CN107054621A - A kind of plug-in transition beam of wing - Google Patents
A kind of plug-in transition beam of wing Download PDFInfo
- Publication number
- CN107054621A CN107054621A CN201710179100.9A CN201710179100A CN107054621A CN 107054621 A CN107054621 A CN 107054621A CN 201710179100 A CN201710179100 A CN 201710179100A CN 107054621 A CN107054621 A CN 107054621A
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- Prior art keywords
- transition
- transition beam
- wing
- plug
- horizontal
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Road Paving Structures (AREA)
Abstract
This application discloses a kind of plug-in transition beam of wing, belong to technical field of aircraft structure design.Including vertical transition beam (1) and two horizontal transition beams (2), one end of vertical transition beam (1) is fixed at the lower wall panels of the wing, two horizontal transition beams (2) are symmetrically distributed in the other end of vertical transition beam (1), set fluted on the horizontal transition beam, the cross section of the vertical transition beam (1) is streamlined.The plug-in transition girder construction of wing of the present invention can meet the requirement of carry equipment, and structural strength meets design requirement, meanwhile, the lift and resistance of aircraft, which will not be constituted, influences.
Description
Technical field
The application belongs to technical field of aircraft structure design, and in particular to a kind of plug-in transition beam of wing.
Background technology
In current aircraft development, according to the requests for alternations of aircraft, it is necessary to which portion's carry is a number of under the wings of an airplane sets
Standby instrument.A kind of transition girder construction of portion's design under the wings of an airplane is needed for this, for carry equipment and instrument.According to the function of aircraft
With require and with reference to aircraft own characteristic, the structure design of transition beam needs to meet following 5 conditions：
1) plug-in transition girder construction can meet the requirement of carry equipment；
2) plug-in transition girder construction will not be constituted on the lift and resistance of aircraft and influenceed；
3) plug-in transition girder construction disclosure satisfy that requirement of strength design；
4) bonding strength of plug-in transition girder construction and wing meets requirement of strength design；
5) the wing regional area structural strength connected with plug-in transition beam disclosure satisfy that requirement.
Because wing structure is the important component to aircraft offer lift, it is also the important load-carrying member of aircaft configuration, passes
The wing transition beam of system is by the way of metal plate sub-assembly is adopted, and carry number of devices is less and volume is larger, and to aircraft drag
Influence etc. be difficult some particular/special requirements for meeting aircraft.
The content of the invention
In order to solve the above problems, present applicant proposes a kind of plug-in transition beam of wing, so that aircraft carry plurality of devices
Instrument, while meeting the influence of airplane ascensional force and resistance.
The plug-in transition beam of the application wing, mainly including vertical transition beam and two horizontal transition beams, vertical transition beam
One end be fixed at the lower wall panels of the wing, two horizontal transition beams are symmetrically distributed in the other end of vertical transition beam, institute
State and set fluted on horizontal transition beam, the cross section of the vertical transition beam is streamlined.
Preferably, ribs is provided with the lower wall panels of the wing, the vertical transition beam is fixed on described add
On strong rib.
In such scheme preferably, vertical transition beam is connected with horizontal transition beam bolt.
In such scheme preferably, vertical transition beam is provided with some through holes in one end of connection horizontal transition beam.
In such scheme preferably, the center section internal diameter of horizontal transition beam is less than the internal diameter at two ends, the centre
Part is provided with the sliding block that is provided with and can be slided along chute direction in strip connected in star, the groove.
In such scheme preferably, the cross section of horizontal transition beam is streamlined.
In such scheme preferably, one end of the remote vertical transition beam of horizontal transition beam is circumferentially arranged some
Bar-shaped trough.
The advantage of the application is：
1) plug-in transition girder construction can meet the requirement of carry equipment；
2) plug-in transition girder construction will not be constituted on the lift and resistance of aircraft and influenceed；
3) plug-in transition girder construction disclosure satisfy that requirement of strength design；
4) bonding strength of plug-in transition girder construction and wing meets requirement of strength design；
5) the wing regional area structural strength connected with plug-in transition beam disclosure satisfy that requirement.
