CN105882936A - Rapid connector for middle wing and outer wing of small portable unmanned aerial vehicle - Google Patents
Rapid connector for middle wing and outer wing of small portable unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105882936A CN105882936A CN201410857422.0A CN201410857422A CN105882936A CN 105882936 A CN105882936 A CN 105882936A CN 201410857422 A CN201410857422 A CN 201410857422A CN 105882936 A CN105882936 A CN 105882936A
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- aerial vehicle
- wing
- 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.)
- Pending
Links
Abstract
The invention relates to a connecting structure design for rapid assembling and disassembling of a middle wing and an outer wing of a small unmanned aerial vehicle. An unmanned aerial vehicle structure made under the guidance of the scheme has the advantages of being convenient to assemble and disassemble, high in environmental adaptability and good in man-machine effect. With the connecting structure design, a lot of assembling and disassembling time can be easily saved when a small unmanned aerial vehicle system is used in battles, and the efficiency of the small unmanned aerial vehicle system can be exerted to the maximum when the small unmanned aerial vehicle system is used in battles. Based on improvement of the manufacturing technological level, the rapid insertion connection design concept is adopted for designing the assembling and disassembling mode of unmanned aerial vehicle structural members, the actual operating experience of operating personnel serves as the design core, the rapid spreading and retracting performance of the unmanned aerial vehicle can be easily improved, the unmanned aerial vehicle can adapt to various working conditions and environments, and the efficiency of the unmanned aerial vehicle system can be fully exerted.
Description
Technical field
The present invention relates to a kind of SUAV wing centre section and outer wing Fast Installation, the attachment structure design of dismounting.With the program for instructing, the feature that the unmanned plane structure completed has installation and removal simple operation, environmental suitability is strong, function expansibility is strong, ergonomic is good, be conducive to Mini-Unmanned Aerial Vehicles to use saving a large amount of assembly and disassembly times in wartime, make Mini-Unmanned Aerial Vehicles operational exertion usefulness obtain and play greatly.
Technical background
The development of unmanned air vehicle technique is an important directions of World Airways industrial development, in addition to the swift and violent lifting of aircraft flight performance and load information post-processing technology level, Flight Vehicle Structure installation reliability, stability, the convenience connected between functional module structure and reliability become the critical function performance indications determining that assessment UAS aircraft performance is good and bad.The use field of UAS is increasingly broader, applied environment becomes increasingly complex, and manipulator proposes requirements at the higher level to aircraft handling.
Traditional each functional module of Mini-Unmanned Aerial Vehicles aircraft is installed and is relied on the screw standard component of different size model or locking device to be fixed.Therefore, conventional small UAS aircraft has the disadvantage in that assembling and dismounting are time-consuming long, is unfavorable for that wartime uses；Maintenance procedures is complicated, need to be equipped with specific purpose tool；The number of fitting parts disassembled is numerous, is difficult to keeping；Maintenance and use cost are high.It is difficult to meet growing military digitizing equipment and uses demand.
By contrast it appeared that, rely on the lifting of manufacturing technology level, use quick grafting design concept that unmanned plane structural member assembly and disassembly mode is designed, experience as design core using the practical operation of operating personnel, be conducive to unmanned plane rapid deployment and remove the lifting receiving performance, can adapt to various work condition environment, give full play to the usefulness of UAS.
Summary of the invention
Ripe structure processing technology is relied on to simplify unmanned plane wing centre section and outer wing attended operation operation.Use for reference ripe designing technique, use physics plugging mode to ensure the use requirement of the quick assembly and disassembly of aircraft.The agility of design prominent structure connection and reliability.
Technical scheme
According to Mini-Unmanned Aerial Vehicles aircraft platforms actual operation requirements, the connector being designed with suitable tolerance fit connects wing centre section and outer wing, and as main load parts.Utilize the compress variation mechanism that is locked as connector of sealing ring.
