, suborbital High Altitude Platform.An aircraft like this is in U.S. Patent No. 5,810, describes in 284.This Flight Vehicle Structure includes known pioneer, centurion and Apollo aircraft.
These aircraft can be in the long-time holding position of stratospheric height, allow ground station use fixing, narrow beam antenna (for example, except simple one be used for initial blip steady do not have 2 ° or 3 ° of bandwidth antennas of steering mechanism).These narrow beam antennas allow between a plurality of ground stations and given aircraft, and carry out channeling between the ground station ground station of adjacency (perhaps near) and a plurality of aircraft.But such aircraft may consume great resource (that is power) remaining the so necessary firm position of narrow beam antenna of use.This power had both consumed in firm operation, consumed again in the quick compensation for instantaneous variation under the local flying condition.
Wish to go to develop a kind of communication system of high-bandwidth signals that provide to a lot of cheapnesss, durable ground station.Different embodiment of the present invention can satisfy some of these needs or all, and advantages associated further is provided.
Summary of the invention
In different embodiment, the present invention has big flight station by a kind of aircraft that provides is provided, and still has the communication system of using narrow beam earth station antenna advantage simultaneously, some that solution needs as mentioned above or whole.
Communication repeating of the present invention system typically comprises an aircraft and a plurality of ground station, and this aircraft is used for reradiated signal.This aircraft is configured to control the position within the flight place of appointment, and the flight place of this appointment only is the part in the visual field on the ground, and the visual field can comprise a plurality of other potential flight places on this ground.This aircraft comprises a communication relay module, and this communication is relayed module and had one or more antennas of communicating by letter with ground station.This ground station is located in the area of coverage, and each ground station has at least one configuration via communicate by letter with this antenna of at least one communication of relay module antenna of signal of communication.
Very narrow of the beamwidth that characteristics of the present invention are these earth station antennas makes it be not enough to the whole flight place of irradiation (that is, send to and/or therefrom receive) simultaneously.Because can running through this flight place, moves by this aircraft, it is steerable that each earth station antenna is configured under the control of an antenna controller, make and to run through in this flight place moves when this aircraft that this earth station antenna can keep the relay module communication of communicating by letter with this aircraft.This antenna controller is configured to limit the manipulation of antenna, makes that it avoids aiming at this antenna in any flight place except the flight place of this appointment.
Advantageously, have the earth station antenna that enough big beamwidth goes to shine whole flight place and compare with having, most of embodiment with these characteristics will have low power as earth station antenna to be used, and will have crosstalk still less for the adjacent communication of use same frequency.In addition, compare with the very little flight place of fully being shone by the narrow beam earth station antenna, operation and consumption energy still less that this aircraft will be carried out still less go to the holding position.
Other characteristics of the present invention are that this position of aircraft information is sent to ground station and/or by ground station's reception, receives this information thereby allow this ground station to need not to make its antenna correctly to aim at this aircraft from aircraft use wide wave beam or omnidirectional antenna.
From below in conjunction with the DETAILED DESCRIPTION OF THE PREFERRED of the accompanying drawing of following to invention, for example, illustrate principle of the present invention, other feature and advantage of the present invention will become apparent.As statement below, allow to set up and use embodiments of the invention, the detailed description of specific preferred embodiment is not intended to limit the claim of enumerating, but has been used for advocating the effect of specific examples of the present invention.
Description of drawings
Fig. 1 is an illustrative view of implementing the preferred embodiment of communication system of the present invention.
Fig. 2 A is the front view of an aircraft that uses in the communication system that Fig. 1 describes.
Fig. 2 B is a vertical view at the aircraft of Fig. 2 A description.
Fig. 3 is another the illustrative view in the communication system of Fig. 1 description.
Fig. 4 be one in the communication system that Fig. 1 describes, use, the front view in the flight place on a plurality of ground stations.
Fig. 5 be one in the communication system that Fig. 1 describes, use, the plane graph in a series of flights place.
Fig. 6 be one in the communication system that Fig. 1 describes, use, the plane graph of a series of ground levels illuminations by overlapping aircraft antenna beam, this aircraft antenna beam is limited to the sub-district in the area of coverage.
Fig. 7 be one in the communication system that Fig. 1 describes, use, the front view of the aircraft of surface antenna aiming in the flight place directionally.
Fig. 8 A be one in the ground station of the communication system of describing at Fig. 1, use in, the diagrammatic depiction of first embodiment of steerable antenna.
