CN207496916U - Thermal protection structure inside a kind of aircraft bay section - Google Patents
Thermal protection structure inside a kind of aircraft bay section Download PDFInfo
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- CN207496916U CN207496916U CN201721631008.3U CN201721631008U CN207496916U CN 207496916 U CN207496916 U CN 207496916U CN 201721631008 U CN201721631008 U CN 201721631008U CN 207496916 U CN207496916 U CN 207496916U
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- thermal protection
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Abstract
The utility model provides thermal protection structure inside a kind of aircraft bay section, including：Bay section, shape are tube body；Several ribs are axially convexly equipped in bay section inner wall along bay section, and are intervally arranged along bay section inner circumferential, and adjacent two rib forms a rib pit between bay section inner wall；Several thermal protection shields, are sheet or bulk, and shape matches with the rib pit shape, is attached on the bay section inner wall in each rib pit by adhesive layer respectively, forms the thermal protection to bay section inner wall.The structure can solve the problems, such as to damage aerodynamic configuration, and it is at low cost to reduce thermal protection during thermal protection shield work, improve thermal protection implementing process.
Description
Technical field
The utility model belongs to aircraft bay section thermal protection technology field, and in particular, to inside a kind of aircraft bay section
Thermal protection structure.
Background technology
Aircraft（flight vehicle）It is in endoatmosphere or exoatmosphere space（Space）The instrument of flight.Flight
Device is divided into 3 classes：Aircraft, spacecraft, rocket and guided missile.In endoatmosphere, the referred to as aircraft of flight, such as balloon, dirigible, flies
Machine etc..The air force lift-off flight that they are generated by the quiet buoyancy of air or air relative motion.In being known as space flight
Spacecraft, such as artificial earth satellite, manned spaceship, space probe, space shuttle.They are obtained under the promotion of carrier rocket
It obtains necessary speed and enters space, then doing the track similar with celestial body by inertia moves.
With the promotion of aircraft speed, surface Aerodynamic Heating is increasingly severe, and Aerodynamic Heating can not only make bay section surface
Temperature increases, and can also pass to inside nacelle, temperature in cabin is caused to increase.When in cabin have non-heatproof structure or electronic instrument
During equipment, thermal protection structure must be just used.
At present, the thermal protection structure of bay section is mostly that covering ablator or ceramic insulation watt progress heat are anti-outside nacelle
Shield.And aerodynamic configuration is damaged during ablator work, ceramic-like heat-barrier material is costly, installation maintenance is constant.
For bay section thermal protection, the current country is primarily present following patent document：
China Patent Publication No.：CN106547965A discloses a kind of thermal protection dress of hypersonic gliding class aircraft
It puts, including heat shield, thermal insulation layer and bearing layer, thermal insulation layer is covered on bearing layer, and heat shield is covered on thermal insulation layer, solar heat protection
Layer and the bearing layer are mutually separated and without connections or contact physically, to ensure that heat shield and the bearing layer are pneumatically adding
Free Transform under thermal environment, heat shield include polylith, and polylith heat shield mutually splices to form entirety, and polylith heat shield is in bay section
Corner, the corner portion of bay section, horizontal tail and nacelle junction mutually splice, heat shield and load at bay section docking
Interlayer is partially provided with multiple solar heat protection items, and multiple solar heat protection separated by gap, solar heat protection item can be free to slide with respect to heat shield, to adapt to
Stress deformation, solar heat protection item are identical with the heat shield material.The present invention passes through heat shield block design, heat shield and bearing layer
Separate design can effectively solve thermally matched and thermal stress problem, improve the reliability of temperature barrier.However, the patent institute
The temperature barrier of offer, complicated, manufacture is of high cost.
Utility model content
Above-mentioned to solve the problems, such as, the purpose of this utility model is to provide thermal protections inside a kind of aircraft bay section
Structure, the structure can be solved the problems, such as to damage aerodynamic configuration, and it is at low cost to reduce thermal protection during thermal protection shield work, be improved
Thermal protection implementing process.
