CN109573094B - Thermal protection device based on butt joint of aircraft cabin sections - Google Patents
Thermal protection device based on butt joint of aircraft cabin sections Download PDFInfo
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- CN109573094B CN109573094B CN201811481114.7A CN201811481114A CN109573094B CN 109573094 B CN109573094 B CN 109573094B CN 201811481114 A CN201811481114 A CN 201811481114A CN 109573094 B CN109573094 B CN 109573094B
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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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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a thermal protection device based on butt joint of aircraft cabin sections, which comprises: the first cabin section shell is covered with a first cabin section protective layer; a second deck section housing coupled to the first deck section housing; a second cabin section protective layer connected with the first cabin section protective layer is covered outside the second cabin section shell; the lap joint cover plate is adapted to a double-side step-shaped cavity formed by the first cabin section protective layer and the second cabin section protective layer and abuts against the first cabin section shell. According to the invention, the cabin section shell, the cabin section protective layer and the lap joint cover plate are independently installed, and the lap joint cover plate enables the first cabin section protective layer and the second cabin section protective layer to be independent from each other, so that the influence of slippage of the first cabin section protective layer and the second cabin section protective layer under high temperature and high pressure is effectively avoided; the step-like structure of the lap cover plate effectively prevents high-speed heat flow from heating the cabin section shell or entering the cabin section.
Description
Technical Field
The invention relates to the technical field of thermal protection of a butt joint structure of cabin sections of a high-speed aircraft, in particular to a thermal protection device based on butt joint of the cabin sections of the aircraft.
Background
The connection of each cabin section of the aircraft generally adopts a U-shaped frame, an L-shaped frame and a double L-shaped frame, and the connection of the U-shaped frame, the L-shaped frame and the double L-shaped frame occupies a large space in the cabin; after the cabin sections are in butt joint or connected, a gap can be formed between the cabin sections, if the gap is not processed, high-speed heat flow can enter the cabin to influence single-machine work in the cabin, particularly for an aircraft with a severe flying environment, a cabin section protective layer, namely a cabin section heat-proof layer, can slide or deform to gradually enlarge the butt joint gap, and the high-speed heat flow directly heats a cabin section metal shell to influence the failure of the cabin section to influence the success or failure of flying.
At present, a protective layer single-side lap joint structure or an embedded structure is generally adopted for a cabin section butt joint heat protection structure in a severe flight environment, the protective layer is guaranteed to be capable of protecting butt joint gaps after axial sliding, the protective layer lap joint structure and the cabin section large-area protective layer are integrated, and the protective layer butt joint heat protection structure is suitable for a U-shaped frame and an L-shaped frame connecting structure of the cabin section.
For aircrafts flying in high Mach long-time atmosphere, especially aircrafts in small-diameter cabin sections, the space in the cabin is limited, the filling ratio coefficient in the cabin is high, the radial connection thermal protection structure is difficult to design, the design reliability is difficult to guarantee, and in order to guarantee the convenience of installation after butt joint of the cabin sections, the protective layer lap joint structure needs to be independently installed.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a thermal protection device based on butt joint of aircraft cabin sections, wherein a cabin section shell, a cabin section protective layer and a lap joint cover plate are independently installed, and the lap joint cover plate enables the first cabin section protective layer and the second cabin section protective layer to be mutually independent, so that the influence of slippage of the first cabin section protective layer and the second cabin section protective layer under high temperature and high pressure is effectively avoided; the step-like structure of the lap cover plate effectively prevents high-speed heat flow from heating the cabin section shell or entering the cabin section.
In order to achieve the above purposes, the technical scheme adopted by the invention is as follows:
a thermal protection device based on docking of aircraft sections, the thermal protection device comprising:
the first cabin section shell is covered with a first cabin section protective layer;
a second deck section housing coupled to the first deck section housing; a second cabin section protective layer connected with the first cabin section protective layer is covered outside the second cabin section shell;
the lap joint cover plate is adapted to a double-side step-shaped cavity formed by the first cabin section protective layer and the second cabin section protective layer and abuts against the first cabin section shell.
On the basis of the technical scheme, the lap joint cover plate is of a T-shaped structure;
the lap joint cover plate is adapted to a double-side single-step-shaped cavity formed by the first cabin section protective layer and the second cabin section protective layer.
On the basis of the technical scheme, gaps exist on the side surfaces of the bilateral step-shaped cavity formed by the lap joint cover plate, the first cabin section protective layer and the second cabin section protective layer.
