CN205131625U - Small -size portable all -wing aircraft overall arrangement unmanned aerial vehicle - Google Patents
Small -size portable all -wing aircraft overall arrangement unmanned aerial vehicle Download PDFInfo
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- CN205131625U CN205131625U CN201520889635.1U CN201520889635U CN205131625U CN 205131625 U CN205131625 U CN 205131625U CN 201520889635 U CN201520889635 U CN 201520889635U CN 205131625 U CN205131625 U CN 205131625U
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- fuselage
- unmanned plane
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- auricle
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Abstract
The utility model discloses a small -size portable all -wing aircraft overall arrangement unmanned aerial vehicle, including the fuselage with locate the wing of fuselage both sides, be wing body fusion structure between fuselage and the wing, the screw has been arranged to the rear end of fuselage, the wing passes through wing body locking mechanism can be dismantled with the fuselage and be connected, unmanned aerial vehicle's flight components and parts all set up on the fuselage. The utility model has the advantages of can realize nimble dismouting, portable, have good flight efficiency again, can bring splendid flight to experience for the user.
Description
Technical field
The utility model is mainly concerned with unmanned plane field, is specifically related to a kind of small portable Flying-wing unmanned plane.
Background technology
Conventional civilian unmanned plane, more such as aerial mapping, takes photo by plane, and the unmanned plane of pipeline patrol all have employed the normal arrangement of larger fuselage.So, airframe is longer, and needs tailplane and vertical tail, and equipment box goes to place unmanned plane with regard to needing larger space, greatly reduces the portability of aircraft; Adopt the unmanned plane of normal arrangement, pneumatic efficiency is lower than Flying-wing, and therefore the cruise duration of Flying-wing's unmanned plane, comparatively normal arrangement unmanned plane was more of a specified duration, and voyage is also farther, can embody stronger duration performance in actual job.
" all-wing aircraft (FlyingWing) " layout is a kind of aerodynamic configuration of aircraft mode being different from Conventional pneumatic layout.All-wing aircraft does not have conventional fuselage and empennage, and its fuselage and wing combine together, are often called BWB(Blended-wingbody) blended wing-body.Some all-wing aircraft fuselages still retain, but certainly do not have empennage.Germany " Wal is many. and water is graceful " brother is considered to the earliest all-wing aircraft designer.The stealthy strategic bomber B2 of the U.S. is exactly the Flying-wing adopted.The aerodynamic efficiency of this layout of all-wing aircraft is very high, because airframe structure is all wing, all can be used for producing lift, and farthest reduce flight resistance, its reflection of radar waves simultaneously is also smaller, and Stealth Fighter is given prominence to.
There is following technical matters in existing civilian unmanned plane:
(1) have employed normal arrangement, the span is very long, not portable, and unmanned plane packing chest needs very large space just can load a whole set of aircraft, brings a lot of inconvenience to user.
(2) UAV aerodynamic layout is unreasonable, and can not obtain good flight usefulness, user's flight experience is not good.
(3) unmanned plane structure design is unreasonable, installs numerous and diverse, and not easily dismounting flexibly, not easily carries.
Utility model content
The technical matters that the utility model solves is: for prior art Problems existing, there is provided one can realize flexible dismounting, be easy to carry, there is again usefulness of well flying, the small portable Flying-wing unmanned plane of splendid flight experience can be brought to user.
For solving the problems of the technologies described above, the utility model by the following technical solutions:
A kind of small portable Flying-wing unmanned plane, comprise fuselage and the wing being located at fuselage both sides, it is blended wing-body body structure between described fuselage and wing, the rear end of described fuselage is furnished with screw propeller, described wing is removably connected by wing body catch gear and fuselage, and the flight components and parts of described unmanned plane are all arranged on fuselage.
As further improvement of the utility model, described wing body catch gear comprises is located at main connecting pin on wing sidewall and secondary connecting pin, and on the sidewall of described fuselage, correspondence is provided with main connecting pin bores portion and secondary connecting pin bores portion.
As further improvement of the utility model, described main connecting pin comprises pin rod and is located at the spherical plunger of pin rod leading section, and described main connecting pin bores portion comprises the deck coordinated with spherical plunger.
