CN104333408B - A kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation - Google Patents
A kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation Download PDFInfo
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- CN104333408B CN104333408B CN201410505466.7A CN201410505466A CN104333408B CN 104333408 B CN104333408 B CN 104333408B CN 201410505466 A CN201410505466 A CN 201410505466A CN 104333408 B CN104333408 B CN 104333408B
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
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- 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
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
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Abstract
A kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation of the present invention, including：First satellite A, the second satellite B；Communication equipment recovers payload data and whole star telemetry after carrying out digital processing to the radiofrequency signal of reception between first satellite A star, and sends user to；Communication equipment is sent to the second satellite B after carrying out digital processing to the remote operating instruction received in radiofrequency signal form between first satellite A star；Communication equipment carries out recovering remote operating instruction after digital processing to radiofrequency signal between second satellite B star, sends associated user to and performs corresponding remote operating task；Communication equipment is sent to the first satellite A to the payload and whole star telemetry that receive after carrying out digital processing in radiofrequency signal form between second satellite B star.The present invention establishes lasting, two-way high dynamic inter-satellite link, meets Space teleoperation task low time delay requirement.
Description
Technical field
The present invention relates to a kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation, belong to satellite
Communication technical field.
Background technology
Need to cooperate by inter-satellite link between two satellites of Space teleoperation task, complete mutual data
Transmission, and coordinate big system to complete some particular tasks.Space teleoperation mission requirements Inter-satellite Communication System possesses lasting, two-way
Communication capacity.Because Space teleoperation task requires higher to real-time communication, therefore, Inter-satellite Communication System should meet space
Requirement of the remote operating task to the low time delay that communicates.In addition, two satellites of Space teleoperation task need in assembled state and divided
From communication task between lasting two-way star is completed in the state of farther out, high requirement is proposed the dynamic capability communicated star,
The signal level received should be prevented to reach that demodulation threshold prevents signal from causing very much the saturation of receiver by force again, therefore needed
Design a kind of low time delay, high dynamic Inter-satellite Communication System for adapting to Space teleoperation task.
The relative position between two satellites due to realizing Space teleoperation task is dynamic change, its design difficulty
Mainly have：(1) transmission power of communication equipment is designed as 10~15mW scopes between star, and receiving sensitivity is designed as -116dBm, is used to
Ensure two stars when at a distance of 15km states, communication control processor can receive the signal level of enough demodulation between star；And ensure two
Star is when apart from 0.15m, and communication control processor can not reach saturation state between star；(2) communication equipment is received, demodulated and divides between design star
The time for solving payload data is 581ms, to meet communication low time delay of the Space teleoperation task to Inter-satellite Communication System
It is required that；(3) communication antenna is arranged on the opposite face of two satellites between design star, and ensures to reach when two satellites are mutually moved
± 60 ° of visible angle, to ensure that communication can provide lasting, two-way reliable and stable communication link between star, it is impossible to exist
Communication disruption region；(4) because of the influence of space environment, the radiofrequency signal for reaching two DVBs is not consistent therefore right
Communication antenna is tested in the isolation of different angles between star, determines that antenna is pacified according to its isolation most close test result
Fill angle, with ensure the reception level of communication equipment between two Satellites as close possible to.
The content of the invention
The technology of the present invention solves problem：Overcome the deficiencies in the prior art there is provided one kind be used for realize high dynamic and
The Inter-satellite Communication System of low time delay Space teleoperation, the present invention can set up lasting, two-way high dynamic inter-satellite link, Neng Gouman
Requirement of the sufficient Space teleoperation task to the low time delay that communicates；The day that communicates between star is determined by using the test result of isolation between antennas
The mounting means of line, so as to realize a kind of low time delay, high dynamic Inter-satellite Communication System for adapting to Space teleoperation task.
