CN104980236A - Method for testing tracing performance of low earth orbit satellite Ka-band data receiving system - Google Patents
Method for testing tracing performance of low earth orbit satellite Ka-band data receiving system Download PDFInfo
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Abstract
The invention provides a method for testing tracing performance of a low earth orbit satellite Ka-band data receiving system. The method comprises: (1) a three-axis antenna is aligned to a Ka-band beacon in a calibration tower and the Ka-band beacon is automatically tracked; (2) the third axis of the three-axis antenna is operated to rotate in uniformly accelerative or uniformly retarded rotation according to a preset angular acceleration; and (3) whether the tracking performance of the system meets the requirements of a tracking satellite based on measured azimuth error values in the automatic beacon tracking process, and if the azimuth error values are always not more than the preset threshold value, the tracking performance of the system meets the requirements of the tracking satellite. The method utilizes the features of the three-axis antenna, and allows the antenna to automatically track the beacons in the third axis rotating process. Thus, conditions that the antenna tracks the Ka-band low orbit satellite are dynamically simulated, and dynamic tracking capability of the satellite data receiving system is tested.
Description
Technical field
The present invention relates to satellite data reception technique field, more specifically, relate to the method for testing of low orbit satellite Ka frequency range data receiving system tracking performance.
Background technology
Along with the in-depth of the understanding to earth resources and environment and the progress of earth observation technology, the rate of information throughput that satellite-ground link needs is more and more higher, such as, remote sensing satellite from present utilizing S frequency range, X frequency range changes utilize Ka frequency range to carry out developing direction that star ground transfer of data is just becoming space flight work into.China also will adopt Ka frequency range down-transmitting data on low rail remote sensing satellite.
Low orbit satellite Ka frequency range transfer of data has dynamic high (because low orbit satellite movement velocity is fast), wave beam is narrow (by 26.5GHz, 12m antenna analysis, beamwidth is 0.065 °) etc. feature, therefore, higher technical requirement is proposed to the tracking performance of low orbit satellite Ka frequency range data receiving system.At present, more deep research is expanded to low orbit satellite Ka frequency range data receiving system both at home and abroad, but there is no the low rail remote sensing satellite utilizing Ka band transmissions data in orbit both at home and abroad at present.
Therefore, the signal of Ka band transmissions can't be utilized directly to test the tracking performance of low orbit satellite Ka frequency range data receiving system by receiving low orbit satellite at present.The tracking performance of indirectly testing low orbit satellite Ka frequency range data receiving system can only be carried out by methods such as aircraft school flying method, static object tracing and target simulator methods.
Fig. 1 is the structured flowchart of existing satellite data receiving system.In general, as shown in Figure 1, existing satellite data receiving system mainly comprises antenna feeder subsystem, antenna mount subsystem and follows the tracks of HF receiving subsystem, and wherein, antenna feeder subsystem mainly comprises parabolic antenna, antenna feed; Antenna mount subsystem mainly comprises antenna mount, antenna control unit, antenna driver element; Follow the tracks of HF receiving subsystem and mainly comprise conjunction road signal amplifier, difference road signal amplifier, passage comprise network, low-converter, track receiver.
The electromagnetic wave signal of parabolic antenna to satellite launch reflects and is converged in paraboloidal focus.Antenna feed is arranged on the focus place of parabolic antenna, for the signal energy converging to parabolic focus all being collected.
The conjunction paths of feed produces and closes road signal, and its difference paths produces difference road signal.Described conjunction road signal comprises data message, and this signal is sent into close in the signal amplifier of road and amplified.Described poor road signal comprises the information (that is, when antenna is just to receive direction, described poor road signal is zero) that antenna departs from receive direction, and this signal is sent in the signal amplifier of difference road and amplified.Afterwards, the conjunction road signal be exaggerated and difference road signal are combined into a road signal in passage comprise network, and this road signal is sent in low-converter and carried out frequency conversion, becomes intermediate-freuqncy signal.Signal after frequency conversion is sent in track receiver, carries out demodulation to recover error signal by track receiver.Error signal sends into antenna control unit, antenna control unit produces angular deviation instruction according to this error signal, antenna driver element is sent in angular deviation instruction, antenna driver element regulates antenna mount to rotate according to this instruction, make antenna alignment receive direction, thus realize antenna to satellite from motion tracking and data receiver.
