CN110001933A - A kind of unmanned plane keeping stable state by changing center of gravity - Google Patents
A kind of unmanned plane keeping stable state by changing center of gravity Download PDFInfo
- Publication number
- CN110001933A CN110001933A CN201910273596.5A CN201910273596A CN110001933A CN 110001933 A CN110001933 A CN 110001933A CN 201910273596 A CN201910273596 A CN 201910273596A CN 110001933 A CN110001933 A CN 110001933A
- Authority
- CN
- China
- Prior art keywords
- gravity
- unmanned plane
- center
- fuselage
- stable state
- 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.)
- Withdrawn
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C17/00—Aircraft stabilisation not otherwise provided for
- B64C17/02—Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus
- B64C17/04—Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus by pendular bodies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of unmanned planes that stable state is kept by changing center of gravity, including fuselage, wing, gravity balance mechanism and lifting gear, the gravity balance mechanism to be mounted on the back side of fuselage bottom, and the lifting gear is mounted on the two sides of fuselage bottom；The gravity balance mechanism includes containing box, signal receiver, Scroll, pendulum line, center of gravity cone, winding motor and adjustment mechanism, the Scroll penetration type is mounted on the middle part of storage box cavity, the pendulum line is wrapped on the outer ring of Scroll, center at the top of the center cone is in the detachable installation in bottom of pendulum line, the winding motor is mounted on the inner cavity of containing box and the output shaft of winding motor is fixedly connected with Scroll, this keeps the unmanned plane of stable state by changing center of gravity, rising and falling for unmanned plane is assisted by the way of mandatory correction drone center of unmanned aerial vehicle, avoid generating unstable or appearance the case where drop of rising and falling because unskilled or air and windage is operated.
Description
Technical field
The present invention relates to air vehicle technique field, specially a kind of unmanned plane that stable state is kept by changing center of gravity.
Background technique
In the past few years, with the continuous development of science and technology and electronic technology, unmanned air vehicle technique has also obtained very big hair
Exhibition, is gradually developed to by military unmanned air vehicle commercial and civilian, and small drone has been also applied to each production and living
Field suffers, and has also appeared a large amount of intelligent and multi-functional unmanned vehicles, primarily serves transmitting information and detection
Effect, unmanned vehicle have the advantages that flexibly, reaction is fast, unmanned flight and operating technology require it is relatively low, its own
It is the new concept aircraft in rapidly developing, is also increasingly taken seriously, described unmanned plane refers to family mostly instantly
Outer sporting a kind of electronic equipment, this class of electronic devices are usually to have certain flight control range, pass through wireless signal
It is controlled, with the continuous development and progress of unmanned plane, the data of flying distance and flying height are also increasing.
Currently, daily seen unmanned plane is all center setting fuselage mostly, fuselage circumference is provided with multiple drivings
Flabellum be used to unmanned plane lifting, such as " a kind of multi-rotor unmanned aerial vehicle " disclosed in Chinese patent (patent No.:
CN104354857B), which includes rack, rotor, rotor motor and stabilizer blade, and the unmanned plane structure in above-mentioned technical proposal is
Instantly most commonly seen, what slightly different is that the working equipment that unmanned plane lower section is carried is different, is applied in every field
In, but no matter which kind of field unmanned plane is applied in, which type of environment, but its overall construction and design are almost that Datong District is small
Different, during practical operation unmanned plane, the unmanned plane in high-altitude is to be highly susceptible to extraneous windage to arrive, empty
The application of aerodynamics can only reduce wind-force bring as far as possible to influence, while unmanned plane is in the process for stopping flight landing
In usually more rely on be fixed angle undercarriage, the direction of undercarriage this kind of first is direction and the angle with unmanned plane
Come what is be changed, wherein there is a problem that it is very big, be when unmanned plane falls in the sky by air drag and
The influence of wind-force be easy to run-off the straight and rollover even drop, it is desirable to well landing be need well manipulation skill,
So still needing a kind of unmanned plane that itself can control equilibrium air resistance and extraneous windage.
