CN104210642A - Fuselage structure of unmanned helicopter with bearing shell - Google Patents
Fuselage structure of unmanned helicopter with bearing shell Download PDFInfo
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- CN104210642A CN104210642A CN201410471819.6A CN201410471819A CN104210642A CN 104210642 A CN104210642 A CN 104210642A CN 201410471819 A CN201410471819 A CN 201410471819A CN 104210642 A CN104210642 A CN 104210642A
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- fuselage
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- 230000003014 reinforcing effect Effects 0.000 claims abstract description 21
- 230000005540 biological transmission Effects 0.000 claims description 5
- 239000003795 chemical substances by application Substances 0.000 description 9
- 238000013461 design Methods 0.000 description 4
- 238000010276 construction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- 230000009286 beneficial effect Effects 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
- 230000007613 environmental effect Effects 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
- 238000013507 mapping Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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Abstract
The invention discloses a fuselage structure of an unmanned helicopter with a bearing shell. A fuselage is divided into a fuselage main body structure (2), an upper opening cover A (1), an upper opening cover B (3), a tail beam (5), a lower opening cover A (6), a lower opening cover B (8), a landing gear (7), a horizontal plate (9), a reinforcing framework A (10), a reinforcing framework B (11) and a vertical tail wing (4), wherein the landing gear (7) is fixedly connected with the fuselage main body structure (2); the vertical tail wing (4) is fixedly connected with the tail beam (5) and the fuselage main body structure (2); the upper opening cover and the lower opening cover are detachably connected with the fuselage main body structure (2); the upper opening cover A (1) is an engine chamber; the upper opening cover B (3) is an electronic device chamber; the lower opening cover A (6) and the lower opening cover B (8) are load chambers. By virtue of the fuselage structure of the unmanned helicopter with the bearing shell, the problems of the conventional unmanned helicopter that the structural mass is large, the skin easily loses stability and the joint of the skin is not sealed tightly of the fuselage structure can be solved.
Description
Technical field
The present invention relates to a kind of depopulated helicopter airframe structure of housing load, it relates to the part design of small-sized depopulated helicopter, belongs 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, also can be used for the non-military task such as flight test, aerial mapping simultaneously.Comparatively fixed wing aircraft, depopulated helicopter has the functions such as hovering, vertical takeoff and landing, can execute the task more flexibly.Because depopulated helicopter parts are many, therefore the position of its all parts needs to consider full machine center of gravity, operating needs, installation interference etc. problem.And due to depopulated helicopter load limited, therefore its full machine unit design is for most important a frame depopulated helicopter.
The transmission of the airframe structure primary responsibility load of depopulated helicopter, main load has the lift and moment of torsion that are brought by rotor, has the aerodynamic force that aerodynamic loading brings, and has the mass force loading and bring load.The main body mechanism of current depopulated helicopter has framework type, truss-like, trusses formula and hybrid etc., then the framework formed at them arranges covering.The load main like this box section that beam, wall, bar, plate are formed again is transmitted, and aerodynamic force is transmitted by covering.
The many employings of structure " basket-hanging " of traditional depopulated helicopter, and hound is arranged near rotor, crossbeam is arranged in fuselage, reinforcing frame is arranged again near rotor, such structure can transfer machine Main Load with it, but major defect is that its architecture quality is very heavy, and covering is due to thin easy unstability.And be also easy to occur that ftracture or poorly sealed problem in the connection of thin skin, the problem caused like this be rain or sand and dust weather under flight be easy to cause safety misadventure.Simultaneously because needs load load and equipment, need to install bearing beam additional in structure originally, and suspension member, and the shape of load also can be restricted, and causes architecture quality to increase further like this.Present patent application, namely for this problem, have developed a kind of depopulated helicopter airframe structure of housing load, achieves good effect.
Summary of the invention
The technical matters solved
It is large that the main body mechanism of traditional depopulated helicopter also exists architecture quality, the easy unstability of covering, the problems such as covering junction is poorly sealed, cause the application of depopulated helicopter to be subject to environmental limit like this, the depopulated helicopter airframe structure of a kind of housing load that present patent application provides can solve the problem.
1. the technical scheme adopted
The present invention is mainly by realize the appropriate design of depopulated helicopter structure.
The technical scheme that the present invention specifically implements below is described.
Fuselage adopts housing to be main load-carrying construction, this eliminates the structures such as the beam in conventional airframe, bar, bears whole aerodynamic force by thicker covering, and the box section of reinforcing frame a small amount of again and thick covering composition carries out power transmission.Its structure 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), alighting gear (7), horizontal plate (9), reinforcing frame A (10), reinforcing frame B (11) and vertical tail (4).Position annexation is therebetween: alighting gear (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 adopts 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) is load storehouse.The particular location of each lid as shown in Figure 2.
In fuselage, arrange that a small amount of reinforcing frame can increase the intensity of structure like this.Fuselage interior structure as shown in Figure 3.Near rotor, arrange that reinforcing frame A (10) can disperse the concentrated load brought by rotor like this, exert all one's strength and be evenly distributed on covering.Reinforcing frame B (11) can make afterbody power transmission forward be able to continuously.Because forebody opening is more, therefore laterally add in mmi machine body and put with horizontal plate (9), like this can transmitted load, but also can at the upper place apparatus of horizontal plate (9).
3. beneficial effect
The invention has the advantages that:
1) case type structure is adopted effectively can to reduce architecture quality.
2) adopt case type structure can reduce traditional depopulated helicopter thin skin seam not tight, the problem of poor sealing, makes this helicopter fly in the rainy day.
3) the lid position of reasonable Arrangement solves conventional helicopters and loads difficult problem, and decrease owing to loading some required suspension members, the lower flap provides two load storehouses can increase the alerting ability of loading, and the shape need of load also can reduce.
Accompanying drawing explanation
Fig. 1 fuselage integral structure axonometric drawing
Fig. 2 each lid position front elevation
Fig. 3 fuselage interior structure shaft side figure
In figure, nomenclature 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, alighting gear; 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 be described:
In the use procedure of depopulated helicopter, installing each lid after needing to be fixed loading can fly.Each lid is set and can carries out rectification to air-flow, obviously reduce the aerodynamic drag of helicopter, increase the aesthetic property of aircraft simultaneously.In working service, because the main load-carrying construction of case type structure is covering, therefore case type fuselage easily checks the defect that structure has.In harsh environment, because the leak tightness of covering is protected, the service life of part can correspondingly improve.
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), alighting gear (7), horizontal plate (9), reinforcing frame A (10), reinforcing frame B (11) and vertical tail (4).Position annexation is therebetween: alighting gear (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 adopts 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) is load storehouse.The particular location of each lid as shown in Figure 2.
In fuselage, arrange that a small amount of reinforcing frame can increase the intensity of structure like this.Fuselage interior structure as shown in Figure 3.Near rotor, arrange that reinforcing frame A (10) can disperse the concentrated load brought by rotor like this, exert all one's strength and be evenly distributed on covering.Reinforcing frame B (11) can make afterbody power transmission forward be able to continuously.Because forebody opening is more, therefore laterally add in mmi machine body and put with horizontal plate (9), like this can transmitted load, but also can at the upper place apparatus of horizontal plate (9).
Claims (1)
1. a depopulated helicopter airframe structure for housing load, is characterized in that: 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), alighting gear (7), horizontal plate (9), reinforcing frame A (10), reinforcing frame B (11) and vertical tail (4); Alighting gear (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 adopts 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) is load storehouse; In fuselage, arrange that reinforcing frame can increase the intensity of structure, near rotor, arrange that reinforcing frame A (10) can disperse the concentrated load brought by rotor, exert all one's strength and be evenly distributed on covering; Reinforcing frame B (11) can make afterbody power transmission forward be able to continuously, because forebody opening is more, therefore laterally adding in mmi machine body puts with horizontal plate (9), like this can transmitted load, again can 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 |
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| 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 |
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| Publication Number | Publication Date |
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| CN104210642A true CN104210642A (en) | 2014-12-17 |
| CN104210642B CN104210642B (en) | 2016-09-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410471819.6A Active CN104210642B (en) | 2014-09-16 | 2014-09-16 | A kind of depopulated helicopter airframe structure of housing load |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554700A (en) * | 2015-01-28 | 2015-04-29 | 张伟 | Upper beam, helicopter airframe adopting same and helicopter |
| CN114030592A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Method for constructing retractable main landing gear bearing structure of helicopter |
Citations (10)
| 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 |
| US20020171009A1 (en) * | 2001-04-04 | 2002-11-21 | Agusta S.P.A | Rescue vehicle |
| US20040031879A1 (en) * | 2002-08-13 | 2004-02-19 | Kay Bruce Frederic | Composite tail cone assembly |
| EP1714867A1 (en) * | 2005-04-22 | 2006-10-25 | Eurocopter | Supporting structure and rotorcraft |
| US20060261216A1 (en) * | 2005-05-18 | 2006-11-23 | Bell Helicopter Textron Inc. | Helicopter one-piece door |
| WO2009048881A2 (en) * | 2007-10-12 | 2009-04-16 | Abe Karem | Composite bulkhead and skin construction |
| 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 |
-
2014
- 2014-09-16 CN CN201410471819.6A patent/CN104210642B/en active Active
Patent Citations (10)
| 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 |
| US20020171009A1 (en) * | 2001-04-04 | 2002-11-21 | Agusta S.P.A | Rescue vehicle |
| US20040031879A1 (en) * | 2002-08-13 | 2004-02-19 | Kay Bruce Frederic | Composite tail cone assembly |
| EP1714867A1 (en) * | 2005-04-22 | 2006-10-25 | Eurocopter | Supporting structure and rotorcraft |
| US20060261216A1 (en) * | 2005-05-18 | 2006-11-23 | Bell Helicopter Textron Inc. | Helicopter one-piece door |
| WO2009048881A2 (en) * | 2007-10-12 | 2009-04-16 | Abe Karem | Composite bulkhead and skin construction |
| 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 |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554700A (en) * | 2015-01-28 | 2015-04-29 | 张伟 | Upper beam, helicopter airframe adopting same and helicopter |
| CN114030592A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Method for constructing retractable main landing gear bearing structure of helicopter |
| 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 |
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| Publication number | Publication date |
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| CN104210642B (en) | 2016-09-07 |
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Owner name: TIANXUN INNOVATION (BEIJING) TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: BEIJING LANTING HUAYI MEDIA CO., LTD. Effective date: 20150526 |
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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. |
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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. |
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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. |