CN204374411U - Satellite laser ranging system - Google Patents
Satellite laser ranging system Download PDFInfo
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- CN204374411U CN204374411U CN201420802041.8U CN201420802041U CN204374411U CN 204374411 U CN204374411 U CN 204374411U CN 201420802041 U CN201420802041 U CN 201420802041U CN 204374411 U CN204374411 U CN 204374411U
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Abstract
The utility model provides a kind of satellite laser ranging system, this satellite laser ranging system, it is characterized in that, comprise range finding computer for controlling, laser instrument, transmitter-telescope, receiving telescope, data acquisition computer, event timer, range gate circuit board, artificial satellite track sight and single-photon avalanche diode.The satellite laser ranging system that the utility model provides, by event timer record main ripple moment and echo moment, the application of At High Resolution range gate can improve the signal to noise ratio (S/N ratio) of system greatly, and then improve effective echo data amount, considerably improve distance accuracy and the range capability of system simultaneously.
Description
Technical field
The utility model relates to laser ranging field, particularly relates to a kind of satellite laser ranging system.
Background technology
Satellite laser ranging (SLR) technology measures laser pulse by research station, reflect via cooperative target (satellite of retroeflector is normally housed), based on the flight time finally turning back to research station, single measurement precision can reach the satellite ranging means of centimetre-sized and even inferior centimeter order.
In existing satellite laser range-measurement system, the laser pulse that laser instrument produces introduces transmitter-telescope through tortuous light path and Cude light path, transmitter-telescope is by the artificial satellite of directive after laser beam datum with back azimuth reverberator, in transmitting light path, take out a very little part simultaneously, electric pulse is formed by main ripple sample circuit, be divided into two-way, one tunnel is called main wave impulse, after pulsqe distributor shaping, as enabling signal or commencing signal, be used for start-up time interval counter (as HP5370B, SR620), it is the service of recording laser x time that another road enters timing circuit, the laser pulse of directive artificial satellite, ground is returned to after the reflector reflects of artificial satellite, by receiving telescope system acceptance, the focus of receiving telescope system is converted to electric pulse through electrooptical device single-photon avalanche diode (C-SPAD), echo-pulse is formed again after pulsqe distributor shaping, as pass gate signal or stop signal, be used for the counting of stand-by time interval counter, the time interval between main wave impulse and echo-pulse just recorded by such time-interval counter, the i.e. turnaround time t of laser between research station and artificial satellite, be multiplied by light velocity c and can calculate distance measurement value.
But, traditional SLR technology of the flight time of single laser pulse measured by above-mentioned employing time-interval counter, for the satellite of multiple orbital attitudes, flight time of laser pulse is not from several milliseconds to hundreds of millisecond etc., therefore time interval clocking technique limits the frequency of operation of SLR system, for high rail satellite, laser repetition rate can only at below 10Hz, because laser repetition rate is low, cause system signal noise ratio low, make system in the measurements high rail satellite and ground shadow in low orbit satellite time inferior capabilities.
Utility model content
(1) technical matters that will solve
The technical problems to be solved in the utility model is to provide a kind of satellite laser ranging system, can improve the signal to noise ratio (S/N ratio) of system.
(2) technical scheme
For solving the problems of the technologies described above, the utility model provides a kind of satellite laser ranging system, comprises range finding computer for controlling, laser instrument, transmitter-telescope, receiving telescope, data acquisition computer, event timer, range gate circuit board, artificial satellite track sight and single-photon avalanche diode;
The forecast position of the real-time calculating artificial satellite of described range finding computer for controlling under survey station coordinate system and obtain guidance information according to described forecast position, and periodically calculate laser ignition moment and range gate forecast moment;
Described artificial satellite track sight is connected with described range finding computer for controlling, transmitter-telescope, receiving telescope, and described artificial satellite track sight controls described transmitter-telescope according to described guidance information and the rotation of described artificial satellite followed by receiving telescope;
Described range gate circuit board is connected with described range finding computer for controlling, laser instrument, single-photon avalanche diode, described range gate circuit board controls the igniting of described laser instrument according to the described laser ignition moment, and controls the enable of described single-photon avalanche diode according to the described range gate forecast moment;
Described laser instrument is connected with described transmitter-telescope, the laser pulse produced at described laser instrument by artificial satellite described in described transmitter-telescope directive while, from the transmitting light path of described laser pulse, get fraction of laser light and form main wave impulse;
Described single-photon avalanche diode is connected with described receiving telescope, and the reflects laser of the described artificial satellite that described receiving telescope receives by described single-photon avalanche diode is converted to electric pulse, forms echo-pulse after described electric pulse shaping;
The moment of main wave impulse described in described event timer record, as the main ripple moment, records the moment of described echo-pulse as the echo moment;
Described data acquisition computer is connected with described event timer, and described data acquisition computer was found range according to the main ripple moment of described event timer record and echo moment.
