CN104333408A - Inter-satellite communication system used for realizing high-dynamic and low-delay space teleoperation - Google Patents
Inter-satellite communication system used for realizing high-dynamic and low-delay space teleoperation Download PDFInfo
- Publication number
- CN104333408A CN104333408A CN201410505466.7A CN201410505466A CN104333408A CN 104333408 A CN104333408 A CN 104333408A CN 201410505466 A CN201410505466 A CN 201410505466A CN 104333408 A CN104333408 A CN 104333408A
- Authority
- CN
- China
- Prior art keywords
- star
- satellite
- antenna
- communication
- transmitter
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Radio Relay Systems (AREA)
Abstract
The invention provides an inter-satellite communication system used for realizing high-dynamic and low-delay space teleoperation. The system comprises a first satellite A and a second satellite B. The inter-satellite communication machine of the first satellite A performs digital processing on a received radio frequency signal and then payload data and entire satellite telemeasuring data are recovered and transmitted to users; the inter-satellite communication machine of the first satellite A performs digital processing on a received teleoperation instruction and then transmits the teleoperation instruction to the second satellite B in a radio frequency signal mode; the inter-satellite communication machine of the second satellite B performs digital processing on the radio frequency signal and then the teleoperation instruction is recovered and transmitted to the related users to perform corresponding teleoperation tasks; and the inter-satellite communication machine of the second satellite B performs digital processing on the received payload and the entire satellite telemeasuring data and then transmits the data to the first satellite A in the radio frequency signal mode. A continuous and bidirectional high-dynamic inter-satellite link is established so that the low-delay requirement of the space teleoperation tasks is met.
Description
Technical field
The present invention relates to a kind of Inter-satellite Communication System for realizing dynamically high and low time delay Space teleoperation, belonging to technical field of satellite communication.
Background technology
Need, by inter-satellite link collaborative work, to complete the transmission of mutual data between two satellites of Space teleoperation task, and coordinate Iarge-scale system to complete some particular task.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 answers meeting spatial remote operating task to the requirement of communication low time delay.In addition, two satellites of Space teleoperation task need assembled state be separated state far away under complete communication task between lasting two-way star, high requirement is proposed to the dynamic capability communicated between star, the signal level received should be made to reach demodulation threshold makes signal can not cause the saturation of receiver too by force again, therefore needs to design a kind of low time delay, the height dynamically Inter-satellite Communication System that adapt to Space teleoperation task.
Due to implementation space remote operating task two satellites between relative position be dynamic change, its design difficulty mainly contains: between (1) star, the transmitting power of communication equipment is designed to 10 ~ 15mW scope, receiving sensitivity is designed to-116dBm, in order to ensure that two stars are when at a distance of 15km state, between star, communication control processor can receive the signal level of enough demodulation; And ensure that two stars are when distance 0.15m, between star, communication control processor can not reach capacity state; (2) design that communication equipment between star receives, demodulation the time decompositing payload data is 581ms, with the communication low time delay requirement of meeting spatial remote operating task to Inter-satellite Communication System; (3) design communication antenna between star and be arranged on the opposite face of two satellites, and ensure to reach when two satellites move mutually ± the visible angle of 60 °, to ensure that between star, communication can provide lasting, two-way reliable and stable communication link, can not exist communication disruption region; (4) because of the impact of space environment, arrive the radiofrequency signal of two satellite receiver and inconsistent, therefore the isolation of communication antenna between star in different angles is tested, the test result determination astronomical cycle angle the most close according to its isolation, close as far as possible to ensure the incoming level of communication equipment between two Satellites.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, provide a kind of Inter-satellite Communication System for realizing dynamically high and low time delay Space teleoperation, the present invention can set up the dynamic inter-satellite link of lasting, two-way height, can meeting spatial remote operating task to communication low time delay requirement; By the mounting means of communication antenna between the test result determination star that adopts isolation between antennas, thus realize a kind ofly adapting to the low time delay of Space teleoperation task, high dynamically Inter-satellite Communication System.
Technical solution of the present invention is:
For realizing an Inter-satellite Communication System for dynamically high and low time delay Space teleoperation, comprising: the first satellite A, the second satellite B; Wherein the first satellite A and the second satellite B to comprise again between communication equipment between star, star communication antenna between microwave network, star respectively;
Between the star of the first satellite A communication antenna by the radiofrequency signal that receives from the second satellite B by microwave network between star, be sent to communication equipment between star and recover the whole star telemetry of payload data and the second satellite B after carrying out BPSK demodulation, filtering, format, descrambling, synchronization check (wherein, filtering, format, descrambling are referred to as digital processing), between star, communication equipment sends the whole star telemetry of payload data and the second satellite B to relevant user's use respectively by CAN; Between the star of simultaneously the first satellite A, communication equipment receives the remote operating instruction of the second satellite B that Star Service subsystem is sent here by CAN, and after BPSK modulation, power amplification, filtering are carried out to this remote operating instruction, by between star between microwave network and star communication antenna be sent to the second satellite B with radiofrequency signal form;
Between the star of the second satellite B, communication antenna receives the radiofrequency signal from A star, communication equipment between the star by microwave network between star this radiofrequency signal being delivered to the second satellite B; Between star communication equipment within a certain period of time radio frequency signal carry out BPSK demodulation, filtering, format, synchronous after recover remote operating instruction, the associated user being sent to B star by RS422 interface performs corresponding remote operating task; Between the star of the second satellite B, communication equipment 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 network and star communication antenna be sent to the first satellite A with radiofrequency signal form.
