CN109573094A - A kind of temperature barrier based on the docking of aircraft bay section - Google Patents
A kind of temperature barrier based on the docking of aircraft bay section Download PDFInfo
- Publication number
- CN109573094A CN109573094A CN201811481114.7A CN201811481114A CN109573094A CN 109573094 A CN109573094 A CN 109573094A CN 201811481114 A CN201811481114 A CN 201811481114A CN 109573094 A CN109573094 A CN 109573094A
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- Prior art keywords
- bay section
- protective layer
- shell
- docking
- bay
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
- Casings For Electric Apparatus (AREA)
Abstract
The invention discloses a kind of temperature barriers based on the docking of aircraft bay section, and the temperature barrier includes: the first bay section shell, is cladded with the first bay section protective layer；Second bay section shell is connected with the first bay section shell；The second bay section shell is cladded with the second bay section protective layer being connected with the first bay section protective layer；Cover board is overlapped, adapt to that the first bay section protective layer and the second bay section protective layer formed bilateral step-like intracavitary is simultaneously connected on the first bay section shell.Its bay section shell of the present invention and bay section protective layer, bay section protective layer and overlap joint cover board are independently installed, overlap joint cover board makes the first bay section protective layer and the second bay section protective layer mutually indepedent, effectively prevents the influence that the first bay section protective layer and the second bay section protective layer slide at high temperature under high pressure；The step-like structure of overlap joint cover board effectively prevents high speed hot-fluid from heating or enter inside bay section for bay section shell.
Description
Technical field
The present invention relates to the thermal protection technology fields of high-speed aircraft bay section docking structure, and in particular to one kind is based on flight
The temperature barrier of device bay section docking.
Background technique
Each bay section connection of aircraft is generally using " u "-shaped frame, L shape frame, the connection of bis- " L shape " shape frames, the connection of these types
It is larger to occupy space in cabin；After bay section docking or connection, one of gap will form between bay section, if not handling gap, meeting
Causing high speed hot-fluid to enter in cabin influences single machine work in cabin, particularly with the severe aircraft of flight environment of vehicle, bay section protective layer,
That is bay section heat shield, it may occur that sliding or deformation cause butt seam to become larger, high speed hot-fluid is directly to bay section metal shell
Heating, leads to bay section failure effect flight success or failure.
Bay section docking thermal protection structure severe for flight environment of vehicle at present generally uses the unilateral bridging arrangement of protective layer
Or embedded structure, guarantee still protect butt seam after protective layer has axial slide, the protective layer of this type overlaps knot
Structure and bay section large area protective layer are integrated, are suitble to bay section " u "-shaped frame and L shape frame connecting structure.
For the aircraft of high Mach long-time endoatmosphere flight, the especially aircraft of minor diameter bay section, in cabin
Space is limited, in cabin load, radially connected thermal protection structure difficult design higher than coefficient, designed reliability it is difficult to ensure that, for protect
The convenience installed after card bay section docking, protective layer bridging arrangement needs independently installed.
Summary of the invention
In view of the deficiencies in the prior art, the purpose of the present invention is to provide a kind of based on the docking of aircraft bay section
Temperature barrier, bay section shell and bay section protective layer, bay section protective layer and overlap joint cover board are independently installed, and overlap joint cover board makes the
One bay section protective layer and the second bay section protective layer are mutually indepedent, effectively prevent the first bay section protective layer and the second bay section protective layer
The influence slid at high temperature under high pressure；Overlap joint cover board step-like structure effectively prevents high speed hot-fluid for bay section shell heat or
Into inside bay section.
To achieve the above objectives, the technical solution adopted by the present invention is that:
A kind of temperature barrier based on the docking of aircraft bay section, the temperature barrier include:
First bay section shell is cladded with the first bay section protective layer；
Second bay section shell is connected with the first bay section shell；The second bay section shell is cladded with and described
The second connected bay section protective layer of one bay section protective layer；
Cover board is overlapped, the bilateral step that the first bay section protective layer and the second bay section protective layer are formed is adapted to
Shape is intracavitary and is connected on the first bay section shell.
