CN2751453Y - Signal level detecting dynamic tracking satellite antenna - Google Patents
Signal level detecting dynamic tracking satellite antenna Download PDFInfo
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- CN2751453Y CN2751453Y CN 200420058643 CN200420058643U CN2751453Y CN 2751453 Y CN2751453 Y CN 2751453Y CN 200420058643 CN200420058643 CN 200420058643 CN 200420058643 U CN200420058643 U CN 200420058643U CN 2751453 Y CN2751453 Y CN 2751453Y
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Abstract
The utility model relates to a signal level detecting dynamic tracking satellite antenna which is composed of a satellite signal level detecting circuit, a satellite antenna, a feeder device, a pitch control motor, an orientation control motor, a roll control motor, a mechanical transmission and speed reducing device, and a control and digital signal processor. The utility model does not use the expensive apparatuses needed by the traditional method any longer, such as inertial navigation platforms, inertia gyroscopic apparatuses, electronic compasses, etc., and adopts the method of the follow-up control system of a combined antenna of a satellite strength signal detecting circuit, realizing the dynamic tracking of the satellite. The utility model can ensure that the antenna aligns to the satellite all the time within a certain dynamic range of a carrier, realizing the uninterrupted satellite communication on the move. The utility model has the advantages of simple system, low cost, light weight, small size, no abnormal interference from geomagnetism, and high reliability.
Description
Technical field
The utility model relates to a kind of satellite signal levels detection method that adopts and realizes the satellite communication antenna with dynamic auto follow-up control.Belong to International Classification of Patents H01Q3/00 " device of change antenna or sensing of antenna system radiated wave or direction figure " technical field.
Background technology
Up to now, dynamic auto tracking satellite antenna system is combined as basic dependence with inertial platform or high-precision gyro mostly, makes up a reference platform that does not physically rotate with carrier.Disclosed among this kind system such as the ZL01104216,94218035.6,92231278.8 and 95190037.4, this type systematic has used satellite signal levels as auxiliary, but the beasurement base that all adopts turn meter (a kind of gyroscopic apparatus) to rotate as most important carrier.Its basic principle is: when carrier moves, the inertia sensing device as: parts such as inertial platform, optic fiber gyroscope, electro-mechanical gyro are experienced this motion, and by computing or circuit, it are converted to rotational angle.By platform controller and mechanical framework structure, adjust same angle round about then, thereby make the physical platform that has frame structure keep motionless at inertial space.And the antenna that is installed on this platform just can keep aiming at all the time original direction, keeps all the time to satelloid, and the rotation with carrier does not change.But in general, high-precision inertial platform and optic fiber gyroscope, electro-mechanical gyro, frame structure all compare accurate and expensive, and its purchase cost often accounts for the overwhelming majority of whole system.In addition, electro-mechanical gyro costliness and reliability are not high, and system start-up needs long time.Therefore, except military systems, civilian system has promptly used mostly with not rising, and also can not repair, so greatly limited the application scenario of this kind system.
Another kind of system uses another kind of angle measurement unit: mechanical compass or electronic compass.Compass is a kind of parts based on magnetic field of the earth variation and measuring principle design.This device can directly be experienced the rotational angle of carrier or platform, rotates an opposite angle by platform control system, and implementation platform is stablized constant in the direction of inertial space.This type systematic such as Chinese patent application 03135684.2.Though it is the high accuracy compass is more cheap than high accuracy Inertial Sensor Unit, also expensive.In addition, compass is subject to the influence of changes of magnetic field, if use occasion has magnetic field unusual, as the changes of magnetic field that calutron, magnet etc. causes, system will be difficult to operate as normal.
The utility model content
The purpose of this utility model is to overcome above-mentioned deficiency, provide a kind of can solve because of carrier movement causes antenna can't be to satelloid, can't keep the signal levelling detecting and dynamic tracking satellite antenna of satellite communication capability problems at the volley.
The purpose of this utility model is achieved through the following technical solutions.
