CN204433027U - Aircraft door hermetically-sealed construction - Google Patents
Aircraft door hermetically-sealed construction Download PDFInfo
- Publication number
- CN204433027U CN204433027U CN201420815937.XU CN201420815937U CN204433027U CN 204433027 U CN204433027 U CN 204433027U CN 201420815937 U CN201420815937 U CN 201420815937U CN 204433027 U CN204433027 U CN 204433027U
- Authority
- CN
- China
- Prior art keywords
- sealing band
- hatch door
- landing pad
- sealing
- sealed construction
- Prior art date
- 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.)
- Active
Links
Landscapes
- Seal Device For Vehicle (AREA)
- Specific Sealing Or Ventilating Devices For Doors And Windows (AREA)
Abstract
The utility model belongs to a kind of seal form, relates to a kind of for the hermetically-sealed construction between Aeronautics and Astronautics aircraft lands frame hatch door and airframe structure.Described aircraft door hermetically-sealed construction comprises sealing band, fuselage sealing strip mounting structure, landing pad hatch door sealing band pressure texture.Wherein, described fuselage sealing strip mounting structure is stairstepping, and described landing pad hatch door sealing band pressure texture is L shape, both are arranged on inner sealing band at docking precompressed, wherein, described sealing band is the circular pipe structure of head hollow, and bottom is the reeded planar structure of middle tool.The utility model aircraft door hermetically-sealed construction good seal performance, safe and reliable, and it is little on aircaft configuration impact, simultaneously easily manufactured, cost is low, and application is wide, can be widely used in landing pad hatch door, lid, equipment hatch door, and in the air can the sealing of folding and unfolding hatch door, there is larger actual application value.
Description
Technical field
The utility model belongs to a kind of seal form, relates to a kind of for the hermetically-sealed construction between Aeronautics and Astronautics aircraft lands frame hatch door and airframe structure.
Background technology
What the recovery of reusable super speed vehicle and landing adopted is landing pad mode, adopt the landing pad hatch door of landing pad mode when aircraft carries out high-speed flight, due to the effect of aerodynamic loading, hatch door can be made to produce distortion, thus gap can be formed between hatch door and airframe structure.High-temperature hot air-flow will be undertaken, into landing pad cabin, causing fatal destruction, thus cause aircraft to reclaim landing to the equipment of the non-refractories such as the tire in landing pad cabin, hydraulic efficiency pressure system and electric system by this gap.Because space in landing pad cabin is large, equipment is many and complicated, is close to merely in landing pad cabin and provides liquid nitrogen cooling to be reliable and effectively to protect continental shelf cabin structure and built-in system equipment.
Utility model content
The purpose of this utility model is: provide that a kind of structure is simple, the aircraft door hermetically-sealed construction of good seal performance.
The technical solution of the utility model is: a kind of aircraft door hermetically-sealed construction, it comprises sealing band, fuselage sealing strip mounting structure, landing pad hatch door sealing band pressure texture, wherein, described fuselage sealing strip mounting structure is stairstepping, described landing pad hatch door sealing band pressure texture is L shape, and both dock precompressed and are arranged on inner sealing band, wherein, described sealing band is the circular pipe structure of head hollow, and bottom is the reeded planar structure of middle tool.
Described sealing band cross sectional shape is Ω shape.
Height between landing pad hatch door sealing band pressure texture and fuselage sealing strip mounting structure is less than the difference of sealing band original height and the maximum distortion of landing pad hatch door under aerodynamic loading effect.
Width between landing pad hatch door sealing band pressure texture and fuselage sealing strip mounting structure be greater than sealing joint strip compress after width.
Described fuselage sealing strip mounting structure and airframe structure one-body molded.
Described sealing band selects resistant to elevated temperatures silaatic.
Technique effect of the present utility model is: the utility model aircraft door hermetically-sealed construction can not only ensure the normal opening and closing of landing pad hatch door, simultaneously when aircraft carries out hypervelocity flight, elevated-temperature seal effect can be played by actv. to landing pad cabin, prevent thermal current from entering landing pad cabin, and can when landing pad hatch door deforms by aerodynamic loading, actv. compensates this distortion, remains the leak tightness in landing pad cabin.This hermetically-sealed construction form also has following advantages simultaneously:
A) structure adaptability is good, adopt this high-temperature sealing structure without the need to designing special mounting structure in fuselage opening structure and landing pad hatch door peripheral structure, little to the structure influence of airframe structure and landing pad hatch door, space, landing pad cabin is arranged that nervous small-sized super speed vehicle has very high practical value.