Can the tracking performance of satellite data receiving system determines this system non-blind area ground tracking satellite obtain satellite data.Therefore, before utilizing satellite data receiving system receiving satellite certificate, need to test its tracking performance.
The factor affecting satellite data receiving system tracking performance mainly contains: the quality factor etc. of tracing mode (as program is followed the tracks of, from motion tracking, antenna set etc.), the pointing accuracy of Satellite Orbit Prediction precision (influencing factor in program tracing mode), system (during antenna direction target because sensing deviation that the reasons such as the mechanical property of system cause), antenna half-power beamwidth, track receiver.Usually, the tracking performance of satellite data receiving system can be characterized by this overall target of systematic tracking accuracy.For low orbit satellite Ka frequency range data receiving system, the requirement of systematic tracking accuracy is less than 1/10 half-power beam width.Such as, if half-power beam width is 0.065 °, so, the requirement of systematic tracking accuracy is less than 0.0065 °.
The aircraft school flying method of the tracking performance of indirectly testing low orbit satellite Ka frequency range data receiving system refers to, the beacon of Ka frequency range is installed the beacon of the Ka frequency range aboard, then made on satellite data receiving system tracking aircraft, thus to the method that the tracking performance of system is tested.The method utilize the air route of aircraft flight come analog satellite flight track, can verifying satellites data receiving system to the follow-up control of dynamic object.But the shortcoming of the method is, need to utilize aircraft and carry out suitable transformation to aircraft, thus cost is high; Need to coordinate with blank pipe, thus difficulty is large, inconvenient.
The static object tracing of the tracking performance of indirectly testing low orbit satellite Ka frequency range data receiving system refers to, the beacon of Ka frequency range is arranged on calibration tower, then and makes the beacon of satellite data receiving system on motion tracking calibration tower, thus to the method that system keeps track performance is tested.Owing to the tracking of the beacon on calibration tower being a kind of static tracking, therefore, making merely is can not test satellite data receiving system to the tracking performance of the dynamic objects such as low orbit satellite in this way.
The target simulator method of the tracking performance of indirectly testing low orbit satellite Ka frequency range data receiving system refers to, simulator is utilized to simulate generation angular deviation signal, and this angular deviation signal is sent into antenna control unit, thus to the method that system keeps track performance is tested.When the method utilizes the artificial angular deviation signal produced to carry out analogue system tracking satellite, the angular deviation signal of actual generation carrys out the tracking performance of test macro.But because the generation of angular deviation signal is relevant with several factors, therefore the method implements difficulty comparatively greatly, and different systems has very large difference, and the versatility of the method is poor.
Summary of the invention
The present invention makes to solve the problems of the technologies described above, its objective is, a kind of method of testing of low orbit satellite Ka frequency range data receiving system tracking performance is provided, the method is simple and direct, practical, good test effect, and can avoid the shortcoming of aircraft school flying method, static object tracing, target simulator method.
To achieve these goals, the invention provides a kind of method of testing of low orbit satellite Ka frequency range data receiving system tracking performance, the method comprises the steps: 1) triaxial antennas in low orbit satellite Ka frequency range data receiving system is aimed at the Ka frequency range beacon in calibration tower and this beacon is carried out from motion tracking; 2) the 3rd axle of described triaxial antennas is made to carry out even acceleration or even underdrive according to predetermined angular acceleration; 3) judge whether the tracking performance of described system meets the requirement of tracking satellite according to the azimuth angle error value measured in the process of beacon described in motion tracking, if the azimuth angle error value measured is less than or equal to predetermined threshold all the time, then be judged as that the tracking performance of this system meets the requirement of tracking satellite, if the azimuth angle error value measured has when being greater than this predetermined threshold, be then judged as that the tracking performance of this system not exclusively meets the requirement of tracking satellite.Here, triaxial antennas is preferably orientation-pitching-three spindle-type triaxial antennas.
