CN113702925B - Millimeter wave guide camouflage effect prevention test system - Google Patents
Millimeter wave guide camouflage effect prevention test system Download PDFInfo
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- CN113702925B CN113702925B CN202110774383.8A CN202110774383A CN113702925B CN 113702925 B CN113702925 B CN 113702925B CN 202110774383 A CN202110774383 A CN 202110774383A CN 113702925 B CN113702925 B CN 113702925B
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- 238000012360 testing method Methods 0.000 title claims abstract description 26
- 230000000694 effects Effects 0.000 title claims abstract description 25
- 230000002265 prevention Effects 0.000 title claims abstract description 17
- 238000004891 communication Methods 0.000 claims abstract description 40
- 230000005540 biological transmission Effects 0.000 claims abstract description 28
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 21
- 238000006243 chemical reaction Methods 0.000 claims description 12
- 238000012544 monitoring process Methods 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 10
- 238000012545 processing Methods 0.000 claims description 8
- 230000003068 static effect Effects 0.000 claims description 8
- 238000001514 detection method Methods 0.000 claims description 5
- 239000000725 suspension Substances 0.000 claims description 4
- 238000010586 diagram Methods 0.000 description 5
- 230000010355 oscillation Effects 0.000 description 3
- 238000009825 accumulation Methods 0.000 description 2
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/40—Means for monitoring or calibrating
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/883—Radar or analogous systems specially adapted for specific applications for missile homing, autodirectors
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Computer Networks & Wireless Communication (AREA)
- General Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses an anti-millimeter wave guidance camouflage effect test system, which comprises a ground control unit, a flight platform and a camouflage target, wherein the flight platform comprises an unmanned aerial vehicle, a millimeter wave guide head, an inertial navigation module, an airborne control subsystem and an airborne wireless transmission subsystem which are respectively arranged on the unmanned aerial vehicle, the airborne control subsystem is respectively in communication connection with the millimeter wave guide head and the inertial navigation module, the airborne control subsystem is also in communication connection with the ground control unit through the airborne wireless transmission subsystem, and the camouflage target comprises a target unit and a camouflage unit arranged on the target unit. The millimeter wave guide camouflage effect prevention test system provided by the invention has the advantages of accurate test and convenience in use.
Description
Technical Field
The invention relates to the technical field of guidance, in particular to a millimeter wave guidance camouflage effect prevention test system.
Background
Guidance refers to techniques and methods for guiding and controlling an aircraft to fly to a target or predetermined trajectory on a regular basis. In the guidance process, the guidance system continuously measures the relative position relation between the aircraft and the target or the preset orbit, and sends guidance information to the aircraft control system so as to control the flight. Common guidance modes such as infrared guidance, millimeter wave radar guidance and the like, and guidance technologies are applied to military fields such as guided shells and the like.
In order to prevent enemy from finding out the target on the my and then tracking and hitting the target through a guidance means, a camouflage means is required to camouflage and hide the target on the my correspondingly. In the actual research and development process, the guidance equipment and the camouflage equipment are required to be subjected to an countermeasure test, but a convenient and effective test system is lacking in reality.
Disclosure of Invention
The invention aims to provide a millimeter wave guidance camouflage effect prevention test system which is used for solving the problem that a convenient and effective test system is lacking in reality.
The utility model provides an anti-millimeter wave guidance camouflage effect test system, includes ground control unit, flight platform and camouflage target, flight platform includes unmanned aerial vehicle and sets up respectively millimeter wave guide on the unmanned aerial vehicle draws head, inertial navigation module, airborne control subsystem and airborne wireless transmission subsystem, airborne control subsystem communication connection respectively millimeter wave guide draw head with inertial navigation module, airborne control subsystem still passes through airborne wireless transmission subsystem communication connection ground control unit, the camouflage target includes target unit and sets up the camouflage unit on target unit.
Based on the above, the millimeter waveguide guide head comprises an antenna receiving and transmitting front end, an intermediate frequency component and a signal processor, wherein the intermediate frequency component is respectively connected with the antenna receiving and transmitting front end and the signal processor.
