CN102180257B - Modular quickly-spliced unmanned aerial vehicle - Google Patents
Modular quickly-spliced unmanned aerial vehicle Download PDFInfo
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- CN102180257B CN102180257B CN 201110095531 CN201110095531A CN102180257B CN 102180257 B CN102180257 B CN 102180257B CN 201110095531 CN201110095531 CN 201110095531 CN 201110095531 A CN201110095531 A CN 201110095531A CN 102180257 B CN102180257 B CN 102180257B
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Abstract
The invention relates to a modular quickly-spliced unmanned aerial vehicle. The unmanned aerial vehicle comprises a left wing module, a hatch module, a vertical module, a body module, a parachute cabin module and a right wing module which are connected with one another through uniformly distributed latch devices, wherein each latch device consists of a latch seat and a locking column; and the latch devices are fixedly arranged on interconnected module materials respectively, and one latch device is a locking latch device. The main constituent parts of the unmanned aerial vehicle are subjected to modular manufacturing, so that smallest volume can be realized for packaging, vehicle-mounted space is increased, and transportation is facilitated; meanwhile, the modular parts are subjected to standardized manufacturing, so that easily damaged parts can be quickly supplemented, installed and used, can be quickly assembled and disassembled and accurately matched when a task is executed, and can be applied to the task immediately, and work efficiency is improved. The unmanned aerial vehicle has a simple integral structure and a scientific and reasonable design, perfectly solves a large number of problems of the conventional unmanned aerial vehicle, and lays a foundation for the development and utilization of the unmanned aerial vehicle.
Description
Technical field
The invention belongs to aviation field, relate to unmanned plane, especially a kind of Modular quick-splicing type unmanned aerial vehicle.
Background technology
China's SUAV (small unmanned aerial vehicle) industry is started late, in the design process one is with reference to external active service unmanned plane design aspect the equipment of profile, specification and lift-launch, fuselage and airfoil member still adopt the mode of captive joint, there is larger deficiency at aspects such as transportation, making, be embodied in: 1, when executing the task, can not realize rapid-assembling and dismounting, can not again drop into task at once; 2, the unmanned plane volume is larger, cause vehicle-mounted and install, the transportation difficulty; 3, can not be in time when a certain damage parts of unmanned plane, rapid interchangeable, can not effectively match during maintenance, can only rebuild.
In recent years, up-to-date technology and the new material development of China's composite material industry are very fast, because its material light weight, excellent in cushion effect, temperature deformation is little (" creep " that the difference of Yin Wendu causes), antiageing (serviceable bife prolongation), the characteristics such as corrosion prevention, thunder and lightning, static and various storeroom compatibility height are used very extensive in many industries.At present, China's unmanned plane can adopt advanced composite material, becomes possibility for the modular production of unmanned plane thus.
By retrieval, find one piece of open source literature relevant with present patent application: a kind of folding small-sized unmanned aerial vehicle (CN101712379A), it comprises: a blended wing-body; A pair of wing, be separately positioned on the left and right sides of described blended wing-body, each described wing and described blended wing-body junction are provided with one first fold mechanism, and described the first fold mechanism is set to make described wing the described wing that launches can be locked in deployed condition with respect to downward the folding also of described blended wing-body; An empennage; A shoe, the one end connects described empennage, the other end is connected with described blended wing-body by one second fold mechanism, and described the second fold mechanism is set to make described shoe the described shoe that launches can be locked in deployed condition with respect to downward the folding also of described blended wing-body.Described SUAV (small unmanned aerial vehicle) can be accommodated in the cuboid packing chest after its housing construction is folding, can utilize pneumatic acting device Automatic-expanding to state of flight to carry out the aerial mission such as aerial input, simultaneously the loadingunloading time shorter, convenient transportation.
Although above-mentioned patent application and present patent application purpose are basic identical, have more different with the technical scheme of present patent application.
Summary of the invention
The object of the invention is to overcome the deficiencies in the prior art part, and a kind of Modular quick-splicing type unmanned aerial vehicle is provided.
The present invention solves its technical matters and is achieved through the following technical solutions:
A kind of Modular quick-splicing type unmanned aerial vehicle, it is characterized in that: unmanned plane comprises port wing module, hatchcover module, vertical module, fuselage module, umbrella cabin module, starboard wing module, above-mentioned adjacent module all adopts uniform latching system to connect each other, latching system is made of snap close seat and lock, and corresponding being packed on the interconnective module material respectively, one of them latching system is the latching system of locking.
And described unmanned plane also comprises port wingtip module and right flank point module.
And, the lockhole locking of described lock front end and snap close seat, install with the permanent seat that is packed on the module material lock rear end.
And, the latching system of described locking reaches the lockhole of making by locking pressure handle, snap close seat, spring and consists of on the snap close seat, on the snap close seat stuck-module material, the locking pressure handle vertically is installed in the made orienting sleeve of snap close seat, its front end is made and is colluded the shape front end and be installed in the lockhole, colludes at lockhole right part and locking pressure handle and forms the lock in place hole between the shape front end.
And described latching system is made of snap close seat and lockhole.