Further, described range gate circuit board comprises latch, the first buffer, local clock, comparer and the second buffer;
Described latch is connected with described first impact damper, described local clock;
Described comparer is connected with described local clock, the second impact damper;
Described first impact damper, described second impact damper are connected with described range finding computer for controlling.
Further, described first impact damper, described second impact damper are connected with described range finding computer for controlling by parallel port.
Further, also comprise Time And Frequency benchmark generator, for providing time reference and frequency reference for described satellite laser ranging system, described Time And Frequency benchmark generator comprises GPS Timing Receiver, pulsqe distributor and frequency divider, described pulsqe distributor is connected with described GPS Timing Receiver, and described frequency divider is connected with described GPS Timing Receiver.
Further, the repetition frequency of described laser instrument Emission Lasers is 2KHz.
(3) beneficial effect
The satellite laser ranging system that the utility model provides, by event timer record main ripple moment and echo moment, the application of At High Resolution range gate can improve the signal to noise ratio (S/N ratio) of system greatly, and then improve effective echo data amount, considerably improve distance accuracy and the range capability of system simultaneously.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of a kind of satellite laser ranging system that the utility model embodiment provides;
Fig. 2 is the schematic diagram of the another kind of satellite laser ranging system that the utility model embodiment provides;
Fig. 3 is the schematic diagram of a kind of artificial satellite track sight that the utility model embodiment provides;
The schematic diagram of a kind of range gate circuit board that Fig. 4 provides for the utility model embodiment.
Embodiment
Below in conjunction with drawings and Examples, embodiment of the present utility model is described in further detail.Following examples for illustration of the utility model, but are not used for limiting scope of the present utility model.
Fig. 1 is the schematic diagram of a kind of satellite laser ranging system that the utility model embodiment provides, and comprises range finding computer for controlling 1, laser instrument 2, transmitter-telescope 3, receiving telescope 4, data acquisition computer 5, event timer 6, range gate circuit board 7, artificial satellite track sight 8 and single-photon avalanche diode 9;
The forecast position of the real-time calculating artificial satellite of described range finding computer for controlling under survey station coordinate system and obtain guidance information according to described forecast position, and periodically calculate laser ignition moment and range gate forecast moment;
Described artificial satellite track sight is connected with described range finding computer for controlling, transmitter-telescope, receiving telescope, and described artificial satellite track sight controls described transmitter-telescope according to described guidance information and the rotation of described artificial satellite followed by receiving telescope;
Described range gate circuit board is connected with described range finding computer for controlling, laser instrument, single-photon avalanche diode, described range gate circuit board controls the igniting of described laser instrument according to the described laser ignition moment, and controls the enable of described single-photon avalanche diode according to the described range gate forecast moment;
Described laser instrument is connected with described transmitter-telescope, the laser pulse produced at described laser instrument by artificial satellite described in described transmitter-telescope directive while, from the transmitting light path of described laser pulse, get fraction of laser light and form main wave impulse;
Described single-photon avalanche diode is connected with described receiving telescope, and the reflects laser of the described artificial satellite that described receiving telescope receives by described single-photon avalanche diode is converted to electric pulse, forms echo-pulse after described electric pulse shaping;
The moment of main wave impulse described in described event timer record, as the main ripple moment, records the moment of described echo-pulse as the echo moment;
Described data acquisition computer is connected with described event timer, and described data acquisition computer was found range according to the main ripple moment of described event timer record and echo moment.
Wherein, the repetition frequency of described laser instrument Emission Lasers is 2KHz.
The satellite laser ranging system that the utility model embodiment provides, by event timer record main ripple moment and echo moment, greatly can improve the signal to noise ratio (S/N ratio) of system, and then improve effective echo data amount, considerably improve distance accuracy and the range capability of system simultaneously.
Fig. 2 is the schematic diagram of the another kind of satellite laser ranging system that the utility model embodiment provides, this satellite laser ranging system comprises range finding computer for controlling, artificial satellite track sight, data acquisition computer, laser instrument, event timer, range gate circuit board, emission coefficient, receiving system and single-photon avalanche diode (C-SPAD), also comprises Time And Frequency benchmark generator;
Wherein, artificial satellite track sight can comprise servo module and time module, and as shown in Figure 3, wherein servo module comprises direct current torque motor, Renishaw Circular gratings, tech-generator, direct current servo driver, encoder to count card and D/A card; Time module can comprise GPS Timing Receiver (as HP58503), antenna, counter card (as TMC-10), in satellite laser range-measurement system, the Satellite Orbit Prediction parameter that general employing international laser range finding service network (ILRS) provides calculates the D coordinates value of satellite under survey station coordinate system (position angle, the angle of pitch, time), by making this time module and UTC time keep synchronous, thus can ensure that telescope accurately points to the satellite that passes by.Wherein, above-mentioned D/A card, encoder to count device card, counter Ka Kenei are embedded in range finding computer for controlling.
