CN109533283B - Collapsible radome fairing and have its helicopter - Google Patents
Collapsible radome fairing and have its helicopter Download PDFInfo
- Publication number
- CN109533283B CN109533283B CN201811340605.XA CN201811340605A CN109533283B CN 109533283 B CN109533283 B CN 109533283B CN 201811340605 A CN201811340605 A CN 201811340605A CN 109533283 B CN109533283 B CN 109533283B
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- folding
- edge
- section
- fairing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
- B64C7/02—Nacelles
Abstract
The application belongs to the technical field of helicopter nacelle fairing structural design, and particularly relates to a foldable fairing, which comprises: a folding plate, one side edge of which is called a connecting edge and the other side edge opposite to the connecting edge is called a folding edge; the cover plate is provided with one side edge which is called a rotating edge, and the rotating edge is hinged with the folding edge; the cover plate is divided into two sections, wherein one section is in an arc shape and is called an arc section, and the other section is in a straight shape and is called a straight section; the rotating edge is the edge of one side of the straight section far away from the arc section; and at least one connecting rod, wherein one end of each connecting rod is called a connecting end, the other end of each connecting rod is called a folding end, and the folding end is hinged with the inner surface of the arc-shaped section. Furthermore, a helicopter with the foldable fairing is also provided.
Description
Technical Field
The application belongs to the technical field of structural design of a fairing of a helicopter nacelle, and particularly relates to a foldable fairing and a helicopter with the same.
Background
Parts such as main reducer, engine in the helicopter power compartment need carry out routine maintenance, when maintaining, need open the radome fairing on it earlier, for improving work efficiency, the staff is direct with the radome fairing of opening as the platform of trampling when maintaining, no longer builds special platform of trampling for this reason. The height of a fairing on the power cabin of the existing helicopter is basically consistent with that of a power platform of the power cabin after the fairing is opened, and when parts such as a main speed reducer, an engine and the like in the power cabin are maintained, the fairing needs to be stooped down, so that the maintenance is very inconvenient and the maintenance efficiency is influenced; in addition, the size of current radome fairing is great, with it as trampling the platform, the staff steps on and can produce great moment of flexure on it, and the structure is firm inadequately, has certain danger, and great size makes its in-process of opening, can sweep great region, easily bumps with other structures on the helicopter.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a collapsible fairing and helicopter having the same that overcomes or alleviates at least one of the above-mentioned disadvantages.
The technical scheme of the application is as follows:
one aspect provides a foldable fairing comprising:
a folding plate, one side edge of which is called a connecting edge and the other side edge opposite to the connecting edge is called a folding edge;
the cover plate is provided with one side edge which is called a rotating edge, and the rotating edge is hinged with the folding edge; the cover plate is divided into two sections, wherein one section is in an arc shape and is called an arc section, and the other section is in a straight shape and is called a straight section; the rotating edge is the edge of one side of the straight section far away from the arc section;
and at least one connecting rod, wherein one end of each connecting rod is called a connecting end, the other end of each connecting rod is called a folding end, and the folding end is hinged with the inner surface of the arc-shaped section.
According to at least one embodiment of the present application, the folding plates and the cover plates are made of a honeycomb composite material.
According to at least one embodiment of the present application, the fairing further comprises:
the two side walls of the U-shaped angle section of the folding plate clamp the wall surface of one side of the folding plate close to the folding edge;
the two side walls of the straight section U-shaped angle section 5 clamp the wall surface of one side of the straight section close to the rotating edge;
and one leaf plate of each folding hinge is riveted on the top surface of the U-shaped angle section of the folding plate, and the other leaf plate of each folding hinge is riveted on the top surface of the straight section U-shaped angle section 5.
According to at least one embodiment of the present application, the fairing further comprises:
each folding plate embedding piece 7 is embedded into a folding plate, one end of each folding plate embedding piece is in threaded connection with one side wall of the folding plate U-shaped angle bar, and the other end of each folding plate embedding piece is in threaded connection with the other side wall of the folding plate U-shaped angle bar;
and each straight section embedding piece 7 is embedded into the straight section, one end of each straight section embedding piece 7 is in threaded connection with one side wall of the straight section U-shaped angle bar 5, and the other end of each straight section embedding piece 7 is in threaded connection with the other side wall of the straight section U-shaped angle bar 5.