Between the star of described first satellite A, communication equipment comprises again Receiver And Transmitter between slave computer between star, star; Between its culminant star, slave computer to comprise between the first star slave computer between slave computer and the second star, and the two is cold standby each other; Between star, receiver to comprise between the first star receiver between receiver and the second star, and both work simultaneously, each other Hot Spare; Between star, transmitter to comprise between the first star transmitter between transmitter and the second star, and the two is cold standby each other;
After between first star of the first satellite A, between receiver and the second star, receiver carries out demodulation, filtering, format, descrambling, synchronous also verification to the radiofrequency signal received simultaneously, obtain from the payload data of the second satellite B and the whole star telemetry of the second satellite B and store, sending it between the first star slave computer between slave computer or the second star simultaneously; Between the first star, between slave computer or the second star, slave computer, according to the correctness of the verification of payload data and whole star telemetry, arranges the validity of payload data and whole star telemetry data packet mark; When between first star of CAN poll first satellite A between slave computer or the second star during slave computer (because two machines are cold standbies, between two stars, slave computer only has a job), and according to certain principle of selecting the best qualified, select the whole star telemetry exporting payload data and the second satellite B; (between the first star slave computer first judge first receiver send payload data and whole star telemetry data packet mark whether effective, if effectively, export the data that the first receiver sends, if invalid, judge second receiver send payload data and whole star telemetry data packet mark whether effective, if effectively, export the data that the second receiver sends, if invalid, still export the data that the first receiver sends, between the second star, slave computer carries out data output according to same principle of selecting the best qualified)
The remote operating instruction of the second satellite B that the Star Service subsystem received is sent here by CAN by slave computer between slave computer or the second star between first star of the first satellite A, be sent to the first transmitter or the second transmitter, after first transmitter or the second transmitter carry out BPSK modulation, power amplification, filtering to this remote operating instruction, by between star between microwave network and star communication antenna be sent to the second satellite B with radiofrequency signal form.
Between first star of described first satellite A, between receiver and the second star, receiver completes after the demodulation of radiofrequency signal received, filtering, format, descrambling, synchronous, verification in 581ms, and stores.
Between the star of described second satellite B, communication equipment to comprise again between star transmitter between receiver and star, and between star, receiver to comprise between the first star receiver between receiver and the second star, and between the first star, between receiver and the second star, receiver works simultaneously, each other Hot Spare; Between star, transmitter to comprise between the first star transmitter between transmitter and the second star, and the two is cold standby each other;
The radiofrequency signal that microwave network between star sends by first receiver of the second satellite B and the second receiver within a certain period of time radio frequency signal carry out BPSK demodulation, filtering, format, synchronous after recover remote operating instruction, the associated user being sent to B star by RS422 interface performs corresponding remote operating task;
First transmitter of the second satellite B or the second transmitter receive 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 network and star communication antenna be sent to the first satellite A with radiofrequency signal form.
Between the star of described first satellite A and the second satellite B, antenna beamwidth is ± 60 °;
Between the star of described first satellite A and the second satellite B, communication antenna communication distance is within the scope of 0.15 ~ 15km;
Between the star of described first satellite A and the second satellite B, antenna is arranged on+X the face ,-X face of satellite body coordinate system respectively;
There is butt joint ring in the+X face of satellite body coordinate system ,-X face in described first satellite A and the second satellite B, B star butt joint ring height 88mm respectively, A star butt joint ring height 103mm;
Between the star of described first satellite A and the second satellite B, communication antenna exceeds celestial body surface 156mm (under assembled state, double star is at X-direction spacing 191mm, according to the test result of radiation patterns star, chooses the antenna height that gain is maximum);
Between described star, the installation principle of communication antenna is as follows:
(1) according to the test result of the radiation patterns star of A star and B star, isolation between the star choosing A star and B star between communication antenna with radio-frequency apparatus on star differs maximum result, and between the star determining A star and B star according to this result communication antenna in the installation site in satellite+X face ,-X face; (on star, radio-frequency apparatus refers to observing and controlling, number biography, load etc.)