Summary of the invention
(1) the technical issues of solving
In view of the deficiencies of the prior art, it the present invention provides a kind of unmanned plane for keeping stable state by changing center of gravity, solves
It is easy to be led to the problem of by air and windage difficulty increase of rising and falling when unmanned plane rises and falls.
(2) technical solution
In order to achieve the above object, the present invention is achieved by the following technical programs: one kind keeps stablizing shape by changing center of gravity
The unmanned plane of state, including fuselage, wing, gravity balance mechanism and lifting gear, the wing are separately positioned on the surrounding of fuselage,
The gravity balance mechanism is mounted on the back side of fuselage bottom, and the lifting gear is mounted on the two sides of fuselage bottom.
The gravity balance mechanism include containing box, signal receiver, Scroll, pendulum line, center of gravity cone, winding motor and
Adjustment mechanism, the top of the containing box and the back side of fuselage bottom are fixedly welded, the detachable installation of signal receiver
On the outer wall of containing box, the Scroll penetration type is mounted on the middle part of storage box cavity, and the pendulum line is wrapped in winding
On the outer ring of axis, the center at the top of the center cone is in the detachable installation in bottom of pendulum line, the winding motor installation
In the inner cavity of containing box and the output shaft of winding motor is fixedly connected with Scroll, and the adjustment mechanism is mounted on storage box cavity
Bottom.
Preferably, the lifting gear includes supporting leg, gas flow tube, cone tank, flow-disturbing lid and swelling bag, the supporting leg
Top be fixedly welded with fuselage bottom, the bottom of the gas flow tube is fixedly welded on the top of supporting leg, and the cone tank is opened
It is located at the middle part of fuselage roof, the flow-disturbing lid is fixedly mounted on the top of cone tank, and the swelling bag is fixedly mounted on support
The bottom of leg.
Preferably, the adjustment mechanism includes balancing frame, angle offset piece and gravitation ball, the outer ring of the balancing frame and receipts
Receiving the bottom of chamber interior wall is fixedly connected, and the top of the angle offset piece is fixedly connected with the bottom of balancing frame, the gravitation ball
Activity is connected between multiple angle offset pieces.
Preferably, power supply and the signal receiver electricity that the power end of the winding motor passes through power supply line and fuselage inner cavity
Connection, the pendulum line penetration type are mounted between balancing frame and angle offset piece.
Preferably, the supporting leg is hollow legs, and the top of the supporting leg is connected with the bottom of gas flow tube, the branch
The side that support leg is located at fuselage inner cavity equidistant offers airflow hole.
Preferably, the swelling bag is bar shaped capsule, and the length of the swelling bag and the bottom lengths of supporting leg are equal, described
The top of swelling bag is connected with the bottom of supporting leg.
Preferably, aeration piece is provided in the middle part of the supporting leg side, the bottom of the supporting leg side is equidistant to be set
It is equipped with conical pipe.
Preferably, the bottom of the conical pipe is connected with swelling bag, and the gas outlet diameter of the taper bottom of the tube is less than
The diameter of pipe shaft, exhaust velocity after swelling bag expansion will be far smaller than the speed of air inlet, on the one hand can provide one
Fixed upwards thrust quickly reduces speed protection unmanned plane when landing, on the other hand can increase support after landing
Contact area between leg and ground avoids turning on one's side, and automatic deflation movement can also be carried out after coming to a complete stop, and does not need to carry out hand again
Dynamic operation.
(3) beneficial effect
The present invention provides a kind of unmanned planes that stable state is kept by changing center of gravity.Have it is following the utility model has the advantages that
(1), the unmanned plane that stable state should be kept by changing center of gravity, come auxiliary by the way of mandatory correction drone center of unmanned aerial vehicle
Rising and falling for unmanned plane is helped, avoids generating because unskilled or air and windage is operated and rising and falling unstable or drop
The case where occur.