Based on the above technical solution, the overlap joint cover board is in T-shape structure；
The overlap joint cover board adapts to the bilateral list that the first bay section protective layer and the second bay section protective layer are formed
It is step-like intracavitary.
Based on the above technical solution, the overlap joint cover board and the first bay section protective layer, second bay section
There are gaps for the side for the bilateral step-like chamber that protective layer is formed.
Based on the above technical solution, the second bay section shell has bending part, undertakes on the bending part
The first bay section shell；Wherein, the first bay section shell is fixed on the second bay section shell by fastener.
Based on the above technical solution, cavity is equipped in the first bay section shell on the bending part,
The cavity is used to connect the voussoir connection component of the first bay section shell Yu the second bay section shell for accommodating portion.
Based on the above technical solution, the voussoir connection component includes:
At least two wedge attachments are placed on the second bay section shell, and part is built in the cavity；
Anti-channeling block is set in the inner cavity that the wedge attachment space is uniformly formed, for preventing the voussoir from connecting
Part is detached from aircraft flight vibration；Wherein, the anti-channeling block is used and is fixed on the second bay section shell described in fastener；Institute
The direction that is screwed into for stating fastener is from the first bay section shell to the second bay section shell.
Based on the above technical solution, the wedge attachment remainder adapts on the second bay section shell
The second notch in.
Based on the above technical solution, the first bay section shell is equipped with opposite with second notch first
Notch, the wedge attachment remainder adapt in the conduit that first notch and second notch are formed.
Based on the above technical solution, the shape adaptation of the anti-channeling block is in the inner cavity that the Wedge-shape connector is formed
In.
Based on the above technical solution, the overlap joint cover board is mounted on first cabin by several solar heat protection connectors
On piece housing.
Compared with the prior art, the advantages of the present invention are as follows:
The present invention provides a kind of temperature barrier based on the docking of aircraft bay section, bay section shell and bay section protective layer,
Bay section protective layer and overlap joint cover board are independently installed, and overlap joint cover board makes the first bay section protective layer and the second bay section protective layer mutually only
It is vertical, effectively prevent the influence that the first bay section protective layer and the second bay section protective layer slide at high temperature under high pressure；Overlap cover board
Step-like structure effectively prevents high speed hot-fluid from heating or enter inside bay section for bay section shell.Flight for minor diameter bay section
Device, space is limited in cabin, loads higher than coefficient in cabin, is connected using voussoir connection component, reduces bay section housing coupling part point
Shared inner space realizes being reliably connected between bay section shell.
Detailed description of the invention
Fig. 1 is a kind of complete section main view of the temperature barrier based on the docking of aircraft bay section in the embodiment of the present invention；
Fig. 2 is sectional view along A-A in Fig. 1；
Fig. 3 removes the complete of overlap joint cover board for the temperature barrier based on the docking of aircraft bay section a kind of in the embodiment of the present invention
Cut open main view；
Fig. 4 is the connection of the first bay section shell and the second bay section shell (removing voussoir connection component) in the embodiment of the present invention
Main sectional view；
Fig. 5 removes bowing for overlap joint cover board for the temperature barrier based on the docking of aircraft bay section a kind of in the embodiment of the present invention
View；
Fig. 6 is the connection top view of the first bay section shell and the second bay section shell in the embodiment of the present invention；
Fig. 7 is the connection main view of the first bay section shell and the second bay section shell in the embodiment of the present invention；
In figure: 1- the first bay section protective layer, 2- overlap cover board, 3- the second bay section protective layer, 4- the first bay section shell, 41-
Cavity, the first notch of 42-, 5- the second bay section shell, the second notch of 51-, 6- solar heat protection connector, 7- wedge attachment, 8- fastening
Part, 9- anti-channeling block.
Specific embodiment
Clear, complete description is carried out below with reference to technical solution of the attached drawing to embodiment each in the present invention, it is clear that institute
The embodiment of description is only a part of the embodiments of the present invention, instead of all the embodiments.Based on the embodiment of the present invention,
Those of ordinary skill in the art's obtained all other embodiment without making creative work belongs to this
Invent protected range.
