CN203951478U - A kind of based on lunar orbit world information link automatization simulation test platform - Google Patents
A kind of based on lunar orbit world information link automatization simulation test platform Download PDFInfo
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- CN203951478U CN203951478U CN201420337779.1U CN201420337779U CN203951478U CN 203951478 U CN203951478 U CN 203951478U CN 201420337779 U CN201420337779 U CN 201420337779U CN 203951478 U CN203951478 U CN 203951478U
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- 238000001514 detection method Methods 0.000 claims abstract description 16
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Abstract
It is a kind of based on lunar orbit world information link automatization simulation test platform that the utility model provides, and comprising: telemetered signal analogue unit; The number number of delivering a letter analogue unit; The integrated observing and controlling data transmission equipment of lunar orbit spacecraft, is connected with described telemetered signal analogue unit and the described number number of delivering a letter analogue unit signal respectively; Radio frequency interface unit, receives up-downgoing carrier signal; Switch matrix, receiving portion descending carrier signal and another part up-link carrier signal; Standard detection equipment, is connected with switch matrix; Transceiver channel combination; Upconverter and low-converter; Observing and controlling synthetical baseband unit, is connected with upconverter and low-converter respectively; Measurement &control computer, is connected with observing and controlling synthetical baseband unit.Based on lunar orbit world information link automatization simulation test platform significantly less manual operations, improve test speed and efficiency, increased the spreadability of test, improved reliability and the fail safe of test.
Description
Technical field
The utility model relates to the space industry of Spacecraft TT&C digital transmission communication simulation test, relates in particular to a kind of based on lunar orbit world information link automatization simulation test platform.
Background technology
In current space industry world information link analog testing platform, conventional design is that observing and controlling simulation test equipment and number pass simulation test equipment separately, only be equipped with observing and controlling synthetical baseband unit, Up/Down Conversion device, test computer and standard signal checkout equipment, the unrealized control to other equipment in platform of test computer, unrealized automatization simulation test function; Conventional analog testing platform, not for lunar orbit world information link simulation test, does not adopt the X frequency range communication technology; Conventional analog testing platform does not possess for the power supply of Spacecraft TT&C data transmission equipment and information interface, can not simulate the various remote measurement baseband signals, number biography baseband signal and the remote control baseband signal that generate aircraft, not possess the function of taking into account the test of Spacecraft TT&C data transmission equipment functional performance and world information link simulation test.The self-looped testing function of conventional analog testing platform in can not implementation platform.The major defect of existing world information link analog testing platform is function singleness, and manual operations is more, and artificial interpretation is more, does not possess the features such as quick and easy to operate.
Utility model content
It is a kind of based on lunar orbit world information link automatization simulation test platform that the utility model provides, and to solve existing world information link analog testing platform function singleness, has the problem of more artificial interpretation.
In order to solve the problems of the technologies described above, the technical solution of the utility model is: a kind of based on lunar orbit world information link automatization simulation test platform, comprising: telemetered signal analogue unit; The number number of delivering a letter analogue unit; The integrated observing and controlling data transmission equipment of lunar orbit spacecraft, be connected with described telemetered signal analogue unit and the described number number of delivering a letter analogue unit signal respectively, and launch descending carrier signal, the integrated observing and controlling data transmission equipment of described lunar orbit spacecraft receives the part up-link carrier signal after via line amplifier amplifies; Radio frequency interface unit, receives described descending carrier signal and up-link carrier signal; Switch matrix, receiving portion descending carrier signal and another part up-link carrier signal, described part descending carrier signal and another part up-link carrier signal are respectively by forming after described radio frequency interface element coupling; Standard detection equipment, is connected with described switch matrix; Transceiver channel combination; Upconverter, output up-link carrier signal is to described transceiver channel combination; Low-converter, accepts another part descending carrier signal, and described another part descending carrier signal carries out forming after direct sum power adjustments after being received by described transceiver channel combination; Observing and controlling synthetical baseband unit, is connected with described upconverter and described low-converter respectively; Measurement &control computer, is connected with described observing and controlling synthetical baseband unit.
