CN104986348B - A kind of radar assembly and the aircraft with which - Google Patents
A kind of radar assembly and the aircraft with which Download PDFInfo
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- CN104986348B CN104986348B CN201510350623.6A CN201510350623A CN104986348B CN 104986348 B CN104986348 B CN 104986348B CN 201510350623 A CN201510350623 A CN 201510350623A CN 104986348 B CN104986348 B CN 104986348B
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- radar
- radome
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Abstract
The invention discloses a kind of radar assembly and the aircraft with which.The radar assembly is arranged on the aircraft, the radar assembly includes the radar supports in radome, turntable, radome and radar front, wherein, the radome, radar supports and radar front are arranged on turntable, the turntable can be rotated relative to the aircraft, detection window is provided with the radome, the radar assembly is further included：Infrared radar, its are arranged on inside the radome, and are supported by radar supports, and the detecting head of infrared radar can be by the space of the outside of the detection window detection radar cover of setting on radome.In the radar assembly of the present invention, the detecting head of infrared radar can be by the space outside the detection window detection radar cover of setting on radome.With respect to prior art, the present invention is integrated with radar by infrared radar, it is therefore prevented that infrared radar protrudes from body, will not produce impact to the performance of the aerodynamic force of aircraft and aircraft.
Description
Technical field
The present invention relates to Radar Technology field used by aircraft, more particularly to a kind of radar assembly and the aircraft with which.
Background technology
In prior art, IRDS is typically mounted on the machine nose position of aircraft, and installing has following lacking in this position
Point：
1., as IRDS can project body, the aerodynamic characteristic of aircraft can be affected；
2. IRDS blocking due to body, it is impossible to realize 360 ° of detections of circumference.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
Content of the invention
It is an object of the invention to provide a kind of radar assembly come overcome or at least mitigate prior art at least one on
State defect.
For achieving the above object, the present invention provides a kind of radar assembly.The radar assembly is arranged aboard, the thunder
Reach radar supports and radar front that assembly is included in radome, turntable, radome, wherein, the radome, radar supports
And radar front is arranged on turntable, the turntable can be rotated relative to the aircraft, and described radome (2) are disc thunder
Cover is reached, on the radome, detection window is provided with, the detection window (3) is arranged at the outer rim of the disc radome, and
And described detection window (3) are two, the radar assembly is further included：Infrared radar, the quantity of infrared radar (4)
For two, the infrared radar is arranged on inside the radome, and is supported by the radar supports, is specifically located at respectively each
The corresponding position of individual detection window (3), the detecting head of the infrared radar can be by the detection of setting on the radome
Window detects the space of the outside of the radome.
Preferably, two detection windows are arranged along the outer rim of the radome, and are separated by 180 degree.
Preferably, the infrared radar is capable of the direction of rotation of relatively described radome and does elevating movement, makes described infrared
The investigative range of the detecting head of radar is 0 degree to 180 degree.
Preferably, the detection window is sized such that the detecting head on the infrared radar is equal in its investigative range
The situation of the outside of the radome can be detected.
Preferably, the detection window is made with infrared glass material.
Present invention also offers a kind of aircraft, the aircraft has radar assembly as above.
Preferably, the aircraft is prior-warning plane, and the radar assembly is arranged at the empennage of the prior-warning plane.
In the radar assembly of the present invention, infrared radar is arranged on inside radome, and is supported by radar supports, infrared thunder
The detecting head for reaching can be by the space outside the detection window detection radar cover of setting on radome.With respect to prior art,
The present invention is integrated with radar by infrared radar, it is therefore prevented that infrared radar protrudes from body, to the aerodynamic force of aircraft and will not fly
The performance of machine produces impact.
Description of the drawings
Fig. 1 is the structural representation of the radar assembly in one embodiment of the invention.
Reference：
| 1 | Radar front | 4 | Infrared radar |
| 2 | Radome | 5 | Turntable |
| 3 | Detection window |
Specific embodiment
For making purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary, it is intended to use
In the explanation present invention, and it is not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment obtained under the premise of creative work is not made by member, belongs to the scope of protection of the invention.Under
Face combines accompanying drawing and embodiments of the invention is described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinal direction ", " horizontal ", "front", "rear",
The orientation of instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " or position relationship be based on accompanying drawing institute
The orientation for showing or position relationship, are for only for ease of the description present invention and simplify description, rather than the dress of instruction or hint indication
Put or element must be with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that protecting to the present invention
The restriction of scope.
Generally, radar assembly is arranged aboard, and radar assembly includes the radar supports in radome, turntable, radome
And radar front, wherein, radome, radar supports and radar front are arranged on turntable, and the turntable can be with respect to institute
State aircraft rotation.
In the radar assembly of the present invention, detection window is provided with radome, and is further included：Infrared radar, described
Infrared radar is arranged on inside the radome, and is supported by the radar supports, and the detecting head of the infrared radar can lead to
Cross the space that the detection window arranged on the radome detects the outside of the radome.
In the radar assembly of the present invention, infrared radar is arranged on inside radome, and is supported by radar supports, infrared thunder
The detecting head for reaching can be by the space outside the detection window detection radar cover of setting on radome.With respect to prior art,
The present invention is integrated with radar by infrared radar, it is therefore prevented that infrared radar protrudes from body, to the aerodynamic force of aircraft and will not fly
The performance of machine produces impact.
Fig. 1 is the structural representation of the radar assembly in one embodiment of the invention.
In the radar assembly shown in Fig. 1, radar assembly includes radar front 1, radome 2, detection window 3, infrared thunder
Reach 4, radar supports and turntable 5.Wherein, radome 2, radar supports and radar front 1 are arranged on turntable 5, described turn
Platform can be rotated relative to aircraft, so that the relatively described aircraft rotation of above-mentioned radome 2, radar supports and radar front 1
Turn, in the present embodiment, above-mentioned rotates to be 360 degree of rotations, i.e., can carry out 360 degree of rotation relative to aircraft.
Referring to Fig. 1, in the present embodiment, infrared radar 4 is arranged on inside radome 2, and is supported by radar supports, infrared
The detecting head of radar 4 can be by the space of the outside of the 3 detection radar cover 2 of detection window of setting on radome 2.It is appreciated that
, as infrared radar 4 is arranged on radar supports, therefore, infrared radar 4 equally can be rotated relative to aircraft.Due to above-mentioned
Radome 2, radar supports and radar front be rotated by turntable, therefore, above-mentioned all parts are synchronous rotary,
Relative position relation between its all parts will not change because of rotation.Referring to Fig. 1, in the present embodiment, two detections
Window 3 is arranged along the outer rim of radome 2, and is separated by 180 degree.
Using this structure, the infrared radar 4 being arranged on inside radome 2 can be made to pass through 3 detection radar of detection window
The space of the outside of cover 2, and due to above-mentioned all parts meeting synchronous rotary, therefore, above-mentioned infrared radar 4 can pass through
Above-mentioned rotation and carry out 360 degree of omnidirectional detection.
Referring to Fig. 1, in the present embodiment, radome 2 is disc for the profile of disc radome, i.e. radome, visits
Survey window 3 to be arranged at the outer rim of disc radome.It is understood that the shape of radome can be set as desired
Meter.For example, the shape of radome can be square or oval.Advantageously, its mid diameter of disc radome is maximum,
And to two ends shrink, using this shape, farthest can reduce aircraft operationally air-flow to the disc radar
The impact of cover.
Referring to Fig. 1, in the present embodiment, two detection windows 3 on radome 2, are provided with, the quantity of infrared radar 4 is two
Individual, and the correspondence position of a detection window 3 is separately positioned on, so that each infrared radar 4 is visited by a detection window 3
Survey the situation of the outside of radome 2.
Using this structure, during the rotation that above-mentioned all parts can be made to carry out 360 degree, it is permissible often to rotate 180 degree
Infrared radar 4 is made to detect the situation outside the radome under 360 degree of scopes.
It is understood that the quantity of the quantity of infrared radar 4 and corresponding detection window 3 can be as needed
And arrange.For example, it is possible to arrange 1,3 or more.
Referring to Fig. 1, in the present embodiment, each infrared radar 4 can do pitching fortune with respect to the direction of rotation of radome 2
Dynamic, the investigative range for making the detecting head of infrared radar 4 is 0 degree to 180 degree.And detection window 3 is sized such that infrared radar 4
On detecting head be all capable of the situation of the outside of detection radar cover 2 in its investigative range.Specifically, the size energy of detection window
The elevation angle for enough making above-mentioned infrared radar 4 be 90 degree or the angle of depression for 90 degree when, can equally detect the outside of radome 2
Space.
Using this structure so that the infrared radar 4 in the radar assembly of the present invention can not only be along above-mentioned radome 2
Direction of rotation carry out 360 degree of detection, additionally it is possible to carry out the detection of 180 degree in corresponding pitch orientation, and pass through two red
The cooperation of outer radar 4, the infrared radar 4 for enabling to the radar assembly of the present invention carry out omnibearing 360 degree of detection.
In the present embodiment, detection window 3 is made with infrared glass material, to ensure in aircraft flight, will not be due to
Air pressure or the impact of other power so that situations such as detection window 3 is damaged occurs.It is understood that detection window 3 is acceptable
Made using other materials.For example, spinelle (MgAl2O4) optical clear pottery etc..As long as this material can be passed through in wave band
The requirement of infrared radar is met in property, and meets the requirement of aerodynamic loading and inertial load in mechanical strength.
Present invention also offers a kind of aircraft, the aircraft includes radar assembly as above.
Advantageously, the aircraft is prior-warning plane, and the radar assembly is arranged at the empennage of the prior-warning plane.
Last it is to be noted that：Above example only in order to technical scheme to be described, rather than a limitation.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：Which is still
Technical scheme described in foregoing embodiments can be modified, or equivalent is carried out to which part technical characteristic and replace
Change；And these modifications or replacement, do not make the essence of appropriate technical solution depart from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (7)
1. a kind of radar assembly, the radar assembly are arranged aboard, and the radar assembly includes radome (2), turntable
(5) radar supports, in radome and radar front (1), wherein, radome (2), radar supports and radar front
(1) it is arranged on turntable (5), turntable (5) can be rotated relative to the aircraft, it is characterised in that radome (2) are
Disc radome, is provided with detection window (3) on the radome (2), the detection window (3) is arranged on the disc radar
At the outer rim of cover, and the detection window (3) is two, and the radar assembly is further included：
Infrared radar (4), the quantity of infrared radar (4) is two, and the infrared radar (4) is arranged on the radome (2)
Inside, and supported by the radar supports, it is specifically located at the corresponding position of each detection window (3) respectively, described red
The detecting head of outer radar (4) can detect radome (2) by described radome (2) the upper detection window (3) for arranging
Outside space.
2. radar assembly as claimed in claim 1, it is characterised in that two detection window (3) are along the radome (2)
Outer rim arrange, and be separated by 180 degree.
3. radar assembly as claimed in claim 2, it is characterised in that infrared radar (4) being capable of relatively described radome
(2) elevating movement is done in direction of rotation, and the investigative range for making the detecting head of the infrared radar (4) is 0 degree to 180 degree.
4. radar assembly as claimed in claim 3, it is characterised in that detection window (3) are sized such that described red
Detecting head on outer radar (4) can all detect the situation of the outside of the radome (2) in its investigative range.
5. radar assembly as claimed in claim 4, it is characterised in that detection window (3) are made with infrared glass material.
6. a kind of aircraft, it is characterised in that the aircraft has the radar assembly as described in any one in claim 1 to 5.
