CN202373696U - Microwave/infrared composite antenna cover for airborne pod - Google Patents
Microwave/infrared composite antenna cover for airborne pod Download PDFInfo
- Publication number
- CN202373696U CN202373696U CN 201120523372 CN201120523372U CN202373696U CN 202373696 U CN202373696 U CN 202373696U CN 201120523372 CN201120523372 CN 201120523372 CN 201120523372 U CN201120523372 U CN 201120523372U CN 202373696 U CN202373696 U CN 202373696U
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- Prior art keywords
- radome
- infrared
- antenna cover
- cover
- window
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Abstract
The utility model provides an antenna cover. An inner skin (6) and an outer skin (7) respectively cover the inner and outer parts of a base body material, a wave transmission area (2) is arranged on the outer side of the antenna cover, which is opposite to a radar antenna, a non-metal honeycomb material (8) is filled between the inner skin (6) and the outer skin (7) of the wave transmission area (2), partial wave transmission is realized on the premise of meeting requirements for overall intensity, and an infrared window (3) is formed at the bottom of the antenna cover, so a radar and an infrared detection device can be simultaneously arranged inside a spatial area which is covered by the antenna cover by using an equipment hanging rack, the defect that the radar and the infrared detection device are tested by simultaneously using two sets of airborne pods is overcome, and intensity requirements of the airborne pods are met.
Description
Technical field
The invention belongs to aircraft pod and use the radome technical field, relate more specifically to a kind ofly can pass through microwave/infrared combined antenna cover.
Background technology
It is step indispensable in the guided missile development process that airborne band flies to test, and in certain type guided missile development process, aircraft pod need bear high-altitude, mal-condition at a high speed, and the intensity of gondola radome has been proposed very high requirement.Simultaneously, the gondola radome of current application can only be selected to see through microwave or infrared ray, in the time of need testing the performance of radar and infrared detection device simultaneously, just can only use two cover gondolas to realize, has not only increased cost, and has used very inconvenience.
Summary of the invention
The invention provides a kind of gondola radome that radar and infrared detection device can be installed simultaneously, overcome the drawback that to use two cover gondola test radars and infrared detection device simultaneously, and satisfied the requirement of strength that gondola uses.
Technical scheme of the present invention: gondola radome main body adopts glass fabric reinforced epoxy based composites (abbreviation fiberglass) to process; Cover with covering respectively inside and outside the main body; The corresponding position that radar antenna is installed has window; Window portion covers inside panel and exterior skin, fills the non-metal honeycomb sandwich material between the covering; Have infrared window on the radome simultaneously, the pre-buried aluminum alloy frame of window edge, infrared crystal and vibration isolation rubber cover are installed on the aluminum alloy frame; Circumferentially imbed the aluminum alloy semi-ring rib at radome, enhance antenna cover integral intensity.Satisfy the requirement that high-altitude, hyper tape fly through the radome intensity after improving, and elongated radar antenna and infrared facility can be installed simultaneously, satisfy and pass through ripple, pass through infrared requirement by the area of space inner utilization equipment hanger of radome envelope.
Description of drawings
Shown in Figure 1 is the structural representation of radome of the present invention.
Shown in Figure 2ly pass through ripple plot structure sketch map for radome of the present invention.
Embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is described in further detail:
Shown in Figure 1 for the structure of radome of the present invention.Radar is set on radome body 1 passes through ripple district 2, infrared window 3, aluminum alloy frame 4 and semi-ring rib 5.Wherein radar passes through between the exterior skin 6, inside panel 7 in ripple district 2 and fills non-metal honeycomb sandwich 8 alternate antenna cover basis materials.According to the overall dimensions of radar antenna, pass through the ripple zone and can design as required.
Radome 1 bottom has infrared window 3, the pre-buried aluminum alloy frame 4 of window edge, and infrared crystal and vibration isolation rubber cover can be installed on the aluminum alloy frame.
