CN105000193B - A kind of servo-actuated radar cover stent and the servo-actuated radar with which and aircraft - Google Patents
A kind of servo-actuated radar cover stent and the servo-actuated radar with which and aircraft Download PDFInfo
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- CN105000193B CN105000193B CN201510349329.3A CN201510349329A CN105000193B CN 105000193 B CN105000193 B CN 105000193B CN 201510349329 A CN201510349329 A CN 201510349329A CN 105000193 B CN105000193 B CN 105000193B
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Abstract
The invention discloses a kind of servo-actuated radar cover stent and the servo-actuated radar with which and aircraft.The servo-actuated radar cover stent includes：Fixing axle, the fixing axle are used for being fixedly installed to the fuselage of the aircraft；Radome fairing, the radome fairing are arranged on the aircraft, and are set in the fixing axle, and the radome fairing can be relative to around fixing axle rotation；Wherein, in the aircraft flight, with respect to the airplane motion gas shock described in radome fairing, so that the radome fairing is rotated with the airflow direction.The servo-actuated radar cover stent of the present invention, in aircraft flight, with respect to the gas shock radome fairing of airplane motion, makes radome fairing rotate with the airflow direction, so that radome fairing is minimum all the time with the contact area of airflow direction.Interference of the servo-actuated radar cover stent in aircraft flight to aircraft is reduced, vector stability is improve, and reduces the resistance that servo-actuated radar cover stent is caused to aircraft in aircraft flight.
Description
Technical field
The present invention relates to Radar Technology field used by aircraft, more particularly to a kind of servo-actuated radar cover stent is used for supporting aircraft
On radome, and the servo-actuated radar with which and aircraft.
Background technology
In existing aircraft, generally radome is supported using fixing support.Although the profile and installation site of support are all
Design is optimized, but in the practical flight of aircraft, due to the flow-disturbing relation of in the air, support is receiving air disturbance
When, its impact to aircraft tail significantly reduces the shipping-direction stability of aircraft still than larger.
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 servo-actuated radar cover stent come overcome or at least mitigate prior art at least
One drawbacks described above.
For achieving the above object, the present invention provides a kind of servo-actuated radar cover stent, for supporting the radome on aircraft.Institute
Stating servo-actuated radar cover stent includes：Fixing axle, the fixing axle are used for being fixedly installed to the fuselage of the aircraft；Radome fairing,
The radome fairing is arranged on the aircraft, and is set in the fixing axle, and the radome fairing can be relative around the fixation
Axle rotates；Wherein, in the aircraft flight, with respect to the airplane motion gas shock described in radome fairing, make institute
State radome fairing to rotate with the airflow direction；The radome fairing includes fixed part and rotating part, and the fixed part is flown with described
The fuselage of machine is fixedly connected, and the rotating part can be relative to around fixing axle rotation.
Preferably, one end of the fixing axle is fixedly connected with the aircraft, the other end of the fixing axle and aircraft
Radome is fixedly connected, for supporting the radome.
Preferably, the fixing axle is hollow, for making the connection line that the aircraft is connected with the radome through institute
Fixing axle is stated so as to be connected with each other.
Preferably, the radome fairing includes two interconnective faces, and the fixing axle is arranged on the two of the radome fairing
The distance between individual face maximum.
Preferably, the shape of the radome fairing makes the sideslip of radome fairing described in the gas shock with respect to the airplane motion
During the envelope curve of angle, the lifting surface area of the radome fairing is minimum.
Preferably, along the size on the axial direction of the fixing axle, the fixed part disclosure satisfy that the rotating part is relative
When the fixing axle rotates, prevent the rotating part to have with the aircraft each other and interfere.
Present invention also offers a kind of servo-actuated radar, the servo-actuated radar includes servo-actuated radome, it is characterised in that described
Servo-actuated radar further includes servo-actuated radar cover stent as above.
Preferably, the servo-actuated radar includes two servo-actuated radar cover stents, and two servo-actuated radomes are propped up
Frame is oppositely arranged, and supports jointly the servo-actuated radome.