Fig. 8 B be one in the ground station of the communication system of describing at Fig. 1, use in, the diagrammatic depiction of second embodiment of steerable antenna.
Embodiment
By the reference following detailed description, the present invention that can understand above-mentioned summary better and limit by the claim of enumerating, this detailed description should be read in conjunction with the accompanying drawing of following.As statement below, allow to set up and use embodiments of the invention, the detailed description of this communication system specific preferred embodiment is not intended to limit the claim of enumerating, but is used to provide its specific example.
With reference to figure 1, implement communication system of the present invention and comprise one or more ground stations 102, one or more aircraft 104, and preferably one or more satellite 106.This ground station is arranged in sub-district 108, and this sub-district 108 is aimed at by the directive antenna of aircraft.Each aircraft is by at stratospheric height, and for example, between the height of 50,000 feet and 70,000 feet, control is within a limited flight place.Preferably, each flight place is the same with another place of flying is set at identical height.This aircraft uses single channel or duplex communication signal to go to relay ground station and communicates by letter to other ground station and/or satellite network.
Aircraft
The present invention preferably includes the geostationary substantially platform that uses an aircraft to require as the control position with stable strong.According to the present invention, this preferred aircraft has the structure that is similar to pioneer, centurion and/or Apollo aircraft.Though the structure of preferred aircraft is described below, more details is provided in U.S. Patent No. 5,810, and in 284, it is incorporated in herein as a reference.However, should be understood that other aircraft, all fall within the scope of the invention such as the aircraft of helicopter, balloon, blimp, kite or other type.
With reference to figure 1,2A and 2B, preferred aircraft 104 embodiment are air wing's aircrafts, that is, it does not have fuselage or empennage.But it has along the span compatible substantially wing shapes and big or small straight wing 112 by one forms.Preferably, six, eight or 14 motor 114 are positioned on the diverse location along the span, and the single screw 116 of each motor-driven goes to produce and advances.Preferably, vertically stabilizing the wing or gondola 118a-118d for two, four or five extends downwards from wing at its low side with the landing device.
This preferred aircraft 104 is a solar energy, and comprises that fuel tank goes storage power to be used for continuously day and night flying.Therefore, it is suitable for continuously in theory, unpiloted flight is more than one thoughtful ten day, (for example, 200 hours), further preferably 3000 hours or longer.In other words, can be designed to can be from the fuel of hydrogen fuel (such as being used for or the liquified hydrogen of fuel cell or conventional internal combustion engine), fossil fuel or other storage, perhaps obtains its some or whole energy such as by day solar energy and the combination of storing the fuels sources of the non-removable or removable fuel of part at night.
This aircraft 104 preferably sequentially is provided with along the span and vertically is divided into five or six module segmentations.From 39 to 43 feet scopes of these section lengths, and have about eight feet chord length.Therefore, this aircraft has about eight feet length, and preferably has about 100,120,200 or 250 feet span.Each supports their weight awing the wing segmentation of this aircraft, so that will minimize at the load in the middle of the segmentation, thereby and the load structure that requires is minimized.
Should extend downwards from the tie point of wing 112 between segmentation by stable wing 118a-118d, each stable wing is installed before the landing gear and trailing wheel.Should stable wing be configured to go to comprise the part of aircraft as gondola, such as electronic equipment, and/or various Payload.One of gondola, " control box " is used to carry control electronics, comprises that an automatic pilot that mainly comprises software removes to control motor and elevator.In addition, this gondola carries detector, comprises global positioning system equipment and communication equipment.
This aircraft comprises that also a communication relays module, and this communication relay module comprises the antenna of aircraft, is used to send to and/or receives from ground station.The antenna of this aircraft has moderate beamwidth, preferably is about 10 °-20 °.
Result as said structure, the preferred embodiment of this aircraft is light and handy (wing area is less than 1 pound per square foot), advance with air speed relatively slowly (from the low latitude 13 joints to the high-altitude 100 joints), and in order to keep aerial sports from the relatively little electric energy of arrays of solar cells needs.The flying quality relatively slowly of this aircraft helps the permanent duration flying quality of this aircraft, and firm operation during the control position.
The flight place
With reference to figure 1 and 3-6, each aircraft 104 control position promptly, keeps substantially with respect to ground station 102 geostationary positions.This geostationary substantially position is a flight place 132 with central point 134 and the distance that laterally and highly floats of allowing.Therefore, this flight place is the cylindrical portion of an airspace typically, and this tubular is longitudinally extended in vertical direction here.Preferably, it is about 60 that this flight place is in, 000-70, and 000 foot height is on normal air transportation and atmospheric interference (for example, storm).At this height, maximum intensity wind and the wind facies in low gaseous blast zone relatively have low speed.