Embed the semi-ring rib 5 that aluminium alloy or other lightweight metal material are processed on the radome 1, according to requirement of strength, the material of semi-ring rib and quantity can correspondingly be adjusted.
Fly test through examination of static(al) load test and actual band, prove that microwave provided by the invention/infrared combined antenna cover satisfies ripple and requirement of strength thoroughly.
It should be noted that; Though described technical scheme of the present invention with reference to preferred implementation; But those skilled in the art are understood that easily protection scope of the present invention is not limited to these embodiments, under the situation that does not depart from basic principle of the present invention; Can to said execution mode and concrete technical characterictic one wherein for example each module split, make up or change; Or the selection of certain module adjusted, split, combination or change material after technical scheme, will fall within protection scope of the present invention.
Claims (2)
1. an aircraft pod is with microwave/infrared combined antenna cover; On the basal body structure material, cover inside panel (7) and exterior skin (6), it is characterized in that: radome basal body structure material has window in the bottom, and window portion covers inside panel (7) and exterior skin (6); Fill non-metal honeycomb sandwich material (8) between the covering; Have infrared window (3) on the radome (1) simultaneously, the pre-buried aluminum alloy frame of window edge (4), infrared crystal and vibration isolation rubber cover are installed on the aluminum alloy frame (4).
2. radome as claimed in claim 1 is characterized in that, said radome (1) lower half is imbedded aluminum alloy semi-ring rib (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120523372 CN202373696U (en) | 2011-12-15 | 2011-12-15 | Microwave/infrared composite antenna cover for airborne pod |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120523372 CN202373696U (en) | 2011-12-15 | 2011-12-15 | Microwave/infrared composite antenna cover for airborne pod |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202373696U true CN202373696U (en) | 2012-08-08 |
Family
ID=46597390
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120523372 Expired - Lifetime CN202373696U (en) | 2011-12-15 | 2011-12-15 | Microwave/infrared composite antenna cover for airborne pod |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202373696U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105576368A (en) * | 2014-10-20 | 2016-05-11 | 波音公司 | Antenna electromagnetic radiation steering system |
| CN105691626A (en) * | 2014-11-28 | 2016-06-22 | 中国飞行试验研究院 | Aircraft fuselage bottom pod |
| CN107565215A (en) * | 2016-07-01 | 2018-01-09 | 陕西飞机工业（集团）有限公司 | A kind of airborne antenna cover structure |
| CN109273849A (en) * | 2017-07-18 | 2019-01-25 | 中国航空工业集团公司济南特种结构研究所 | A kind of honeycomb reinforces radar cover structure self |
| CN111969317A (en) * | 2020-08-26 | 2020-11-20 | 中国航空工业集团公司济南特种结构研究所 | Low-stress high-rigidity radome structure |
-
2011
- 2011-12-15 CN CN 201120523372 patent/CN202373696U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105576368A (en) * | 2014-10-20 | 2016-05-11 | 波音公司 | Antenna electromagnetic radiation steering system |
| CN105691626A (en) * | 2014-11-28 | 2016-06-22 | 中国飞行试验研究院 | Aircraft fuselage bottom pod |
| CN105691626B (en) * | 2014-11-28 | 2018-07-20 | 中国飞行试验研究院 | A kind of airframe bottom gondola |
| CN107565215A (en) * | 2016-07-01 | 2018-01-09 | 陕西飞机工业（集团）有限公司 | A kind of airborne antenna cover structure |
| CN107565215B (en) * | 2016-07-01 | 2020-04-07 | 陕西飞机工业（集团）有限公司 | Airborne radome structure |
| CN109273849A (en) * | 2017-07-18 | 2019-01-25 | 中国航空工业集团公司济南特种结构研究所 | A kind of honeycomb reinforces radar cover structure self |
| CN111969317A (en) * | 2020-08-26 | 2020-11-20 | 中国航空工业集团公司济南特种结构研究所 | Low-stress high-rigidity radome structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120808 |
|
| CX01 | Expiry of patent term |