And described lock is installed together by screw-threaded engagement and permanent seat.
Advantage of the present invention and good effect are:
1, this unmanned plane carries out the modular manufacturing with the main composition parts, can realize minimum volume packing, and vehicle-mounted space is increased, and has made things convenient for transportation.
2, this unmanned plane carries out the normalisation manufacturing with modular component, and consumable accessory can replenish fast thus, and Fast Installation is used, and can realize rapid-assembling and dismounting when executing the task, and cooperates accurately, can drop into task at once, increases work efficiency.
3, this unmanned plane is when a certain standard modular damage parts, directly quick-replaceable; Connect quick and precisely fast between the modular parts, intensity is high, and fastening design is rigorous, and is stable without diastema.
4, this unmanned plane integral structure is simple, and design science is reasonable, and perfection has overcome the problems that existing unmanned plane exists, for the development and use of unmanned plane are laid a good foundation.
Description of drawings
Fig. 1 is unmanned plane blast structural representation of the present invention;
Fig. 2 is each module connection structure confined explosion enlarged diagram of the present invention;
Fig. 3 is the perspective view (lock-out state) of the snap close seat of locking of the present invention;
Fig. 4 is the perspective view of the lockhole release position of Fig. 3;
Fig. 5 is the not snap close seat perspective view of locking of the present invention;
Fig. 6 is the mounting structure schematic diagram of lock of the present invention and wing.
The specific embodiment
The invention will be further described by specific embodiment below in conjunction with accompanying drawing, and following examples are descriptive, are not determinate, can not limit protection scope of the present invention with this.
A kind of Modular quick-splicing type unmanned aerial vehicle comprises eight kinds of modules and the latching system of installing therebetween.Wherein, eight kinds of modules are respectively: port wingtip module 1, port wing module 2, hatchcover module 3, vertical module 4, fuselage module 5, umbrella cabin module 7, starboard wing module 8 and right flank point module 9, the positional structure of above-mentioned module is prior art, does not repeat them here.
Above-mentioned module all adopts latching system to connect fast each other, arranging according to the area that connects between each module of latching system decided, in the present embodiment accompanying drawing, left and right wing module adopts three latching systems with being connected of fuselage, one of them snap close is with locking, the usefulness in order to locate, two lockings not in addition.
Concrete latching system structure is referring to Fig. 2,3,4,5,6.Latching system is made of snap close seat (12 and 15) and lock 17, the structure of lock is referring to Fig. 6, its front end is made the dead bolt shape, be shaped with latch recess, install by screw-threaded engagement mode and the bonding permanent seat 18 that is packed in (the present embodiment accompanying drawing is depicted as starboard wing) on the module material rear end, by screw-threaded engagement, can regulate the extension elongation of lock.
The latching system of locking is referring to Fig. 3,4, reaching the lockhole 13 of making by locking pressure handle 10, snap close seat 12, spring 11 on the snap close seat consists of, the snap close seat is fixed on each module by the mode such as gluing, the locking pressure handle vertically is installed in the made orienting sleeve of snap close seat (not having label), its front end is made and is colluded shape front end and can being installed in the lockhole, colludes formation lock in place hole 14 between the shape front end at lockhole right part and locking pressure handle.During use, as long as depress the locking pressure handle, it colludes the shape front end and retracts downwards, can discharge lockhole thus, and lock can insert in the lockhole, and it is empty that transverse shifting arrives lock in place; After unclamping the locking pressure handle, the restoring force effect of spring can make colludes the shape front end and protrudes upward, and locks thus lock.
The latching system of locking referring to Fig. 5, only is not to be made of snap close seat 15 and lockhole 16.
The latching system of installing between adjacent module will guarantee that one of them is that locking gets final product.
Among the present invention, latching system can adopt resin material to make.
Claims (4)
1. Modular quick-splicing type unmanned aerial vehicle, it is characterized in that: unmanned plane comprises port wing module, hatchcover module, vertical module, fuselage module, umbrella cabin module, starboard wing module, the fuselage module all adopts uniform latching system to be connected with other intermodules, latching system is made of snap close seat and lock, and corresponding being packed on the interconnective module material respectively, one of them latching system is the latching system of locking;
The latching system of described locking reaches the lockhole of making by locking pressure handle, snap close seat, spring and consists of on the snap close seat, the snap close seat is fixed on the module material, the locking pressure handle vertically is installed in the made orienting sleeve of snap close seat, locking pressure handle front end is made and is colluded the shape front end and be installed in the lockhole, colludes formation lock in place hole between the shape front end at lockhole right part and locking pressure handle.
2. Modular quick-splicing type unmanned aerial vehicle according to claim 1 is characterized in that: described unmanned plane also comprises port wingtip module and right flank point module.
3. Modular quick-splicing type unmanned aerial vehicle according to claim 1 is characterized in that: the lockhole locking of described lock front end and snap close seat, lock rear end and the permanent seat installation that is packed on the module material.
