CN205081243U - Directional diagram restructural satellite guidance antenna - Google Patents
Directional diagram restructural satellite guidance antenna Download PDFInfo
- Publication number
- CN205081243U CN205081243U CN201520742847.7U CN201520742847U CN205081243U CN 205081243 U CN205081243 U CN 205081243U CN 201520742847 U CN201520742847 U CN 201520742847U CN 205081243 U CN205081243 U CN 205081243U
- Authority
- CN
- China
- Prior art keywords
- antenna
- electric bridge
- pcb
- antenna body
- shell
- 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
Landscapes
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
The utility model provides a directional diagram is like restructural satellite guidance antenna, includes antenna house, antenna main part PCB, feed probe and antenna paster, antenna main part PCB set up in the antenna house, antenna main part PCB two -layer about divideing into, upper PCB is the ceramic dielectric structure, the structural surface of ceramic dielectric is metal paster layer, metal paster layer be equipped with the passive antenna of four feed microstrip forms, the PCB's of lower floor lower surface is equipped with the multiplexing feed network of double - circuit, amplifier circuit and filter circuit for the whole metal level that applies copper on, upper PCB center be equipped with the circular shape plated -through hole realize about the short circuit on surface metal layer, antenna main part PCB use the plated -through hole as the centre of symmetry, be provided with four feed probes, four feed probes pass antenna main part PCB and are connected with the multiplexing feed network of double - circuit.
Description
Technical field
The utility model relates to satellite guidance antenna technical field.Be specifically related to directional diagram reconstructable satellite guidance antenna, be mainly used in shell satellite guidance system.
Background technology
The satellite guidance shell of open report, the U.S. has guided missile system branch company of Ray Thcon to participate in XM982 " refreshing sword " 155 millimeters of guided cartridges of development, " dynamically " satellite guidance module that Russia has Moscow " compass " design bureau to develop.The satellite guidance of precision guided weapon is the high-performance and low-cost guidance technology of current latest development, satellite guidance is not subject to bad weather as the restriction of natural or made rain, snow, wind, haze, dirt, mist, smog, light etc., be applicable to round-the-clock meteorological condition, can throw in low latitude or high-altitude, to have after penetrating no matter, Multi-target Attacking and Strike out of air defence area ability, have the advantages that reliability is high and production cost is low, not only independently can use but also can jointly form high performance multiple platform with other guidance technologies and guide form, particularly GPS/INS guidance.Satellite guidance is current state-of-the-art precise guidance mode in the world, has installed the shell of satellite guidance additional, can carry out precision strike according to the coordinate determined in advance to point target, reduces subsidiary injury.Related data shows, the strike error of common 152 millimeters of shells can reach 100 meters, adopts departing from after satellite guidance to be no more than 10 meters, improves the fighting efficiency of shell greatly.
GPS, GLONASS, Beidou navigation satellite-signal are at well-known transmitted on frequencies, its modulation signature is widely known by the people, signal to noise ratio is lower again, carry out disturbing or cheating and be one and be relatively easy to thing, Iran just utilizes GPS perturbation technique to capture RQ-170 " sentry " the stealthy unmanned plane of Central Intelligence Agency.By attacker, satellite-signal is effectively disturbed; accuracy at target will reduce greatly; guided weapon is caused to depart from target of attack; even by misleading wide; greatly can reduce the fighting efficiency of guided weapon, thus reach the object protected the safety of one's own side's target or one's own side is lost and be reduced to a minimum.The satellite-signal that attacker avoids guided weapon to receive as far as possible is interfered, and improves the antijamming capability of guidance system, ensures the fighting efficiency of guided weapon.In complicated electromagnetic interference environment, how to improve the antijamming capability of satellite guidance system, become the technical barrier that correlation engineering designer faces.
In satellite navigation Anti-Jamming Technique, general employing has the antenna of anti-interference function and has the algorithm of anti-interference function.Because shell volume is little, running high speed rotates, and must carry thorax and is emitted through the high temperature in journey and accelerates overload, but the Anti-Jamming Technique that really can be used on shell is also few.Existing shell satellite guidance antenna is generally adopt omnidirectional antenna, and gain is low, does not have antijamming capability.Therefore be necessary to design a kind of directional diagram reconstructable big-dipper satellite guidance antenna, when not increasing volume and structure complexity, there is certain antijamming capability, meeting the requirements at the higher level of shell satellite guidance antenna.