Further, the integrated observing and controlling data transmission equipment of described lunar orbit spacecraft is connected with described telemetered signal analogue unit, and launches the descending telemetry carrier signal of X frequency range.
Further, the integrated observing and controlling data transmission equipment of described lunar orbit spacecraft is connected with the described number number of delivering a letter analogue unit, and launches line number posting ripple signal under X frequency range.
Further, described radio frequency interface unit receives the described descending carrier signal after line amplifier amplifies.
Further, described switch matrix is X frequency range switch matrix, and described upconverter is X frequency range upconverter, and described low-converter is X frequency range low-converter.
Further, described standard detection equipment comprises spectrum analysis detecting unit, frequency detecting unit, power detecting unit, vector signal detecting unit and video signal detection unit.
Further, based on lunar orbit world information link automatization simulation test platform, also comprise school zero transponder, described school zero transponder is configured in the integrated observing and controlling data transmission equipment of described lunar orbit spacecraft.
Further, based on lunar orbit world information link automatization simulation test platform, also comprise fixed attenuator and adjustable attenuator, described fixed attenuator and described adjustable attenuator are integrated in described transceiver channel combination.
Further, based on lunar orbit world information link automatization simulation test platform, also comprise isolating transformer, described isolating transformer makes mains-supplied keeps apart with the ground connection of testing equipment.
Further, based on lunar orbit world information link automatization simulation test platform, also comprise micro-wave coupler, described micro-wave coupler is positioned at described radio frequency interface unit.
What the utility model provided has following beneficial effect based on lunar orbit world information link automatization simulation test platform:
Based on lunar orbit world information link automatization simulation test platform integrated Spacecraft TT&C count the function of the test of leaflet machine equipment, subsystem test and whole Spacecraft TT&C docking test, complete function, has improved the utilization ratio of test platform.Test platform passes integrated design for Spacecraft TT&C number, and observing and controlling number is passed to the ground simulation test system integration in a set of platform, is convenient to the mode of operation according to aerocraft real, and observing and controlling, Data Channel are carried out to combine analog test.
Based on lunar orbit world information link automatization simulation test platform, possesses automatic test function, employing is with the power transceiver channel combination of regulatory function on a large scale, and the line amplifier technology of high frequency cable direct current supply, reduced manual operations, convenient every test is parallel to be carried out, improve test speed and efficiency, and adopted transceiver channel combination and line amplifier every straight design to improve the fail safe of testing.By integrated aircraft observing and controlling, count the function of the test of leaflet machine equipment, subsystem test and whole Spacecraft TT&C docking test; Integrated observing and controlling, number pass ground simulation test function.By test computer, control all devices in platform, gather running status and the test data of each equipment, realize automatic test, adopt switch matrix automatic switchover up-downgoing carrier signal, avoided a large amount of and manually connected, improved the reliability of test.For lunar orbit flight observing and controlling number, pass frequency many, the many features of while working channel, to each frequency, each channel is equipped with separately hardware simulation passage, has guaranteed the deep, careful and comprehensive of test.
Further, adopt isolating transformer, civil power 220v is powered and kept apart with the ground connection of testing equipment, avoid mains-supplied ground directly to power and be connected with aircraft, further avoid mains-supplied unstable voltage on the ground to cause the damage of aircraft devices, described grounding design has been avoided the power supply insecurity in aircraft test process from source, has improved the fail safe of observing and controlling work.
Further, based on configuring school zero transponder in the information link automatization simulation test platform of the lunar orbit world, realized in the non-participating situation of Spacecraft TT&C data transmission equipment, self-looped testing in the information link automatization simulation test platform of the world, observing and controlling upward signal and observing and controlling down channel, from closed loop, can be realized to described test platform range finding school zero power energy.This design provides the self-checking function based on lunar orbit world information link automatization simulation test platform.