Radiation patterns star defines: radiation patterns star (RM) is the whole star state of the art of one arranged side by side with structure star (SM), electrical star (EM) and thermal control star (TM) in satellite development process.It is on examination star between antenna system radiation and covering performance, antenna one of coupled characteristic electrically test star.Radiation patterns star is a kind of engineering model that high frequency electromagnetic property is equivalent to real satellite, this model outside dimension equivalence completely in electromagnetic property with surperficial electromagnetic property and real satellite specifically.Radiation patterns satellite experiment is all installed on request on model star by antenna on star, tests the electrical property of each antenna under spacecraft (satellite) installation environment respectively;
(2) according to the installation site determining communication antenna between A, B star in step (1), and according to the setting angle of the test result determination antenna of communication antenna receive-transmit isolation between A, B star and mode:
A, relevant position communication antenna between the star of A, B satellite is installed in the radiation patterns star determined in step (1);
B, choose the operating frequency f1 of Inter-satellite Communication System, keep antenna between B star motionless, between the star of the first satellite A the reference direction (according to demand specifically set) of communication antenna base point to satellite+Z-direction, utilize vector network analyzer to test the isolation recording A, B satellite antenna respectively;
C, keep antenna between B star motionless, between the star of the first satellite A the reference direction of communication antenna base point to satellite+Y-direction, utilize vector network analyzer to record the test result of A, B satellite antenna isolation respectively;
Between d, maintenance B star, antenna is motionless, makes the reference direction of communication antenna base between the star of A star point to-the Z ,-Y-direction of satellite, utilizes vector network analyzer to record the test result of A, B satellite antenna isolation respectively;
Between e, A star, antenna keeps motionless, and between the star of the second satellite B, the reference direction of communication antenna base points to+the Z ,+Y of satellite ,-Z ,-Y-direction, utilizes vector network analyzer to record communication antenna isolation degree test result between A, B star respectively;
F, choose the operating frequency f2 of Inter-satellite Communication System, repeat step b, c, d, e, the reference direction recording communication antenna base between A, B Satellite points to isolation between antennas test result when+the Z ,+Y of satellite ,-Z ,-Y-direction;
G, according to above test result, between A, B Satellite obtain measurement during identical with A, B satellite antenna reference direction under f2 for operating frequency f1 sensing, communication antenna isolation carries out asking poor, and the position that the one group of isolation asking poor absolute value minimum is corresponding is setting angle and the direction of communication antenna between A, B Satellite.
Described first satellite A and the second satellite B is between 0.15 ~ 200m, and between star, transmitter works in small-power (generally getting-20dBm) state; Described first satellite A and the second satellite B is between 10m ~ 15km, and between star, transmitter works in high-power state (generally getting 10dBm); Described first satellite A and the second satellite B is at a distance of within the scope of 10 ~ 200m, and between star, transmitter can carry out the switching of high-power, low power state.
Between the star of described first satellite A, transmitter sends the numeric data code speed of radiofrequency signal is 2000bps.
The payload data that between the star of described second satellite B, transmitter sends and whole star telemetry length are respectively 256 bytes, and information code speed is 4096bps.
The present invention compared with prior art tool has the following advantages:
(1) the present invention can set up the dynamic inter-satellite link of lasting, two-way height, can meeting spatial remote operating task to communication low time delay requirement; Simultaneously by the mounting means of communication antenna between the test result determination star that adopts isolation between antennas, realize adapting to the low time delay of Space teleoperation task, high dynamically Inter-satellite Communication System, be that domestic and international moonlet field is the first, applicability strengthens greatly.
(2) the present invention relates to a kind of dynamic Inter-satellite Communication System of height adapting to Space teleoperation task, meeting spatial remote operating task is to the demand of low time delay, lasting, the two-way dynamic Inter-satellite Communication System of height.
(3) when the astronomical cycle mode that the present invention adopts overcomes two combinations of satellites states, near field electromagnetic environment is on the impact of communication environment between star, communication antenna between the star of two satellites is installed on celestial body surface, rotate two antennas, its isolation within the scope of 360 ° is tested, the immediate mode of isolation degree test result choosing communication antenna between one group of two star determines its setting angle, meets the high dynamic need of link between satellite.
(4) instant invention overcomes the electromagnetic compatibility problem of two multiple high-frequency apparatus of satellite, carry out simulation analysis calculating to frequency, receiver Out-of-band rejection, what solve complex electromagnetic environment affects problem.
(5) between A, B star in the present invention, communication control processor possesses the high Dynamical capture scope of 74dB, the machine that receives between star can detect and the strongest radiofrequency signal of correct demodulation-42dBm, also can detect and the most weak radiofrequency signal of correct demodulation-116dBm, through verification experimental verification, in the dynamic range of 74dB, its demodulation bit error rate is 0.
Accompanying drawing explanation
Fig. 1 is present system structure chart.
Embodiment
Just by reference to the accompanying drawings the present invention is described further below.
As shown in Figure 1, a kind of Inter-satellite Communication System for realizing dynamically high and low time delay Space teleoperation of the present invention, comprises the first satellite A, the second satellite B; Wherein the first satellite A and the second satellite B to comprise again between communication equipment between star, star communication antenna between microwave network, star respectively;
Between the star of the first satellite A communication antenna by the radiofrequency signal that receives from the second satellite B by microwave network between star, be sent to communication equipment between star and recover the whole star telemetry of payload data and the second satellite B after carrying out BPSK demodulation, filtering, format, descrambling, synchronization check (wherein, filtering, format, descrambling are referred to as digital processing), between star, communication equipment sends the whole star telemetry of payload data and the second satellite B to relevant user's use respectively by CAN; Between the star of simultaneously the first satellite A, communication equipment receives the remote operating instruction of the second satellite B that Star Service subsystem is sent here by CAN, and after BPSK modulation, power amplification, filtering are carried out to this remote operating instruction, by between star between microwave network and star communication antenna be sent to the second satellite B with radiofrequency signal form;
Between the star of the second satellite B, communication antenna receives the radiofrequency signal from A star, communication equipment between the star by microwave network between star this radiofrequency signal being delivered to the second satellite B; Between star communication equipment within a certain period of time radio frequency signal carry out BPSK demodulation, filtering, format, synchronous after recover remote operating instruction, the associated user being sent to B star by RS422 interface performs corresponding remote operating task; Between the star of the second satellite B, communication equipment 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 network and star communication antenna be sent to the first satellite A with radiofrequency signal form.
