CN103821938A - Rudderpost thermal sealing structure - Google Patents
Rudderpost thermal sealing structure Download PDFInfo
- Publication number
- CN103821938A CN103821938A CN201310460849.2A CN201310460849A CN103821938A CN 103821938 A CN103821938 A CN 103821938A CN 201310460849 A CN201310460849 A CN 201310460849A CN 103821938 A CN103821938 A CN 103821938A
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- China
- Prior art keywords
- rudderpost
- sealing structure
- coupling shaft
- aircraft
- solar heat
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Abstract
The invention discloses a rudderpost thermal sealing structure. The rudderpost thermal sealing structure is characterized in that a heatproof ring (2) is bonded outside an adapter shaft (1), heatproof putty (7) is applied around the heatproof ring (2), and a graphite gasket (3), a steel gasket (4) and a flexible gasket (5) are sequentially mounted below the adapter shaft (1). By the rudderpost thermal sealing structure, failure of the whole flying experiment due to the fact that high-temperature airflow outside an aircraft enters the inside of the aircraft through a rotating part of a rudder system can be prevented.
Description
Technical field
The present invention relates to the heat sealing of hypersonic aircraft.Be specifically related to the heat sealing structure of air rudder system in flight course.Guarantee that flight test airvane system heat sealing effectively, reliably.
Background technique
Hypersonic aircraft take scramjet engine as power has the feature of body/engine integration, and under hypersonic flight condition, air-flow density of heat flow rate is large, aircraft surface is played to the effect of heating.Meanwhile, if aircraft surface has the little gap towards aircraft inside, hot air flow can be passed into aircraft inside by little gap rapidly, thereby the equipment of aircraft inside is exerted an influence, and whole flight is produced to subversive destruction.
Airvane is controlled flight attitude and the lift of aircraft by rotation.Steering wheel is installed on the housing of aircraft, for controlling the rotation of airvane.Airvane is connected by screw in Coupling Shaft, and Coupling Shaft 1 is connected by screw in being arranged on carry-on steering wheel again.Gapless between Coupling Shaft 1 and aircraft casing, adding the factors such as thermal expansion and can cause between Coupling Shaft 1 and housing stuckly in flight course, affects the normal rotation of airvane; Between Coupling Shaft 1 and aircraft casing, have gap, High Temperature Gas fails to be convened for lack of a quorum and is passed to steering wheel by gap, and in the time exceeding the serviceability temperature of steering wheel self, steering wheel can lose efficacy.
In this case, be connected and be even more important for the reliable sealing between the airvane of aircraft exterior and the steering wheel of aircraft inside.
Not yet find effective rudder system heat sealing structure.
Summary of the invention
The present invention is directed to existing technical problem, proposed a kind of hypersonic aircraft rudderpost heat sealing structure, prevent that the high temperature gas flow of aircraft exterior from importing into aircraft inside by the rotatable parts of rudder system, cause the failure of whole flight test.
A kind of rudderpost heat sealing of the present invention structure, is characterized in that bonding solar heat protection ring outside Coupling Shaft, smears solar heat protection putty at solar heat protection ring periphery simultaneously; Graphite gasket, Steel Washer, flexible gaskets are installed successively under Coupling Shaft.
Preferably, solar heat protection ring is high silica material.
A kind of rudderpost heat sealing of the present invention structure, when steering wheel 8 drives airvane 10 to rotate, because solar heat protection ring 2 is bonded in the outer surface of Coupling Shaft 1, prevents high-temperature gas heating Coupling Shaft 1; Solar heat protection putty 10 spreads upon the surrounding of Coupling Shaft 1 and solar heat protection ring 1, can stop high-temperature gas to enter into deck store 9.Graphite gasket 3 is in order in the time that Coupling Shaft is rotated, and lubricate, guarantees that airvane rotates lubricated; Flexible gaskets 5 is in order to compensate the radial displacement in flight course.Steel Washer 4, in order to graphite gasket 3 and flexible gaskets 5 are separated, plays bidirectional protective effect.Glass fibre reinforced plastics packing ring 6 reaches steering wheel in order to the heat that stops Coupling Shaft 1.
By above technological scheme, effectively realize the heat sealing of rudderpost.
Accompanying drawing explanation
Fig. 1: airvane system connection diagram;
Coupling Shaft 1, solar heat protection ring 2, graphite gasket 3, Steel Washer 4, flexible gaskets 5, glass fibre reinforced plastics packing ring 6, solar heat protection putty 7, steering wheel 8, deck store 9, airvane 10.
Embodiment
Below in conjunction with accompanying drawing, the present invention will be further described.
As shown in Figure 1, airvane 10 is connected with Coupling Shaft 1 by screw.Coupling Shaft 1 is connected with steering wheel 10 by screw, and steering wheel is arranged on aircraft casing, makes steering wheel 8 drive airvane 10 to rotate.
