CN107706541A - A kind of supersonic speed missile-borne combined type omnidirectional telemetering antenna - Google Patents
A kind of supersonic speed missile-borne combined type omnidirectional telemetering antenna Download PDFInfo
- Publication number
- CN107706541A CN107706541A CN201710627163.6A CN201710627163A CN107706541A CN 107706541 A CN107706541 A CN 107706541A CN 201710627163 A CN201710627163 A CN 201710627163A CN 107706541 A CN107706541 A CN 107706541A
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- antenna
- quadrant
- combined type
- missile
- telemetering
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q21/00—Antenna arrays or systems
- H01Q21/0006—Particular feeding systems
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/50—Structural association of antennas with earthing switches, lead-in devices or lightning protectors
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/52—Means for reducing coupling between antennas; Means for reducing coupling between an antenna and another structure
- H01Q1/521—Means for reducing coupling between antennas; Means for reducing coupling between an antenna and another structure reducing the coupling between adjacent antennas
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q21/00—Antenna arrays or systems
- H01Q21/24—Combinations of antenna units polarised in different directions for transmitting or receiving circularly and elliptically polarised waves or waves linearly polarised in any direction
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q5/00—Arrangements for simultaneous operation of antennas on two or more different wavebands, e.g. dual-band or multi-band arrangements
- H01Q5/20—Arrangements for simultaneous operation of antennas on two or more different wavebands, e.g. dual-band or multi-band arrangements characterised by the operating wavebands
Abstract
A kind of supersonic speed missile-borne combined type omnidirectional telemetering antenna, is related to missile-borne telemetering antenna field；Including body and four quadrant antennas, four quadrant antennas are respectively first quartile antenna, the second quadrant antenna, third quadrant antenna and fourth quadrant antenna；Wherein, body outer wall is taper barrel-like structure；Four quadrant antenna symmetries are fixedly mounted on the outer wall of body, and the angle of two neighboring quadrant antenna is 90 °.Four quadrant antennas are located normal on the same plane of body, and from projectile tail to bullet direction, and first quartile antenna, the second quadrant antenna, third quadrant antenna and fourth quadrant antenna are along arranged clockwise；In the groove on the surface that 4 quadrant antennas are fixedly mounted on body, and the upper surface of antenna house smoothly transits with body；Present invention, avoiding being operated in large-sized supports that interference situation occurs frequently because multiple antennas is same, the loss for causing signal in overlapping region is avoided；Reduce the structural requirements such as antenna section, body surface be conformal.
Description
Technical field
The present invention relates to a kind of missile-borne telemetering antenna field, particularly a kind of supersonic speed missile-borne combined type omnidirectional's remote measurement day
Line.
Background technology
In modern high technology local war, such as the Gulf War, Kosovo War, Afghan War and nearest Yi La
Gram war and Libyan War, medium and long distance missile attack turn into one of main effective strike means.Guided missile is that one kind can
The unmanned vehicle of control, it is internal be equipped with warhead, and the main distinction of it and other conventional weapons is that technical staff can root
According to needing to guide guided missile to fly by desired trajectory, and guidance system more accurately hit can be passed through.
In desired trajectory in-flight, field technicians obtain the data such as its state of flight to guided missile by missile-borne telemetering antenna
Information.Data-Link is most important on future battlefield, and the aeronautical data catenary system using missile-borne, airborne data link as representative is various
Important part in data catenary system.
In recent years, as modern high technology war improves constantly to the performance requirement of guided missile, and the environment that guided missile is special,
More special requirements are proposed to missile-borne telemetering antenna：First, in order to reduce the mechanical characteristic to guided missile, mechanical structure and strong
The influence of degree, it is desirable to which missile-borne telemetering antenna can be conformal with body；, to adapt to point to change by the motor-driven antenna brought of body
The directional diagram of missile-borne telemetering antenna is asked to have fixed covering power, that is, the characteristic for possessing wave beam forming.
In the prior art, also realize that missile-borne telemetering antenna can be conformal with body without corresponding design；Can not
Ensure that missile-borne telemetering antenna possesses the characteristic of wave beam forming.
The content of the invention
It is an object of the invention to overcome the above-mentioned deficiency of prior art, there is provided a kind of supersonic speed missile-borne combined type omnidirectional is distant
Observation line, avoid and interference situation occurs because multiple antennas is operated in large-sized supports together frequently, avoid in overlapping region
Cause the loss of signal；Reduce the structural requirements such as antenna section, body surface be conformal.
The above-mentioned purpose of the present invention is achieved by following technical solution：
A kind of supersonic speed missile-borne combined type omnidirectional telemetering antenna, including body and four quadrant antennas, four quadrant antennas
Respectively first quartile antenna, the second quadrant antenna, third quadrant antenna and fourth quadrant antenna；Wherein, body outer wall is cone
Shape barrel-like structure；Four quadrant antenna symmetries are fixedly mounted on the outer wall of body, and the angle of two neighboring quadrant antenna is 90 °.
In a kind of above-mentioned supersonic speed missile-borne combined type omnidirectional telemetering antenna, four quadrant antennas are located normal to body
On same plane, and from projectile tail to bullet direction, first quartile antenna, the second quadrant antenna, third quadrant antenna and four-quadrant
Antenna is limited along arranged clockwise.
In a kind of above-mentioned supersonic speed missile-borne combined type omnidirectional telemetering antenna, four quadrant antennas are micro-strip day
Line.
In a kind of above-mentioned supersonic speed missile-borne combined type omnidirectional telemetering antenna, the first quartile antenna, the second quadrant day
Line, third quadrant antenna and fourth quadrant antenna include antenna radiation unit, antenna feeding network, antenna base, SMA sockets
And antenna house；The antenna base is ladder platy structure；One side of antenna base is provided with the groove of projection；Antenna spoke
It is rectangular plate-like structure to penetrate unit；Antenna radiation unit level is fixedly mounted in the groove of antenna base；Antenna radiation unit
Antenna feeding network is provided between antenna base groove floor；One side of antenna base is installed with cylinder
SMA sockets；The top of radome antenna radiating element, and the base of antenna house is fixedly mounted on the upper surface of body.
In a kind of above-mentioned supersonic speed missile-borne combined type omnidirectional telemetering antenna, the antenna house is rectangular plate-like structure, and
It is provided with rectangular recess；Antenna house a length of 128-132mm, a width of 108-112mm, a height of 25-30mm；The a length of 108- of groove
112mm, a width of 98-102mm, depth 13-17mm.
In a kind of above-mentioned supersonic speed missile-borne combined type omnidirectional telemetering antenna, the antenna feeding network is H types gap coupling
Feed rectangular microband paste antenna unit is closed, polarization mode is that the feed of two 90 ° of phase differences produces circular polarisation.
In a kind of above-mentioned supersonic speed missile-borne combined type omnidirectional telemetering antenna, the antenna house is ceramics or quartz glass material
Material；Realize that the temperature of four quadrant antennas is less than or equal to 150 DEG C.
In above-mentioned missile-borne combined type omnidirectional remote measurement fourth quadrant antenna, the surface of the body is provided with and quadrant antenna
Corresponding groove；First quartile antenna, the second quadrant antenna, third quadrant antenna and fourth quadrant antenna are fixedly mounted on body
Surface groove in, and the upper surface of antenna house smoothly transits with body surface.
In above-mentioned missile-borne combined type omnidirectional remote measurement fourth quadrant antenna, each quadrant antenna is along body circumference cone of coverage
Spend for -60 °~+60 °；The overlapping angle of adjacent quadrants antenna is 30 °；Each quadrant antenna plays direction of principal axis angle of coverage along vertical
For -45 °~+45 °, gain >=-10dBi.
In above-mentioned missile-borne combined type omnidirectional remote measurement fourth quadrant antenna, the work of first quartile antenna and third quadrant antenna
Working frequency is 2100-2300MHz；The working frequency of second quadrant antenna and fourth quadrant antenna is 2300-2500MHz.
The present invention has the following advantages that compared with prior art：
(1) present invention uses the antenna combination mode of two kinds of different frequencies, and cross is staggered installation of, and passes through each quadrant antenna
Wave cover angular domain formed along the circumferential covering of 360 ° of body, this method can be avoided because multiple antennas the same as being operated in big chi frequently
Interference situation occurs on very little carrier, causes Partial angle gain to be less than index request, you can to avoid causing in overlapping region
The loss of signal, and the method is easily realized in engineering；
(2) present invention uses microstrip antenna form, while takes " H " type aperture-coupled mode to carry out broadening work band
Width, reduce the structural requirements such as antenna section, body surface be conformal.
Brief description of the drawings
Fig. 1 is the distribution schematic diagram of the adherent installation antenna in body surface of the present invention；
Fig. 2 is inventive antenna size and mounting interface schematic diagram；
Fig. 3 is inventive antenna cover appearance and size schematic diagram；
Fig. 4 is the present invention one, third quadrant antenna and two, fourth quadrant antenna beam scope complementary type；
Fig. 5 is modular antenna compound direction figure of the present invention.
Embodiment
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings：
The present invention proposes a kind of brand-new missile-borne omnidirectional telemetering antenna combination, its task be by radio-frequency carrier signal earthward
Stand transmitting, when guided missile is hit, ground station transmits information, it requires that guided missile is remained when a range of motor-driven
Communication link between ground control station.Posture kept stable, is opened after atmosphere reenters before guided missile atmosphere reenters
Begin to rotate, because telemetry system can not obtain missile attitude information, in order to ensure that communication link does not interrupt, it is necessary to using omnidirectional antennas
Line design.All stage normal works that remote-measuring equipment will may occur in interception on bullet, therefore antenna and equipment can not
Installed in engine section, it can be only installed at and reenter part；In order to keep reentering the good aerodynamic configuration in part, antenna must with again
Enter part body syntype.
The present invention utilizes the gain features of antenna radiation pattern itself, and gain is stronger on main lobe direction, with beam area
Increase gain is gradually successively decreased, if opposite scan from the edge angular domain of antenna beam scope to main lobe direction, gain gradually strengthens.
Determine to be operated in different frequencies respectively from two, fourth quadrant antenna using one, three, weaken antenna and interfere with each other the shadow brought
Ring.One, third quadrant Antenna Operation frequency gain is set to be unsatisfactory for index angular regions as two, fourth quadrant antenna work by design
Make frequency gain and meet index region, i.e., each quadrant antenna circumference beam area control is in ± 60 °, angle overlapping region
30°.The mode supplemented by different frequent points gain circumferentially 360 ° of scopes can be attained by gain index.But due to body
Rotation causes frequency handover, and ground receiver needs in frequency handover signal capture again, is needed from signal is obtained to signal capture
Time about 20ms is wanted, calculating 20ms times body according to body rotating speed rotates most angle no more than 20 °, therefore the frequency of Antenna Operation two
Point meets that the angle overlapping region of technical indicator gain need to be not less than 20 °, allows signal recapture when can have enough, establishes
Link, to ensure to rise in body, to be threaded through journey link unimpeded.
It is as shown in Figure 1 the distribution schematic diagram of the adherent installation antenna in body surface, as seen from the figure, a kind of supersonic speed missile-borne group
Box-like omnidirectional's telemetering antenna, it is characterised in that：Including body 1 and four quadrant antennas, four quadrant antennas be respectively first as
Limit antenna 2, the second quadrant antenna 3, third quadrant antenna 5 and fourth quadrant antenna 4；Wherein, the outer wall of body 1 is taper tubbiness knot
Structure；Four quadrant antenna symmetries are fixedly mounted on the outer wall of body 1, and the angle of two neighboring quadrant antenna is 90 °.And body 1
Surface be provided with groove corresponding with quadrant antenna；First quartile antenna 2, the second quadrant antenna 3, the and of third quadrant antenna 5
Fourth quadrant antenna 4 is fixedly mounted in the groove on the surface of body 1, and the upper surface of antenna house 10 and the surface of body 1 are smooth
Transition.