Further, adopt the micro-wave coupler in radio frequency signal interface unit that up-downgoing carrier signal is sent into switch matrix, switch matrix can automatically switch up-downgoing carrier signal under the control of test computer, send into the test of carrying out radiofrequency signal in standard test equipment, avoided a large amount of and manually connected and repeatedly plug connector is caused to damage, improved the efficiency of test and the reliability of equipment.
Further, described a kind of based on lunar orbit world information link automatization simulation test platform for lunar orbit distance, the signal power dynamic range of observing and controlling Data Channel is large, highly sensitive feature, integrated fixed attenuator and adjustable attenuator in transceiver channel combination in platform, realize signal power adjustable function on a large scale, avoids external attenuator on high frequency cable, improved the reliability of system, convenient test operation.
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Accompanying drawing explanation
Below in conjunction with accompanying drawing, the utility model is described in further detail:
Fig. 1 is the modular structure schematic diagram based on lunar orbit world information link automatization simulation test platform that the utility model embodiment provides.
In Fig. 1:
101: telemetered signal analogue unit; 102: the number number of delivering a letter analogue unit; 103: the integrated observing and controlling data transmission equipment of lunar orbit spacecraft; 104: line amplifier; 105: radio frequency interface unit; 106: switch matrix; 107a: spectrum analysis detecting unit; 107b: frequency detecting unit; 107c: power detecting unit; 107d: vector signal detecting unit; 107e: video signal detection unit; 108: transceiver channel combination; 109a: an X frequency range upconverter; 109b: the 2nd X frequency range upconverter; 110a: an X frequency range low-converter; 110b the 2nd X frequency range low-converter; 110c: the 3rd X frequency range low-converter; 111: observing and controlling synthetical baseband unit; 112: Measurement &control computer; 113: ground-plane antenna; 114: school zero transponder; 115: isolating transformer; 116: the network switch; 117: DC power supply
Embodiment
Below in conjunction with the drawings and specific embodiments to being described in further detail based on lunar orbit world information link automatization simulation test platform of the utility model proposes.According to the following describes and claims, advantage of the present utility model and feature will be clearer.It should be noted that, accompanying drawing all adopts very the form of simplifying and all uses non-ratio accurately, only in order to convenient, the object of aid illustration the utility model embodiment lucidly.
Core concept of the present utility model is, provide based on lunar orbit world information link automatization simulation test platform integrated Spacecraft TT&C count the function of the test of leaflet machine equipment, subsystem test and whole Spacecraft TT&C docking test, complete function, has improved the utilization ratio of test platform.Test platform passes integrated design for Spacecraft TT&C number, and observing and controlling number is passed to the ground simulation test system integration in a set of platform, is convenient to the mode of operation according to aerocraft real, and observing and controlling, Data Channel are carried out to combine analog test.Based on lunar orbit world information link automatization simulation test platform, possesses automatic test function, employing is with the power transceiver channel combination of regulatory function on a large scale, and the line amplifier technology of high frequency cable direct current supply, reduced manual operations, convenient every test is parallel to be carried out, improve test speed and efficiency, and adopted transceiver channel combination and line amplifier every straight design to improve the fail safe of testing.By integrated aircraft observing and controlling, count the function of the test of leaflet machine equipment, subsystem test and whole Spacecraft TT&C docking test; Integrated observing and controlling, number pass ground simulation test function.By test computer, control all devices in platform, gather running status and the test data of each equipment, realize automatic test, adopt switch matrix automatic switchover up-downgoing carrier signal, avoided a large amount of and manually connected, improved the reliability of test.For lunar orbit flight observing and controlling number, pass frequency many, the many features of while working channel, to each frequency, each channel is equipped with separately hardware simulation passage, has guaranteed the deep, careful and comprehensive of test.