(2), the unmanned plane of stable state, novel Landing Gear Design should be kept by changing center of gravity, unmanned plane is rising
When the air drag of fuselage is reduced by upper and lower air circulation, utilize when landing air drag when falling to carry out
Volume expansion variation increases air drag to guarantee unmanned plane stable landing, while also increasing the positive drop resistant performance of unmanned plane.
(3), should by change center of gravity keep stable state unmanned plane, when novel undercarriage takes off air runoff without
Man-machine body inner cavity is flowed through, and on the one hand carries out flow-disturbing and guiding to the air-flow of fuselage circumference, on the other hand can also be to fuselage
The electronic component of inner cavity cools down, and avoids the excessively high work for influencing unmanned plane of flying for long time internal temperature.
(4), the unmanned plane of stable state should be kept by changing center of gravity, the design of center cone not only can be only used for nobody
The Fast-Balance of machine, but also can be used as ship anchor is similar to, the fixed point rapid descent for unmanned plane.
Detailed description of the invention
Fig. 1 is schematic structural view of the invention；
Fig. 2 is lifting gear structural schematic diagram of the present invention；
Fig. 3 is gravity balance apparatus structure schematic diagram of the present invention；
Fig. 4 is present invention adjustment apparatus structure schematic diagram.
In figure: 1 fuselage, 2 wings, 3 gravity balance mechanisms, 301 containing boxs, 302 signal receivers, 303 Scrolls, 304
Pendulum line, 305 centers of gravity cone, 306 winding motors, 307 adjustment devices, 3071 balancing patches, 3072 angle offset pieces, 3073 gravity
Ball, 4 lifting gears, 401 supporting legs, 402 gas flow tubes, 403 cone tanks, 404 flow-disturbing lids, 405 swelling bags, 406 airflow holes, 407
Aeration piece, 408 conical pipes.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.
In the present invention unless specifically defined or limited otherwise, term " installation ", " connected ", " connection ", " fixation " etc.
Term shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integral；It can be mechanical connect
It connects, is also possible to be electrically connected；It can be directly connected, can also can be in two elements indirectly connected through an intermediary
The interaction relationship of the connection in portion or two elements.It for the ordinary skill in the art, can be according to specific feelings
Condition understands the concrete meaning of above-mentioned term in the present invention.
Please refer to Fig. 1-4, the present invention provides a kind of technical solution: it is a kind of by change center of gravity keep stable state nobody
Machine, including fuselage 1, wing 2, gravity balance mechanism 3 and lifting gear 4, wing 2 are separately positioned on the surrounding of fuselage 1, and center of gravity is flat
Weighing apparatus mechanism 3 is mounted on the back side of 1 bottom of fuselage, and lifting gear 4 is mounted on the two sides of 1 bottom of fuselage, and gravity balance mechanism 3 includes
Containing box 301, signal receiver 302, Scroll 303, pendulum line 304, center of gravity cone 305, winding motor 306 and adjustment mechanism
307, the back side at the top and 1 bottom of fuselage of containing box 301 is fixedly welded, and signal receiver 302 is removably mounted to store
On the outer wall of case 301,303 penetration type of Scroll is mounted on the middle part of 301 inner cavity of containing box, and pendulum line 304 is wrapped in Scroll
On 303 outer ring, the center at 305 top of center cone is in the detachable installation in bottom of pendulum line 304, and winding motor 306 is pacified
Mounted in the inner cavity of containing box 301 and the output shaft of winding motor 306 is fixedly connected with Scroll 303, and adjustment mechanism 307 is mounted on