On the basis of the technical scheme, the second cabin shell is provided with a bent part, and the first cabin shell is received on the bent part; wherein the first deck section housing is secured to the second deck section housing by fasteners.
On the basis of the technical scheme, a cavity is formed in the first cabin shell located on the bent portion, and the cavity is used for accommodating a wedge connecting assembly of a part used for connecting the first cabin shell and the second cabin shell.
On the basis of the above technical scheme, the wedge connecting assembly includes:
at least two wedge connectors disposed on the second deck section housing and partially disposed in the cavity;
the anti-channeling blocks are arranged in an inner cavity formed by uniformly distributing the space of the wedge block connecting piece and are used for preventing the wedge block connecting piece from being separated in the flying vibration of the aircraft; the anti-channeling block is fixed on the second cabin section shell through a fastener; the fastener is threaded in a direction from the first deck section housing to the second deck section housing.
On the basis of the technical scheme, the rest part of the wedge connector is matched in a second notch on the second cabin shell.
On the basis of the technical scheme, a first notch opposite to the second notch is formed in the first cabin shell, and the rest part of the wedge block connecting piece is matched in a channel formed by the first notch and the second notch.
On the basis of the technical scheme, the shape of the anti-channeling block is matched with an inner cavity formed by the wedge block connecting piece.
On the basis of the technical scheme, the lap joint cover plate is installed on the first cabin section shell through a plurality of heat-proof connecting pieces.
Compared with the prior art, the invention has the advantages that:
the invention provides a thermal protection device based on butt joint of cabin sections of an aircraft, wherein a cabin section shell, a cabin section protective layer and a lap joint cover plate are independently installed, and the lap joint cover plate enables the first cabin section protective layer and the second cabin section protective layer to be mutually independent, so that the influence of slippage of the first cabin section protective layer and the second cabin section protective layer at high temperature and high pressure is effectively avoided; the step-like structure of the lap cover plate effectively prevents high-speed heat flow from heating the cabin section shell or entering the cabin section. For the aircraft with the small-diameter cabin, the space in the cabin is limited, the filling ratio coefficient in the cabin is high, the cabin is connected by the wedge block connecting assembly, the internal space occupied by the connecting part of the cabin shell is reduced, and the reliable connection between the cabin shells is realized.
Drawings
FIG. 1 is a front elevational view, in full section, of a thermal protection device based on docking of aircraft sections in an embodiment of the present invention;
FIG. 2 is a sectional view taken along line A-A of FIG. 1;
FIG. 3 is a front elevational view, in full section, of a thermal protection device with a lap joint cover removed, based on aircraft cabin docking, in an embodiment of the present invention;
FIG. 4 is a front cross-sectional view of the connection of a first deck section housing and a second deck section housing (with the wedge connection assembly removed) in an embodiment of the present invention;
FIG. 5 is a top view of a thermal protection device with a detached lap cover plate based on aircraft cabin docking according to an embodiment of the present disclosure;
FIG. 6 is a top view of the connection of a first deck section housing and a second deck section housing in an embodiment of the present invention;
FIG. 7 is a front view of the connection of a first deck section housing and a second deck section housing in an embodiment of the present invention;
in the figure: 1-first cabin section protective layer, 2-lap joint cover plate, 3-second cabin section protective layer, 4-first cabin section shell, 41-cavity, 42-first notch, 5-second cabin section shell, 51-second notch, 6-heat-proof connector, 7-wedge connector, 8-fastener and 9-anti-channeling block.
Detailed Description
The technical solutions of the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings, and it is to be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without any inventive step, are within the scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. It is to be noted that all the figures are exemplary representations. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The present invention will be described in further detail below with reference to specific embodiments and with reference to the attached drawings.
Example 1
Referring to fig. 1 to 7, an embodiment of the invention provides a thermal protection device based on aircraft cabin segment butt joint, where the thermal protection device includes a first cabin segment shell 4, a second cabin segment shell 5, a first cabin segment protective layer 1, a second cabin segment protective layer 3, and a lap joint cover plate 2;
a first cabin section protective layer 1 covers the first cabin section shell 4; the second cabin shell 5 is connected with the first cabin shell 4; a second cabin protective layer 3 connected with the first cabin protective layer 1 is covered outside the second cabin shell 5; the first cabin section protective layer 1 and the second cabin section protective layer 3 are both made of high-efficiency heat-proof materials and are fixedly mounted outside the first cabin section shell 4 and the second cabin section shell 5 respectively.