Preferably, each aircraft 104 is maintained at independent flight place 132, and this flight place 132 separates by the flight place of spacing 136 with other.In arbitrary given time, each aircraft can be any position (as describing at Fig. 5) in its flight place.This spacing had both guaranteed that an aircraft does not fly within the beamwidth of another relevant ground-plane antenna, was used for protecting this aircraft to avoid knocking each other again.
Ground station
With reference to figure 1 and 3, this ground station 102 in each sub-district 108 is land communication nodes, and preferably broadcast singal arrives one or more aircraft 104, and/or from one or more aircraft 104 received signals.The number of this ground station is typically than the number of sub-district more out and away (that is, having numerous ground stations in the sub-district of majority).The communication equipment of continental rise is connected to this ground station, and typically comprises one or more end user terminal (that is the communication equipment that, is used for one or more terminal uses).Each ground station comprises one or more narrow beam antennas, its each can broadcast singal to the antenna of the communication module on of aircraft, and/or from the antenna receiving communication signal of the communication module on of aircraft.
This earth station antenna preferably has narrow beamwidth, for example, about 2 °, 2.5 °, 3 ° or 4 °, is provided for high potential bandwidth with suitable power level.These antenna has one and is provided for from about 3 ° or the 6 ° steering mechanism that turn the antenna aiming of nominal position, and this nominal position is to three times of about earth station antenna beamwidth.This communication system comprises one or more controllers, thereby goes the manipulation of order and control earth station antenna.An independent controller can be in each ground station, and perhaps single controller can be arranged in or aircraft or control ground station.This control ground station keeps in touch with this aircraft, and this aircraft is relayed control information and given another ground station, perhaps directly communicates by letter with the ground station of routine.In addition, a controller can be co-located in a plurality of systems part, such as partly in aircraft and partly in each ground station.
Single ground station can comprise a plurality of earth station antennas that can aim at and insert signal from different aircraft, therefore increase available bandwidth.Independent controller can be controlled different antennas, and perhaps the individual system controller can be controlled all earth station antennas.
This ground station also comprises an initial aiming adjusting mechanism.A kind of typically manual adjustment of this mechanical device and automatic tracking system comprise the S meter of some type, are targeted to the central point 134 in flight place 132 with the nominal that helps to be provided with antenna.
The ground station sub-district
Antenna on each aircraft 104 is configured and aims to shine a ground region 142 of being filled by a sub-district 108 substantially.These preferably hexagonal sub-districts can have varying sized character, and it preferably is complementary at the beamwidth of the distance that equals the aircraft cruising altitude with off-air antennas.The antenna of this aircraft can aim at and shine staggered ground region, so that realize the area of coverage 144 comprehensive honeycombs is covered.This area of coverage typically can have and is about 10 to 30 miles radius.
On this aircraft 104, this aircraft antenna is carried in one or more payload modules.Use gimbals, this antenna keeps its attitude, and from rolling, the pitching of this aircraft, wave with translational motion damping.Preferably all aircraft antennas are installed on the single gimbal-mounted platform, to limit the number of effective gimbals.Therefore, the target of each aircraft antenna is maintained on its corresponding sub-district 108.
Antenna beam control
With reference to figure 7, under the present invention, need not to move, the size in flight place 132 can hide narrow beam 152 greater than ground station 102.Slight twisting by utilizing the earth station antenna direction (promptly, minimum manipulation), this communication system can obtain benefit with narrow beam ground-plane antenna (otherwise need the flight place approximately from center reference point laterally ± 0.5 mile and vertical ± 0.1 mile), this aircraft can be obtained the benefit with big fight zone simultaneously, such as approximately from center reference point laterally ± 1.5 miles and vertically ± 1.0 miles.
Especially, this aircraft can move to keep the average power still less in less position than needs, and this aircraft can pass thunderstorm, eddy current and vertical aerial sports such as high wind, high-altitude controlling the position under the difficult condition more.In addition, from viewpoint of reliability, as often or as it can not be operated fiercely, and antenna platform will be easier to be stable with more limited deflection.