The present invention technical solution be：
A kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation, including：First satellite A,
Two satellite B；Wherein the first satellite A and the second satellite B are respectively again including the day that communicated between star between communication equipment, star between Microwave Net, star
Line；
Communication antenna passes through microwave network between star by the radiofrequency signal from the second satellite B is received between first satellite A star
Network, sends and recovers payload data after carrying out BPSK demodulation, filtering, formatting, descrambling, synchronization check to communication equipment between star
With the second satellite B whole star telemetry (wherein, filter, format, descrambling is referred to as digital processing), communication equipment passes through between star
Payload data is respectively transmitted and used to related user by CAN to the second satellite B whole star telemetry；While the
Communication equipment receives the remote operating instruction for the second satellite B that Star Service subsystem is sent by CAN between one satellite A star, and right
Remote operating instruction is carried out after BPSK modulation, power amplification, filtering, by between star between Microwave Net and star communication antenna with radio frequency
Signal form is sent to the second satellite B；
Communication antenna receives the radiofrequency signal from A stars between second satellite B star, is penetrated this by Microwave Net between star
Frequency signal delivers to communication equipment between the second satellite B star；Between star communication equipment radiofrequency signal is carried out within a certain period of time BPSK demodulation,
Remote operating instruction is recovered after filtering, formatting, synchronization, the associated user for being transferred to B stars by RS422 interfaces performs phase
The remote operating task answered；Communication equipment receives the payload from Star Service subsystem and whole star remote measurement between second satellite B star
Data, and BPSK modulation, power amplification, filtering are carried out to it, by the way that communication antenna is believed with radio frequency between Microwave Net and star between star
Number form is sent to the first satellite A.
Communication equipment includes Receiver And Transmitter between slave computer, star between star again between the star of the first satellite A；Between its culminant star
Slave computer includes slave computer between slave computer and the second star between the first star, the two cold standby each other；Receiver includes the first star between star
Between receiver between receiver and the second star, both work simultaneously, each other Hot Spare；Emitter includes emitter between the first star between star
And second emitter between star, the two cold standby each other；
Receiver is solved to the radiofrequency signal of reception simultaneously between receiver and the second star between first satellite A the first star
Adjust, filtering, format, descrambling, synchronization and after verifying, obtain payload data from the second satellite B and the second satellite B
Whole star telemetry is simultaneously stored, while slave computer between slave computer or the second star between sending it to the first star；First star
Between between slave computer or the second star slave computer according to the correctness of the verification of payload data and whole star telemetry, be provided with
Imitate the validity of load data and whole star telemetry data packet mark；When slave computer between the first satellite of CAN poll A the first star
Or during the second slave computer between star (because two machines are that slave computer only one of which works between cold standby, two stars), and according to certain
Principle of selecting the best qualified, selection output payload data and the second satellite B whole star telemetry；(slave computer is sentenced first between the first star
Whether the payload data and whole star telemetry data packet mark that disconnected first receiver is sent are effective, and output first connects if effectively
The data that receipts machine is sent, the payload data and whole star telemetry data packet mark of the transmission of the second receiver are judged if invalid is
The no data that the transmission of the second receiver is effectively exported if effectively, still export the data of the first receiver transmission if invalid, the
Slave computer carries out data output according to same principle of selecting the best qualified between two stars)
Slave computer passes through the Star Service subsystem received between slave computer or the second star between first satellite A the first star
The remote operating instruction for the second satellite B that CAN is sent, sends to the first emitter or the second emitter, the first emitter
Or second emitter remote operating instruction is carried out after BPSK modulation, power amplification, filtering, pass through Microwave Net between star and star
Between communication antenna sent in radiofrequency signal form to the second satellite B.
Receiver completes to penetrate reception in 581ms between receiver and the second star between the first star of the first satellite A
After the demodulation of frequency signal, filtering, formatting, descrambling, synchronization, verification, and stored.
Communication equipment is again including receiver includes between emitter, star between receiver and star between star between the star of the second satellite B
Receiver works simultaneously between receiver and the second star between receiver between receiver and the second star, the first star between first star, hot each other
Backup；Emitter includes emitter between emitter and the second star between the first star between star, the two cold standby each other；
The radiofrequency signal that second satellite B the first receiver and the second receiver sends Microwave Net between star is in a timing
It is interior that radiofrequency signal is carried out to recover remote operating instruction after BPSK demodulation, filtering, formatting, synchronization, will by RS422 interfaces
Its associated user for sending B stars to performs corresponding remote operating task；
Second satellite B the first emitter or the second emitter receives payload from Star Service subsystem and whole
Star telemetry, and BPSK modulation, power amplification, filtering are carried out to it, by between star between Microwave Net and star communication antenna with
Radiofrequency signal form is sent to the first satellite A.