The effect that the present invention produces
Rely on the present invention, manipulator is without using instrument, by single stepping, wing centre section is reliably connected with outer wing together with.Equipment is set up and removes between the time receiving within 5～8 minutes, being reduced to 1 minute.Embody agility and the operability of UAS.
Detailed description of the invention
The present invention is mainly achieved by following proposal: in accompanying drawing 1, part 1 is connector before outer wing, and part 2 is outer wing connector, and part 3 is sealing ring, and part 4 is plug connector before wing centre section, and part 5 is connector after wing centre section.Wherein part 1 and part 4 are matched in clearance, and the primary load bearing parts connected as wing centre section, outer wing.When after part 1 insert 4, part 3 because of under free state diameter bigger than part 4 internal diameter, therefore suffer from compression, by the clearance seal of part 1 with part 4.Before outer wing in the middle of plug connector and the aperture of the side opening air that is contemplated to be formed in confined space by part 1, part 3, part 4 is discharged, in order to part 1 smoothly in insert 4, can be shown in accompanying drawing 2.And after part 3 compression, producing certain frictional force with part 4, preventing member 3 is deviate from.And the connection of part 2 and part 5 mainly prevents from twisting between wing centre section and outer wing.In order to prevent location, part 5 is designed as long arc hole, sees accompanying drawing 3.
The wing centre section of present invention design, outer wing plug connector, can be that metal, composite etc. various meet intensity, the material of rigidity requirement is made.The size of the fit tolerance of the internal diameter depending mainly on the size of plug connector of sealing ring and two plug connectors.Form in above-described embodiment is not limited to for the form of plug connector on wing centre section, outer wing.The plug connector of the two is exchanged, it is also possible to reach identical effect.
Accompanying drawing explanation
Fig. 1 is wing centre section and outer wing connection diagram
Fig. 2 is plug connector schematic diagram before outer wing
Fig. 3 is connector schematic diagram after wing centre section.
Claims (3)
1. the present invention relates to a kind of SUAV wing centre section and outer wing Fast Installation,
The attachment structure design of dismounting.It is characterized in that completing with the program for instructing
Unmanned plane structure have that installation and removal are convenient, environmental suitability merit strong, man-machine
The feature imitated.The present invention is conducive to saving during Mini-Unmanned Aerial Vehicles operational exertion
Mount and dismount the time in a large number, make Mini-Unmanned Aerial Vehicles usefulness when operational exertion
Obtain and farthest play.
Wing centre section the most according to claim 1 and outer wing Fast Installation, dismounting
Attachment structure, it is characterised in that by structure connect, retaining mechanism carried out integrated
Design, reaches the requirement of wing centre section and outer wing fast assembling-disassembling.
3. according to the wing centre section described in claim 1,2 and outer wing Fast Installation, tear open
The attachment structure unloaded, it is characterised in that: it is designed with patching of suitable tolerance fit
Part connects wing centre section and outer wing, and as main load parts.Utilize the pressure of sealing ring
Compression deformation amount as the mechanism that is locked of connector, beneficially unmanned plane launch and
Remove receipts performance boost.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410857422.0A CN105882936A (en) | 2014-12-31 | 2014-12-31 | Rapid connector for middle wing and outer wing of small portable unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410857422.0A CN105882936A (en) | 2014-12-31 | 2014-12-31 | Rapid connector for middle wing and outer wing of small portable unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105882936A true CN105882936A (en) | 2016-08-24 |
Family
ID=56700880