Present invention also offers a kind of aircraft, the aircraft includes servo-actuated radar as above.
The servo-actuated radar cover stent of the present invention, radome fairing can be relative to rotating around rotary shaft；In aircraft flight, phase
For the gas shock radome fairing of airplane motion, radome fairing is made to rotate with the airflow direction, so that radome fairing and air-flow side
To contact area minimum all the time.Interference of the servo-actuated radar cover stent in aircraft flight to aircraft is reduced, is improve
Vector stability, and the resistance that servo-actuated radar cover stent is caused in aircraft flight is reduced to aircraft.
Description of the drawings
Fig. 1 is structural representation of the servo-actuated radar cover stent according to an embodiment of the invention on aircraft.
Fig. 2 is another structural representation of the servo-actuated radar cover stent shown in Fig. 1.
Reference：
| 1 | Radome fairing | 12 | Rotating part |
| 2 | Fixing axle | 4 | Radome |
| 3 | Aircraft | ||
| 11 | Fixed part |
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.
The servo-actuated radar cover stent of the present invention, for supporting the radome on aircraft, including fixing axle, radome fairing, wherein,
Fixing axle is used for being fixedly installed to the fuselage of aircraft；Radome fairing arrange aboard, and sheathed on the rotary shaft, radome fairing energy
Enough relative to rotating around rotary shaft.Wherein, in aircraft flight, with respect to the gas shock radome fairing of airplane motion, make whole
Stream cover is rotated with the airflow direction, so that the leading edge alignment air current flow direction of radome fairing, even if the stress surface of radome fairing
Product is minimum.
The servo-actuated radar cover stent of the present invention, radome fairing can be relative to rotating around rotary shaft；In aircraft flight, phase
For the gas shock radome fairing of airplane motion, radome fairing is made to rotate with the airflow direction, so that radome fairing and air-flow side
To contact area minimum all the time.Interference of the servo-actuated radar cover stent in aircraft flight to aircraft is reduced, is improve
Vector stability, and the resistance that servo-actuated radar cover stent is caused in aircraft flight is reduced to aircraft.
Fig. 1 is structural representation of the servo-actuated radar cover stent according to an embodiment of the invention on aircraft.Fig. 2 is
Another structural representation of the servo-actuated radar cover stent shown in Fig. 1.
Radar generally on aircraft is arranged on the empennage position of aircraft, and radar includes the radar inside radome, radome
Component.
Servo-actuated radar cover stent shown in Fig. 1 includes fixing axle 2 and radome fairing 1.
Referring to Fig. 1 and Fig. 2, fixing axle 2 is used for being fixedly installed to the fuselage of aircraft 3.Specifically, 2 one end of fixing axle is solid
Surely arrange to aircraft 3, the other end is used for being connected with radome 4, for supporting radome 4.
In the present embodiment, the middle part of fixing axle 2 is hollow, and the connection line for making aircraft 3 be connected with radome 4 is passed through
Behind the hollow inside of fixing axle 2, it is connected with each other.
It is understood that fixing axle 2 is used for supporting radome 4, therefore, its intensity at least should can carry radome
4 load.
It is understood that in an alternative embodiment, fixing axle is solid shafting, to increase the intensity of fixing axle.Thunder
Cover 4 is reached with the connection line of aircraft 3 by outside cabling.
Referring to Fig. 1 and Fig. 2, in the present embodiment, radome fairing 1 is arranged on aircraft 3, and is set in fixing axle 2, and whole
Stream cover 1 can be relative to rotating around fixing axle 2.Specifically, in the present embodiment, radome fairing 1 is internal has the appearance for accommodating fixing axle 2
Portion is put, fixing axle 2 is in the holding part inside radome fairing 1.In the flight course of aircraft, with respect to the gas of airplane motion
Stream impact radome fairing 1, makes radome fairing 1 rotate with airflow direction.