4. Modular quick-splicing type unmanned aerial vehicle according to claim 3, it is characterized in that: described lock is installed together by screw-threaded engagement and permanent seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110095531 CN102180257B (en) | 2011-04-15 | 2011-04-15 | Modular quickly-spliced unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110095531 CN102180257B (en) | 2011-04-15 | 2011-04-15 | Modular quickly-spliced unmanned aerial vehicle |
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| CN102180257A CN102180257A (en) | 2011-09-14 |
| CN102180257B true CN102180257B (en) | 2013-04-03 |
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| CN 201110095531 Expired - Fee Related CN102180257B (en) | 2011-04-15 | 2011-04-15 | Modular quickly-spliced unmanned aerial vehicle |
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Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8939810B1 (en) * | 2012-04-05 | 2015-01-27 | Noel F. Suknanan | Unitary model airplane component kit |
| CN102923296A (en) * | 2012-11-16 | 2013-02-13 | 中国航空工业集团公司西安飞机设计研究所 | Modularized unmanned aerial vehicle |
| CN105752334A (en) * | 2013-11-05 | 2016-07-13 | 湖北易瓦特科技股份有限公司 | Unmanned aircraft |
| CN106143886B (en) * | 2015-03-25 | 2018-11-06 | 北京天翼合创科技发展有限公司 | One kind can disintegrate formula multi-rotor aerocraft |
| CN105235904B (en) * | 2015-10-29 | 2017-03-08 | 北京航天科颐技术有限公司 | A kind of attachment means of target drone and spliced target drone |
| 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 |
| US10940932B2 (en) * | 2017-10-11 | 2021-03-09 | Wing Aviation Llc | Modular fuselage for unmanned aerial vehicle |
| CN108001685A (en) * | 2017-12-15 | 2018-05-08 | 佛山市神风航空科技有限公司 | A kind of unmanned plane for aerophotogrammetry |
| CN109367759A (en) * | 2018-10-17 | 2019-02-22 | 江西洪都航空工业集团有限责任公司 | A kind of modularization aircraft |
| CN211618061U (en) * | 2019-09-05 | 2020-10-02 | 深圳市道通智能航空技术有限公司 | Wing disassembly assembly and aircraft |
| CN110641666A (en) * | 2019-09-21 | 2020-01-03 | 天津大学 | Large-scale heavy load underwater vehicle of two buoyancy hybrid drive |
| CN112520011A (en) * | 2020-12-14 | 2021-03-19 | 中宇航通(北京)航空集团有限公司 | Quick-release quick-lock structure and method and unmanned aerial vehicle |
| CN114572417A (en) * | 2022-03-23 | 2022-06-03 | 沃飞长空科技(成都)有限公司 | Quick locking device and aircraft comprising same |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1435355A (en) * | 2002-12-04 | 2003-08-13 | 韩国庆 | Light buzzard-type wing jet plane and its use, and aircaft carrier using it as ship plane |
| RU2321523C1 (en) * | 2006-08-15 | 2008-04-10 | Федеральное государственное унитарное предприятие "Научно-производственное объединение им. С.А. Лавочкина" | Small-sized unmanned flying vehicle |
| CN201357945Y (en) * | 2009-03-16 | 2009-12-09 | 孙炜 | Modularized multifunctional unmanned aerial vehicle |
| CN201989945U (en) * | 2011-04-15 | 2011-09-28 | 天津全华时代航天科技发展有限公司 | Modular quick-splicing type unmanned aerial vehicle |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7237750B2 (en) * | 2004-10-29 | 2007-07-03 | L3 Communications | Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV) |
| WO2011002331A1 (en) * | 2009-07-02 | 2011-01-06 | Открытое Акционерное Общество "Научно-Производственная Корпорация "Иркут" | Small unmanned aircraft system |
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2011
- 2011-04-15 CN CN 201110095531 patent/CN102180257B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1435355A (en) * | 2002-12-04 | 2003-08-13 | 韩国庆 | Light buzzard-type wing jet plane and its use, and aircaft carrier using it as ship plane |
| RU2321523C1 (en) * | 2006-08-15 | 2008-04-10 | Федеральное государственное унитарное предприятие "Научно-производственное объединение им. С.А. Лавочкина" | Small-sized unmanned flying vehicle |
| CN201357945Y (en) * | 2009-03-16 | 2009-12-09 | 孙炜 | Modularized multifunctional unmanned aerial vehicle |
| CN201989945U (en) * | 2011-04-15 | 2011-09-28 | 天津全华时代航天科技发展有限公司 | Modular quick-splicing type unmanned aerial vehicle |
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| CN102180257A (en) | 2011-09-14 |
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Denomination of invention: Modular quickly-spliced unmanned aerial vehicle Effective date of registration: 20130731 Granted publication date: 20130403 Pledgee: Pudong Shanghai Development Bank Limited by Share Ltd. Tianjin branch Pledgor: CHINA-TIMES AEROSPACE TECHNOLOGY Co.,Ltd. Registration number: 2013120000021 |
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Date of cancellation: 20160422 Granted publication date: 20130403 Pledgee: Pudong Shanghai Development Bank Limited by Share Ltd. Tianjin branch Pledgor: CHINA-TIMES AEROSPACE TECHNOLOGY Co.,Ltd. Registration number: 2013120000021 |
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