CN110901919B - Helicopter hangs acoustic cover - Google Patents
Helicopter hangs acoustic cover Download PDFInfo
- Publication number
- CN110901919B CN110901919B CN201911227975.7A CN201911227975A CN110901919B CN 110901919 B CN110901919 B CN 110901919B CN 201911227975 A CN201911227975 A CN 201911227975A CN 110901919 B CN110901919 B CN 110901919B
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- China
- Prior art keywords
- cover
- acoustic
- hanging
- helicopter
- lower section
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
- B64D1/10—Stowage arrangements for the devices in aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention belongs to the field of structural design of helicopters, and discloses a helicopter hanging sound cover.A hanging sound cover 1 comprises an upper section hanging sound cover 2 and a lower section hanging sound cover 3, wherein one end of the upper section hanging sound cover 2 is clamped and connected with one end of the lower section hanging sound cover 3; the upper section acoustic hanging cover 2 and the lower section acoustic hanging cover 3 are both of carbon fiber composite material honeycomb sandwich structures; the upper section hanging acoustic hood 2 and the lower section hanging acoustic hood 3 are both cylindrical, and the inner walls of the upper section hanging acoustic hood 2 and the lower section hanging acoustic hood 3 are coated with polyurethane high-stripping adhesive. The multifunctional helicopter sound-hanging cover is wear-resistant, and defects such as pits and cracks are not easy to occur after collision.
Description
Technical Field
The invention belongs to the field of structural design of helicopters, and relates to a multifunctional helicopter hanging sound cover.
Background
The suspension cover is used for providing a channel for the helicopter to suspend sonar equipment, and is usually arranged at the middle position of the floor of a passenger cabin. The design and the connection mode of the suspended acoustic cover not only influence the installation of the suspended acoustic cover, but also influence the use of suspended sonar equipment and the like. The common suspension sound cover structure of the helicopter generally adopts a cylindrical horn mouth type structure form.
The suspended sound cover structure is a working channel for suspending sonar equipment, and is very easy to wear and collide; however, the existing acoustic hood structure on the helicopter is generally non-wear-resistant, and is easy to have defects such as pits, cracks and the like after collision; the acoustic enclosure is damaged and cannot be normally used, and inconvenience is brought to maintenance and use of the suspended sonar equipment.
Disclosure of Invention
The purpose of the invention is as follows: the multifunctional helicopter sound-hanging cover is wear-resistant and is not easy to have defects of pits, cracks and the like after collision.
The technical scheme of the invention is as follows: a helicopter hangs acoustic hood, hang acoustic hood 1 including upper segment hang acoustic hood 2 and lower segment hang acoustic hood 3 while being said, hang one end of acoustic hood 2 and hang one end of acoustic hood 3 and block and connect while being said;
the upper section suspended sound cover 2 and the lower section suspended sound cover 3 are both of carbon fiber composite material honeycomb sandwich structures;
the upper section hanging acoustic hood 2 and the lower section hanging acoustic hood 3 are both cylindrical, and the inner walls of the upper section hanging acoustic hood 2 and the lower section hanging acoustic hood 3 are coated with polyurethane high-stripping adhesive.
Further, the carbon fiber composite material honeycomb sandwich structure comprises a honeycomb core and a carbon fiber layer, wherein the carbon fiber layer is arranged on two sides of the honeycomb core, and the honeycomb core and the carbon fiber layer are formed through hot press molding.
Further, the honeycomb core is a paper honeycomb core.
Further, the acoustic hanging cover 1 further comprises a rubber ring 6, and the rubber ring 6 is sleeved on the outer surface of the port of the upper acoustic hanging cover 2 and is located between the connection part of the upper acoustic hanging cover 2 and the lower acoustic hanging cover 3.
Furthermore, a bent edge 20 is arranged at the port of the upper section acoustic hanging cover 2 far away from the lower section acoustic hanging cover 3, the bent edge 20 protrudes towards the outer side of the lower section acoustic hanging cover 3,
when the upper acoustic hood 2 is installed, the upper acoustic hood 2 penetrates through the cabin floor 4, and the flange 20 is located above the cabin floor 4 of the helicopter.
Further, the beads 20 are fixedly connected to the cabin floor 4 by means of fastening screws 8.
Furthermore, a flaring 30 is arranged at the port of the lower section acoustic hanging cover 3 far away from the upper section acoustic hanging cover 2, the flaring 30 is convenient for the retraction of the hanging device,
and installing a lower section suspended sound cover 3, wherein the lower section suspended sound cover 3 penetrates through the airplane skin 5, and the flaring 30 is positioned below the airplane skin 5 of the helicopter.
