CN104210642B - A kind of depopulated helicopter airframe structure of housing load - Google Patents
A kind of depopulated helicopter airframe structure of housing load Download PDFInfo
- Publication number
- CN104210642B CN104210642B CN201410471819.6A CN201410471819A CN104210642B CN 104210642 B CN104210642 B CN 104210642B CN 201410471819 A CN201410471819 A CN 201410471819A CN 104210642 B CN104210642 B CN 104210642B
- Authority
- CN
- China
- Prior art keywords
- fuselage
- flap
- load
- reinforcing frame
- depopulated helicopter
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 20
- 210000000744 eyelid Anatomy 0.000 claims abstract description 14
- 230000005540 biological transmission Effects 0.000 claims description 4
- 239000003795 chemical substances by application Substances 0.000 description 9
- 238000013461 design Methods 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000013507 mapping Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004899 motility Effects 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Landscapes
- Body Structure For Vehicles (AREA)
- Superstructure Of Vehicle (AREA)
Abstract
The depopulated helicopter airframe structure of a kind of housing load, this fuselage is divided into fuselage agent structure (2), upper flap A (1) and upper flap B (3), tail boom (5), the lower flap A (6) and the lower flap B (8), undercarriage (7), horizontal plate (9), reinforcing frame A (10), reinforcing frame B (11) and vertical tail (4)；Undercarriage (7) and fuselage agent structure (2) are connected, and vertical tail (4) is connected with tail boom (5) and fuselage agent structure (2)；Upper and lower lid all uses detachable connection with fuselage agent structure (2)；Wherein upper flap A (1) is engine bin, and upper flap B (3) is electronics bay, and the lower flap A (6) and the lower flap B (8) are load storehouse.It is big that the main body mechanism of traditional depopulated helicopter also exists architecture quality, and the easy unstability of eyelid covering, the problems such as eyelid covering junction is poorly sealed, present patent application well solves the problems referred to above.
Description
Technical field
The present invention relates to the depopulated helicopter airframe structure of a kind of housing load, it relates to the part design of small-sized depopulated helicopter,
Belong to aviation aircraft design field.
Background technology
Depopulated helicopter is generally used for aviation target, battlefield investigation, injures the military mission such as assessment, target guide, the most also
Can be used for the non-military task such as flight test, aerial mapping.For relatively fixed wing airplane, depopulated helicopter has hovering, vertical
Play degradation function, it is possible to perform task more flexibly.Owing to depopulated helicopter parts are many, the therefore position of its all parts
Needs consider full machine center of gravity, use requirement, installation interference etc. problem.And owing to depopulated helicopter load is limited, because of
This its full machine overall construction design is most important for a frame depopulated helicopter.
The airframe structure of depopulated helicopter is mainly responsible for the transmission of load, and main load has the lift and torsion brought by rotor
Square, has the aerodynamic force that aerodynamic loading brings, and has and loads the mass force bringing load.The main body mechanism of depopulated helicopter has structure at present
Eyelid covering is arranged in posture, truss-like, trusses formula and hybrid etc., then the framework constituted at them.Main load is again
The box section that beam, wall, bar, plate are constituted is transmitted, and aerodynamic force is transmitted by eyelid covering.
The many employings of the structure " basket-hanging " of traditional depopulated helicopter, and it is disposed about hound at rotor, cloth in fuselage
Putting crossbeam, then be disposed about reinforcing frame at rotor, such structure can transmit the Main Load on fuselage, but major defect
The architecture quality being it is the heaviest, and eyelid covering is due to thin easy unstability.And the connection of thin skin be also easy to cracking or
Poorly sealed problem, so cause a problem in that rain or the weather of sand and dust under flight easily lead to security incident.With
Time load load and equipment due to needs, need to install additional bearing beam, and suspension member in structure originally, and the shape of load
Also can be restricted, so cause architecture quality to increase further.Present patent application, i.e. for this problem, have developed a kind of shell
The depopulated helicopter airframe structure of body load, achieves good effect.
Summary of the invention
Solve the technical problem that
It is big that the main body mechanism of traditional depopulated helicopter also exists architecture quality, and the easy unstability of eyelid covering, eyelid covering junction is poorly sealed
Etc. problem, the application of depopulated helicopter is so caused to be limited by environment, the nothing of a kind of housing load that present patent application provides
People's helicopter fuselage structure can solve the problems referred to above.