The bottom of 301 inner cavity of containing box, lifting gear 4 include supporting leg 401, gas flow tube 402, cone tank 403, flow-disturbing lid 404 and swollen
Swollen capsule 405, top and 1 bottom of fuselage of supporting leg 401 are fixedly welded, and the bottom of gas flow tube 402 is fixedly welded on supporting leg 401
Top, cone tank 403 is provided with the middle part at the top of fuselage 1, and flow-disturbing lid 404 is fixedly mounted on the top of cone tank 403, expands
Capsule 405 is fixedly mounted on the bottom of supporting leg 401, and supporting leg 401 is hollow legs, top and the gas flow tube 402 of supporting leg 401
Bottom is connected, supporting leg 401 be located at 1 inner cavity of fuselage side it is equidistant offer airflow hole 406, swelling bag 405 is bar shaped
The length of capsule, swelling bag 405 is equal with the bottom lengths of supporting leg 401, the top of swelling bag 405 and the bottom of supporting leg 401
It is connected, aeration piece 407 is provided in the middle part of 401 side of supporting leg, the bottom of 407 side of supporting leg has been equidistantly positioned taper
The bottom of pipe 408, conical pipe 408 is connected with swelling bag 405, and the gas outlet diameter of 408 bottom of conical pipe is less than the straight of pipe shaft
Diameter, adjustment mechanism 307 include balancing frame 3071, angle offset piece 3072 and gravitation ball 3073, the outer ring of balancing frame 3071 and receipts
Receiving the bottom of 301 inner wall of case is fixedly connected, and the top of angle offset piece 3072 is fixedly connected with the bottom of balancing frame 3071, gravity
3073 activity of ball is connected between multiple angle offset pieces 3072, and the power end of winding motor 306 passes through in power supply line and fuselage 1
The power supply and signal receiver 302 of chamber are electrically connected, and 304 penetration type of pendulum line is mounted on balancing frame 3071 and angle offset piece
Between 3072.
It is unmanned to occur by extraneous gas when this keeps the unmanned plane of stable state to work by changing center of gravity (or when using)
Stream or wind-force interfere and generation inclination or angle change flight are unstable, are sent out signal by the control switch on remote controler
It send to signal receiver 302, signal receiver 302 is dynamic by that will directly control the generation energization of winding motor 306 after signal
Make, then control winding motor 306 rotate in one direction, by output shaft drive Scroll 303 rotation by pendulum line 304 into
Row release, pendulum line 304 by the outside of 305 release of the center of gravity of its bottom cone to 301 bottom of containing box, center of gravity cone 305 it is vertical
State will pull the correction of the progress angle of fuselage 1 of unmanned plane by force, while angle offset piece 3072 will be with fuselage 1
Tilt and corresponding angle change occur, therewith change be gravitation ball 3073 along the inclination of angle offset piece 3072 and into
Row corresponding movement successively assists center of gravity cone 305 to carry out the corrections of centers of gravity by self gravity as far as possible towards lower movement
Guarantee the stabilization of unmanned plane during flying, when riseing on line, the air-flow at top enters cone tank 403 by flow-disturbing lid 404
Inner cavity, enter back into the inner cavity of gas flow tube 402 and be finally directly flowed into 1 inner cavity of fuselage most heel row via airflow hole 406
The outside of fuselage 1 out, when unmanned plane falls, air flows directly into conical pipe 408, air via the guiding of aeration piece 407
The inner cavity that swelling bag 405 is entered by the small de-air hole of bottom, since the speed and volume that enter air are far longer than discharge
When speed and volume, so swelling bag 405 will expand until the bottom of supporting leg 401 package is increased and ground
The contact area in face, and with center of gravity cone 305 leading landing, it is determined that landing place, unmanned plane landing when more
The steady safety added.