Brief description of the drawings
Fig. 1 is the structural representation of a preferred embodiment of the plug-in transition beam of the application wing.
Fig. 2 is the plug-in transition beam right view of wing of the application embodiment illustrated in fig. 1.
Fig. 3 for embodiment illustrated in fig. 2 A-A to sectional view.
Fig. 4 is the B-B direction sectional view of embodiment illustrated in fig. 2.
Fig. 5 for embodiment illustrated in fig. 2 C-C to sectional view.
Fig. 6 is the horizontal transition girder construction schematic diagram of the application embodiment illustrated in fig. 1.
Fig. 7 for embodiment illustrated in fig. 6 A-A to sectional view.
Fig. 8 is the B-B direction sectional view of embodiment illustrated in fig. 6.
Fig. 9 for embodiment illustrated in fig. 6 C-C to sectional view.
Wherein, 1 is vertical transition beam, and 2 be horizontal transition beam, and 3 be ribs, and 4 be wing lower wall panels, and 21 be groove, 22
For sliding block.
Embodiment
To make the purpose, technical scheme and advantage of the application implementation clearer, below in conjunction with the embodiment of the present application
Accompanying drawing, the technical scheme in the embodiment of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the application
A part of embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
In explaining the application, and it is not intended that limitation to the application.Based on the embodiment in the application, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of the application protection.Under
Embodiments herein is described in detail with reference to accompanying drawing for face.
In the description of the present application, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of description the application and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the application is protected
The limitation of scope.
Present applicant proposes a kind of plug-in transition beam of wing, so that aircraft carry plurality of devices instrument, while meeting aircraft
The influence of lift and resistance.
The plug-in transition beam of the application wing as shown in figure 1, mainly include vertical transition beam 1 and two horizontal transition beams 2,
One end of vertical transition beam 1 is fixed at the wing lower wall panels 4, and two horizontal transition beams 2 are symmetrically distributed in vertical transition beam 1
The other end, set fluted on the horizontal transition beam, for carry equipment, or when hanging equipment is loaded in horizontal transition beam 1
When upper, carried out for the equipment to institute's carry spacing.The cross section of the vertical transition beam 1 is streamlined, as shown in figure 3, being
The A-A of vertical transition beam 1 cuts open schematic diagram, i.e., the cross-sectional view of vertical transition beam 1.It will be apparent from this figure that vertical mistake
The cross section of bridging beam 1 is ellipsoid like structure, and two ends are disposed as streamlined, and the cross section with wing is closely similar, Neng Gouman
Requirement of the sufficient aircraft in flight course to resistance.
Fig. 2 gives wing plug-in transition beam right view, is set from the inside of the vertical transition beam 1 of the signal it can be seen from the figure that
Put and want multistage strip connected in star, Fig. 3 gives the A-A with groove and cutd open, Fig. 4 gives its B-B with horizontal transition Liang Chu
Cut open, the B-B is cutd open as sectional view at un-grooved, it can be seen that Fig. 3 and Fig. 4's main difference is that whether middle slots, set
The purpose of elongated slot is the weight for mitigating vertical transition beam, meanwhile, necessary part is set to entity, is conducive to structural strengthening.
The plug-in transition beam of wing and one end of wing junction are set to L-type material, and are fixed in the lower wall panels of wing, excellent
Choosing, as shown in figure 1, having carried out strengthening design to wing lower wall panels regional area structure, in the lower wall panels of the wing
Ribs 3 is provided with, the vertical transition beam 1 is fixed on the ribs 3, specifically, ribs 3 is stretching out wing downwards
It is provided with section bar connection strap band at lower wall panels, section bar connection strap band is tabular section bar, or two tabular section bars be arrangeding in parallel
For clamping vertical transition beam end, vertical transition beam and wing lower wall panels are connected using the section bar connection strap band of metal plate roll forming,
Its mode first choice bolt connection.