As further improvement of the utility model, described deck has the hollowed out spherical hole coordinated with spherical plunger, and described spherical plunger is clamp-oned in hollowed out spherical hole fixing to be blocked by deck.
As further improvement of the utility model, described wing body catch gear also comprises auricle fixation kit, described auricle fixation kit comprises the spill auricle seat be located on fuselage and the auricle be located on wing, salient is provided with in described spill auricle seat, described auricle is provided with the through hole coordinated with salient, when described auricle inserts in spill auricle seat, described salient snaps in through hole fixing to be blocked by auricle.
As further improvement of the utility model, described main connecting pin and secondary connecting pin are made by carbon fibre material, and the length of described main connecting pin is greater than the length of secondary connecting pin and auricle fixation kit.
As further improvement of the utility model, the front portion of described fuselage is towards projection, described fuselage interior is from first to last furnished with GPS sensor module, battery component, control assembly and photomoduel successively, a digital rudder controller assembly is respectively provided with about the rear portion of photomoduel, the rear portion of described digital rudder controller assembly is provided with electricity tune cabin and for driving the drive motor of screw propeller, described photomoduel is arranged in the middle part of fuselage.
As further improvement of the utility model, the end face correspondence of described fuselage is provided with detachable battery hatchcover and phase cabin cover.
As further improvement of the utility model, the top of described fuselage is provided with antenna and pitot.
As further improvement of the utility model, described fuselage and wing all adopt lightweighting materials to make.
Compared with prior art, the utility model has the advantage of:
(1) small portable Flying-wing of the present utility model unmanned plane, by being optimized design to the version of unmanned plane and aerodynamic arrangement, adopt the Flying-wing that structure is simpler, pneumatic efficiency is higher, make unmanned plane have good aerodynamic arrangement, can usefulness of well flying be realized; Meanwhile, wing and fuselage can realize dismounting very fast, easily, and the entirety being easy to unmanned plane is carried and assembly operation, enormously simplify the operating process of unmanned plane.The utility model had and can realize flexible dismounting, be easy to carry, there is again usefulness of well flying, the advantage of splendid flight experience can be brought to user.
(2) small portable Flying-wing of the present utility model unmanned plane, by carrying out multinomial optimal design and specific scientific offering to fuselage device arrangements, further increase the flight usefulness of unmanned plane, simultaneously by adopting lightweighting materials to make, aircraft is made to be easy to operation, and without the need to using other to let fly away and regenerative apparatus, bring better flight experience to user further.
Accompanying drawing explanation
Fig. 1 is the spatial structure principle schematic of the utility model small portable Flying-wing unmanned plane.
Fig. 2 be the utility model small portable Flying-wing unmanned plane look up structural principle schematic diagram.
Fig. 3 is the side-looking structural principle schematic diagram of the utility model small portable Flying-wing unmanned aerial vehicle body.
Structural principle schematic diagram when Fig. 4 is the unmanned plane dismounting of the utility model small portable Flying-wing.
Structural principle schematic diagram when Fig. 5 is the unmanned plane auricle fixation kit separation of the utility model small portable Flying-wing.
Structural principle schematic diagram when Fig. 6 is the unmanned plane auricle fixation kit combination of the utility model small portable Flying-wing.
Structural principle schematic diagram when Fig. 7 is the utility model small portable Flying-wing unmanned plane connecting pin components apart.
Structural principle schematic diagram when Fig. 8 is the unmanned plane connecting pin assembly combination of the utility model small portable Flying-wing.
Fig. 9 is the major elements schematic diagram of the utility model small portable Flying-wing unmanned aerial vehicle body components and parts.
Marginal data:
1, fuselage; 10, electricity adjusts cabin; 11, drive motor; 12, battery hatch; 13, phase cabin cover; 14, antenna; 15, pitot; 2, wing; 3, screw propeller; 4, wing body catch gear; 41, main connecting pin; 411, pin rod; 412, spherical plunger; 42, secondary connecting pin; 43, main connecting pin bores portion; 431, deck; 44, secondary connecting pin bores portion; 45, auricle fixation kit; 451, spill auricle seat; 452, auricle; 5, GPS sensor module; 6, battery component; 7, control assembly; 8, photomoduel; 9, digital rudder controller assembly.