Fig. 1 is the modular structure schematic diagram based on lunar orbit world information link automatization simulation test platform that the utility model embodiment provides.With reference to Fig. 1, telemetered signal analogue unit 101; The number number of delivering a letter analogue unit 102; The integrated observing and controlling data transmission equipment 103 of lunar orbit spacecraft, be connected with described telemetered signal analogue unit 101 and the described number number of delivering a letter analogue unit 102 signals respectively, and launch descending carrier signal, the integrated observing and controlling data transmission equipment 103 of described lunar orbit spacecraft receives the part up-link carrier signal after via line amplifier 104 amplifies; Radio frequency interface unit 105, receives described descending carrier signal and up-link carrier signal; Switch matrix 106, receiving portion descending carrier signal and another part up-link carrier signal, described part descending carrier signal and another part up-link carrier signal are respectively by forming after 105 couplings of described radio frequency interface unit; Standard detection equipment, is connected with described switch matrix 106; Transceiver channel combination 108; Upconverter, output up-link carrier signal is to described transceiver channel combination 108; Low-converter 110, accepts another part descending carrier signal, and described another part descending carrier signal carries out forming after direct sum power adjustments after being received by described transceiver channel combination 108; Observing and controlling synthetical baseband unit 111, is connected with described upconverter and described low-converter 110 respectively; Measurement &control computer 112, is connected with described observing and controlling synthetical baseband unit 111.
In the present embodiment, the integrated observing and controlling data transmission equipment 103 of described lunar orbit spacecraft is connected with described telemetered signal analogue unit 101, and launch the descending telemetry carrier signal of X frequency range, the integrated observing and controlling data transmission equipment 103 of described lunar orbit spacecraft is connected with the described number number of delivering a letter analogue unit 102, and launches line number posting ripple signal under X frequency range.Described switch matrix 106 is X frequency range switch matrix, and described upconverter is X frequency range upconverter, and described low-converter 110 is X frequency range low-converter.DC power supply 117 is that the integrated observing and controlling data transmission equipment 103 of described lunar orbit spacecraft is for direct current.
Described radio frequency interface unit 105 receives the described descending carrier signal after line amplifier 104 amplifies.Particularly, based on lunar orbit world information link automatization simulation test platform, by ground-plane antenna 113, receive descending telemetry carrier signal and lower line number posting ripple signal, described descending telemetry carrier signal and lower line number posting ripple signal are sent into radio frequency interface unit 105 after line amplifier 104 amplifies.Feature based on lunar orbit world information link automatization simulation test platform for space flight field trial long transmission distance adopts the line amplifier technology of high frequency cable direct current supply in platform, and signal transmission is amplified.The line amplifier technology of high frequency cable direct current supply adopts high frequency cable inner core directly to present the mode of direct current supply, line amplifier 104 is powered, avoided when test, use separately length to carry out line amplifier 104 power supplies apart from service cable, reduce number of cables, improved the convenience of test.Meanwhile, transceiver channel combination 108 and line amplifier 104 in platform all adopt every straight design, avoid the direct current on high frequency cable inner core to enter testing equipment by high frequency cable, avoid testing equipment to damage, and have increased the fail safe of test.
Further, described standard detection equipment comprises spectrum analysis detecting unit 107a, frequency detecting unit 107b, power detecting unit 107c, vector signal detecting unit 107d and video signal detection unit 107e.
Measurement &control computer 112 is realized Ethernet by the network switch 116 with other equipment in test platform and is connected, and by Ethernet, controls each testing equipment in test platform, gathers running status and the test data of each equipment, realizes automatic test function.
Based on lunar orbit world information link automatization simulation test platform, also comprise school zero transponder 114, described school zero transponder 114 is configured in the integrated observing and controlling data transmission equipment 103 of described lunar orbit spacecraft.The school of configuration zero transponder 114, realized in the non-participating situation of Spacecraft TT&C data transmission equipment, self-looped testing in the information link automatization simulation test platform of the world, from closed loop, can realize described test platform range finding school zero power energy by observing and controlling upward signal and observing and controlling down channel.This design provides the self-checking function based on lunar orbit world information link automatization simulation test platform.