At the outer bonding solar heat protection ring 2 of Coupling Shaft 1, prevent high-temperature gas heating Coupling Shaft 1.Solar heat protection ring 2 is high silica material, simultaneously smears solar heat protection putty 7 at solar heat protection ring 2 peripheries, and solar heat protection putty 7 can prevent that high-temperature gas from scurrying into heat steering wheel 8 on the one hand, simultaneously due to the characteristic of himself, can be noncondensing for a long time, and do not affect the normal rotation of Coupling Shaft 1.In Coupling Shaft, graphite gasket 3, Steel Washer 4, flexible gaskets 5 are installed successively for 1 time.Graphite gasket 3 lubricates are considered thermal expansion simultaneously, place flexible gaskets 53 times, to thermal expansion redeeming in graphite gasket.By Steel Washer 4, graphite gasket 3 and flexible gaskets 5 are separated, play bidirectional protective effect.Frictional influence while utilizing graphite gasket 3 and flexible gaskets 5 simultaneously to consider the rotation of Coupling Shaft 1 and thermal expansion radially.
Installation method of the present invention is as follows.By screw, Coupling Shaft 1 is connected with airvane 10.Again flexible gaskets 5, Steel Washer 4 and graphite gasket 3 are placed on steering wheel 8 successively.Again the Coupling Shaft 1 that is connected with airvane 10 is connected on steering wheel 8.
Various not illustrating the restriction of essence of an invention Composition of contents, person of an ordinary skill in the technical field, having read after specification and can the embodiment described in the past having been made an amendment or is out of shape, deviate from essence of an invention and scope.
Claims (2)
1. a rudderpost heat sealing structure, is characterized in that bonding solar heat protection ring (2) outside Coupling Shaft (1), smears solar heat protection putty (7) at solar heat protection ring (2) periphery simultaneously.Graphite gasket (3), Steel Washer (4), flexible gaskets (5) are installed successively under Coupling Shaft (1).
2. a kind of rudderpost heat sealing structure as claimed in claim 1, is characterized in that solar heat protection ring (2) is high silica material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460849.2A CN103821938A (en) | 2013-09-30 | 2013-09-30 | Rudderpost thermal sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460849.2A CN103821938A (en) | 2013-09-30 | 2013-09-30 | Rudderpost thermal sealing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103821938A true CN103821938A (en) | 2014-05-28 |
Family
ID=50757146
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310460849.2A Pending CN103821938A (en) | 2013-09-30 | 2013-09-30 | Rudderpost thermal sealing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103821938A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181317A (en) * | 2015-09-22 | 2015-12-23 | 中国航天空气动力技术研究院 | Rudderpost heat sealing test device |
| CN109073089A (en) * | 2016-02-23 | 2018-12-21 | 约翰起重机英国有限公司 | The system and method for predictive diagnosis for mechanical system |
| CN113606056A (en) * | 2021-09-18 | 2021-11-05 | 天津爱思达航天科技有限公司 | Heat-proof tail cabin structure of rocket engine |
| CN113739649A (en) * | 2021-08-09 | 2021-12-03 | 上海机电工程研究所 | Thermal protection device for clearance of telescopic duck rudder cabin body |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101565184A (en) * | 2009-05-22 | 2009-10-28 | 宜昌南玻硅材料有限公司 | Electrode sealing method in hydrogen furnace device for polysilicon production and device thereof |
| CN201716128U (en) * | 2010-05-25 | 2011-01-19 | 湖北航天技术研究院总体设计所 | Temperature measuring device for outer surface of high-speed aircraft |
| US20110226896A1 (en) * | 2009-11-06 | 2011-09-22 | Mitsubishi Aircraft Corporation | Lightning-resistant fastener, cap, fastener member, and method for attaching lightning-resistant fastener |
| CN202946516U (en) * | 2012-10-18 | 2013-05-22 | 北京临近空间飞行器系统工程研究所 | Screw thermal protection device |
| CN203670769U (en) * | 2013-09-30 | 2014-06-25 | 中国人民解放军国防科学技术大学 | Rudder spindle heat sealing structure |
-
2013
- 2013-09-30 CN CN201310460849.2A patent/CN103821938A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101565184A (en) * | 2009-05-22 | 2009-10-28 | 宜昌南玻硅材料有限公司 | Electrode sealing method in hydrogen furnace device for polysilicon production and device thereof |
| US20110226896A1 (en) * | 2009-11-06 | 2011-09-22 | Mitsubishi Aircraft Corporation | Lightning-resistant fastener, cap, fastener member, and method for attaching lightning-resistant fastener |
| CN201716128U (en) * | 2010-05-25 | 2011-01-19 | 湖北航天技术研究院总体设计所 | Temperature measuring device for outer surface of high-speed aircraft |
| CN202946516U (en) * | 2012-10-18 | 2013-05-22 | 北京临近空间飞行器系统工程研究所 | Screw thermal protection device |
| CN203670769U (en) * | 2013-09-30 | 2014-06-25 | 中国人民解放军国防科学技术大学 | Rudder spindle heat sealing structure |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105181317A (en) * | 2015-09-22 | 2015-12-23 | 中国航天空气动力技术研究院 | Rudderpost heat sealing test device |
| CN109073089A (en) * | 2016-02-23 | 2018-12-21 | 约翰起重机英国有限公司 | The system and method for predictive diagnosis for mechanical system |
| CN109073089B (en) * | 2016-02-23 | 2020-09-04 | 约翰起重机英国有限公司 | System and method for predictive diagnostics of a mechanical system |
| CN113739649A (en) * | 2021-08-09 | 2021-12-03 | 上海机电工程研究所 | Thermal protection device for clearance of telescopic duck rudder cabin body |
| CN113606056A (en) * | 2021-09-18 | 2021-11-05 | 天津爱思达航天科技有限公司 | Heat-proof tail cabin structure of rocket engine |
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Application publication date: 20140528 |