1. the technical scheme used
The present invention is mainly by realizing the appropriate design of depopulated helicopter structure.
The technical scheme that the following description present invention is embodied as.
Fuselage uses housing to be main load-carrying construction, this eliminates the structures such as the beam in conventional airframe, bar, by
Thicker eyelid covering bears whole aerodynamic force, and the box section of the most a small amount of reinforcing frame and thick eyelid covering composition passes
Power.Its structure is as shown in Figure 1.Full fuselage is divided into fuselage agent structure (2), upper flap A (1) and upper flap
B (3), tail boom (5), the lower flap A (6) and the lower flap B (8), undercarriage (7), horizontal plate (9),
Reinforcing frame A (10), reinforcing frame B (11) and vertical tail (4).Position annexation therebetween is: undercarriage
(7) it is connected with fuselage agent structure (2), vertical tail (4) and tail boom (5) and fuselage agent structure (2)
It is connected.Upper and lower lid all uses detachable connection with fuselage agent structure (2).Wherein upper flap A (1) is
Engine bin, upper flap B (3) is electronics bay, and the lower flap A (6) and the lower flap B (8) are load storehouse.
The particular location of each lid is as shown in Figure 2.
In fuselage, arrange that a small amount of reinforcing frame so can increase the intensity of structure.Fuselage interior structure such as Fig. 3 institute
Show.It is disposed about, at rotor, the concentrfated load that reinforcing frame A (10) so can disperse to be brought by rotor, makes power uniform
It is distributed on eyelid covering.Reinforcing frame B (11) can make afterbody power transmission forward be able to continuously.Due to fore-body
Opening is more, therefore laterally adds in mmi machine body and puts with horizontal plate (9), so can transmit load, but also can
With at the upper place apparatus of horizontal plate (9).
3. beneficial effect
It is an advantage of the current invention that:
1) case type structure is used can effectively to reduce architecture quality.
2) case type structure is used can to reduce tradition depopulated helicopter thin skin seam not tight, the problem of poor sealing so that should
Helicopter flew in the rainy day.
3) the lid position of reasonable Arrangement solves conventional helicopters and loads difficult problem, decreases owing to some required for loading are hung
Part, the lower flap provides two load storehouses can increase the motility of loading, and the shape need of load can also reduce.
Accompanying drawing explanation
Fig. 1 fuselage overall structure axonometric drawing.
Fig. 2 each lid position front view.
Fig. 3 fuselage interior axis of no-feathering mapping.
In figure, symbol description is as follows:
1, upper flap A；2, fuselage agent structure；3, upper flap B；4, vertical tail；5, tail boom；6, the lower flap
A；7, undercarriage；8, the lower flap B；9, horizontal plate；10, reinforcing frame A；11, reinforcing frame B.
Detailed description of the invention
See Fig. 1 Fig. 3, below by example, embodiments of the present invention illustrated:
During the use of depopulated helicopter, installing each lid after needing to be fixed loading can fly.Arrange
Each lid can carry out rectification to air-flow, hence it is evident that reduces the aerodynamic drag of helicopter, increases the aesthetic property of aircraft simultaneously.Using
Maintenance aspect, owing to the main load-carrying construction of case type structure is eyelid covering, therefore case type fuselage is readily inspected what structure had
Defect.In adverse circumstances, owing to the sealing of eyelid covering is protected, can improve accordingly the service life of part.
Full fuselage is divided into fuselage agent structure (2), upper flap A (1) and upper flap B (3), tail boom (5), the lower flap A
(6) and the lower flap B (8), undercarriage (7), horizontal plate (9), reinforcing frame A (10), reinforcing frame B (11) and hang down
Fin (4).Position annexation therebetween is: undercarriage (7) and fuselage agent structure (2) are connected, vertical tail (4)
It is connected with tail boom (5) and fuselage agent structure (2).Upper and lower lid and fuselage agent structure (2) all use detachable company
Connect.Wherein upper flap A (1) is engine bin, and upper flap B (3) is electronics bay, the lower flap A (6) and the lower flap B
(8) it is load storehouse.The particular location of each lid is as shown in Figure 2.
In fuselage, arrange that a small amount of reinforcing frame so can increase the intensity of structure.Fuselage interior structure is as shown in Figure 3.In rotation
The wing is disposed about the concentrfated load that reinforcing frame A (10) so can disperse to be brought by rotor, makes power be evenly distributed on eyelid covering.
