CN102684774B - Method for calibrating gain and time delay of antenna in constellation communication mode - Google Patents
Method for calibrating gain and time delay of antenna in constellation communication mode Download PDFInfo
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- CN102684774B CN102684774B CN201210171232.4A CN201210171232A CN102684774B CN 102684774 B CN102684774 B CN 102684774B CN 201210171232 A CN201210171232 A CN 201210171232A CN 102684774 B CN102684774 B CN 102684774B
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Abstract
The invention discloses a method for calibrating gain and time delay of an antenna in a constellation communication mode. The transmission characteristic can be tested once by utilizing a vector network analyzer based on abandoning the gain and the time delay of the traditional test antenna; and according to the characteristics of constellation, calibrated gain and time delay can be further confirmed by utilizing the characteristics of the whole spacecraft in a constellation wireless mode, so that the correctness of a test can be verified. The method does not need complicated ground support equipment and is simple and universal for a satellite in the constellation communication mode; by utilizing the method, the time delay and the gain of the antenna can be calibrated once and further verified in the constellation wireless mode, so that the calibrated precision is higher. By adopting the simple calibration method, the complexity of the test in the constellation wireless mode is greatly reduced, and the efficiency is improved. The calibration method is suitable for the constellation with two satellites, and is also simple and feasible for calibration of various satellites, thereby being a practical and effective calibration method.
Description
Technical field
Demarcate the method for antenna gain and time delay under the present invention relates to a kind of constellation communication pattern, belong to formation flight device technical field.
Background technology
Flight formation constellation pattern is a kind of novel space networking model, inter-satellite link is adopted to carry out intersatellite communication, not only be conducive to improving constellation operation performance, expand constellation detection covering spatial domain scope, but also being conducive to the scale reducing ground support system, the observing and controlling and the number that enormously simplify ground system pass management.
Existing constellation communication pattern, that is developing is many, and the experience that success is flown in-orbit is less.Therefore, for spacing wireless constellation networking model, we need abundant checking under wireless status is carried out on ground, and verify wireless under state, with regard to needing, the parameter of antenna is demarcated.
In space communication system, antenna is used as emitting electromagnetic wave and receives electromagnetic wave signal, during transmitting, the power output of transmitter by antenna to space radiation; During reception, convert the electromagnetic wave energy in space to radio-frequency (RF) energy by antenna and send receiver to, for space system, and the sensitivity of receiver is an important index parameter, here the signal energy of transmitter is known, space radiation also can calculate, and therefore the accuracy of antenna gain is the prerequisite ensureing receiver sensitivity.
In constellation measuring system, find range by measuring time delay, therefore Time Delay of Systems null value is the prerequisite ensureing that whether range finding is correct, and the time delay of antenna is the important component part of system, therefore the calibration accuracy of antenna delay is also very important, the direct influential system range accuracy of preparation of the time delay of antenna.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, demarcates the method for antenna gain and time delay under proposing a kind of constellation communication pattern.
