CN102156303A - Miniature helium optical pump magnetometer applicable to small-sized aircraft - Google Patents
Miniature helium optical pump magnetometer applicable to small-sized aircraft Download PDFInfo
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- CN102156303A CN102156303A CN 201110070637 CN201110070637A CN102156303A CN 102156303 A CN102156303 A CN 102156303A CN 201110070637 CN201110070637 CN 201110070637 CN 201110070637 A CN201110070637 A CN 201110070637A CN 102156303 A CN102156303 A CN 102156303A
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Abstract
The invention relates to a miniature helium optical pump magnetometer applicable to a small-sized aircraft, comprising a mainframe, a helium optical pump probe A and a helium optical pump probe B, wherein a motherboard, a helium optical pump magnetometer circuit, a GPS (Global Positioning System) board and a switching power supply module are arranged in the mainframe; the motherboard is respectively connected with the helium optical pump magnetometer circuit, the GPS board, a serial port A, a serial port B and a serial port C; the helium optical pump magnetometer circuit is connected with the helium optical pump probe A by an interface of the helium optical pump probe A and connected with the helium optical pump probe B by an interface of the helium optical pump probe B; an input end of the switching power supply module is connected with a power supply input interface by a power supply switch; and an output end of the switching power supply module is respectively connected with the motherboard, the GPS board and the helium optical pump magnetometer circuit. The miniature helium optical pump magnetometer provided by the invention has the advantages of small volume, light weight, low power consumption, and capabilities of automatically collecting multiple data in an unmanned way and replacing an optical pumping magnetometer, a magnetic compensating instrument and an aviation comprehensive data collecting system in the traditional aeromagnetic survey system.
Description
Technical field
Aviation magnetic method prospecting technical field of the present invention mainly is a kind of mini helium light pump magnetic apparatus that is applicable to small aircraft.
Background technology
In mineral products and petroleum exploration field, use optically pumped magnetometer to carry out the prospecting of aviation magnetic method widely.Carrying out aviation magnetic method when prospecting in the prior art, all be to adopt relatively large fixed wing aircraft such as Y-12 to carry out airborne survey, the strictness of Y-12 aircraft is subjected to civil aviation, military control, flight needs confirmation request, the loaded down with trivial details strictness of formality, and the pilot needs special aviation driving school to cultivate for many years, uses the navigate cost of magnetic prospecting of this type of aircraft also higher.Continuous development along with the unmanned plane technology, as the unmanned flying platform in the aviation aircraft series with it in advantages such as security, high maneuverability and low costs, application is more and more widely arranged in fields such as military surveillance, aeroplane photography, remote sensing monitoring and public safeties.Use small aircraft such as unmanned plane to compare relatively large fixed wing aircraft such as Y-12 as the platform of magnetic airborne surveys very big advantage will be arranged.
The employed magnetic airborne surveys of existing large-scale fixed wing aircraft system generally is made up of necessary instruments such as optically pumped magnetometer gradometer, magnetic compensation instrument, aviation integrated data acceptance system and altitude gauges, it is all bigger that the whole system volume is not less than 500mm length * 500mm wide * 300mm height, weight are not less than 30kg, power consumption is not less than 200W, and need manually-operated, can't satisfy the installation requirement of unmanned plane platform, people press for little, in light weight, low in energy consumption, the unattended high precision magnetic method of the volume survey system that small aircraft such as a suitable unmanned plane is installed.
Summary of the invention
Purpose of the present invention will overcome the deficiency of above-mentioned technology just, and a kind of mini helium light pump magnetic apparatus that is applicable to small aircraft is provided.
The present invention solves the technical scheme that its technical matters adopts: this mini helium light pump magnetic apparatus that is applicable to small aircraft, it comprises main frame, helium optical pumping probe A, helium optical pumping probe B, be provided with a mainboard in the described main frame, the helium light pump magnetic apparatus circuit, GPS plate and switch power module, mainboard respectively with the helium light pump magnetic apparatus circuit, the GPS plate, serial port A, serial port B is connected with serial port C, the GPS plate is connected with gps antenna by the gps antenna interface, the helium light pump magnetic apparatus circuit is connected with helium optical pumping probe A by helium optical pumping probe A interface, and the helium light pump magnetic apparatus circuit is connected with helium optical pumping probe B by helium optical pumping probe B interface; The input end of switch power module is connected with power input interface by power switch, and power input interface is connected with the lithium polymer battery group, and the output terminal of switch power module is connected with mainboard, GPS plate and helium light pump magnetic apparatus circuit respectively.