In order to achieve the above objectives, the technical solution of the utility model is：
Thermal protection structure inside a kind of aircraft bay section, the structure include：Bay section, shape are tube body；Several ribs, edge
Bay section is axially convexly equipped in bay section inner wall, and is intervally arranged along bay section inner circumferential, and adjacent two rib forms a muscle between bay section inner wall
Pit；Several thermal protection shields are sheet or bulk, and shape is matched with the rib pit shape, passes through adhesive layer respectively
It is attached on the bay section inner wall in each rib pit, forms the thermal protection to bay section inner wall.
Further, thermal protection coating is coated between the adjacent thermal protection shield at gap.
Further, the thermal protection shield is also attached at rib surface by adhesive layer, is formed to the complete of bay section inner wall
Covering.
Further, the thermal protection shield is flexible thermal protection shield.
Further, the adhesive layer is high temperature adhesive layer.
Further, the thermal protection shield is organosilicon heat-insulating and sealing machine layer.
The beneficial effects of the utility model are：
Using internal thermal protection structure, exterior compartment section surface can be machined out, and have good aerodynamic configuration.
Thermally protective materials price is low, reduces thermal protection cost.
Thermally protective materials are flexible, and process implementing is simple.
Description of the drawings
Fig. 1 is the structure diagram of thermal protection structure inside a kind of aircraft bay section provided by the utility model；
Fig. 2 is rib and rib pit inside thermal protection structure inside a kind of aircraft bay section provided by the utility model
Structure diagram.
Specific embodiment
With reference to Fig. 1 ~ Fig. 2, thermal protection structure inside a kind of aircraft bay section described in the utility model, the structure packet
It includes：Bay section 1, shape are tube body；Several ribs 2 are convexly equipped in 1 inner wall of bay section, and weekly interval is arranged along bay section 1 along bay section 1 is axial
Cloth, adjacent two rib 2 form a rib pit 3 between 1 inner wall of bay section；Several thermal protection shields 4, for sheet or bulk, shape
It is matched with 3 shape of rib pit, is attached at 1 inner wall of bay section in each rib pit 3 by adhesive layer 5 respectively
On, form the thermal protection to 1 inner wall of bay section.
Further, thermal protection coating is coated between the adjacent thermal protection shield 4 at gap（It is not shown）.
Further, the thermal protection shield 4 is also attached at 2 surface of rib by adhesive layer 5, is formed to 1 inner wall of bay section
It is completely covered.
Further, the thermal protection shield 4 is flexible thermal protection shield.
Further, the adhesive layer 5 is high temperature adhesive layer.
Further, the thermal protection shield 4 is organosilicon heat-insulating and sealing machine layer.
The thermal protection principle of thermal protection structure is as follows inside a kind of aircraft bay section described in the utility model：
Be made of external nacelle load-carrying construction+inside thermal protection shield, external nacelle be heat-resisting load-carrying construction, internal thermal protection
Material selection flexibility thermally protective materials, and can be suppressed according to different parts thermal protection shield thickness requirements using press moulding mode.
According to bay section internal structural space and stent geomery, thermally protective materials are cut into corresponding size, then using can
Thermally protective materials are pasted on inside nacelle by the high temperature adhesive of connection nacelle titanium alloy material and thermally protective materials.
For 1 internal structure feature of bay section, to 4 thickness of the different parts thermal protection shield such as 1 inner wall of bay section and mounting bracket into
Row design；
According to 4 thickness requirements of thermal protection shield, using press moulding mode by flexible thermally protective materials organosilicon heat-insulating and sealing agent pressure
Different-thickness sheet body is made；
According to rib 2 and 3 design feature of rib pit and size, thermal protection shield 4 is cropped to corresponding size；
By adhesive layer 5（It is preferred that high temperature adhesive）Coated in 4 adhesive surface of thermal protection shield, then thermal protection shield 4 is pasted on
1 inner wall of bay section, filling rib pit 3；
According to 1 inner surface space size of bay section, monoblock thermal protection shield 4 is pasted on 1 inner wall of bay section, while cover rib
Pit 3 and rib 2, and thermal protection coating is formed in joint filling thermal protection coating, complete thermal protection inside bay section.
It should be noted that above example is merely intended for describing the technical solutions of the present application, but not for limiting the present application.Although ginseng
The utility model is described in detail according to preferred embodiment, it will be understood by those of ordinary skill in the art that, it can be to reality
It is modified or replaced equivalently with novel technical solution, it, should all without departing from the range of technical solutions of the utility model
Cover in the right of the utility model.