A kind of signal levelling detecting and dynamic tracking satellite antenna is mounted in the automatic tracking antenna system on the mobile vehicle.This antenna system is made up of satellite signal levels testing circuit (1), satellite antenna and feeder equipment (2), pitching control motor (3), control of azimuth motor (4), roll control motor (5), machine driving and deceleration device (6), control and digital signal processor (7); Satellite signal levels testing circuit (1) is connected with digital signal processor (7) with control, control divides three the tunnel with the output of digital signal processor (7), respectively with pitching control motor and circuit for controlling motor (3), control of azimuth motor and circuit for controlling motor (4), roll control motor is connected with circuit for controlling motor (5), described (3), (4), (5) the other end is connected with satellite antenna feeder equipment (2) with deceleration device (6) by machine driving, and the other end of satellite antenna and feeder equipment (2) is connected with satellite signal levels testing circuit (1) again.
Satellite antenna described in the utility model comprises reflection planar antenna, flat type antenna, waveguide crack class antenna etc.
In said system, can omit roll control motor (5), form the satellite automatic follow-up antenna system that is called diaxon.
In said system, can omit pitching control motor (3) and roll control motor (5) simultaneously, form the satellite automatic follow-up antenna system that is called single shaft.
Antenna system of the present utility model can realize the initial alignment of satellite and the dynamic tracking of satellite, and can satisfy general user's request.But, do not use the compass device because native system has omitted traditional gyro and inertial platform yet.Therefore, system can't obtain the angle error amount of antenna, still may produce the situation that satellite is lost or antenna does not catch up with when the carrier tempo turn.For overcoming this shortcoming, can utilize the direction characteristic of antenna to improve the follow-up control of antenna.We call this method: the antenna rotational angle is differentiated and the rough model method of antenna alignment error angle set up based on satellite signal levels intensity.The principle of the method is as follows:
General antenna all has as the equiform direction characteristic in mountain peak or is called the directional pattern of antenna.High peak position correspondence the axis of orientation center of antenna.When signal is injected the direction axis coinciding of direction and antenna, the antenna gain maximum, the signal of collection is the strongest.When signal inject the axis centre position of deviation in driction antenna the time, the gain of antenna can descend, the signal that antenna receives can die down.But, the angle between the absorption direction of signal and the axle center of antenna not simultaneously, corresponding change in signal strength rate and inequality on the unit angle.If promptly with signal strength signal intensity the angle of deviation is differentiated, its derivative value will change with the angle difference that antenna departs from.In other words, when antenna was in the different angles of deviation, it is also inequality that the unit angle changes the change in signal strength rate of bringing.Therefore, this change in signal strength rate in fact with the angle of deviation height correlation of antenna.And in general, in the adjacent domain of antenna axle center, antenna axle center offset signal incident direction angle is big more, and the slope after signal strength signal intensity is differentiated is also big more, and (concrete slope variation is relevant with the directional diagram of specific antenna.Antenna difference, slope variation feature are also different).Therefore, slope can be used as the reference value use of error angle really.We use the integrated signal of " error angle " variable replacing low precision gyroscope angular-rate sensor.Directly control antenna control system high speed rotating is eliminated this " error angle " fast.Reach without gyro, also can improve the purpose of the quick tracking characteristics of system dynamics.The method is applied in the dynamic tracking satellite antenna system that our company designs voluntarily.
Another principle of the utility model institute foundation is a shelter derivative comprehensive distinguishing method, after promptly satellite-signal intensity is differentiated respectively to the time with to angle, derivative is fully utilized, and can be used to carry out the differentiation of shelter.Its discrimination principles is as follows: when carrier in the middle of traveling process on the road, it is common phenomena that there is certain shelter (as: building, bridge, indication plate etc.) in the roadside.This moment, satellite was blocked.Satellite-signal is blocked.If but thought that antenna has departed from satellite direction this moment and the direction of removing to adjust hastily antenna will make antenna really depart from the satellite true directions, would cause and lose satellite.How could distinguish satellite-signal signal interruption and the carrier turning antenna that causes that be blocked and fail to follow the tracks of the signal interruption that satellite causes? its determination methods be exactly satellite-signal intensity to before the derivative of time and this time one constantly satellite-signal intensity to the derivative of antenna corner as the common reference amount.A kind of decision criteria of collaborative formation: if satellite-signal intensity weakens suddenly, satellite-signal becomes big to the derivative of time.If but this moment, the eve satellite-signal intensity derivative value that differentiate draws to the antenna corner was also little, then explanation eve antenna does not at this moment have big alignment error.Therefore, this satellite-signal is lost because shelter blocks and causes.System's control antenna of needn't being eager is done the direction adjustment.Can carry out the shelter of antenna differentiates with this kind method.Reduce the unnecessary adjustment of antenna.Catch the ability of satellite behind the shelter of raising system rapidly once more, reduce capture time.