As preferably, be provided with display control device, mainboard is connected with display control device by VGA interface, USB interface A, PS/2 keyboard interface, is connected with storer by USB interface B.
Described mainboard is connected with the three-component flux-gate magnetometer by serial port A, is connected with altitude gauge by serial port B, is connected with data radio station by serial port C; Altitude gauge is connected with the radar altimeter antenna, and data radio station is connected with the data radio station antenna.
Main frame can be installed a helium optical pumping probe geomagnetic total field metering system or two helium optical pumping probe geomagnetic total field gradiometry modes as required, can connect three-component flux-gate magnetometer, altitude gauge by serial port, can be when having people's aircraft platform to use by connecting display control device demonstration information needed and main frame being controlled, system can work or by the data chainning interface it be monitored automatically when the unmanned vehicle platform uses.
Main frame of the present invention is built-in with the efficient switch power module, can adapt to multiple direct supply input such as lead-acid batteries, lithium polymer battery group, onboard generators, Overall Power Consumption is no more than 25W when using single helium optical pumping to pop one's head in, and the general power consumption of existing magnetic airborne surveys system is more than 100W.
Main frame of the present invention is built-in aircraft magnetic interference compensation software can be measured attitude of flight vehicle by external three-component flux-gate magnetometer, and the magnetic interference that causes because of attitude of flight vehicle during helium light pump magnetic apparatus is measured compensates, thereby guarantees data precision.
Magnetic method that main frame of the present invention is built-in prospecting software, the plan survey line can be set as required, the vectored flight device is along the flight of plan survey line, gather in real time and storage geomagnetic total field data, earth magnetism three-component data, altitude data, GPS locator data and time data, and the data radio station interface is provided, can selectively packing data be sent to land station by data radio station.
Main frame of the present invention is integrated with helium light pump magnetic apparatus, GPS and data acquisition system (DAS) height, all hardware is installed in the aluminium alloy compartment of a sealing, all connectors adopt watertight connector to guarantee reliably use in the moist salt mist environment in low latitude, ocean, the main frame volume is not more than 300mm length * 300mm wide * 200mm height, the about 2kg of main frame weight, the about 0.8kg of each helium optical pumping probe weight can adapt to the load-carrying ability of small aircrafts such as unmanned plane fully.
In the fixed-wing unmanned plane, main frame, altitude gauge, data radio station, lithium polymer battery group are installed in the position of ventral inside away from aircraft engine, helium optical pumping probe A and helium optical pumping probe B are installed in two wing tips respectively, the three-component flux-gate magnetometer is installed in the aircraft front end, the radar altimeter antenna is installed in ventral, the data radio station antenna is installed in head upper, and gps antenna is installed in the fuselage top.
In rotor wing unmanned aerial vehicle, main frame, altitude gauge, data radio station, lithium polymer battery group are installed in the hanger of ventral below, the ventral lower horizontal crosses out two carbon fiber bars, helium optical pumping probe A and helium optical pumping probe B are installed in the top of carbon fiber bar respectively, the three-component flux-gate magnetometer is installed in below, aircraft foot piece middle part, gps antenna is installed in top, aircraft foot piece middle part, and the radar altimeter antenna is installed in the hanger below of ventral, and the data radio station antenna is installed in foot piece afterbody below.
In the power dalta wing, main frame, altitude gauge, data radio station, lithium polymer battery group are installed in the instrument container, instrument container is installed on the Passenger On Board seat, display control device is installed in built in instrusment plate below, head level forward stretches out a carbon fiber pipe, helium optical pumping probe A is installed in the carbon fiber pipe top, the three-component flux-gate magnetometer is installed in the inside of carbon fiber pipe apart from 1 meter of head, gps antenna is installed in carbon fiber pipe inside apart from 0.5 meter of head, and radar altimeter antenna and data radio station antenna are installed in the ventral below.
The effect that the present invention is useful is: the invention provides the mini helium light pump magnetic apparatus that is applicable to small aircrafts such as unmanned plane, but little, in light weight, the low in energy consumption unmanned of its volume is gathered several data automatically, can replace optically pumped magnetometer, magnetic compensation instrument and aviation integrated data acceptance system in the existing magnetic airborne surveys system.
Description of drawings
The mini helium light pump magnetic apparatus theory diagram of Fig. 1;
Fig. 2 main machine structure synoptic diagram;
The system chart that Fig. 3 typical case uses;
Fig. 4 fixed-wing unmanned plane platform application scheme of installation;
Fig. 5 rotor wing unmanned aerial vehicle platform application scheme of installation;
Fig. 6 power dalta wing platform application scheme of installation.
Description of reference numerals: aluminum alloy casing 1, mainboard 2, helium light pump magnetic apparatus circuit 3, GPS plate 4, switch power module 5, power switch 6, serial port A-7, serial port B-8, serial port C-9, VGA interface 10, USB interface A-11, USB interface B-12, PS/2 keyboard interface-13, power input interface-14, helium optical pumping probe A-15, helium optical pumping probe B-16, gps antenna interface 17, three-component flux-gate magnetometer 18, altitude gauge 19, data radio station 20, main frame 21, gps antenna 22, lithium polymer battery group 23, carbon fiber bar 24, carbon fiber pipe 25, radar altimeter antenna 26, data radio station antenna 27, display control device 28, helium optical pumping probe A interface-29, helium optical pumping probe B interface-30, instrument container 31.
Embodiment
The invention will be further described below in conjunction with drawings and Examples:
As shown in the figure, this mini helium light pump magnetic apparatus that is applicable to small aircraft, it comprises main frame 21, helium optical pumping probe A 15, helium optical pumping probe B 16, be provided with a mainboard 2, display control device 28, helium light pump magnetic apparatus circuit 3, GPS plate 4 and switch power module 5 in the described main frame 21, mainboard 2 is connected with helium light pump magnetic apparatus circuit 3, GPS plate 4, serial port A7, serial port B8 and serial port C9 respectively, mainboard 2 is connected with display control device 28 by VGA interface 10, USB interface A11, PS/2 keyboard interface 13, is connected with storer by USB interface B12.GPS plate 4 is connected with gps antenna 22 by gps antenna interface 17, helium light pump magnetic apparatus circuit 3 is connected with helium optical pumping probe A 15 by helium optical pumping probe A interface 29, and helium light pump magnetic apparatus circuit 3 is connected with helium optical pumping probe B 16 by helium optical pumping probe B interface 30; The input end of switch power module 5 is connected with power input interface 14 by power switch 6, power input interface 14 is connected with lithium polymer battery group 23, and the output terminal of switch power module 5 is connected with mainboard 2, GPS plate 4 and helium light pump magnetic apparatus circuit 3 respectively.
Described mainboard 2 is connected with three-component flux-gate magnetometer 18 by serial port A7, is connected with altitude gauge 19 by serial port B8, is connected with data radio station 20 by serial port C9; Altitude gauge 19 is connected with radar altimeter antenna 26, and data radio station 20 is connected with data radio station antenna 27.
PC104 mainboard 2 among the present invention preferably grinds the EC3-1641 type PC104 industrial computer mainboard of auspicious science and technology, the OEM4-G2L of GPS plate 4 preferred Novatel companies, also can use other any plane precision to be better than 2m, the data output frequency is greater than the GPS plate of 5Hz, the S67-1575-39 of gps antenna 22 preferred Novatel companies.The DFM28G type three-component flux-gate magnetometer of three-component flux-gate magnetometer 18 preferred Billingsley companies, also can select for use other to have serial port output and survey magnetic sensitivity to be better than 0.5nT, three quadrature degree are better than 0.5 ° small-sized three-component flux-gate magnetometer.Altitude gauge 19 can use and have serial port output and survey high range greater than 500m, and resolution is better than the miniradar altitude gauge of 0.2m.20 preferred days smart ND250A wireless digital broadcasting stations of data radio station also can be selected the micro radio data radio station of other terrestrial transmission sighting distances greater than 2km for use.