Reinforcing frame B (11) can make afterbody power transmission forward be able to continuously.Owing to fore-body opening is more, therefore mmi machine
Body laterally adds and puts with horizontal plate (9), so can transmit load, but also can be at the upper place apparatus of horizontal plate (9).
Claims (1)
1. the depopulated helicopter airframe structure of a housing load, it is characterised in that: this fuselage be divided into fuselage agent structure (2), on
Lid A (1) and upper flap B (3), tail boom (5), the lower flap A (6) and the lower flap B (8), undercarriage (7),
Horizontal plate (9), reinforcing frame A (10), reinforcing frame B (11) and vertical tail (4)；Undercarriage (7) and fuselage body junction
Structure (2) is connected, and vertical tail (4) is connected with tail boom (5) and fuselage agent structure (2)；Upper and lower lid and fuselage master
Body structure (2) all uses detachable connection；Wherein upper flap A (1) is engine bin, and upper flap B (3) is that electronics sets
Standby cabin, the lower flap A (6) and the lower flap B (8) are load storehouse；In fuselage, arrange that reinforcing frame can increase the intensity of structure,
Rotor is disposed about the concentrfated load that reinforcing frame A (10) can disperse to be brought by rotor, makes power be evenly distributed on eyelid covering；Strengthen
Frame B (11) can make afterbody power transmission forward be able to continuously, owing to fore-body opening is more, therefore horizontal in mmi machine body
Put with horizontal plate (9) to adding, so can transmit load, again can be at the upper place apparatus of horizontal plate (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410471819.6A CN104210642B (en) | 2014-09-16 | 2014-09-16 | A kind of depopulated helicopter airframe structure of housing load |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410471819.6A CN104210642B (en) | 2014-09-16 | 2014-09-16 | A kind of depopulated helicopter airframe structure of housing load |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104210642A CN104210642A (en) | 2014-12-17 |
| CN104210642B true CN104210642B (en) | 2016-09-07 |
Family
ID=52092649
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410471819.6A Active CN104210642B (en) | 2014-09-16 | 2014-09-16 | A kind of depopulated helicopter airframe structure of housing load |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104210642B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554700B (en) * | 2015-01-28 | 2017-11-17 | 张伟 | Upper beam, helicopter body and helicopter using the upper beam |
| CN114030592B (en) * | 2021-11-19 | 2023-10-20 | 中国直升机设计研究所 | Construction method of retractable main landing gear bearing structure of helicopter |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1083788A (en) * | 1992-07-22 | 1994-03-16 | 欧洲直升机法国公司 | The airframe structure of helicopter |
| US6126113A (en) * | 1998-09-21 | 2000-10-03 | Navickas; Thomas Joseph | Helicopter removable drive train platform |
| EP1714867A1 (en) * | 2005-04-22 | 2006-10-25 | Eurocopter | Supporting structure and rotorcraft |
| CN201240500Y (en) * | 2008-07-25 | 2009-05-20 | 朱家乐 | Small-sized unmanned helicopter body structure system |
| CN102774492A (en) * | 2012-06-08 | 2012-11-14 | 无锡汉和航空技术有限公司 | Small unmanned helicopter fuselage |
| CN204056285U (en) * | 2014-09-16 | 2014-12-31 | 北京兰亭华谊文化传媒有限责任公司 | A kind of depopulated helicopter airframe structure of housing load |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ITTO20010327A1 (en) * | 2001-04-04 | 2002-10-04 | Augusta S P A | RESCUE VEHICLE. |
| US6729576B2 (en) * | 2002-08-13 | 2004-05-04 | Sikorsky Aircraft Corporation | Composite tail cone assembly |
| US7275717B2 (en) * | 2005-05-18 | 2007-10-02 | Bell Helicopter Textron Inc. | Helicopter one-piece door |
| US8490920B2 (en) * | 2007-10-12 | 2013-07-23 | Abe Karem | Composite bulkhead and skin construction |
-
2014
- 2014-09-16 CN CN201410471819.6A patent/CN104210642B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1083788A (en) * | 1992-07-22 | 1994-03-16 | 欧洲直升机法国公司 | The airframe structure of helicopter |