During earth station antenna under being implemented in the present invention was handled, this earth station antenna controller preferably disposes to be handled this antenna beam and goes to run through whole flight place and move.They further preferably dispose and remove to limit the earth station antenna beam steering, make that this wave beam is avoided passing through within any flight place except flight specific, appointment place.This structure may appear in control system software or the hardware, because the wave beam amount that needs to handle will depend on ground station and the relative position in the place of flying, and the size and dimension that depends on this flight place.Especially, directly the ground station below the flight place is than needing higher locomotivity away from the broad flight place of the ground station of position of aircraft in fact.Similarly, will need higher locomotivity away from the direct high flight place of ground station below the flight place of ground station's ratio of position of aircraft in fact.These geometric requirements can easily be calculated by controller.
Turn to Fig. 8 A and 8B now, earth station antenna typically will comprise a feed horn 202 and a main reflector 204.This antenna can also comprise an auxiliary speculum 206.
This preferably is used to handle the actuator that twists antenna is low power and long-lived.Because they do not need the big angle of deflection, they can be simple mechanisms cheaply, and can have more reliability than the gimbal system of wide-angle.Wherein operable mechanical device type is servomotor, stepping motor, piezo-activator and bimetal strip.Can also use gimbals in certain embodiments of the present invention.
The manipulation of this antenna can turn in many different modes.For example, can reconfigure a complete combination of antennas.But, further preferably, have only the part of combination of antennas, such as main reflector (referring to Fig. 8 A), auxiliary reflector (referring to Fig. 8 B), perhaps this feed horn can reconfigure to the position 208 of deflection.Because they usually are small device, the reflector that preferably reconfigures this feed horn or should assist.Reconfigure or this feed horn or this auxiliary reflector if use, with comparing of needing for fixed antenna, it may be necessary using big main reflector.
The antenna of other types also within the scope of the invention.For example, can use a phased array, promptly, one group of antenna, the respective phase of corresponding signal of antenna of wherein feeding is changed with a kind of like this method, that is, be enhanced in effective radiation mode of this array of direction of wanting, and be suppressed in effective radiation mode of undesired this array of direction.In this case, this antenna can be handled with electronics method.Similarly, a series of narrow beam antennas that aim at the pattern that covers whole flight place can be selected by a control system as independent steerable antenna.Therefore, not all embodiment needs actual running machinery to remove to handle this antenna.
The beam direction control system
In order to remove to handle this earth station antenna, make when its fly through place move in its wave beam follow this aircraft, this ground station must obtain antenna control information (that is the information of and level vertical about the earth station antenna directional control of needs).This information can be developed in many different control system embodiment in many different modes.Typically, this information is from position of aircraft information, and from the information of relevant ground station with respect to the relative position in flight place, produce.
At first embodiment that is used for earth station antenna directional control of the present invention system, the position of this aircraft is set up by this aircraft, such as reading by a global positioning system of use (GPS).This information is sent to each ground station then, perhaps encodes in the carrier signal that sends to each unit usually, perhaps uses broad beam or omnidirectional antenna to go to send and/or receive this information through narrow broadcast channel.
This information can provide with many forms.For example, this information can be used as an absolute geographical position, with respect to the relative position of the aircraft of this sub-district, and perhaps the relative position with respect to the aircraft in this flight place sends.In other words, this information can be transformed into the antenna control information of each group that is used for each given sub-district and/or one or more ground stations, and sends then.
It should be noted that the representative of antenna direction information and/or aircraft location information needs low-down data speed and little transmitting power to go a spot of data that send.Those information must arrive each and have the ground station that an antenna aims at this aircraft.Each ground station must set up the elevation angle and the azimuth that are suitable for its geographical position with respect to this aircraft and handle.If a wide aboard directional antenna is used to send the aircraft directional information to all users that arrive, then or this information will be encoded to each ground station, the manipulation necessary condition of regulation antenna, perhaps need be based on the positional information of this aircraft, its oneself manipulation must be calculated by each ground station.
At second embodiment that is used for earth station antenna directional control of the present invention system, the position of each aircraft can be set up by the central control station of continental rise, such as by using radar range finding and bearing measurement.The mode that this information can be discussed with first embodiment that is similar in the above for earth station antenna directional control system is for the aircraft telemeasurement, and relays and give ground station.Similarly, those information can be by other device, such as available Ground Communication System or independently wireless transmission be sent to ground station.Once more, this information can provide such as aircraft location information or antenna control command information with many forms.