Wherein, required maximum Azimuth Acceleration when the triaxial antennas that described predetermined angular acceleration should be more than or equal to this system follows the tracks of low orbit satellite.Described predetermined threshold can be 1/10 of Ka frequency range half-power beam width.
Preferably, described predetermined angular acceleration can according to following formulae discovery:
Wherein,
for maximum Azimuth Acceleration, unit is rad/s
2;
for maximum Azimuth, Speed, Altitude, unit is rad/s; H is satellite orbital altitude, and unit is km; μ is geocentric gravitational constant, is taken as 3.986005 × 10
14m
3/ s
2); r
efor earth radius, 6378.14km can be taken as;
for the maximum angle of pitch.
Preferably, the described maximum angle of pitch
83 ° can be taken as.
In addition, the slewing area of the 3rd axle of described triaxial antennas can between ± 180 °.
Preferably, described azimuth angle error value can error voltage measured by the track receiver in this system and the directional sensitivity of demarcating in advance calculate.
From description above with put into practice, present invention utilizes the feature of triaxial antennas, while rotation the 3rd axle, regulate the orientation of antenna and pitching that the beacon of antenna to the Ka frequency range on calibration tower is carried out from motion tracking, thus dynamically can simulate the situation of antenna tracking Ka frequency range low orbit satellite and test out the dynamic tracking capabilities of satellite data receiving system.The solution of the present invention is avoided using aircraft school to fly to wait the method that cost is high, convenience is poor, avoid the technological difficulties producing simulation angular error signal in target simulator method, also solve static object tracing can not testing authentication low orbit satellite data receiving system to the problem of the follow-up control of dynamic object, therefore, the research of method of the present invention to low orbit satellite Ka frequency range data receiving system is highly profitable.
Accompanying drawing explanation
Fig. 1 is the structured flowchart of existing satellite data receiving system;
Fig. 2 is satellite orbit angle analysis model;
Fig. 3 is the tracking blind area comparison diagram of orientation-pitching type antenna and triaxial antennas;
Fig. 4 is the flow chart of the method for testing of low orbit satellite Ka frequency range data receiving system tracking performance described in one embodiment of the present of invention;
Fig. 5 is the schematic diagram of the 3rd axle of triaxial antennas.
Embodiment
The embodiment of the method for testing of low orbit satellite Ka frequency range data receiving system tracking performance of the present invention is described below with reference to the accompanying drawings.Those of ordinary skill in the art can recognize, when without departing from the spirit and scope of the present invention, can revise by various different mode to described embodiment.Therefore, accompanying drawing is illustrative with being described in essence, instead of for limiting the protection range of claim.
Usually, in satellite data receiving system, antenna mount adopts triaxial antennas mounting usually.Triaxial antennas mounting be by orientation-bottom of pitching type antenna mount is set up turntable (being called for short the 3rd axle) that a table top tilts and is formed.The original object of setting up the 3rd axle is the tracking blind area in order to eliminate when high elevation angle satellite crosses top.Below in conjunction with Fig. 2 and Fig. 3, concise and to the point description is carried out to triaxial antennas mounting.
Fig. 2 is satellite orbit angle analysis model.As shown in Figure 2, if orientation-pitching type antenna is in the A point on plane (such as ground) α, satellite flies along the straight line m right-to-left being parallel to plane α with speed v.The orthographic projection of straight line m on the plane α any point that to be straight line m ', S be on straight line m, M is its orthographic projection on straight line m ', and T is a specified point on straight line m, and N is its orthographic projection on straight line m ', and has AT ⊥ m, AN ⊥ m '.Satellite is through a T, and it was just called top for antenna, and T also can be called summit.∠ MAN be antenna tracking satellite to azimuth during S point, be designated as θ, ∠ SAM be antenna tracking satellite to angle of pitch during S point, be designated as
antenna tracking satellite has been azimuth angle theta=0 during the T of summit, the angle of pitch
(i.e. the maximum angle of pitch).Satellite altitude SM or TN is designated as h.According to simple geometric operation, the rate of change that can obtain antenna azimuth θ t is in time:
As shown from the above formula, when the maximum angle of pitch
when exceeding certain value, satellite is crossed before and after top (θ ~ 0), and the change d θ/dt of antenna azimuth is too large, thus makes antenna cannot tracking satellite.So, cross before and after top at satellite and just create antenna tracking blind area.