Based on lunar orbit world information link automatization simulation test platform, also comprise fixed attenuator and adjustable attenuator, described fixed attenuator and described adjustable attenuator are integrated in described transceiver channel combination 108, realize signal power adjustable function on a large scale, avoid external attenuator on high frequency cable, improved the reliability of system, convenient test operation.
Based on lunar orbit world information link automatization simulation test platform, adopt isolating transformer 115, civil power 220V is powered and kept apart with the ground connection of testing equipment, avoid mains-supplied ground directly to power and be connected with aircraft, avoid mains-supplied unstable voltage on the ground to cause the damage of aircraft devices.Described grounding design has been avoided the power supply insecurity in aircraft test process from source, has improved the fail safe of observing and controlling work.
Simulation test for up remote control channel, by Measurement &control computer 112 simulation ground remote control commands, be sent to observing and controlling synthetical baseband unit 111, in observing and controlling synthetical baseband unit 111, modulation generates remote control 70MHz intermediate frequency carrier, by two-way, output to respectively an X frequency range upconverter 109a and the 2nd X frequency range upconverter 109b, in upconverter, be converted to X frequency range carrier wave, further send in transceiver channel combination 108, carry out DC feedback, every value design and power adjustments, send into again radio frequency interface unit 105, in radio frequency interface unit 105, a coupling part is to X frequency range switch matrix, can automatically switch to respectively each standard detection equipment, another part is launched by ground-plane antenna 113 after directly sending in line amplifier 104 and amplifying.The integrated observing and controlling data transmission equipment of lunar orbit spacecraft receives observing and controlling upward signal, has realized the simulation test of up remote control channel.
For the simulation test of descending telemeter channel, the integrated observing and controlling data transmission equipment 103 of lunar orbit spacecraft receives the aircraft remote measurement analog signal of telemetered signal analogue unit 101, processes the descending telemetry carrier signal of backward ground simulation test platform transmitting X frequency range.Based on lunar orbit world information link automatization simulation test platform, by ground-plane antenna 113, receive this descending telemetry carrier signal, after amplifying, line amplifier 104 sends into radio frequency interface unit 105, in radio frequency interface unit 105, a coupling part, to X frequency range switch matrix, can automatically switch to respectively each standard detection equipment; Another part is directly sent into transceiver channel combination 108, carry out every value and power adjustments, be sent to again an X frequency range low-converter 110a and the 2nd X frequency range low-converter 110 b, through being down-converted to after 70MHz intermediate frequency, send into observing and controlling synthetical baseband unit 111, process and obtain after descending telemetry intelligence (TELINT), be sent to Measurement &control computer 112 and process and show.
For the simulation test of descending Data Channel, the aircraft number that the integrated observing and controlling data transmission equipment 103 of lunar orbit spacecraft receives the number number of delivering a letter analogue unit 102 passes analog signal, processes line number posting ripple signal under backward ground simulation test platform transmitting X frequency range.Based on lunar orbit world information link automatization simulation test platform, by ground-plane antenna 113, receive this lower line number posting ripple signal, after amplifying, line amplifier 104 sends into radio frequency interface unit 105, in radio frequency interface unit 105, a coupling part, to X frequency range switch matrix, can automatically switch to respectively each standard detection equipment; Another part is directly sent into transceiver channel combination 108, carry out every value and power adjustments, be sent to again the 3rd X frequency range low-converter 110c, through being down-converted to after 70MHz intermediate frequency, send into observing and controlling synthetical baseband unit 111, demodulation process obtains lower line number and delivers a letter after breath, is sent to Measurement &control computer 112 and processes and show.
After above-mentioned analog channel is set up, by Measurement &control computer 112 comparison remote controls, remote measurement and number, pass the error rate, standard test equipment detection observing and controlling number is caught, the signal quality of descending carrier.