First satellite A
Between the star of the first satellite A, communication equipment comprises again Receiver And Transmitter between slave computer between star, star; Between its culminant star, slave computer to comprise between the first star slave computer between slave computer and the second star, and the two is cold standby each other; Between star, receiver to comprise between the first star receiver between receiver and the second star, and both work simultaneously, each other Hot Spare; Between star, transmitter to comprise between the first star transmitter between transmitter and the second star, and the two is cold standby each other;
After between first star of the first satellite A, between receiver and the second star, receiver carries out demodulation, filtering, format, descrambling, synchronous also verification to the radiofrequency signal received simultaneously, obtain from the payload data of the second satellite B and the whole star telemetry of the second satellite B and store, sending it between the first star slave computer between slave computer or the second star simultaneously; Between the first star, between slave computer or the second star, slave computer, according to the correctness of the verification of payload data and whole star telemetry, arranges the validity of payload data and whole star telemetry data packet mark; When between first star of CAN poll first satellite A between slave computer or the second star during slave computer (because two machines are cold standbies, between two stars, slave computer only has a job), and according to certain principle of selecting the best qualified, select the whole star telemetry exporting payload data and the second satellite B; Between the first star slave computer first judge first receiver send payload data and whole star telemetry data packet mark whether effective, if effectively, export the data that the first receiver sends, if invalid, judge second receiver send payload data and whole star telemetry data packet mark whether effective, if effectively, export the data that the second receiver sends, if invalid, still export the data that the first receiver sends, between the second star, slave computer carries out data output according to same principle of selecting the best qualified.
The remote operating instruction of the second satellite B that the Star Service subsystem received is sent here by CAN by slave computer between slave computer or the second star between first star of the first satellite A, be sent to the first transmitter or the second transmitter, after first transmitter or the second transmitter carry out BPSK modulation, power amplification, filtering to this remote operating instruction, by between star between microwave network and star communication antenna be sent to the second satellite B with radiofrequency signal form.
Between first star of the first satellite A, between receiver and the second star, receiver completes after the demodulation of radiofrequency signal received, filtering, format, descrambling, synchronous, verification in 581ms, and stores.
Between the star of the first satellite A, antenna beamwidth is ± 60 °.
Between the star of the first satellite A, transmitter sends the numeric data code speed of radiofrequency signal is 2000bps.
Second satellite B
Between the star of the second satellite B, communication equipment to comprise again between star transmitter between receiver and star, and between star, receiver to comprise between the first star receiver between receiver and the second star, and between the first star, between receiver and the second star, receiver works simultaneously, each other Hot Spare; Between star, transmitter to comprise between the first star transmitter between transmitter and the second star, and the two is cold standby each other;
The radiofrequency signal that microwave network between star sends by first receiver of the second satellite B and the second receiver within a certain period of time radio frequency signal carry out BPSK demodulation, filtering, format, synchronous after recover remote operating instruction, the associated user being sent to B star by RS422 interface performs corresponding remote operating task;
First transmitter of the second satellite B or the second transmitter receive 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 network and star communication antenna be sent to the first satellite A with radiofrequency signal form.
Between the star of the second satellite B, antenna beamwidth is ± 60 °.
The payload data that between the star of the second satellite B, transmitter sends and whole star telemetry length are respectively 256 bytes, and information code speed is 4096bps.
Between the star of the first satellite A and the second satellite B, antenna meets the following conditions:
Between the star of the first satellite A and the second satellite B, communication antenna communication distance is within the scope of 0.15 ~ 15km;
Between the star of the first satellite A and the second satellite B, communication antenna exceeds celestial body surface 156mm (under assembled state, double star is at X-direction spacing 191mm, according to the test result of radiation patterns star, chooses the antenna height that gain is maximum);
Between the star of the first satellite A and the second satellite B, antenna is arranged on+X the face ,-X face of satellite body coordinate system respectively;
There is butt joint ring in the+X face of satellite body coordinate system ,-X face in the first satellite A and the second satellite B, B star butt joint ring height 88mm respectively, A star butt joint ring height 103mm.
Between star, the installation principle of communication antenna is as follows:
(1) according to the test result of the radiation patterns star of A star and B star, isolation between the star choosing A star and B star between communication antenna with radio-frequency apparatus on star differs maximum result, and the X face of communication antenna at satellite body coordinate system, the concrete installation site in-X face between the star determining A star and B star according to this result; (on star, radio-frequency apparatus refers to observing and controlling, number biography, load etc.)
Radiation patterns star defines: radiation patterns star (RM) is the whole star state of the art of one arranged side by side with structure star (SM), electrical star (EM) and thermal control star (TM) in satellite development process.It is on examination star between antenna system radiation and covering performance, antenna one of coupled characteristic electrically test star.Radiation patterns star is a kind of engineering model that high frequency electromagnetic property is equivalent to real satellite, this model outside dimension equivalence completely in electromagnetic property with surperficial electromagnetic property and real satellite specifically.Radiation patterns satellite experiment is all installed on request on model star by antenna on star, tests the electrical property of each antenna under spacecraft (satellite) installation environment respectively.