What b) seal is effective, and dependable performance, owing to have employed high-temperature-resisting silicon rubber, strict requirement is done to the ambient temperature mechanical properties of sealing band, mechanical behavior under high temperature, elevated-temperature seal ability and ageing properties etc. simultaneously, made this hermetically-sealed construction can meet various harsh service conditions.
C) sealing band convenient formation, can adopt the molding modes such as extruding and mold pressing according to concrete application conditions.
D) cost is low, applied range, can be widely used in landing pad hatch door, lid, equipment hatch door, and in the air can the sealing of folding and unfolding hatch door.
Accompanying drawing explanation
Fig. 1 is the utility model aircraft door sealed structural representation;
Fig. 2 is the schematic cross-section of sealing band;
Wherein, sealing band 1, fuselage sealing strip mounting structure 2, landing pad hatch door sealing band pressure texture 3.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is elaborated.
Refer to Fig. 1, it is the utility model aircraft door sealed structural representation.Described aircraft door hermetically-sealed construction comprises sealing band 1, fuselage sealing strip mounting structure 2, landing pad hatch door sealing band pressure texture 3.Wherein, described fuselage sealing strip mounting structure 2 is stairstepping, and with the mode of global formation and airframe structure one-body molded, in addition, also can shaping separately after, adopt the mode of mechanical connection to be installed on fuselage.
Refer to Fig. 2, it is the section drawing of sealing band.The similar Ω shape of described sealing band 1 cross sectional shape, namely head is the round section of hollow, and bottom is the reeded planar structure of middle tool.This kind of Ω cross-sectional profile bottom surface is plane, can well coordinate with fuselage sealing strip mounting structure 2, and the round section of hollow and the groove energy actv. of bottom surface provide amount of compression large as far as possible.Sealing band 1 is installed on fuselage sealing strip mounting structure 2 stairstepping top plan by gluing mode.
Described landing pad hatch door sealing band pressure texture 3 is the L shape shown in Fig. 1, and this structure directly can be integrated into the edge of landing pad hatch door.When hatch door is closed, landing pad hatch door sealing band pressure texture 3 compression seal bar 1 in advance, the cross sectional shape of sealing band 1 is changed, when landing pad hatch door is when being subject to external load and deforming, sealing band 1 cross section of distortion can initiatively be recovered to original Ω shape, thus to contacting with landing pad hatch door sealing band pressure texture 3 compressing surface all the time, sealing function are played to landing pad cabin.
Height h (sealing band 1 compresses rear size) between landing pad hatch door sealing band pressure texture 3 and fuselage sealing strip mounting structure 2, width L1, opposite joint size L2 and L3.The height h arranged is less than the difference of sealing band 1 original height H and the maximum distortion of landing pad hatch door under aerodynamic loading effect, make the amount of compression of sealing band 1 be greater than the maximum distortion of landing pad hatch door, thus make sealing band 1 can be close to the compressing surface of continental shelf hatch door sealing band pressure texture 3 all the time.The width L1 arranged be greater than sealing band 1 compress after width D, when making the compression of sealing band 1, Width can freely stretch, and does not affect compression performance.And gap clearance L2 between landing pad hatch door sealing band pressure texture 3 and fuselage sealing strip mounting structure 2 and L3 size can meet the requirement of landing pad cabin door open and close.
The rigidity of suitable landing pad hatch door sealing band pressure texture 3, fuselage sealing strip mounting structure 2 and sealing band 1 is set.Landing pad hatch door sealing band pressure texture 3 and fuselage sealing strip mounting structure 2 should design firm as much as possible, and sealing band 1 is under the prerequisite meeting resilience function, should rigidity be arranged lower, when hatch door is closed, little to the antagonistic force of landing pad hatch door sealing band pressure texture 3, ensure that hatch door closed condition is indeformable.
