CN210072061U - Vehicle-mounted camera bellows for testing radiation power of airplane radar - Google Patents
Vehicle-mounted camera bellows for testing radiation power of airplane radar Download PDFInfo
- Publication number
- CN210072061U CN210072061U CN201920538032.5U CN201920538032U CN210072061U CN 210072061 U CN210072061 U CN 210072061U CN 201920538032 U CN201920538032 U CN 201920538032U CN 210072061 U CN210072061 U CN 210072061U
- Authority
- CN
- China
- Prior art keywords
- radar
- camera
- camera bellows
- vehicle
- cooling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Radar Systems Or Details Thereof (AREA)
Abstract
The utility model discloses a vehicle-mounted camera bellows for aircraft radar radiation power test, which comprises a cooling system, wherein the cooling system comprises a liquid cold source and a cooling plate; the side surface of the front end of the dark box is provided with a radar; the wall plate of the camera bellows directly opposite to the radar and four wall plates inside the camera bellows adjacent to the radar are respectively provided with a cooling plate, and the liquid cooling source is connected with the cooling plates through pipelines. The utility model discloses a cooling system's liquid cooling cools off the heat that absorbing material absorbed the radiant energy and produce to guarantee absorbing material's life-span and radar operational environment's temperature, have better practicality.
Description
Technical Field
The utility model belongs to the technical field of aircraft radar is with test camera bellows, concretely relates to vehicular camera bellows that is used for aircraft radar radiation power to test.
Background
In recent years, airborne radars have two major changes, namely, mechanical scanning is developed to electric scanning, so that the scanning rate of the traditional radar is greatly broken through, and a foundation is laid for space synthesis of detection beams and partition of radar array surfaces; on the other hand, the passive radar is developed into the active radar, so that the radar breaks through the power limitation of a transmitter, the multi-stage amplification of radar signals is realized, and the detection distance of the radar is greatly increased. Especially, in the currently mainstream active phased array radar, the transmitted signals are amplified again in a large number of T/R components at the antenna end, the radiation power is greatly increased, and the detection distance is further broken through. However, as the complexity and importance of the radar antenna are higher and higher, a large number of tests on the core components and core indexes of the antenna are required to be performed by the radar under a high-voltage radiation state, which also causes the difficulty and danger of the detection of the radiation power to be multiplied.
In order to avoid the harm, research institutions usually adopt a method of building a fully-shielded darkroom to perform radar related radiation testing, however, the relatively large size and high cost are not practical for host factories and armies, and the frequent dragging of radar or airplanes to the darkroom in the radar testing and maintenance of each link is inconvenient, time-consuming and labor-consuming.
Consequently, for the radar radiation correlation performance who satisfies host computer factory level, the outdoor field of army level active radar user detects and maintains the demand, avoids the high-power radiation of radar to the harm of near personnel and environment, the utility model relates to a miniaturized, portable on-vehicle radar inhale ripples test camera bellows, fine solution present host computer factory level, army level radar user do not have the circumstances of radar outdoor field radiation correlation performance test condition.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a vehicular camera bellows for aircraft radar radiation power test, the utility model discloses a cooling system's liquid cooling cools off the heat that absorbing material absorbed the radiant energy and produce to guarantee absorbing material's life-span and radar operational environment's temperature, have better practicality.
The utility model discloses mainly realize through following technical scheme: a vehicle-mounted camera bellows for aircraft radar radiation power testing comprises a cooling system, wherein the cooling system comprises a liquid cold source and a cooling plate; the side surface of the front end of the dark box is provided with a radar; the wall plate of the camera bellows directly opposite to the radar and four wall plates inside the camera bellows adjacent to the radar are respectively provided with a cooling plate, and the liquid cooling source is connected with the cooling plates through pipelines.
In order to better realize the utility model, the cooling plate comprises a main cooling plate and an auxiliary cooling plate, the wall plate of the camera bellows opposite to the radar is provided with the main cooling plate, and the wall plate of the camera bellows adjacent to the radar is respectively provided with the auxiliary cooling plate; the liquid cooling source is connected with the main cooling plate through a first pipeline and is respectively connected with the auxiliary cooling plates on the four wall plates through second pipelines; the main cooling plate and the auxiliary cooling plate are respectively connected with the liquid cooling source through return pipes.
For better realization the utility model discloses, it is further, be provided with absorbing material on the wallboard of the positive opposite camera bellows of radar and four inside wallboards of camera bellows adjacent with the radar respectively, the cooling plate sets up between absorbing material and camera bellows's wallboard.
In order to better realize the utility model, furthermore, the wave-absorbing material is a high-temperature-resistant silicon carbide type pointed cone wave-absorbing material; the wave-absorbing material is clamped on the cooling plate and the wall plate of the camera bellows through the clamping grooves and is firmly adhered through the thermal conductive adhesive.
In order to better realize the utility model, the side surface of the front end of the camera bellows is provided with a through radar embedding interface for installing a radar; the radar embedding interface at the front end of the camera bellows is made of a polyurethane tin foil sponge material; and the peripheral seat of the embedded interface is sealed and shielded.
For better realization the utility model discloses, it is further, the length of camera bellows is longer than radar beam forming distance by 0.5m, and the length of camera bellows: width: the high ratio is 3:1:1 to 2:1: 1.
For better realization the utility model discloses, it is further, each side of camera bellows is connected through the concatenation, the connection can be dismantled to the rear panel of camera bellows.
In order to better realize the utility model, the utility model further comprises a testing system, wherein the testing system comprises a receiving horn, a cable and a frequency spectrograph, and the receiving horn is arranged on a wall plate in the camera bellows opposite to the radiation center of the radar antenna; the receiving loudspeaker is connected with the frequency spectrograph through a cable.
For better realization the utility model discloses, it is further, still include the on-vehicle system, the on-vehicle system is including supporting lift adjustment device, the bottom of camera bellows is provided with supports lift adjustment device.
The utility model discloses mainly found a portable, miniaturized, the on-vehicle microwave test camera bellows of resistant high power, the design idea of this simple and easy camera bellows is compression camera bellows size as far as possible, suitably takes into account radar radiation power test, and the condition of radar radiation function inspection on the construction satisfied outfield aircraft only needs can carry out radar radiation with aircraft radar front end (radar antenna part) embedding suction incasement, and then accomplishes outfield radar radiation power and detects and maintenance work.
The utility model discloses mainly constitute by inhaling ripples camera bellows, test system (including receiving loudspeaker, cable, frequency spectrograph and the computer that carries out radar control and test data processing), on-vehicle operating system and cooling system, the concrete description is as follows:
1. dimension design of camera bellows
The length dimension is selected to be longer than the radar beam forming distance (meter level) by half a meter;
length: width: the high selection is between 3:1:1 and 2:1: 1.
2. Safety design of camera bellows
Arranging wave-absorbing materials on six surfaces of the dark box, and proposing to select high-temperature-resistant silicon carbide type pointed cone wave-absorbing materials;
the material performance and size are selected according to the surface radiation power density of the wave-absorbing material;
note: considering the aperture efficiency epsilon of the antennaAAnd transmission efficiency epsilonTThen, the maximum radiation power density at the position of the planar aperture antenna R is calculated by the following formula:
wherein: pinRepresenting the antenna input power, epsilonLAs an efficiency factor, DmaxAnd the maximum value of the directional gain function of the antenna, wherein gamma is a reflection coefficient, and R is the distance from the antenna, wherein A is the area of the antenna, and lambda is the working wavelength.
And a cooling plate is arranged at the front surface of the radar and behind the wave-absorbing materials on the four adjacent surfaces, and the heat generated by the wave-absorbing materials absorbing the radiant energy is cooled in a liquid cooling mode, so that the service life of the wave-absorbing materials and the temperature of the radar working environment are ensured.
3. Design of shielding performance of dark box
A shielding layer is added to prevent energy leakage or external electromagnetic interference in the camera obscura; the material generally selects steel plates, copper meshes and other materials, and the material and the thickness are selected according to the actual test environment requirements, and if the environment needs to be 100dB, a steel plate with the thickness of 2-3mm can be selected.
4. Design of dark box structure mode
The whole wave absorption box is spliced and connected, and particularly, the rear panel is used as a main maintenance channel and can be quickly disassembled and assembled so as to be beneficial to maintenance; the wave-absorbing material is arranged on the cooling plate and the wall plate in a clamping groove mode and is firmly adhered through the thermal conductive adhesive; the embedded interface at the front end of the aircraft radar is suggested to be made of polyurethane wave-absorbing sea surface materials, and the embedded periphery is subjected to sealing shielding treatment; a plurality of embedded panels can be manufactured according to different airplane or radar antenna sizes, and the camera bellows can be used for different airplanes or different radars.
5. Cooling system design
The cooling system consists of a liquid cold source, a cooling plate and corresponding connecting pipelines;
a main cooling plate is erected on a wall plate of the black box opposite to the radar and takes a main radiation energy absorption task;
the auxiliary cooling plates are laid on the other four surfaces and used for absorbing the radiation energy in the direction;
the liquid cooling is divided into two channels, one channel supplies cooling liquid to the main cooling plate, and the other channel supplies cooling liquid to the four auxiliary cooling plates.
6. Test system
A receiving horn of the test system is arranged on a wall plate of the black box right opposite to the radiation center of the radar antenna;
the horn is connected with the frequency spectrograph through the small hole by a cable;
the computer can be connected with the airplane radar and is used for monitoring the working state of the radar and controlling the radar to start radiation on the ground;
the frequency spectrograph can be connected with a computer, the computer resource is used for controlling the test, and the test data is processed.
7. Vehicle-mounted system
The vehicle-mounted system has necessary moving capability, and is provided with vehicle body fixing and camera bellows lifting functions for adjusting the height of the camera bellows to be matched with the front end of the airplane.
The utility model has the advantages that:
(1) the utility model discloses a cooling system's liquid cooling cools off the heat that absorbing material absorbed the radiant energy and produce to guarantee absorbing material's life-span and radar operational environment's temperature, have better practicality.
(2) The utility model discloses a security reliability is good: the utility model is provided with a reliable wave-absorbing structure and a good shielding structure, so that the radiation power in the test box is completely isolated and absorbed, the safety of surrounding personnel is ensured, and the electromagnetic environmental pollution is avoided; meanwhile, the interference of external electromagnetic signals on radar radiation related performance test is isolated, and the electromagnetic performance of the radar is basically detected under the condition of near free space.
(3) The utility model discloses have the relatively reliable detectability: the utility model discloses though very big compression camera bellows design size, still compromise radar beam forming's test distance, adopt mark earlier school in the test, can obtain more accurate test result to offset space and test system loss through twice test.
(4) The utility model discloses the convenience is high: the utility model has smaller size, adopts the vehicle-mounted design, has flexible moving capability, and can basically meet the external field radar radiation related performance test under the condition of not moving the airplane; on the other hand, the utility model discloses can be according to a plurality of embedding panels of different aircraft or radar antenna size preparation, realize just can satisfying the test demand of different radars, aircraft through changing the embedding panel.
(5) The utility model discloses economic practicality is strong: compare the full shield darkroom, the utility model discloses no matter be area, still the cost all can not its dozens of or even hundreds of times to can also possess certain and comparatively reliable radar radiation capability test ability, the comprehensive sexual valence relative altitude provides a reliable way for safe test, the maintenance of main airport, army outfield radar radiation correlation performance.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of a connecting structure of a black box and a receiving horn;
FIG. 3 is a schematic plan view of a microwave absorbing material disassembled in a dark box;
FIG. 4 is a schematic illustration of a cooling system;
fig. 5 is a schematic view of the structure of the inside of the cooling plate.
Wherein: 1-a dark box, 2-a supporting lifting adjusting device, 3-a receiving loudspeaker and 4-a radar embedded interface.
Detailed Description
Example 1:
a vehicle-mounted camera bellows for aircraft radar radiation power test is disclosed, as shown in figures 4 and 5, and comprises a cooling system, wherein the cooling system comprises a liquid cooling source and a cooling plate; the side surface of the front end of the dark box 1 is provided with a radar; the wall plate of camera bellows 1 and the four inside wall plates of camera bellows 1 adjacent to the radar that are just opposite of radar are provided with the cooling plate respectively, the liquid cooling source passes through the pipe connection cooling plate.
As shown in fig. 5, the cooling plate is provided therein with a cooling duct in which a cooling liquid is provided. The utility model discloses a cooling system's liquid cooling cools off the heat that absorbing material absorbed the radiant energy and produce to guarantee absorbing material's life-span and radar operational environment's temperature, have better practicality.
Example 2:
the present embodiment is optimized based on embodiment 1, and as shown in fig. 4 and 5, the cooling plates include a main cooling plate and an auxiliary cooling plate, the wall plate of the camera bellows 1 opposite to the radar is provided with the main cooling plate, and the wall plates of the camera bellows 1 adjacent to the radar are respectively provided with the auxiliary cooling plates; the liquid cooling source is connected with the main cooling plate through a first pipeline and is respectively connected with the auxiliary cooling plates on the four wall plates through second pipelines; the main cooling plate and the auxiliary cooling plate are respectively connected with the liquid cooling source through return pipes.
As shown in fig. 4, the cooling liquid circulates among the main cooling plate, the auxiliary cooling plate, and the liquid cooling source; as shown in fig. 5, the cooling plate is provided therein with a cooling duct in which a cooling liquid is provided. The utility model discloses a cooling system's liquid cooling cools off the heat that absorbing material absorbed the radiant energy and produce to guarantee absorbing material's life-span and radar operational environment's temperature, have better practicality.
Other parts of this embodiment are the same as embodiment 1, and thus are not described again.
Example 3:
the present embodiment is optimized on the basis of embodiment 1 or 2, as shown in fig. 3, wave absorbing materials are respectively disposed on the wall plate of the black box 1 opposite to the radar and the four wall plates inside the black box 1 adjacent to the radar, and the cooling plate is disposed between the wave absorbing materials and the wall plate of the black box 1. The wave-absorbing material is a high-temperature-resistant silicon carbide type pointed cone wave-absorbing material; the wave-absorbing material is clamped on the cooling plate and the wall plate of the camera bellows 1 through the clamping grooves and is firmly adhered through thermal conductive adhesive.
The utility model is provided with a reliable wave-absorbing structure and a good shielding structure, so that the radiation power in the test box is completely isolated and absorbed, the safety of surrounding personnel is ensured, and the electromagnetic environmental pollution is avoided; meanwhile, the interference of external electromagnetic signals on radar radiation related performance test is isolated, and the electromagnetic performance of the radar is basically detected under the condition of near free space.
The rest of this embodiment is the same as embodiment 1 or 2, and therefore, the description thereof is omitted.
Example 4:
the embodiment is optimized on the basis of any one of embodiments 1 to 3, and as shown in fig. 2, a penetrating radar embedding interface 4 is arranged on the side surface of the front end of the dark box 1 and used for installing a radar; the radar embedded interface 4 at the front end of the camera bellows 1 is made of a polyurethane tin foil sponge material; and the peripheral seat of the embedded interface is sealed and shielded.
The utility model is provided with a reliable wave-absorbing structure and a good shielding structure, so that the radiation power in the test box is completely isolated and absorbed, the safety of surrounding personnel is ensured, and the electromagnetic environmental pollution is avoided; meanwhile, the interference of external electromagnetic signals on radar radiation related performance test is isolated, and the electromagnetic performance of the radar is basically detected under the condition of near free space.
Other parts of this embodiment are the same as any of embodiments 1 to 3, and thus are not described again.
Example 5:
this embodiment is optimized based on embodiment 1, as shown in fig. 2, the length of the dark box 1 is 0.5m longer than the radar beam forming distance, and the length of the dark box 1 is: width: the high ratio is 3:1:1 to 2:1: 1. Each side of the camera bellows 1 is connected by splicing, and the back panel of the camera bellows 1 is detachably connected.
The utility model discloses the convenience is high: the utility model has smaller size, adopts the vehicle-mounted design, has flexible moving capability, and can basically meet the external field radar radiation related performance test under the condition of not moving the airplane; on the other hand, the utility model discloses can be according to a plurality of embedding panels of different aircraft or radar antenna size preparation, realize just can satisfying the test demand of different radars, aircraft through changing the embedding panel. The utility model discloses economic practicality is strong: compare the full shield darkroom, the utility model discloses no matter be area, still the cost all can not its dozens of or even hundreds of times to can also possess certain and comparatively reliable radar radiation capability test ability, the comprehensive sexual valence relative altitude provides a reliable way for safe test, the maintenance of main airport, army outfield radar radiation correlation performance.
Other parts of this embodiment are the same as those of embodiment 1, and thus are not described again.
Example 6:
the embodiment is optimized on the basis of the embodiment 1, and further comprises a test system, wherein the test system comprises a receiving loudspeaker 3, a cable and a frequency spectrograph, and the receiving loudspeaker 3 is arranged on a wall plate in the camera bellows 1 opposite to the radiation center of the radar antenna; the receiving horn 3 is connected with the frequency spectrograph through a cable. As shown in fig. 1, the solar camera further comprises a vehicle-mounted system, wherein the vehicle-mounted system comprises a supporting lifting adjusting device 2, and the bottom of the camera bellows 1 is provided with the supporting lifting adjusting device 2.
As shown in figure 1, the vehicle-mounted system has necessary moving capability and is provided with a vehicle body fixing function and a camera 1 lifting function, and the supporting lifting adjusting device 2 is used for adjusting the camera 1 to be matched with the front end height of the airplane.
The utility model discloses have the relatively reliable detectability: the utility model discloses though 1 design dimension of very big compression camera bellows, still compromise radar beam forming's test distance, adopt mark earlier school in the test, can obtain more accurate test result to offset space and test system loss through twice test. The utility model discloses economic practicality is strong: compare the full shield darkroom, the utility model discloses no matter be area, still the cost all can not its dozens of or even hundreds of times to can also possess certain and comparatively reliable radar radiation capability test ability, the comprehensive sexual valence relative altitude provides a reliable way for safe test, the maintenance of main airport, army outfield radar radiation correlation performance.
Other parts of this embodiment are the same as those of embodiment 1, and thus are not described again.
The above is only the preferred embodiment of the present invention, not to the limitation of the present invention in any form, all the technical matters of the present invention all fall into the protection scope of the present invention to any simple modification and equivalent change of the above embodiments.
Claims (9)
1. A vehicle-mounted camera bellows for testing the radiation power of an aircraft radar is characterized by comprising a cooling system, a camera module and a power supply module, wherein the cooling system comprises a liquid cold source and a cooling plate; the side surface of the front end of the dark box (1) is provided with a radar; the wall plates of the camera bellows (1) opposite to the radar and the four wall plates inside the camera bellows (1) adjacent to the radar are respectively provided with a cooling plate, and the liquid cooling source is connected with the cooling plates through pipelines.
2. The vehicle-mounted camera box for the aircraft radar radiated power test according to the claim 1, characterized in that the cooling plates comprise a main cooling plate and an auxiliary cooling plate, the wall of the camera box (1) opposite to the radar is provided with the main cooling plate, and the wall of the camera box (1) adjacent to the radar is provided with the auxiliary cooling plate respectively; the liquid cooling source is connected with the main cooling plate through a first pipeline and is respectively connected with the auxiliary cooling plates on the four wall plates through second pipelines; the main cooling plate and the auxiliary cooling plate are respectively connected with the liquid cooling source through return pipes.
3. The vehicle-mounted camera bellows for the aircraft radar radiation power test according to the claim 1, characterized in that the wall of the camera bellows (1) opposite to the radar and the four wall plates inside the camera bellows (1) adjacent to the radar are respectively provided with wave-absorbing materials, and the cooling plates are arranged between the wave-absorbing materials and the wall plates of the camera bellows (1).
4. The vehicle-mounted camera bellows for aircraft radar radiation power testing according to claim 3, wherein the wave-absorbing material is a high-temperature-resistant silicon carbide type pointed cone wave-absorbing material; the wave-absorbing material is clamped on the cooling plate and the wall plate of the camera bellows (1) through the clamping grooves and is firmly adhered through thermal conductive adhesive.
5. The vehicle-mounted camera box for the aircraft radar radiation power test is characterized in that the side face of the front end of the camera box (1) is provided with a through radar embedding interface (4) for installing a radar; the radar embedding interface (4) at the front end of the camera bellows (1) is made of a polyurethane tin foil sponge material; and the peripheral seat of the embedded interface is sealed and shielded.