Based on lunar orbit world information link automatization simulation test platform, adopt the micro-wave coupler of radio frequency signal interface unit 105 that five carrier signals of up-downgoing are sent into X frequency range switch matrix, X frequency range switch matrix can automatically switch five carrier signals of up-downgoing under the control of Measurement &control computer 112, sends into respectively the test of carrying out radiofrequency signal in spectrum analysis detecting unit 107a, frequency detecting unit 107b, power detecting unit 107c, vector signal detecting unit 107d and five standard test equipment of video signal detection unit 107e.Avoided a large amount of and manually connected, avoided repeatedly plugging connector being caused to damage, improved the efficiency of test and the reliability of equipment.
Based on lunar orbit world information link automatization simulation test platform integrated Spacecraft TT&C count the function of the test of leaflet machine equipment, subsystem test and whole Spacecraft TT&C docking test, complete function, has improved the utilization ratio of test platform.Test platform passes integrated design for Spacecraft TT&C number, and observing and controlling number is passed to the ground simulation test system integration in a set of platform, is convenient to the mode of operation according to aerocraft real, and observing and controlling, Data Channel are carried out to combine analog test.Based on lunar orbit world information link automatization simulation test platform significantly less manual operations, improve test speed and efficiency, increased the spreadability of test, improved reliability and the fail safe of test.
Obviously, those skilled in the art can carry out various changes and distortion and not depart from spirit and scope of the present utility model the utility model.Like this, if within of the present utility model these are revised and modification belongs to the scope of the utility model claim and equivalent technologies thereof, the utility model is also intended to comprise these changes and modification interior.
Claims (10)
1. based on a lunar orbit world information link automatization simulation test platform, it is characterized in that, comprising: telemetered signal analogue unit;
The number number of delivering a letter analogue unit;
The integrated observing and controlling data transmission equipment of lunar orbit spacecraft, be connected with described telemetered signal analogue unit and the described number number of delivering a letter analogue unit signal respectively, and launch descending carrier signal, the integrated observing and controlling data transmission equipment of described lunar orbit spacecraft receives the part up-link carrier signal after via line amplifier amplifies;
Radio frequency interface unit, receives described descending carrier signal and up-link carrier signal;
Switch matrix, receiving portion descending carrier signal and another part up-link carrier signal, described part descending carrier signal and another part up-link carrier signal are respectively by forming after described radio frequency interface element coupling;
Standard detection equipment, is connected with described switch matrix;
Transceiver channel combination;
Upconverter, output up-link carrier signal is to described transceiver channel combination;
Low-converter, accepts another part descending carrier signal, and described another part descending carrier signal carries out forming after direct sum power adjustments after being received by described transceiver channel combination;
Observing and controlling synthetical baseband unit, is connected with described upconverter and described low-converter respectively;
Measurement &control computer, is connected with described observing and controlling synthetical baseband unit.
2. according to claim 1 based on lunar orbit world information link automatization simulation test platform, it is characterized in that, the integrated observing and controlling data transmission equipment of described lunar orbit spacecraft is connected with described telemetered signal analogue unit, and launches the descending telemetry carrier signal of X frequency range.
3. according to claim 1 based on lunar orbit world information link automatization simulation test platform, it is characterized in that, the integrated observing and controlling data transmission equipment of described lunar orbit spacecraft is connected with the described number number of delivering a letter analogue unit, and launches line number posting ripple signal under X frequency range.
4. according to claim 1ly based on lunar orbit world information link automatization simulation test platform, it is characterized in that, described radio frequency interface unit receives the described descending carrier signal after line amplifier amplifies.
5. according to claim 1 based on lunar orbit world information link automatization simulation test platform, it is characterized in that, described switch matrix is X frequency range switch matrix, and described upconverter is X frequency range upconverter, and described low-converter is X frequency range low-converter.