Referring to Fig. 2, in the present embodiment, radome fairing 1 includes fixed part 11 and rotating part 12, fixed part 11 and aircraft 4
Fuselage be fixedly connected, rotating part 12 can be relative to rotating around rotary shaft 2.And fixed part 11 is along the axial direction of fixing axle 2
Size when disclosure satisfy that rotating part 12 is relatively fixed axle 2 and rotates, prevent rotating part 12 to have with aircraft each other and interfere.
Using this structure, the position that can be contacted radome fairing 1 with aircraft 3 is arranged to be fixed on aircraft 3, and not phase
Aircraft 3 is rotated, it is therefore prevented that when 1 relative rotation axi of radome fairing 2 is rotated, between radome fairing 1 and aircraft 3, produce interference.
Referring to Fig. 2, radome fairing 1 includes two interconnective faces, and fixing axle 2 is arranged between two faces of radome fairing 1
Apart from maximum, and make the pressure heart (the vertical paper of in figure direction inwards) after fixing axle 2 of radome fairing 1.Specifically,
The holding part of above-mentioned radome fairing 1 is arranged on head of the whole radome fairing 1 along aircraft to tail direction, the thickness of radome fairing 1
At maximum position, and radome fairing 1 is located at the position at the middle part of the direction.So, when radome fairing 1 rotates, in the middle part of this
The volume of the part of both sides is of substantially equal, and symmetrically.
Referring to Fig. 2, in the present embodiment, the shape of radome fairing 1 makes the gas shock radome fairing 1 with respect to airplane motion
During yaw angle envelope curve, the lifting surface area of radome fairing 1 is minimum.Specifically, radome fairing 1 itself has streamline profile, when flowing and fly
After machine axis has sideslip angle beta, due to pressing the heart after fixing axle 2,1 head of radome fairing can be partial to direction of flow to radome fairing 1.
Present invention also offers a kind of servo-actuated radar, the servo-actuated radar includes servo-actuated radome, and the servo-actuated radar enters
One step includes servo-actuated radar cover stent as above.It is understood that being set according to the size of servo-actuated radome and aircraft
Meter demand.One or more servo-actuated radar cover stents can be set.Referring to Fig. 2, in the present embodiment, servo-actuated radar includes two
Servo-actuated radar cover stent, and two servo-actuated radar cover stents are oppositely arranged, and support jointly the servo-actuated radome.
Present invention also offers a kind of aircraft, the aircraft includes servo-actuated radar as above.
Advantageously, the aircraft is 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 (9)
1. a kind of servo-actuated radar cover stent, for supporting the radome on aircraft, it is characterised in that the servo-actuated radar cover stent
Including：
Fixing axle (2), the fixing axle are used for being fixedly installed to the fuselage of the aircraft (3)；
Radome fairing (1), radome fairing (1) are arranged on the aircraft, and are set in the fixing axle (2), the rectification
Cover (1) can be relative to around the fixing axle (2) rotation；Wherein,
In the aircraft flight, with respect to the airplane motion gas shock described in radome fairing (1), make the rectification
Cover (1) is rotated with the airflow direction；
Described radome fairing (1) includes fixed part (11) and rotating part (12), the machine of fixed part (11) and the aircraft (3)
Body is fixedly connected, and rotating part (12) can be relative to around the fixing axle (2) rotation.
2. servo-actuated radar cover stent as claimed in claim 1, it is characterised in that the one end of fixing axle (2) is flown with described
Machine (3) is fixedly connected, and the other end of fixing axle (2) is fixedly connected with the radome (4) of aircraft, for supporting the radar
Cover (4).
3. servo-actuated radar cover stent as claimed in claim 2, it is characterised in that fixing axle (2) are hollow, described for making
The connection line that aircraft is connected with the radome is through fixing axle (2) so as to be connected with each other.
4. servo-actuated radar cover stent as claimed in claim 3, it is characterised in that described radome fairing (1) is mutually interconnected including two
The face for connecing, fixing axle (2) are arranged on the distance between two faces of the radome fairing (1) maximum.
