CN100509556C - Connecting structure for middle and outside wings of unmanned aerial vehicle - Google Patents
Connecting structure for middle and outside wings of unmanned aerial vehicle Download PDFInfo
- Publication number
- CN100509556C CN100509556C CNB2007103046952A CN200710304695A CN100509556C CN 100509556 C CN100509556 C CN 100509556C CN B2007103046952 A CNB2007103046952 A CN B2007103046952A CN 200710304695 A CN200710304695 A CN 200710304695A CN 100509556 C CN100509556 C CN 100509556C
- Authority
- CN
- China
- Prior art keywords
- wing
- joint
- pectination
- outer wing
- centre section
- 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.)
- Expired - Fee Related
Links
Images
Abstract
The present invention discloses a mid-wing and external-wing connection structure of an unmanned aerial vehicle. A mid-wing end rib and an external-wing root rib are the aluminium alloy reinforced ribs with comb-shaped joints. At the butt joint of the two reinforced ribs, the mid-wing and the external-wing are jointed by butt joint bolts made from high-intensified aluminium alloy material. After the mid-wing and the external-wing are butted, a joint seam is covered by a cowling made from composite material that is two rows of bolts are used fix the cowling at the reinforced ribs along the edge of the cowling. The mid-wing end rib and the external-wing root rib are considered as the butt joint of the mid-wing and the external-wing to integrate the joint and the structure as a whole, which reduces the complexity of the coordination relation and the connection relation and the manufacture error and assembly error by single joint, and the joint point and the grinder and the supporting structure of the external-wing are in one axial line, which ensures that the transmission force is continuous. The present invention has simple connection manner, which is convenient for disassembling and assembling and for checking the damage condition of a connection piece.
Description
Technical field
The invention belongs to the aviation machine field, relate to outer wing interconnection technique in a kind of unmanned plane.
Background technology
At present, unmanned plane has been widely used in campaign and the scouting of strategy level, supervision, target positioning, target is injured numerous areas such as assessment, electronic countermeasure, communication repeating.Because advantage and outstanding behaviours in practice thereof such as the unmanned plane cost are low, and penetration ability is good, army also presses for the unmanned plane that uses various function admirables.So safety, reliability, economy and operating needs are to unmanned plane design-calculated ultimate challenge.
The in-flight task of wing is to produce lift to support aircraft weight and to realize maneuvering flight.At this moment, act on huge aerodynamic force on the surface of wing, also needing sometimes driving engine, alighting gear are installed, or in wing, arranging ammunition cabins, weapon and fuel tank etc., these loadings also will be to the sizable concentrated load of wing effect, as thrust, impact, mass force etc.Realize the task that wing is born, wing configuration neither can be destroyed under these loadings with regard to guaranteeing it, also can not produce dangerous distortion, also require the structural weight of wing itself light as much as possible simultaneously, aspects such as technology, maintenance use are convenient as far as possible, suitable.Therefore the wing that different shaping occurs although the moulding difference for the basic mission (generation lift) of realizing wing, is the same substantially on the essential structure element of current wing, mainly contains spar, rib, long purlin, covering, abutment joint etc.Wing is divided into beam type, one piece and hybrid at present.
For the connection of outer wing in the unmanned plane, connection structure commonly used has two kinds, and a kind of is to connect by several abutment joints (concentrating intersection point), be that intersection point connects, the connection of middle outer wing couples together with several intersection points, and the girder construction comprehensive utilization is made good use of, can transmit bigger shearing and moment of flexure, use more extensively, can not give full play to but its defective is a covering load benefit, secondly, processing capacity is big, and waste of material is more, and its joint and spar are made of one, be not easy after the damage to repair, each several part connects more complicated; Another kind of structure is mainly by a lot of connecting connecting bolt along wing case periphery, also make the periphery formula connect or enclose frame and connect, can give full play to covering load efficient, the jointing that does not need the purpose made complexity, but bolt quantity is more, the outer wing work capacity that is linked and packed in the increase, simultaneously jointing is coordinated to bring difficulty each other, must add king bolt and hole tolerance on fit for this reason, thereby all bring adverse effect aspect Transfer of Shear and the strength at repeated alternation two, secondly, can not transmit bigger shearing and moment of flexure, the purpose that inaccessible structure composition utilizes, therefore, above-mentioned type of attachment is not easy to dismounting, and only is applicable to thin airfoil.
Summary of the invention
Main purpose of the present invention provides a kind of simple and practical middle outer wing connection structure, in order to improve the complexity of outer wing connection structure in the unmanned plane.At the unmanned plane layout characteristics, designed a kind of middle preferably outer wing connection structure of simple comprehensive application that is applicable to unmanned plane.