Detailed description of the invention
Below in conjunction with specific embodiments and the drawings, the utility model is described in further detail.
As shown in Figures 1 to 9, the utility model provides a kind of small portable Flying-wing unmanned plane, and comprise fuselage 1 and the wing 2 being located at fuselage 1 both sides, be blended wing-body body structure between fuselage 1 and wing 2, the rear end of fuselage 1 is furnished with screw propeller 3.In the present embodiment, the shape of fuselage 1 is preferably revised a little by the lines of NACA2412 aerofoil profile and is drawn, relative camber gets 1.4 ~ 1.8%, and relative thickness gets 7 ~ 9%, and wing 2 leading edge sweep is preferably 30o, and wing 2 trailing sweep is preferably 20o.Make this unmanned plane have good aerodynamic arrangement by this flying wing type design, can usefulness of well flying be realized.Meanwhile, for ease of carrying, the wing 2 of unmanned plane is removably connected by wing body catch gear 4 and fuselage 1, and the flight components and parts of unmanned plane are all arranged on fuselage 1.When needs carry, only wing 2 need be separated with fuselage 1, make the space taken of unmanned plane very little, be convenient to store, be convenient to carrying; When it is desired to be used, wing body catch gear 4 is utilized fuselage 1 and wing 2 to be carried out combining.Simultaneously, because flight components and parts are all arranged on fuselage 1 by unmanned plane of the present utility model, make on wing 2 without any flight components and parts, when fuselage 1 and wing 2 carry out splitting or combining by needs, due to the complicated dismounting problem without the need to considering components and parts, operating personal can be dismantled or install unmanned plane by fast speed, and whole process is fast very convenient, can carry out carrying or place in operation by fast speed.Just by above design, the utility model had and can realize flexible dismounting, be easy to carry, there is again usefulness of well flying, the advantage of splendid flight experience can be brought to user.
As shown in Fig. 4 to Fig. 8, further, in the preferred embodiment, wing body catch gear 4 comprises is located at main connecting pin 41 on wing 2 sidewall and secondary connecting pin 42, and on the sidewall of fuselage 1, correspondence is provided with main connecting pin bores portion 43 and secondary connecting pin bores portion 44.Main connecting pin 41 comprises pin rod 411 and is located at the spherical plunger 412 of pin rod 411 leading section, main connecting pin bores portion 43 comprises the deck 431 coordinated with spherical plunger 412, deck 431 has the hollowed out spherical hole coordinated with spherical plunger 412, and spherical plunger 412 is clamp-oned in hollowed out spherical hole to be blocked fixing by deck 431; During installation, only need clamp-on in deck 431 by spherical plunger 412, spherical plunger 412 will be blocked fixing by squeezed swollen deck 431; Firmly outwards extract when need be separated.Auricle fixation kit 45 is provided with between major-minor connecting pin assembly, auricle fixation kit 45 comprises the spill auricle seat 451 be located on fuselage 1 and the auricle 452 be located on wing 2, salient is provided with in spill auricle seat 451, auricle 452 is provided with the through hole coordinated with salient, when auricle 452 inserts in spill auricle seat 451, salient snaps in through hole to block fixing by auricle 452.The fixing design of auricle is added by this connecting pin, make to connect very firm between fuselage 1 and wing 2, this installation is simultaneously inserted, is separated the connection mode of extracting, also there is convenient, fast, labour-saving advantage, be conducive to rapid-assembling and the dismounting of unmanned plane, substantially reduce the setup time before unmanned plane operation, improve the service efficiency of unmanned plane, improve the portability of unmanned plane in carrying assembling process.