Wherein, four quadrant antennas are located normal on the same plane of body 1, and from projectile tail to bullet direction, first
Quadrant antenna 2, the second quadrant antenna 3, third quadrant antenna 5 and fourth quadrant antenna 4 are along arranged clockwise；And four quadrant days
Line is microstrip antenna.The working frequency of first quartile antenna 2 and third quadrant antenna 5 is 2100-2300MHz；Second quadrant
The working frequency of antenna 3 and fourth quadrant antenna 4 is 2300-2500MHz.
Antenna size and mounting interface schematic diagram are illustrated in figure 2, as seen from the figure, first quartile antenna 2, the second quadrant day
Line 3, third quadrant antenna 5 and fourth quadrant antenna 4 include antenna radiation unit 6, antenna feeding network 7, antenna base 8,
SMA sockets 9 and antenna house 10；The antenna base 8 is ladder platy structure；One side of antenna base 8 is provided with projection
Groove；Antenna radiation unit 6 is rectangular plate-like structure；The level of antenna radiation unit 6 is fixedly mounted on the groove of antenna base 8
It is interior；Antenna feeding network 7 is provided between antenna radiation unit 6 and the groove floor of antenna base 8；One side of antenna base 8
Face is installed with cylindrical SMA sockets 9；The top of the antenna radiation unit 6 of antenna house 10, and peace is fixed on the base of antenna house 10
Mounted in the upper surface of body 1.Wherein, antenna feeding network 7 is H type aperture-coupled rectangular microband paste antenna units, pole
Change mode is that the feed of two 90 ° of phase differences produces circular polarisation.
Antenna house appearance and size schematic diagram is illustrated in figure 3, as seen from the figure, antenna house 10 is rectangular plate-like structure, and is set
It is equipped with rectangular recess；Antenna house 10 a length of 128-132mm, a width of 108-112mm, a height of 25-30mm；The a length of 108- of groove
112mm, a width of 98-102mm, depth 13-17mm.
Antenna house 10 is ceramics or silica glass material；Realize that the temperature of four quadrant antennas is less than or equal to 150 DEG C.
The present invention one, third quadrant antenna and two, fourth quadrant antenna beam scope complementary type are illustrated in figure 4, by
Figure understand, each quadrant antenna along body circumference angle of coverage be -60 °~+60 °；The overlapping angle of adjacent quadrants antenna is
30°；Each quadrant antenna is -45 °~+45 ° along the vertical direction of principal axis angle of coverage that plays, gain >=-10dBi.According to use demand
The working method used with antenna, it is desirable to be able to realize circumferential 360 ° cover all around.But because bullet has reentered rotation, it is used to
Guiding systems can not provide effective attitude information.If antenna scheme is angularly distributed along bullet week using multiple antennas while same frequency
The scheme of work, the directional diagram that multiple antennas finally synthesize the depressed area of gain can occur in two antenna radiation pattern intersections,
The antenna gain index of gain depressed area can be less than system requirements index, and in antenna gain depressed area, losing lock occurs in system link
State.For the relatively low situation of gain of above-mentioned antenna gain depressed area, comprehensive analysis is carried out to system work, if four days
Line is operated in two different frequencies, it is assumed that the Antenna Operation of first and third quadrant is in F1 frequencies, the frequency range of F1 frequencies
2100-2300MHz；And the Antenna Operation of second, four-quadrant, in F2 frequencies, the frequency range of F2 frequencies is 2300-2500MHz；
And it is ± 60 ° that two antennas per frequency, which circumferentially cover angular domain, such two groups of frequency antenna radiation patterns can carry out space combination, hand over
Folded angular domain is 30 °.Equivalent to the data link that two different frequent points are established between vacant lot, while two pairs of antennas can be avoided
Lowest gain point overlaps, the signal received from any mobile TT ＆ C station in ground for time domain angle be it is continuous, it is continual.