It is understood that in the present embodiment, vertical transition beam 1 connects with the preferred connected mode of horizontal transition beam 2 for bolt
Connect.
In the present embodiment, vertical transition beam 1 connection horizontal transition beam 2 one end be provided with some through holes, with reference to Fig. 1,
Fig. 2 and Fig. 5, wherein Fig. 5 are that Fig. 2 is provided with the C-C of through hole to sectional view.Three through holes are give at least in the present embodiment
Signal, it is to be understood that the through hole be used for carry equipment.
In the present embodiment, the center section internal diameter of horizontal transition beam 2 is less than the internal diameter at two ends, and the center section is provided with
The sliding block 22 that can be slided along chute direction is provided with strip connected in star 21, the groove 21.The structure of horizontal transition beam 2 is such as
Shown in Fig. 6, the center section internal diameter of horizontal transition beam 2 is smaller, and two ends internal diameter is larger, can in order to the carry junction of equipment
It is stuck in this less subregion of internal diameter, prevents to two ends, particularly slides outward.Groove structure may be referred to Fig. 8 institutes
The B-B direction sectional view of the horizontal transition beam 2 shown.It is understood that general carry junction is semicircle shape structure, and hang
Carry junction and be provided with projection, when semicircle shape structure is overlapped on the center section of horizontal transition beam shown in Fig. 62, projection is lucky
Can stretch into the groove shown in Fig. 8, afterwards promote sliding block 22, make its contact tab, thus to carry junction carry out laterally with
The displacement limitation of longitudinal direction.
In the present embodiment, the cross section of horizontal transition beam 2 is streamlined.And in the remote vertical transition of horizontal transition beam 2
One end of beam 1 is circumferentially arranged some bar-shaped troughs, and streamlined structure may be referred to the A-A of Fig. 7 horizontal transition beam 2 to section view
Figure, its two ends is set to smoothly transit, to reduce aircraft flight resistance.In Fig. 6, Fig. 7 and Fig. 9, it can be seen that horizontal transition beam
One end of 2 remote vertical transition beam 1 is evenly equipped with some bar-shaped troughs, and each the equipment and instrument of carry is needed to be adapted to connection.
To reduce the flight resistance of transition beam and carry equipment to aircraft, the overall structure of transition beam is minimized as far as possible,
Simultaneously to meet requirement of strength design, each transition beam adds structure using integrated machine.
The application is set to possess advantages below by foregoing description：
1) plug-in transition girder construction can meet the requirement of carry equipment；
2) plug-in transition girder construction will not be constituted on the lift and resistance of aircraft and influenceed；
3) plug-in transition girder construction disclosure satisfy that requirement of strength design；
4) bonding strength of plug-in transition girder construction and wing meets requirement of strength design；
5) the wing regional area structural strength connected with plug-in transition beam disclosure satisfy that requirement.
It is last it is to be noted that：Above example is only to the technical scheme for illustrating the application, rather than its limitations.To the greatest extent
The application is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of each embodiment technical scheme of the application
God and scope.
Claims (7)
1. a kind of plug-in transition beam of wing, it is characterised in that：Including vertical transition beam (1) and two horizontal transition beams (2), erect
One end of straight transition beam (1) is fixed at the lower wall panels of the wing, and two horizontal transition beams (2) are symmetrically distributed in vertical transition
Set fluted on the other end of beam (1), the horizontal transition beam, the cross section of the vertical transition beam (1) is streamlined.
2. the plug-in transition beam of wing as claimed in claim 1, it is characterised in that：It is provided with and adds in the lower wall panels of the wing
Strong rib (3), the vertical transition beam (1) is fixed on the ribs (3).
3. the plug-in transition beam of wing as claimed in claim 1, it is characterised in that：Vertical transition beam (1) and horizontal transition beam (2)
Bolt connection.
4. the plug-in transition beam of wing as claimed in claim 1, it is characterised in that：Vertical transition beam (1) is in connection horizontal transition
One end of beam (2) is provided with some through holes.
