CN101214853A - 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
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- CN101214853A CN101214853A CNA2007103046952A CN200710304695A CN101214853A CN 101214853 A CN101214853 A CN 101214853A CN A2007103046952 A CNA2007103046952 A CN A2007103046952A CN 200710304695 A CN200710304695 A CN 200710304695A CN 101214853 A CN101214853 A CN 101214853A
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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
4 a pectination joint connecting bore 4b pectination joint connecting bores
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 (5)
1. outer wing connection structure in the unmanned plane 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.
2. outer wing connection structure in a kind of unmanned plane according to claim 1 is characterized in that: described outer wing root pectination joint is the U shape parts of a two ends symmetry, and its two ends have a hole, and the side has a bolt containing slot.
3. outer wing connection structure in a kind of unmanned plane according to claim 1 is characterized in that: described wing centre section end rib pectination joint is the U shape parts of a two ends symmetry, and its two ends have a hole, and the side has a nut containing slot.
4. according to outer wing connection structure in claim 1, the 2 or 3 described a kind of unmanned planes, it is characterized in that: 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 is connected with nut.
5. outer wing connection structure in a kind of unmanned plane according to claim 1 is characterized in that: 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.
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 true CN101214853A (en) | 2008-07-09 |
| CN100509556C CN100509556C (en) | 2009-07-08 |
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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 |
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| CN (1) | CN100509556C (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103068674A (en) * | 2010-04-12 | 2013-04-24 | 空中客车运作有限责任公司 | Fixed wing of an aircraft |
| CN105270603A (en) * | 2015-10-27 | 2016-01-27 | 镇江顺宇飞行器有限公司 | Unmanned fixed-wing aircraft with large aspect ratio |
| US9422049B2 (en) | 2011-03-28 | 2016-08-23 | Airbus Operations Limited | Joint |
| CN106005365A (en) * | 2016-08-06 | 2016-10-12 | 北京耐威智能科技有限公司 | Built-in connecting assembly, external connecting assembly, connecting device, wing and airplane |
| CN106114816A (en) * | 2016-07-23 | 2016-11-16 | 北京耐威智能科技有限公司 | A kind of wing attachment means, wing and aircraft |
| CN106275376A (en) * | 2016-08-31 | 2017-01-04 | 北京奇正数元科技股份有限公司 | A kind of center framework of small-sized unmanned plane |
| CN106335651A (en) * | 2015-07-07 | 2017-01-18 | 波音公司 | Alignment fixture and method for aligning first component and second component |
| EP3248863A1 (en) * | 2016-05-24 | 2017-11-29 | Airbus Operations Limited | Winglet |
| US10272990B2 (en) | 2014-09-30 | 2019-04-30 | Commercial Aircraft Corporation Of China, Ltd | Aircraft wing assembly |
| 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 |
| CN111895905A (en) * | 2020-05-27 | 2020-11-06 | 中国计量大学 | Error compensation method for hexagonal axis straightness detection system |
| CN113733595A (en) * | 2021-08-30 | 2021-12-03 | 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 (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106218862A (en) * | 2010-04-12 | 2016-12-14 | 空中客车运作有限责任公司 | The fixed-wing of airborne vehicle |
| US9056671B2 (en) | 2010-04-12 | 2015-06-16 | Airbus Operations Gmbh | Fixed wing of an aircraft |
| CN106218862B (en) * | 2010-04-12 | 2018-12-11 | 空中客车运作有限责任公司 | A kind of wing configuring aircraft is used for the method and its wing structure of concrete application |
| CN103068674A (en) * | 2010-04-12 | 2013-04-24 | 空中客车运作有限责任公司 | Fixed wing of an aircraft |
| US9555874B2 (en) | 2010-04-12 | 2017-01-31 | Airbus Operations Gmbh | Fixed wing of an aircraft |
| US9701392B2 (en) | 2011-03-28 | 2017-07-11 | Airbus Operations Limited | Joint |
| US9422049B2 (en) | 2011-03-28 | 2016-08-23 | Airbus Operations Limited | Joint |
| US10272990B2 (en) | 2014-09-30 | 2019-04-30 | Commercial Aircraft Corporation Of China, Ltd | Aircraft wing assembly |
| CN106335651A (en) * | 2015-07-07 | 2017-01-18 | 波音公司 | Alignment fixture and method for aligning first component and second component |
| CN106335651B (en) * | 2015-07-07 | 2018-12-11 | 波音公司 | Alignment and fixation part and method for being directed at the first component with second component |
| CN105270603A (en) * | 2015-10-27 | 2016-01-27 | 镇江顺宇飞行器有限公司 | Unmanned fixed-wing aircraft with large aspect ratio |
| US10597145B2 (en) | 2016-05-24 | 2020-03-24 | Airbus Operations Limited | Winglet |
| EP3248863A1 (en) * | 2016-05-24 | 2017-11-29 | Airbus Operations Limited | Winglet |
| CN107444613A (en) * | 2016-05-24 | 2017-12-08 | 空中客车英国运营有限责任公司 | 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 |
| CN106114816A (en) * | 2016-07-23 | 2016-11-16 | 北京耐威智能科技有限公司 | A kind of wing attachment means, wing and aircraft |
| CN106005365A (en) * | 2016-08-06 | 2016-10-12 | 北京耐威智能科技有限公司 | Built-in connecting assembly, external connecting assembly, connecting device, wing and airplane |
| 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 |
| CN106275376A (en) * | 2016-08-31 | 2017-01-04 | 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 |
| CN111895905A (en) * | 2020-05-27 | 2020-11-06 | 中国计量大学 | Error compensation method for hexagonal axis straightness detection system |
| CN113733595A (en) * | 2021-08-30 | 2021-12-03 | 北京航空航天大学 | Processing method of fully-wrapped composite material foam sandwich wing rib |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100509556C (en) | 2009-07-08 |
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Granted publication date: 20090708 Termination date: 20111228 |