Compare with conventional method, it is necessary that the design does not re-use conventional method, as: cores such as Inertial navigation platform, inertia gyroscope device, electronic compass and expensive equipment.This device adopts the method for satellite strength signal testing circuit combined antenna following control system, realizes the dynamic tracking of satellite.This device can guarantee within the certain dynamic range of carrier antenna all the time to satelloid, be implemented in move in continual satellite communication.Owing to saved Inertial navigation platform, gyropanel or price apparatus such as gyroscopic apparatus, electronic compass, native system is compared simpler with legacy system, with low cost, and is in light weight, and volume is little.Be not subjected to the unusual interference of earth magnetism, system reliability improves greatly.And price is minimum.Therefore, the utility model is more suitable for that carrier (for example: automobile, boats and ships, train, aircraft etc.) keeps incessantly at the volley that satellite is unidirectional in requiring, both-way communication ability or satellite television receiving ability, but want cube little, the satellite communication application system of in light weight, cheap, high reliability.
Description of drawings
Fig. 1 is the block diagram of the utility model antenna system.
Embodiment
As shown in Figure 1, the course of work of the present utility model is: after the antenna system start, control is sent instruction with digital signal processor 7, circuit for controlling motor 5 places a certain initial position with pitching control motor 3 and control of azimuth motor 4 with antenna 2, and antenna azimuth, the antenna angle of site, the antenna roll angle of record this moment and come from satellite signal levels testing circuit 1 satellite-signal intensity.Under the instruction of control and digital signal processor 7, circuit for controlling motor 5 moves an angle with drive controlling motor 3,4 control antenna devices 2 by a certain control law then.And note once more this moment the various angles of antenna and this kind angle under come from the satellite-signal intensity of satellite signal levels testing circuit 1, and compare with once preceding or preceding satellite-signal intensity several times.If this satellite-signal intensity increases, illustrate that then the rotation direction of antenna is correct.Control is sent instruction with digital signal processor 7, and circuit for controlling motor 5 continues to rotate along this direction with drive controlling motor 3,4 control antennas.After if antenna rotates a certain angle, find the satellite-signal strength reduction, it is excessive to illustrate that then antenna rotation direction error or antenna have rotated.Control is sent instruction with digital signal processor 7, and circuit for controlling motor 5 rotates round about with drive controlling motor 3,4 control antenna devices 2, or reduces the angle of rotation tolerance of antenna.By the comparison of satellite-signal intensity one by one, seek the maximum value position of satellite-signal intensity.And the pairing antenna direction of the maximum value position of satellite-signal intensity: azimuth, the angle of pitch, roll angle are exactly the accurate direction of satellite.
Under aforementioned operation principle instructed, the utility model can have various control strategy and satellite acquisition and tracking implementation method.Wherein typical a kind of diaxon (orientation and pitching) is achieved as follows:
Initial satellite acquisition and aligning: after the system boot, antenna is preset on a certain angle of pitch, system begins 360 degree scanning directions.Record aerial position and corresponding satellite-signal intensity are sought satellite-signal maximum intensity position.If do not find satellite-signal, then conversion one antenna elevation angle carries out azimuth 360 degree search again.Up to finding satellite-signal maximum intensity position.Control antenna is to satelloid then.
In addition, in the 360 degree azimuth scan processes that antenna carries out, we are by the signal processing computer, are function with the intensity of signal, and the rotational angle of antenna is differentiated.And dynamically use angular error of computational mathematics method match and with the respective function curve e (θ) of change in signal strength rate.This curve will use when the sky line following as antenna alignment error correction curve.