Utility model content
This limitation using novel object to be for existing shell satellite guidance antenna.Design a kind of directional diagram reconstructable satellite guidance antenna, be mainly used in shell satellite guidance.By directional diagram reconfiguration technique, make the directional diagram maximum possible deflection sky direction of antenna, reduce the gain towards ground, increase upper half-space gain simultaneously, avoid ground satellite-signal jammer to the interference of guidance system and deception, improve the antijamming capability improving satellite guidance system in complicated electromagnetic interference environment, ensure the fighting efficiency of guided weapon.
For overcoming the deficiency that prior art exists, the technical scheme that the utility model provides is: a kind of directional image restructural satellite guidance antenna, comprise radome, antenna body PCB, feed probes and antenna patch, described antenna body PCB is arranged in radome, described antenna body PCB is divided into two-layer up and down, upper strata PCB is ceramic dielectric structure, ceramic dielectric structure upper surface is metal patch layer, described metal patch layer is provided with the passive antenna of the micro-band forms of four feeds, the lower surface of lower floor PCB is the overall metal level applying copper, metal level is provided with the multiplexing feeding network of two-way, amplifying circuit and filter circuit, the short circuit that circular plated-through hole realizes upper and lower surface metal level is provided with at PCB center, upper strata, at antenna body PCB take plated-through hole as symmetrical centre, be provided with four feed probes, four feed probes are connected with the multiplexing feeding network of two-way through antenna body PCB.
Further, the multiplexing feeding network of described two-way is by the first electric bridge, second electric bridge, 3rd electric bridge and the 4th electric bridge composition, and with the first electric bridge, 3rd electric bridge, second electric bridge, the signal combiner sequentially passing through microstrip line composition closed loop of the 4th electric bridge, wherein the first electric bridge with the second electric bridge is connected all separately two feed probes, at the 3rd electric bridge, the first delivery outlet is set, 4th electric bridge arranges the second delivery outlet, and two the microstrip line electrical length wherein the first electric bridge connected are longer than two microstrip line 0.25 wavelength that the second electric bridge connects, described signal combiner is identical to the microstrip line length of four symmetric feeds probes.
Further, the 3dB electric bridge of four described electric bridges to be models be HC1400P03.
Further, described radome is arranged on the head of shell, is shell metal shell in the below of antenna body PCB, and the top of antenna body PCB is shell nose fuze.
Switchable two kinds of feeding classifications are adopted by such structure, in shell rising and decline process, dextrorotation feed and left-handed feed respectively, make shell under any attitude, the peak value of dextrorotation gain pattern points into the sky, and the valley of dextrorotation gain is pointed to ground, realize antenna pattern restructural; Improve guidance system to the antijamming capability of ground satellite-signal jammer.
Upper strata antenna receives satellite-signal, through the multiplexing feeding network of two-way, a point two-way is input to elementary amplifying circuit, according to the difference of the shell angle of pitch, select a wherein road to be input to rear class to amplify and filter circuit, what guarantee received is the right hand signal having larger gain towards upper half-space.The angle of pitch of shell can judge according to initial transmissions angle and emission process Satellite locator data, also can be provided by INS.The switching of the multiplexing feeding network of two-way adopts radio-frequency (RF) switch to complete, and control signal can adopt the power supply current potential be carried on feeder line.
The utility model is relative to prior art, and tool has the following advantages and effect:
1, adopt the multiplexing feeding network of switchable two-way, realize antenna pattern restructural, switch simple, with low cost, ensure that antenna dextrorotation gain pattern is partial to upper half-space all the time, upper half-space gain increases, the ability of receiving satellite signal strengthens, and is conducive to searching star and effective location fast.
2, adopt short circuit rod structure, avoid other holding wires of product top to the harmful effect of antenna pattern, reduce surface wave interference, improve the antijamming capability to ground based jammer.
3, adopt four feed feeds, improve antenna axial ratio bandwidth, improve directional diagram axial symmetry, be applicable to High Rotation Speed body.
4, adopt circular patch shape, realize better symmetry, realize antenna miniaturization.
Accompanying drawing explanation
Fig. 1 is structure cutaway view of the present utility model.
Fig. 2 is the structural representation of the utility model antenna body.
