CN107364566A - A kind of solar heat protection antenna opening cover combined structure of detachable antenna out of my cabin - Google Patents
A kind of solar heat protection antenna opening cover combined structure of detachable antenna out of my cabin Download PDFInfo
- Publication number
- CN107364566A CN107364566A CN201710509135.4A CN201710509135A CN107364566A CN 107364566 A CN107364566 A CN 107364566A CN 201710509135 A CN201710509135 A CN 201710509135A CN 107364566 A CN107364566 A CN 107364566A
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- China
- Prior art keywords
- lid
- antenna
- heat shield
- bay section
- cabin
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- 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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Aerials (AREA)
Abstract
A kind of disclosure of the invention solar heat protection antenna opening cover combined structure of detachable antenna out of my cabin,Including ceramic antenna mouth window (1),Lid heat shield (2),Lid metal flanging (3),Anti- thermal screw (4),Bay section housing heat shield (5),Bay section casing metal layer (6),Rubber blanket (7),Lid heat shield (2) and the flanging of lid metal (3) integrated molding,It is Nian Jie with ceramic antenna mouth window flange,Lid is arranged in bay section by anti-thermal screw (4),L-type sealing structure is designed between lid heat shield (2) and bay section housing heat shield (5) prevents hot-fluid from being conducted into bay section casing metal layer (6) and nacelle,Antenna lid can be dismantled from out of my cabin on housing,It is easy to product final assemble to test,Antenna can after be filled on unit,Improve structure space utilization rate,And it can effectively obstruct the Aerodynamic Heating during aircraft flight,Ensure structural intergrity and thermally matched.
Description
Technical field
The invention belongs to the anti-heat insulation structural design field of aircraft bay section, is related to a kind of anti-hot day of detachable antenna out of my cabin
Line lid combining structure.
Background technology
There is a more antenna opening window aircraft bay section outer surface, aircraft by antenna electromagnetic wave through antenna opening window with it is outer
Boundary communicates.During aircraft long-time high-speed flight, antenna opening window outer surface bears more harsh Aerodynamic Heating and load
Environment.Therefore, electrical property and anti-Design on thermal insulation are mainly considered when antenna opening window designs.In traditional antenna opening window construction, antenna
Mouth window installs fixation in cabin, after the completion of bay section assembling, carries out antenna electric performance test, to dismantle antenna, can only first remove
Below deck equipment, then vacating space dismounting antenna, installation and removal are inconvenient, and time-consuming.And for small-sized bay section, the sky in bay section
Between will directly limit antenna installation and operating space, bay section design when filling rate be limited.
It is convenient repeatedly in assembly or disassembly out of my cabin for this reason, it is necessary to design a kind of solar heat protection antenna lid dismountable out of my cabin,
It is easy to antenna general assembly to test, improves bay section space availability ratio, and can effectively prevent heat-insulated.
The content of the invention
To solve the demand, the invention provides a kind of solar heat protection antenna opening cover combined structure of detachable antenna out of my cabin,
It is intended that antenna lid mounts and dismounts from out of my cabin, antenna can mount and dismount from out of my cabin, be easy to antenna general assembly to test,
Bay section space availability ratio is improved, and can effectively be prevented heat-insulated.
To achieve the above object, the invention provides a kind of solar heat protection antenna opening cover combined structure of detachable antenna out of my cabin,
Including ceramic antenna mouth window (1), lid heat shield (2), lid metal flanging (3), anti-thermal screw (4), bay section housing heat shield
(5), bay section casing metal layer (6), rubber blanket (7), wherein,
Ceramic antenna mouth window (1) is " several " sub- certain thickness flange of shape structure band, is the wave transparent window of antenna.Antenna opening
Window (1) passes through among lid heat shield (2), and flange is crimped by lid heat shield (2) and lid metal flanging (3), lid gold
Belong to flanging (3) and play main pressuring action, lid heat shield (2) auxiliary compresses, and is mainly used in solar heat protection.
Ceramic antenna mouth window (1), lid heat shield (2) and lid metal flanging (3) integrated molding respectively, jointly with pottery
Porcelain antenna opening window (1) flange is adhesively fixed, between lid metal flanging (3) and ceramic antenna mouth window (1) flange between reserved 1-2mm
Gap, for coordinating ceramic antenna mouth window (1), thermal stress deformation stretches caused by Aerodynamic Heating in flight course.
Lid heat shield (2) is connected by anti-thermal screw (4) with bay section housing, and lid heat shield (2) is prevented with bay section housing
L-type sealing structure is used between thermosphere (5), prevents that hot-fluid conducts into bay section casing metal layer (6) and cabin out of my cabin.Rubber blanket
(7) between ceramic antenna mouth window (1) and bay section casing metal layer (6), there is support sealing function.