For reaching above purpose, the technical solution used in the present invention is as follows:
Wing centre section end rib and outer wing root are the aluminum alloy materials strengthening ribs of band pectination joint, each joint is the U shape parts of two ends symmetry, the two ends of symmetry have a hole, it is pectination joint connecting bore, the pectination joint side that wherein is positioned on the outer wing root has a bolt containing slot, the pectination joint side that is positioned on the wing centre section end rib has a nut containing slot, joint at these two strengthening ribs, wing centre section is in the same place by the butt joint bolted connection of high-strength aluminum alloy material with outer wing, the beam of several point of connection and middle outer wing and sewing with long stitches on an axis.During butt joint, to go in the bolt containing slot on the outer wing root the connecting bolt horizontal positioned, arc pallet nut horizontal positioned is gone in the nut containing slot on the wing centre section end rib, and the pectination joint connecting bore of butt joint screw bolt passes outer wing root and wing centre section end rib joint is connected with the arc pallet nut; After the middle outer wing butt joint, seam covers with the shoulder cowling of composite material, promptly is fixed on the strengthening rib along the foreskin periphery with two row's screws.
The invention has the advantages that:
(1) with the root of wing centre section end rib and outer wing as in the outer wing abutment joint, it is united two into one joint and structure, reduced the complexity of rapport and annexation, and the manufacturing errors and the assembly error of independent joint.
(2) several docking points of China and foreign countries' wing tip rib are arranged in the close profile place of lower aerofoil, and the beam of point of connection and middle outer wing with sew with long stitches on an axis, make power transmission continuous.
(3) connection mode is simple, is convenient to the condition in damaged of dismounting and inspection attaching parts.
(4) connection and power transmission only realize by the attaching parts at last lower aerofoil place.
Description of drawings
Fig. 1 is the connection diagram of outer wing connection structure in a kind of unmanned plane of the present invention;
Fig. 2 is the johning knot composition of outer wing connection structure in a kind of unmanned plane of the present invention;
Fig. 3 is a pectination joint section-drawing.
Among the figure: 1 wing centre section end rib, 2 outer wing root 3a pectination joint 3b pectination joints
4a pectination joint connecting bore 4b pectination joint connecting bore
7 pairs of connecting bolts of 5 bolt containing slot, 6 nut containing slot, 8 arc pallet nuts
The specific embodiment
The present invention is described in further detail below in conjunction with the drawings and specific embodiments.
Outer wing connection structure in a kind of unmanned plane of the present invention, as shown in Figure 1, wing centre section end rib 1 and outer wing root 2 are aluminum alloy materials strengthening ribs of band pectination joint 3a, 3b, and at the joint of these two strengthening ribs, wing centre section and outer wing link together to connecting bolt 7 by high-strength aluminum alloy material.During butt joint, at first each pectination joint connecting bore of wing centre section end rib 1 and outer wing root 2 is aimed at successively, as shown in Figure 2, to go in the bolt containing slot 5 on the outer wing root 2 connecting bolt 7 horizontal positioned, arc pallet nut 8 horizontal positioned are gone on the wing centre section end rib 1 in the corresponding nut containing slot 6, to pass pectination joint connecting bore 4b, the 4a of outer wing root 2 and wing centre section end rib 1 joint to connecting bolt 7 successively, and be connected with arc pallet nut 8, thereby two strengthening ribs are coupled together; Be parallel to as shown in Figure 3 connecting bolt 7 direction pectination joint 3a, 3b section-drawing, for expendable weight at utmost, pectination joint 3a, 3b are the U shape parts of two ends symmetry, the two ends of symmetry have a hole, be pectination joint connecting bore 4a, 4b, the pectination joint 3b side that wherein is positioned on the outer wing root 2 has a bolt containing slot 5, and the pectination joint 3a side that is positioned on the wing centre section end rib 1 has a nut containing slot 6.Successively all pectination joint 3a, 3b on wing centre section end rib 1 and the outer wing root 2 in kind are connected, have so just finished the butt joint of middle outer wing.For guaranteeing aerodynamic configuration, after the middle outer wing butt joint, seam covers with the shoulder cowling of composite material, promptly is fixed on the strengthening rib along the foreskin periphery with two row's screws.Can adjust according to the wing size connecting bolt 7 numbers, be 10 to connecting bolt 7 numbers in the present embodiment.