5. servo-actuated radar cover stent as claimed in claim 4, it is characterised in that the shape of radome fairing (1) make with respect to
Described in the gas shock of the airplane motion during yaw angle envelope curve of radome fairing (1), the lifting surface area of radome fairing (1) is most
Little.
6. servo-actuated radar cover stent as claimed in claim 1, it is characterised in that fixed part (11) are along the fixing axle
(2) the size on axial direction disclosure satisfy that the rotating part (12) relative to the fixing axle (2) rotate when, prevent the rotation
Transfer part (12) is had each other with the aircraft interferes.
7. a kind of servo-actuated radar, the servo-actuated radar include servo-actuated radome, it is characterised in that the servo-actuated radar is wrapped further
Include the servo-actuated radar cover stent as described in any one in claim 1 to 6.
8. servo-actuated radar as claimed in claim 7, it is characterised in that the servo-actuated radar includes two servo-actuated radomes
Support, and two servo-actuated radar cover stents are oppositely arranged, and support jointly the servo-actuated radome.
9. a kind of aircraft, it is characterised in that the aircraft includes the servo-actuated radar as described in any one in claim 7 or 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510349329.3A CN105000193B (en) | 2015-06-23 | 2015-06-23 | A kind of servo-actuated radar cover stent and the servo-actuated radar with which and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510349329.3A CN105000193B (en) | 2015-06-23 | 2015-06-23 | A kind of servo-actuated radar cover stent and the servo-actuated radar with which and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105000193A CN105000193A (en) | 2015-10-28 |
| CN105000193B true CN105000193B (en) | 2017-03-08 |
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| CN201510349329.3A Active CN105000193B (en) | 2015-06-23 | 2015-06-23 | A kind of servo-actuated radar cover stent and the servo-actuated radar with which and aircraft |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106379510A (en) * | 2016-09-29 | 2017-02-08 | 华东电子工程研究所（中国电子科技集团公司第三十八研究所） | Load structure integrated sensor flight vehicle |
| CN106628109A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Rotating and connecting structure of aircraft radome |
| CN107477096B (en) * | 2017-09-30 | 2019-09-24 | 中国航空工业集团公司西安飞机设计研究所 | A kind of connection structure of large size rotary body and shaft |
| CN108045554A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of turbofan twin vertical fin early warning plane |
| CN109558691A (en) * | 2018-12-14 | 2019-04-02 | 中国航空工业集团公司西安飞机设计研究所 | A kind of shock resistance design method of airborne equipment bracket |
| CN109665112A (en) * | 2019-01-31 | 2019-04-23 | 江苏恒铭达航空设备有限公司 | Helicopter electronic self-defence component mounting bracket and helicopter |
| CN112623185A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Radome bracket with control surface |
| CN112896544B (en) * | 2021-02-04 | 2022-11-15 | 浙江大学 | A placer outside frame for aircraft cover support soon |
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|---|---|---|---|---|
| US4738531A (en) * | 1986-01-23 | 1988-04-19 | Westinghouse Electric Corp. | Distributed antenna array location apparatus |
| US5639173A (en) * | 1996-04-03 | 1997-06-17 | Northrop Grumman Corporation | Linkage support system |
| US7966872B2 (en) * | 2008-07-23 | 2011-06-28 | The Boeing Company | In-flight testing kits and methods for evaluating proposed aerodynamic structures for aircraft |
| CN201613856U (en) * | 2010-03-08 | 2010-10-27 | 梁吉隆 | Speed-measuring early-warning aircraft and system integrating fixing frame thereof |
| CN202289469U (en) * | 2011-09-02 | 2012-07-04 | 骅威科技股份有限公司 | Remote control toy early warning plane model |
| CN202754143U (en) * | 2012-07-26 | 2013-02-27 | 沈阳申蓝航空科技有限公司 | Rotating engine vertical take-off and landing aircraft |
| CN204279947U (en) * | 2014-11-10 | 2015-04-22 | 四川量迅科技有限公司 | The unmanned prior-warning plane of a kind of novel long-range |
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