Further, in the preferred embodiment, main connecting pin 41 and secondary connecting pin 42 are made by carbon fibre material, and the length of main connecting pin 41 is greater than the length of secondary connecting pin 42 and auricle fixation kit 45.Carbon fiber pipe has large, the lightweight advantage of hardness, makes the weight alleviating unmanned plane while ensure that stable connection.Simultaneously, by arranging the longer main connecting pin 41 of length, when mounted, first main connecting pin 41 longer for length is inserted, to make between fuselage 1 and wing 2 first to set up preliminary connection, then with main connecting pin 41 very convenient, fast for bench mark gets final product by aiming between other secondary connecting pin 42, auricle fixation kit 45 and connecting, solve the problem of not easily aiming between multiple fabricated section, improve and install fixing speed, whole process is fast very convenient.
As shown in Figure 9, further, in the preferred embodiment, the front portion of fuselage 1 is towards projection, fuselage 1 inside is from first to last furnished with GPS sensor module 5, battery component 6, control assembly 7, photomoduel 8 successively, about the rear portion of photomoduel 8, be respectively provided with a digital rudder controller assembly 9, the rear portion of digital rudder controller assembly 9 is provided with electricity tune cabin 10 and for driving the drive motor 11 of screw propeller 3, photomoduel 8 is arranged in the middle part of fuselage 1.Components and parts due to unmanned plane are all arranged on fuselage 1, in order to obtain optimum aerodynamic arrangement, improve the flight usefulness of unmanned plane, the utility model adopts above-mentioned compact device arrangements design in fuselage 1 inside, under the condition considering gravity allocation, all components and parts are arranged within this aerodynamic configuration optimized, so both meet the loading of equipment, also achieve the trim of unmanned plane center of gravity, the aerodynamic configuration of unmanned plane also obtains actv. optimization simultaneously.The reason of above-mentioned compact device arrangements design is as follows:
Due to the pattern taking rear end screw propeller 3 to drive, electricity adjusts cabin 10 and the most afterbody for driving drive motor 11 position of screw propeller 3 to be located at fuselage 1; Electricity adjusts cabin 10 to be connected by electric wire with drive motor 11, as far as possible close to the weight that can reduce wire rod; Photomoduel 8 and battery component 6 are two parts the heaviest in fuselage 1, and counterweight adjustment is main by these two parts, and photomoduel 8 considers that the convenience of taking pictures preferably is placed on aircraft midway location, therefore battery component 6 can only be placed on head position; After these parts arrange, remaining position is just as the putting position of other parts.Complete center of gravity trim after putting, center of gravity is in the camera near the heart, and before aerodynamic center a bit, complete machine is the state of static-stability.
Further, in the preferred embodiment, the top of fuselage 1 is provided with antenna 14 and pitot 15.The top that antenna 14 and pitot 15 are located at fuselage 1 is convenient to not cause damage to antenna 14 and pitot 15 when unmanned plane lands.The end face correspondence of fuselage 1 is provided with detachable battery hatchcover 61 and phase cabin cover 81.Detachable battery hatchcover 61 is convenient to carry out replacing charging to battery component 6 or directly charge; Detouchable phase cabin cover 81 is convenient to photomoduel 8 to take out carry out changing or obtaining photographic information.
Further, in the preferred embodiment, fuselage 1 and wing 2 all adopt lightweighting materials to make.In the present embodiment, fuselage 1 and wing 2 all adopt good springiness, lightweight EPP foamed materials is made (in other embodiments, also other lightweighting materials can be adopted to make), substantially reduce size and the weight of unmanned plane, the span of wing 2 is designed to 0.98 ~ 1.05 meter by the present embodiment simultaneously, maximum take-off weight is designed to 700g ~ 750g, coordinates the blended wing-body Flying-wing of unique optimization, makes unmanned plane airborne period of the present utility model can reach 30 ~ 45 minutes.Meanwhile, due to lightweight, wing load is little, and hand can be adopted to throw the mode flown, and eliminates complicated launching cradle device, allows user use more convenient.When needs land, unmanned plane according to predetermined course line under the control of flight control system, can wipe ground landing, eliminates parachuting or the catch net system of unmanned plane recovery, is conducive to user more efficient, safer, reclaims unmanned plane more easily.
Below be only preferred implementation of the present utility model, protection domain of the present utility model be not only confined to above-described embodiment, all technical schemes belonged under the utility model thinking all belong to protection domain of the present utility model.It should be pointed out that for those skilled in the art, not departing from the some improvements and modifications under the utility model principle prerequisite, protection domain of the present utility model should be considered as.