In conclusion the unmanned plane of stable state should be kept by changing center of gravity, using mandatory correction drone center of unmanned aerial vehicle
Mode assist rising and falling for unmanned plane, avoid generating shakiness of rising and falling because unskilled or air and windage is operated
The case where determining or dropping appearance, novel Landing Gear Design, unmanned plane are reduced when rising by upper and lower air circulation
The air drag of fuselage utilizes when landing air drag when falling to carry out volume expansion variation, increases air drag
To guarantee unmanned plane stable landing, while the also increase positive drop resistant performance of unmanned plane, air when novel undercarriage takes off
The body inner cavity of runoff unmanned plane is flowed through, and on the one hand carries out flow-disturbing and guiding to the air-flow of fuselage circumference, on the other hand can be with
Cool down to the electronic component of fuselage inner cavity, avoids the excessively high work for influencing unmanned plane of flying for long time internal temperature, center
The design of cone not only can be only used for the Fast-Balance of unmanned plane, but also can use as ship anchor is similar to, and be used for nobody
The fixed point rapid descent of machine.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
Anyone skilled in the art in the technical scope disclosed by the present invention, according to the technique and scheme of the present invention and its
Inventive concept is subject to equivalent substitution or change, should be covered by the protection scope of the present invention.
Claims (8)
1. a kind of unmanned plane for keeping stable state by changing center of gravity, it is characterised in that: including fuselage (1), wing (2), again
Heart balance mechanism (3) and lifting gear (4), the wing (2) are separately positioned on the surrounding of fuselage (1), the gravity balance machine
Structure (3) is mounted on the back side of fuselage (1) bottom, and the lifting gear (4) is mounted on the two sides of fuselage (1) bottom；
The gravity balance mechanism (3) includes containing box (301), signal receiver (302), Scroll (303), pendulum line
(304), center of gravity cone (305), winding motor (306) and adjustment mechanism (307), the top and fuselage (1) of the containing box (301)
The back side of bottom is fixedly welded, and the signal receiver (302) is removably mounted on the outer wall of containing box (301), described
Scroll (303) penetration type is mounted on the middle part of containing box (301) inner cavity, and the pendulum line (304) is wrapped in Scroll (303)
Outer ring on, the center at the top of the center cone (305) is in the detachable installation in bottom of pendulum line (304), the winding
Motor (306) is mounted on the inner cavity of containing box (301) and the output shaft of winding motor (306) is fixedly connected with Scroll (303),
The adjustment mechanism (307) is mounted on the bottom of containing box (301) inner cavity.
2. a kind of unmanned plane for keeping stable state by changing center of gravity according to claim 1, it is characterised in that: described
Lifting gear (4) includes supporting leg (401), gas flow tube (402), cone tank (403), flow-disturbing lid (404) and swelling bag (405),
The top of the supporting leg (401) is fixedly welded with fuselage (1) bottom, and the bottom of the gas flow tube (402) is fixedly welded on branch
The top of support leg (401), the cone tank (403) are provided with the middle part at the top of fuselage (1), the fixed peace of the flow-disturbing lid (404)
Mounted in the top of cone tank (403), the swelling bag (405) is fixedly mounted on the bottom of supporting leg (401).
3. a kind of unmanned plane for keeping stable state by changing center of gravity according to claim 1, it is characterised in that: described
Adjustment mechanism (307) includes balancing frame (3071), angle offset piece (3072) and gravitation ball (3073), the balancing frame (3071)
Outer ring be fixedly connected with the bottom of containing box (301) inner wall, the top of the angle offset piece (3072) and balancing frame
(3071) bottom is fixedly connected, and gravitation ball (3073) activity is connected between multiple angle offset pieces (3072).
4. a kind of unmanned plane for keeping stable state by changing center of gravity according to claim 1, it is characterised in that: described
The power end of winding motor (306) is electrically connected by power supply line with the power supply of fuselage (1) inner cavity and signal receiver (302),
Pendulum line (304) penetration type is mounted between balancing frame (3071) and angle offset piece (3072).
5. a kind of unmanned plane for keeping stable state by changing center of gravity according to claim 2, it is characterised in that: described
Supporting leg (401) is hollow legs, and the top of the supporting leg (401) is connected with the bottom of gas flow tube (402), the supporting leg
(401) side positioned at fuselage (1) inner cavity equidistant offers airflow hole (406).