Further, ribs 31 are provided on the outer surface of the flared opening 30 for improving the rigidity of the flared opening 30.
Further, the lower stage sling cover 3 is fixedly connected to the aircraft skin 5 at the connection part with the flaring 30 through a fastening screw 7.
The invention has the beneficial effects that: because the sound hanging cover adopts a carbon fiber composite material honeycomb sandwich structure and polyurethane high-peel adhesive is sprayed on the inner wall of the sound hanging cover, the whole sound hanging cover is connected with the cabin floor and the lower skin through screws and bolts; the structure weight is effectively reduced, and the corrosion resistance, wear resistance and anti-collision capacity of the acoustic hood are greatly improved; the sound hanging cover has the functions of being fast and convenient to install and detach; the use experience of customers and the maintenance requirement of an outfield are well met.
Drawings
FIG. 1 is a schematic view of the installation position of a suspended sound cover;
FIG. 2 is a schematic view of the combined structure of the acoustic enclosure;
FIG. 3 is a schematic sectional view of the acoustic enclosure;
fig. 4 is a schematic connection diagram of the acoustic enclosure.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious 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 given herein without making any creative effort, shall fall within the protection scope of the present invention.
Fig. 1 is a schematic view of the installation position of the acoustic enclosure, and the acoustic enclosure of the present embodiment is installed between a cabin floor 4 and a bottom aircraft skin 5.
Fig. 2 is a schematic view of a combined structure of a suspended acoustic enclosure, fig. 3 is a schematic view of a segmented structure of the suspended acoustic enclosure, fig. 4 is a schematic view of a connection of the suspended acoustic enclosure, and as shown in fig. 2, fig. 3 and fig. 4,
the helicopter sound suspension cover provided by the embodiment comprises an upper section sound suspension cover 2 and a lower section sound suspension cover 3, wherein one end of the upper section sound suspension cover 2 is clamped and connected with one end of the lower section sound suspension cover 3;
the upper section suspended sound cover 2 and the lower section suspended sound cover 3 are both of carbon fiber composite material honeycomb sandwich structures; the upper section hanging acoustic hood 2 and the lower section hanging acoustic hood 3 are both cylindrical, and the inner walls of the upper section hanging acoustic hood 2 and the lower section hanging acoustic hood 3 are coated with polyurethane high-stripping adhesive.
The suspended sound cover 3 of the embodiment adopts a carbon fiber composite material honeycomb sandwich structure, the inner wall of the suspended sound cover is sprayed with polyurethane high-peel adhesive, and the whole suspended sound cover is connected with a cabin floor and a lower skin through screws and bolts; not only effectively reduce the structural weight, improved the corrosion-resistant, wear-resisting and anti-collision ability of hanging the acoustic hood greatly.
Further, the carbon-fibre composite material honeycomb sandwich structure of this embodiment includes honeycomb core and carbon fiber and spreads the layer, the both sides of honeycomb core are the carbon fiber and spread the layer, honeycomb core and carbon fiber are spread the layer and are passed through hot briquetting. Specifically, the honeycomb core is a paper honeycomb core.
As shown in fig. 3, the acoustic hanging cover 1 further includes a rubber ring 6, and the rubber ring 6 is sleeved on the outer surface of the port of the upper acoustic hanging cover 2 and is located between the connection portions of the upper acoustic hanging cover 2 and the lower acoustic hanging cover 3. Specifically, the rubber ring 6 is located on the outer surface of the port of the upper acoustic hanging shield 2 and located on the inner surface of the port of the lower acoustic hanging shield 3. The upper section acoustic hanging cover 2 and the lower section acoustic hanging cover 3 are tightly connected through the rubber ring 6.
Furthermore, a bent edge 20 is arranged at the port of the upper section acoustic hanging cover 2 far away from the lower section acoustic hanging cover 3, the bent edge 20 protrudes towards the outer side of the lower section acoustic hanging cover 3,
when the upper acoustic enclosure 2 is installed, the upper acoustic enclosure 2 passes through the cabin floor 4, and the flange 20 is located above the cabin floor 4 of the helicopter. The beads 20 are fixedly connected to the cabin floor 4 by means of fastening screws 8.
Furthermore, a flaring opening 30 is arranged at a port of the lower section suspended acoustic cover 3, which is far away from the upper section suspended acoustic cover 2, the flaring opening 30 is convenient for the retraction of the suspension device, the lower section suspended acoustic cover 3 is installed, the lower section suspended acoustic cover 3 penetrates through the airplane skin 5, and the flaring opening 30 is positioned below the airplane skin 5 of the helicopter.