Claims (10)
1. a small portable Flying-wing unmanned plane, comprise fuselage (1) and be located at the wing (2) of fuselage (1) both sides, be blended wing-body body structure between described fuselage (1) and wing (2), the rear end of described fuselage (1) is furnished with screw propeller (3), it is characterized in that, described wing (2) is removably connected by wing body catch gear (4) and fuselage (1), and the flight components and parts of described unmanned plane are all arranged on fuselage (1).
2. small portable Flying-wing according to claim 1 unmanned plane, it is characterized in that, described wing body catch gear (4) comprises is located at main connecting pin (41) on wing (2) sidewall and secondary connecting pin (42), and on the sidewall of described fuselage (1), correspondence is provided with main connecting pin bores portion (43) and secondary connecting pin bores portion (44).
3. small portable Flying-wing according to claim 2 unmanned plane, it is characterized in that, described main connecting pin (41) comprises pin rod (411) and is located at the spherical plunger (412) of pin rod (411) leading section, and described main connecting pin bores portion (43) comprises the deck (431) coordinated with spherical plunger (412).
4. small portable Flying-wing according to claim 3 unmanned plane, it is characterized in that, described deck (431) has the hollowed out spherical hole coordinated with spherical plunger (412), and described spherical plunger (412) is clamp-oned in hollowed out spherical hole to be blocked fixing by deck (431).
5. small portable Flying-wing according to claim 2 unmanned plane, it is characterized in that, described wing body catch gear (4) also comprises auricle fixation kit (45), described auricle fixation kit (45) comprises the spill auricle seat (451) be located on fuselage (1) and the auricle (452) be located on wing (2), salient is provided with in described spill auricle seat (451), described auricle (452) is provided with the through hole coordinated with salient, when described auricle (452) inserts in spill auricle seat (451), described salient snaps in through hole to block fixing by auricle (452).
6. small portable Flying-wing according to claim 2 unmanned plane, it is characterized in that, described main connecting pin (41) and secondary connecting pin (42) are made by carbon fibre material, and the length of described main connecting pin (41) is greater than the length of secondary connecting pin (42) and auricle fixation kit (45).
7. according to the small portable Flying-wing unmanned plane in claim 1 ~ 6 described in any one, it is characterized in that, the front portion of described fuselage (1) is towards projection, described fuselage (1) inside is from first to last furnished with GPS sensor module (5) successively, battery component (6), control assembly (7) and photomoduel (8), a digital rudder controller assembly (9) is respectively provided with about the rear portion of photomoduel (8), the rear portion of described digital rudder controller assembly (9) is provided with electricity and adjusts cabin (10) and for driving the drive motor (11) of screw propeller (3), described photomoduel (8) is arranged in the middle part of fuselage (1).
8. small portable Flying-wing according to claim 7 unmanned plane, is characterized in that, the end face correspondence of described fuselage (1) is provided with detachable battery hatchcover (12) and phase cabin cover (13).
9. small-sized Flying-wing according to claim 7 unmanned plane, is characterized in that, the top of described fuselage (1) is provided with antenna (14) and pitot (15).