6. a kind of unmanned plane for keeping stable state by changing center of gravity according to claim 2, it is characterised in that: described
Swelling bag (405) is bar shaped capsule, and the length of the swelling bag (405) is equal with the bottom lengths of supporting leg (401), the expansion
The top of capsule (405) is connected with the bottom of supporting leg (401).
7. a kind of unmanned plane for keeping stable state by changing center of gravity according to claim 2, it is characterised in that: described
It is provided with aeration piece (407) in the middle part of supporting leg (401) side, the bottom of supporting leg (407) side has been equidistantly positioned
Conical pipe (408).
8. a kind of unmanned plane for keeping stable state by changing center of gravity according to claim 7, it is characterised in that: described
The bottom of conical pipe (408) is connected with swelling bag (405), and the gas outlet diameter of conical pipe (408) bottom is less than pipe shaft
Diameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910273596.5A CN110001933A (en) | 2019-04-06 | 2019-04-06 | A kind of unmanned plane keeping stable state by changing center of gravity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910273596.5A CN110001933A (en) | 2019-04-06 | 2019-04-06 | A kind of unmanned plane keeping stable state by changing center of gravity |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110001933A true CN110001933A (en) | 2019-07-12 |
Family
ID=67170116
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910273596.5A Withdrawn CN110001933A (en) | 2019-04-06 | 2019-04-06 | A kind of unmanned plane keeping stable state by changing center of gravity |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110001933A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114909976A (en) * | 2022-07-18 | 2022-08-16 | 山东兰图地理信息工程有限公司 | Survey and drawing device for collecting thickness of underwater silt |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008007147A1 (en) * | 2006-07-13 | 2008-01-17 | Hoverwing Limited | Aircraft |
| CN203318676U (en) * | 2013-05-30 | 2013-12-04 | 南京信息工程大学 | Coaxial double-wing aircraft with moving centre-of-gravity ball |
| CN205311892U (en) * | 2015-12-30 | 2016-06-15 | 苏州妙旋无人机应用有限公司 | Controllable formula unmanned aerial vehicle of focus |
| CN205819559U (en) * | 2016-07-18 | 2016-12-21 | 杨永泉 | A kind of rotor wing unmanned aerial vehicle with kuppe |
| CN206766343U (en) * | 2016-09-08 | 2017-12-19 | 厦门九星天翔航空科技有限公司 | One kind collection sample anticollision unmanned plane |
| CN207060377U (en) * | 2017-08-01 | 2018-03-02 | 广州极飞科技有限公司 | Unmanned plane |
| CN207089646U (en) * | 2017-08-10 | 2018-03-13 | 昊翔电能运动科技(昆山)有限公司 | The rack construction of aircraft |
| CN207346071U (en) * | 2017-08-01 | 2018-05-11 | 广州极飞科技有限公司 | Unmanned plane and based shell |
| CN108569400A (en) * | 2018-06-20 | 2018-09-25 | 芜湖易迅生产力促进中心有限责任公司 | A kind of power circuit patrolling robot |
| CN109319112A (en) * | 2018-10-30 | 2019-02-12 | 佛山市神风航空科技有限公司 | It is a kind of to be vertically moved up or down fixed wing aircraft with balance mechanism |
| WO2019061386A1 (en) * | 2017-09-30 | 2019-04-04 | 林燕凤 | Unmanned aerial vehicle fall protection device |
-
2019
- 2019-04-06 CN CN201910273596.5A patent/CN110001933A/en not_active Withdrawn
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008007147A1 (en) * | 2006-07-13 | 2008-01-17 | Hoverwing Limited | Aircraft |