As shown in Figure 4, in the fixed-wing unmanned plane, main frame 21, altitude gauge 19, data radio station 20, lithium polymer battery group 23 are installed in the position of ventral inside away from aircraft engine, helium optical pumping probe A 15 and helium optical pumping probe B 16 are installed in two wing tips respectively, three-component flux-gate magnetometer 18 is installed in the aircraft front end, radar altimeter antenna 26 is installed in ventral, and data radio station antenna 27 is installed in head upper, and gps antenna 22 is installed in the fuselage top.
As shown in Figure 5, in rotor wing unmanned aerial vehicle, main frame 21, altitude gauge 19, data radio station 20, lithium polymer battery group 23 are installed in the hanger of ventral below, the ventral lower horizontal crosses out the long carbon fiber bar 24 of two 3m, helium optical pumping probe A 15 and helium optical pumping probe B 16 are installed in the top of carbon fiber bar 24 respectively, three-component flux-gate magnetometer 18 is installed in below, aircraft foot piece middle part, gps antenna 22 is installed in top, aircraft foot piece middle part, radar altimeter antenna 26 is installed in the hanger below of ventral, and data radio station antenna 27 is installed in foot piece afterbody below.
As shown in Figure 6, in the power dalta wing, main frame 21, altitude gauge 19, data radio station 20, lithium polymer battery group 23 is installed in the instrument container 31, instrument container is installed on the Passenger On Board seat, display control device 28 is installed in built in instrusment plate below, head level forward stretches out the carbon fiber pipe 25 of a 2.5m length, helium optical pumping probe A 15 is installed in carbon fiber pipe 25 tops, three-component flux-gate magnetometer 18 is installed in the inside of carbon fiber pipe 25 apart from 1 meter of head, gps antenna 22 is installed in carbon fiber pipe 25 inside apart from 0.5 meter of head, and radar altimeter antenna 26 and data radio station antenna 27 are installed in the ventral below.
In addition to the implementation, all employings are equal to the technical scheme of replacement or equivalent transformation formation, all drop on the protection domain of requirement of the present invention.
Claims (6)
1. mini helium light pump magnetic apparatus that is applicable to small aircraft, it comprises main frame (21), helium optical pumping probe A (15), helium optical pumping probe B (16), it is characterized in that: be provided with a mainboard (2) in the described main frame (21), helium light pump magnetic apparatus circuit (3), GPS plate (4) and switch power module (5), mainboard (2) respectively with helium light pump magnetic apparatus circuit (3), GPS plate (4), serial port A(7), serial port B(8) with serial port C(9) be connected, GPS plate (4) is connected with gps antenna (22) by gps antenna interface (17), helium light pump magnetic apparatus circuit (3) is connected with helium optical pumping probe A (15) by helium optical pumping probe A interface (29), and helium light pump magnetic apparatus circuit (3) is connected with helium optical pumping probe B (16) by helium optical pumping probe B interface (30); The input end of switch power module (5) is connected with power input interface (14) by power switch (6), power input interface (14) is connected with lithium polymer battery group (23), and the output terminal of switch power module (5) is connected with mainboard (2), GPS plate (4) and helium light pump magnetic apparatus circuit (3) respectively.
2. the mini helium light pump magnetic apparatus that is applicable to small aircraft according to claim 1, it is characterized in that: be provided with display control device (28), mainboard (2) is by VGA interface (10), USB interface A(11), PS/2 keyboard interface (13) is connected with display control device (28), by USB interface B(12) be connected with storer.
3. the mini helium light pump magnetic apparatus that is applicable to small aircraft according to claim 1, it is characterized in that: described mainboard (2) is by serial port A(7) be connected with three-component flux-gate magnetometer (18), by serial port B(8) be connected with altitude gauge (19), by serial port C(9) be connected with data radio station (20); Altitude gauge (19) is connected with radar altimeter antenna (26), and data radio station (20) is connected with data radio station antenna (27).