At the 3rd embodiment that is used for earth station antenna directional control of the present invention system, the position of this aircraft is set up by each ground station, is set up by a tracking system of providing for oneself such as the transmission signal strength based on this aircraft.In such system, periodically handled by this earth station antenna of little angle, and signal strength signal intensity is compared in each position.This antenna of strong signal indication is close at this carry-on center.Certainly, as long as this ground station be need not the message transmission from this aircraft by locked on its corresponding aircraft, it will stay on the aircraft of locking.
Should be noted that if the antenna of the 3rd embodiment loses the trace of this aircraft, such as may occurring when this system cut-off the time, can implement to cover the way of search of its range of movement of covering in whole flight place.If this antenna control information is sent to the ground station that embeds in the aircraft standard transmission, when this antenna loses the clue of aircraft, will lose this aircraft, this performance also may be for other embodiment necessary.Use the common needs of eliminating very big or frequent search of omnidirectional antenna by this control system.
Other consideration
Be used for the principle that the low-angle antenna of earth station antenna handles and can be suitable for various flights place size, such as laterally ± 15 mile and vertically ± 5 miles, perhaps laterally ± 20 miles and vertically ± 3 miles.But in this control position lost, it is more relevant that quadratic effect becomes, such as distance significant difference change in signal strength, perhaps otherwise shield other users' of same frequency interference by accurate directivity.In addition, the interval between the flight place of a flight place and vicinity may increase.
Low-angle is handled and also can be used on aircraft antenna and earth station antenna, increases accurate control on the gimbals of wide-angle, stablizes this antenna when flight.
In whole communication system, presumable ground station not only uses the low-angle adjustment.Above-mentioned ground station will comprise mobile earth station, with the ground station that is designed to switch communication between different aircraft (for example, being used for aircraft commander and control).
Should be understood that the limited directivity adjustment of use on fixed charge method earth station, in ground station, increased cost and complexity, but it provides many benefits, relate to efficient, energy supply and as the mobility of the stratosphere flight device of relay station.Therefore, under many embodiment of the present invention, can improve efficient, cost and the reliability of overall communication system.
The system of this generation can be used for the two-way communication between ground station and other positions, to the One-to-All Broadcast of ground station, perhaps or even by the One-to-All Broadcast of ground station.Therefore, should be understood that in the above the antenna irradiation sub-district described or flight place are the references for the antenna beamwidth of taking at certain distance, there is no need an antenna configurations and go to send communication, but not received communication only.
Though illustrated and described particular form of the present invention, obviously do not broken away from the spirit and scope of the present invention and can carry out various modifications.Therefore, though only described the present invention in detail with reference to preferred embodiment, those those of ordinary skills will understand not depart from the scope of the present invention and can carry out various modifications.Therefore, the present invention does not mean that by above-mentioned argumentation restriction, but limits according to following claim.
Claims (21)
1. communication repeating system comprises:
The aircraft of the internal control position, flight place of appointment in the middle of a plurality of potential flight places is removed in configuration, and this aircraft comprises that a communication relays module, and this communication relay module comprises one or more antennas;
Be positioned at a plurality of ground stations of the area of coverage, each ground station comprises an antenna, and configuration is via signal of communication at least one antenna communication with the relay module of communicating by letter, and this earth station antenna has the beamwidth that is not enough to shine simultaneously whole flight place; With
An antenna controller, wherein to be configured under the control of this antenna controller be steerable to each earth station antenna, make when this aircraft movements runs through the flight place of this appointment, this earth station antenna can keep communicating by letter with this and relay module communication, and wherein this antenna controller is configured to limit the manipulation of this antenna, makes except avoiding commanding antenna in any flight place the flight place of this appointment.
2. according to the communication repeating system of claim 1, wherein this antenna controller is configured to make position of aircraft information to be sent to each ground station, and each ground station is from this position of aircraft information calculations antenna control information.
3. according to the communication repeating system of claim 2, wherein this antenna controller is configured to make that this position of aircraft information is to develop from the detector on this aircraft.
4. according to the communication repeating system of claim 2, wherein this antenna controller is configured to make this position of aircraft information from being arranged on ground detector exploitation.
5. according to the communication repeating system of claim 1, wherein this antenna controller is configured to make the antenna control information to be sent to each ground station.
6. according to the communication repeating system of claim 1, wherein this antenna controller is configured to make that the information that is embedded in the antenna controller in the signal of communication sends to each ground station from this communication repeating module to this earth station antenna.
7. according to the communication repeating system of claim 1, wherein this antenna controller is configured to make that the information of antenna controller is received by each ground station via an omnidirectional antenna.