Selection of the present utility model: landing pad hatch door and aberdeen cutlet frame cabin peripheral openings structure select resistant to elevated temperatures titanium alloy or high-temperature alloy material, prevent the Aerodynamic Heating produced during super speed vehicle high-speed flight to the damage of hermetically-sealed construction.Meanwhile, seal profile 4 selects resistant to elevated temperatures silaatic, and made sealing band 1 has high-low temperature resistant, wear-resisting, ageing resistance good.
The utility model aircraft door hermetically-sealed construction can not only ensure the normal opening and closing of landing pad hatch door, simultaneously when aircraft carries out hypervelocity flight, elevated-temperature seal effect can be played by actv. to landing pad cabin, prevent thermal current from entering landing pad cabin, and can when landing pad hatch door deforms by aerodynamic loading, actv. compensates this distortion, remains the leak tightness in landing pad cabin.Structure adaptability is good simultaneously, adopt this high-temperature sealing structure without the need to designing special mounting structure in fuselage opening structure and landing pad hatch door peripheral structure, little to the structure influence of airframe structure and landing pad hatch door, space, landing pad cabin is arranged that nervous small-sized super speed vehicle has very high practical value.Owing to have employed high-temperature-resisting silicon rubber, done strict requirement to the ambient temperature mechanical properties of sealing band 1, mechanical behavior under high temperature, elevated-temperature seal ability and ageing properties etc., what therefore seal is effective, dependable performance, can meet various harsh service conditions simultaneously.And sealing band convenient formation, can adopt the molding modes such as extruding and mold pressing according to concrete application conditions, therefore cost is low, applied range simultaneously, landing pad hatch door, lid, equipment hatch door can be widely used in, and in the air can the sealing of folding and unfolding hatch door, there is larger actual application value.
Claims (6)
1. an aircraft door hermetically-sealed construction, it is characterized in that: comprise sealing band, fuselage sealing strip mounting structure, landing pad hatch door sealing band pressure texture, wherein, described fuselage sealing strip mounting structure is stairstepping, described landing pad hatch door sealing band pressure texture is L shape, and both dock precompressed and are arranged on inner sealing band, wherein, described sealing band is the circular pipe structure of head hollow, and bottom is the reeded planar structure of middle tool.
2. aircraft door hermetically-sealed construction according to claim 1, is characterized in that: described sealing band cross sectional shape is Ω shape.
3. the aircraft door hermetically-sealed construction according to any one of claim 1 to 2, is characterized in that: the height between landing pad hatch door sealing band pressure texture and fuselage sealing strip mounting structure is less than the difference of sealing band original height and the maximum distortion of landing pad hatch door under aerodynamic loading effect.
4. aircraft door hermetically-sealed construction according to claim 3, is characterized in that: the width between landing pad hatch door sealing band pressure texture and fuselage sealing strip mounting structure be greater than sealing joint strip compress after width.
5. aircraft door hermetically-sealed construction according to claim 4, is characterized in that: described fuselage sealing strip mounting structure and airframe structure one-body molded.
6. aircraft door hermetically-sealed construction according to claim 5, is characterized in that: described sealing band selects resistant to elevated temperatures silaatic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420815937.XU CN204433027U (en) | 2014-12-19 | 2014-12-19 | Aircraft door hermetically-sealed construction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420815937.XU CN204433027U (en) | 2014-12-19 | 2014-12-19 | Aircraft door hermetically-sealed construction |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204433027U true CN204433027U (en) | 2015-07-01 |
Family
ID=53600929
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420815937.XU Active CN204433027U (en) | 2014-12-19 | 2014-12-19 | Aircraft door hermetically-sealed construction |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204433027U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105148481A (en) * | 2015-09-17 | 2015-12-16 | 西安石油大学 | Manhole sealing device for negative pressure physical training device |