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410857422.0A Pending CN105882936A (en) | 2014-12-31 | 2014-12-31 | Rapid connector for middle wing and outer wing of small portable unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105882936A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019232941A1 (en) * | 2018-06-06 | 2019-12-12 | 东汉太阳能无人机技术有限公司 | Wing of unmanned aerial vehicle and unmanned aerial vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2737444Y (en) * | 2004-06-01 | 2005-11-02 | 杨良杰 | Assembling model airplane |
| CN2866863Y (en) * | 2005-11-11 | 2007-02-07 | 潍柴动力股份有限公司 | Diesel engine cylinder head and oil feed pipe connecting apparatus |
| US7237750B2 (en) * | 2004-10-29 | 2007-07-03 | L3 Communications | Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV) |
| CN201085931Y (en) * | 2007-08-03 | 2008-07-16 | 西安大地测绘工程有限责任公司 | Insertion airfoil of miniature pilotless plane |
| CN101816837A (en) * | 2010-05-04 | 2010-09-01 | 张立岩 | Conveniently-disassembled model plane |
| CN102730182A (en) * | 2012-06-20 | 2012-10-17 | 中国航天时代电子公司 | Unmanned aerial vehicle wing and body connection apparatus |
-
2014
- 2014-12-31 CN CN201410857422.0A patent/CN105882936A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2737444Y (en) * | 2004-06-01 | 2005-11-02 | 杨良杰 | Assembling model airplane |
| US7237750B2 (en) * | 2004-10-29 | 2007-07-03 | L3 Communications | Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV) |
| CN2866863Y (en) * | 2005-11-11 | 2007-02-07 | 潍柴动力股份有限公司 | Diesel engine cylinder head and oil feed pipe connecting apparatus |
| CN201085931Y (en) * | 2007-08-03 | 2008-07-16 | 西安大地测绘工程有限责任公司 | Insertion airfoil of miniature pilotless plane |
| CN101816837A (en) * | 2010-05-04 | 2010-09-01 | 张立岩 | Conveniently-disassembled model plane |
| CN102730182A (en) * | 2012-06-20 | 2012-10-17 | 中国航天时代电子公司 | Unmanned aerial vehicle wing and body connection apparatus |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019232941A1 (en) * | 2018-06-06 | 2019-12-12 | 东汉太阳能无人机技术有限公司 | Wing of unmanned aerial vehicle and unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204776056U (en) | Cloud platform quick assembly disassembly device | |
| CN202322102U (en) | Flange connection structure and tower crane with same | |
| CN108106503B (en) | A kind of folded surface locking mechanism in place | |
| CN202597687U (en) | Spring self-locking bolt plug | |
| CN108138586B (en) | Engine crankcase support apparatus and interface | |
| US9895932B2 (en) | Tire tube | |
| CN202510578U (en) | Novel diaphragm component structure of coupler | |
| CN105882936A (en) | Rapid connector for middle wing and outer wing of small portable unmanned aerial vehicle | |
| CN102060100B (en) | Aircraft fuselage-wing connecting mechanism | |
| CN105882941A (en) | Rapid connector for vertical tail and horizontal tail of small portable unmanned aerial vehicle | |
| CN106523505B (en) | A kind of anti-loose fastening assembly of automatic spacing | |
| CN206087348U (en) | Cloud platform fast dismantle device | |
| CN105882988A (en) | Quick dismounting and mounting design scheme for load and body of small unmanned aerial vehicle | |
| EP4220869A1 (en) | A plug-in assembly structure and an unmanned aerial vehicle with composite wing | |
| CN206590104U (en) | The device for quickly disassembling of unmanned airplane empennage | |
| CN202953167U (en) | Unmanned aerial vehicle with wing inserted fixing device | |
| CN105730679A (en) | Quick connector for vehicle body and tail boom of portable small unmanned aerial vehicle | |
| CN110380275B (en) | Connecting nut assembly capable of being taken out and disassembled | |
| CN206539584U (en) | A kind of anti-loose fastening assembly of automatic spacing | |
| CN205633029U (en) | Fixed rotor unmanned aerial vehicle overall structure convenient to equipment | |
| CN205429608U (en) | Novel clamp is fixed to cable | |
| CN104120932B (en) | A kind of screw thread quick-detachable lock | |
| CN204330296U (en) | A kind of sealing shroud performance test fixture of constant velocity cardan joint assembly | |
| CN203779450U (en) | Self-dismounted cover plate structure | |
| CN110104224B (en) | Plugging assembly, fairing and aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160824 |