Based on the above, the antenna receiving and transmitting front end comprises a feed source and difference module, an antenna module, a transmitting and receiving module and a mixing local oscillator module, wherein the mixing local oscillator module is connected with the intermediate frequency component and the transmitting and receiving module, and the feed source and difference module is connected with the antenna module and the transmitting and receiving module.
Based on the above, the intermediate frequency component includes an intermediate frequency receiver and a frequency synthesizer.
Based on the above, the signal processor includes a signal processing module, an ADC module, a clock module, a baseband signal module, and an interface communication module.
Based on the above, the airborne control subsystem comprises a communication board, a storage board, a clock module, an SD card module and a plurality of communication interface conversion modules, wherein the communication interface conversion modules are respectively connected with the communication board, the clock module and the SD card module are respectively connected with the storage board, and the storage board is also connected with the communication interface conversion modules.
Based on the above, the ground control unit comprises a flight control navigation system, a ground control station and a communication link, wherein the flight control navigation system comprises an airborne sensor, a flight control computer and a data acquisition and recording module, the ground control station is in communication connection with the airborne control subsystem through the communication link, and the flight control computer receives monitoring information of the airborne sensor and stores the monitoring information into the data acquisition and recording module
The method of the invention has the following advantages: according to the invention, the ground control unit, the flight platform and the camouflage target are matched with each other to camouflage the target unit, the guidance test is carried out through the flight platform to detect the camouflage effect, and the ground control unit is used for effectively controlling the flight platform, so that the invention has the advantages of accurate test and convenient use.
Drawings
FIG. 1 is a schematic diagram of the system operation of the present invention.
Fig. 2 is a schematic block diagram of the system of the present invention.
Fig. 3 is a schematic block diagram of a millimeter waveguide leader system of the present invention.
Fig. 4 is a schematic block diagram of the system of the on-board control subsystem of the present invention.
Fig. 5 is a schematic block diagram of a system of the floor control unit of the present invention.
Detailed Description
The technical solution of the present invention will be clearly and completely described in conjunction with the specific embodiments, but it should be understood by those skilled in the art that the embodiments described below are only for illustrating the present invention and should not be construed as limiting the scope of the present invention. All other embodiments, which can be made by one of ordinary skill in the art without undue burden on the person of ordinary skill in the art based on the embodiments of the present invention, are within the scope of the present invention.
As shown in fig. 1 and fig. 2, the millimeter wave guidance camouflage effect test system comprises a ground control unit, a flight platform and a camouflage target, wherein the flight platform comprises an unmanned aerial vehicle, a millimeter wave guide head, an inertial navigation module, an airborne control subsystem and an airborne wireless transmission subsystem, the millimeter wave guide head and the inertial navigation module are respectively arranged on the unmanned aerial vehicle, the airborne control subsystem is respectively in communication connection with the millimeter wave guide head and the inertial navigation module, the airborne control subsystem is also in communication connection with the ground control unit through the airborne wireless transmission subsystem, and the camouflage target comprises a target unit and a camouflage unit arranged on the target unit.
In practice, the target unit can be a static target or a dynamic target, namely a moving target, when the static target is detected, firstly, the camouflage target for preventing millimeter wave guidance camouflage is taken as a accompanying sample, and the camouflage target is arranged in a test field according to the operational requirement of the test sample; secondly, controlling the unmanned aerial vehicle on the upper part of the portable machine through a ground control station, flying to an air suspension with a distance of more than 5Km and a relative height of more than 200m, transmitting an unmanned aerial vehicle flight control signal of the ground control station to an airborne control subsystem through a ground wireless transmission subsystem and an airborne wireless transmission subsystem, and outputting a flight control signal by the airborne control subsystem to control the unmanned aerial vehicle to fly; thirdly, sending a starting instruction through a ground control station, controlling the millimeter waveguide leading radar to start, entering a target searching working state, and marking the moment as T1; fourthly, controlling the unmanned aerial vehicle to fly from far to near to a target through a ground control station, and outputting radar working state information and a target echo signal in real time by a millimeter waveguide leader; according to the target echo signal, the millimeter waveguide leader completes detection, positioning and tracking of the target; and the working state information and echo signal data output by the guide head are stored in real time to a data memory of the airborne control subsystem, and are transmitted to a ground control station for real-time display and monitoring through the airborne control subsystem and the wireless transmission subsystem. When the millimeter waveguide leading radar detects a target, entering a target tracking working state, and marking the moment as T2; fifthly, controlling the unmanned aerial vehicle to return through a ground control station; step six, implementing static millimeter wave guide camouflage prevention on the accompanying sample placed at the original position, and repeating the step two to the step four as a sample, wherein the time when the marking seeker enters the target searching working state in the step two is t1; in the fourth step, the moment when the marking seeker enters the target tracking working state is t2; and seventh, evaluating the static millimeter wave prevention guidance camouflage effect according to whether t= (T2-T1) - (T2-T1) is larger than T, wherein T is the millimeter wave prevention guidance camouflage effect index requirement.