Claims (1)
1, outer wing connection structure in a kind of unmanned plane, it is characterized in that: being connected of wing centre section and outer wing is with the butt joint bolted connection by pectination joint that wing centre section end rib and these two strengthening ribs of outer wing root are respectively carried, described pectination joint and wing centre section end rib and outer wing root are respectively integrative-structure, and described wing centre section end rib and outer wing root are the aluminum alloy materials strengthening ribs of band pectination joint, and described is high-strength aluminum alloy material to connecting bolt;
Pectination joint interface on described wing centre section end rib and the outer wing root goes a part to form groove for the consideration button of loss of weight, form the U shape parts of two ends symmetry, described U shape parts two ends have connecting bore, and wing centre section end rib pectination joint side has nut containing slot, outer wing root pectination joint side has bolt containing slot, described connecting bolt is lain in a horizontal plane in the bolt containing slot on the outer wing root, nut lies in a horizontal plane in the nut containing slot on the described wing centre section end rib, the pectination joint connecting bore of butt joint screw bolt passes outer wing root and wing centre section end rib joint, be connected with nut, wing centre section end rib pectination joint contacts with face with the opposite face of outer wing root pectination joint, and the beam of several point of connection and middle outer wing and sewing with long stitches on an axis;
Described nut is the arc pallet nut, does not need other instruments when the effect of arc pallet nut is to install, and arc pallet face and nut containing slot inside face match, and have played locking effect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007103046952A CN100509556C (en) | 2007-12-28 | 2007-12-28 | Connecting structure for middle and outside wings of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007103046952A CN100509556C (en) | 2007-12-28 | 2007-12-28 | Connecting structure for middle and outside wings of unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101214853A CN101214853A (en) | 2008-07-09 |
| CN100509556C true CN100509556C (en) | 2009-07-08 |
Family
ID=39621381
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2007103046952A Expired - Fee Related CN100509556C (en) | 2007-12-28 | 2007-12-28 | Connecting structure for middle and outside wings of unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100509556C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3130534A4 (en) * | 2014-09-30 | 2018-01-24 | Commercial Aircraft Corporation Of China Ltd | Airplane wing assembly |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011127938A1 (en) * | 2010-04-12 | 2011-10-20 | Airbus Operations Gmbh | Fixed wing of an aircraft |
| GB201105104D0 (en) | 2011-03-28 | 2011-05-11 | Airbus Operations Ltd | Joint |
| US9981367B2 (en) * | 2015-07-07 | 2018-05-29 | The Boeing Company | Exterior indexing process and tooling |
| CN105270603B (en) * | 2015-10-27 | 2018-02-13 | 镇江顺宇飞行器有限公司 | A kind of unmanned Fixed Wing AirVehicle of high aspect ratio |
| GB2551311A (en) * | 2016-05-24 | 2017-12-20 | Airbus Operations Ltd | Winglet |
| CN106114816B (en) * | 2016-07-23 | 2018-06-15 | 北京耐威智能科技有限公司 | A kind of wing attachment device, wing and aircraft |
| CN106005365B (en) * | 2016-08-06 | 2018-09-11 | 北京耐威智能科技有限公司 | Built-in connection component, external connection component, attachment device, wing and aircraft |
| CN106275376B (en) * | 2016-08-31 | 2018-05-04 | 北京奇正数元科技股份有限公司 | A kind of center framework of small-sized unmanned plane |
| CN109808868A (en) * | 2018-11-22 | 2019-05-28 | 成都飞机工业（集团）有限责任公司 | A kind of interior outer wing docking structure of small drone |
| CN111895905B (en) * | 2020-05-27 | 2022-04-19 | 中国计量大学 | Error compensation method for hexagonal axis straightness detection system |
| CN113733595B (en) * | 2021-08-30 | 2022-06-14 | 北京航空航天大学 | Processing method of fully-wrapped composite material foam sandwich wing rib |
-
2007
- 2007-12-28 CN CNB2007103046952A patent/CN100509556C/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3130534A4 (en) * | 2014-09-30 | 2018-01-24 | Commercial Aircraft Corporation Of China Ltd | Airplane wing assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101214853A (en) | 2008-07-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100509556C (en) | Connecting structure for middle and outside wings of unmanned aerial vehicle | |
| CN105416565B (en) | Solar airplane | |
| US8613404B2 (en) | Take-up device for thrust forces with connecting rods for aircraft engine attachment pylon, integrating three aligned ball joints | |
| US5263821A (en) | Mid-beam jointed reconfigurable bearingless main rotor assembly | |
| CN100497088C (en) | Connecting structure for unmanned aerial vehicle body and wing | |
| US8544800B2 (en) | Integrated wingtip extensions for jet transport aircraft and other types of aircraft | |
| US7566029B2 (en) | Suspension for suspending a jet engine on an aircraft strut | |
| CN107416183B (en) | Spar connection structure of aircraft wing | |
| US20090146007A1 (en) | Methods and Systems for Attaching Aircraft Wings to Fuselages | |
| US20040251381A1 (en) | Front fastening device for aircraft engine | |
| US20040251380A1 (en) | Aircraft engine rear suspension with thrust recovery | |
| US20110089292A1 (en) | Aircraft joint | |
| US8444085B2 (en) | Support structure | |
| US20140217233A1 (en) | Aircraft propulsion assembly | |
| US9499274B2 (en) | Aircraft pylon and aircraft | |
| CN116691997A (en) | Heavy-load light aircraft | |
| CN208278310U (en) | A kind of modularization all-wing aircraft for unmanned plane | |
| US20210101689A1 (en) | Engine pylon for coupling a jet engine to a wing of an aircraft | |
| US8308105B2 (en) | Aircraft engine pylon attachment | |
| US11001369B2 (en) | Hybrid light weight rotorcraft hub trunnions | |
| CN209126952U (en) | A kind of close coupled type bending point biography rudder face transmission mechanism | |
| CN218258680U (en) | EVTOL aircraft wing connection structure | |
| CN215155591U (en) | Aircraft wing | |
| US11542025B2 (en) | Aircraft propulsion assembly comprising links of a front engine mount that are directly connected to a front transverse reinforcement of a primary structure of an aircraft pylon | |
| CN217945497U (en) | eVTOL aircraft horizontal tail |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090708 Termination date: 20111228 |