5. the plug-in transition beam of wing as claimed in claim 1, it is characterised in that：The center section internal diameter of horizontal transition beam (2)
Less than the internal diameter at two ends, the center section is provided with strip connected in star (21), and interior be provided with of the groove (21) can be along cunning
The sliding block (22) that groove direction is slided.
6. the plug-in transition beam of wing as claimed in claim 1, it is characterised in that：The cross section of horizontal transition beam (2) is streamline
Type.
7. the plug-in transition beam of wing as claimed in claim 1, it is characterised in that：The remote vertical transition of horizontal transition beam (2)
One end of beam (1) is circumferentially arranged some bar-shaped troughs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710179100.9A CN107054621A (en) | 2017-03-23 | 2017-03-23 | A kind of plug-in transition beam of wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710179100.9A CN107054621A (en) | 2017-03-23 | 2017-03-23 | A kind of plug-in transition beam of wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107054621A true CN107054621A (en) | 2017-08-18 |
Family
ID=59618035
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710179100.9A Pending CN107054621A (en) | 2017-03-23 | 2017-03-23 | A kind of plug-in transition beam of wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107054621A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639307A (en) * | 2018-06-22 | 2018-10-12 | 西安飞机工业（集团）有限责任公司 | A kind of connection structure of the outer hanging joint of aircraft |
| CN113665786A (en) * | 2020-05-15 | 2021-11-19 | 中航西飞民用飞机有限责任公司 | External hanging structure of aircraft wing |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6340134B1 (en) * | 1999-10-12 | 2002-01-22 | Ronald G. Meschino | Wing combination for drag reduction, aircraft including such a wing, and a method of reducing the drag of an existing aircraft |
| CN101233046A (en) * | 2005-07-29 | 2008-07-30 | 法国空中客车公司 | Assembly for aircraft comprising a wing system element as well as an attachment mast |
| CN205525034U (en) * | 2016-01-25 | 2016-08-31 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft supporting mechanism |
| CN106275419A (en) * | 2016-09-30 | 2017-01-04 | 顺丰科技有限公司 | The hanger of VUAV and unmanned plane |
| CN106275417A (en) * | 2016-09-12 | 2017-01-04 | 上海圣尧智能科技有限公司 | A kind of Fixed Wing AirVehicle with many rotors |
| CN106379543A (en) * | 2016-09-30 | 2017-02-08 | 顺丰科技有限公司 | Hanging rack of vertical take-off and landing unmanned plane and loading method of hanging rack |
-
2017
- 2017-03-23 CN CN201710179100.9A patent/CN107054621A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6340134B1 (en) * | 1999-10-12 | 2002-01-22 | Ronald G. Meschino | Wing combination for drag reduction, aircraft including such a wing, and a method of reducing the drag of an existing aircraft |
| CN101233046A (en) * | 2005-07-29 | 2008-07-30 | 法国空中客车公司 | Assembly for aircraft comprising a wing system element as well as an attachment mast |
| CN205525034U (en) * | 2016-01-25 | 2016-08-31 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft supporting mechanism |
| CN106275417A (en) * | 2016-09-12 | 2017-01-04 | 上海圣尧智能科技有限公司 | A kind of Fixed Wing AirVehicle with many rotors |
| CN106275419A (en) * | 2016-09-30 | 2017-01-04 | 顺丰科技有限公司 | The hanger of VUAV and unmanned plane |
| CN106379543A (en) * | 2016-09-30 | 2017-02-08 | 顺丰科技有限公司 | Hanging rack of vertical take-off and landing unmanned plane and loading method of hanging rack |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639307A (en) * | 2018-06-22 | 2018-10-12 | 西安飞机工业（集团）有限责任公司 | A kind of connection structure of the outer hanging joint of aircraft |
| CN113665786A (en) * | 2020-05-15 | 2021-11-19 | 中航西飞民用飞机有限责任公司 | External hanging structure of aircraft wing |
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Application publication date: 20170818 |
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| WD01 | Invention patent application deemed withdrawn after publication |