4. the mini helium light pump magnetic apparatus that is applicable to small aircraft according to claim 1, it is characterized in that: in the fixed-wing unmanned plane, main frame (21), altitude gauge (19), data radio station (20), lithium polymer battery group (23) is installed in the position of ventral inside away from aircraft engine, helium optical pumping probe A (15) and helium optical pumping probe B (16) are installed in two wing tips respectively, three-component flux-gate magnetometer (18) is installed in the aircraft front end, radar altimeter antenna (26) is installed in ventral, data radio station antenna (27) is installed in head upper, and gps antenna (22) is installed in the fuselage top.
5. the mini helium light pump magnetic apparatus that is applicable to small aircraft according to claim 1, it is characterized in that: in rotor wing unmanned aerial vehicle, main frame (21), altitude gauge (19), data radio station (20), lithium polymer battery group (23) is installed in the hanger of ventral below, the ventral lower horizontal crosses out two carbon fiber bars (24), helium optical pumping probe A (15) and helium optical pumping probe B (16) are installed in the top of carbon fiber bar (24) respectively, three-component flux-gate magnetometer (18) is installed in below, aircraft foot piece middle part, gps antenna (22) is installed in top, aircraft foot piece middle part, radar altimeter antenna (26) is installed in the hanger below of ventral, and data radio station antenna (27) is installed in foot piece afterbody below.
6. the mini helium light pump magnetic apparatus that is applicable to small aircraft according to claim 1, it is characterized in that: in the power dalta wing, main frame (21), altitude gauge (19), data radio station (20), lithium polymer battery group (23) is installed in the instrument container (31), instrument container (31) is installed on the Passenger On Board seat, display control device (28) is installed in built in instrusment plate below, head level forward stretches out a carbon fiber pipe (25), helium optical pumping probe A (15) is installed in carbon fiber pipe (25) top, three-component flux-gate magnetometer (18) is installed in the inside of carbon fiber pipe (25) apart from 1 meter of head, it is inner apart from 0.5 meter of head that gps antenna (22) is installed in carbon fiber pipe (25), and radar altimeter antenna (26) and data radio station antenna (27) are installed in the ventral below.
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| CN 201110070637 CN102156303A (en) | 2011-03-23 | 2011-03-23 | Miniature helium optical pump magnetometer applicable to small-sized aircraft |
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| CN 201110070637 CN102156303A (en) | 2011-03-23 | 2011-03-23 | Miniature helium optical pump magnetometer applicable to small-sized aircraft |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102520455A (en) * | 2011-12-14 | 2012-06-27 | 吉林大学 | Aviation geomagnetic vector detection apparatus |
| CN102854537A (en) * | 2012-09-13 | 2013-01-02 | 成都理工大学 | Digital quick tracking helium optical pumping magnetometer |
| CN103424780A (en) * | 2013-08-27 | 2013-12-04 | 中国航空无线电电子研究所 | Aircraft magnetic environment compensation method based on induction coils |
| CN103852737A (en) * | 2014-03-14 | 2014-06-11 | 武汉理工大学 | Optimized cesium-light-pump weak magnetic detection device |
| CN103941297A (en) * | 2014-04-21 | 2014-07-23 | 中国科学院地质与地球物理研究所 | Aeromagnetic measuring device and method based on fixed-wing unmanned aerial vehicle |
| CN104122597A (en) * | 2013-08-22 | 2014-10-29 | 中国科学院遥感与数字地球研究所 | Unmanned aerial vehicle aeromagnetic detecting system and method |