Antenna beamwidth is ± 60 ° between the first satellite A and the second satellite B star；
Communication antenna communication distance is in the range of 0.15m-15km between the first satellite A and the second satellite B star；
Antenna is separately mounted to the+X faces of satellite body coordinate system ,-X between the first satellite A and the second satellite B star
Face；
There is butt joint ring, B stars in the+X faces of satellite body coordinate system ,-X faces respectively in the first satellite A and the second satellite B
Butt joint ring height 88mm, A star butt joint ring height 103mm；
Communication antenna is higher by celestial body surface 156mm (lower pair of assembled states between the first satellite A and the second satellite B star
Star is in X-direction spacing 191mm, according to the test result of radiation patterns star, chooses the maximum antenna height of gain)；
The installation principle of communication antenna is as follows between the star：
(1) according to the test result of A stars and the radiation patterns star of B stars, communication antenna and star between the star of A stars and B stars are chosen
The maximum result of isolation difference between upper radio-frequency apparatus, and communication antenna is being defended between determining according to the result star of A stars and B stars
The X faces of star body coordinate system, the specific installation site in-X faces；
Radiation patterns star is defined：Radiation patterns star (RM) be in satellite development process with structure star (SM), electrical star (EM)
A kind of whole star state of the art arranged side by side with thermal control star (TM).It is examined on star between antenna system radiation and covering performance, antenna
One of coupled characteristic electrically tests star.Radiation patterns star is a kind of stage die that high frequency electromagnetic property is equivalent to real satellite
Type, the specifically electromagnetic property on the model outside dimension and surface and real satellite are fully equivalent in electromagnetic property.Radiation patterns
Satellite experiment is all to be installed on antenna on star on model star on request, and each antenna is tested respectively in spacecraft (satellite) mounting ring
Electrical property under border；
(2) according to the installation site of communication antenna between determination A, B star in step (1), and according to the day that communicated between A, B star
The test result of line receive-transmit isolation determines the setting angle and mode of antenna：
A, the relevant position being installed on communication antenna between the star of A, B satellite in the radiation patterns star determined in step (1)；
B, the working frequency f1 for choosing Inter-satellite Communication System, antenna is motionless between keeping B stars, leads between the first satellite A star
Believe that the reference direction (specific setting according to demand) of antenna base points to the +Z direction of satellite, tested using vector network analyzer
The isolation of A, B satellite antenna is recorded respectively；
Antenna is motionless between c, holding B stars, and the reference direction of communication antenna base points to satellite between the first satellite A star
+Y direction, the test result of A, B satellite antenna isolation is recorded using vector network analyzer respectively；
D, keep B stars between antenna it is motionless so that between the star of A stars communication antenna base reference direction point to satellite-
Z, -Y direction, the test result of A, B satellite antenna isolation is recorded using vector network analyzer respectively；
Antenna is remained stationary as between e, A star, and the reference direction of communication antenna base points to satellite between the second satellite B star
+ Z ,+Y ,-Z, -Y direction, communication antenna isolation degree test result between A, B star is recorded using vector network analyzer respectively；
F, the working frequency f2, repeat step b, c, d, e for choosing Inter-satellite Communication System, record communication between A, B Satellite
The reference direction of antenna base points to isolation between antennas test result when the+Z of satellite ,+Y ,-Z, -Y direction；
G, according to above test result, surveyed during sensing that working frequency f1 is identical with A, B satellite antenna reference direction under f2
Communication antenna isolation carries out asking poor between A, B Satellite measured, the corresponding position of one group of isolation for asking poor absolute value minimum
It is set to the setting angle of communication antenna and direction between A, B Satellite.
The first satellite A and the second satellite B is between 0.15~200m, and emitter works in small-power (one between star
As take -20dBm) state；The first satellite A and the second satellite B is between 10m~15km, and emitter is worked in greatly between star
Power rating (typically takes 10dBm)；The first satellite A and the second satellite B is at a distance of in the range of 10~200m, emitter between star
High-power, low power state switching can be carried out.
The data bit rate that emitter sends radiofrequency signal between the star of the first satellite A is 2000bps.
The payload data and whole star telemetry length of emitter transmission are respectively between the star of the second satellite B
256 bytes, information bit rate is 4096bps.
The present invention has the following advantages that compared with prior art：
(1) present invention can set up lasting, two-way high dynamic inter-satellite link, disclosure satisfy that Space teleoperation task to logical
Believe the requirement of low time delay；The mounting means of communication antenna between star is determined by using the test result of isolation between antennas simultaneously, it is real
Low time delay, the high dynamic Inter-satellite Communication System of Space teleoperation task are now adapted to, is that domestic and international moonlet field is the first, applicability
Greatly enhance.