Further, ribs 31 are provided on the outer surface of the flared opening 30 for improving the rigidity of the flared opening 30.
Further, the lower stage acoustic hood 3 is fixedly connected to the aircraft skin 5 at the connection part with the flaring 30 through fastening screws 7.
The foregoing is illustrative of the present invention and is not to be construed as limiting thereof. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. A helicopter hangs acoustic hood, characterized by, hang acoustic hood (1) including upper segment hang acoustic hood (2) and lower section hang acoustic hood (3), hang one end of acoustic hood (2) and hang one end card and connection of acoustic hood (3) with the lower section;
the upper section hanging sound cover (2) and the lower section hanging sound cover (3) are both of carbon fiber composite material honeycomb sandwich structures;
the upper section hanging acoustic hood (2) and the lower section hanging acoustic hood (3) are both cylindrical, and the inner walls of the upper section hanging acoustic hood (2) and the lower section hanging acoustic hood (3) are coated with polyurethane high-peel adhesive; a port of the upper section acoustic hanging cover (2) far away from the lower section acoustic hanging cover (3) is provided with a bent edge (20), and the bent edge (20) protrudes towards the outer side of the lower section acoustic hanging cover (3); and a port of the lower section acoustic hanging cover (3) far away from the upper section acoustic hanging cover (2) is provided with a flaring opening (30), and the flaring opening (30) is convenient for the retraction of the lifting device.
2. The helicopter hoisting acoustic cover of claim 1 wherein the carbon fiber composite honeycomb sandwich structure comprises a honeycomb core and a carbon fiber lay-up, wherein the carbon fiber lay-up is on both sides of the honeycomb core, and the honeycomb core and the carbon fiber lay-up are formed by hot pressing.
3. A helicopter sling cover as defined in claim 2 wherein said honeycomb core is a paper honeycomb core.
4. The helicopter sling cover according to claim 1, wherein the sling cover (1) further comprises a rubber ring (6), and the rubber ring (6) is sleeved on the outer surface of the port of the upper sling cover (2) and is positioned between the connection part of the upper sling cover (2) and the lower sling cover (3).
5. A helicopter sling cover according to claim 1 wherein,
when the upper section acoustic hood (2) is installed, the upper section acoustic hood (2) penetrates through the cabin floor (4), and the bent edge (20) is located above the cabin floor (4) of the helicopter.
6. Helicopter noising cover according to claim 5, characterized in that the beading (20) is fixedly connected to the cabin floor (4) by means of fastening screws (8).
7. A helicopter sling cover according to claim 1 wherein,
when the lower section suspended sound cover (3) is installed, the lower section suspended sound cover (3) penetrates through the airplane skin (5), and the flaring opening (30) is located below the airplane skin (5) of the helicopter.
8. A helicopter rumble cover according to claim 7, characterized in that the outer surface of said flared end (30) is provided with ribs (31) for increasing the rigidity of the flared end (30).
9. The acoustic helicopter hoisting cover according to claim 7, characterized in that the connection point of the lower stage acoustic hoisting cover (3) and the flaring (30) is fixedly connected to the aircraft skin (5) by means of fastening screws (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911227975.7A CN110901919B (en) | 2019-12-04 | 2019-12-04 | Helicopter hangs acoustic cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911227975.7A CN110901919B (en) | 2019-12-04 | 2019-12-04 | Helicopter hangs acoustic cover |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110901919A CN110901919A (en) | 2020-03-24 |
| CN110901919B true CN110901919B (en) | 2023-04-18 |
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ID=69822148
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911227975.7A Active CN110901919B (en) | 2019-12-04 | 2019-12-04 | Helicopter hangs acoustic cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110901919B (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2894561B1 (en) * | 2005-12-14 | 2008-02-15 | Eurocopter France | AEROTRANSPORTABLE RESERVOIR FOR STORING A PRODUCT TO LARGUER IN FLIGHT |
| WO2016190911A2 (en) * | 2015-03-26 | 2016-12-01 | Sikorsky Aircraft Corporation | Selective passive release system |
| FR3046777B1 (en) * | 2016-01-14 | 2018-02-16 | Dassault Aviation | CLOSURE HATCH OF AN OPENING MADE THROUGH THE STRUCTURE OF AN AIRCRAFT, STRUCTURE, AND METHOD THEREOF |
| CN207565844U (en) * | 2017-12-03 | 2018-07-03 | 中国直升机设计研究所 | A kind of observable gondola |
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2019
- 2019-12-04 CN CN201911227975.7A patent/CN110901919B/en active Active
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| Publication number | Publication date |
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| CN110901919A (en) | 2020-03-24 |
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