Claims (6)
1. thermal protection structure inside a kind of aircraft bay section, which is characterized in that the structure includes：
Bay section, shape are tube body；
Several ribs are axially convexly equipped in bay section inner wall along bay section, and are intervally arranged along bay section inner circumferential, and adjacent two rib is in bay section
A rib pit is formed between wall；
Several thermal protection shields, are sheet or bulk, and shape is matched with the rib pit shape, attached respectively by adhesive layer
In on the bay section inner wall in each rib pit, the thermal protection to bay section inner wall is formed.
2. thermal protection structure inside aircraft bay section according to claim 1, which is characterized in that the adjacent thermal protection shield
Between thermal protection coating is coated at gap.
3. thermal protection structure inside aircraft bay section according to claim 1, which is characterized in that the thermal protection shield is also logical
It crosses adhesive layer and is attached at rib surface, formed and bay section inner wall is completely covered.
4. thermal protection structure inside the aircraft bay section according to claim 1 or 3, which is characterized in that the thermal protection shield
For flexible thermal protection shield.
5. thermal protection structure inside aircraft bay section according to claim 1 or 3, which is characterized in that the adhesive layer is
High temperature adhesive layer.
6. thermal protection structure inside the aircraft bay section according to claim 1 or 3, which is characterized in that the thermal protection shield
For organosilicon heat-insulating and sealing machine layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721631008.3U CN207496916U (en) | 2017-11-30 | 2017-11-30 | Thermal protection structure inside a kind of aircraft bay section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721631008.3U CN207496916U (en) | 2017-11-30 | 2017-11-30 | Thermal protection structure inside a kind of aircraft bay section |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207496916U true CN207496916U (en) | 2018-06-15 |
Family
ID=62507520
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721631008.3U Active CN207496916U (en) | 2017-11-30 | 2017-11-30 | Thermal protection structure inside a kind of aircraft bay section |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207496916U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927943A (en) * | 2019-04-04 | 2019-06-25 | 北京卫星制造厂有限公司 | Recoverable airship solar heat protection and carrying integral structure |
| CN113021226A (en) * | 2021-03-03 | 2021-06-25 | 航天特种材料及工艺技术研究所 | Sleeving tool and sleeving method for upper closed type outer heat-proof layer of cabin section |
| CN113955076A (en) * | 2021-11-11 | 2022-01-21 | 湖北航天技术研究院总体设计所 | Aircraft with wing and cabin section heat insulation structure |
| CN116280159A (en) * | 2023-05-18 | 2023-06-23 | 北京凌空天行科技有限责任公司 | Aircraft combined cabin section fixed wing structure |
| CN116923734A (en) * | 2023-08-15 | 2023-10-24 | 北京新风航天装备有限公司 | Assembling method of inner heat insulation layer of nano material |
-
2017
- 2017-11-30 CN CN201721631008.3U patent/CN207496916U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927943A (en) * | 2019-04-04 | 2019-06-25 | 北京卫星制造厂有限公司 | Recoverable airship solar heat protection and carrying integral structure |
| CN109927943B (en) * | 2019-04-04 | 2022-03-04 | 北京卫星制造厂有限公司 | Heat-proof and bearing integrated structure of return airship |
| CN113021226A (en) * | 2021-03-03 | 2021-06-25 | 航天特种材料及工艺技术研究所 | Sleeving tool and sleeving method for upper closed type outer heat-proof layer of cabin section |
| CN113955076A (en) * | 2021-11-11 | 2022-01-21 | 湖北航天技术研究院总体设计所 | Aircraft with wing and cabin section heat insulation structure |
| CN116280159A (en) * | 2023-05-18 | 2023-06-23 | 北京凌空天行科技有限责任公司 | Aircraft combined cabin section fixed wing structure |
| CN116280159B (en) * | 2023-05-18 | 2023-08-29 | 北京凌空天行科技有限责任公司 | Aircraft combined cabin section fixed wing structure |
| CN116923734A (en) * | 2023-08-15 | 2023-10-24 | 北京新风航天装备有限公司 | Assembling method of inner heat insulation layer of nano material |
| CN116923734B (en) * | 2023-08-15 | 2024-01-05 | 北京新风航天装备有限公司 | Assembling method of inner heat insulation layer of nano material |
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