CN104787302B - A kind of attachment structure between tilting radome fairing and cant beam - Google Patents
A kind of attachment structure between tilting radome fairing and cant beam Download PDFInfo
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- CN104787302B CN104787302B CN201510161290.2A CN201510161290A CN104787302B CN 104787302 B CN104787302 B CN 104787302B CN 201510161290 A CN201510161290 A CN 201510161290A CN 104787302 B CN104787302 B CN 104787302B
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- radome fairing
- rotating shaft
- tilting
- hinge
- attachment structure
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Abstract
The present invention proposes a kind of attachment structure simple in construction and convenient disassembly being used between tilting radome fairing and cant beam.Attachment structure between a kind of tilting radome fairing and cant beam, this attachment structure is specially：The side of tilting radome fairing and cant beam is flexibly connected by quick-detachable lock, and opposite side between the two is from top to bottom furnished with several coaxial connection units, and opening quick-detachable lock hypsokinesis inclined radome fairing can rotate along the common axis of this several connection unit；Above-mentioned each connection unit specifically includes hinge, rotating shaft and bearing, and wherein hinge is bolted with radome fairing, and bearing is bolted with fuselage, coordinates between rotating shaft and bearing for gap, and rotating shaft is integrally formed with hinge.Reliability of the present invention is high, convenient disassembly；Compared with general radome fairing hinge means, it is possible to achieve the function of Fast Installation dismounting, while safe and reliable.
Description
Technical field
The present invention relates to the attachment structure between a kind of tilting radome fairing and cant beam.
Background technology
Because helicopter engine, tail reducer etc. safeguard frequent, radome fairing need to be dismantled often at this, and helicopter rectification
Often profile is complex for cover, it is considered to the need for the frequent demolition and maintenance of radome fairing and the limitation such as connecting-piece structure size, weight,
Therefore it is a kind of can the radome fairing hinge means of Fast Installation be just particularly important.Several radome fairings that current main flow helicopter is selected
Hinge means mainly has the hinge connection mode of hinge plus poker or joint plus rotating shaft.The former hinge means depositing due to poker
, it is difficult to dismantle, while poker is buckled in the case of vibrations in the presence of abrasion and the possibility come off, it can be damaged if poker is got on blade
Hinder blade, bring potential safety hazard, consequence is hardly imaginable.And the latter's joint adds the hinge connection mode of rotating shaft complicated, connection
It is cumbersome, disassembling operations are brought with certain difficulty.
The content of the invention
The technical problem to be solved in the present invention：It is a kind of for tilting radome fairing and cant beam it is an object of the invention to propose
Between attachment structure simple in construction and convenient disassembly.
Technical scheme：Attachment structure between a kind of tilting radome fairing and cant beam, this attachment structure is specific
For：The side of tilting radome fairing and cant beam is flexibly connected by quick-detachable lock, if opposite side between the two is from top to bottom furnished with
Dry coaxial connection unit, opening quick-detachable lock hypsokinesis inclined radome fairing can revolve along the common axis of this several connection unit
Turn；Above-mentioned each connection unit specifically includes hinge, rotating shaft and bearing, and wherein hinge is bolted with inclined radome fairing,
Bearing is bolted with fuselage, is coordinated between rotating shaft and bearing for gap, and rotating shaft is integrally formed with hinge.
Further optimize, the connection unit includes 2~4.
In such scheme, further optimize, from top to bottom, the length of the rotating shaft of the connection unit is gradually incremented by.
Beneficial effects of the present invention：
A kind of attachment structure good appearance 1st, between tilting radome fairing and cant beam proposed by the present invention, reliability be high,
Convenient disassembly.
2nd, compared with general radome fairing hinge means, it is possible to achieve the function of Fast Installation dismounting, at the same it is safe and reliable, have
Effect avoids the potential safety hazard that poker structure is brought.
Brief description of the drawings
Fig. 1 is the schematic diagram in the attachment structure wherein left side between tilting radome fairing proposed by the present invention and cant beam.
Fig. 2 is the schematic diagram of connection member 3 in Fig. 1.
Fig. 3 is the schematic diagram on the right side of the attachment structure between tilting radome fairing proposed by the present invention and cant beam.
Wherein, 1 be cant beam radome fairing, 2 be cant beam, 3 be connection unit, 4 be quick-detachable lock, 3.1 be hinge, 3.2 be rotating shaft,
3.3 be bearing.
Embodiment
Embodiment 1：
The embodiment that the invention will now be described in detail with reference to the accompanying drawings.