(2) according to the installation site obtained in step (1), and according to the setting angle of the test result determination antenna of communication antenna receive-transmit isolation between A, B star and mode:
A, communication antenna between the star of A, B satellite is installed on the relevant position in radiation patterns star;
B, choose the operating frequency f1 of Inter-satellite Communication System, keep antenna between B star motionless, between the star of the first satellite A the reference direction (according to demand specifically set) of communication antenna base point to satellite+Z-direction, utilize vector network analyzer to test the isolation recording A, B satellite antenna respectively;
C, keep antenna between B star motionless, between the star of the first satellite A the reference direction of communication antenna base point to satellite+Y-direction, utilize vector network analyzer to record the test result of A, B satellite antenna isolation respectively;
Between d, maintenance B star, antenna is motionless, makes the reference direction of communication antenna base between the star of A star point to-the Z ,-Y-direction of satellite, utilizes vector network analyzer to record the test result of A, B satellite antenna isolation respectively;
Between e, A star, antenna keeps motionless, and between the star of the second satellite B, the reference direction of communication antenna base points to+the Z ,+Y of satellite ,-Z ,-Y-direction, utilizes vector network analyzer to record communication antenna isolation degree test result between A, B star respectively;
F, choose the operating frequency f2 of Inter-satellite Communication System, repeat step b, c, d, e, the reference direction recording communication antenna base between A, B Satellite points to isolation between antennas test result when+the Z ,+Y of satellite ,-Z ,-Y-direction;
G, according to above test result, between A, B Satellite obtain measurement during identical with A, B satellite antenna reference direction under f2 for operating frequency f1 sensing, communication antenna isolation carries out asking poor, and the position that the one group of isolation asking poor absolute value minimum is corresponding is setting angle and the direction of communication antenna between A, B Satellite.
First satellite A and the second satellite B is between 0.15 ~ 200m, and between star, transmitter works in small-power (generally getting-20dBm) state; Described first satellite A and the second satellite B is between 10m ~ 15km, and between star, transmitter works in high-power state (generally getting 10dBm); Described first satellite A and the second satellite B is at a distance of within the scope of 10 ~ 200m, and between star, transmitter can carry out the switching of high-power, low power state.
After the present invention's design, whether there is electromagnetic interference and whether electric wire isolation meets the demands at operating frequency f1, f2 place, needs are verified.
Inter-satellite Communication System operating frequency f1, f2 to choose the verification mode whether meeting index request as follows:
(1) utilize the electromagnetic interference of simulation software CADFEKO to the radio-frequency apparatus of satellite to analyze, concrete emulation is as follows:
(1a) choose the operating frequency f1 of Inter-satellite Communication System according to the suggestion of CCSDS (international space data system consultative committee) near space agreement, f2, f1 and f2 are in S-band;
(1b) carry out analysis of electromagnetic interference to the operating frequency of f1, f2 frequency and spread spectrum answering machine, make the f1 of communication subsystem between star, the frequency of f2 and spread spectrum answering machine not generating strap is disturbed outward;
(1c) according to communication antenna between star and Spread Spectrum TT&C antenna arrangement model, CADFEKO software is utilized to carry out isolation (isolation comprises the effect that antenna receives and dispatches gain and the spatial) Simulation Analysis between emission source and reception source to it, according to receiver Out-of-band rejection and space isolation, calculate interfering signal power;
(1d) between star, the sensitivity of communication equipment should be greater than the power level of spread spectrum answering machine interference signal; Interfering signal power intensity with communication equipment between clock star should be less than the receiving sensitivity of spread spectrum answering machine, then think and can not produce mutual interference between communication subsystem and spread spectrum answering machine between star.
(2) radiation patterns star is utilized to carry out the checking of Inter-satellite Communication System:
(2a) setup test environment: select the darkroom of half opening to carry out isolation between antennas test job, adopt Agilent8363B vector network analyzer;
(2b) between the star of the first satellite A, the antenna pattern of communication antenna is tested, and between record star, communication subsystem is at the receive-transmit isolation of f1, f2 two frequency bins;
(2c) between the star of the second satellite B, the antenna pattern of communication antenna is tested, and between record star, communication subsystem is at the receive-transmit isolation of f1, f2 two frequency bins;
(2d) distance of the first satellite A and the second satellite B is set to 0.15m, between record star, communication subsystem is at the receive-transmit isolation of f1, f2 two frequency bins;
(2e) distance of the first satellite A and the second satellite B is set to 20m, between record star, communication subsystem is at the receive-transmit isolation of f1, f2 two frequency bins;
If four kinds of states (2f) in step 2b, 2c, 2d, 2e all meet index request, then Inter-satellite Communication System meets the demands.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (9)
1., for realizing an Inter-satellite Communication System for dynamically high and low time delay Space teleoperation, it is characterized in that comprising: the first satellite A, the second satellite B; Wherein the first satellite A and the second satellite B to comprise again between communication equipment between star, star communication antenna between microwave network, star respectively;
Between the star of the first satellite A communication antenna by the radiofrequency signal that receives from the second satellite B by microwave network between star, be sent to communication equipment between star recovers payload data and the second satellite B whole star telemetry after carrying out BPSK demodulation, filtering, format, descrambling, synchronization check, between star, communication equipment sends the whole star telemetry of payload data and the second satellite B to relevant user's use respectively by CAN; Between the star of simultaneously the first satellite A, communication equipment receives the remote operating instruction of the second satellite B that Star Service subsystem is sent here by CAN, and after BPSK modulation, power amplification, filtering are carried out to this remote operating instruction, by between star between microwave network and star communication antenna be sent to the second satellite B with radiofrequency signal form;
Between the star of the second satellite B, communication antenna receives the radiofrequency signal from A star, communication equipment between the star by microwave network between star this radiofrequency signal being delivered to the second satellite B; Between star communication equipment within a certain period of time radio frequency signal carry out BPSK demodulation, filtering, format, synchronous after recover remote operating instruction, the associated user being sent to B star by RS422 interface performs corresponding remote operating task; Between the star of the second satellite B, communication equipment 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 network and star communication antenna be sent to the first satellite A with radiofrequency signal form.
