CN103625631A - Design method for vertical tail docking structure - Google Patents
Design method for vertical tail docking structure Download PDFInfo
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- CN103625631A CN103625631A CN201310373937.9A CN201310373937A CN103625631A CN 103625631 A CN103625631 A CN 103625631A CN 201310373937 A CN201310373937 A CN 201310373937A CN 103625631 A CN103625631 A CN 103625631A
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- docking
- vertical fin
- joint
- vertical tail
- monaural
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Abstract
The invention provides a design method for a vertical tail docking structure. The design method is characterized in that an amount of single lug joints are respectively arranged at the root of a vertical tail at two sides of a course, a same amount of double lug joints are correspondingly arranged at a docking structure of the vertical tail, the diameters of holes in the single lug joints are equal to those of holes in the corresponding double lug joints, the axes of the holes are coaxial, bushes are pressed into docking through holes of the single lug joints and the double lug joints, and the single lug joints and the double lug joints are fixedly connected in a bolt connection mode. According to the invention, docking between the box section of a vertical tail composite material and fuselage lugs is realized in multi-point docking manner, so connection processing amount is reduced, connection workload is reduced, docking weight is lowered down, assembling workload is decreased, rapid docking between the vertical tail and a fuselage is realized, and connection of a few points enables the purpose of docking to be achieved and requirements on usage of an airplane to be met; thus, a development period is shortened, production cost is reduced, and maintainability and replaceability of a product are improved.
Description
Technical field
The invention belongs to aeroplane structure design technical field, be specifically related to a kind of vertical fin docking structure method of designing.
Background technology
The docking structures such as vertical fin and fuselage, wing generally adopt the to connect the flat surface of profile-type to dock with the form of bolt tension or adopt the spaced point of intensive ingot joint type with the form docking of bolt tension.These version assembly difficulty are large, need fine limit work to connect the flat surface, and processing capacity is large; For the safety of structure, docking weight is larger; The time needing during docking is longer; It is not very desirable that connecting bolt is carried with the form of tension.See shown in Fig. 1 and Fig. 2.Along with the lead time requirement of current and following aircraft, rapid Design, manufacture fast, assemble fast etc. becomes the factor that aircraft development must be considered.
Summary of the invention
The object of the invention is: vertical fin composite torsion-box adopts the form of multiple spot docking to dock with fuselage auricle, solve the problems such as aircraft rapid Design, manufacture, assembling, maintenance, replacing, meet the requirement of aircaft configuration docking minimum weight simultaneously, meet aircaft configuration docking intensity, rigidity Design requirement.
Technical scheme of the present invention is: a kind of vertical fin docking structure method of designing, it is characterized in that, in both sides, vertical fin root course, arrange respectively monaural joint, the ears joint of corresponding layout equal number in the structure with its docking, the hole of above-mentioned monaural joint equates with the bore dia of corresponding ears joint, and axis coaxle, is pressed into lining in the through hole docking at above-mentioned monaural joint with ears joint, and with bolt connecting mode, above-mentioned monaural joint and ears joint is fastenedly connected.
In described vertical fin root both lateral sides, arrange respectively two monaural joints, each monaural joint is connected in the structure of docking with vertical fin by the rod assembly of an adjustable in length, and two rod assembly directions of above-mentioned horizontal direction form " eight " word structure.
Described lining is slotted liner bushing, and endoporus is taper, and tapering D is 1 ° to 2 °, and bolt is conical bolt.
The quantity of described monaural joint and ears joint is 3-8.
The invention has the beneficial effects as follows: vertical fin composite torsion-box adopts the form of multiple spot docking to dock with fuselage auricle, reduced connection processing capacity, reduced connection work capacity, reduced docking weight, reduced fitting work amount, vertical fin energy fast speed is docked in fuselage, by the connection of seldom putting, reached the operating needs that docks object and meet aircraft.Thereby shortened the lead time, reduced productive costs, improved maintainability, the convertibility of product.