Modular antenna compound direction figure is illustrated in figure 5, as seen from the figure, when system operating mode works for dual-frequency point
When, it is assumed that first blind spot of system work is the antenna for being operated in F1 frequencies, as can be seen from the figure when antenna is operated in A
Point, now system is in out-of-lock condition, and the telemetered signal for being operated in F2 frequencies is substantially at transmitting antenna maximum gain in A points
Area.Now F1 frequencies telemetered signal is lock-out state, and mobile TT ＆ C station can receive telemetered signal and be demodulated, and obtain remote measurement
Information.For Antenna Operation in B points, antenna gain is more than -10dBi, and ground maneuver tracking telemetry and command station reception device starts to capture signal, caught
It is about 20ms to obtain the time.When missile spin, maximum (top) speed is 1080 °/s, and antenna beam angle corresponding to capture time is 20 °,
That is Antenna Operation is operated in the telemetered signal acquisition success of F1 frequencies at C point positions, and now F1 frequencies telemetered signal locks.
And the telemetered signal in A points to C points section F2 frequencies always works at lock-out state.Until in the arrival of next blind area, entrance
State circulation.According to above-mentioned analysis, ground only needs a mobile TT ＆ C station to receive and demodulated continuously to believe in a time domain
Number, no interruption.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (10)
- A kind of 1. supersonic speed missile-borne combined type omnidirectional telemetering antenna, it is characterised in that：Including body (1) and four quadrant antennas, Four quadrant antennas are respectively first quartile antenna (2), the second quadrant antenna (3), third quadrant antenna (5) and fourth quadrant day Line (4)；Wherein, body (1) outer wall is taper barrel-like structure；Four quadrant antenna symmetries are fixedly mounted on the outer wall of body (1), The angle of two neighboring quadrant antenna is 90 °.
- A kind of 2. supersonic speed missile-borne combined type omnidirectional telemetering antenna according to claim 1, it is characterised in that：Four quadrants Antenna is located normal on the same plane of body (1), and from projectile tail to bullet direction, first quartile antenna (2), the second quadrant Antenna (3), third quadrant antenna (5) and fourth quadrant antenna (4) are along arranged clockwise.
- A kind of 3. supersonic speed missile-borne combined type omnidirectional telemetering antenna according to claim 2, it is characterised in that：Described four Quadrant antenna is microstrip antenna.
- A kind of 4. supersonic speed missile-borne combined type omnidirectional telemetering antenna according to claim 3, it is characterised in that：Described first Quadrant antenna (2), the second quadrant antenna (3), third quadrant antenna (5) and fourth quadrant antenna (4) include aerial radiation list First (6), antenna feeding network (7), antenna base (8), SMA sockets (9) and antenna house (10)；The antenna base (8) is rank Terraced platy structure；One side of antenna base (8) is provided with the groove of projection；Antenna radiation unit (6) is rectangular plate-like knot Structure；Antenna radiation unit (6) level is fixedly mounted in the groove of antenna base (8)；Antenna radiation unit (6) and antenna base (8) antenna feeding network (7) is provided between groove floor；One side of antenna base (8) is installed with cylindrical SMA Socket (9)；The top of antenna house (10) antenna radiation unit (6), and the base of antenna house (10) is fixedly mounted on body (1) Upper surface.
- A kind of 5. supersonic speed missile-borne combined type omnidirectional telemetering antenna according to claim 4, it is characterised in that：The antenna It is rectangular plate-like structure to cover (10), and is provided with rectangular recess；Antenna house (10) a length of 128-132mm, a width of 108-112mm, A height of 25-30mm；Groove a length of 108-112mm, a width of 98-102mm, depth 13-17mm.
- A kind of 6. supersonic speed missile-borne combined type omnidirectional telemetering antenna according to claim 4, it is characterised in that：The antenna Feeding network (7) is H type aperture-coupled rectangular microband paste antenna units, and polarization mode is the feedback of two 90 ° of phase differences Electricity produces circular polarisation.