Particularly, range finding computer for controlling primary responsibility calculates the forecast position of satellite under survey station coordinate system in real time and guidance information is issued to servo module, and periodically calculates range gate forecast moment and laser ignition moment and issue to range gate circuit board;
Servo module receives follows satellite rotation from the transmitter-telescope in the guidance information control emission coefficient of range finding computer for controlling and the receiving telescope in receiving system;
This Time And Frequency benchmark generator is used for providing time reference and frequency reference for artificial satellite laser range-measurement system, specifically comprise GPS Timing Receiver, pulsqe distributor and frequency divider, wherein, pulsqe distributor is connected with GPS Timing Receiver, and frequency divider is connected with GPS Timing Receiver.；
Range gate circuit board accurately controls the igniting of laser instrument and the enable of C-SAPD according to the time information from range finding computer for controlling;
Data acquisition computer periodically reads in main ripple moment sequence and echo moment sequence from event timer, carries out exact matching, thus calculate laser time of flight according to satellite alert to main ripple moment and echo moment.Particularly, while the laser pulse of laser instrument generation passes through transmitter-telescope directive artificial satellite, from the transmitting light path of laser pulse, get fraction of laser light by photoelectric probe, constant proportion time discriminator and form main wave impulse; When receiving telescope receives the reflects laser of artificial satellite, by single-photon avalanche diode, this reflects laser is converted to electric pulse, then by interface card by this electric pulse shaping thus formed echo-pulse; In above process, the moment of the main wave impulse of event timer record as the main ripple moment, record echo-pulse moment as the echo moment, then data acquisition computer was found range according to the main ripple moment of recording in event timer and echo moment.
As shown in Figure 4, above-mentioned range gate circuit board comprises latch, the first buffer, local clock, comparer and the second buffer; Wherein, described latch is connected with described first impact damper, described local clock; Described comparer is connected with described local clock, the second impact damper; Described first impact damper, described second impact damper are connected with described range finding computer for controlling.
Particularly, Xilinx Spartan3 Series FPGA (Field Programmable Gate Array, field programmable gate array) device can be adopted as the core devices of this range gate circuit board.This range gate circuit board internal main will realize three zones, is the foundation of local clock respectively, the gate moment compares output, main ripple latches output epoch.Particularly, it is 5ns that local clock sets up resolution by the 1PPS signal that receives and 10MHz signal, is less than the local clock of 30us with UTC timing tracking accuracy; When there being main ripple signal to arrive, then clock value now being latched and send into buffer memory, being periodically sent to computing machine by parallel port; Periodically receive the range gate forecast moment and laser ignition moment that issue from computing machine, these moment and present clock are compared, if equal, output pulse signal is to C-SPAD or laser instrument, wherein, described first impact damper, described second impact damper are connected with described range finding computer for controlling by parallel port, thus the data realized between range gate circuit board and range finding computer for controlling are transmitted.
The utility model is by introducing SLR field by the laser instrument of higher laser repetition rate and technology thereof, adopt event timer record main ripple moment and echo moment, and mate according to Satellite Orbit Prediction, and then acquisition laser time of flight, packing density and the detection probability of success can be substantially increased in the unit interval, during low orbit satellite in detection in high rail satellite and ground shadow, reveals great advantage relative to traditional SLR technique table.
Above embodiment is only for illustration of the utility model; and be not limitation of the utility model; the those of ordinary skill of relevant technical field; when not departing from spirit and scope of the present utility model; can also make a variety of changes and modification; therefore all equivalent technical schemes also belong to category of the present utility model, and scope of patent protection of the present utility model should be defined by the claims.
Claims (5)
1. a satellite laser ranging system, it is characterized in that, comprise range finding computer for controlling, laser instrument, transmitter-telescope, receiving telescope, data acquisition computer, event timer, range gate circuit board, artificial satellite track sight and single-photon avalanche diode;
The forecast position of the real-time calculating artificial satellite of described range finding computer for controlling under survey station coordinate system and obtain guidance information according to described forecast position, and periodically calculate laser ignition moment and range gate forecast moment;
Described artificial satellite track sight is connected with described range finding computer for controlling, transmitter-telescope, receiving telescope, and described artificial satellite track sight controls described transmitter-telescope according to described guidance information and the rotation of described artificial satellite followed by receiving telescope;
Described range gate circuit board is connected with described range finding computer for controlling, laser instrument, single-photon avalanche diode, described range gate circuit board controls the igniting of described laser instrument according to the described laser ignition moment, and controls the enable of described single-photon avalanche diode according to the described range gate forecast moment;
Described laser instrument is connected with described transmitter-telescope, the laser pulse produced at described laser instrument by artificial satellite described in described transmitter-telescope directive while, from the transmitting light path of described laser pulse, get fraction of laser light and form main wave impulse;
Described single-photon avalanche diode is connected with described receiving telescope, and the reflects laser of the described artificial satellite that described receiving telescope receives by described single-photon avalanche diode is converted to electric pulse, forms echo-pulse after described electric pulse shaping;
The moment of main wave impulse described in described event timer record, as the main ripple moment, records the moment of described echo-pulse as the echo moment;
Described data acquisition computer is connected with described event timer, and described data acquisition computer was found range according to the main ripple moment of described event timer record and echo moment.
2. satellite laser ranging system according to claim 1, is characterized in that, described range gate circuit board comprises latch, the first buffer, local clock, comparer and the second buffer;
Described latch is connected with described first impact damper, described local clock;
Described comparer is connected with described local clock, the second impact damper;
Described first impact damper, described second impact damper are connected with described range finding computer for controlling.
3. satellite laser ranging system according to claim 2, is characterized in that, described first impact damper, described second impact damper are connected with described range finding computer for controlling by parallel port.
4. satellite laser ranging system according to claim 1, it is characterized in that, also comprise Time And Frequency benchmark generator, for providing time reference and frequency reference for described satellite laser ranging system, described Time And Frequency benchmark generator comprises GPS Timing Receiver, pulsqe distributor and frequency divider, described pulsqe distributor is connected with described GPS Timing Receiver, and described frequency divider is connected with described GPS Timing Receiver.
5. satellite laser ranging system according to claim 1, is characterized in that, the repetition frequency of described laser instrument Emission Lasers is 2KHz.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420802041.8U CN204374411U (en) | 2014-12-16 | 2014-12-16 | Satellite laser ranging system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420802041.8U CN204374411U (en) | 2014-12-16 | 2014-12-16 | Satellite laser ranging system |
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| CN204374411U true CN204374411U (en) | 2015-06-03 |
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| CN201420802041.8U Expired - Fee Related CN204374411U (en) | 2014-12-16 | 2014-12-16 | Satellite laser ranging system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106990516A (en) * | 2017-05-26 | 2017-07-28 | 上海微小卫星工程中心 | Satellite-borne laser communication wide-angle pointing device |
| CN107015234A (en) * | 2017-05-19 | 2017-08-04 | 中国科学院国家天文台长春人造卫星观测站 | Embedded satellite laser ranging control system |
| CN104535992B (en) * | 2014-12-16 | 2017-12-01 | 中国测绘科学研究院 | Satellite laser ranging system |
| CN108931778A (en) * | 2017-05-27 | 2018-12-04 | 艾普瑞(上海)精密光电有限公司 | A kind of coaxial range-finding telescope and its distance measuring method |
| CN111505658A (en) * | 2020-04-16 | 2020-08-07 | 中国科学院上海天文台 | Pulse group type laser ranging method with adjustable repetition frequency |
-
2014
- 2014-12-16 CN CN201420802041.8U patent/CN204374411U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104535992B (en) * | 2014-12-16 | 2017-12-01 | 中国测绘科学研究院 | Satellite laser ranging system |
| CN107015234A (en) * | 2017-05-19 | 2017-08-04 | 中国科学院国家天文台长春人造卫星观测站 | Embedded satellite laser ranging control system |
| CN107015234B (en) * | 2017-05-19 | 2019-08-09 | 中国科学院国家天文台长春人造卫星观测站 | Embedded satellite laser ranging control system |
| CN106990516A (en) * | 2017-05-26 | 2017-07-28 | 上海微小卫星工程中心 | Satellite-borne laser communication wide-angle pointing device |
| CN106990516B (en) * | 2017-05-26 | 2020-10-02 | 上海微小卫星工程中心 | Satellite-borne laser communication wide-angle pointing device |
| CN108931778A (en) * | 2017-05-27 | 2018-12-04 | 艾普瑞(上海)精密光电有限公司 | A kind of coaxial range-finding telescope and its distance measuring method |
| CN111505658A (en) * | 2020-04-16 | 2020-08-07 | 中国科学院上海天文台 | Pulse group type laser ranging method with adjustable repetition frequency |
| CN111505658B (en) * | 2020-04-16 | 2023-04-07 | 中国科学院上海天文台 | Pulse group type laser ranging method with adjustable repetition frequency |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150603 Termination date: 20161216 |
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| CF01 | Termination of patent right due to non-payment of annual fee |