In the description of the present invention, it should be noted that term " center ", "upper", "lower", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" be based on the orientation or positional relationship shown in the drawings, merely to
Convenient for description the present invention and simplify description, rather than the device or element of indication or suggestion meaning must have a particular orientation,
It is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.In addition, term " first ", " second ",
" third " is used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.It should be pointed out that all attached drawings are illustrative expression.For the ordinary skill of this field
For personnel, the concrete meaning of above-mentioned term in the present invention can be understood with concrete condition.
The present invention is described in further detail below through specific implementation examples and in conjunction with the accompanying drawings.
Embodiment 1
Referring to shown in Fig. 1~7, the embodiment of the present invention provides a kind of temperature barrier based on the docking of aircraft bay section, institute
State temperature barrier include the first bay section shell 4, the second bay section shell 5, the first bay section protective layer 1, the second bay section protective layer 3 and
Overlap cover board 2；
The first bay section shell 4 is cladded with the first bay section protective layer 1；The second bay section shell 5 and first cabin
Piece housing 4 is connected；The second bay section shell 5 is cladded with the second bay section protective layer being connected with the first bay section protective layer 1
3；The first bay section protective layer 1, the second bay section protective layer 3 are efficient heat insulation material, are respectively and fixedly installed to institute
State the first bay section shell 4, outside the second bay section shell 5.
Overlap cover board 2, adapt to the first bay section protective layer 1 and the second bay section protective layer 3 formed it is bilateral
It is step-like intracavitary and be connected on the first bay section shell 4；And the overlap joint cover board 2 and the first bay section protective layer 1, institute
Stating the side of bilateral step-like chamber of the second bay section protective layer 3 formation, there are gaps；Specifically, if the overlap joint cover board 2 passes through
Dry solar heat protection connector 6 is mounted on the first bay section shell 4, under high Mach flight environment of vehicle the first bay section protective layer 1,
The second bay section protective layer 3 can occur to slide or shrink, and the bilateral step-like overlap joint cover board 2 can carry out bay section shell
Effectively prevent that heat-insulated, prevention high-speed flow heats bay section shell or enters inside bay section；In embodiments of the present invention, the overlap joint
Cover board 2 is in T-shape structure；The overlap joint cover board 2 and the first bay section protective layer 1 and the second bay section protective layer 3 formation
Bilateral separate unit stage structure, T-shape structure effectively prevent heat-insulated, prevention high-speed flow to bay section shell for the overlap joint cover board 2 in satisfaction
Body heats or enters the simple structure under the premise of bay section inside.In the present embodiment, the overlap joint cover board 2 select it is efficiently anti-every
Hot material.
As further improving and supplementing to the present embodiment, as shown in Figure 1, the second bay section shell 5 has bending
Portion 52 undertakes the first bay section shell 4 on the bending part 52；Wherein, the first bay section shell 4 passes through fastener 8
It is fixed on the second bay section shell 5.Cavity 41 is equipped in the first bay section shell 4 on the bending part 52,
The cavity 41 is connect for connecting the first bay section shell 4 with the voussoir of the second bay section shell 5 for accommodating portion
Component.The first bay section shell 4 is undertaken on the second bay section shell 5, and this connection type is suitable for minor diameter bay section
Aircraft, since space is limited in cabin, in cabin load it is higher than coefficient, using voussoir connection effectively reduce bay section connection structure institute
Account for inner space.
As further improving and supplementing to the present embodiment, as figures 2-6, the voussoir connection component includes extremely
Few two wedge attachments 7, anti-channeling block 9；At least two wedge attachments 7 are placed on the second bay section shell 5, and part is built in
In the cavity 41.In the present embodiment, the wedge attachment 7 is two；The anti-channeling block 9 is set to the wedge attachment
In the inner cavity that 7 spaces are uniformly formed, and the shape adaptation of the anti-channeling block 9 is used in the inner cavity that the Wedge-shape connector 7 is formed
In prevent the wedge attachment 7 aircraft flight vibration in be detached from；Wherein, the anti-channeling block 9 is fixed on using fastener 8
On the second bay section shell 5；The direction that is screwed into of the fastener 8 is from the first bay section shell 4 to second bay section
Shell 5.
Specifically, as shown in fig. 7,7 remainder of the wedge attachment adapts on the second bay section shell 5
In two notches 51.The first bay section shell 4 is equipped with first notch 42 opposite with second notch 51, and the voussoir connects
7 remainder of fitting adapts in the conduit that first notch 42 and second notch 51 are formed.
The wedge attachment 7 is in " L " shape, and one end is lying in first notch 42 and second notch 51,
The other end in the cavity 41, be equipped between two wedge attachments 7 one be in rectangle anti-channeling block 9, and it is described anti-
It alters block 9 and is fixedly mounted on the movement for being used to limit the wedge attachment 7 on the second bay section shell 5 using fastener 8,
In the present embodiment fastener 8 be attachment screw, prevent can the wedge attachment 7 aircraft flight vibration in be detached from, realize
The first bay section shell 4 and the second bay section shell 5 are reliably connected.
After the completion of the first bay section shell 4 is connected with the second bay section shell 5 using voussoir connection component；First
Bay section protective layer 1, the second bay section protective layer 3 are just installed before the first bay section shell 4 and the second bay section shell 5 connect
On the first bay section shell 4 and the second bay section shell 5 or the first bay section protective layer 1, the second bay section protective layer 3
The first bay section shell 4 and described the are being mounted on after the first bay section shell 4 and the second bay section shell 5 connection
On two bay section shells 5；Specifically, the voussoir connection component is fully fallen within the scope of the bottom surface of the overlap joint cover board 2.
The embodiment of the present invention provides a kind of temperature barrier based on the docking of aircraft bay section, and bay section shell and bay section are anti-
Sheath, bay section protective layer and overlap joint cover board are independently installed, and overlap joint cover board makes the first bay section protective layer 1 and the second bay section protective layer
3 is mutually indepedent, effectively prevents the influence that the first bay section protective layer 1 and the second bay section protective layer 3 slide at high temperature under high pressure；It takes
The step-like structure of connects cover plate 2 effectively prevents high speed hot-fluid from heating or enter inside bay section for bay section shell.For minor diameter
The aircraft of bay section, space is limited in cabin, loads higher than coefficient in cabin, is connected using voussoir connection component, reduces bay section shell
Inner space shared by body coupling part realizes being reliably connected between bay section shell.
The present invention is not limited to the above-described embodiments, for those skilled in the art, is not departing from
Under the premise of the principle of the invention, several improvements and modifications can also be made, these improvements and modifications are also considered as protection of the invention
Within the scope of.The content being not described in detail in this specification belongs to the prior art well known to professional and technical personnel in the field.
Claims (10)
1. a kind of temperature barrier based on the docking of aircraft bay section, which is characterized in that the temperature barrier includes:
First bay section shell (4) is cladded with the first bay section protective layer (1)；
Second bay section shell (5) is connected with the first bay section shell (4)；The second bay section shell (5) is cladded with and institute
State the second connected bay section protective layer (3) of the first bay section protective layer (1)；
It overlaps cover board (2), adapts to pair that the first bay section protective layer (1) and the second bay section protective layer (3) are formed
Side platform scalariform is intracavitary and is connected on the first bay section shell (4).
2. the temperature barrier according to claim 1 based on the docking of aircraft bay section, which is characterized in that the overlap joint lid
Plate (2) is in T-shape structure；
Overlap joint cover board (2) adapts to pair that the first bay section protective layer (1) and the second bay section protective layer (3) are formed
Side separate unit scalariform is intracavitary.
3. the temperature barrier according to claim 1 based on the docking of aircraft bay section, which is characterized in that the overlap joint lid
It deposits the side for the bilateral step-like chamber that plate (2) is formed with the first bay section protective layer (1), the second bay section protective layer (3)
In gap.
4. the temperature barrier according to claim 1 based on the docking of aircraft bay section, which is characterized in that second cabin
Piece housing (5) has bending part (52), undertakes the first bay section shell (4) on the bending part (52)；Wherein, described
One bay section shell (4) is fixed on the second bay section shell (5) by fastener (8).
5. the temperature barrier according to claim 4 based on the docking of aircraft bay section, which is characterized in that be located at the folding
Cavity (41) are equipped in the first bay section shell (4) on turn of bilge (52), the cavity (41) is for accommodating portion for connecting
Connect the voussoir connection component of the first bay section shell (4) Yu the second bay section shell (5).
6. the temperature barrier according to claim 5 based on the docking of aircraft bay section, which is characterized in that the voussoir connects
Connected components include:
At least two wedge attachments (7) are placed on the second bay section shell (5), and part is built in the cavity (41)
In；
Anti-channeling block (9) is set in the inner cavity that the wedge attachment (7) space is uniformly formed, for preventing the voussoir from connecting
Fitting (7) is detached from aircraft flight vibration；Wherein, the anti-channeling block (9) is fixed on second cabin using fastener (8)
On piece housing (5)；The direction that is screwed into of the fastener (8) is from the first bay section shell (4) Xiang Suoshu the second bay section shell
(5)。
7. the temperature barrier according to claim 6 based on the docking of aircraft bay section, which is characterized in that the voussoir connects
Fitting (7) remainder adapts in the second notch (51) on the second bay section shell (5).
8. the temperature barrier according to claim 7 based on the docking of aircraft bay section, which is characterized in that first cabin
Piece housing (4) is equipped with first notch (42) opposite with second notch (51), wedge attachment (7) remainder
It adapts in the conduit of first notch (42) and second notch (51) formation.
9. the temperature barrier according to claim 6 based on the docking of aircraft bay section, which is characterized in that the anti-channeling block
(9) shape adaptation is in the inner cavity that the Wedge-shape connector (7) is formed.
10. the temperature barrier according to claim 1 based on the docking of aircraft bay section, which is characterized in that the overlap joint
Cover board (2) is mounted on the first bay section shell (4) by several solar heat protection connectors (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811481114.7A CN109573094B (en) | 2018-12-05 | 2018-12-05 | Thermal protection device based on butt joint of aircraft cabin sections |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811481114.7A CN109573094B (en) | 2018-12-05 | 2018-12-05 | Thermal protection device based on butt joint of aircraft cabin sections |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109573094A true CN109573094A (en) | 2019-04-05 |
| CN109573094B CN109573094B (en) | 2020-08-18 |
Family
ID=65926052
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811481114.7A Active CN109573094B (en) | 2018-12-05 | 2018-12-05 | Thermal protection device based on butt joint of aircraft cabin sections |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109573094B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111114771A (en) * | 2019-11-25 | 2020-05-08 | 中国空气动力研究与发展中心 | Ultrahigh-temperature end heat sealing structure of hypersonic aircraft |
| CN113978696A (en) * | 2021-11-08 | 2022-01-28 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202320771U (en) * | 2011-09-26 | 2012-07-11 | 江西洪都航空工业集团有限责任公司 | Connecting structure with inner fixture block for cabin sections |
| US8356772B2 (en) * | 2008-08-12 | 2013-01-22 | Airbus Operations Gmbh | Lightweight structure |
| WO2013142902A2 (en) * | 2012-03-29 | 2013-10-03 | Rosebank Engineering Pty Ltd | Methods for treating aircraft structures |
| CN105346703A (en) * | 2015-11-19 | 2016-02-24 | 江西洪都航空工业集团有限责任公司 | Cabin section connecting structure |
-
2018
- 2018-12-05 CN CN201811481114.7A patent/CN109573094B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8356772B2 (en) * | 2008-08-12 | 2013-01-22 | Airbus Operations Gmbh | Lightweight structure |
| CN202320771U (en) * | 2011-09-26 | 2012-07-11 | 江西洪都航空工业集团有限责任公司 | Connecting structure with inner fixture block for cabin sections |
| WO2013142902A2 (en) * | 2012-03-29 | 2013-10-03 | Rosebank Engineering Pty Ltd | Methods for treating aircraft structures |
| CN105346703A (en) * | 2015-11-19 | 2016-02-24 | 江西洪都航空工业集团有限责任公司 | Cabin section connecting structure |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111114771A (en) * | 2019-11-25 | 2020-05-08 | 中国空气动力研究与发展中心 | Ultrahigh-temperature end heat sealing structure of hypersonic aircraft |
| CN113978696A (en) * | 2021-11-08 | 2022-01-28 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
| CN113978696B (en) * | 2021-11-08 | 2024-04-09 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109573094B (en) | 2020-08-18 |
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