8. according to the communication repeating system of claim 1, wherein this antenna controller is configured to make the information of antenna controller to send to each ground station from the position of a continental rise.
9. according to the communication repeating system of claim 1, these a plurality of ground stations further comprise a tracking system, and configuration goes to detect the positional information of relevant this aircraft with respect to ground station;
Wherein this antenna controller is configured to use the positional information of relevant this aircraft, goes to produce the antenna control command that is used to handle this earth station antenna.
10. according to the communication repeating system of claim 1, wherein each ground station of these a plurality of ground stations comprises a tracking system, and configuration goes to detect the positional information of relevant this aircraft with respect to ground station;
Wherein this antenna controller is configured to use the positional information of relevant this aircraft, goes to produce the antenna control command that is used to handle this earth station antenna.
11. communication repeating system according to claim 10, wherein the tracking system of each ground station is configured to use the signal strength signal intensity of the signal that is received by earth station antenna, go to detect information about the position of this aircraft, if and wherein this earth station antenna has lost to communicate by letter with this and has relayed the communication of module, this aircraft is arranged in the place of this appointment simultaneously, and this antenna controller is further configured with way of search and produces the antenna control command that is used to handle this antenna.
12. according to the communication repeating system of claim 1, wherein this aircraft is an equipment that is selected from the group of blimp, aircraft and kite.
13. according to the communication repeating system of claim 1, wherein the place of this appointment laterally extends to much about 1.5 miles from the reference position, and vertically about at the most 1 mile.
14. according to the communication repeating system of claim 1, wherein the place of this appointment laterally extends to many 20 miles from the reference position, and vertically at the most 3 miles.
15. according to the communication repeating system of claim 1, wherein this antenna controller and this earth station antenna are configured to make that this earth station antenna is steerable on about 6 degree at the most.
16. according to the communication repeating system of claim 1, wherein this antenna controller and this earth station antenna are configured to make that this earth station antenna is steerable on about 3 degree at the most.
17. according to the communication repeating system of claim 1, wherein each earth station antenna comprises a main reflector and a horn antenna, and wherein moves this main reflector with respect to this horn antenna, each earth station antenna is steerable.
18. according to the communication repeating system of claim 1, wherein each earth station antenna comprises a main reflector and a horn antenna, and wherein moves this horn antenna with respect to this main reflector, each earth station antenna is steerable.
19. communication repeating system according to claim 1, wherein each earth station antenna comprises a main reflector, an auxiliary reflector and a horn antenna, and wherein move this auxiliary reflector with respect at least one of this main reflector and this horn antenna, each earth station antenna is steerable.
20. a communication repeating system comprises:
The aircraft of the internal control position, flight place of appointment in the middle of a plurality of potential flight places is removed in configuration, and this aircraft comprises that a communication relays module, and this communication relay module comprises one or more antennas;
Be positioned at a plurality of ground stations of the area of coverage, each ground station comprises an antenna, and configuration is via signal of communication at least one antenna communication with the relay module of communicating by letter, and this earth station antenna has the beamwidth that is not enough to shine simultaneously whole flight place; With
A device that is used to control this earth station antenna, wherein to be configured under the control of this device that is used to control be steerable to each earth station antenna, make when face station aircraft movements runs through the flight place of ground station's appointment expediently, this earth station antenna can keep communicating by letter with this and relay module communication, and wherein this device that is used to control is configured to limit the manipulation of earth station antenna, makes except avoiding commanding antenna in any flight place the flight place of appointment.
21. the method for a trunking traffic comprises:
An aircraft is provided, and the internal control position, flight place of appointment in the middle of a plurality of potential flight places is gone in configuration, and this aircraft comprises that a communication relays module, and this communication relay module comprises one or more antennas;
Provide a plurality of ground stations for the area of coverage, each ground station comprises an antenna, and configuration is via signal of communication at least one antenna communication with the relay module of communicating by letter, and this earth station antenna has the beamwidth that is not enough to shine simultaneously whole flight place; With
Control the manipulation of this earth station antenna, make and to run through in the flight place of this appointment when this aircraft movements, their keep and the communicating by letter of this communication repeating module, and feasible except the flight place of this appointment, and they avoid aiming at any flight place.
Applications Claiming Priority (2)
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| US19779900P | 2000-04-14 | 2000-04-14 | |
| US60/197,799 | 2000-04-14 |
Publications (1)
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| CN1422447A true CN1422447A (en) | 2003-06-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN01807848A Pending CN1422447A (en) | 2000-04-14 | 2001-04-14 | Mobile radio communication system |
Country Status (10)
| Country | Link |
|---|---|
| EP (1) | EP1277253A2 (en) |
| JP (1) | JP2003531543A (en) |
| KR (1) | KR20030016248A (en) |
| CN (1) | CN1422447A (en) |
| AU (1) | AU2001255374A1 (en) |
| BR (1) | BR0110300A (en) |
| CA (1) | CA2403777A1 (en) |
| MX (1) | MXPA02009655A (en) |
| RU (1) | RU2002129589A (en) |
| WO (1) | WO2001080356A2 (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1960056B (en) * | 2006-09-22 | 2011-07-20 | 中国电子科技集团公司第二十八研究所 | Method and system of following motion object by mobile type antenna |
| CN107431526A (en) * | 2014-02-17 | 2017-12-01 | 尤比库姆特有限责任公司 | Mobility and power management for High Altitude Platform (HAP) communication system |
| CN107968677A (en) * | 2016-10-20 | 2018-04-27 | 株式会社理光 | Relay, the method and system of direction propagation wireless signal |
| WO2018121478A1 (en) * | 2016-12-30 | 2018-07-05 | 华为技术有限公司 | Air-to-ground communication system, method, and device |
| CN108496131A (en) * | 2017-04-21 | 2018-09-04 | 深圳市大疆创新科技有限公司 | Unmanned plane searching method and ground control terminal |
| CN109104241A (en) * | 2018-07-09 | 2018-12-28 | 西安理工大学 | In a kind of laser communication can aircraft carry it is all-optical, dual to relay and method |
| CN109417420A (en) * | 2016-07-15 | 2019-03-01 | 高通股份有限公司 | Dynamic beam for unmanned vehicle turns to |
| CN111034243A (en) * | 2017-08-31 | 2020-04-17 | 三菱电机株式会社 | Communication device |
| CN111264037A (en) * | 2017-10-23 | 2020-06-09 | IPCom两合公司 | Reducing aircraft induced disturbances |
| CN112130305A (en) * | 2017-05-26 | 2020-12-25 | 上海微小卫星工程中心 | Satellite tracking and aiming system and wide-angle pointing method thereof |
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| JP2005159448A (en) * | 2003-11-20 | 2005-06-16 | National Institute Of Information & Communication Technology | Wide band radio communication system |
| JP4940054B2 (en) * | 2007-08-16 | 2012-05-30 | キヤノン株式会社 | Wireless communication system, wireless communication apparatus, and control method thereof |
| US20140313073A1 (en) * | 2013-03-15 | 2014-10-23 | Carlo Dinallo | Method and apparatus for establishing communications with a satellite |
| GB2536016A (en) * | 2015-03-03 | 2016-09-07 | Stratospheric Platforms Ltd | Means of improving data transfer |
| GB2536015A (en) * | 2015-03-03 | 2016-09-07 | Stratospheric Platforms Ltd | Process and apparatus for communicating with a user antenna |
| GB2536018A (en) * | 2015-03-03 | 2016-09-07 | Stratospheric Platforms Ltd | Increasing data transfer rates |
| GB2536017A (en) * | 2015-03-03 | 2016-09-07 | Stratospheric Platforms Ltd | Generation and use of similar multiple beams |
| US9871577B2 (en) * | 2015-11-30 | 2018-01-16 | Google Llc | Global communication network |
| GB2553302A (en) * | 2016-08-30 | 2018-03-07 | Avanti Communications Group Plc | Satellite equipment |
| CN108270476B (en) | 2016-12-30 | 2021-07-20 | 华为技术有限公司 | High-altitude communication system, method and device |
| JP6643417B2 (en) * | 2018-08-02 | 2020-02-12 | Ｈａｐｓモバイル株式会社 | Systems, controllers and light aircraft |
| US11711134B2 (en) | 2021-03-15 | 2023-07-25 | Nokia Technologies Oy | Autonomous beam switch in HAPS coverage |
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| US5810284A (en) * | 1995-03-15 | 1998-09-22 | Hibbs; Bart D. | Aircraft |
| US5579018A (en) * | 1995-05-11 | 1996-11-26 | Space Systems/Loral, Inc. | Redundant differential linear actuator |
| JP3313636B2 (en) * | 1997-12-22 | 2002-08-12 | 日本電気株式会社 | Antenna device for low-orbit satellite communication |
| FR2782193A1 (en) * | 1998-08-04 | 2000-02-11 | Agence Spatiale Europeenne | RECEPTION ANTENNA WITH EXCENTRE REFLECTOR SCANNED BY THE RECEPTION HEAD, IN PARTICULAR FOR THE RECEPTION OF SEVERAL TELEVISION SATELLITES AND ITS PROCESS FOR IMPLEMENTATION |
| AU5805299A (en) * | 1998-09-08 | 2000-03-27 | Angel Technologies Corporation | Network for providing wireless communications using an atmospheric platform |
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2001
- 2001-04-14 CN CN01807848A patent/CN1422447A/en active Pending
- 2001-04-14 CA CA002403777A patent/CA2403777A1/en not_active Abandoned
- 2001-04-14 WO PCT/US2001/012173 patent/WO2001080356A2/en not_active Application Discontinuation
- 2001-04-14 KR KR1020027013773A patent/KR20030016248A/en not_active Application Discontinuation
- 2001-04-14 JP JP2001577645A patent/JP2003531543A/en not_active Withdrawn
- 2001-04-14 RU RU2002129589/09A patent/RU2002129589A/en not_active Application Discontinuation
- 2001-04-14 EP EP01928526A patent/EP1277253A2/en not_active Withdrawn
- 2001-04-14 MX MXPA02009655A patent/MXPA02009655A/en unknown
- 2001-04-14 AU AU2001255374A patent/AU2001255374A1/en not_active Abandoned
- 2001-04-14 BR BR0110300-8A patent/BR0110300A/en not_active Application Discontinuation
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1960056B (en) * | 2006-09-22 | 2011-07-20 | 中国电子科技集团公司第二十八研究所 | Method and system of following motion object by mobile type antenna |
| CN107431526A (en) * | 2014-02-17 | 2017-12-01 | 尤比库姆特有限责任公司 | Mobility and power management for High Altitude Platform (HAP) communication system |
| CN109417420A (en) * | 2016-07-15 | 2019-03-01 | 高通股份有限公司 | Dynamic beam for unmanned vehicle turns to |
| CN109417420B (en) * | 2016-07-15 | 2021-10-12 | 高通股份有限公司 | Dynamic beam steering for unmanned aerial vehicles |
| CN107968677A (en) * | 2016-10-20 | 2018-04-27 | 株式会社理光 | Relay, the method and system of direction propagation wireless signal |
| US10637558B2 (en) | 2016-12-30 | 2020-04-28 | Huawei Technologies Co., Ltd. | High-altitude communications system, method, and apparatus |
| CN108271118A (en) * | 2016-12-30 | 2018-07-10 | 华为技术有限公司 | high altitude communication system, method and device |
| WO2018121478A1 (en) * | 2016-12-30 | 2018-07-05 | 华为技术有限公司 | Air-to-ground communication system, method, and device |
| CN108496131A (en) * | 2017-04-21 | 2018-09-04 | 深圳市大疆创新科技有限公司 | Unmanned plane searching method and ground control terminal |
| CN112130305A (en) * | 2017-05-26 | 2020-12-25 | 上海微小卫星工程中心 | Satellite tracking and aiming system and wide-angle pointing method thereof |
| CN111034243A (en) * | 2017-08-31 | 2020-04-17 | 三菱电机株式会社 | Communication device |
| CN111264037A (en) * | 2017-10-23 | 2020-06-09 | IPCom两合公司 | Reducing aircraft induced disturbances |
| CN111264037B (en) * | 2017-10-23 | 2022-06-14 | IPCom两合公司 | Reducing aircraft induced disturbances |
| CN109104241A (en) * | 2018-07-09 | 2018-12-28 | 西安理工大学 | In a kind of laser communication can aircraft carry it is all-optical, dual to relay and method |
| CN109104241B (en) * | 2018-07-09 | 2021-07-20 | 西安理工大学 | All-optical bidirectional relay device and method capable of being mounted on aircraft in laser communication |
Also Published As
| Publication number | Publication date |
|---|---|
| EP1277253A2 (en) | 2003-01-22 |
| MXPA02009655A (en) | 2004-07-30 |
| WO2001080356A2 (en) | 2001-10-25 |
| CA2403777A1 (en) | 2001-10-25 |
| AU2001255374A1 (en) | 2001-10-30 |
| RU2002129589A (en) | 2004-03-10 |
| WO2001080356A3 (en) | 2002-02-07 |
| JP2003531543A (en) | 2003-10-21 |
| KR20030016248A (en) | 2003-02-26 |
| BR0110300A (en) | 2003-12-30 |
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