When detecting and evaluating the dynamic millimeter wave guide camouflage prevention effect, firstly, taking equipment for preventing millimeter wave guide camouflage to be implemented as a partner sample, and setting the partner sample in a test field according to the operational requirement; secondly, controlling the unmanned aerial vehicle on the upper part of the portable machine through a ground control station, flying to an air suspension with a distance of more than 5Km and a relative height of more than 200m, transmitting an unmanned aerial vehicle flight control signal of the ground control station to an airborne control subsystem through a ground wireless transmission subsystem and an airborne wireless transmission subsystem, and outputting a flight control signal by the airborne control subsystem to control the unmanned aerial vehicle to fly; thirdly, sending a starting instruction through a ground control station, controlling the millimeter waveguide leading radar to start, and entering a target searching working state; fourthly, controlling the unmanned aerial vehicle to fly from far to near to a target through a ground control station, and outputting radar working state information and a target echo signal in real time by a millimeter waveguide leader; according to the target echo signal, the millimeter waveguide leader completes detection, positioning and tracking of the target; the working state information and target echo signal data output by the guide head are stored in real time to a data memory of the airborne control subsystem, and are transmitted to a ground control station for real-time display and monitoring through the airborne control subsystem and the wireless transmission subsystem; fifthly, when the millimeter wave guide head radar detects a target, entering a target tracking working state, and implementing dynamic millimeter wave guide camouflage prevention on the accompanying sample placed at the original position; sixthly, when the ground control station monitors that the guide head loses the target, reentering the target searching working state, and marking the moment as T1; controlling the unmanned aerial vehicle to fly continuously to the target, and if the guide head is always in the target searching working state in the flying process, marking the moment when the unmanned aerial vehicle flies to the position 200m away from the target as T2=T1+t; if the millimeter waveguide leading head detects the target again in the flying process, the target enters a target tracking working state, and the moment is marked as T2; seventh, controlling the unmanned aerial vehicle to return through a ground control station; and eighth step, evaluating the dynamic millimeter wave guide camouflage effect according to whether t=T2-T1 is larger than T, wherein T is the millimeter wave guide camouflage effect index requirement.
As shown in fig. 3, the millimeter waveguide guide head comprises an antenna receiving and transmitting front end, an intermediate frequency component and a signal processor, wherein the intermediate frequency component is respectively connected with the antenna receiving and transmitting front end and the signal processor. Specifically, the antenna receiving and transmitting front end comprises a feed source and difference module, an antenna module, a transmitting and receiving module and a mixing local oscillator module, wherein the mixing local oscillator module is connected with the intermediate frequency assembly and the transmitting and receiving module, and the feed source and difference module is connected with the antenna module and the transmitting and receiving module. The intermediate frequency component comprises an intermediate frequency receiver and a frequency synthesizer. The signal processor comprises a signal processing module, an ADC module, a clock module, a baseband signal module and an interface communication module. In practice, the antenna cover is also included for protecting the antenna; the antenna module actually comprises a parabolic antenna and/or a slot array antenna. The guide head also comprises a servo extension which is used for driving the antenna to swing so as to search the target. When the system works, the frequency synthesizer of the intermediate frequency component generates a high-frequency local oscillation signal and an intermediate frequency excitation signal, and the high-frequency local oscillation signal and the intermediate frequency excitation signal are transmitted by an antenna after up-conversion of the frequency mixing local oscillation module at the front end of receiving and transmitting. The antenna receives the echo signal, the transmitting and receiving module of the front end of the antenna receives and receives the down-conversion, the down-converted signal finishes the second down-conversion and receiving and amplifying processes through the intermediate frequency receiver, and the received baseband signal is sent to the signal processor for processing. The signal processor is used for completing the sampling of intermediate frequency signals, and then algorithms such as digital orthogonalization processing, filtering downsampling, pulse compression, phase-coherent accumulation, constant false alarm detection, clustering fusion, parameter extraction and target identification, track processing and the like are adopted for processing signal streams, wherein the line-of-sight angle errors of the targets in a guidance head antenna coordinate system are extracted by the sum signal, pitch difference and azimuth difference signals through the parameter extraction algorithm, and the distance and speed information of the targets are extracted through the phase-coherent accumulation. The processing result is reported to a flight control system of the missile, and the antenna beam is controlled to point to the target through the servo extension, so that the target is searched, intercepted and tracked.
As shown in fig. 4, the airborne control subsystem includes a communication board, a storage board, a clock module, an SD card module and a plurality of communication interface conversion modules, where the plurality of communication interface conversion modules are respectively connected to the communication board, the clock module and the SD card module are respectively connected to the storage board, and the storage board is also connected to the communication interface conversion modules. The airborne control subsystem actually further comprises an airborne power supply system for supplying power to all components on the aircraft, and mainly comprises a battery pack, a switch, a voltmeter, an overcurrent protector and a voltage converter. The airborne control subsystem is mainly used for receiving and storing the data of the detected target and inertial navigation and forwarding the data to the wireless transmission device in real time. The actual airborne control subsystem comprises an STM32 communication board, an STM32 storage board, a 5-block TTL-to-422 module, a 2-block TTL-to-232 module, a clock module and an SD card module, wherein a tested piece serial port is used for connecting a guide head, a communication board programming serial port is used for programming a communication board, a wireless transmission device serial port is used for connecting an airborne wireless transmission subsystem, an inertial navigation serial port is used for connecting an inertial navigation module, a storage board programming serial port is used for programming a storage board programming program, a test serial port is used during debugging, and a differential serial port is a redundancy design serial port. The SD card module is connected with the storage board. In practice, the wireless transmission subsystem is a small-sized and light-weight frequency-modulation data transmission station, and the parameters are as follows:
| Product model | P900 |
| Frequency range | 902—928MHz |
| Transmission mode | Frequency hopping |
| Transmission distance | 60km |
| Serial port baud rate | Asynchronous at less than or equal to 230.4kbps |
| Transmitting power | 100mW—1W(20—30dbm) |
| Voltage (V) | 3.3V |
| Operating temperature | -55℃—+85℃ |
| External dimension | 26.5*33*3.5mm |
As shown in fig. 5, the ground control unit comprises a flight control navigation system, a ground control station and a communication link, wherein the flight control navigation system comprises an airborne sensor, a flight control computer and a data acquisition and recording module, and the ground control station is in communication connection with the airborne control subsystem through the communication link, receives monitoring information of the airborne sensor and stores the monitoring information into the data acquisition and recording module. The ground control unit mainly completes the measurement of the flight attitude and position, the flight state monitoring, the autonomous route flight control and the automatic flight safety protection, and can communicate with the task equipment to complete the special user requirements. In this embodiment, the communication link and the wireless transmission subsystem are the same wireless communication system.
While the invention has been described in detail in the foregoing general description and specific examples, it will be apparent to those skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications or improvements may be made without departing from the spirit of the invention and are intended to be within the scope of the invention as claimed.
Claims (6)
1. A millimeter wave guidance camouflage effect prevention test system is characterized in that: the system comprises a ground control unit, a flight platform and a camouflage target, wherein the flight platform comprises an unmanned aerial vehicle, a millimeter wave guide head, an inertial navigation module, an airborne control subsystem and an airborne wireless transmission subsystem which are respectively arranged on the unmanned aerial vehicle, the airborne control subsystem is respectively in communication connection with the millimeter wave guide head and the inertial navigation module, the airborne control subsystem is also in communication connection with the ground control unit through the airborne wireless transmission subsystem, and the camouflage target comprises a target unit and a camouflage unit arranged on the target unit;
The ground control unit comprises a flight control navigation system, a ground control station and a communication link, wherein the flight control navigation system comprises an airborne sensor, a flight control computer and a data acquisition and recording module, the ground control station is in communication connection with the airborne control subsystem through the communication link, and the flight control computer receives monitoring information of the airborne sensor and stores the monitoring information into the data acquisition and recording module;
the target unit includes: static targets and dynamic targets;
When the static target is detected, firstly, a camouflage target for performing millimeter wave prevention guidance camouflage is used as a partner sample and is arranged in a test field according to the combat use requirement; secondly, controlling the unmanned aerial vehicle on the upper part of the portable machine through a ground control station, flying to an air suspension with a distance of more than 5Km and a relative height of more than 200m, transmitting an unmanned aerial vehicle flight control signal of the ground control station to an airborne control subsystem through a ground wireless transmission subsystem and an airborne wireless transmission subsystem, and outputting a flight control signal by the airborne control subsystem to control the unmanned aerial vehicle to fly; thirdly, sending a starting instruction through a ground control station, controlling the millimeter waveguide leading radar to start, entering a target searching working state, and marking the moment as T1; fourthly, controlling the unmanned aerial vehicle to fly from far to near to a target through a ground control station, and outputting radar working state information and a target echo signal in real time by a millimeter waveguide leader; according to the target echo signal, the millimeter waveguide leader completes detection, positioning and tracking of the target; the working state information and echo signal data output by the guide head are stored in real time to a data memory of the airborne control subsystem, and are transmitted to a ground control station for real-time display and monitoring through the airborne control subsystem and the wireless transmission subsystem, when the millimeter waveguide guide head radar detects a target, the target enters a target tracking working state, and the moment is marked as T2; fifthly, controlling the unmanned aerial vehicle to return through a ground control station; step six, implementing static millimeter wave guide camouflage prevention on the accompanying sample placed at the original position, and repeating the step two to the step four as a sample, wherein the time when the marking seeker enters the target searching working state in the step two is t1; in the fourth step, the moment when the marking seeker enters the target tracking working state is t2; seventh, evaluating the static millimeter wave prevention guidance camouflage effect according to whether t= (T2-T1) - (T2-T1) is larger than T, wherein T is the millimeter wave prevention guidance camouflage effect index requirement;
When detecting and evaluating the dynamic millimeter wave guide camouflage prevention effect, firstly, taking equipment for preventing millimeter wave guide camouflage to be implemented as a partner sample, and setting the partner sample in a test field according to the operational requirement; secondly, controlling the unmanned aerial vehicle on the upper part of the portable machine through a ground control station, flying to an air suspension with a distance of more than 5Km and a relative height of more than 200m, transmitting an unmanned aerial vehicle flight control signal of the ground control station to an airborne control subsystem through a ground wireless transmission subsystem and an airborne wireless transmission subsystem, and outputting a flight control signal by the airborne control subsystem to control the unmanned aerial vehicle to fly; thirdly, sending a starting instruction through a ground control station, controlling the millimeter waveguide leading radar to start, and entering a target searching working state; fourthly, controlling the unmanned aerial vehicle to fly from far to near to a target through a ground control station, and outputting radar working state information and a target echo signal in real time by a millimeter waveguide leader; according to the target echo signal, the millimeter waveguide leader completes detection, positioning and tracking of the target; the working state information and target echo signal data output by the guide head are stored in real time to a data memory of the airborne control subsystem, and are transmitted to a ground control station for real-time display and monitoring through the airborne control subsystem and the wireless transmission subsystem; fifthly, when the millimeter wave guide head radar detects a target, entering a target tracking working state, and implementing dynamic millimeter wave guide camouflage prevention on the accompanying sample placed at the original position; sixthly, when the ground control station monitors that the guide head loses the target, reentering the target searching working state, and marking the moment as T1; controlling the unmanned aerial vehicle to fly continuously to the target, and if the guide head is always in the target searching working state in the flying process, marking the moment when the unmanned aerial vehicle flies to the position 200m away from the target as T2=T1+t; if the millimeter waveguide leading head detects the target again in the flying process, the target enters a target tracking working state, and the moment is marked as T2; seventh, controlling the unmanned aerial vehicle to return through a ground control station; and eighth step, evaluating the dynamic millimeter wave guide camouflage effect according to whether t=T2-T1 is larger than T, wherein T is the millimeter wave guide camouflage effect index requirement.