6. A vehicle-mounted camera for aircraft radar radiated power testing according to any one of claims 1 to 5, characterized in that the length of the camera (1) is 0.5m longer than the radar beam forming distance, and the length of the camera (1): width: the high ratio is 3:1:1 to 2:1: 1.
7. A vehicle-mounted camera chamber for aircraft radar radiated power testing according to claim 6, characterized in that the sides of the camera chamber (1) are connected by splicing, and the rear panel of the camera chamber (1) is detachably connected.
8. The vehicle-mounted camera bellows for the aircraft radar radiated power test according to the claim 1, characterized by further comprising a test system, wherein the test system comprises a receiving horn (3), a cable and a spectrometer, the receiving horn (3) is arranged on a wall plate in the interior of the camera bellows (1) opposite to the radar antenna radiation center; the receiving loudspeaker (3) is connected with the frequency spectrograph through a cable.
9. A vehicle-mounted camera box for aircraft radar radiated power testing according to claim 1, characterized by further comprising a vehicle-mounted system, wherein the vehicle-mounted system comprises a supporting lifting adjusting device (2), and the bottom of the camera box (1) is provided with the supporting lifting adjusting device (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920538032.5U CN210072061U (en) | 2019-04-19 | 2019-04-19 | Vehicle-mounted camera bellows for testing radiation power of airplane radar |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920538032.5U CN210072061U (en) | 2019-04-19 | 2019-04-19 | Vehicle-mounted camera bellows for testing radiation power of airplane radar |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210072061U true CN210072061U (en) | 2020-02-14 |
Family
ID=69437739
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920538032.5U Active CN210072061U (en) | 2019-04-19 | 2019-04-19 | Vehicle-mounted camera bellows for testing radiation power of airplane radar |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210072061U (en) |
-
2019
- 2019-04-19 CN CN201920538032.5U patent/CN210072061U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6492586B2 (en) | Space photovoltaic power generation system, power satellite, and control satellite | |
| EP1189329B1 (en) | Space photovoltaic power generation method and system | |
| CN205982435U (en) | Field test system is reduceed in small -size integration | |
| CN106950975B (en) | Large angle maneuver high-resolution microwave remote sensing satellite overall control method | |
| EP1189328B1 (en) | Space photovoltaic power generation system | |
| Pellegrini et al. | MID-radio telescope, single pixel feed packages for the square kilometer array: an overview | |
| Wang et al. | Retro-directive beamforming versus retro-reflective beamforming with applications in wireless power transmission | |
| Rodenbeck et al. | Terrestrial microwave power beaming | |
| CN107918703B (en) | Design method for wide-band radio frequency receiving satellite unintentional radiation emission limit value | |
| CN210072061U (en) | Vehicle-mounted camera bellows for testing radiation power of airplane radar | |
| Bathker et al. | Beam-waveguide antenna performance predictions with comparisons to experimental results | |
| Dorsey et al. | Design and performance of frequency selective surface with integrated photodiodes for photonic calibration of phased array antennas | |
| Chippendale et al. | ASKAP: Progress towards 36 parabolic reflectors with phased array feeds | |
| CN108732429A (en) | A kind of antenna reflective face passive cross modulation test device | |
| CN108832299B (en) | Intelligent wall structure based on solid-state plasma | |
| Udintsev et al. | Progress in ITER ECE Diagnostic Design and integration | |
| Wang et al. | Design of a microwave power transmission demonstration system for space solar power station | |
| CHANG et al. | Programmable metasurface for simultaneously wireless information and power transfer system | |
| CN212963039U (en) | Unmanned aerial vehicle defense system | |
| Pantaleev et al. | Design, implementation and tests of the signal chain for the twin telescopes at Onsala Space Observatory | |
| PEENS-HOUGH et al. | MID-Radio Telescope, Single Pixel Feed Packages for the Square Kilometer Array: An Overview | |
| JP5377140B2 (en) | Two-way wireless connection system | |
| Xianhao et al. | Antenna Modeling and Simulation Method Analysis and Research | |
| CN103036036B (en) | Exterior aerial device | |
| CN212111767U (en) | Unmanned aerial vehicle detection radar |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |