CN211376939U - Motion mechanism of satellite-borne SAR radar Ka-band antenna - Google Patents
Motion mechanism of satellite-borne SAR radar Ka-band antenna Download PDFInfo
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- CN211376939U CN211376939U CN202020250968.0U CN202020250968U CN211376939U CN 211376939 U CN211376939 U CN 211376939U CN 202020250968 U CN202020250968 U CN 202020250968U CN 211376939 U CN211376939 U CN 211376939U
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Abstract
The utility model discloses a motion mechanism of a satellite-borne SAR radar Ka-band antenna, wherein the lower parts of a first support leg and a second support leg are hinged on a rotating shaft, and the upper ends of the first support leg and the second support leg are symmetrically fixed on a frustum-shaped outer side wall of a shell of a Ka-band antenna rectifier; the bottom surfaces of the third and fourth support legs are vertically and symmetrically fixed at the periphery of the upper end surface of the rotary table, the rotating motor is connected at the center of the lower end surface of the rotary table, the rotating shaft is transversely connected between the upper parts of the third and fourth support legs and can rotate, and the pitching motor is connected at the end part of the rotating shaft; the first gear is coaxially sleeved in the middle of the rotating shaft, the second gear is semicircular and fixed at the bottom of the tail shell of the Ka-band antenna rectifier, and the first gear is meshed with the second gear; because the semicircular second gear is meshed with the first gear coaxially connected with the pitching motor, the turntable coaxially connected with the rotating motor and the four support leg structures on the turntable are combined, the accurate azimuth pointing and the accuracy compensation of the Ka-band antenna are realized, and the structure is simple, stable and reliable.
Description
Technical Field
The utility model relates to a satellite-borne SAR radar Ka wave band antenna field especially relates to a motion of satellite-borne SAR radar Ka wave band antenna.
Background
With the development of the space technology, a space deployable antenna with light weight, high storage rate and high reliability has become an important research field of aerospace science and technology, and the research on the basic problems of the structural innovative design of the deployable antenna, feasibility verification analysis and the like is important content of the space deployable antenna.
Aiming at an S-band SAR running in an earth 800Km orbit and with a satellite orbit inclination angle of 20-50 degrees, in order to meet the requirement that the diameter size of a satellite accommodating bin of a carrier rocket is smaller than 4m, folding and storing design needs to be carried out on each antenna module of the satellite, and the pointing accuracy of the pitching directions of a C-band antenna, an S-band antenna and a Ku-band antenna of the SAR is also guaranteed.
As shown in fig. 1 and fig. 2, fig. 1 is a perspective view of one side of the satellite embodiment loaded with the SAR radar Ka-band antenna of the present invention, fig. 2 is a perspective view of the other side of the satellite embodiment loaded with the SAR radar Ka-band antenna of the present invention, in order to more clearly show the composition of the satellite embodiment loaded with the SAR radar Ka-band antenna, fig. 1 and fig. 2 show that the solar cell panels in the expansion state at both sides of the satellite loaded with the SAR radar Ka-band antenna are all cut off; the solar cell panels 120 with the length of 11.5m and the width of 2m after being unfolded are symmetrically arranged at two sides of the rear half section of the satellite body 110, and the solar cell panel folding bin cover plates 121 are symmetrically arranged on the side wall of the satellite body 110 where the solar cell panels 120 are located; the head of the satellite body 110 is an SAR radar C-band antenna 210; the satellite orbital transfer hydrazine fuel propulsion system 130 and a propulsion tail pipe 131 thereof are positioned at the tail part of the satellite body 110; nitrogen attitude control systems 140 are symmetrically arranged on both sides of the rear end and the front end of the satellite body 110 respectively; the storage tanks 150 (of nitrogen, hydrazine fuel and hydrazine fuel combustion improver) are all positioned in the rear half section of the satellite body 110 and positioned between the nitrogen attitude control system 140 at the rear end of the satellite body 110 and the solar cell panel 120; an interferometer 220 and a Ka-band 1500mm parabolic antenna (Ka-band antenna for short, the same below) 230 with a pitching angle of +/-20 degrees are arranged on the side wall of one side of the middle part of the satellite body 110; an S-band 700mm parabolic antenna (called S-band antenna for short, the same below) 240 with a pitch angle of +20 degrees/15 degrees, a laser reflector 250 and a satellite Doppler orbit determination positioning system 260 are all positioned on the side wall of the other side of the middle part of the satellite body 110; the SAR service system 270 is arranged in the front half section of the satellite body 110, and the SAR service system 270 is located between the SAR radar C-band antenna 210 and the SAR radar S-band antenna 240; a microwave radiometer 280 is arranged on the side wall of the satellite body 110 where the SAR service system 270 is located; the sidewall of the rear portion of the satellite body 110 is further provided with a high-grade track delay tracking radiometer 290, and the high-grade track delay tracking radiometer 290 is located between the storage tank 150 (of nitrogen, hydrazine fuel and hydrazine fuel combustion improver) and the solar cell panel 120.
Due to the particularity of the space environment where the space-borne SAR is located and the severe environment conditions, the requirements for long service life, high reliability, small size, light weight, small gap between antenna array panels, flatness and thermal deformation are required, the requirements for thermal design, radiation resistance, electromagnetic compatibility design, unfolding and locking of an antenna mechanism and the like are all strict, and a series of structural key technologies need to be solved.
Therefore, there is still a need for improvement and development of the prior art.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model provides a motion of satellite-borne SAR radar Ka wave band antenna can realize Ka wave band antenna's accurate azimuth and precision compensation, and simple structure, reliable and stable.
The technical scheme of the utility model as follows: a movement mechanism of a satellite-borne SAR radar Ka-band antenna comprises a rotating motor, a rotary table, a first supporting leg, a second supporting leg, a third supporting leg, a fourth supporting leg, a pitching motor, a rotating shaft, a first gear and a second gear; wherein,
a motor shaft of the rotating motor is connected to the center of the lower end face of the rotary table and used for driving the rotary table to rotate around the axis line of the rotary table, and further the rotating angle of the Ka-band antenna is adjusted;
the bottom surfaces of the third supporting leg and the fourth supporting leg are vertically and symmetrically fixed at the periphery of the upper end surface of the rotary table, the rotary shaft is transversely connected between the upper parts of the third supporting leg and the fourth supporting leg through corresponding bearings and can rotate, and the pitching motor is connected to the end part of the rotary shaft and is used for driving the rotary shaft to rotate around the axis line of the rotary shaft;
the lower parts of the first supporting leg and the second supporting leg are hinged to the rotating shaft through corresponding bearings, the first supporting leg and the second supporting leg are located on the inner sides of the third supporting leg and the fourth supporting leg, and the upper ends of the first supporting leg and the second supporting leg are symmetrically fixed on the frustum-shaped outer side wall of the shell of the Ka-band antenna rectifier;
the first gear is coaxially sleeved in the middle of the rotating shaft, the second gear is semicircular and is fixed to the bottom of a tail shell of the Ka-band antenna rectifier, and the first gear is meshed with the second gear and is used for driving the second gear to rotate through the rotating shaft and the first gear under the driving of the pitching motor, so that the pitching angle of the Ka-band antenna is accurately adjusted.
The motion mechanism of the satellite-borne SAR radar Ka-band antenna comprises: the middle upper part of the first support leg is provided with a first forked groove, the first forked groove is positioned on the end surface of the first support leg in the thickness direction, the upper end of the first support leg inclines inwards, and the opening of the first forked groove extends to the upper end of the first support leg; symmetrically, the well upper portion of second stabilizer blade is provided with the second bifurcation groove, the second bifurcation groove is located the terminal surface of second stabilizer blade thickness direction, just the inboard slope in upper end of second stabilizer blade, the oral area in second bifurcation groove extends to the upper end of second stabilizer blade.
The motion mechanism of the satellite-borne SAR radar Ka-band antenna comprises: the satellite shell at the Ka-band antenna is sequentially composed of an inner-layer aluminum alloy skin, an inner-layer side skin cell metal rubber mat, an aluminum alloy honeycomb interlayer, an outer-layer side skin cell metal rubber mat and an outer-layer aluminum alloy skin from inside to outside, and the honeycomb cells of the aluminum alloy honeycomb interlayer are filled with silicon aerogel.