7. aircraft as claimed in claim 6, it is characterised in that the aircraft is prior-warning plane, the radar assembly is arranged on
At the empennage of the prior-warning plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510350623.6A CN104986348B (en) | 2015-06-23 | 2015-06-23 | A kind of radar assembly and the aircraft with which |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510350623.6A CN104986348B (en) | 2015-06-23 | 2015-06-23 | A kind of radar assembly and the aircraft with which |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104986348A CN104986348A (en) | 2015-10-21 |
| CN104986348B true CN104986348B (en) | 2017-03-08 |
Family
ID=54298281
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510350623.6A Active CN104986348B (en) | 2015-06-23 | 2015-06-23 | A kind of radar assembly and the aircraft with which |
Country Status (1)
| Country | Link |
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| CN (1) | CN104986348B (en) |
Citations (8)
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| GB582257A (en) * | 1944-06-17 | 1946-11-11 | Hughes Henry & Son Ltd | Improvements in and relating to stabilised radar scanner equipment mounted on vehicles of all kinds |
| CN2598166Y (en) * | 2002-12-31 | 2004-01-07 | 中国科学院电子学研究所 | Double frequency co-face microband array aerial |
| CN102692163A (en) * | 2011-03-25 | 2012-09-26 | 哈尔滨开恩科技开发有限公司 | Jellyfish mine |
| CN202661061U (en) * | 2012-05-10 | 2013-01-09 | 上海慧昌智能交通系统有限公司 | Protractor adjustable in angle |
| CN102882002A (en) * | 2012-09-27 | 2013-01-16 | 中国科学院长春光学精密机械与物理研究所 | Composite frequency-selective-surface invisible radome |
| CN103376451A (en) * | 2012-04-16 | 2013-10-30 | 中国科学院电子学研究所 | Airborne double-waveband synthetic aperture radar system and method for measuring vegetation thickness utilizing same |
| CN103765672A (en) * | 2011-06-27 | 2014-04-30 | 空中客车运营简化股份公司 | Method of opening a protective dome, in particular a radome, and radome equipped with a pantograph for implementation thereof |
| CN104332705A (en) * | 2014-10-16 | 2015-02-04 | 西安电子工程研究所 | Integral type airborne millimeter wave radar antenna cover |
-
2015
- 2015-06-23 CN CN201510350623.6A patent/CN104986348B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB582257A (en) * | 1944-06-17 | 1946-11-11 | Hughes Henry & Son Ltd | Improvements in and relating to stabilised radar scanner equipment mounted on vehicles of all kinds |
| CN2598166Y (en) * | 2002-12-31 | 2004-01-07 | 中国科学院电子学研究所 | Double frequency co-face microband array aerial |
| CN102692163A (en) * | 2011-03-25 | 2012-09-26 | 哈尔滨开恩科技开发有限公司 | Jellyfish mine |
| CN103765672A (en) * | 2011-06-27 | 2014-04-30 | 空中客车运营简化股份公司 | Method of opening a protective dome, in particular a radome, and radome equipped with a pantograph for implementation thereof |
| CN103376451A (en) * | 2012-04-16 | 2013-10-30 | 中国科学院电子学研究所 | Airborne double-waveband synthetic aperture radar system and method for measuring vegetation thickness utilizing same |
| CN202661061U (en) * | 2012-05-10 | 2013-01-09 | 上海慧昌智能交通系统有限公司 | Protractor adjustable in angle |
| CN102882002A (en) * | 2012-09-27 | 2013-01-16 | 中国科学院长春光学精密机械与物理研究所 | Composite frequency-selective-surface invisible radome |
| CN104332705A (en) * | 2014-10-16 | 2015-02-04 | 西安电子工程研究所 | Integral type airborne millimeter wave radar antenna cover |
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| Publication number | Publication date |
|---|---|
| CN104986348A (en) | 2015-10-21 |
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