Technical scheme of the present invention is:
Demarcate a method for antenna gain and time delay under constellation communication pattern, rely on the first satellite, the second satellite, ground-plane antenna and vector network analyzer and realize, step is as follows:
(1) alignd by the phase center of two same antennas on ground, the distance between the phase center of two antennas is d
0;
(2) the radio frequency mouth of the two ends of vector network analyzer and two ground-plane antennas is carried out closed loop connection, the overall gain G of this closed loop link can be obtained by vector network analyzer measurement
awith overall delay T
a;
(3) by formula G
f0=92.45+20lgd
0+ 20lg f
0and T
f0=d
0/ c calculates the loss G of free space
f0with the Electromagnetic Wave Propagation time delay T of free space
f0, f
0for wave frequency, c is the light velocity;
(4) by formula G
0=(G
a-G
f0)/2 and T
0=(T
a-T
f0)/2 calculate the gain G of ground-plane antenna
0with time delay T
0;
(5) in the antenna on the first satellite, ground-plane antenna and vector network analyzer are carried out closed loop connection, then can be obtained the overall gain G of this closed loop link by vector network analyzer measurement
bwith overall delay T
b;
By formula G
1=G
b-G
0-G
f0and T
1=T
b-T
0-T
f0calculate the gain G of the antenna on described first satellite
1with time delay T
1;
In antenna on second satellite, ground-plane antenna one and vector network analyzer are carried out closed loop connection, then can be obtained the overall gain G of this closed loop link by vector network analyzer measurement
cwith overall delay T
c;
By formula G
2=G
c-G
0-G
f0and T
2=T
c-T
0-T
f0calculate the gain G of the antenna on described second satellite
2with time delay T
2;
(6) two ends of adjustable attenuator are carried out closed loop respectively by cable with the two ends of vector network analyzer to be connected, then can be measured the decay G obtaining this closed loop link by vector network analyzer
10with time delay T
10
(7) by formula P
1=P-G
1-G
2-G
10calculate the power P of receiver on star
1, pass through formula S
1=S+T
1+ T
2+ T
10calculate time delay S between star
1, P is the power of transmitter on star, and S postpones between star when satellite not adding antenna;
(8) P is judged
1=P '
1with S
1=S '
1whether all set up, if all set up, then the parameter of demarcating is effective, if not all set up, then returns step (2) from newly carrying out; P '
1the receiver actual power determined for utilizing remote measurement on star, S '
1for time delay between the actual star that satellite itself provides.
Invention advantage is compared with prior art:
(1) because time delay and gain all belong to transmission characteristic, present invention utilizes the feature of vector network analyzer, carried out disposable demarcation to two parameters, with traditional method of measurement ratio, associated test devices greatly reduces;
(2) order of general constellation test first carries out single satellite and ground installation wireless test, and then the wireless test carried out between constellation, traditional standard antenna has been used as in ground by the present invention cleverly, avoids and introduces traditional standard antenna, saved cost;
(3) present invention utilizes the feature of the Cross-Link measurement time difference, in conjunction with the own characteristic of receiver on star, make use of and calculate and satellite own characteristic, further double calculation is checked to time difference of antenna and gain;
(4) the present invention has generality to there being constellation pattern, is applicable to double star, is also applicable to many stars, therefore has good promotion and application and is worth.
Accompanying drawing explanation
Fig. 1 is the schematic diagram that the closed loop measuring ground-plane antenna connects;
Fig. 2 is the schematic diagram that measurement first satellite is connected with the closed loop of ground-plane antenna
Fig. 3 is the schematic diagram that measurement second satellite is connected with the closed loop of ground-plane antenna
Fig. 4 is the closed loop connection diagram measuring adjustable attenuator and two end cables
Fig. 5 is the connection diagram between constellation
Fig. 6 is flow chart of the present invention.
Embodiment
In space communication system, antenna is used as emitting electromagnetic wave and receives electromagnetic wave signal, during transmitting, the power output of transmitter by antenna to space radiation; During reception, convert the electromagnetic wave energy in space to radio-frequency (RF) energy by antenna and send receiver to, for space system, and the sensitivity of receiver is an important index parameter, here the signal energy of transmitter is known, space radiation can calculate, and therefore the accuracy of antenna gain is the prerequisite ensureing receiver sensitivity.
In constellation measuring system, find range by measuring time delay, therefore Time Delay of Systems null value is the prerequisite ensureing that whether range finding is correct, and the time delay of antenna is the important component part of system, therefore the accuracy of the measurement of antenna delay is also very important, therefore the direct influential system range accuracy of the preparation of the time delay of antenna.