2. a kind of Inter-satellite Communication System for realizing dynamically high and low time delay Space teleoperation according to claim 1, is characterized in that: between the star of described first satellite A, communication equipment comprises again Receiver And Transmitter between slave computer between star, star; Between its culminant star, slave computer to comprise between the first star slave computer between slave computer and the second star, and the two is cold standby each other; Between star, receiver to comprise between the first star receiver between receiver and the second star, and both work simultaneously, each other Hot Spare; Between star, transmitter to comprise between the first star transmitter between transmitter and the second star, and the two is cold standby each other;
After between first star of the first satellite A, between receiver and the second star, receiver carries out demodulation, filtering, format, descrambling, synchronous also verification to the radiofrequency signal received simultaneously, obtain from the payload data of the second satellite B and the whole star telemetry of the second satellite B and store, sending it between the first star slave computer between slave computer or the second star simultaneously; Between the first star, between slave computer or the second star, slave computer, according to the correctness of the verification of payload data and whole star telemetry, arranges the validity of payload data and whole star telemetry data packet mark; Between slave computer or the second star during slave computer, according to certain principle of selecting the best qualified, the whole star telemetry exporting two-way payload data and the second satellite B is selected when between first star of CAN poll first satellite A;
The remote operating instruction of the second satellite B that the Star Service subsystem received is sent here by CAN by slave computer between slave computer or the second star between first star of the first satellite A, be sent to the first transmitter or the second transmitter, after first transmitter or the second transmitter carry out BPSK modulation, power amplification, filtering to this remote operating instruction, by between star between microwave network and star communication antenna be sent to the second satellite B with radiofrequency signal form.
3. a kind of Inter-satellite Communication System for realizing dynamically high and low time delay Space teleoperation according to claim 1, it is characterized in that: between first star of described first satellite A, between receiver and the second star, receiver completes after the demodulation of radiofrequency signal received, filtering, format, descrambling, synchronous, verification in 581ms, and stores.
4. a kind of Inter-satellite Communication System for realizing dynamically high and low time delay Space teleoperation according to claim 1, it is characterized in that: between the star of described second satellite B, communication equipment to comprise again between star transmitter between receiver and star, between star, receiver to comprise between the first star receiver between receiver and the second star, between the first star, between receiver and the second star, receiver works simultaneously, each other Hot Spare; Between star, transmitter to comprise between the first star transmitter between transmitter and the second star, and the two is cold standby each other;
The radiofrequency signal that microwave network between star sends by first receiver of the second satellite B and the second receiver within a certain period of time radio frequency signal carry out BPSK demodulation, filtering, format, synchronous after recover remote operating instruction, the associated user being sent to B star by RS422 interface performs corresponding remote operating task;
First transmitter of the second satellite B or the second transmitter receive 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 network and star communication antenna be sent to the first satellite A with radiofrequency signal form.
5. a kind of Inter-satellite Communication System for realizing dynamically high and low time delay Space teleoperation according to claim 1, is characterized in that: between the star of described first satellite A and the second satellite B, antenna beamwidth is ± 60 °;
Between the star of described first satellite A and the second satellite B, communication antenna communication distance is within the scope of 0.15 ~ 15km;
Between the star of described first satellite A and the second satellite B, communication antenna exceeds celestial body surface 156mm;
Between the star of described first satellite A and the second satellite B, antenna is arranged on+X the face ,-X face of satellite body coordinate system respectively;
There is butt joint ring in the+X face of satellite body coordinate system ,-X face in described first satellite A and the second satellite B, B star butt joint ring height 88mm respectively, A star butt joint ring height 103mm.
6. a kind of Inter-satellite Communication System for realizing dynamically high and low time delay Space teleoperation according to claim 1, is characterized in that: between described star, the installation principle of communication antenna is as follows:
(1) according to the test result of the radiation patterns star of A star and B star, isolation between the star choosing A star and B star between communication antenna with radio-frequency apparatus on star differs maximum result, and the X face of communication antenna at satellite body coordinate system, the concrete installation site in-X face between the star determining A star and B star according to this result;
(2) according to the installation site determining communication antenna between A, B star in step (1), and according to the setting angle of the test result determination antenna of communication antenna receive-transmit isolation between A, B star and mode:
A, relevant position communication antenna between the star of A, B satellite is installed in the radiation patterns star determined in step (1);
B, choose the operating frequency f1 of Inter-satellite Communication System, keep antenna between B star motionless, between the star of the first satellite A the reference direction of communication antenna base point to satellite+Z-direction, utilize vector network analyzer to test the isolation recording A, B satellite antenna respectively;
C, keep antenna between B star motionless, between the star of the first satellite A the reference direction of communication antenna base point to satellite+Y-direction, utilize vector network analyzer to record the test result of A, B satellite antenna isolation respectively;
Between d, maintenance B star, antenna is motionless, makes the reference direction of communication antenna base between the star of A star point to-the Z ,-Y-direction of satellite, utilizes vector network analyzer to record the test result of A, B satellite antenna isolation respectively;
Between e, A star, antenna keeps motionless, and between the star of the second satellite B, the reference direction of communication antenna base points to+the Z ,+Y of satellite ,-Z ,-Y-direction, utilizes vector network analyzer to record communication antenna isolation degree test result between A, B star respectively;
F, choose the operating frequency f2 of Inter-satellite Communication System, repeat step b, c, d, e, the reference direction recording communication antenna base between A, B Satellite points to isolation between antennas test result when+the Z ,+Y of satellite ,-Z ,-Y-direction;
G, according to above test result, between A, B Satellite obtain measurement during identical with A, B satellite antenna reference direction under f2 for operating frequency f1 sensing, communication antenna isolation carries out asking poor, and the position that the one group of isolation asking poor absolute value minimum is corresponding is setting angle and the direction of communication antenna between A, B Satellite.
7. a kind of Inter-satellite Communication System for realizing dynamically high and low time delay Space teleoperation task according to claim 1, is characterized in that: described first satellite A and the second satellite B is between 0.15 ~ 200m, and between star, transmitter works in small-power state; Described first satellite A and the second satellite B is between 10m ~ 15km, and between star, transmitter works in high-power state; Described first satellite A and the second satellite B is at a distance of within the scope of 10 ~ 200m, and between star, transmitter can carry out the switching of high-power, low power state.
8. a kind of Inter-satellite Communication System for realizing dynamically high and low time delay Space teleoperation according to claim 1, is characterized in that: between the star of described first satellite A, transmitter sends the numeric data code speed of radiofrequency signal is 2000bps.
9. a kind of Inter-satellite Communication System for realizing dynamically high and low time delay Space teleoperation according to claim 1, it is characterized in that: the payload data that between the star of described second satellite B, transmitter sends and whole star telemetry length are respectively 256 bytes, and information code speed is 4096bps.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410505466.7A CN104333408B (en) | 2014-09-26 | 2014-09-26 | A kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410505466.7A CN104333408B (en) | 2014-09-26 | 2014-09-26 | A kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104333408A true CN104333408A (en) | 2015-02-04 |
| CN104333408B CN104333408B (en) | 2017-09-29 |
Family
ID=52408070
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410505466.7A Active CN104333408B (en) | 2014-09-26 | 2014-09-26 | A kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104333408B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105262533A (en) * | 2015-10-30 | 2016-01-20 | 中国空间技术研究院 | IP based satellite-earth forwarding and satellite networking integrated system of GEO satellites |
| CN107528628A (en) * | 2017-09-28 | 2017-12-29 | 中国电子科技集团公司第七研究所 | The signal synchronizing method of satellite communication system, device and system |
| CN107846245A (en) * | 2017-11-20 | 2018-03-27 | 航天东方红卫星有限公司 | A kind of design method of synchronous double star GPS raw measurement datas |
| CN108833032A (en) * | 2018-06-20 | 2018-11-16 | 中国人民解放军火箭军工程大学 | A kind of evaluation system for high dynamic receiver |
| CN110266362A (en) * | 2019-07-04 | 2019-09-20 | 北京邮电大学 | A kind of received disturbance restraining method of group of stars multi-beam based on millimeter wave |
| CN112737709A (en) * | 2021-01-08 | 2021-04-30 | 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 |
| CN112751605A (en) * | 2020-12-29 | 2021-05-04 | 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 |
| CN112910782A (en) * | 2021-01-05 | 2021-06-04 | 西北工业大学 | Method for realizing minimum time delay of space teleoperation system based on relay communication |
| CN113395486A (en) * | 2021-03-19 | 2021-09-14 | 天地信息网络有限公司 | Ground area continuous monitoring system based on space brain |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101354828A (en) * | 2008-09-12 | 2009-01-28 | 航天东方红卫星有限公司 | Method for transporting and managing satellite constellation information |