As shown in Figure 1, Figure 2 and Figure 3, the attachment structure between a kind of tilting radome fairing and cant beam, this attachment structure tool
Body is：The right side of tilting radome fairing 1 and cant beam 2 is flexibly connected by quick-detachable lock 4, and it is coaxial that left side is from top to bottom furnished with several
And structure identical connection unit 3, opening the hypsokinesis inclined radome fairing 1 of quick-detachable lock 4 can be along the common axle of this several connection unit 3
Line rotates；Above-mentioned each connection unit 3 specifically includes hinge 3.1, rotating shaft 3.2 and bearing 3.3, wherein hinge 3.1 and tilting
Radome fairing 1 is bolted, and bearing 3.3 is bolted with fuselage, is coordinated between rotating shaft 3.2 and bearing 3.3 for gap,
Rotating shaft 3.2 is integrally formed with hinge 3.1.
Rotating shaft 3.2 is integrally formed with hinge 3.1, it is possible to prevente effectively from because rotating shaft 3.2 is de- in the unloading process of inclined radome fairing 1
Fall the potential safety hazard got to other systems and brought.The operation principle of the present invention is to be tilted by radome fairing installation direction (with Fig. 1
Be horizontal direction with arrow meaning course in Fig. 3, radome fairing installation direction and horizontal direction are in an angle) characteristic and structure it is special
Property, gravitational effect is made full use of, so as to which effectively rotating shaft 3.2 is fixed in the mounting hole of bearing 3.3.
In the present embodiment, the connection unit 3 preferably in attachment structure includes two, and two connection units 3 are coaxially set
Put.
The length of the rotating shaft 3.2 of connection unit 3 is from top to bottom gradually incremented by.The length of rotating shaft 3.2 is pressed from top to bottom gradually
It is incremented by optimization design, so as to realize that the rotating shaft 3.2 of two connection units 3 during installation loads correspondence bearing one by one from top to bottom
Function in 3.3 mounting hole, makes alignment install more efficient quick.
Embodiment 2：
The embodiment that the invention will now be described in detail with reference to the accompanying drawings.
As shown in Figure 1, Figure 2 and Figure 3, the attachment structure between a kind of tilting radome fairing and cant beam, this attachment structure tool
Body is：The right side of tilting radome fairing 1 and cant beam 2 is flexibly connected by quick-detachable lock 4, and it is coaxial that left side is from top to bottom furnished with several
And structure identical connection unit 3, opening the hypsokinesis inclined radome fairing 1 of quick-detachable lock 4 can be along the common axle of this several connection unit 3
Line rotates；Above-mentioned each connection unit 3 specifically includes hinge 3.1, rotating shaft 3.2 and bearing 3.3, wherein hinge 3.1 and tilting
Radome fairing 1 is bolted, and bearing 3.3 is bolted with fuselage, is coordinated between rotating shaft 3.2 and bearing 3.3 for gap,
Rotating shaft 3.2 is integrally formed with hinge 3.1.
Rotating shaft 3.2 is integrally formed with hinge 3.1, it is possible to prevente effectively from because rotating shaft 3.2 is de- in the unloading process of inclined radome fairing 1
Fall the potential safety hazard got to other systems and brought.The operation principle of the present invention be by radome fairing installation direction slope characteristic and
Architectural characteristic, makes full use of gravitational effect, so as to which effectively rotating shaft 3.2 is fixed in the mounting hole of bearing 3.3.
In the present embodiment, the connection unit 3 preferably in attachment structure includes three, and three connection units 3 are coaxially disposed.
The length of the rotating shaft 3.2 of connection unit 3 is from top to bottom gradually incremented by.The length of rotating shaft 3.2 is pressed from top to bottom gradually
It is incremented by optimization design, so as to realize that the rotating shaft 3.2 of connection unit 3 during installation loads correspondence bearing 3.3 one by one from top to bottom
Mounting hole in function, make alignment that more efficient quick to be installed.
Embodiment 3：
The embodiment that the invention will now be described in detail with reference to the accompanying drawings.
As shown in Figure 1, Figure 2 and Figure 3, the attachment structure between a kind of tilting radome fairing and cant beam, this attachment structure tool
Body is：The right side of tilting radome fairing 1 and cant beam 2 is flexibly connected by quick-detachable lock 4, and it is coaxial that left side is from top to bottom furnished with several
And structure identical connection unit 3, opening the hypsokinesis inclined radome fairing 1 of quick-detachable lock 4 can be along the common axle of this several connection unit 3
Line rotates；Above-mentioned each connection unit 3 specifically includes hinge 3.1, rotating shaft 3.2 and bearing 3.3, wherein hinge 3.1 and tilting
Radome fairing 1 is bolted, and bearing 3.3 is bolted with fuselage, is coordinated between rotating shaft 3.2 and bearing 3.3 for gap,
Rotating shaft 3.2 is integrally formed with hinge 3.1.
Rotating shaft 3.2 is integrally formed with hinge 3.1, it is possible to prevente effectively from because rotating shaft 3.2 is de- in the unloading process of inclined radome fairing 1
Fall the potential safety hazard got to other systems and brought.The operation principle of the present invention be by radome fairing installation direction slope characteristic and
Architectural characteristic, makes full use of gravitational effect, so as to which effectively rotating shaft 3.2 is fixed in the mounting hole of bearing 3.3.
In the present embodiment, the connection unit 3 preferably in attachment structure includes four, and four connection units 3 are coaxially disposed.
The length of the rotating shaft 3.2 of connection unit 3 is from top to bottom gradually incremented by.The length of rotating shaft 3.2 is pressed from top to bottom gradually
It is incremented by optimization design, so as to realize that the rotating shaft 3.2 of connection unit 3 during installation loads correspondence bearing 3.3 one by one from top to bottom
Function in mounting hole, makes alignment install more efficient quick.
Claims (2)
1. the attachment structure between a kind of tilting radome fairing and cant beam, this attachment structure is specially：Tilting radome fairing (1) and
The side of body cant beam (2) is flexibly connected by quick-detachable lock (4), and opposite side is from top to bottom furnished with several coaxial connection units
(3), the tilting radome fairing (1) can be along the common axle of this several connection unit (3) after the opening quick-detachable lock (4)
Line rotates；Each connection unit (3) specifically includes hinge (3.1), rotating shaft (3.2) and bearing (3.3), wherein the hinge
(3.1) it is bolted with tilting radome fairing (1), the bearing (3.3) is bolted with fuselage, the rotating shaft
(3.2) coordinate between bearing (3.3) for gap, it is characterised in that：The rotating shaft (3.2) is integrally formed with hinge (3.1)；
From top to bottom, the length of the rotating shaft (3.2) of the connection unit (3) is gradually incremented by.
2. attachment structure according to claim 1, it is characterised in that：The connection unit (3) includes 2~4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510161290.2A CN104787302B (en) | 2015-04-07 | 2015-04-07 | A kind of attachment structure between tilting radome fairing and cant beam |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510161290.2A CN104787302B (en) | 2015-04-07 | 2015-04-07 | A kind of attachment structure between tilting radome fairing and cant beam |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104787302A CN104787302A (en) | 2015-07-22 |
| CN104787302B true CN104787302B (en) | 2017-11-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510161290.2A Active CN104787302B (en) | 2015-04-07 | 2015-04-07 | A kind of attachment structure between tilting radome fairing and cant beam |
Country Status (1)
| Country | Link |
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| CN (1) | CN104787302B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3031082B1 (en) * | 2014-12-30 | 2017-02-10 | Airbus Operations Sas | JUNCTION ASSEMBLY CONNECTING A FUSELAGE AIRCRAFT AIRCRAFT FITTING WITH SINGER IN PARTICULAR POSITION |
| CN108910080B (en) * | 2018-06-26 | 2021-11-02 | 中国直升机设计研究所 | Helicopter tail rotor pneumatic load environment simulation test device |
| CN114212273B (en) * | 2021-12-10 | 2023-05-26 | 江西昌河航空工业有限公司 | Installation positioning device for repairing sectional long hinge of helicopter |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10348981B4 (en) * | 2003-10-22 | 2009-04-09 | Eurocopter Deutschland Gmbh | Rotor, in particular for a rotary aircraft |
| DE202010014056U1 (en) * | 2010-10-07 | 2010-12-09 | Kiesewetter, Uwe | Rear fairing for the aerodynamic optimization of radio-controlled model helicopters |
| CN102501977A (en) * | 2011-11-01 | 2012-06-20 | 哈尔滨飞机工业集团有限责任公司 | Engine fairing |
| CN203201337U (en) * | 2013-04-12 | 2013-09-18 | 浙江龙纪汽车零部件有限公司 | Automobile door hinge convenient to dismantle |
| CN104384920B (en) * | 2014-08-26 | 2018-10-02 | 中国直升机设计研究所 | A kind of light helicopter structural member assembly devices and methods therefor |
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- 2015-04-07 CN CN201510161290.2A patent/CN104787302B/en active Active
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| CN104787302A (en) | 2015-07-22 |
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