Introduction of the present invention be that a kind of gain of antenna and time delay demarcate a kind of method simultaneously, and the result of demarcating is verified under constellation pattern, the method relies on vector network analyzer, ground two same antennas, the first satellite, the second satellite and adjustable attenuator.Step of the present invention is as follows:
(1) alignd by the phase center of two same antennas on ground, the distance between the phase center of two antennas is d0;
(2) as shown in Figure 1, the radio frequency mouth of the two ends of vector network analyzer and two ground-plane antennas is carried out closed loop connection, the gain of note ground-plane antenna is G
0, the time delay of antenna is T
0, the loss of antenna phase center free space is G
f0, space time delay is T
f0, the overall gain G of this closed loop link is obtained by vector network analyzer measurement
awith overall delay T
a, wherein G
a=2G
0+ G
f0, T
a=2T
0+ T
f0;
(3) gain G of ground-plane antenna is pushed over out by step (2)
0=(G
a-G
f0)/2, time delay T
0=(T
a-T
f0)/2, wherein the formula of the loss of free space is G
f0=92.45+20lgd
0+ 20lg f
0, the Electromagnetic Wave Propagation time delay T of free space
f0=d
0/ c, f
0for wave frequency, c is the light velocity, can draw the gain G of ground-plane antenna thus
0with antenna transmission time delay T
0;
(4) in the antenna on the first satellite, ground-plane antenna and vector network analyzer are carried out closed loop connection, as shown in Figure 2, remember the gain G of the antenna on the first satellite
1, time delay is T
1, then the overall gain G of this closed loop link can be obtained by vector network analyzer measurement
bwith overall delay T
b, wherein G
b=G
1+ G
0+ G
f0, T
b=T
1+ T
0+ T
f0;
(5) gain of the first satellite antenna is pushed over out by formula G by step (4)
1=G
b-G
0-G
f0and T
1=T
b-T
0-T
f0, from previous step, T
0, T
f0, G
0, G
f0for known quantity, the gain G of the antenna on the first satellite therefore can be calculated
1with time delay T
1;
(6) in like manner, in the antenna on the second satellite, ground-plane antenna and vector network analyzer are carried out closed loop connection, and as shown in Figure 3, other same step (4) and (5), remember the gain G of the antenna on the second satellite
2, time delay is T
2, the overall gain G of this closed loop link can be obtained by vector network analyzer measurement
cwith overall delay T
c, by formula G
2=G
c-G
0-G
f0and T
2=T
c-T
0-T
f0calculate the gain G of the antenna on described second satellite
2with time delay T
2;
(7) as shown in Figure 4, the two ends of adjustable attenuator are carried out closed loop respectively by cable with the two ends of vector network analyzer and is connected, then can be measured the complete attenuation G obtaining this closed loop link by vector network analyzer
10with overall delay T
10;
(8) adjustable attenuator in step (7) and two ends are accessed in constellation respectively by cable, as shown in Figure 5, the entrance power of receiver is controlled by reconciling adjustable attenuator, after the entrance power i.e. power of the second satellite transmitter of receiver wirelessly transmits, deduct various space losses etc., at the power of the first satellite receiver mouth, if P is the power of transmitter on the second satellite, can be measured as known in advance, P
1be the power of receiver entrance on the first satellite, by formula P
1=P-G
1-G
2-G
10-G
f0the entrance power P of known first satellite receiver
1; When setting S as not adding antenna, communicate between whole star under cable status all propagation delay times simultaneously, and comprise the propagation delay time that the first satellite, the second satellite are all, S directly measures by communication equipment between star, if S
1for propagation delay time between the star under wireless after adding antenna, comprise space, the first satellite antenna, the second satellite antenna, therefore can calculate S
1=S+T
1+ T
2+ T
10+ T
f0, calculate time delay S between star
1; , S is the constellation time delay of communication measurement between star under cable status when satellite not adding antenna,
(8) last in the pattern of Fig. 5, we can draw the power P of the first satellite receiver reality by remote measurement on star '
1, simultaneously directly measure all propagation delay time S ' under radio conditions between star by communication equipment between star
1, by P '
1and S '
1respectively with the P that calculates in step (7)
1and S
1compare, namely judge P
1=P '
1with S
1=S '
1whether all set up, if all set up, then the antenna gain of demarcating before illustrating and time delay effectively, if not all set up, then return step (2) from newly carrying out.
The content that in specification of the present invention, other are not described in detail belongs to the known technology of professional and technical personnel in the field.