The motion mechanism of the satellite-borne SAR radar Ka-band antenna comprises: inner layer aluminum alloy skin and outer aluminum alloy skin all adopt 1.5 mm's 5A06 aluminum alloy skin preparation, inner layer side skin cell metal cushion and outer layer side skin cell metal cushion all adopt 0.3 mm's skin cell metal glue preparation, aluminum alloy honeycomb interlayer adopts 8.0 mm's 5A06 aluminum alloy honeycomb interlayer preparation.
The motion mechanism of the satellite-borne SAR radar Ka-band antenna comprises: a plurality of heat conduction copper pipes are laid in the aluminum alloy honeycomb interlayer at intervals in parallel, and the heat conduction copper pipes are attached to the outer layer side skin cell metal rubber gasket in an attached mode.
The motion mechanism of the satellite-borne SAR radar Ka-band antenna comprises: the heat conduction copper pipe is made of a square copper pipe with the thickness of 0.8mm, the length of 5mm and the width of 5 mm.
The utility model provides a motion of satellite-borne SAR radar Ka wave band antenna, owing to adopted the meshing of semicircular second gear and pitch motor coaxial coupling's first gear mutually, combine the revolving stage of coaxial coupling rotating electrical machines and four stabilizer blade structures on it, realized the directional and precision compensation in accurate position of Ka wave band antenna, and simple structure, reliable and stable.
Drawings
FIG. 1 is a perspective view of one side of an embodiment of the present invention of a satellite carrying a SAR radar Ka-band antenna;
FIG. 2 is a perspective view of the other side of an embodiment of the present invention of a satellite loaded with a SAR radar Ka-band antenna;
FIG. 3 is a partial enlarged view of an embodiment of the present invention satellite loaded with a SAR radar Ka-band antenna;
FIG. 4 is an enlarged perspective view of an embodiment of the Ka-band antenna movement mechanism of the spaceborne SAR radar of the present invention;
FIG. 5 is a schematic diagram of the layer structure of the satellite housing at the Ka-band antenna of the present invention;
summary of the numbers in the figures: satellite body 110, satellite housing 112 (at Ka band antenna 230), solar panel 120, solar panel folding cover plate 121, satellite orbital transfer hydrazine fuel propulsion system 130, propulsion tail pipe 131, nitrogen attitude control system 140, storage tank 150 (of nitrogen, hydrazine fuel oxidizer), SAR radar C-band antenna 210, interferometer 220, Ka band antenna 230, Ka band antenna motion bin 231, metal bellows 232, Ka band antenna rectifier housing 233, tail housing 234, first leg 235a, second leg 235b, first fork slot 235C, second fork slot 235d, third leg 236a, fourth leg 236b, S-band antenna 240, laser reflector 250, satellite doppler orbit determination system 260, SAR service system 270, microwave radiometer 280, advanced orbit delay scanning radiometer 290, pitch motor 610, rotating shaft 620, first gear 630, second gear 640, The device comprises a rotating motor 650, a turntable 660, an inner layer aluminum alloy skin 701, an inner layer side skin cell metal rubber mat 702, an aluminum alloy honeycomb interlayer 703, honeycomb cells 703a, an outer layer side skin cell metal rubber mat 704 and an outer layer aluminum alloy skin 705.
Detailed Description
The following detailed description and examples of the present invention are provided in connection with the accompanying drawings, which are set forth for the purpose of illustration only and are not intended to limit the invention.
Because the SAR radar C-band antenna 210 is a main antenna of the whole satellite for performing satellite tasks, sometimes various tasks need to be performed on different inclination orbits, the satellite body 110 of the satellite-borne SAR radar controls the attitude and the direction of the SAR radar C-band antenna 210 through a nitrogen attitude control system, but the Ka-band antenna 230 is not a phased array antenna and needs to be subjected to azimuth change correction through a motion mechanism, so that the precise azimuth pointing and the precision compensation of the Ka-band antenna 230 are realized.