The lap joint cover plate 2 is adapted to a double-side step-shaped cavity formed by the first cabin section protective layer 1 and the second cabin section protective layer 3 and abuts against the first cabin section shell 4; a gap is formed on the side surface of a double-side step-shaped cavity formed by the lap joint cover plate 2, the first cabin section protective layer 1 and the second cabin section protective layer 3; specifically, the lap joint cover 2 is installed on the first cabin section shell 4 through a plurality of heat-proof connecting pieces 6, the first cabin section protective layer 1 and the second cabin section protective layer 3 can slide or shrink under the high Mach flight environment, and the lap joint cover 2 with the step-shaped two sides can effectively prevent and insulate heat of the cabin section shell and prevent high-speed airflow from heating the cabin section shell or entering the cabin section; in the embodiment of the invention, the lap joint cover plate 2 is in a T-shaped structure; the lap joint cover plate 2, the first cabin section protective layer 1 and the second cabin section protective layer 3 form a double-side single-step structure, and the T-shaped structure is the simplest structure of the lap joint cover plate 2 on the premise of effectively preventing heat insulation and preventing high-speed airflow from heating the cabin section shell or entering the cabin section. In this embodiment, the lap cover plate 2 is made of a high-efficiency heat-proof material.
As a further improvement and supplement to the present embodiment, as shown in fig. 1, the second cabin shell 5 has a bent portion, and the first cabin shell 4 is received on the bent portion; wherein the first pod housing 4 is secured to the second pod housing 5 by fasteners 8. A cavity 41 is arranged in the first cabin shell 4 on the bent portion, and the cavity 41 is used for accommodating a part of a wedge connecting assembly for connecting the first cabin shell 4 and the second cabin shell 5. The first cabin section shell 4 is connected to the second cabin section shell 5, the connection mode is suitable for an aircraft with a small-diameter cabin section, the cabin space is limited, the cabin filling ratio coefficient is high, and the occupied inner space of the cabin section connection structure is effectively reduced by wedge block connection.
As a further improvement and supplement to the present embodiment, as shown in fig. 2 to 6, the wedge connecting assembly includes at least two wedge connecting pieces 7 and a tamper-proof block 9; at least two wedge connectors 7 are placed on the second deck section housing 5 and are partially embedded in the cavity 41. In this embodiment, there are two wedge connectors 7; the anti-channeling blocks 9 are arranged in inner cavities formed by uniformly distributed spaces of the wedge block connecting pieces 7, and the shapes of the anti-channeling blocks 9 are matched with the inner cavities formed by the wedge block connecting pieces 7 and used for preventing the wedge block connecting pieces 7 from being separated in flight vibration of an aircraft; wherein the anti-channeling block 9 is fixed to the second deck section housing 5 using a fastener 8; the fastener 8 is screwed in the direction from the first cabin shell 4 to the second cabin shell 5.
Specifically, as shown in fig. 7, the remainder of the wedge connector 7 fits within a second slot 51 on the second deck section housing 5. The first cabin shell 4 is provided with a first notch 42 opposite to the second notch 51, and the rest part of the wedge connector 7 is fitted in a channel formed by the first notch 42 and the second notch 51.
The wedge connecting pieces 7 are in an L shape, one end of each wedge connecting piece is horizontally arranged in the first notch 42 and the second notch 51, the other end of each wedge connecting piece is embedded in the cavity 41, a rectangular anti-crossing block 9 is installed between the two wedge connecting pieces 7, the anti-crossing block 9 is fixedly installed on the second cabin section shell 5 through a fastening piece 8 and used for limiting the movement of the wedge connecting pieces 7, the fastening piece 8 is a connecting screw in the embodiment, the wedge connecting pieces 7 are prevented from being separated in flight vibration of an aircraft, and reliable connection of the first cabin section shell 4 and the second cabin section shell 5 is achieved.
After the first cabin section shell 4 and the second cabin section shell 5 are connected by adopting a wedge connecting assembly; a first cabin protective layer 1 and a second cabin protective layer 3 are installed on the first cabin shell 4 and the second cabin shell 5 before the first cabin shell 4 and the second cabin shell 5 are connected, or the first cabin protective layer 1 and the second cabin protective layer 3 are installed on the first cabin shell 4 and the second cabin shell 5 after the first cabin shell 4 and the second cabin shell 5 are connected; in particular, the wedge connection assemblies all fall within the bottom surface of the lap cover 2.
The embodiment of the invention provides a thermal protection device based on butt joint of aircraft cabin sections, wherein a cabin section shell, a cabin section protective layer and a lap joint cover plate are independently installed, and the lap joint cover plate enables a first cabin section protective layer 1 and a second cabin section protective layer 3 to be mutually independent, so that the influence of slippage of the first cabin section protective layer 1 and the second cabin section protective layer 3 under high temperature and high pressure is effectively avoided; the stepped structure of the lap cover 2 effectively prevents high-speed heat flow from heating the cabin shell or entering the cabin interior. For the aircraft with the small-diameter cabin, the space in the cabin is limited, the filling ratio coefficient in the cabin is high, the cabin is connected by the wedge block connecting assembly, the internal space occupied by the connecting part of the cabin shell is reduced, and the reliable connection between the cabin shells is realized.
The present invention is not limited to the above-described embodiments, and it will be apparent to those skilled in the art that various modifications and improvements can be made without departing from the principle of the present invention, and such modifications and improvements are also considered to be within the scope of the present invention. Those not described in detail in this specification are within the skill of the art.
Claims (10)
1. A thermal protection device based on docking of aircraft cabin sections, characterized in that the thermal protection device comprises:
a first cabin section shell (4) covered with a first cabin section protective layer (1);
a second cabin shell (5) connected to the first cabin shell (4); a second cabin section protective layer (3) connected with the first cabin section protective layer (1) is covered outside the second cabin section shell (5);
the lap joint cover plate (2) is adapted to a double-side step-shaped cavity formed by the first cabin section protective layer (1) and the second cabin section protective layer (3) and abuts against the first cabin section shell (4).
2. The thermal protection device based on aircraft cabin docking according to claim 1, characterized in that said lap-joint cover plate (2) is of "T" type structure;
the lap joint cover plate (2) is adapted to a double-side single-step cavity formed by the first cabin section protective layer (1) and the second cabin section protective layer (3).
3. The thermal protection device based on aircraft cabin docking according to claim 1, characterized in that the overlapping cover plates (2) have a gap with the side of the bilateral step-shaped cavity formed by the first and second cabin protection layers (1, 3).
4. The thermal protection device based on aircraft cabin docking according to claim 1, characterized in that the second cabin shell (5) has a bend on which the first cabin shell (4) is received; wherein the first cabin shell (4) is fixed to the second cabin shell (5) by a fastener (8).
5. The aircraft-cabin-docking-based thermal protection device according to claim 4, characterized in that a cavity (41) is provided in the first cabin shell (4) on the bend, the cavity (41) being used to accommodate a wedge connection assembly partially used to connect the first cabin shell (4) with the second cabin shell (5).
6. The aircraft cabin docking-based thermal protection device of claim 5, wherein the wedge connection assembly comprises:
at least two wedge connectors (7) placed on the second deck section casing (5) and partially embedded in the cavity (41);
the anti-channeling blocks (9) are arranged in inner cavities formed by the uniformly distributed space of the wedge block connecting pieces (7) and are used for preventing the wedge block connecting pieces (7) from being separated in the flying vibration of the aircraft; wherein the anti-channeling block (9) is fixed on the second cabin section shell (5) by a fastener (8); the fastening element (8) is screwed in the direction from the first cabin housing (4) to the second cabin housing (5).
7. The aircraft-segment-docking-based thermal protection device according to claim 6, characterized in that the wedge connector (7) remaining portion fits into a second notch (51) on the second segment shell (5).
8. The aircraft-segment-docking-based thermal protection device according to claim 7, characterized in that the first segment shell (4) is provided with a first notch (42) opposite to the second notch (51), the remaining part of the wedge connector (7) fitting into the channel formed by the first notch (42) and the second notch (51).
9. The thermal protection device based on the docking of aircraft sections according to claim 6, characterized in that the shape of the tamper-proof block (9) fits into an inner cavity formed by the wedge connection (7).
10. Thermal protection device based on aircraft cabin docking according to claim 1, characterized in that the lap cover plate (2) is mounted on the first cabin shell (4) by means of several heat protection connections (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 CN109573094A (en) | 2019-04-05 |
| CN109573094B true CN109573094B (en) | 2020-08-18 |
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| 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 |
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| CN (1) | CN109573094B (en) |
Families Citing this family (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 |
| 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 |
Family Cites Families (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 |
| US10093434B2 (en) * | 2012-03-29 | 2018-10-09 | 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 |
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2018
- 2018-12-05 CN CN201811481114.7A patent/CN109573094B/en active Active
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