| CN104730589A (en) * | 2015-03-30 | 2015-06-24 | 上海海事大学 | Aeromagnetic measuring data collection system and device |
| CN107045150A (en) * | 2016-12-20 | 2017-08-15 | 中国船舶重工集团公司第七〇五研究所 | A kind of multi-rotor unmanned aerial vehicle helium optical pumping magnetic airborne survey system |
| CN108802839A (en) * | 2018-06-08 | 2018-11-13 | 北京桔灯地球物理勘探股份有限公司 | Caesium optical pumping magnetic survey method based on fixed-wing unmanned plane |
| CN112550706A (en) * | 2020-12-09 | 2021-03-26 | 中国地质科学院地球物理地球化学勘查研究所 | Multipurpose unmanned aerial vehicle aeromagnetic probe rod |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6588701B2 (en) * | 2000-09-26 | 2003-07-08 | Rafael Armament Development Authority, Ltd. | Unmanned mobile device |
| CN101044416A (en) * | 2004-10-08 | 2007-09-26 | 菲格鲁空中勘测公司 | Unmanned airborne vehicle for geophysical surveying |
| CN201698036U (en) * | 2009-11-05 | 2011-01-05 | 中国船舶重工集团公司第七一五研究所 | Portable magnetometer |
| CN202003038U (en) * | 2011-03-23 | 2011-10-05 | 中国船舶重工集团公司第七一五研究所 | Mini-helium optically-pumped magnetometer suitable for miniature aircrafts |
-
2011
- 2011-03-23 CN CN 201110070637 patent/CN102156303A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6588701B2 (en) * | 2000-09-26 | 2003-07-08 | Rafael Armament Development Authority, Ltd. | Unmanned mobile device |
| CN101044416A (en) * | 2004-10-08 | 2007-09-26 | 菲格鲁空中勘测公司 | Unmanned airborne vehicle for geophysical surveying |
| CN201698036U (en) * | 2009-11-05 | 2011-01-05 | 中国船舶重工集团公司第七一五研究所 | Portable magnetometer |
| CN202003038U (en) * | 2011-03-23 | 2011-10-05 | 中国船舶重工集团公司第七一五研究所 | Mini-helium optically-pumped magnetometer suitable for miniature aircrafts |
Non-Patent Citations (1)
| Title |
|---|
| 《物探与化探》 20101231 王庆乙等 MAMSS-1超低空高精度航磁系统的研制 712-716 6 第34卷, 第6期 * |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102520455B (en) * | 2011-12-14 | 2013-08-07 | 吉林大学 | Aviation geomagnetic vector detection apparatus |
| CN102520455A (en) * | 2011-12-14 | 2012-06-27 | 吉林大学 | Aviation geomagnetic vector detection apparatus |
| CN102854537A (en) * | 2012-09-13 | 2013-01-02 | 成都理工大学 | Digital quick tracking helium optical pumping magnetometer |
| CN102854537B (en) * | 2012-09-13 | 2015-12-16 | 成都理工大学 | A kind of digital quick tracking helium light pump magnetic apparatus |
| CN104122597A (en) * | 2013-08-22 | 2014-10-29 | 中国科学院遥感与数字地球研究所 | Unmanned aerial vehicle aeromagnetic detecting system and method |
| CN103424780A (en) * | 2013-08-27 | 2013-12-04 | 中国航空无线电电子研究所 | Aircraft magnetic environment compensation method based on induction coils |
| CN103424780B (en) * | 2013-08-27 | 2016-05-18 | 中国航空无线电电子研究所 | Carrier aircraft magnetic environment compensation method based on induction coil |
| CN103852737A (en) * | 2014-03-14 | 2014-06-11 | 武汉理工大学 | Optimized cesium-light-pump weak magnetic detection device |
| CN103941297A (en) * | 2014-04-21 | 2014-07-23 | 中国科学院地质与地球物理研究所 | Aeromagnetic measuring device and method based on fixed-wing unmanned aerial vehicle |
| CN104730589A (en) * | 2015-03-30 | 2015-06-24 | 上海海事大学 | Aeromagnetic measuring data collection system and device |
| CN104730589B (en) * | 2015-03-30 | 2017-12-05 | 上海海事大学 | A kind of magnetic airborne survey data collecting system and device |
| CN107045150A (en) * | 2016-12-20 | 2017-08-15 | 中国船舶重工集团公司第七〇五研究所 | A kind of multi-rotor unmanned aerial vehicle helium optical pumping magnetic airborne survey system |
| CN108802839A (en) * | 2018-06-08 | 2018-11-13 | 北京桔灯地球物理勘探股份有限公司 | Caesium optical pumping magnetic survey method based on fixed-wing unmanned plane |
| CN112550706A (en) * | 2020-12-09 | 2021-03-26 | 中国地质科学院地球物理地球化学勘查研究所 | Multipurpose unmanned aerial vehicle aeromagnetic probe rod |
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Application publication date: 20110817 |