Therefore, as shown in fig. 3, fig. 3 is an enlarged perspective view of an embodiment of the inventive satellite-borne SAR radar Ka-band antenna movement mechanism, the Ka-band antenna movement mechanism includes a rotating motor 650, a turntable 660, a first leg 235a, a second leg 235b, a third leg 236a, a fourth leg 236b, a pitching motor 610, a rotating shaft 620, a first gear 630 and a second gear 640, wherein a motor shaft of the rotating motor 650 is connected to a center of a lower end face of the turntable 660, and is used for driving the turntable 660 to rotate around its own axial lead, thereby adjusting a rotation angle of the Ka-band antenna 230; the bottom surfaces of the third leg 236a and the fourth leg 236b are vertically and symmetrically fixed at the periphery of the upper end surface of the turntable 660, the rotating shaft 620 is transversely connected between the upper parts of the third leg 236a and the fourth leg 236b through corresponding bearings and can rotate, and the pitching motor 610 is connected to the end part of the rotating shaft 620 and is used for driving the rotating shaft 620 to rotate around the axis line of the rotating shaft 620; the lower parts of the first leg 235a and the second leg 235b are hinged on the rotating shaft 620 via corresponding bearings, the first leg 235a and the second leg 235b are both located at the inner sides of the third leg 236a and the fourth leg 236a, and the upper ends of the first leg 235a and the second leg 235b are symmetrically fixed on the frustum-shaped outer side wall of the Ka-band antenna rectifier casing 233; the first gear 630 is coaxially sleeved in the middle of the rotating shaft 620, the second gear 640 is semicircular and is fixed at the bottom of the tail shell 234 of the shell 233 of the Ka-band antenna rectifier, and the first gear 630 is meshed with the second gear 640 and is used for driving the second gear 640 to rotate through the rotating shaft 620 and the first gear 630 under the driving of the pitching motor 610, so that the pitching angle of the Ka-band antenna 230 is accurately adjusted.
Preferably, all bearings used by the motion mechanism of the Ka-band antenna are ceramic bearings, and the ceramic bearings have the advantages of high strength and small expansion coefficient, and can adapt to a temperature difference environment of-180 ℃/120 ℃ to prevent fit clearance seizure.
Preferably, the first gear 630 and the second gear 640 are both made of titanium alloy materials, and the gear fit clearance is matched with the gear in 4-level precision according to the national standard gear precision grade, so as to reduce the error of the pitching angle of the Ka-band antenna 230.
In the preferred embodiment of the utility model, the middle upper part of the first supporting leg 235a is provided with a first branch groove 235c, the first branch groove 235c is located on the end surface of the first supporting leg 235a in the thickness direction, the upper end of the first supporting leg 235a is inclined to the inner side, and the mouth of the first branch groove 235c extends to the upper end of the first supporting leg 235 a; symmetrically, a second fork groove 235d is arranged at the middle upper part of the second supporting leg 235b, the second fork groove 235d is positioned on the end surface of the second supporting leg 235b in the thickness direction, the upper end of the second supporting leg 235b inclines inwards, and the mouth of the second fork groove 235d extends to the upper end of the second supporting leg 235 b; therefore, the structural rigidity of the first supporting leg 235a and the second supporting leg 235b connected with the shell 233 of the Ka-band antenna rectifier is further improved, and the accuracy and the stability of the pitching angle of the Ka-band antenna 230 are further ensured.
With reference to fig. 4, fig. 4 is the utility model discloses load SAR radar Ka band antenna's satellite embodiment's partial enlargement, be provided with circular sunken Ka band antenna motion storehouse 231 on the satellite body 110 of shown Ka band antenna 230 department, revolving stage 660 is located the center department of Ka band antenna motion storehouse 231 bottom, be provided with thermal-insulated radiation protection's corrugated metal pipe 232 between revolving stage 660 and Ka band antenna rectifier casing 233's tail-shell 234 for protection antenna power and signal control are walked the line, and the in-process protection cable of kaband antenna 230 every single move 20 does not receive the damage to and play the effect of thermal-insulated protection to the cable under the poor condition of space high temperature.
In addition, because the satellite-borne SAR radar needs to bear a huge temperature difference environment of-180 ℃/120 ℃ in a space environment, an outer side protective wall of the satellite-borne SAR radar has enough assembly strength and also has heat conduction and heat insulation functions, in order to solve the problem that the Ka-band antenna 230 is isolated from external high and low temperature differences in the working process of outer space, when the outer side protective wall of the whole satellite is designed, a light-weight honeycomb sandwich structure capable of reducing weight, enhancing, insulating external heat and guiding out internal heat is adopted for a satellite shell including the Ka-band antenna.
With reference to fig. 5, fig. 5 is a schematic layer structure diagram of the satellite housing at Ka band antenna of the present invention, the satellite housing 112 at Ka band antenna 230 in fig. 4 is sequentially composed of an inner aluminum alloy skin 701, an inner side skin cell metal rubber mat 702, an aluminum alloy honeycomb interlayer 703, an outer side skin cell metal rubber mat 704 and an outer aluminum alloy skin 705 from inside to outside, and the honeycomb cells 703a of the aluminum alloy honeycomb interlayer 703 are filled with silicon aerogel; the thermal conductivity of the silicon aerogel used as the heat insulation filling at the temperature of 800K is only 0.03 w/m.K, the melting point of the silicon aerogel is up to 1200 ℃, the silicon aerogel can bear pressure which is thousands of times of the self-mass, the silicon aerogel has certain strength, the density of the silicon aerogel is only 2.75-3.5 times of the air density, and the silicon aerogel is combined with the structure of the aluminum alloy honeycomb interlayer 703 to reduce weight, enhance strength and insulate heat outside.
Preferably, the inner aluminum alloy skin 701 and the outer aluminum alloy skin 705 are both made of 5a06 aluminum alloy skins with the thickness of 1.5mm, the inner layer side skin cell metal rubber mat 702 and the outer layer side skin cell metal rubber mat 704 are both made of skin cell metal rubber with the thickness of 0.3mm, and the aluminum alloy honeycomb interlayer 703 is made of 5a06 aluminum alloy honeycomb interlayer with the thickness of 8.0 mm.
Meanwhile, as a plurality of active devices are arranged in the satellite-borne SAR radar, a plurality of heat generated during working can be dissipated, preferably, a plurality of heat conducting copper pipes 706 are laid in the aluminum alloy honeycomb interlayer 703 in parallel at intervals, and the heat conducting copper pipes 706 are attached to the outer layer side skin cell metal rubber mat 704; therefore, heat generated by the active device during working is led out to the outside of the satellite-borne SAR through the heat conducting copper pipe 706, the outer layer side skin cell metal rubber pad 704 and the outer layer aluminum alloy skin 705 in sequence by utilizing the temperature control system of the satellite-borne SAR, so that the working stability of the satellite-borne SAR is ensured, and the service life of the satellite-borne SAR is prolonged.
Preferably, the heat conduction copper pipe is made of a square copper pipe with the thickness of 0.8mm, the length of 5mm and the width of 5 mm.
It should be understood that the above-mentioned embodiments are only preferred embodiments of the present invention, and are not intended to limit the technical solutions of the present invention, and those skilled in the art can add, subtract, replace, change or modify the above-mentioned embodiments within the spirit and principle of the present invention, and all such additions, substitutions, changes or modifications should fall within the scope of the appended claims.
Claims (6)
1. A movement mechanism of a satellite-borne SAR radar Ka-band antenna is characterized by comprising a rotating motor, a rotary table, a first supporting leg, a second supporting leg, a third supporting leg, a fourth supporting leg, a pitching motor, a rotating shaft, a first gear and a second gear; wherein,
a motor shaft of the rotating motor is connected to the center of the lower end face of the rotary table and used for driving the rotary table to rotate around the axis line of the rotary table, and further the rotating angle of the Ka-band antenna is adjusted;
the bottom surfaces of the third supporting leg and the fourth supporting leg are vertically and symmetrically fixed at the periphery of the upper end surface of the rotary table, the rotary shaft is transversely connected between the upper parts of the third supporting leg and the fourth supporting leg through corresponding bearings and can rotate, and the pitching motor is connected to the end part of the rotary shaft and is used for driving the rotary shaft to rotate around the axis line of the rotary shaft;
the lower parts of the first supporting leg and the second supporting leg are hinged to the rotating shaft through corresponding bearings, the first supporting leg and the second supporting leg are located on the inner sides of the third supporting leg and the fourth supporting leg, and the upper ends of the first supporting leg and the second supporting leg are symmetrically fixed on the frustum-shaped outer side wall of the shell of the Ka-band antenna rectifier;
the first gear is coaxially sleeved in the middle of the rotating shaft, the second gear is semicircular and is fixed to the bottom of a tail shell of the Ka-band antenna rectifier, and the first gear is meshed with the second gear and is used for driving the second gear to rotate through the rotating shaft and the first gear under the driving of the pitching motor, so that the pitching angle of the Ka-band antenna is accurately adjusted.