Fig. 3 is the schematic diagram of the multiplexing feeding network of the utility model two-way.
Embodiment
Below by embodiment, the utility model will be further described by reference to the accompanying drawings.As shown in Figures 1 to 3, specific embodiment of the utility model is a kind of directional image restructural satellite guidance antenna, comprise radome 2, antenna body PCB10, feed probes 7 and antenna patch 8, described antenna body PCB10 is arranged in radome 2, described antenna body PCB10 is divided into two-layer up and down, upper strata PCB3 is ceramic dielectric structure, ceramic dielectric structure upper surface is metal patch 8, described metal patch 8 is provided with the passive antenna of the micro-band forms of four feeds, the lower surface of lower floor PCB6 is the overall metal level applying copper, metal level is provided with the multiplexing feeding network 5 of two-way, amplifying circuit and filter circuit, the short circuit that circular plated-through hole realizes upper and lower surface metal level is provided with at PCB3 center, upper strata, at antenna body PCB take plated-through hole as symmetrical centre, be provided with four feed probes, 7, four feed probes 7 to be connected with the multiplexing feeding network 5 of two-way through antenna body PCB10.The multiplexing feeding network 5 of described two-way is by the first electric bridge B1, second electric bridge B2, 3rd electric bridge B3 and the 4th electric bridge B4 forms, and with the first electric bridge B1, 3rd electric bridge B3, second electric bridge B2, the signal combiner sequentially passing through microstrip line composition closed loop of the 4th electric bridge B4, wherein the first electric bridge B1 is connected two feed probes 7 all separately with on the second electric bridge B2, at the 3rd electric bridge B3, the first delivery outlet is set, 4th electric bridge B4 arranges the second delivery outlet, and two the microstrip line electrical length wherein the first electric bridge B1 connected are longer than two microstrip line 0.25 wavelength that the second electric bridge connects, the microstrip line length of described signal combiner 5 to four symmetric feeds probes 7 is identical.The 3dB electric bridge of four described electric bridges to be models be HC1400P03.Described radome 2 is arranged on the head of shell, is shell metal shell in the below of antenna body PCB10, and the top of antenna body PCB10 is shell nose fuze 4.
More than show and describe general principle of the present utility model, principal character and advantage, it is only the preferable examples that the utility model antenna is implemented, not any restriction is done to technical scope, the technical staff of the industry should understand, under the prerequisite not departing from intention spirit and scope of the present utility model, also have various changes and modifications, every above example is made according to technical spirit of the present utility model any trickle amendment, equivalent variations and modification, all still belong to the technical solution of the utility model scope.
Claims (4)
1. a directional diagram reconstructable satellite guidance antenna, comprise radome, antenna body PCB, feed probes and antenna patch, described antenna body PCB is arranged in radome, it is characterized in that described antenna body PCB is divided into two-layer up and down, upper strata PCB is ceramic dielectric structure, ceramic dielectric structure upper surface is metal patch, described metal patch is provided with the passive antenna of the micro-band forms of four feeds, the lower surface of lower floor PCB is the overall metal level applying copper, and metal level is provided with the multiplexing feeding network of two-way, amplifying circuit and filter circuit; The short circuit that circular plated-through hole realizes upper and lower surface metal level is provided with at PCB center, upper strata, be symmetrical centre with plated-through hole in antenna body PCB, be provided with four feed probes, four feed probes are connected with the multiplexing feeding network of two-way through antenna body PCB.
2. directional diagram reconstructable satellite guidance antenna according to claim 1, it is characterized in that the multiplexing feeding network of described two-way is by the first electric bridge, second electric bridge, 3rd electric bridge and the 4th electric bridge composition, and with the first electric bridge, 3rd electric bridge, second electric bridge, the signal combiner sequentially passing through microstrip line composition closed loop of the 4th electric bridge, wherein the first electric bridge with the second electric bridge is connected all separately two feed probes, at the 3rd electric bridge, the first delivery outlet is set, 4th electric bridge arranges the second delivery outlet, and two the microstrip line electrical length wherein the first electric bridge connected are longer than two microstrip line 0.25 wavelength that the second electric bridge connects, described signal combiner is identical to the microstrip line length of four symmetric feeds probes.
3. directional diagram reconstructable satellite guidance antenna according to claim 2, is characterized in that four described electric bridges to be models is the 3dB electric bridge of HC1400P03.