| CN105260505A (en) * | 2015-09-14 | 2016-01-20 | 中国运载火箭技术研究院 | Finite element method based aircraft cabin door seal load computing method |
| CN109229332A (en) * | 2018-09-06 | 2019-01-18 | 上海空间推进研究所 | The manned bay door system of near space |
| CN111907692A (en) * | 2020-08-14 | 2020-11-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Cabin door heat sealing structure |
| EP3812277A1 (en) * | 2019-10-25 | 2021-04-28 | Goodrich Corporation | Aircraft component with extruded elastomeric surface |
| CN113968248A (en) * | 2020-07-22 | 2022-01-25 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | A sealed equipment cabin and vacuum pipeline train for vacuum pipeline train |
| CN114212276A (en) * | 2021-11-30 | 2022-03-22 | 北京卫星制造厂有限公司 | Space station cabin door and method for assembling and adjusting cabin door sealing structure |
-
2014
- 2014-12-19 CN CN201420815937.XU patent/CN204433027U/en active Active
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105260505A (en) * | 2015-09-14 | 2016-01-20 | 中国运载火箭技术研究院 | Finite element method based aircraft cabin door seal load computing method |
| CN105260505B (en) * | 2015-09-14 | 2018-07-06 | 中国运载火箭技术研究院 | A kind of aircraft door seal load analysis method based on finite element |
| CN105148481A (en) * | 2015-09-17 | 2015-12-16 | 西安石油大学 | Manhole sealing device for negative pressure physical training device |
| CN109229332A (en) * | 2018-09-06 | 2019-01-18 | 上海空间推进研究所 | The manned bay door system of near space |
| EP3812277A1 (en) * | 2019-10-25 | 2021-04-28 | Goodrich Corporation | Aircraft component with extruded elastomeric surface |
| US11713137B2 (en) | 2019-10-25 | 2023-08-01 | Goodrich Corporation | Extruded elastomeric surface or erosion plys |
| CN113968248A (en) * | 2020-07-22 | 2022-01-25 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | A sealed equipment cabin and vacuum pipeline train for vacuum pipeline train |
| CN111907692A (en) * | 2020-08-14 | 2020-11-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Cabin door heat sealing structure |
| CN114212276A (en) * | 2021-11-30 | 2022-03-22 | 北京卫星制造厂有限公司 | Space station cabin door and method for assembling and adjusting cabin door sealing structure |
| CN114212276B (en) * | 2021-11-30 | 2023-08-11 | 北京卫星制造厂有限公司 | Space station cabin door and assembling and adjusting method of cabin door sealing structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204433027U (en) | Aircraft door hermetically-sealed construction | |
| CN101370710B (en) | Method of de-icing the leading edge of an aerodynamic surface and aircraft implementing such a method | |
| US20160167269A1 (en) | Method of fabricating a composite material blade having an integrated metal leading edge for a gas turbine aeroengine | |
| CN103274043B (en) | Stratospheric airship paved with flexible thin-film solar cells and paving method of flexible thin-film solar cells | |
| WO2010010382A3 (en) | Method of stiffening a rib during assembly | |
| CN203581388U (en) | High-supersonic aircraft and air inlet channel internal and external waverider integration device | |
| CN207625957U (en) | A kind of air-pressure balancing device of automobile electronics | |
| CN104339668A (en) | Integrated forming method of carbon fiber chair backs | |
| CN204788078U (en) | Hot seal structure of radome fairing end cap | |
| US20160138715A1 (en) | System and Apparatus for Aerodynamically Sealing Surfaces | |
| CN204223173U (en) | A kind of being applicable to hits the SUAV (small unmanned aerial vehicle) leading edge of a wing assembly netted and reclaim | |
| CN203188856U (en) | Sliding door sealing strip | |
| CN106827592B (en) | Sealing method for composite material structure manufacturing combined die | |
| CN108609158B (en) | Passive follow-up sealing structure | |
| CN110953387A (en) | Aerostatics utricule fills gassing all-in-one | |
| CN203008732U (en) | Hollowed functional rubber sealing tape which is deformable under compression | |
| CN204255606U (en) | The turning anti-icing equipment of icing wind tunnel | |
| CN202448720U (en) | Operator cabin door seal strip | |
| CN208415130U (en) | A kind of deceleration strip | |
| CN103410397B (en) | A kind of car, ship escape device | |
| CN103047414B (en) | A kind of end socket of injecting glue notch and apply the method that this end socket manufactures heat-insulation aluminum section | |
| CN206436442U (en) | The automotive wire bundle and plug connector waterproof bolt mould of a kind of simple operation | |
| CN207644393U (en) | A kind of sealing joint strip used for rail vehicle and the door device using the sealing joint strip | |
| CN205025271U (en) | A rubber strip for packing door, window space | |
| CN106005425B (en) | A kind of surface contact bus unit |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee after: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |