CN104986348A - Radar assembly and aircraft with same - Google Patents
Radar assembly and aircraft with same Download PDFInfo
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- CN104986348A CN104986348A CN201510350623.6A CN201510350623A CN104986348A CN 104986348 A CN104986348 A CN 104986348A CN 201510350623 A CN201510350623 A CN 201510350623A CN 104986348 A CN104986348 A CN 104986348A
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Abstract
The invention discloses a radar assembly and an aircraft with the same. The radar assembly is arranged on the aircraft and comprises a radome, a rotating table, radar supports in the radome, and radar array planes in the radome. The radome, the radar supports and the radar array planes are arranged on the rotating table. The rotating table can rotate relative to the aircraft. Detection windows are formed in the radome. The radar assembly further comprises infrared radar arranged in the radome and supported by the radar supports. Probes of the infrared radar can detect the external situation of the radome through the detection windows in the radome. In the radar assembly, the probes of the infrared radar can detect the external situation of the radome through the detection windows in the radome. Compared with the prior art, the infrared radar and radome are integrated, the infrared radar is prevented from protruding out of an aircraft body, and the aerodynamic force and performance of the aircraft can not be influenced.
Description
Technical field
The present invention relates to aircraft Radar Technology field, particularly relate to a kind of radar assembly and there is its aircraft.
Background technology
In prior art, infrared detection system is arranged on the machine nose position of aircraft usually, and being arranged on this position has following shortcoming:
1., because infrared detection system can give prominence to body, the aerodynamic characteristic of aircraft can be affected;
2. infrared detection system blocking due to body, can not realize circumference 360 ° of detections.
Therefore, wish a kind of technical scheme to overcome or at least alleviate at least one above-mentioned defect of prior art.
Summary of the invention
The object of the present invention is to provide a kind of radar assembly to overcome or at least alleviate at least one above-mentioned defect of prior art.
For achieving the above object, the invention provides a kind of radar assembly.Described radar assembly is arranged on described aircraft, described radar assembly comprises radome, turntable, radar supports in radome and radar front, wherein, described radome, radar supports and radar front are arranged on turntable, described turntable can rotate relative to described aircraft, described radome is provided with detection window, described radar assembly comprises further: infra-red radar, it is inner that described infra-red radar is arranged on described radome, and supported by described radar supports, the detecting head of described infra-red radar can detect the external circumstances of described radome by the detection window that described radome is arranged.
Preferably, described radome is disc radome, and described detection window is arranged on the outer rim place of described disc radome.
Preferably, described radome is provided with two detection windows, the quantity of described infra-red radar is two, and is separately positioned on the correspondence position of a detection window, thus makes each described infra-red radar detect the situation of the outside of described radome by a described detection window.
Preferably, two described detection windows are arranged along the outer rim of described radome, and are separated by 180 degree.
Preferably, described infra-red radar the hand of rotation of relatively described radome can do luffing, makes the investigative range of the detecting head of described infra-red radar be 0 degree to 180 degree.
Preferably, the size of described detection window is suitable for making the detecting head on described infra-red radar in its investigative range, all can detect the situation of the outside of described radome.
Preferably, described detection window is made with infrared glass material.
Present invention also offers a kind of aircraft, described aircraft has radar assembly as above.
Preferably, described aircraft is prior-warning plane, and described radar assembly is arranged on the empennage place of described prior-warning plane.
In radar assembly of the present invention, infra-red radar is arranged on radome inside, and is supported by radar supports, and the detecting head of infra-red radar can by the detection window acquisition radar cover external circumstances that radome is arranged.Relative to prior art, the present invention by infra-red radar and radar integrated, prevent infra-red radar to protrude from body, can not have an impact to the performance of the aerodynamic force of aircraft and aircraft.
Accompanying drawing explanation
Fig. 1 is the structural representation of the radar assembly in one embodiment of the invention.
Reference numeral:
| 1 | Radar front | 4 | Infra-red radar |
| 2 | Radome | 5 | Turntable |
| 3 | Detection window |
Detailed description of the invention
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
Usually, radar assembly is arranged aboard, and radar assembly comprises radar supports in radome, turntable, radome and radar front, and wherein, radome, radar supports and radar front are arranged on turntable, and described turntable can rotate relative to described aircraft.
In radar assembly of the present invention, radome is provided with detection window, and comprise further: infra-red radar, it is inner that described infra-red radar is arranged on described radome, and supported by described radar supports, the detecting head of described infra-red radar can detect the external circumstances of described radome by the detection window that described radome is arranged.
In radar assembly of the present invention, infra-red radar is arranged on radome inside, and is supported by radar supports, and the detecting head of infra-red radar can by the detection window acquisition radar cover external circumstances that radome is arranged.Relative to prior art, the present invention by infra-red radar and radar integrated, prevent infra-red radar to protrude from body, can not have an impact to the performance of the aerodynamic force of aircraft and aircraft.
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 comprises radar front 1, radome 2, detection window 3, infra-red radar 4, radar supports and turntable 5.Wherein, radome 2, radar supports and radar front 1 are arranged on turntable 5, described turntable can rotate relative to aircraft, thus above-mentioned radome 2, radar supports and radar front 1 are rotated relative to described aircraft, in the present embodiment, above-mentioned rotates to be 360 degree of rotations, namely can carry out 360 degree rotating relative to aircraft.
See Fig. 1, in the present embodiment, it is inner that infra-red radar 4 is arranged on radome 2, and supported by radar supports, and the detecting head of infra-red radar 4 can by the external circumstances of the detection window 3 acquisition radar cover 2 of setting on radome 2.Be understandable that, because infra-red radar 4 is arranged on radar supports, therefore, infra-red radar 4 can rotate relative to aircraft equally.Because above-mentioned radome 2, radar supports and radar front are by turntable driven rotary, therefore, above-mentioned all parts is synchronous rotary, and the relative position relation between its all parts can not change because of rotation.See Fig. 1, in the present embodiment, two detection windows 3 are arranged along the outer rim of radome 2, and are separated by 180 degree.
Adopt this structure, can make to be arranged on the external circumstances of infra-red radar 4 by detection window 3 acquisition radar cover 2 of radome 2 inside, and due to above-mentioned all parts meeting synchronous rotary, therefore, namely above-mentioned infra-red radar 4 can carry out the omnidirectional detection of 360 degree by above-mentioned rotation.
See Fig. 1, in the present embodiment, radome 2 is disc radome, and namely the profile of radome is disc, and detection window 3 is arranged on the outer rim place of disc radome.Be understandable that, the shape of radome can design as required.Such as, the shape of radome can be square or oval.Advantageously, disc radome largest diameter in the middle part of it, and shrinking to two ends, adopts this shape, can farthest reduce aircraft operationally air-flow on the impact of described disc radome.
See Fig. 1, in the present embodiment, radome 2 is provided with two detection windows 3, the quantity of infra-red radar 4 is two, and be separately positioned on the correspondence position of a detection window 3, thus make each infra-red radar 4 by the situation of the outside of a detection window 3 acquisition radar cover 2.
Adopt this structure, when above-mentioned all parts can be made to carry out the rotation of 360 degree, often rotate 180 degree of situations that infra-red radar 4 namely can be made to detect the radome outside under 360 degree of scopes.
Be understandable that, the quantity of infra-red radar 4 and the quantity of the detection window 3 corresponding with it can be arranged as required.Such as, 1,3 or more can be arranged.
See Fig. 1, in the present embodiment, each infra-red radar 4 hand of rotation of radome 2 relatively can do luffing, makes the investigative range of the detecting head of infra-red radar 4 be 0 degree to 180 degree.And the size of detection window 3 is suitable for making detecting head on infra-red radar 4 all can the situation of outside of acquisition radar cover 2 in its investigative range.Particularly, the size of detection window can make the elevation angle of above-mentioned infra-red radar 4 be 90 degree or the angle of depression when being 90 degree, can detect the external circumstances of radome 2 equally.
Adopt this structure, make the infra-red radar 4 in radar assembly of the present invention can not only carry out the detection of 360 degree along the hand of rotation of above-mentioned radome 2, the detection of 180 degree can also be carried out in corresponding pitch orientation, and pass through the cooperation of two infra-red radars 4, the infra-red radar 4 of radar assembly of the present invention can be made to carry out the detection of omnibearing 360 degree.
In the present embodiment, detection window 3 is made with infrared glass material, to ensure in aircraft flight, will, due to the impact of air pressure or other power, the situations such as detection window 3 damage be occurred.Be understandable that, detection window 3 can also adopt other materials to make.Such as, akerite (MgAl
2o
4) optical clear pottery etc.As long as this material can meet the requirement of infra-red radar in wave band permeability, and meets the requirement of aerodynamic loading and inertia loading on mechanical strength.
Present invention also offers a kind of aircraft, described aircraft comprises radar assembly as above.
Advantageously, this aircraft is prior-warning plane, and this radar assembly is arranged on the empennage place of described prior-warning plane.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (9)
1. a radar assembly, described radar assembly is arranged on described aircraft, described radar assembly comprises radar supports in radome (2), turntable (5), radome and radar front (1), wherein, described radome (2), radar supports and radar front (1) are arranged on turntable (5), described turntable (5) can rotate relative to described aircraft, it is characterized in that, described radome (2) is provided with detection window (3), described radar assembly comprises further:
Infra-red radar (4), it is inner that described infra-red radar (4) is arranged on described radome (2), and supported by described radar supports, the detecting head of described infra-red radar (4) can detect the external circumstances of described radome (2) by the upper detection window (3) arranged of described radome (2).
2. radar assembly as claimed in claim 1, it is characterized in that, described radome (2) is disc radome, and described detection window (3) is arranged on the outer rim place of described disc radome.
3. radar assembly as claimed in claim 2, it is characterized in that, described radome (2) is provided with two detection windows (3), the quantity of described infra-red radar (4) is two, and be separately positioned on the correspondence position of a detection window (3), thus each described infra-red radar (4) is made to detect the situation of the outside of described radome (2) by a described detection window (3).
4. radar assembly as claimed in claim 3, is characterized in that, two described detection windows (3) are arranged along the outer rim of described radome (2), and are separated by 180 degree.
5. radar assembly as claimed in claim 4, it is characterized in that, described infra-red radar (4) hand of rotation of relatively described radome (2) can do luffing, makes the investigative range of the detecting head of described infra-red radar (4) be 0 degree to 180 degree.
6. radar assembly as claimed in claim 5, it is characterized in that, the size of described detection window (3) is suitable for making the detecting head on described infra-red radar (4) in its investigative range, all can detect the situation of the outside of described radome (2).
7. radar assembly as claimed in claim 6, it is characterized in that, described detection window (3) is made with infrared glass material.
8. an aircraft, is characterized in that, described aircraft has radar assembly as claimed in any of claims 1 to 7 in one of claims.
9. aircraft as claimed in claim 8, it is characterized in that, described aircraft is prior-warning plane, and described radar assembly is arranged on the empennage place of described 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 |
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| Publication Number | Publication Date |
|---|---|
| CN104986348A true CN104986348A (en) | 2015-10-21 |
| CN104986348B CN104986348B (en) | 2017-03-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510350623.6A Active CN104986348B (en) | 2015-06-23 | 2015-06-23 | A kind of radar assembly and the aircraft with which |
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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 |
|---|---|
| CN104986348B (en) | 2017-03-08 |
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