In order to eliminate antenna tracking blind area, can in orientation-bottom of pitching type antenna mount is set up the turntable (the 3rd axle) that a table top tilts, thus is formed triaxial antennas mounting.Fig. 3 is the tracking blind area comparison diagram of orientation-pitching type antenna and triaxial antennas.For orientation-pitching type antenna, as shown in the left part in Fig. 3, region between ray AC and AD forms the tracking blind area of this antenna, and the region between ray AB and AC forms the safe tracing area of this antenna, and during top, (T point) satellite is in tracking blind area excessively.The event of antenna tilt δ angle is made owing to adding the 3rd axle, for triaxial antennas, as shown in the right part in Fig. 3, the safe tracing area of antenna becomes the region between ray AB ' and AC ', follow the tracks of blind area with regard to making satellite when pushing up shift out like this, now the maximum angle of pitch of antenna becomes
Have the antenna of triaxial antennas mounting when tracking satellite, the 3rd axle just no longer changes after set, only the azimuth of antenna and the angle of pitch need be regulated to carry out tracking satellite.
In order to test the ability of the tracking satellite of low orbit satellite Ka frequency range data receiving system, the present invention utilizes the 3rd axle of static calibration tower and rotation to carry out the relative motion of analog satellite and antenna, thus overcome the simple static object tracing that uses and can not test satellite data receiving system to the shortcoming of the tracking performance of the dynamic objects such as low orbit satellite, also avoid the method using the costs such as aircraft school flying method high, inconvenient simultaneously.According to the feature of three-axis mount, when antenna is in the state from motion tracking calibration tower beacon in orientation and pitching, if at the uniform velocity, even acceleration or even underdrive the 3rd axle, then azimuth axis also will at the uniform velocity, even acceleration or even deceleration rotate backward, thus guarantee the automatic tracking mode of antenna to calibration tower beacon.Due in the actual tracing process of low orbit satellite, maximum angular rate needed for antenna, maximum angular acceleration all appear on azimuth axis, and satellite cross before and after top to the rate of pitch of antenna and angular acceleration less demanding, therefore can adopt and keep antenna to follow the tracks of to calibration tower beacon the motion that the method for simultaneously rotating the 3rd axle carrys out simulated target in orientation and pitching, thus the Passing zenith tracing ability of testing authentication low orbit satellite Ka UHF band reception system.In other words, the rotation of the 3rd axle can the motion of analog satellite when passing through summit.Therefore, if can prove that the antenna of the 3rd axle rotation can follow the tracks of the beacon on calibration tower by test, so, just can prove that this antenna can follow the tracks of satellite when crossing top.Because when summit crossed by passing of satelline antenna, the tracking difficulty of antenna is maximum, therefore, also just can prove that this antenna can ground, non-blind area tracking satellite.
Fig. 4 is flow chart, shows the method for testing of the low orbit satellite Ka frequency range data receiving system tracking performance described in one embodiment of the present of invention.As shown in Figure 4, method of the present invention comprises the steps:
First, in step sl, the triaxial antennas in low orbit satellite Ka frequency range data receiving system is aimed at the Ka frequency range beacon in calibration tower, and this beacon is carried out from motion tracking.Here, triaxial antennas is preferably orientation-pitching-three spindle-type triaxial antennas.In this step, first by the 3rd axle set of triaxial antennas, then can the azimuth of manual adjustments triaxial antennas and the angle of pitch, make triaxial antennas aim at Ka frequency range beacon in calibration tower.Specifically, when the beacon signal that antenna receives is maximum, just think that the beam center of antenna has aimed at the beacon on calibration tower.