| CN101917285A (en) * | 2010-07-29 | 2010-12-15 | 航天东方红卫星有限公司 | Three-machine realization method for moonlet service host machine double-machine cooling structure |
| US20110237248A1 (en) * | 2006-01-18 | 2011-09-29 | Per Wahlberg | Systems and Methods for Communicating with Satellites Via Non-Compliant Antennas |
| CN102323597A (en) * | 2011-08-19 | 2012-01-18 | 航天东方红卫星有限公司 | GPS (Global Positioning System)-based inter-satellite baseline measurement method for flight of formed array around satellite |
| CN102684774A (en) * | 2012-05-25 | 2012-09-19 | 航天东方红卫星有限公司 | Method for calibrating gain and time delay of antenna in constellation communication mode |
| CN102854515A (en) * | 2012-03-31 | 2013-01-02 | 航天东方红卫星有限公司 | Method for calibrating combination zero value under constellation positioning mode |
-
2014
- 2014-09-26 CN CN201410505466.7A patent/CN104333408B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110237248A1 (en) * | 2006-01-18 | 2011-09-29 | Per Wahlberg | Systems and Methods for Communicating with Satellites Via Non-Compliant Antennas |
| CN101354828A (en) * | 2008-09-12 | 2009-01-28 | 航天东方红卫星有限公司 | Method for transporting and managing satellite constellation information |
| CN101917285A (en) * | 2010-07-29 | 2010-12-15 | 航天东方红卫星有限公司 | Three-machine realization method for moonlet service host machine double-machine cooling structure |
| CN102323597A (en) * | 2011-08-19 | 2012-01-18 | 航天东方红卫星有限公司 | GPS (Global Positioning System)-based inter-satellite baseline measurement method for flight of formed array around satellite |
| CN102854515A (en) * | 2012-03-31 | 2013-01-02 | 航天东方红卫星有限公司 | Method for calibrating combination zero value under constellation positioning mode |
| CN102684774A (en) * | 2012-05-25 | 2012-09-19 | 航天东方红卫星有限公司 | Method for calibrating gain and time delay of antenna in constellation communication mode |
Non-Patent Citations (1)
| Title |
|---|
| 张蕾，严林，高翠东等: "一种绕飞编队卫星星间链路系统的总体设计方法", 《航天器工程》 * |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN105262533A (en) * | 2015-10-30 | 2016-01-20 | 中国空间技术研究院 | IP based satellite-earth forwarding and satellite networking integrated system of GEO satellites |
| 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 |
| CN107528628A (en) * | 2017-09-28 | 2017-12-29 | 中国电子科技集团公司第七研究所 | The signal synchronizing method of satellite communication system, device and system |
| CN107846245A (en) * | 2017-11-20 | 2018-03-27 | 航天东方红卫星有限公司 | A kind of design method of synchronous double star GPS raw measurement datas |
| CN108833032A (en) * | 2018-06-20 | 2018-11-16 | 中国人民解放军火箭军工程大学 | A kind of evaluation system for high dynamic receiver |
| CN110266362A (en) * | 2019-07-04 | 2019-09-20 | 北京邮电大学 | A kind of received disturbance restraining method of group of stars multi-beam based on millimeter wave |
| 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 |
| CN112751605A (en) * | 2020-12-29 | 2021-05-04 | 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 |
| 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 |
| CN112910782A (en) * | 2021-01-05 | 2021-06-04 | 西北工业大学 | Method for realizing minimum time delay of space teleoperation system based on relay communication |
| 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 |
| CN112737709A (en) * | 2021-01-08 | 2021-04-30 | 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 |
| CN113395486A (en) * | 2021-03-19 | 2021-09-14 | 天地信息网络有限公司 | Ground area continuous monitoring system based on space brain |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104333408B (en) | 2017-09-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104333408A (en) | Inter-satellite communication system used for realizing high-dynamic and low-delay space teleoperation | |
| CN102685673B (en) | A kind of cable system | |
| CN107820334B (en) | Wireless gateway | |
| CN207869090U (en) | A kind of wireless telecommunication system of multichannel unmanned plane | |
| CN101667873A (en) | Method and system for testing radio-frequency performance of receiver in multi-antenna channel environment | |
| CN101641979A (en) | Test device, mobile radio device and method for testing a mobile radio device | |
| CN102866627A (en) | Beidou seamless high-precision time service implementation method and system | |
| CN109217947B (en) | Method and device for testing intercepted probability performance of radiation signal of data link equipment | |
| KR20120070147A (en) | Apparatus and method for measuring multiple link wireless channel | |
| CN204967832U (en) | Jointly disturb system based on frequency spectrum perception and modulation recognition | |
| CN106658712A (en) | Communication terminal positioning method system | |
| CN108880634A (en) | A kind of communication means | |
| CN106656286B (en) | Energy transmission system based on MIMO transmission technology in wireless energy supply network | |
| CN205071011U (en) | Simulation of full duplex radio communication is from interference elimination device | |
| CN103973377A (en) | Base station testing method, base station testing device and base station testing system | |
| CN103428746A (en) | Space performance verification method and system of multi-antenna device | |
| CN101668228A (en) | Device and method for testing interface | |
| CN209949210U (en) | 5G terminal anti-interference degree test system and equipment | |
| Yu et al. | FPGA-based hardware-in-the-loop simulation of user selection algorithms for cooperative transmission technology over LOS channel on geosynchronous satellites | |
| CN106888076A (en) | Synchronous method and device is realized in a kind of wave beam training | |
| CN102148885A (en) | Method and system for testing multi-antenna terminal | |
| CN108462536B (en) | Relay satellite rocket-borne user terminal initial parameter remote binding system | |
| US10149180B2 (en) | Radio communication system, elevator control system using same, and substation facility monitoring system | |
| CN105227251A (en) | Based on multiple antennas two-way channel measurement mechanism and the calibration steps of distributed structure/architecture | |
| CN103199947A (en) | Ground test method of communication link between detectors |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |