CN103979100B - A kind of main landing gear fairing of general-purpose aircraft - Google Patents
A kind of main landing gear fairing of general-purpose aircraft Download PDFInfo
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- CN103979100B CN103979100B CN201410172239.7A CN201410172239A CN103979100B CN 103979100 B CN103979100 B CN 103979100B CN 201410172239 A CN201410172239 A CN 201410172239A CN 103979100 B CN103979100 B CN 103979100B
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- strut member
- fairing
- landing gear
- main landing
- posterior
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- 238000010276 construction Methods 0.000 claims description 23
- 238000007789 sealing Methods 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 abstract description 3
- 238000004378 air conditioning Methods 0.000 description 2
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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Abstract
The invention belongs to airplane structural design technology, relate to a kind of main landing gear fairing of general-purpose aircraft.Main landing gear fairing by left front fairing, front lower fairing, right front fairing, left back fairing, right back fairing, left front strut member, right front supports, front cross strut member, middle part horizontal support piece, posterior transversal strut member, rear left strut member, posterior central strut member, rear right strut member, back support member, led covering, hairbrush under cabin, safeguarded lid, connect edge strip and form, the present invention realizes main landing gear folding and unfolding rectification object, reduce interference drag, promote maneuvering performance.In fairing and fuselage principal space structure, hold and arrange the systems such as main landing gear, hydraulic pressure, a/c system, solve limited space in cabin, layout limitation problem.Master rises in cabin and forms confined space by fairing and hairbrush sealing structural component, avoids main landing gear and internal unit to expose in atmosphere, is formed and effectively protect.
Description
Technical field
The invention belongs to airplane structural design technology, relate to a kind of main landing gear fairing of general-purpose aircraft.
Background technology
Existing short distance general-purpose aircraft fairing comprises wing body fairing, cowling etc., does not generally have main landing gear dome structure.Aerodynamic interference resistance is comparatively large in-flight, and manipulative capability reduces, and main landing gear exposes in atmosphere simultaneously, subjects to corrosion.And existing short distance branch line civil aircraft, the space of fuselage interior is smaller, inevitably more difficult for system layout, can not hold and settle large equipment.Usually, the main landing gear fairing of airliner and wing body fairing merge one; Large freight aircraft main landing gear fairing is distributed in the left and right sides, to receive tandem-wheel main gear, again because large aircraft main landing gear fairing is arranged in fuselage or Wing-Body Configurations central box section, therefore, be not suitable for and be arranged on the less general-purpose aircraft of script fuselage diameter, further, general-purpose aircraft fuselage does not have space main landing gear yet.
Summary of the invention
The object of this invention is to provide a kind of main landing gear fairing of general-purpose aircraft that can meet short distance aircraft main landing gear and not subject to corrode.
Technical solution of the present invention is,
Main landing gear fairing is by left front fairing, front lower fairing, right front fairing, left back fairing, right back fairing, left front strut member, right front supports, front cross strut member, middle part horizontal support piece, posterior transversal strut member, rear left strut member, posterior central strut member, rear right strut member, back support member, lead covering under cabin, hairbrush, safeguard lid, connect edge strip composition, left front strut member, right front supports, front cross strut member, middle part horizontal support piece, posterior transversal strut member, rear left strut member, posterior central strut member, rear right strut member, back support member composition main landing gear fairing skeleton, left front strut member, on right front supports, edge strip is connected with housing construction, left front strut member, the right-hand member of right front supports is connected with the left end of front cross strut member, front cross strut member, middle part horizontal support piece, the upper edge strip of posterior transversal strut member is connected with housing construction, rear left strut member, posterior central strut member, the upper edge strip of rear right strut member is connected with housing construction, rear left strut member, posterior central strut member, rear right strut member left end is connected with middle part horizontal support piece, right-hand member is connected with posterior transversal strut member, the upper edge strip of back support member is connected with housing construction, under having led cabin, covering left end is connected with front cross strut member, lead the right-hand member of covering under cabin to be connected with middle part horizontal support piece, hairbrush is arranged on the semicircle opening part having led covering under cabin, safeguard lid border respectively with posterior transversal strut member, left back fairing, right back fairing is connected, left front fairing, front lower fairing, right front fairing, left back fairing, right back fairing composition fairing outer hull and left front strut member, right front supports, front cross strut member, middle part horizontal support piece, posterior transversal strut member, rear left strut member, posterior central strut member, rear right strut member, the main landing gear fairing skeleton structure that back support member forms jointly is connected, and the border of fairing outer hull is connected with housing construction by connecting edge strip.
Advantage of the present invention and effect
The present invention realizes main landing gear draw-in and draw-off function, carries out necessary rectification to profile, reduces interference drag, promotes maneuvering performance.In fairing and fuselage principal space structure, hold and arrange the systems such as main landing gear, illumination, hydraulic pressure, a/c system, solve limited space in cabin, layout limitation problem.Master rises in cabin and forms confined space by fairing and hairbrush sealing structural component, avoids main landing gear and internal unit to expose in atmosphere, is formed and effectively protect.Main landing gear fairing is arranged on airframe structure outside by the present invention, and main landing gear income, in fairing, has adapted to the feature that general-purpose aircraft fuselage diameter is less.
Accompanying drawing explanation
Fig. 1 is left front axis side view of the present invention;
Fig. 2 is birds-eye view of the present invention;
Fig. 3 is the schematic diagram of the embodiment of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is elaborated.As shown in the figure, main landing gear fairing comprises:
Left front fairing 1, front lower fairing 2, right front fairing 3, left back fairing 4, right back fairing 5, left front strut member 6, right front supports 7, front cross strut member 8, middle part horizontal support piece 9, posterior transversal strut member 10, rear left strut member 11, posterior central strut member 12, rear right strut member 13, back support member 14, lead covering 15, hairbrush 16 under cabin, safeguarded lid 17, connect edge strip 18 and form.
Left front strut member 6, right front supports 7, front cross strut member 8, middle part horizontal support piece 9, posterior transversal strut member 10, rear left strut member 11, posterior central strut member 12, rear right strut member 13, back support member 14 form main landing gear fairing skeleton.On left front strut member 6, right front supports 7, edge strip is connected with housing construction, and right-hand member is connected with front cross strut member 8.On front cross strut member 8, middle part horizontal support piece 9, posterior transversal strut member 10, edge strip is connected with housing construction.On rear left strut member 11, posterior central strut member 12, rear right strut member 13, edge strip is connected with housing construction, and left end is connected with middle part horizontal support piece 9, and right-hand member is connected with posterior transversal strut member 10.On back support member 14, edge strip is connected with housing construction.Under having led cabin, covering 15 left end is connected with front cross strut member 8, and right-hand member is connected with middle part horizontal support piece 9.Hairbrush 16 is arranged on the semicircle opening part having led covering 15 under cabin.Safeguard that lid 17 border is connected with posterior transversal strut member 10, left back fairing 4, right back fairing 5 respectively.Left front fairing 1, front lower fairing 2, right front fairing 3, left back fairing 4, right back fairing 5 form fairing outer hull and are connected with the main landing gear fairing skeleton structure that left front strut member 6, right front supports 7, front cross strut member 8, middle part horizontal support piece 9, posterior transversal strut member 10, rear left strut member 11, posterior central strut member 12, rear right strut member 13, back support member 14 form jointly, and border is connected with housing construction by connecting edge strip 18.
Left front fairing 1, left front strut member 6, front cross strut member 8 form cassette space structure with housing construction.Front lower fairing 2, left front strut member 6, right front supports 7, front cross strut member 8 form cassette space structure with housing construction.Right front fairing 3, right front supports 7, front cross strut member 8 form cassette space structure with housing construction.Be main landing gear compartment between front cross strut member 8, middle part horizontal support piece 9.Hairbrush 16 to have led under cabin space between covering 15 and main landing gear for sealing, and can effectively prevent sandstone, ponding enters and led cabin.Middle part horizontal support piece 9, posterior transversal strut member 10, rear left strut member 11, posterior central strut member 12, rear right strut member 13 form 2 the cassette space structures in left and right.Left back fairing 4, right back fairing 5, posterior transversal strut member 10 form cassette space structure.Above-mentioned cassette space structure all can effectively hold arrangement airborne equipment.Safeguard that lid 17 is for plant maintenance.Back support member 14 is for strengthening the rear portion boxlike space structure after separating.Connecting edge strip 18 can effectively prevent forming machine body structure to connect crackle.
Embodiment
Left front strut member 6, right front supports 7, front cross strut member 8, middle part horizontal support piece 9, posterior transversal strut member 10, rear left strut member 11, posterior central strut member 12, rear right strut member 13, back support member 14 form main landing gear fairing skeleton and are connected with housing construction.Left front fairing 1, front lower fairing 2, right front fairing 3, left back fairing 4, right back fairing 5 form fairing outer hull and are connected with the main landing gear fairing skeleton structure that left front strut member 6, right front supports 7, front cross strut member 8, middle part horizontal support piece 9, posterior transversal strut member 10, rear left strut member 11, posterior central strut member 12, rear right strut member 13, back support member 14 form jointly, and border is connected with housing construction by connecting edge strip 18.
Left front fairing 1, left front strut member 6, front cross strut member 8 and housing construction forms in cassette space structure and arrange left front emergency light 19 and left front landing lights 20, and arrange air-conditioning duct.Front lower fairing 2, left front strut member 6, right front supports 7, front cross strut member 8 and housing construction form in cassette space structure and arrange air-conditioning compressor and pipeline 21.Right front fairing 3, right front supports 7, front cross strut member 8 and housing construction forms in cassette space structure and arrange right front emergency light 22 and right front landing lights 23.Front cross strut member 8, middle part horizontal support piece 9 main landing gear compartments arrange main landing gear, Lighting System.Hairbrush 16 to have led under cabin space between covering 15 and main landing gear for sealing, and can effectively prevent sandstone, ponding enters and led cabin.Middle part horizontal support piece 9, posterior transversal strut member 10, rear left strut member 11, posterior central strut member 12, rear right strut member 13 form 2 the cassette space structures in left and right, arrange hydraulic emergency current collector and Hydraulic Main current collector respectively.Left back fairing 4, right back fairing 5, posterior transversal strut member 10 form in cassette space structure and arrange emergency brake current collector 25, left back emergency light 26, right back emergency light 27.Safeguard that lid 17 is safeguarded for emergency brake current collector 25.Connect edge strip 18 can effectively Crack prevention along the diffusion of fuselage wallboard main structure, extension.
Claims (1)
1. a main landing gear fairing for general-purpose aircraft, is characterized in that, main landing gear fairing is by left front fairing (1), front lower fairing (2), right front fairing (3), left back fairing (4), right back fairing (5), left front strut member (6), right front supports (7), front cross strut member (8), middle part horizontal support piece (9), posterior transversal strut member (10), rear left strut member (11), posterior central strut member (12), rear right strut member (13), back support member (14), lead covering (15) under cabin, hairbrush (16), safeguard lid (17), connect edge strip (18) composition, left front strut member (6), right front supports (7), front cross strut member (8), middle part horizontal support piece (9), posterior transversal strut member (10), rear left strut member (11), posterior central strut member (12), rear right strut member (13), back support member (14) composition main landing gear fairing skeleton, left front strut member (6), the upper edge strip of right front supports (7) is connected with housing construction, left front strut member (6), the right-hand member of right front supports (7) is connected with the left end of front cross strut member (8), front cross strut member (8), middle part horizontal support piece (9), the upper edge strip of posterior transversal strut member (10) is connected with housing construction, rear left strut member (11), posterior central strut member (12), the upper edge strip of rear right strut member (13) is connected with housing construction, rear left strut member (11), posterior central strut member (12), rear right strut member (13) left end is connected with middle part horizontal support piece (9), right-hand member is connected with posterior transversal strut member (10), the upper edge strip of back support member (14) is connected with housing construction, under having led cabin, covering (15) left end is connected with front cross strut member (8), lead the right-hand member of covering (15) under cabin to be connected with middle part horizontal support piece (9), hairbrush (16) is arranged on the semicircle opening part having led covering (15) under cabin, safeguard lid (17) border respectively with posterior transversal strut member (10), left back fairing (4), right back fairing (5) is connected, left front fairing (1), front lower fairing (2), right front fairing (3), left back fairing (4), right back fairing (5) composition fairing outer hull and left front strut member (6), right front supports (7), front cross strut member (8), middle part horizontal support piece (9), posterior transversal strut member (10), rear left strut member (11), posterior central strut member (12), rear right strut member (13), the main landing gear fairing skeleton structure that back support member (14) forms jointly is connected, and the border of fairing outer hull is connected with housing construction by connecting edge strip (18).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410172239.7A CN103979100B (en) | 2014-04-25 | 2014-04-25 | A kind of main landing gear fairing of general-purpose aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410172239.7A CN103979100B (en) | 2014-04-25 | 2014-04-25 | A kind of main landing gear fairing of general-purpose aircraft |
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| Publication Number | Publication Date |
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| CN103979100A CN103979100A (en) | 2014-08-13 |
| CN103979100B true CN103979100B (en) | 2015-12-30 |
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| CN201410172239.7A Expired - Fee Related CN103979100B (en) | 2014-04-25 | 2014-04-25 | A kind of main landing gear fairing of general-purpose aircraft |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9650154B2 (en) * | 2014-12-05 | 2017-05-16 | Gulfstream Aerospace Corporation | Aircraft landing gear assemblies with non-rotating light element clusters |
| CN105485864B (en) * | 2016-02-02 | 2019-01-25 | 北京航天发射技术研究所 | A kind of multipath environment comprehensive regulation system |
| US10745114B2 (en) * | 2017-08-07 | 2020-08-18 | The Boeing Company | Drag reduction device for exposed landing gear cavities |
| CN109720538B (en) * | 2018-11-12 | 2023-08-01 | 中航通飞华南飞机工业有限公司 | Built-in wheel cabin structure of aircraft fuselage side |
| CN117326049B (en) * | 2023-11-15 | 2024-10-22 | 中航通飞华南飞机工业有限公司 | Fairing of high-prop main landing gear of large-scale water plane |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2180462A (en) * | 1937-12-16 | 1939-11-21 | Seversky Aircraft Corp | Aircraft structure |
| US3653615A (en) * | 1969-06-03 | 1972-04-04 | Spence William | Aircraft nose opening mechanism |
| US4027836A (en) * | 1976-03-01 | 1977-06-07 | Seibel Julia K | Drag reducing fairing for landing gear |
| CN101489867A (en) * | 2006-07-12 | 2009-07-22 | 空中客车法国公司 | Storage compartment for the nose gear of an aircraft |
| US7946531B2 (en) * | 2008-02-14 | 2011-05-24 | The Boeing Company | Debris deflecting device, system, and method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2925462B1 (en) * | 2007-12-20 | 2010-07-30 | Airbus France | STORAGE BOX FOR A FRONT TRAIN FOR AN AIRCRAFT |
-
2014
- 2014-04-25 CN CN201410172239.7A patent/CN103979100B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2180462A (en) * | 1937-12-16 | 1939-11-21 | Seversky Aircraft Corp | Aircraft structure |
| US3653615A (en) * | 1969-06-03 | 1972-04-04 | Spence William | Aircraft nose opening mechanism |
| US4027836A (en) * | 1976-03-01 | 1977-06-07 | Seibel Julia K | Drag reducing fairing for landing gear |
| CN101489867A (en) * | 2006-07-12 | 2009-07-22 | 空中客车法国公司 | Storage compartment for the nose gear of an aircraft |
| US7946531B2 (en) * | 2008-02-14 | 2011-05-24 | The Boeing Company | Debris deflecting device, system, and method |
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| CN103979100A (en) | 2014-08-13 |
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Effective date of registration: 20170606 Address after: 150066 Heilongjiang Province, Harbin city Youxie Street Pingfang District No. 15 Patentee after: HARBIN HAFEI AVIATION INDUSTRY Co.,Ltd. Address before: 150066 Heilongjiang Province, Harbin city Youxie Street Pingfang District No. 15 Patentee before: HARBIN AIRCRAFT INDUSTRY (Group) Co.,Ltd. |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151230 |
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