According to at least one embodiment of the present application, there are two links.
According to at least one embodiment of the present application, the fairing further comprises:
the two folding double-lug joints are fixedly provided with the inner surfaces of the arc sections;
each folding monaural joint is fixedly arranged at one folding end and is hinged with one folding binaural joint.
According to at least one embodiment of the present application, the fairing further comprises: two segmental arc embedding subassemblies, every segmental arc embedding subassembly embedding segmental arc, and pass through bolted connection with folding ears joint.
Another aspect provides a helicopter having a power pod with a power platform intersecting a fuselage skin, and comprising any of the fairings described above, wherein,
the connecting ends of the two connecting rods are hinged with the power platform;
the connecting edge of the folding plate is hinged with the power platform;
the cowling has:
in a closed state, the arc-shaped section covers the power platform;
in the opening state, the folding plate deviates towards the skin direction of the fuselage, and the arc section deviates from the upper part of the power platform.
According to at least one embodiment of the application, the folding plate abuts the fuselage skin when the fairing is in the open state.
According to at least one embodiment of the present application, the straight section is parallel to the power platform when the fairing is in the open position.
The application has at least the following beneficial technical effects: a collapsible fairing, and a helicopter having such a fairing, is provided that is hinged to the power platform of the helicopter and that rotates relative to the power platform as the folding plate articulates against the straight section during opening from the closed position to the open position, thereby reducing the area swept by the folding plate and reducing the likelihood of the folding plate colliding with other structures on the helicopter.
Drawings
FIG. 1 is a schematic structural view of a foldable fairing provided in an embodiment of the present application in an open position;
FIG. 2 is a schematic structural view of a foldable fairing provided in accordance with an embodiment of the present application in a closed position;
FIG. 3 is a schematic cross-sectional view of a folded plate hinged to a straight section according to an embodiment of the present application;
FIG. 4 is a schematic structural diagram of a folding binaural joint and a folding monaural joint hinge provided by an embodiment of the present application;
FIG. 5 is a schematic cross-sectional view of a folded binaural joint secured to an arcuate segment as provided by an embodiment of the present application;
fig. 6 is a schematic structural diagram of a folding plate hinged to a power platform according to an embodiment of the present application.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. 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.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
The present application is described in further detail below with reference to fig. 1 to 6.
One aspect provides a foldable fairing comprising:
a folding plate 1, one side edge of which is called a connecting edge and the other side edge opposite to the connecting edge is called a folding edge;
a cover plate 2, one side edge of which is called a turning edge, and the turning edge is hinged with the folding edge; the cover plate 2 is divided into two sections, wherein one section is in an arc shape and is called an arc section 21, and the other section is in a straight shape and is called a straight section 22; the rotating edge is the edge of one side of the straight section far away from the arc section 21;
at least one link 3, each link 3 having one end called a link end and the other end called a folded end, the folded end being hinged to the inner surface of the arc-shaped section 21.
In some alternative embodiments, the folding plate 1 and the cover plate 2 are made of a honeycomb composite material.
In some optional embodiments, the foldable fairing further comprises: the two side walls of the U-shaped angle section 4 of the folding plate clamp the wall surface of one side of the folding plate 1 close to the folding edge; the two side walls of the straight section U-shaped angle section 5 clamp the wall surface of the straight section 22 close to one side of the rotating edge; and one leaf of each folding hinge 6 is riveted on the top surface of the U-shaped angle bar 4 of the folding plate, and the other leaf of each folding hinge 6 is riveted on the top surface of the U-shaped angle bar 5 of the straight section.
In some optional embodiments, the foldable fairing further comprises: the folding plate embedded parts 7 are embedded in the folding plate 1, one end of each folding plate embedded part 7 is in threaded connection with one side wall of the folding plate U-shaped angle section 4, and the other end of each folding plate embedded part 7 is in threaded connection with the other side wall of the folding plate U-shaped angle section 4; and each straight section insert 8 is embedded into the straight section 22, one end of each straight section insert 8 is in threaded connection with one side wall of the straight section U-shaped angle bar 5, and the other end of each straight section insert 8 is in threaded connection with the other side wall of the straight section U-shaped angle bar 5.
