CN104986325A - Ventilation pressure relief structure of fairing - Google Patents
Ventilation pressure relief structure of fairing Download PDFInfo
- Publication number
- CN104986325A CN104986325A CN201510346421.4A CN201510346421A CN104986325A CN 104986325 A CN104986325 A CN 104986325A CN 201510346421 A CN201510346421 A CN 201510346421A CN 104986325 A CN104986325 A CN 104986325A
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- Prior art keywords
- fairing
- ventilation
- honeycomb core
- pressure relief
- covering
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Abstract
The invention provides a ventilation pressure relief structure of a fairing and relates to the field of structural designing of aircrafts. The ventilation pressure relief structure is used for ventilation pressure relief of an aircraft fairing (1). A hole matched with a ventilation tube (3) is formed in the fairing (1), and the wall of the hole is coated with room-temperature curing adhesive (5); the ventilation tube (3) is of a broken-line tubular structure, one end of the ventilation tube (3) is inserted in the hole in the fairing (1), and the part, arranged outside the fairing (1), of the ventilation tube (3) is supported and fixed to the outer surface of the skin of the fairing (1) through a paper honeycomb core (4); a glass fabric skin (2) is cured on the outer surface of the skin of the fairing (1) together with the honeycomb core (4) and the ventilation tube (3). The ventilation pressure relief structure of the fairing is convenient to manufacture and simple in structure, the inside and the outside of the fairing (1) are communicated through arranging the ventilation tube on the fairing, the pressure difference inside and outside the fairing is reduced, the fairing is guaranteed not to bear additional load caused by pressure difference, the sealing performance is good, the stability of the device is greatly improved, and safety and reliability are realized.
Description
Technical field
The present invention relates to technical field of aircraft structure design, in particular to a kind of fairing ventilation pressure relief.
Background technology
Aircraft radome in the middle of prior art in installation, in use procedure, owing to install or improper use may make fairing that is airtight or non-hermetically sealed all be in " partly " airtight conditions.Aircraft under " partly " airtight conditions may the rapid change of height residing for aircraft when performing aerial mission, causes that fairing is inside and outside forms larger difference of pressure.When difference of pressure is little fairing the structure short time in be unlikely to be damaged, long difference of pressure inherently makes the structure of fairing damage, and needs to overhaul fairing or change; If fairing external and internal pressure is excessive, may immediately cause dome structure to destroy, security threat is caused to the aircraft performing aerial mission.The problem needing most solution is now exactly how to design dome structure, makes the air pressure inside and outside fairing be in state of equilibrium always.
Summary of the invention
The object of the invention is to solve above-mentioned deficiency of the prior art, provide a kind of simple and reasonable, reduce that aircraft radome external and internal pressure is poor, fairing that protection fairing does not bear the increment load brought due to difference of pressure ventilates pressure relief.
Object of the present invention is achieved through the following technical solutions: a kind of fairing ventilation pressure relief, be arranged on the fairing of aircraft, the ventilation of fairing on aircraft, pressure release, comprise glass fabric covering, breather pipe, paper honeycomb core, cold setting adhesive, wherein, fairing offers the hole of matching with breather pipe, hole wall is coated with cold setting adhesive; Breather pipe is fold-line-shaped tubular structure, and the hole in fairing is inserted in one end, and the breather pipe part be placed in outside fairing is supported by paper honeycomb core and is fixed on the covering outside face of fairing; Glass fabric covering and honeycomb core, breather pipe co-curing are at fairing covering outside face.
, between the covering of fairing and glass fabric covering, between breather pipe and paper honeycomb core in such scheme preferably, the covering of fairing be coated with cold setting adhesive between paper honeycomb core and carry out bonding.
In above-mentioned either a program preferably, fairing covering and glass fabric covering lap-joint paper honeycomb core are filled.
The beneficial effect of fairing ventilation pressure relief provided by the present invention is, structure is simple, easily manufactured, by arranging breather pipe by UNICOM inside and outside fairing on fairing, reduce the difference of pressure inside and outside fairing, ensure that fairing does not bear the increment load because difference of pressure causes, good airproof performance, device stability improve greatly, safe and reliable.