| CN203318676U (en) * | 2013-05-30 | 2013-12-04 | 南京信息工程大学 | Coaxial double-wing aircraft with moving centre-of-gravity ball |
| CN205311892U (en) * | 2015-12-30 | 2016-06-15 | 苏州妙旋无人机应用有限公司 | Controllable formula unmanned aerial vehicle of focus |
| CN205819559U (en) * | 2016-07-18 | 2016-12-21 | 杨永泉 | A kind of rotor wing unmanned aerial vehicle with kuppe |
| CN206766343U (en) * | 2016-09-08 | 2017-12-19 | 厦门九星天翔航空科技有限公司 | One kind collection sample anticollision unmanned plane |
| CN207060377U (en) * | 2017-08-01 | 2018-03-02 | 广州极飞科技有限公司 | Unmanned plane |
| CN207346071U (en) * | 2017-08-01 | 2018-05-11 | 广州极飞科技有限公司 | Unmanned plane and based shell |
| CN207089646U (en) * | 2017-08-10 | 2018-03-13 | 昊翔电能运动科技(昆山)有限公司 | The rack construction of aircraft |
| WO2019061386A1 (en) * | 2017-09-30 | 2019-04-04 | 林燕凤 | Unmanned aerial vehicle fall protection device |
| CN108569400A (en) * | 2018-06-20 | 2018-09-25 | 芜湖易迅生产力促进中心有限责任公司 | A kind of power circuit patrolling robot |
| CN109319112A (en) * | 2018-10-30 | 2019-02-12 | 佛山市神风航空科技有限公司 | It is a kind of to be vertically moved up or down fixed wing aircraft with balance mechanism |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114909976A (en) * | 2022-07-18 | 2022-08-16 | 山东兰图地理信息工程有限公司 | Survey and drawing device for collecting thickness of underwater silt |
| CN114909976B (en) * | 2022-07-18 | 2022-09-13 | 山东兰图地理信息工程有限公司 | Survey and drawing device for collecting thickness of underwater silt |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6565037B1 (en) | Hybrid aircraft and methods of flying | |
| CN205891232U (en) | Urgent safe launching appliance of four rotor unmanned aerial vehicle | |
| US6142414A (en) | Rotor--aerostat composite aircraft | |
| CN106956773A (en) | Tilting rotor formula VUAV and its control method | |
| CN102119102A (en) | Rotational bottom blade type flight vehicle | |
| CN108146608B (en) | Rotor and inflatable air bag combined type floating aircraft with vector thrust | |
| CN105258904B (en) | A kind of rotary missile coning motion stability wind tunnel test methods | |
| CN106470899A (en) | The elimination torque of propeller type VTOL flying object and compatible device of keeping in balance | |
| CN105775122A (en) | Tilt rotor type aircraft | |
| CN110001933A (en) | A kind of unmanned plane keeping stable state by changing center of gravity | |
| CN105059525B (en) | A kind of small-sized vertically taking off and landing flyer aerodynamic arrangement | |
| CN205554576U (en) | Multiaxis screw and rotor combination flight lift arrangement | |
| RU130953U1 (en) | UNMANNED AIRCRAFT (OPTIONS) | |
| CN202070153U (en) | Rotor drive device of coaxial dual-propeller model helicopter | |
| CN203318682U (en) | Solar parafoil aerocraft | |
| CN106927033B (en) | Vertical coaxial double-rotor aircraft | |
| US8692406B2 (en) | Air-guiding carrier type wind power collection device | |
| CN202923882U (en) | Solar spaceship | |
| CN201086824Y (en) | Dish shaped aircraft | |
| CN209290679U (en) | Multi-rotor unmanned aerial vehicle | |
| CN208616193U (en) | One kind is verted three axis composite wing unmanned planes | |
| CN210653671U (en) | Unmanned aerial vehicle protection device that falls | |
| CN109720563A (en) | Intelligent quadrotor gliding unmanned plane and its flight control method | |
| CN208393615U (en) | The fuselage ring and aircraft of aircraft | |
| CN206900650U (en) | A kind of vertical coaxial dual-rotor helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190712 |