4. the directional diagram reconstructable satellite guidance antenna according to claim 1 or 2 or 3, is characterized in that described radome is arranged on the head of shell, is shell metal shell in the below of antenna body PCB, and the top of antenna body PCB is shell nose fuze.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520742847.7U CN205081243U (en) | 2015-09-24 | 2015-09-24 | Directional diagram restructural satellite guidance antenna |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520742847.7U CN205081243U (en) | 2015-09-24 | 2015-09-24 | Directional diagram restructural satellite guidance antenna |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205081243U true CN205081243U (en) | 2016-03-09 |
Family
ID=55433625
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520742847.7U Active CN205081243U (en) | 2015-09-24 | 2015-09-24 | Directional diagram restructural satellite guidance antenna |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205081243U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106532222A (en) * | 2016-11-14 | 2017-03-22 | 东南大学 | Built-in folded monopulse antenna |
| CN110190375A (en) * | 2019-04-24 | 2019-08-30 | 西安思丹德信息技术有限公司 | A kind of arrow load monopole telemetering transmitting antenna and the rocket based on it |
-
2015
- 2015-09-24 CN CN201520742847.7U patent/CN205081243U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106532222A (en) * | 2016-11-14 | 2017-03-22 | 东南大学 | Built-in folded monopulse antenna |
| CN106532222B (en) * | 2016-11-14 | 2019-02-22 | 东南大学 | Built-in folding monopulse antenna |
| CN110190375A (en) * | 2019-04-24 | 2019-08-30 | 西安思丹德信息技术有限公司 | A kind of arrow load monopole telemetering transmitting antenna and the rocket based on it |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2346291C2 (en) | Multiband radar facility | |
| CN112902756A (en) | Low-slow small-flight target designated point trapping method based on low-altitude rejection system | |
| CN107515391A (en) | Full frequency band unmanned plane signal accurately identifies, laterally with alignment system and method | |
| CN107328306A (en) | A kind of low slow small flight equipment counter devices and methods therefor | |
| CN103869347A (en) | Beidou satellite navigation and positioning system | |
| CN104880723B (en) | A kind of method and apparatus of single star DF and location Ground emitter signals | |
| CN205081243U (en) | Directional diagram restructural satellite guidance antenna | |
| CN114508966B (en) | Air-ground combined multi-level interception follow-up defense system | |
| CN108507577B (en) | A kind of mission planning method based on data-link and aircraft sensibility | |
| CN115063544A (en) | Radar detection power range calculation method for accompanying support interference | |
| CN108287341A (en) | A kind of Low Altitude Target Detection method and its system, electronic equipment | |
| CN107643514A (en) | A kind of array calibration method of buoy base/shipborne radar based on direct wave | |
| Gaoqian et al. | Radar netting technology & its development | |
| CN206330486U (en) | A kind of new low collateral damage unmanned vehicle blocking apparatus | |
| CN203759250U (en) | BeiDou navigation and positioning satellite system | |
| CN208508962U (en) | A kind of unmanned plane defence installation | |
| Cherneyak et al. | Radar in the Soviet Union and Russia: A brief historical outline | |
| Chen et al. | Distributed massive UAV jamming optimization algorithm with artificial bee colony | |
| CN103916145B (en) | Rotate feed radio telescope receiver system | |
| US20230273324A1 (en) | System to Mitigate hit precision of Cruise Missiles ( CMMS ) | |
| CN104569967A (en) | 8 mm one-dimensional phase scanning system cruise radar | |
| RU2226278C2 (en) | Method of counteraction to air defense aids and device for its realization | |
| CN117554953B (en) | Control method and system of flying target prevention and control system | |
| Ren et al. | UAV Swarm Cooperative Penetration Electronic countermeasures technology modeling and application | |
| Jin et al. | Application of Acoustic Detection Technology in Reconnaissance Warning Equipments |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 314001 No.398 Zhenye Road, Nanhu District, Jiaxing City, Zhejiang Province Patentee after: ZHEJIANG JINYICHANG TECHNOLOGY CO.,LTD. Address before: 314100 Jiashan Avenue, Jiashan County, Jiaxing, Zhejiang 1897 Patentee before: JIASHAN JINCHANG ELECTRONICS CO.,LTD. |