Accompanying drawing explanation
Fig. 1 is the integral structure schematic diagram of the preferred embodiment according to fairing ventilation pressure relief of the present invention;
Fig. 2 is embodiment illustrated in fig. 1 along breather pipe horizontal section structural representation according to fairing of the present invention ventilation pressure relief;
Fig. 3 is embodiment illustrated in fig. 1 along breather pipe longitudinal profile structural representation according to fairing of the present invention ventilation pressure relief.
Reference numeral:
1-fairing, 2-glass fabric covering, 3-breather pipe, 4-paper honeycomb core, 5-cold setting adhesive.
Detailed description of the invention
In order to understand the fairing ventilation pressure relief according to the present invention program better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to fairing ventilation pressure relief of the present invention.
As Figure 1-3, fairing ventilation pressure relief provided by the invention, be arranged on the fairing 1 of aircraft, the ventilation of fairing on aircraft, pressure release, comprise glass fabric covering 2, breather pipe 3, paper honeycomb core 4, cold setting adhesive 5, wherein, fairing 1 offers the hole of matching with breather pipe 3, hole wall is coated with cold setting adhesive 5; Breather pipe 3 is fold-line-shaped tubular structure, and the hole in fairing 1 is inserted in one end, and breather pipe 3 part be placed in outside fairing 1 is supported by paper honeycomb core 4 and is fixed on the covering outside face of fairing 1; Glass fabric covering 2 and honeycomb core 4, breather pipe 3 are solidificated in fairing 1 covering outside face.Between the covering of fairing 1 and glass fabric covering 2, between breather pipe 3 and paper honeycomb core 4, the covering of fairing 1 be coated with cold setting adhesive 5 between paper honeycomb core 4 and carry out bonding.Fairing 1 covering and glass fabric covering 2 lap-joint paper honeycomb core 4 are filled.
Fairing 1 coordinates with breather pipe 3 on the hole wall in opened hole, between glass fabric covering 2 and the covering of fairing 1, between the covering of fairing 1 and paper honeycomb core 4, between breather pipe 3 and paper honeycomb core 4, be coated with cold setting adhesive 5, be enough to the sealing effectiveness ensureing fairing 1 entirety, so fairing ventilation pressure relief provided by the present invention is applied to the risk of leaking that fairing 1 can not increase fairing 1, simultaneously when aircraft high-speed flight, outside high velocity air can not have an impact to fairing pressure relief ventilatory effect of ventilating.Except breather pipe 3 needs bill in advance to alone become except type, between other devices, adopt normal temperature cementing structure, may be used for the fairing in original design stage, installing additional of the fairing that also may be used for installing.
In concrete use procedure, fairing ventilation pressure relief provided by the invention is for aircraft radome.Do not consider pressure relief of ventilating during this radome original design, need install ventilation pressure relief additional when reality uses, the ventilation relief tube installed additional is GFRP honeycomb sandwich structure, and glass fabric covering 2 adopts triplex glass fabric; Breather pipe 3 is middle temperature epoxy glass fabric prepreg product, internal diameter
external diameter
paper honeycomb core 4 is high-modulus aramid paper honeycomb core, thickness 15mm; Ventilation pressure relief adopts normal temperature cure technique, and plate-plate and plate-core glue are as cold curing adhesive 5.
More than be described in detail in conjunction with fairing ventilation pressure relief specific embodiment of the present invention, but be not limitation of the present invention, everyly according to technical spirit of the present invention, technical scope of the present invention is all belonged to any simple modification made for any of the above embodiments, also it should be noted that, comprise the combination in any between each part mentioned above according to the category of fairing ventilation pressure relief technical scheme of the present invention.
Claims (3)
1. a fairing ventilation pressure relief, be arranged on the fairing (1) of aircraft, the ventilation of fairing on aircraft, pressure release, it is characterized in that: comprise glass fabric covering (2), breather pipe (3), paper honeycomb core (4), cold setting adhesive (5), wherein, fairing (1) offers the hole of matching with breather pipe (3), hole wall is coated with cold setting adhesive (5); Breather pipe (3) is fold-line-shaped tubular structure, the hole in fairing (1) is inserted in one end, and breather pipe (3) is placed in fairing (1) part outward and is supported by paper honeycomb core (4) and be fixed on the covering outside face of fairing (1); Glass fabric covering (2) and honeycomb core (4), breather pipe (3) co-curing are at fairing (1) covering outside face.
2. aircraft load lid anchor fitting as claimed in claim 1, it is characterized in that: between the covering of fairing (1) and described glass fabric covering (2), between described breather pipe (3) and paper honeycomb core (4), the covering of described fairing (1) be coated with cold setting adhesive (5) between paper honeycomb core (4) and carry out bonding.
3. aircraft load lid anchor fitting as claimed in claim 1 or 2, is characterized in that: described fairing (1) covering and described glass fabric covering (2) lap-joint paper honeycomb core (4) fill.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510346421.4A CN104986325B (en) | 2015-06-19 | 2015-06-19 | A kind of radome fairing ventilation pressure relief |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510346421.4A CN104986325B (en) | 2015-06-19 | 2015-06-19 | A kind of radome fairing ventilation pressure relief |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104986325A true CN104986325A (en) | 2015-10-21 |
| CN104986325B CN104986325B (en) | 2017-12-12 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510346421.4A Active CN104986325B (en) | 2015-06-19 | 2015-06-19 | A kind of radome fairing ventilation pressure relief |
Country Status (1)
| Country | Link |
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| CN (1) | CN104986325B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107768822A (en) * | 2017-11-22 | 2018-03-06 | 广东通宇通讯股份有限公司 | A kind of antenna sealing structure and antenna |
| CN107781183A (en) * | 2016-08-26 | 2018-03-09 | 天津海天方圆节能技术有限公司 | A kind of air-foil fan equipment |
| CN108216576A (en) * | 2016-12-15 | 2018-06-29 | 姬志刚 | A kind of structure for preventing fluid cone |
| CN114560105A (en) * | 2022-03-24 | 2022-05-31 | 青岛泰泓轨道装备有限公司 | Carrier rocket welding aluminum honeycomb fairing and preparation method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN202130570U (en) * | 2011-05-16 | 2012-02-01 | 湖北航天技术研究院总体设计所 | Aircraft cowling shell |
| CN203347905U (en) * | 2013-01-03 | 2013-12-18 | 中国航空工业集团公司西安飞机设计研究所 | Piston engine adjustable exhaust air door |
| CN203895600U (en) * | 2014-05-14 | 2014-10-22 | 中国电子科技集团公司第三十八研究所 | Airborne radome equipped with self-balance air pressure function |
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2015
- 2015-06-19 CN CN201510346421.4A patent/CN104986325B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202130570U (en) * | 2011-05-16 | 2012-02-01 | 湖北航天技术研究院总体设计所 | Aircraft cowling shell |
| CN203347905U (en) * | 2013-01-03 | 2013-12-18 | 中国航空工业集团公司西安飞机设计研究所 | Piston engine adjustable exhaust air door |
| CN203895600U (en) * | 2014-05-14 | 2014-10-22 | 中国电子科技集团公司第三十八研究所 | Airborne radome equipped with self-balance air pressure function |
Non-Patent Citations (1)
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| 柳醉: "关于某型飞机垂尾翼根整流罩结构的设计与研究", 《民用飞机设计与研究》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107781183A (en) * | 2016-08-26 | 2018-03-09 | 天津海天方圆节能技术有限公司 | A kind of air-foil fan equipment |
| CN108216576A (en) * | 2016-12-15 | 2018-06-29 | 姬志刚 | A kind of structure for preventing fluid cone |
| CN107768822A (en) * | 2017-11-22 | 2018-03-06 | 广东通宇通讯股份有限公司 | A kind of antenna sealing structure and antenna |
| CN107768822B (en) * | 2017-11-22 | 2024-01-05 | 广东通宇通讯股份有限公司 | Antenna sealing structure and antenna |
| CN114560105A (en) * | 2022-03-24 | 2022-05-31 | 青岛泰泓轨道装备有限公司 | Carrier rocket welding aluminum honeycomb fairing and preparation method thereof |
| CN114560105B (en) * | 2022-03-24 | 2023-08-08 | 青岛泰泓轨道装备有限公司 | Carrier rocket welded aluminum honeycomb fairing and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104986325B (en) | 2017-12-12 |
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