Claims (1)
1. demarcate a method for antenna gain and time delay under constellation communication pattern, rely on the first satellite, the second satellite, ground-plane antenna and vector network analyzer and realize, it is characterized in that step is as follows:
(1) alignd by the phase center of two same antennas on ground, the distance between the phase center of two antennas is d
0;
(2) the radio frequency mouth of the two ends of vector network analyzer and two ground-plane antennas is carried out closed loop connection, the overall gain G of this closed loop link can be obtained by vector network analyzer measurement
awith overall delay T
a;
(3) by formula G
f0=92.45+20lgd
0+ 20lg f
0and T
f0=d
0/ c calculates the loss G of free space
f0with the Electromagnetic Wave Propagation time delay T of free space
f0, f
0for wave frequency, c is the light velocity;
(4) by formula G
0=(G
a-G
f0)/2 and T
0=(T
a-T
f0)/2 calculate the gain G of ground-plane antenna
0with time delay T
0;
(5) in the antenna on the first satellite, ground-plane antenna and vector network analyzer are carried out closed loop connection, then can be obtained the overall gain G of this closed loop link by vector network analyzer measurement
bwith overall delay T
b;
By formula G
1=G
b-G
0-G
f0and T
1=T
b-T
0-T
f0calculate the gain G of the antenna on described first satellite
1with time delay T
1;
In antenna on second satellite, ground-plane antenna one and vector network analyzer are carried out closed loop connection, then can be obtained the overall gain G of this closed loop link by vector network analyzer measurement
cwith overall delay T
c;
By formula G
2=G
c-G
0-G
f0and T
2=T
c-T
0-T
f0calculate the gain G of the antenna on described second satellite
2with time delay T
2;
(6) two ends of adjustable attenuator are carried out closed loop respectively by cable with the two ends of vector network analyzer to be connected, then can be measured the decay G obtaining this closed loop link by vector network analyzer
10with time delay T
10;
(7) by formula P
1=P-G
1-G
2-G
10-G
f0calculate the power P of receiver entrance on the first satellite
1, pass through formula S
1=S+T
1+ T
2+ T
10+ T
f0calculate time delay S between star
1, P is the power of transmitter on the second satellite, and S postpones between star when satellite not adding antenna;
(8) P is judged
1=P '
1with S
1=S '
1whether all set up, if all set up, then the parameter of demarcating is effective, if not all set up, then returns step (2) from newly carrying out; P '
1the receiver actual power determined for utilizing remote measurement on star, S '
1for directly being measured all propagation delay times under radio conditions between star by communication equipment between star.
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|---|---|---|---|
| CN201210171232.4A CN102684774B (en) | 2012-05-25 | 2012-05-25 | Method for calibrating gain and time delay of antenna in constellation communication mode |
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| CN102684774B true CN102684774B (en) | 2015-04-22 |
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| CN104333408B (en) * | 2014-09-26 | 2017-09-29 | 航天东方红卫星有限公司 | A kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5740164A (en) * | 1993-02-09 | 1998-04-14 | Teledesic Corporation | Traffic routing for satellite communication system |
| CN101494495A (en) * | 2009-02-27 | 2009-07-29 | 航天东方红卫星有限公司 | Method for implementing split-second precision synchronism using spread-spectrum answering machine |
| CN101902288A (en) * | 2010-08-02 | 2010-12-01 | 中国航天科工集团第二研究院二○三所 | Method for measuring delay of direct sequence spread spectrum binary phase shift keying modulator |
-
2012
- 2012-05-25 CN CN201210171232.4A patent/CN102684774B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5740164A (en) * | 1993-02-09 | 1998-04-14 | Teledesic Corporation | Traffic routing for satellite communication system |
| CN101494495A (en) * | 2009-02-27 | 2009-07-29 | 航天东方红卫星有限公司 | Method for implementing split-second precision synchronism using spread-spectrum answering machine |
| CN101902288A (en) * | 2010-08-02 | 2010-12-01 | 中国航天科工集团第二研究院二○三所 | Method for measuring delay of direct sequence spread spectrum binary phase shift keying modulator |
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