10. according to the small portable Flying-wing unmanned plane in claim 1 ~ 6 described in any one, it is characterized in that, described fuselage (1) and wing (2) all adopt lightweighting materials to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520889635.1U CN205131625U (en) | 2015-11-10 | 2015-11-10 | Small -size portable all -wing aircraft overall arrangement unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520889635.1U CN205131625U (en) | 2015-11-10 | 2015-11-10 | Small -size portable all -wing aircraft overall arrangement unmanned aerial vehicle |
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| CN205131625U true CN205131625U (en) | 2016-04-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520889635.1U Expired - Fee Related CN205131625U (en) | 2015-11-10 | 2015-11-10 | Small -size portable all -wing aircraft overall arrangement unmanned aerial vehicle |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043666A (en) * | 2016-08-24 | 2016-10-26 | 广州朱雀航空科技有限公司 | Wing of unmanned plane |
| CN106081098A (en) * | 2016-08-24 | 2016-11-09 | 广州朱雀航空科技有限公司 | A kind of unmanned plane |
| CN106143898A (en) * | 2016-08-08 | 2016-11-23 | 北京奇正数元科技股份有限公司 | A kind of VTOL tilting rotor fixed wing airplane |
| CN106240812A (en) * | 2016-08-30 | 2016-12-21 | 广州三飞航空科技有限公司 | One lifts unmanned plane easily |
| CN107264813A (en) * | 2017-05-24 | 2017-10-20 | 南京理工大学 | A kind of tailstock vertical takeoff and landing vehicle flight control system |
| 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 |
| CN108146611A (en) * | 2017-12-22 | 2018-06-12 | 中山市得高行知识产权中心（有限合伙） | A kind of portable agricultural formula unmanned plane and its application method |
| CN109250066A (en) * | 2018-09-29 | 2019-01-22 | 长光卫星技术有限公司 | A kind of unmanned wing body locking device of wing body separate type and locking method |
| CN109269363A (en) * | 2018-11-16 | 2019-01-25 | 湖南省军合科技有限公司 | A kind of Flying-wing individual soldier hand-thrown type scout missile |
| CN110254745A (en) * | 2019-06-03 | 2019-09-20 | 西安飞机工业（集团）有限责任公司 | A kind of modularization flying wing type multimachine body aircraft joining method |
| CN110697018A (en) * | 2019-10-23 | 2020-01-17 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle wing and fuselage connecting device |
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2015
- 2015-11-10 CN CN201520889635.1U patent/CN205131625U/en not_active Expired - Fee Related
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106143898B (en) * | 2016-08-08 | 2018-07-10 | 北京奇正数元科技股份有限公司 | A kind of VTOL tilting rotor fixed wing aircraft |
| CN106143898A (en) * | 2016-08-08 | 2016-11-23 | 北京奇正数元科技股份有限公司 | A kind of VTOL tilting rotor fixed wing airplane |
| CN106081098A (en) * | 2016-08-24 | 2016-11-09 | 广州朱雀航空科技有限公司 | A kind of unmanned plane |
| CN106043666A (en) * | 2016-08-24 | 2016-10-26 | 广州朱雀航空科技有限公司 | Wing of unmanned plane |
| CN106240812A (en) * | 2016-08-30 | 2016-12-21 | 广州三飞航空科技有限公司 | One lifts unmanned plane easily |
| CN106240812B (en) * | 2016-08-30 | 2018-08-03 | 广州三飞航空科技有限公司 | It is a kind of to lift easily unmanned plane |
| CN107264813A (en) * | 2017-05-24 | 2017-10-20 | 南京理工大学 | A kind of tailstock vertical takeoff and landing vehicle flight control system |
| 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 |
| CN108146611A (en) * | 2017-12-22 | 2018-06-12 | 中山市得高行知识产权中心（有限合伙） | A kind of portable agricultural formula unmanned plane and its application method |
| CN108146611B (en) * | 2017-12-22 | 2022-03-11 | 中山市得高行知识产权中心（有限合伙） | Portable agricultural unmanned aerial vehicle and use method thereof |
| CN109250066A (en) * | 2018-09-29 | 2019-01-22 | 长光卫星技术有限公司 | A kind of unmanned wing body locking device of wing body separate type and locking method |
| CN109269363A (en) * | 2018-11-16 | 2019-01-25 | 湖南省军合科技有限公司 | A kind of Flying-wing individual soldier hand-thrown type scout missile |
| CN109269363B (en) * | 2018-11-16 | 2024-05-10 | 湖南省军合科技有限公司 | Single-soldier hand-throwing type fly-round missile with flying wing layout |
| CN110254745A (en) * | 2019-06-03 | 2019-09-20 | 西安飞机工业（集团）有限责任公司 | A kind of modularization flying wing type multimachine body aircraft joining method |
| CN110697018A (en) * | 2019-10-23 | 2020-01-17 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle wing and fuselage connecting device |
| CN110697018B (en) * | 2019-10-23 | 2021-10-01 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle wing and fuselage connecting device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160406 Termination date: 20211110 |