(2) the present invention relates to a kind of high dynamic Inter-satellite Communication System for adapting to Space teleoperation task, the distant behaviour in space is met
Make demand of the task to low time delay, lasting, two-way high dynamic Inter-satellite Communication System.
(3) near field electromagnetic environment is star when the antenna mounting means that the present invention is used overcomes two combinations of satellites states
The influence of communication environment, celestial body surface is installed on by communication antenna between the star of two satellites, two antennas is rotated, to it at 360 °
In the range of isolation tested, choose one group of two star between communication antenna the immediate mode of isolation degree test result it is true
Its fixed setting angle, meets the high dynamic demand of link between satellite.
(4) instant invention overcomes the electromagnetic compatibility problem of two a variety of high-frequency apparatus of satellite, to pressing down outside frequency, receiver band
System carries out simulation analysis calculating, solves the problems, such as the influence of complex electromagnetic environment.
(5) communication control processor possesses and receives function between 74dB high dynamic capture range, star between A, B star in the present invention
Enough detections and correctly demodulation -42dBm most strong radiofrequency signal, can also be detected and correct demodulation -116dBm most weak radiofrequency signal,
Experiment proves that, its demodulation bit error rate is 0 in 74dB dynamic range.
Brief description of the drawings
Fig. 1 is present system structure chart.
Embodiment
Just the present invention is described further with reference to accompanying drawing below.
As shown in figure 1, a kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation of the present invention, bag
Include the first satellite A, the second satellite B；Wherein the first satellite A and the second satellite B are respectively again including microwave network between communication equipment, star between star
Communication antenna between network, star；
Communication antenna passes through microwave network between star by the radiofrequency signal from the second satellite B is received between first satellite A star
Network, sends and recovers payload data after carrying out BPSK demodulation, filtering, formatting, descrambling, synchronization check to communication equipment between star
With the second satellite B whole star telemetry (wherein, filter, format, descrambling is referred to as digital processing), communication equipment passes through between star
Payload data is respectively transmitted and used to related user by CAN to the second satellite B whole star telemetry；While the
Communication equipment receives the remote operating instruction for the second satellite B that Star Service subsystem is sent by CAN between one satellite A star, and right
Remote operating instruction is carried out after BPSK modulation, power amplification, filtering, by between star between Microwave Net and star communication antenna with radio frequency
Signal form is sent to the second satellite B；
Communication antenna receives the radiofrequency signal from A stars between second satellite B star, is penetrated this by Microwave Net between star
Frequency signal delivers to communication equipment between the second satellite B star；Between star communication equipment radiofrequency signal is carried out within a certain period of time BPSK demodulation,
Remote operating instruction is recovered after filtering, formatting, synchronization, the associated user for being transferred to B stars by RS422 interfaces performs phase
The remote operating task answered；Communication equipment receives the payload from Star Service subsystem and whole star remote measurement between second satellite B star
Data, and BPSK modulation, power amplification, filtering are carried out to it, by the way that communication antenna is believed with radio frequency between Microwave Net and star between star
Number form is sent to the first satellite A.
First satellite A
Communication equipment includes Receiver And Transmitter between slave computer, star between star again between first satellite A star；It is the next between its culminant star
Machine includes slave computer between slave computer and the second star between the first star, the two cold standby each other；Receiver is indirect including the first star between star
Receiver between receipts machine and the second star, both work simultaneously, each other Hot Spare；Emitter includes emitter and the between the first star between star
Emitter between two stars, the two cold standby each other；
Receiver is solved to the radiofrequency signal of reception simultaneously between receiver and the second star between first satellite A the first star
Adjust, filtering, format, descrambling, synchronization and after verifying, obtain payload data from the second satellite B and the second satellite B
Whole star telemetry is simultaneously stored, while slave computer between slave computer or the second star between sending it to the first star；First star
Between between slave computer or the second star slave computer according to the correctness of the verification of payload data and whole star telemetry, be provided with
Imitate the validity of load data and whole star telemetry data packet mark；When slave computer between the first satellite of CAN poll A the first star
Or during the second slave computer between star (because two machines are that slave computer only one of which works between cold standby, two stars), and according to certain
Principle of selecting the best qualified, selection output payload data and the second satellite B whole star telemetry；Slave computer is first determined whether between first star
Whether the payload data and whole star telemetry data packet mark that the first receiver is sent are effective, and output first is received if effectively
Machine send data, judge if invalid second receiver send payload data and whole star telemetry data packet mark whether
Effectively, the data of the second receiver transmission are exported if effectively, the data of the first receiver transmission, second are still exported if invalid
Slave computer carries out data output according to same principle of selecting the best qualified between star.