6. according to claim 1 based on lunar orbit world information link automatization simulation test platform, it is characterized in that, described standard detection equipment comprises spectrum analysis detecting unit, frequency detecting unit, power detecting unit, vector signal detecting unit and video signal detection unit.
7. according to claim 1ly based on lunar orbit world information link automatization simulation test platform, it is characterized in that, also comprise school zero transponder, described school zero transponder is configured in the integrated observing and controlling data transmission equipment of described lunar orbit spacecraft.
8. according to claim 1 based on lunar orbit world information link automatization simulation test platform, it is characterized in that, also comprise fixed attenuator and adjustable attenuator, described fixed attenuator and described adjustable attenuator are integrated in described transceiver channel combination.
9. according to claim 1ly based on lunar orbit world information link automatization simulation test platform, it is characterized in that, also comprise isolating transformer, described isolating transformer makes mains-supplied keeps apart with the ground connection of testing equipment.
10. according to claim 1ly based on lunar orbit world information link automatization simulation test platform, it is characterized in that, also comprise micro-wave coupler, described micro-wave coupler is positioned at described radio frequency interface unit.
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| CN201420337779.1U CN203951478U (en) | 2014-06-24 | 2014-06-24 | A kind of based on lunar orbit world information link automatization simulation test platform |
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| CN201420337779.1U CN203951478U (en) | 2014-06-24 | 2014-06-24 | A kind of based on lunar orbit world information link automatization simulation test platform |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105892305A (en) * | 2014-12-15 | 2016-08-24 | 北京空间技术研制试验中心 | General spacecraft ground test bed system |
| CN110554618A (en) * | 2019-10-10 | 2019-12-10 | 西安电子工程研究所 | communication system simulation method based on radar darkroom |
| CN111131929A (en) * | 2019-12-16 | 2020-05-08 | 上海卫星工程研究所 | Spacecraft measurement and control data transmission signal processing and data distribution device and communication method thereof |
| CN111212335A (en) * | 2019-12-16 | 2020-05-29 | 上海卫星工程研究所 | Deep space detector radio frequency test system self-checking device and test method thereof |
| CN113114345A (en) * | 2021-04-26 | 2021-07-13 | 上海卫星工程研究所 | Radio frequency signal conditioning equipment integrating intensive measurement and control, data transmission and relay |
-
2014
- 2014-06-24 CN CN201420337779.1U patent/CN203951478U/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105892305A (en) * | 2014-12-15 | 2016-08-24 | 北京空间技术研制试验中心 | General spacecraft ground test bed system |
| CN105892305B (en) * | 2014-12-15 | 2019-07-30 | 北京空间技术研制试验中心 | General spacecraft ground tests bed system |
| CN110554618A (en) * | 2019-10-10 | 2019-12-10 | 西安电子工程研究所 | communication system simulation method based on radar darkroom |
| CN110554618B (en) * | 2019-10-10 | 2022-06-21 | 西安电子工程研究所 | Communication system simulation method based on radar darkroom |
| CN111131929A (en) * | 2019-12-16 | 2020-05-08 | 上海卫星工程研究所 | Spacecraft measurement and control data transmission signal processing and data distribution device and communication method thereof |
| CN111212335A (en) * | 2019-12-16 | 2020-05-29 | 上海卫星工程研究所 | Deep space detector radio frequency test system self-checking device and test method thereof |
| CN111212335B (en) * | 2019-12-16 | 2021-09-14 | 上海卫星工程研究所 | Deep space detector radio frequency test system self-checking device and test method thereof |
| CN111131929B (en) * | 2019-12-16 | 2021-11-16 | 上海卫星工程研究所 | Spacecraft measurement and control data transmission signal processing and data distribution device and communication method thereof |
| CN113114345A (en) * | 2021-04-26 | 2021-07-13 | 上海卫星工程研究所 | Radio frequency signal conditioning equipment integrating intensive measurement and control, data transmission and relay |
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Granted publication date: 20141119 |