In some alternative embodiments, there are two links 3.
In some optional embodiments, the foldable fairing further comprises: the two folding double-lug joints 9 are fixedly provided with the inner surfaces of the arc sections 21; two folding monaural joints 10, each folding monaural joint 10 is fixedly arranged at one folding end and is hinged with one folding binaural joint 9.
In some alternative embodiments, two arc segment embedding assemblies 11 are further included, and each arc segment embedding assembly 11 is embedded into an arc segment 21 and is connected with the folding double lug joint 9 through a bolt.
Another aspect provides a helicopter having a power pod with a power platform 12 intersecting a fuselage skin 13, and comprising any of the fairings described above, wherein,
the connecting ends of the two connecting rods 3 are hinged with the power platform 12;
the connecting edge of the folding plate 1 is hinged with the power platform 12;
the cowling has:
in the closed state, the arc section 21 is covered above the power platform 12;
in the open state, the folding plate 1 is displaced in the direction of the fuselage skin 13, and the curved section 21 is displaced above the power platform 12.
In some alternative embodiments, the folding plate 1 abuts the fuselage skin 13 when the fairing is in the open position, thereby providing support for the fairing, stabilizing its structure and reducing the risk of personnel stepping on it.
In some alternative embodiments, the straight section 22 is parallel to the power platform when the cowling is in the open position to facilitate work on the power platform.
In some optional embodiments, the power platform further comprises two connecting double-lug joints which are fixedly arranged on the power platform 12; the two connecting single-lug joints are fixedly arranged at the connecting end of one connecting rod 3 and hinged with one connecting double-lug joint; and one leaf plate of each connecting hinge is fixedly connected with the power platform, and the other leaf plate is fixedly connected with the wall surface of one side, close to the connecting edge, of the folding plate 1.
When the fairing is in an open state, a worker can take the straight section of the fairing as a stepping platform, and when equipment in the power cabin is maintained, the straight section is lower than the power platform 12, so that the bending frequency and strength can be reduced when the worker performs maintenance operation.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (10)
1. A foldable fairing, comprising:
a folding plate (1) having one side edge called connecting edge and the opposite side edge called folding edge;
a cover panel (2) having one side edge, called the turning edge, hinged to the folding edge; the cover plate (2) is divided into two sections, wherein one section is in an arc shape and is called an arc section (21), and the other section is in a straight shape and is called a straight section (22); the rotating edge is the edge of one side of the straight section far away from the arc-shaped section (21);
at least one connecting rod (3), one end of each connecting rod (3) is called a connecting end, the other end is called a folding end, and the folding end is hinged with the inner surface of the arc-shaped section (21).
2. Fairing according to claim 1, characterized in that the folding plate (1) and the cover plate (2) are manufactured from a honeycomb composite material.
3. The fairing as recited in claim 2, further comprising:
the two side walls of the U-shaped angle section (4) of the folding plate clamp the wall surface of one side, close to the folding edge, of the folding plate (1);
the two side walls of the straight section U-shaped angle bar (5) clamp the wall surface of one side of the straight section (22) close to the rotating edge;
and one leaf of each folding hinge (6) is riveted to the top surface of the U-shaped angle bar (4) of the folding plate, and the other leaf of each folding hinge (6) is riveted to the top surface of the U-shaped angle bar (5) of the straight section.
4. The fairing as recited in claim 3, further comprising:
the folding plate embedding pieces (7) are embedded into the folding plate (1), one end of each folding plate embedding piece (7) is in threaded connection with one side wall of the folding plate U-shaped angle bar (4), and the other end of each folding plate embedding piece is in threaded connection with the other side wall of the folding plate U-shaped angle bar (4);
the straight section embedded parts (8) are embedded into the straight sections (22), one end of each straight section embedded part (8) is in threaded connection with one side wall of the straight section U-shaped angle bar (5), and the other end of each straight section embedded part is in threaded connection with the other side wall of the straight section U-shaped angle bar (5).
5. The fairing according to claim 1, characterized in that said connecting rods (3) are two in number.
6. The fairing as recited in claim 5, further comprising:
the two folding double-lug joints (9) are fixedly arranged on the inner surface of the arc-shaped section (21);
two folding monaural joints (10), each folding monaural joint (10) is fixedly arranged at one folding end and is hinged with one folding binaural joint (9).
7. The fairing as recited in claim 6, further comprising two said arcuate segment insert assemblies (11), each said arcuate segment insert assembly (11) being inserted into said arcuate segment (21) and bolted to said folded binaural joint (9).
8. Helicopter having a power pod with a power platform (12) intersecting a fuselage skin (13), characterized in that it comprises a fairing according to any of claims 1-7, wherein,
the connecting ends of the two connecting rods (3) are hinged with the power platform (12);
the connecting edge of the folding plate (1) is hinged with the power platform (12);
the cowling has:
in a closed state, the arc-shaped section (21) covers the power platform (12);
in an open state, the folding plate (1) deviates towards the fuselage skin (13), and the arc-shaped section (21) deviates above the power platform (12).
9. A helicopter according to claim 8, characterized in that said folded sheet (1) abuts said fuselage skin (13) when said fairing is in said open condition.
10. A helicopter according to claim 9, characterized in that said fairing, when in said open position, has a straight section (22) parallel to said power platform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811340605.XA CN109533283B (en) | 2018-11-12 | 2018-11-12 | Collapsible radome fairing and have its helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811340605.XA CN109533283B (en) | 2018-11-12 | 2018-11-12 | Collapsible radome fairing and have its helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109533283A CN109533283A (en) | 2019-03-29 |
| CN109533283B true CN109533283B (en) | 2020-09-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811340605.XA Active CN109533283B (en) | 2018-11-12 | 2018-11-12 | Collapsible radome fairing and have its helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109533283B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112160804B (en) * | 2020-09-25 | 2023-03-24 | 中国直升机设计研究所 | Engine exhaust pipe fairing |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3008671A (en) * | 1956-12-31 | 1961-11-14 | United Aircraft Corp | Main rotor and pylon fairing |
| CN201362366Y (en) * | 2009-01-08 | 2009-12-16 | 江西昌河航空工业有限公司 | Cowling lock mechanism of helicopter nacelle |
| US20090321573A1 (en) * | 2005-09-28 | 2009-12-31 | Walliser Eric W | Rotor/wing dual mode hub fairing system |
| CN203111495U (en) * | 2012-11-16 | 2013-08-07 | 哈尔滨飞机工业集团有限责任公司 | Helicopter tail speed-reducer cowling |
| CN204433035U (en) * | 2015-01-04 | 2015-07-01 | 哈尔滨飞机工业集团有限责任公司 | Retarder fairing in a kind of helicopter |
| CN106428515A (en) * | 2016-09-23 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Foldable cabin door |
-
2018
- 2018-11-12 CN CN201811340605.XA patent/CN109533283B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3008671A (en) * | 1956-12-31 | 1961-11-14 | United Aircraft Corp | Main rotor and pylon fairing |
| US20090321573A1 (en) * | 2005-09-28 | 2009-12-31 | Walliser Eric W | Rotor/wing dual mode hub fairing system |
| CN201362366Y (en) * | 2009-01-08 | 2009-12-16 | 江西昌河航空工业有限公司 | Cowling lock mechanism of helicopter nacelle |
| CN203111495U (en) * | 2012-11-16 | 2013-08-07 | 哈尔滨飞机工业集团有限责任公司 | Helicopter tail speed-reducer cowling |
| CN204433035U (en) * | 2015-01-04 | 2015-07-01 | 哈尔滨飞机工业集团有限责任公司 | Retarder fairing in a kind of helicopter |
| CN106428515A (en) * | 2016-09-23 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Foldable cabin door |
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| Publication number | Publication date |
|---|---|
| CN109533283A (en) | 2019-03-29 |
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