2. The millimeter wave guidance camouflage effect test system of claim 1, wherein: the millimeter waveguide guide head comprises an antenna receiving and transmitting front end, an intermediate frequency component and a signal processor, wherein the intermediate frequency component is respectively connected with the antenna receiving and transmitting front end and the signal processor.
3. The millimeter wave guidance camouflage effect test system of claim 2, wherein: the antenna receiving and transmitting front end comprises a feed source and difference module, an antenna module, a transmitting and receiving module and a mixing local oscillator module, wherein the mixing local oscillator module is connected with the intermediate frequency assembly and the transmitting and receiving module, and the feed source and difference module is connected with the antenna module and the transmitting and receiving module.
4. The millimeter wave guidance camouflage effect test system of claim 2, wherein: the intermediate frequency component comprises an intermediate frequency receiver and a frequency synthesizer.
5. The millimeter wave guidance camouflage effect test system of claim 2, wherein: the signal processor comprises a signal processing module, an ADC module, a clock module, a baseband signal module and an interface communication module.
6. The millimeter wave guidance camouflage effect test system of claim 1, wherein: the airborne control subsystem comprises a communication board, a storage board, a clock module, an SD card module and a plurality of communication interface conversion modules, wherein the communication interface conversion modules are respectively connected with the communication board, the clock module and the SD card module are respectively connected with the storage board, and the storage board is also connected with the communication interface conversion modules.
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| CN202110774383.8A CN113702925B (en) | 2021-07-08 | 2021-07-08 | Millimeter wave guide camouflage effect prevention test system |
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| CN202110774383.8A CN113702925B (en) | 2021-07-08 | 2021-07-08 | Millimeter wave guide camouflage effect prevention test system |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3782641D1 (en) * | 1987-01-28 | 1992-12-17 | Unisys Corp | RADAR TARGETING SYSTEM USING RADIO WAVES IN THE MILLIMETER AREA. |
| KR20130029674A (en) * | 2011-09-15 | 2013-03-25 | 국방과학연구소 | Flight simulation apparatus and method thereof |
| CN103440389A (en) * | 2013-08-31 | 2013-12-11 | 西安电子科技大学 | Infrared camouflage effect simulation system and infrared camouflage effect evaluation method based on full link |
| CN106134458B (en) * | 2013-07-31 | 2015-05-13 | 中国人民解放军63956部队 | Dirigible for target acquisition/camouflage protection carries complete polarization SAR system |
-
2021
- 2021-07-08 CN CN202110774383.8A patent/CN113702925B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3782641D1 (en) * | 1987-01-28 | 1992-12-17 | Unisys Corp | RADAR TARGETING SYSTEM USING RADIO WAVES IN THE MILLIMETER AREA. |
| KR20130029674A (en) * | 2011-09-15 | 2013-03-25 | 국방과학연구소 | Flight simulation apparatus and method thereof |
| CN106134458B (en) * | 2013-07-31 | 2015-05-13 | 中国人民解放军63956部队 | Dirigible for target acquisition/camouflage protection carries complete polarization SAR system |
| CN103440389A (en) * | 2013-08-31 | 2013-12-11 | 西安电子科技大学 | Infrared camouflage effect simulation system and infrared camouflage effect evaluation method based on full link |
Non-Patent Citations (1)
| Title |
|---|
| 防成像制导武器打击伪装效果仿真评估系统研究;袁世东等;《工兵装备研究》;第27卷(第1期);第21-24页 * |
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