Accompanying drawing explanation
Fig. 1 is vertical fin structural representation
Fig. 2 is docking structure schematic diagram
1, butted section bars 2, the structure 3 of docking with vertical fin, to connecting bolt
Fig. 3 is taper slotted liner bushing schematic diagram
Fig. 4 is rod assembly schematic diagram
Fig. 5 is vertical fin and the schematic diagram that docks of its docking structure
1, vertical fin wallboard 2, the structure 3 of docking with vertical fin, docking structure (referring to Fig. 6) 4, docking structure (referring to Fig. 7)
Fig. 6 is vertical fin wallboard and the schematic diagram that docks of its docking structure
1, vertical fin wallboard 2, the structure 5 of docking with vertical fin, to connecting bolt group (comprising taper slotted liner bushing, conical bolt, adjustment pad)
Fig. 7 is vertical fin beam and the schematic diagram that docks of its docking structure
1, vertical fin wallboard 2, the structure 6 of docking with vertical fin, vertical fin beam 7, rod assembly
The specific embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail:
The structure 2 that shown in accompanying drawing 5,6,7, the present invention mainly comprises vertical fin wallboard 1, dock with vertical fin, docking structure 3, docking structure 4, to connecting bolt group 5, vertical fin beam 6, rod assembly 7.Vertical fin wallboard 1 is composite structure, and version is composite stiffened band monaural joint; The structure 2 of docking with vertical fin is metal construction, and version is ears joint, corresponding with monaural joint; Docking structure 3(is to connecting bolt group 5) be metallic combination structure, comprise taper slotted liner bushing, conical bolt, adjustment pad etc.; Docking structure 4(pull bar 7) be metallic combination structure, its scantling length is adjustable; Vertical fin beam 6 is composite material and metallic combination structure, 2 monaural joints of its termination band.
Above-mentioned vertical fin wallboard 1 and vertical fin beam 6 are respectively by being connected in the structure 2 of docking with vertical fin connecting bolt group 5 and rod assembly 7.
Vertical fin composite torsion-box adopts the form of multiple spot docking to dock with fuselage auricle, reduced connection processing capacity, reduced connection work capacity, reduced docking weight, reduced fitting work amount, vertical fin energy fast speed is docked in fuselage, by the connection of seldom putting, reached the operating needs that docks object and meet aircraft.Thereby shortened the lead time, reduced productive costs, improved maintainability, the convertibility of product.
Claims (4)
1. a vertical fin docking structure method of designing, it is characterized in that, in both sides, vertical fin root course, arrange respectively monaural joint, the ears joint of corresponding layout equal number in the structure with its docking, the hole of above-mentioned monaural joint equates with the bore dia of corresponding ears joint, and axis coaxle, is pressed into lining in the through hole docking at above-mentioned monaural joint with ears joint, and with bolt connecting mode, above-mentioned monaural joint and ears joint is fastenedly connected.
2. vertical fin docking structure method of designing according to claim 1, it is characterized in that, in described vertical fin root both lateral sides, arrange respectively two monaural joints, each monaural joint is connected in the structure of docking with vertical fin by the pull bar of an adjustable in length, and two pull bar directions of above-mentioned horizontal direction form " eight " word structure.
3. vertical fin docking structure method of designing according to claim 1, is characterized in that, described lining is slotted liner bushing, and endoporus is taper, and tapering is 1 ° to 2 °, and bolt is conical bolt.
4. vertical fin docking structure method of designing according to claim 1, is characterized in that, the quantity of described monaural joint and ears joint is 3-8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310373937.9A CN103625631A (en) | 2013-08-23 | 2013-08-23 | Design method for vertical tail docking structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310373937.9A CN103625631A (en) | 2013-08-23 | 2013-08-23 | Design method for vertical tail docking structure |
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| CN103625631A true CN103625631A (en) | 2014-03-12 |
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| CN201310373937.9A Pending CN103625631A (en) | 2013-08-23 | 2013-08-23 | Design method for vertical tail docking structure |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3181443A1 (en) * | 2015-12-18 | 2017-06-21 | The Boeing Company | Fuselage structure for accomodating tails and canards of different sizes and shapes |
| CN107628232A (en) * | 2017-08-11 | 2018-01-26 | 精功（绍兴）复合材料技术研发有限公司 | A kind of composite unmanned airplane empennage and its manufacture method |
| EP3418588A1 (en) * | 2017-06-23 | 2018-12-26 | Airbus Operations S.A.S. | Lug fastening system with angular offset appendages |
| CN109110153A (en) * | 2018-07-27 | 2019-01-01 | 哈尔滨工业大学 | A kind of support device for aircraft vertical fin and the test of fuselage bonding strength |
| CN109592003A (en) * | 2018-11-05 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of band stringer, docking auricle integral composite aerofoil wall panel structure |
| CN109720544A (en) * | 2018-11-12 | 2019-05-07 | 中航通飞研究院有限公司 | A kind of large water aircraft fuselage vertical fin docking structure |
| CN113830285A (en) * | 2021-10-25 | 2021-12-24 | 中航通飞华南飞机工业有限公司 | Horizontal vertical fin butt joint for realizing safe damage of tip part of wing beam of main box section of vertical fin |
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| US20110089292A1 (en) * | 2009-01-26 | 2011-04-21 | Airbus Operations Limited | Aircraft joint |
| CN102307782A (en) * | 2008-12-18 | 2012-01-04 | 空客运营有限公司 | Structure of the load-introduction area in the fuselage rear section of an aircraft |
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| JP2001138996A (en) * | 1999-11-10 | 2001-05-22 | Mikio Kuzuu | Airplane mounted with fourth-fifth wings and satabilizer wing |
| KR20040023944A (en) * | 2002-09-12 | 2004-03-20 | 한국항공우주산업 주식회사 | Installing structure for the vertical tail of airplane |
| CN101267983A (en) * | 2005-09-27 | 2008-09-17 | 法国空中客车公司 | Engine suspension device inserted between an aircraft wing and said engine |
| US20090302159A1 (en) * | 2007-01-16 | 2009-12-10 | Sagem Defense Securite | Aircraft Wing Including a Plurality of Dismountable Members |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3181443A1 (en) * | 2015-12-18 | 2017-06-21 | The Boeing Company | Fuselage structure for accomodating tails and canards of different sizes and shapes |
| US9849966B2 (en) | 2015-12-18 | 2017-12-26 | The Boeing Company | Fuselage structure for accommodating tails and canards of different sizes and shapes |
| RU2728474C2 (en) * | 2015-12-18 | 2020-07-29 | Зе Боинг Компани | Fuselage design for placement of empennage and front horizontal empennage of various sizes and shapes |
| EP3418588A1 (en) * | 2017-06-23 | 2018-12-26 | Airbus Operations S.A.S. | Lug fastening system with angular offset appendages |
| FR3068091A1 (en) * | 2017-06-23 | 2018-12-28 | Airbus Operations (S.A.S.) | HOLDING SYSTEM HAVING DECAL APPENDICES ANGULARLY |
| US11549529B2 (en) | 2017-06-23 | 2023-01-10 | Airbus Operations (Sas) | Fastening system having tenons provided with angularly offset appendages |
| CN107628232A (en) * | 2017-08-11 | 2018-01-26 | 精功（绍兴）复合材料技术研发有限公司 | A kind of composite unmanned airplane empennage and its manufacture method |
| CN109110153A (en) * | 2018-07-27 | 2019-01-01 | 哈尔滨工业大学 | A kind of support device for aircraft vertical fin and the test of fuselage bonding strength |
| CN109110153B (en) * | 2018-07-27 | 2020-04-24 | 哈尔滨工业大学 | Supporting device for connection strength test of airplane vertical fin and airplane body |
| CN109592003A (en) * | 2018-11-05 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of band stringer, docking auricle integral composite aerofoil wall panel structure |
| CN109592003B (en) * | 2018-11-05 | 2022-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Integral composite material wing surface wallboard structure with stringer and butt joint lug |
| CN109720544A (en) * | 2018-11-12 | 2019-05-07 | 中航通飞研究院有限公司 | A kind of large water aircraft fuselage vertical fin docking structure |
| CN113830285A (en) * | 2021-10-25 | 2021-12-24 | 中航通飞华南飞机工业有限公司 | Horizontal vertical fin butt joint for realizing safe damage of tip part of wing beam of main box section of vertical fin |
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Application publication date: 20140312 |