| US6126113A (en) * | 1998-09-21 | 2000-10-03 | Navickas; Thomas Joseph | Helicopter removable drive train platform |
| EP1714867A1 (en) * | 2005-04-22 | 2006-10-25 | Eurocopter | Supporting structure and rotorcraft |
| CN201240500Y (en) * | 2008-07-25 | 2009-05-20 | 朱家乐 | Small-sized unmanned helicopter body structure system |
| CN102774492A (en) * | 2012-06-08 | 2012-11-14 | 无锡汉和航空技术有限公司 | Small unmanned helicopter fuselage |
| CN204056285U (en) * | 2014-09-16 | 2014-12-31 | 北京兰亭华谊文化传媒有限责任公司 | A kind of depopulated helicopter airframe structure of housing load |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104210642A (en) | 2014-12-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9321526B2 (en) | Compound helicopter | |
| US10005554B2 (en) | Unmanned aerial vehicle | |
| US9656736B2 (en) | Method for assembling an aircraft aft portion | |
| CN107972843B (en) | A kind of lightweight, high maintainable unmanned plane composite structure system | |
| CN104210642B (en) | A kind of depopulated helicopter airframe structure of housing load | |
| CN102139757A (en) | Framed front center fuselage suitable for unmanned plane and model plane | |
| CN204056285U (en) | A kind of depopulated helicopter airframe structure of housing load | |
| CN102963521A (en) | Central wing of horizontal tail of civil airplane | |
| CN105691626A (en) | Aircraft fuselage bottom pod | |
| CN204433031U (en) | Portable fast assembling-disassembling unmanned plane | |
| CN206417207U (en) | A kind of new unmanned plane cargo hold | |
| CN115214904A (en) | eVTOL aircraft flight test bench | |
| CN210618450U (en) | Airplane baseline device | |
| CN203727641U (en) | Reconnaissance drone | |
| CN105836102B (en) | A kind of high performance mini plateau scounting aeroplane | |
| CN113148188A (en) | Dual-power vertical take-off and landing fixed-wing unmanned aerial vehicle | |
| CN103523240B (en) | Airborne geophysical prospecting equipment props up extension structure for pod | |
| CN206218240U (en) | A kind of battery cabin structure of multi-rotor unmanned aerial vehicle | |
| CN103640705B (en) | One plug-in device anchor fitting on Small General Aircraft | |
| CN109484611A (en) | A kind of fuselage bearing structure of the dynamic unmanned plane of oil | |
| CN204979212U (en) | Remote sensing fixed wing uavs | |
| CN203698646U (en) | Flying wing imitating rapidly ascending unmanned plane | |
| CN108860592A (en) | Single vortex-spraying type composite wing manned vehicle afterwards | |
| CN203638095U (en) | Unmanned mapping machine | |
| CN115056962B (en) | Upper single-wing aircraft wing body connecting structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| ASS | Succession or assignment of patent right |
Owner name: TIANXUN INNOVATION (BEIJING) TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: BEIJING LANTING HUAYI MEDIA CO., LTD. Effective date: 20150526 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20150526 Address after: 100191 Haidian District, Xueyuan Road, No., the world building, Ning, the world's 35 Applicant after: TIANXUN INNOVATION (BEIJING) TECHNOLOGY CO.,LTD. Address before: 100088, Room 501, Bai Yan building, 238 middle Fourth Ring Road, Haidian District, Beijing Applicant before: BEIJING LANTING HUAYI MEDIA Co.,Ltd. |
|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20161223 Address after: 213000 Changzhou Changzhou science and technology center in the city of Jiangsu Wu Zhong Road, No. 18, A1 Patentee after: VOLITATION (CHANGZHOU) INTELLIGENT TECHNOLOGY CO.,LTD. Address before: 100191 Haidian District, Xueyuan Road, No., the world building, Ning, the world's 35 Patentee before: TIANXUN INNOVATION (BEIJING) TECHNOLOGY CO.,LTD. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20221230 Address after: Room 2211, 22nd Floor, Block D, Zhizhen Building, No. 7 Zhichun Road, Haidian District, Beijing 100088 Patentee after: TIANXUN INNOVATION (BEIJING) TECHNOLOGY CO.,LTD. Address before: Building A1, Zhongke entrepreneurship center, Changzhou science and Education City, No.18, middle Changwu Road, Changzhou, Jiangsu Province, 213000 Patentee before: VOLITATION (CHANGZHOU) INTELLIGENT TECHNOLOGY CO.,LTD. |