- A kind of 7. supersonic speed missile-borne combined type omnidirectional telemetering antenna according to claim 5, it is characterised in that：The antenna (10) are covered for ceramics or silica glass material；Realize that the temperature of four quadrant antennas is less than or equal to 150 DEG C.
- 8. missile-borne combined type omnidirectional remote measurement fourth quadrant antenna according to claim 4, it is characterised in that：The body (1) surface is provided with groove corresponding with quadrant antenna；First quartile antenna (2), the second quadrant antenna (3), third quadrant In the groove on the surface that antenna (5) and fourth quadrant antenna (4) are fixedly mounted on body (1), and the upper surface of antenna house (10) Smoothly transitted with body (1) surface.
- 9. missile-borne combined type omnidirectional remote measurement fourth quadrant antenna according to claim 8, it is characterised in that：Each quadrant day Line along body circumference angle of coverage be -60 °~+60 °；The overlapping angle of adjacent quadrants antenna is 30 °；Each quadrant antenna edge The vertical direction of principal axis angle of coverage that plays is -45 °~+45 °, gain >=-10dBi.
- 10. missile-borne combined type omnidirectional remote measurement fourth quadrant antenna according to claim 1, it is characterised in that：First quartile The working frequency of antenna (2) and third quadrant antenna (5) is 2100-2300MHz；Second quadrant antenna (3) and fourth quadrant day The working frequency of line (4) is 2300-2500MHz.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710627163.6A CN107706541B (en) | 2017-07-28 | 2017-07-28 | A kind of supersonic speed missile-borne combined type omnidirectional telemetering antenna |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710627163.6A CN107706541B (en) | 2017-07-28 | 2017-07-28 | A kind of supersonic speed missile-borne combined type omnidirectional telemetering antenna |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107706541A true CN107706541A (en) | 2018-02-16 |
| CN107706541B CN107706541B (en) | 2019-11-12 |
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| CN201710627163.6A Active CN107706541B (en) | 2017-07-28 | 2017-07-28 | A kind of supersonic speed missile-borne combined type omnidirectional telemetering antenna |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110808479A (en) * | 2019-10-30 | 2020-02-18 | 中国空空导弹研究院 | Missile-borne integrated conformal communication antenna |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101621158A (en) * | 2009-08-14 | 2010-01-06 | 南京伏欧安电子技术有限公司 | Taper conformal omnidirectional double-frequency micro-strip antenna array |
| WO2010029125A1 (en) * | 2008-09-12 | 2010-03-18 | Advanced Automotive Antennas, S.L. | Flush-mounted low-profile resonant hole antenna |
| CN203300804U (en) * | 2013-04-03 | 2013-11-20 | 上海航天测控通信研究所 | Low-profile broad-beam rocket-borne or missile-borne antenna |
| CN105305027A (en) * | 2015-11-19 | 2016-02-03 | 广东盛路通信科技股份有限公司 | Missile-borne conformal microstrip antenna |
-
2017
- 2017-07-28 CN CN201710627163.6A patent/CN107706541B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010029125A1 (en) * | 2008-09-12 | 2010-03-18 | Advanced Automotive Antennas, S.L. | Flush-mounted low-profile resonant hole antenna |
| CN101621158A (en) * | 2009-08-14 | 2010-01-06 | 南京伏欧安电子技术有限公司 | Taper conformal omnidirectional double-frequency micro-strip antenna array |
| CN203300804U (en) * | 2013-04-03 | 2013-11-20 | 上海航天测控通信研究所 | Low-profile broad-beam rocket-borne or missile-borne antenna |
| CN105305027A (en) * | 2015-11-19 | 2016-02-03 | 广东盛路通信科技股份有限公司 | Missile-borne conformal microstrip antenna |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110808479A (en) * | 2019-10-30 | 2020-02-18 | 中国空空导弹研究院 | Missile-borne integrated conformal communication antenna |
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| CN107706541B (en) | 2019-11-12 |
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