Slave computer passes through the Star Service subsystem received between slave computer or the second star between first satellite A the first star
The remote operating instruction for the second satellite B that CAN is sent, sends to the first emitter or the second emitter, the first emitter
Or second emitter remote operating instruction is carried out after BPSK modulation, power amplification, filtering, pass through Microwave Net between star and star
Between communication antenna sent in radiofrequency signal form to the second satellite B.
Receiver completes the radio frequency letter to reception in 581ms between receiver and the second star between first satellite A the first star
Number demodulation, filtering, formatting, descrambling, synchronization, after verification, and stored.
Antenna beamwidth is ± 60 ° between first satellite A star.
The data bit rate that emitter sends radiofrequency signal between first satellite A star is 2000bps.
Second satellite B
Communication equipment is again including receiver includes first between emitter, star between receiver and star between star between second satellite B star
Receiver works simultaneously between receiver and the second star between receiver between receiver and the second star, the first star between star, each other Hot Spare；
Emitter includes emitter between emitter and the second star between the first star between star, the two cold standby each other；
The radiofrequency signal that second satellite B the first receiver and the second receiver sends Microwave Net between star is in a timing
It is interior that radiofrequency signal is carried out to recover remote operating instruction after BPSK demodulation, filtering, formatting, synchronization, will by RS422 interfaces
Its associated user for sending B stars to performs corresponding remote operating task；
Second satellite B the first emitter or the second emitter receives payload from Star Service subsystem and whole
Star telemetry, and BPSK modulation, power amplification, filtering are carried out to it, by between star between Microwave Net and star communication antenna with
Radiofrequency signal form is sent to the first satellite A.
Antenna beamwidth is ± 60 ° between second satellite B star.
The payload data and whole star telemetry length that emitter is sent between second satellite B star are respectively 256 words
Section, information bit rate is 4096bps.
First satellite A and the second satellite B installation principle：
Communication antenna communication distance is in the range of 0.15m-15km between first satellite A and the second satellite B star；
Communication antenna is higher by celestial body surface 156mm (double star is in X under assembled state between first satellite A and the second satellite B star
Direction spacing 191mm, according to the test result of radiation patterns star, chooses the maximum antenna height of gain)；
Antenna is separately mounted to the+X faces of satellite body coordinate system ,-X faces between first satellite A and the second satellite B star；
There is butt joint ring, B stars pair in the+X faces of satellite body coordinate system ,-X faces respectively in the first satellite A and the second satellite B
Meet ring height 88mm, A star butt joint ring height 103mm.
The installation principle of communication antenna is as follows between star：
(1) according to the test result of A stars and the radiation patterns star of B stars, communication antenna and star between the star of A stars and B stars are chosen
The maximum result of isolation difference between upper radio-frequency apparatus, and communication antenna is being defended between determining according to the result star of A stars and B stars
The X faces of star body coordinate system, the specific installation site in-X faces；(radio-frequency apparatus refers to observing and controlling, number biography, load etc. on star).
Radiation patterns star is defined：Radiation patterns star (RM) be in satellite development process with structure star (SM), electrical star (EM)
A kind of whole star state of the art arranged side by side with thermal control star (TM).It is examined on star between antenna system radiation and covering performance, antenna
One of coupled characteristic electrically tests star.Radiation patterns star is a kind of stage die that high frequency electromagnetic property is equivalent to real satellite
Type, the specifically electromagnetic property on the model outside dimension and surface and real satellite are fully equivalent in electromagnetic property.Radiation patterns
Satellite experiment is all to be installed on antenna on star on model star on request, and each antenna is tested respectively in spacecraft (satellite) mounting ring
Electrical property under border.
(2) according to the installation site obtained in step (1), and according to the survey of communication antenna receive-transmit isolation between A, B star
Test result determines the setting angle and mode of antenna：
A, communication antenna between the star of A, B satellite is installed on the relevant position in radiation patterns star；
B, the working frequency f1 for choosing Inter-satellite Communication System, antenna is motionless between keeping B stars, leads between the first satellite A star
Believe that the reference direction (specific setting according to demand) of antenna base points to the +Z direction of satellite, tested using vector network analyzer
The isolation of A, B satellite antenna is recorded respectively；
Antenna is motionless between c, holding B stars, and the reference direction of communication antenna base points to satellite between the first satellite A star
+Y direction, the test result of A, B satellite antenna isolation is recorded using vector network analyzer respectively；
D, keep B stars between antenna it is motionless so that between the star of A stars communication antenna base reference direction point to satellite-
Z, -Y direction, the test result of A, B satellite antenna isolation is recorded using vector network analyzer respectively；
Antenna is remained stationary as between e, A star, and the reference direction of communication antenna base points to satellite between the second satellite B star
+ Z ,+Y ,-Z, -Y direction, communication antenna isolation degree test result between A, B star is recorded using vector network analyzer respectively；
F, the working frequency f2, repeat step b, c, d, e for choosing Inter-satellite Communication System, record communication between A, B Satellite
The reference direction of antenna base points to isolation between antennas test result when the+Z of satellite ,+Y ,-Z, -Y direction；
G, according to above test result, surveyed during sensing that working frequency f1 is identical with A, B satellite antenna reference direction under f2
Communication antenna isolation carries out asking poor between A, B Satellite measured, the corresponding position of one group of isolation for asking poor absolute value minimum
It is set to the setting angle of communication antenna and direction between A, B Satellite.
First satellite A and the second satellite B between 0.15~200m, between star emitter work in small-power (typically take-
20dBm) state；The first satellite A and the second satellite B is between 10m~15km, and emitter works in high-power shape between star
State (typically takes 10dBm)；The first satellite A and the second satellite B is at a distance of in the range of 10~200m, and emitter can be carried out between star
High-power, low power state switching.
After present invention design is finished, whether electromagnetic interference and electric wire isolation are whether there is working frequency f1, f2 at
Meet and require, it is necessary to be verified.
The verification mode whether Inter-satellite Communication System working frequency f1, f2 selection meet index request is as follows：
(1) electromagnetic interference of the radio-frequency apparatus of satellite is analyzed using simulation software CADFEKO, specific emulation is such as
Under：
(1a) leads to according between the suggestion of CCSDS (international space data system consultative committee) near space agreement selection star
The working frequency f1, f2, f1 and f2 of letter system are in S-band；
(1b) carries out analysis of electromagnetic interference to f1, the working frequency of f2 frequencies and spread spectrum answering machine so that communication point between star
The f1 of system, f2 and the frequency of spread spectrum answering machine do not produce out-of-band interference；
(1c) is sent out it according to communication antenna between star and Spread Spectrum TT＆C antenna arrangement model using CADFEKO softwares
Isolation (isolation receives and dispatches the effect of gain and spatial comprising the antenna) simulation calculation point penetrated between source and reception source
Analysis, isolates according to receiver Out-of-band rejection and space, calculates interfering signal power；
The sensitivity of communication equipment should be greater than spreading the power level of answering machine interference signal between (1d) star；Communicated between clock star
The interfering signal power intensity of machine should be less than spreading the receiving sensitivity of answering machine, then it is assumed that communication subsystem should with spread spectrum between star
Answer to produce between machine and interfere.
(2) checking of Inter-satellite Communication System is carried out using radiation patterns star：
(2a) setup test environment：The darkroom of half opening is selected to carry out isolation between antennas test job, using Agilent
8363B vector network analyzers；
The antenna pattern of communication antenna is tested between (2b) first satellite A star, and communication subsystem exists between record star
The receive-transmit isolation of f1, f2 two frequency bins；
The antenna pattern of communication antenna is tested between (2c) second satellite B star, and communication subsystem exists between record star
The receive-transmit isolation of f1, f2 two frequency bins；
First satellite A and the second satellite B distance are set to 0.15m by (2d), and communication subsystem is in f1, f2 between recording star
The receive-transmit isolation of two frequency bins；
First satellite A and the second satellite B distance are set to 20m by (2e), and communication subsystem is in f1, f2 two between recording star
The receive-transmit isolation of individual frequency；
(2f) if four kinds of states in step 2b, 2c, 2d, 2e are satisfied by index request, then Inter-satellite Communication System, which is met, wants
Ask.
Unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (4)
1. a kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation, it is characterised in that including：First
Satellite A, the second satellite B；Wherein the first satellite A and the second satellite B are respectively again including Microwave Net, star between communication equipment, star between star
Between communication antenna；
Between first satellite A star communication antenna will receive the radiofrequency signal from the second satellite B pass through Microwave Net between star, hair
Deliver to communication equipment between star and recovered after BPSK demodulation, filtering, formatting, descrambling, synchronization check payload data and the
Communication equipment is distant by the whole star of payload data and the second satellite B by CAN between two satellite B whole star telemetry, star
Survey data are respectively transmitted to be used to related user；Communication equipment reception Star Service subsystem passes through CAN between the first satellite A star simultaneously
The remote operating instruction for the second satellite B that bus is sent, and remote operating instruction is carried out after BPSK modulation, power amplification, filtering,
By the way that communication antenna is sent to the second satellite B in radiofrequency signal form between Microwave Net and star between star；
Communication antenna receives the radiofrequency signal from A stars between second satellite B star, is believed the radio frequency by Microwave Net between star
Number deliver to communication equipment between the second satellite B star；Communication equipment carries out BPSK demodulation, filtering, formatting, synchronization to radiofrequency signal between star
After recover remote operating instruction, the associated user for being transferred to B stars by RS422 interfaces performs corresponding remote operating task；
Communication equipment receives payload and whole star telemetry from Star Service subsystem between second satellite B star, and it is carried out
BPSK modulation, power amplification, filtering, by the way that communication antenna is sent to first in radiofrequency signal form between Microwave Net and star between star
Satellite A；
Communication equipment includes Receiver And Transmitter between slave computer, star between star again between the star of the first satellite A；It is the next between its culminant star
Machine includes slave computer between slave computer and the second star between the first star, the two cold standby each other；Receiver is indirect including the first star between star
Receiver between receipts machine and the second star, both work simultaneously, each other Hot Spare；Emitter includes emitter and the between the first star between star
Emitter between two stars, the two cold standby each other；
Receiver is demodulated to the radiofrequency signal of reception, filtered simultaneously between receiver and the second star between first satellite A the first star
After ripple, formatting, descrambling, synchronization and verification, the payload data from the second satellite B and the second satellite B whole star are obtained
Telemetry is simultaneously stored, while slave computer between slave computer or the second star between sending it to the first star；Under between first star
Slave computer sets and effectively carried according to the correctness of the verification of payload data and whole star telemetry between position machine or the second star
The validity of lotus data and whole star telemetry data packet mark；When slave computer between the first satellite of CAN poll A the first star or
Between two stars during slave computer, according to certain principle of selecting the best qualified, selection output two-way payload data and the second satellite B whole star are distant
Survey data；
Slave computer is total by CAN by the Star Service subsystem received between slave computer or the second star between first satellite A the first star
The remote operating instruction for the second satellite B that line is sent, sends to the first emitter or the second emitter, the first emitter or the
Two emitters are carried out after BPSK modulation, power amplification, filtering to remote operating instruction, by being communicated between star between Microwave Net and star
Antenna is sent to the second satellite B in radiofrequency signal form；
Receiver is completed in 581ms to the radiofrequency signal of reception between receiver and the second star between first satellite A the first star
After demodulation, filtering, formatting, descrambling, synchronization, verification, and stored；
Communication equipment is again including receiver includes first between emitter, star between receiver and star between star between the star of the second satellite B
Receiver works simultaneously between receiver and the second star between receiver between receiver and the second star, the first star between star, each other Hot Spare；
Emitter includes emitter between emitter and the second star between the first star between star, the two cold standby each other；
The radiofrequency signal that second satellite B the first receiver and the second receiver sends Microwave Net between star is within a certain period of time
Radiofrequency signal is carried out to recover remote operating instruction after BPSK demodulation, filtering, formatting, synchronization, passed by RS422 interfaces
The associated user for giving B stars performs corresponding remote operating task；
It is distant that second satellite B the first emitter or the second emitter receives payload and whole star from Star Service subsystem
Survey data, and BPSK modulation, power amplification, filtering carried out to it, by between star between Microwave Net and star communication antenna with radio frequency
Signal form is sent to the first satellite A；
Antenna beamwidth is ± 60 ° between the first satellite A and the second satellite B star；
Communication antenna communication distance is in the range of 0.15m~15km between the first satellite A and the second satellite B star；
Communication antenna is higher by celestial body surface 156mm between the first satellite A and the second satellite B star；
Antenna is separately mounted to the+X faces of satellite body coordinate system ,-X faces between the first satellite A and the second satellite B star；
There is butt joint ring, B stars pair in the+X faces of satellite body coordinate system ,-X faces respectively in the first satellite A and the second satellite B
Meet ring height 88mm, A star butt joint ring height 103mm；
The installation principle of communication antenna is as follows between star：
(1) according to the test result of A stars and the radiation patterns star of B stars, communication antenna on star with penetrating between choosing the star of A stars and B stars
The maximum result of the isolation difference of frequency equipment room, and between determining according to the result star of A stars and B stars communication antenna in satellite sheet
The X faces of body coordinate system, the specific installation site in-X faces；
(2) according to the installation site of communication antenna between determination A, B star in step (1), and received according to communication antenna between A, B star
The test result of hair isolation determines the setting angle and mode of antenna：
A, the relevant position being installed on communication antenna between the star of A, B satellite in the radiation patterns star determined in step (1)；
B, the working frequency f1 for choosing Inter-satellite Communication System, antenna is motionless between keeping B stars, and communicate day between the first satellite A star
The reference direction of line base points to the +Z direction of satellite, is tested using vector network analyzer and records A, B satellite antenna respectively
Isolation；
Antenna is motionless between c, holding B stars, and the reference direction of communication antenna base points to the+Y sides of satellite between the first satellite A star
To recording the test result of A, B satellite antenna isolation respectively using vector network analyzer；
Antenna is motionless between d, holding B stars so that the reference direction of communication antenna base points to-the Z ,-Y of satellite between the star of A stars
Direction, the test result of A, B satellite antenna isolation is recorded using vector network analyzer respectively；
Antenna is remained stationary as between e, A star, between the second satellite B star communication antenna base reference direction point to satellite+Z ,+
Y ,-Z, -Y direction, communication antenna isolation degree test result between A, B star is recorded using vector network analyzer respectively；
F, the working frequency f2, repeat step b, c, d, e for choosing Inter-satellite Communication System, record communication antenna between A, B Satellite
The reference direction of base points to isolation between antennas test result when the+Z of satellite ,+Y ,-Z, -Y direction；
G, according to above test result, measured during sensing that working frequency f1 is identical with A, B satellite antenna reference direction under f2
To A, B Satellite between communication antenna isolation carry out asking poor, the corresponding position of one group of isolation for seeking poor absolute value minimum is
The setting angle of communication antenna and direction between A, B Satellite.
2. a kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation according to claim 1,
It is characterized in that：The first satellite A and the second satellite B is between 0.15~200m, and emitter works in small-power between star
State；The first satellite A and the second satellite B is between 10m~15km, and emitter works in high-power state between star；Institute
The first satellite A and the second satellite B is stated at a distance of in the range of 10~200m, emitter can carry out high-power, low power shape between star
State switches.
3. a kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation according to claim 1,
It is characterized in that：The data bit rate that emitter sends radiofrequency signal between the star of the first satellite A is 2000bps.
4. a kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation according to claim 1,
It is characterized in that：Emitter is sent between the star of the second satellite B payload data and whole star telemetry length difference
For 256 bytes, information bit rate is 4096bps.
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| CN105262533B (en) * | 2015-10-30 | 2018-08-31 | 中国空间技术研究院 | Forward to a kind of GEO satellite IP-based star the integral system of the networking between star |
| CN107528628B (en) * | 2017-09-28 | 2020-01-10 | 中国电子科技集团公司第七研究所 | Signal synchronization method, device and system of satellite communication system |
| CN107846245B (en) * | 2017-11-20 | 2020-06-09 | 航天东方红卫星有限公司 | Design method of synchronous double-star GPS original measurement data |
| CN108833032B (en) * | 2018-06-20 | 2019-08-09 | 中国人民解放***箭军工程大学 | A kind of evaluation system for high dynamic receiver |
| CN110266362B (en) * | 2019-07-04 | 2020-08-18 | 北京邮电大学 | Millimeter wave based interference suppression method for constellation multi-beam reception |
| CN112751605B (en) * | 2020-12-29 | 2022-12-27 | 上海卫星工程研究所 | Method, system and medium for testing capturing and tracking characteristics of double-star dynamic inter-satellite link |
| CN112910782B (en) * | 2021-01-05 | 2022-11-22 | 西北工业大学 | Method for realizing minimum time delay of space teleoperation system based on relay communication |
| CN112737709B (en) * | 2021-01-08 | 2022-12-27 | 上海剑桥科技股份有限公司 | Test system and method based on transmission device, computer readable storage medium and electronic equipment |
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