After triaxial antennas aims at described beacon, low orbit satellite Ka frequency range data receiving system is set to automatic tracking mode, triaxial antennas is carried out from motion tracking described beacon.Now, because the beacon on calibration tower is static, therefore, the poor road signal that the poor paths of antenna feed produces is zero, and track receiver does not all have error voltage to produce in orientation and pitching yet, and antenna will aim at beacon statically.
Afterwards, in step s 2, the 3rd axle of described triaxial antennas is made to carry out even acceleration or even underdrive according to predetermined angular acceleration.Fig. 5 is schematic diagram, shows the 3rd axle of triaxial antennas.As shown in Figure 5, triaxial antennas the 3rd axle is the turntable that a table top tilts, and the angle of inclination of this turntable table top is that δ, δ can be designed as 5 ° to 7 °.Can get δ is in the present invention 7 °, and like this, the maximum angle of pitch of antenna is 90 °-7 °=83 °.In addition, the 3rd axle can rotate around the axle perpendicular to turntable bottom surface, and the scope of angle of rotation can between ± 180 °, as shown in the two-way curve arrow in Fig. 5.
The angular acceleration that 3rd axle rotates should be more than or equal to required maximum Azimuth Acceleration when triaxial antennas follows the tracks of low orbit satellite, like this, could simulate the tracking to low orbit satellite.In addition, to in the actual tracing process of low orbit satellite, maximum angular rate needed for antenna, maximum angular acceleration all appear on azimuth axis, satellite cross before and after top to the rate of pitch of antenna and angle of pitch acceleration less demanding, therefore, maximum Azimuth Acceleration being given the 3rd axle just can situation when analog satellite crosses top well enough.And antenna also has certain angular speed and angular acceleration change in pitching in the rotation process of the 3rd axle, therefore, rotate the 3rd axle and also can verify the follow-up control of antenna in pitching.
In one embodiment, described predetermined angular acceleration is according to following formulae discovery:
Wherein,
for maximum Azimuth Acceleration, unit is rad/s
2;
for maximum Azimuth, Speed, Altitude, unit is rad/s; H is satellite orbital altitude, and unit is km; μ is geocentric gravitational constant, is taken as 3.986005 × 10
14m
3/ s
2); r
efor earth radius, 6378.14km can be taken as;
for the maximum angle of pitch.Preferably, the described maximum angle of pitch
83 ° can be taken as.
The computing formula of above-mentioned angular acceleration is from the computing formula of low rail (sun-synchronous orbit) satellite relative to the dynamic property of ground receiving system.Utilize above-mentioned formula, if the maximum tracking elevation angle of antenna is 83 °, when the satellite that can calculate multiple orbital attitudes crosses top, the maximum angular rate needed for antenna tracking satellite and maximum angular acceleration.Table 1 shows result of calculation.Also the result of calculation of maximum angle of pitch acceleration is listed in Table 1 as a comparison.The computing formula of maximum angle of pitch acceleration is as follows:
From table 1, less demanding to angle of pitch acceleration.
Table 1
In the process that the 3rd axle rotates, because system is in automatic tracking mode, therefore, angular error signal can be delivered to antenna control unit by track receiver continuously, antenna control unit sends position command accordingly, control antenna changes azimuth and the angle of pitch, to make antenna directional beacon all the time.
Then, in step s3, judge that can described system the Ka frequency range data of complete reception low orbit satellite transmission according to the azimuth angle error value measured in the process of beacon described in motion tracking, if the azimuth angle error value measured is less than or equal to predetermined threshold all the time, then be judged as the Ka frequency range data of the complete reception low orbit satellite transmission of this system energy, if the azimuth angle error value measured has when being greater than this predetermined threshold, be then judged as that this system can not the Ka frequency range data of complete reception low orbit satellite transmission.
Specifically, described predetermined threshold can be 1/10 of Ka frequency range half-power beam width.Such as, if half-power beam width is 0.065 °, so, namely described predetermined threshold can be set to 0.0065 °.
Described azimuth angle error value can error voltage measured by the track receiver in this system and the directional sensitivity of demarcating in advance calculate.