2. The kinematic mechanism of the spaceborne SAR radar Ka-band antenna according to claim 1, characterized in that: the middle upper part of the first support leg is provided with a first forked groove, the first forked groove is positioned on the end surface of the first support leg in the thickness direction, the upper end of the first support leg inclines inwards, and the opening of the first forked groove extends to the upper end of the first support leg; symmetrically, the well upper portion of second stabilizer blade is provided with the second bifurcation groove, the second bifurcation groove is located the terminal surface of second stabilizer blade thickness direction, just the inboard slope in upper end of second stabilizer blade, the oral area in second bifurcation groove extends to the upper end of second stabilizer blade.
3. The kinematic mechanism of the spaceborne SAR radar Ka-band antenna according to claim 1, characterized in that: the satellite shell at the Ka-band antenna is sequentially composed of an inner-layer aluminum alloy skin, an inner-layer side skin cell metal rubber mat, an aluminum alloy honeycomb interlayer, an outer-layer side skin cell metal rubber mat and an outer-layer aluminum alloy skin from inside to outside, and the honeycomb cells of the aluminum alloy honeycomb interlayer are filled with silicon aerogel.
4. The kinematic mechanism of the spaceborne SAR radar Ka-band antenna according to claim 3, characterized in that: inner layer aluminum alloy skin and outer aluminum alloy skin all adopt 1.5 mm's 5A06 aluminum alloy skin preparation, inner layer side skin cell metal cushion and outer layer side skin cell metal cushion all adopt 0.3 mm's skin cell metal glue preparation, aluminum alloy honeycomb interlayer adopts 8.0 mm's 5A06 aluminum alloy honeycomb interlayer preparation.
5. The kinematic mechanism of the spaceborne SAR radar Ka-band antenna according to claim 3, characterized in that: a plurality of heat conduction copper pipes are laid in the aluminum alloy honeycomb interlayer at intervals in parallel, and the heat conduction copper pipes are attached to the outer layer side skin cell metal rubber gasket in an attached mode.
6. The kinematic mechanism of the spaceborne SAR radar Ka-band antenna according to claim 5, characterized in that: the heat conduction copper pipe is made of a square copper pipe with the thickness of 0.8mm, the length of 5mm and the width of 5 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202020250968.0U CN211376939U (en) | 2020-03-04 | 2020-03-04 | Motion mechanism of satellite-borne SAR radar Ka-band antenna |
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| CN202020250968.0U CN211376939U (en) | 2020-03-04 | 2020-03-04 | Motion mechanism of satellite-borne SAR radar Ka-band antenna |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113291378A (en) * | 2021-03-16 | 2021-08-24 | 浙江金乙昌科技股份有限公司 | Vehicle remote driving control platform and driving control system thereof |
| CN115685187A (en) * | 2022-07-08 | 2023-02-03 | 中山大学 | High-integration portable MIMO deformation monitoring radar device and correction method |
-
2020
- 2020-03-04 CN CN202020250968.0U patent/CN211376939U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113291378A (en) * | 2021-03-16 | 2021-08-24 | 浙江金乙昌科技股份有限公司 | Vehicle remote driving control platform and driving control system thereof |
| CN115685187A (en) * | 2022-07-08 | 2023-02-03 | 中山大学 | High-integration portable MIMO deformation monitoring radar device and correction method |
| CN115685187B (en) * | 2022-07-08 | 2023-10-13 | 中山大学 | High-integration portable MIMO deformation monitoring radar device and correction method |
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