In general, by the contemplated above technical scheme of the present invention, following beneficial effect can be obtained：
1st, the present invention setting by ceramic antenna mouth window (1) and lid heat shield (2) and lid metal flanging (3) structure
Meter, can effectively be compressed with fixed antenna mouth window, thermal stress deformation caused by Aerodynamic Heating during coordinated flight.
2nd, being connected between lid and bay section housing using anti-thermal screw (4), antenna lid dismounting can be repeated several times out of my cabin,
And can effectively it prevent heat-insulated.
3rd, antenna can be attached on unit from out of my cabin, can multiple installing/dismounting repeatedly, be easy to product final assemble to test, can improve
Space availability ratio in cabin.
Brief description of the drawings
Fig. 1 is schematic structural view of the invention；
Fig. 2 is CONSTRUCTED SPECIFICATION schematic diagram of the present invention.
Fig. 3 is combining structure exploded perspective view of the present invention.
Embodiment
In order to make the purpose , technical scheme and advantage of the present invention be clearer, below in conjunction with accompanying drawing and Case Simulation
Analysis, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein is only explaining this
Invention, is not intended to limit the present invention.In addition, technology involved in each embodiment of invention described below is special
As long as sign does not form conflict each other, can is mutually combined.
As shown in figure 1, a kind of solar heat protection antenna opening cover combined structure of detachable antenna out of my cabin, including ceramic antenna mouth window
(1), lid heat shield (2), lid metal flanging (3), anti-thermal screw (4), bay section housing heat shield (5), bay section casing metal
Layer (6), rubber blanket (7), antenna (8), unit (9), wherein,
Ceramic antenna mouth window (1) is " several " sub- certain thickness flange of shape structure band, is the wave transparent window of antenna.Antenna opening
Window (1) passes through among lid heat shield (2), and flange is crimped by lid heat shield (2) and lid metal flanging (3), lid gold
Belong to flanging (3) and play main pressuring action, lid heat shield (2) auxiliary compresses, and is mainly used in solar heat protection.
Antenna (8) is arranged on unit (9), after unit (9) is attached to bay section inside, dismantles antenna lid, antenna (8) can
By being attached to after the opening at lid on unit (9), and being dismounted for multiple times.
As shown in figure 3, ceramic antenna mouth window (1), lid heat shield (2) and lid metal flanging (3) one chemical conversion respectively
Type, it is adhesively fixed jointly with ceramic antenna mouth window (1) flange, between lid metal flanging (3) and ceramic antenna mouth window (1) flange
Reserved 1-2mm gaps, for coordinating ceramic antenna mouth window (1), thermal stress deformation stretches caused by Aerodynamic Heating in flight course.
As shown in Fig. 2 lid heat shield (2) is connected by anti-thermal screw (4) with bay section housing, lid heat shield (2) with
L-type sealing structure is used between bay section housing heat shield (5), prevents that hot-fluid passes into bay section casing metal layer (6) and cabin out of my cabin
Lead.Rubber blanket (7) is located between ceramic antenna mouth window (1) and bay section casing metal layer (6), has support sealing function.
Mounted and dismounted by anti-thermal screw, lid can mount to bay section housing or be dismantled from bay section housing.According to
Aerodynamic Heating calculates and experiment examination, and during aircraft long-time high-speed flight, lid hull-skin temperature is reachable >=and 1000 °, cabin
Temperature≤70 ° at section internal antenna, bay section metal shell temperature≤200 °, meet anti-insulation requirement.
As it will be easily appreciated by one skilled in the art that the preferred embodiments of the present invention are the foregoing is only, not limiting
The system present invention, all any modification, equivalent and improvement made within the spirit and principles of the invention etc., should be included in
Within protection scope of the present invention.
Claims (2)
1. a kind of solar heat protection antenna opening cover combined structure of detachable antenna out of my cabin, including：Ceramic antenna mouth window (1), lid solar heat protection
Layer (2), lid metal flanging (3), anti-thermal screw (4), bay section housing heat shield (5), bay section casing metal layer (6), rubber blanket
(7), wherein：
Ceramic antenna mouth window (1) is " several " sub- certain thickness flange of shape structure band, is made of wave transparent material；Antenna opening window (1)
Passed through among from lid heat shield (2), flange is crimped by lid heat shield (2) and lid metal flanging (3), lid metal flanging
(3) main pressuring action is played, lid heat shield (2) auxiliary compresses, and is mainly used in solar heat protection；Lid heat shield (2) passes through solar heat protection spiral shell
Nail (4) is connected with bay section housing, and L-type sealing structure is used between lid heat shield (2) and bay section housing heat shield (5), is prevented
Hot-fluid conducts into bay section casing metal layer (6) and cabin out of my cabin；Rubber blanket (7) is located at ceramic antenna mouth window (1) and bay section housing
Between metal level (6), there is support sealing function.
2. a kind of solar heat protection antenna opening cover combined structure of detachable antenna out of my cabin according to claim 1, antenna opening window
(1), lid heat shield (2) and lid metal flanging (3) difference integrated molding, lid heat shield (2) and lid metal flanging
(3) it is adhesively fixed jointly with ceramic antenna mouth window (1) flange, between lid metal flanging (3) and ceramic antenna mouth window (1) flange
Reserved 1-2mm gaps, for coordinating ceramic antenna mouth window (1), thermal stress deformation stretches caused by Aerodynamic Heating in flight course.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710509135.4A CN107364566B (en) | 2017-06-28 | 2017-06-28 | Heat-proof antenna opening cover combined structure of outdoor detachable antenna |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710509135.4A CN107364566B (en) | 2017-06-28 | 2017-06-28 | Heat-proof antenna opening cover combined structure of outdoor detachable antenna |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107364566A true CN107364566A (en) | 2017-11-21 |
| CN107364566B CN107364566B (en) | 2020-01-03 |
Family
ID=60305667
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710509135.4A Active CN107364566B (en) | 2017-06-28 | 2017-06-28 | Heat-proof antenna opening cover combined structure of outdoor detachable antenna |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107364566B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109264027A (en) * | 2018-08-13 | 2019-01-25 | 北京蓝箭空间科技有限公司 | Blanking cover, cargo tank structure and the space launch vehicle of bay section for space launch vehicle |
| CN110723275A (en) * | 2019-10-24 | 2020-01-24 | 湖北航天技术研究院总体设计所 | High-temperature heat-proof opening cover structure |
| CN111661311A (en) * | 2020-06-04 | 2020-09-15 | 河北柒壹壹玖工业自动化技术有限公司 | Solar unmanned aerial vehicle for bearing communication device |
| CN112960102A (en) * | 2021-03-18 | 2021-06-15 | 上海机电工程研究所 | Aircraft conical cabin integrated equipment installation opening cover and installation method |
| CN114674182A (en) * | 2022-03-22 | 2022-06-28 | 星河动力(北京)空间科技有限公司 | Separation shield screw protection structure and preparation device and protection method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| EP0325702A1 (en) * | 1987-11-13 | 1989-08-02 | Dornier Gmbh | Microstrip antenna |
| CN103545594A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Hypersonic aircraft telemetry antenna window mounting device |
| CN203666992U (en) * | 2013-12-06 | 2014-06-25 | 中国航空工业集团公司济南特种结构研究所 | Handrail structure for radar antenna housing |
| CN105914463A (en) * | 2016-06-28 | 2016-08-31 | 湖北航天技术研究院总体设计所 | Flexible connection device for high-temperature resistant radome |
-
2017
- 2017-06-28 CN CN201710509135.4A patent/CN107364566B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0325702A1 (en) * | 1987-11-13 | 1989-08-02 | Dornier Gmbh | Microstrip antenna |
| CN103545594A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Hypersonic aircraft telemetry antenna window mounting device |
| CN203666992U (en) * | 2013-12-06 | 2014-06-25 | 中国航空工业集团公司济南特种结构研究所 | Handrail structure for radar antenna housing |
| CN105914463A (en) * | 2016-06-28 | 2016-08-31 | 湖北航天技术研究院总体设计所 | Flexible connection device for high-temperature resistant radome |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109264027A (en) * | 2018-08-13 | 2019-01-25 | 北京蓝箭空间科技有限公司 | Blanking cover, cargo tank structure and the space launch vehicle of bay section for space launch vehicle |
| CN109264027B (en) * | 2018-08-13 | 2021-09-14 | 蓝箭航天空间科技股份有限公司 | A blanking cover, cabin section structure and space launch vehicle for cabin section of space launch vehicle |
| CN110723275A (en) * | 2019-10-24 | 2020-01-24 | 湖北航天技术研究院总体设计所 | High-temperature heat-proof opening cover structure |
| CN111661311A (en) * | 2020-06-04 | 2020-09-15 | 河北柒壹壹玖工业自动化技术有限公司 | Solar unmanned aerial vehicle for bearing communication device |
| CN112960102A (en) * | 2021-03-18 | 2021-06-15 | 上海机电工程研究所 | Aircraft conical cabin integrated equipment installation opening cover and installation method |
| CN114674182A (en) * | 2022-03-22 | 2022-06-28 | 星河动力(北京)空间科技有限公司 | Separation shield screw protection structure and preparation device and protection method thereof |
| CN114674182B (en) * | 2022-03-22 | 2023-11-14 | 星河动力(北京)空间科技有限公司 | Separation shield screw protection structure, preparation device and protection method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107364566B (en) | 2020-01-03 |
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