If judge that the tracking performance of system not exclusively meets tracking satellite requirement, so, should check the various aspects of system, the dynamic property of improved system.System after improvement can re-use method of the present invention and test, until system is by test of the present invention, becomes and can follow the tracks of low orbit satellite and the receiving system receiving Ka band satellite data.
From description above with put into practice, present invention utilizes the feature of triaxial antennas, while rotation the 3rd axle, regulate the orientation of antenna and pitching that the beacon of antenna to the Ka frequency range on calibration tower is carried out from motion tracking, thus dynamically can simulate the situation of antenna tracking Ka frequency range low orbit satellite and test out the dynamic tracking capabilities of satellite data receiving system.The solution of the present invention is avoided using aircraft school to fly to wait the method that cost is high, convenience is poor, avoid the technological difficulties producing simulation angular error signal in target simulator method, also solve static object tracing can not testing authentication low orbit satellite data receiving system to the problem of the follow-up control of dynamic object, therefore, the research of method of the present invention to low orbit satellite Ka frequency range data receiving system is highly profitable.
It will be appreciated by those skilled in the art that the method for testing of the low orbit satellite Ka frequency range data receiving system tracking performance that the invention described above is proposed, various improvement and combination can also be made on the basis not departing from content of the present invention.Therefore, protection scope of the present invention should be determined by the content of appending claims.
Claims (5)
1. a method of testing for low orbit satellite Ka frequency range data receiving system tracking performance, comprises the steps:
1) triaxial antennas in low orbit satellite Ka frequency range data receiving system is aimed at the Ka frequency range beacon in calibration tower and this beacon is carried out from motion tracking;
2) the 3rd axle of described triaxial antennas is made to carry out even acceleration or even underdrive according to predetermined angular acceleration;
3) judge whether the tracking performance of described system meets the requirement of tracking satellite according to the azimuth angle error value measured in the process of beacon described in motion tracking, if the azimuth angle error value measured is less than or equal to predetermined threshold all the time, then be judged as that the tracking performance of this system meets the requirement of tracking satellite, if the azimuth angle error value measured has when being greater than this predetermined threshold, be then judged as that the tracking performance of this system not exclusively meets the requirement of tracking satellite.
2. the method for testing of low orbit satellite Ka frequency range data receiving system tracking performance as claimed in claim 1, wherein, maximum Azimuth Acceleration required when the triaxial antennas that described predetermined angular acceleration is more than or equal to this system follows the tracks of low orbit satellite.
3. the method for testing of low orbit satellite Ka frequency range data receiving system tracking performance as claimed in claim 1, wherein, described predetermined angular acceleration is according to following formulae discovery:
Wherein,
for maximum Azimuth Acceleration;
for maximum Azimuth, Speed, Altitude; H is satellite orbital altitude; μ is geocentric gravitational constant, is taken as 3.986005 × 10
14m
3/ s
2; r
efor earth radius;
for the maximum angle of pitch.
4. the method for testing of low orbit satellite Ka frequency range data receiving system tracking performance as claimed in claim 1, wherein, described predetermined threshold is 1/10 of Ka frequency range half-power beam width.
5. the method for testing of low orbit satellite Ka frequency range data receiving system tracking performance as claimed in claim 1, wherein, the error voltage of described azimuth angle error value measured by the track receiver in this system and the directional sensitivity of demarcating in advance calculate.
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| CN108802771A (en) * | 2018-08-24 | 2018-11-13 | 武汉导航与位置服务工业技术研究院有限责任公司 | Navigation satellite signal tracking method, equipment, system and storage medium |
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| CN112556636A (en) * | 2020-11-30 | 2021-03-26 | 国家卫星气象中心(国家空间天气监测预警中心) | Method for calibrating receiving antenna by using GPS data provided by satellite |
| CN112556636B (en) * | 2020-11-30 | 2022-11-11 | 国家卫星气象中心(国家空间天气监测预警中心) | Method for calibrating receiving antenna by using GPS data provided by satellite |
| CN112965041A (en) * | 2021-02-10 | 2021-06-15 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Spherical phased array antenna wave control self-tracking difference array division method |
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