The satellite dynamic tracking: when carrier moves when making antenna depart from satellite direction, antenna is done cone shape scanning or rectangular shape scanning or helix shape scanning along satellite direction.Write down under each position the satellite-signal intensity of satellite signal levels testing circuit 1 output.In the antenna scanning swing process, obtain the satellite-signal angle rate of change of this moment simultaneously.Search function curve e (θ) and draw rough antenna error angle θ
1If θ
1Greater than predetermined in advance critical error angle, then control antenna directly rotates θ to the direction that signal strength signal intensity increases
1The angle.Again carry out Satellite Tracking by cone shape scanning or rectangular shape scanning or helix shape scan mode then.
This antenna system can form the different realization of many kinds by changing search strategy or Search/Track algorithm, improves and follows the tracks of dynamic property and tracking accuracy.
Control described in the system and digital signal processor 7 adopt the TSM320C24 digital signal processor, and circuit for controlling motor 5 adopts QA743035 low-power stepper motor driver, and all the other are common parts.
Claims (2)
1, a kind of signal levelling detecting and dynamic tracking satellite antenna, be mounted in the automatic tracking antenna system on the mobile vehicle, it is characterized in that: this antenna system is made up of satellite signal levels testing circuit (1), satellite antenna and feeder equipment (2), pitching control motor (3), control of azimuth motor (4), roll control motor (5), machine driving and deceleration device (6), control and digital signal processor (7); Satellite signal levels testing circuit (1) is connected with digital signal processor (7) with control, control divides three the tunnel with the output of digital signal processor (7), is connected with circuit for controlling motor (5) with circuit for controlling motor (4), roll control motor with circuit for controlling motor (3), control of azimuth motor with pitching control motor respectively; The other end of described (3), (4), (5) is connected with satellite antenna and feeder equipment (2) with deceleration device (6) by machine driving, and the other end of satellite antenna and feeder equipment (2) is connected with satellite signal levels testing circuit (1) again.
2, signal levelling detecting and dynamic tracking satellite antenna according to claim 1 is characterized in that: the antenna in described satellite antenna and the feeder equipment (2) is the reflection-type antenna, or planar antennas, or waveguide slotted array class antenna.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420058643 CN2751453Y (en) | 2004-12-14 | 2004-12-14 | Signal level detecting dynamic tracking satellite antenna |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420058643 CN2751453Y (en) | 2004-12-14 | 2004-12-14 | Signal level detecting dynamic tracking satellite antenna |
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| Publication Number | Publication Date |
|---|---|
| CN2751453Y true CN2751453Y (en) | 2006-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200420058643 Expired - Fee Related CN2751453Y (en) | 2004-12-14 | 2004-12-14 | Signal level detecting dynamic tracking satellite antenna |
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| CN (1) | CN2751453Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101494318B (en) * | 2009-03-11 | 2011-07-27 | 熊猫电子集团有限公司 | Method and apparatus for automatically adjusting Ka waveband mobile satellite communications antenna attitude |
| CN101924274B (en) * | 2009-06-11 | 2013-04-10 | 宇沃德有限公司 | Automatic satellite tracking antenna system for receiving circular polarized wave |
| CN104795633A (en) * | 2015-04-02 | 2015-07-22 | 深圳市华信天线技术有限公司 | Shipborne satellite antenna and satellite tracking method thereof |
-
2004
- 2004-12-14 CN CN 200420058643 patent/CN2751453Y/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101494318B (en) * | 2009-03-11 | 2011-07-27 | 熊猫电子集团有限公司 | Method and apparatus for automatically adjusting Ka waveband mobile satellite communications antenna attitude |
| CN101924274B (en) * | 2009-06-11 | 2013-04-10 | 宇沃德有限公司 | Automatic satellite tracking antenna system for receiving circular polarized wave |
| CN104795633A (en) * | 2015-04-02 | 2015-07-22 | 深圳市华信天线技术有限公司 | Shipborne satellite antenna and satellite tracking method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |