CN107985574B - Buoyancy assisted lifting unmanned aerial vehicle - Google Patents
Buoyancy assisted lifting unmanned aerial vehicle Download PDFInfo
- Publication number
- CN107985574B CN107985574B CN201711170530.0A CN201711170530A CN107985574B CN 107985574 B CN107985574 B CN 107985574B CN 201711170530 A CN201711170530 A CN 201711170530A CN 107985574 B CN107985574 B CN 107985574B
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- unmanned aerial
- aerial vehicle
- connecting block
- lateral wall
- side wall
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Abstract
The invention discloses a buoyancy-assisted lifting unmanned aerial vehicle which comprises an unmanned aerial vehicle, wherein a connecting block is arranged on the side wall of the upper end of the unmanned aerial vehicle, a fixing block is arranged above the connecting block, an air bag is arranged on the side wall of the upper end of the fixing block, a mounting groove is formed in the side wall of the lower end of the fixing block, the connecting block penetrates into the mounting groove and is arranged, the connecting block is of a hollow structure, grooves are formed in the side walls of the two sides of the connecting block, the bottoms of the grooves are connected with a clamping block through a plurality of springs, a first clamping groove matched with the clamping block is formed in the side wall of the mounting groove, the inner wall of the connecting block is rotatably connected with a vertically arranged first threaded rod through a first rotating piece, a rotating rod is transversely arranged in the connecting block and penetrates through the side wall of. The buoyancy assisted lifting unmanned aerial vehicle is simple in structure and convenient to operate, and the buoyancy assisted lifting unmanned aerial vehicle is stronger in cruising ability and more flexible to operate.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a buoyancy assisted lifting unmanned aerial vehicle.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. Because the device has the advantages of low cost, good cost-effectiveness ratio, good maneuvering performance, convenient use and the like, the device is widely applied to the fields of aerial photography, agriculture, plant protection, self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, electric power inspection, disaster relief, movie and television shooting and the like. Unmanned aerial vehicle is the aircraft that begins to put into practical use gradually at present, and it has flexible, the reaction is quick, unmanned flight, operation require advantage such as low. The unmanned aerial vehicle is provided with various sensors, such as a camera, can realize real-time image transmission and high-risk area detection functions, and is widely applied to the fields of fire fighting, military affairs, traffic, police affairs, exploration, meteorology and the like so as to realize cruise shooting and monitoring of specified areas. Unmanned aerial vehicles generally include an organism portion, a control portion, a power portion, and a load portion; the machine body part is a frame and a plurality of wing arms arranged on the frame; the power part refers to a power source, a motor and a rotor wing which are arranged on a wing arm; the control part is a control mechanism arranged in the frame; the load part is a load carried on the frame. The power source can be a lithium battery or a fuel cell. Currently, most unmanned aerial vehicles are designed and manufactured based on the flight principle of helicopters, and can realize vertical lifting and high-altitude hovering, so as to meet the requirements of aerial photography and monitoring, and the unmanned aerial vehicles are most commonly of a fixed wing type and a multi-rotor type (such as four rotors). However, the problem is that the lift source of the unmanned aerial vehicle in the prior art is generally only a rotor wing, and the fixed wing type unmanned aerial vehicle has high meteorological conditions, high take-off and landing requirements and high cost when working; the power source of the multi-rotor unmanned aerial vehicle is generally a battery, the battery of the existing four-rotor unmanned aerial vehicle is generally 5000mAh, the flight time is only 15-20 minutes, the endurance is poor, the rotor of the unmanned aerial vehicle in the prior art is generally fixed at the tail end of a support arm, the rotating angle of the unmanned aerial vehicle cannot be adjusted, and the flexibility is slightly insufficient.
Disclosure of Invention
The invention aims to solve the problems that the endurance is poor in the prior art, the rotating angle of a rotor wing of an unmanned aerial vehicle in the prior art cannot be adjusted because the rotor wing is generally fixed at the tail end of a support arm, and the flexibility is slightly insufficient, and provides a buoyancy assisted lifting unmanned aerial vehicle.
In order to achieve the purpose, the invention adopts the following technical scheme:
a buoyancy-assisted lifting unmanned aerial vehicle comprises an unmanned aerial vehicle body, wherein a connecting block is arranged on the upper end side wall of the unmanned aerial vehicle body, a fixing block is arranged above the connecting block, an air bag is arranged on the upper end side wall of the fixing block, a mounting groove is formed in the lower end side wall of the fixing block, the connecting block penetrates into the mounting groove and is arranged, the connecting block is of a hollow structure, grooves are formed in the side walls of the two sides of the connecting block, clamping blocks are connected to the bottoms of the grooves through a plurality of springs, a first clamping groove matched with the clamping blocks is formed in the side wall of the mounting groove, a first threaded rod which is vertically arranged is rotatably connected to the inner wall of the connecting block through a first rotating piece, a rotating rod is transversely arranged in the connecting block and penetrates through one side wall of the connecting block, a first helical gear matched with the first threaded rod is arranged at one, the side wall of the first nut is rotatably connected with two first connecting rods through a first rotating shaft, one ends of the two first connecting rods, which are far away from the first nut, are rotatably connected with a second connecting rod through a second rotating shaft, the second connecting rods penetrate through the side wall of the groove and are fixedly connected with the clamping block, the side wall of the unmanned aerial vehicle is transversely provided with a plurality of first support arms, one ends of the first support arms, which are far away from the unmanned aerial vehicle, are connected with second support arms through positioning pins, the positioning pins penetrate through the second support arms, the positioning pins are of hollow structures, the bottoms of the positioning pins are rotatably connected with second threaded rods through second rotating members, the second threaded rods penetrate through the side wall of the upper ends of the positioning pins, the inner walls of the positioning pins are rotatably connected with two third threaded rods through third rotating members, the third threaded rods are respectively positioned at two sides of the second threaded rods, and one ends of the two third threaded rods, two the lateral wall of third threaded rod all overlaps and is equipped with the second nut rather than matching, the lateral wall of second nut is equipped with the kelly, and the kelly runs through the lateral wall setting of locating pin, the lateral wall of second support arm is equipped with the second draw-in groove that matches with the kelly, the one end that first support arm was kept away from to the second support arm is equipped with the mount pad, the mount pad is hollow structure, be equipped with driving motor in the mount pad, driving motor has the roating seat through drive shaft connection, and the drive shaft runs through the lateral wall setting of mount pad, the lateral wall of roating seat is equipped with rotor motor, and is equipped with the rotor on the rotor motor.
Preferably, be equipped with the pump among the unmanned aerial vehicle, and the pump passes through the gas tube and is connected with the gasbag.
Preferably, unmanned aerial vehicle's upper end lateral wall is equipped with places the chamber.
Preferably, unmanned aerial vehicle's lower extreme is equipped with the stores pylon.
Preferably, the opening of the mounting groove is sleeved with a dust cover.
Preferably, the lateral wall of recess is equipped with two spouts, and the spout is located the both sides of recess respectively, two the spout all passes through slider and fixture block sliding connection.
Preferably, the rotating rod is wrapped with a rubber protective sleeve.
The unmanned aerial vehicle has a simple structure and is convenient to operate, the air bag with the rising floating buoyancy is connected to the body of the unmanned aerial vehicle to offset partial gravity in the self weight of the unmanned aerial vehicle body, so that energy consumed by offsetting gravity to do work when the unmanned aerial vehicle power mechanism drives the rotor wing device to drive the unmanned aerial vehicle to rise and fly is reduced, the energy consumption of the power mechanism is greatly reduced, the cruising ability of the unmanned aerial vehicle is improved, the energy utilization rate is effectively improved, the unmanned aerial vehicle can be more easily lifted off and quickly enter a working state, when the unmanned aerial vehicle is not used, the air bag can be disassembled to be arranged in a placing cavity of the unmanned aerial vehicle, when the unmanned aerial vehicle is disassembled, the rotating rod is rotated to drive the first helical gear to rotate, the first helical gear drives the first threaded rod to rotate, and the first nut on the first threaded rod is limited by the two first connecting rods, so that, the first nut drives the two first connecting rods to move, the two first connecting rods are close to each other, the first connecting rods drive the second connecting rods to shrink into the connecting blocks, the second connecting rods drive the clamping blocks to shrink into the grooves, the clamping blocks are separated from the first clamping grooves, the fixing blocks are pulled out of the connecting blocks to finish disassembly, in order to carry the unmanned aerial vehicle, the second support arm is connected with the first support arm through the positioning pins, when the second support arm is connected onto the first support arm, the positioning pins are inserted, then the second threaded rod is rotated, the second threaded rod drives the second helical gear to rotate, the second helical gear drives the third threaded rod to rotate, the second nut on the third threaded rod is limited by the clamping rods, so that the second nut can move on the third threaded rod, the second nut drives the clamping rods to be buckled with the second clamping grooves, the positioning pins are fixed, in order to enable the unmanned aerial vehicle to have stronger flexibility, the driving motor drives the rotary base, so that the rotor on the rotary seat can rotate.
Drawings
Fig. 1 is a schematic structural view of a buoyancy assisted lifting unmanned aerial vehicle provided by the invention;
FIG. 2 is a schematic view of the structure at A in FIG. 1;
FIG. 3 is a schematic view of the structure at B in FIG. 1;
fig. 4 is a schematic structural diagram at C in fig. 1.
In the figure: the device comprises an Unmanned Aerial Vehicle (UAV), a connecting block, a fixing block, an air bag, a mounting groove, a spring, a clamping block, a clamping groove, a clamping block.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
Referring to fig. 1-4, a buoyancy assisted lifting unmanned aerial vehicle comprises an unmanned aerial vehicle 1, wherein an inflator pump is arranged in the unmanned aerial vehicle 1 and is connected with an air bag 4 through an inflation tube 36, so as to conveniently inflate the air bag 4 and prevent the air bag 4 from leaking air chronically to influence the lifting force of the unmanned aerial vehicle 1, a placing cavity is arranged on the upper end side wall of the unmanned aerial vehicle 1, the air bag 4 can be placed in the placing cavity after the air bag 4 is detached from the unmanned aerial vehicle 1, a hanging frame is arranged on the lower end of the unmanned aerial vehicle 1, so that corresponding equipment can be hung on the bottom of the unmanned aerial vehicle 1 conveniently, a connecting block 2 is arranged on the upper end side wall of the unmanned aerial vehicle 1, a fixing block 3 is arranged above the connecting block 2, the air bag 4 is arranged on the upper end side wall of the fixing block 3, a mounting, the connecting block 2 penetrates through the mounting groove 5 to be arranged, the connecting block 2 is of a hollow structure, grooves 6 are arranged on the side walls of two sides of the connecting block 2, two sliding grooves 37 are arranged on the side walls of the grooves 6, the sliding grooves 37 are respectively positioned on two sides of the grooves 6, the two sliding grooves 37 are connected with the clamping block 8 in a sliding mode through sliding blocks 38, the clamping block 8 is prevented from sliding out of the grooves 6, instable mounting is caused, the bottom of each groove 6 is connected with the clamping block 8 through a plurality of springs 7, a first clamping groove 9 matched with the clamping block 8 is arranged on the side wall of the mounting groove 5, a vertically arranged first threaded rod 11 is connected to the inner wall of the connecting block 2 in a rotating mode through a first rotating piece 10, a rotating rod 12 is transversely arranged in the connecting block 2, a rubber protective sleeve is wrapped on the rotating rod 12, when the rotating rod 12 is prevented from being rotated by hand, the rotating rod 12 is scratched to the hand, the rotating rod 12 penetrates through, the lateral wall of the first threaded rod 11 is sleeved with a first nut 14 matched with the first threaded rod, the lateral wall of the first nut 14 is rotatably connected with two first connecting rods 16 through a first rotating shaft 15, one ends of the two first connecting rods 16 far away from the first nut 14 are rotatably connected with second connecting rods 18 through second rotating shafts 17, the second connecting rods 18 penetrate through the lateral wall of the groove 6 and are fixedly connected with the fixture blocks 8, the lateral wall of the unmanned aerial vehicle 1 is transversely provided with a plurality of first supporting arms 19, one ends of the first supporting arms 19 far away from the unmanned aerial vehicle 1 are connected with second supporting arms 21 through positioning pins 20, the positioning pins 20 penetrate through the second supporting arms 21, the positioning pins 20 are of a hollow structure, the bottoms of the positioning pins 20 are rotatably connected with second threaded rods 23 through second rotating pieces 22, the second threaded rods 23 penetrate through the upper end lateral walls of the positioning pins 20, the inner walls of the positioning pins 20 are rotatably, and third threaded rod 25 is located the both sides of second threaded rod 23 respectively, the one end that third rotation piece 24 was kept away from to two third threaded rods 25 all is equipped with the second helical gear 26 that matches with second threaded rod 23, the lateral wall of two third threaded rods 25 all overlaps and is equipped with rather than the second nut 27 that matches, the lateral wall of second nut 27 is equipped with kelly 28, and kelly 28 runs through the lateral wall setting of locating pin 20, the lateral wall of second support arm 21 is equipped with the second draw-in groove 29 that matches with kelly 28, the one end that first support arm 19 was kept away from to second support arm 21 is equipped with mount pad 30, mount pad 30 is hollow structure, be equipped with driving motor 31 in the mount pad 30, driving motor 31 is connected with roating seat 33 through drive shaft 32, and drive shaft 32 runs through the lateral wall setting of mount pad 30, the lateral wall of roating seat 33 is equipped with rotor motor 34, and be equipped.
The unmanned aerial vehicle has a simple structure and is convenient to operate, the air bag 4 with the rising floating buoyancy is connected to the body of the unmanned aerial vehicle 1 to counteract partial gravity in the self weight of the body of the unmanned aerial vehicle 1, so that energy consumed by counteracting gravity acting when a power mechanism of the unmanned aerial vehicle 1 drives the rotor wing device to drive the unmanned aerial vehicle 1 to ascend and fly is reduced, energy consumption of the power mechanism is greatly reduced, the cruising ability of the unmanned aerial vehicle 1 is improved, the energy utilization rate is effectively improved, the unmanned aerial vehicle 1 can be more easily lifted off and quickly enter a working state, when the unmanned aerial vehicle is not used, the air bag 4 can be disassembled to be arranged in a placing cavity of the unmanned aerial vehicle 1, when the unmanned aerial vehicle is disassembled, the rotating rod 12 is rotated, the rotating rod 12 drives the first helical gear 13 to rotate, the first helical gear 13 drives the first threaded rod 11 to rotate, and the first nut 14 on the first, therefore, the first nut 14 can move on the first threaded rod 11, the first nut 14 drives the two first connecting rods 16 to move, the two first connecting rods 16 approach to each other, the first connecting rod 16 drives the second connecting rod 18 to contract into the connecting block 2, the second connecting rod 18 drives the clamping block 8 to retract into the groove 6, the clamping block 8 is separated from the first clamping groove 9, the fixing block 3 is pulled out of the connecting block 2 to finish disassembly, in order to carry the unmanned aerial vehicle 1, the second support arm 21 is connected with the first support arm 19 through the positioning pin 20, when the second support arm 21 is connected onto the first support arm 19, the positioning pin 20 is inserted, then the second threaded rod 23 is rotated, the second threaded rod 23 drives the second bevel gear 26 to rotate, the second threaded rod 26 drives the third threaded rod 25 to rotate, the second nut 27 on the third threaded rod 25 is limited by the clamping rod 28, so that the second nut 27 can move on the third threaded rod 25, second nut 27 takes kelly 28 and second draw-in groove 29 buckle to fix locating pin 20, for making unmanned aerial vehicle 1 have stronger flexibility, driving motor 31 drives roating seat 33 through drive shaft 32 and rotates, thereby makes rotor 35 on the roating seat 33 rotatable.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (7)
1. The buoyancy assisted unmanned aerial vehicle comprises an unmanned aerial vehicle (1) and is characterized in that a connecting block (2) is arranged on the upper end side wall of the unmanned aerial vehicle (1), a fixing block (3) is arranged above the connecting block (2), an air bag (4) is arranged on the upper end side wall of the fixing block (3), a mounting groove (5) is arranged on the lower end side wall of the fixing block (3), the connecting block (2) penetrates into the mounting groove (5) to be arranged, the connecting block (2) is of a hollow structure, grooves (6) are formed in the side walls of the two sides of the connecting block (2), the bottoms of the grooves (6) are connected with clamping blocks (8) through a plurality of springs (7), first clamping grooves (9) matched with the clamping blocks (8) are formed in the side walls of the mounting groove (5), and a first threaded rod (11) which is vertically arranged is rotatably connected to the inner wall of, transversely be equipped with bull stick (12) in connecting block (2), and one side lateral wall setting of bull stick (12) through connection piece (2), the one end that bull stick (12) are close to first threaded rod (11) is equipped with first helical gear (13) with first threaded rod (11) matching, the lateral wall cover of first threaded rod (11) is equipped with first nut (14) rather than the matching, the lateral wall of first nut (14) rotates through first pivot (15) and is connected with two first connecting rods (16), two the one end that first nut (14) were kept away from in first connecting rod (16) all rotates through second pivot (17) and is connected with second connecting rod (18), and second connecting rod (18) run through the lateral wall of recess (6) and with fixture block (8) fixed connection, the lateral wall of unmanned aerial vehicle (1) transversely is equipped with a plurality of first support arms (19), the one end that unmanned aerial vehicle (1) was kept away from in first support arm (19) is connected with second support arm (21) through locating pin (20) And the positioning pin (20) is arranged by penetrating through the second support arm (21), the positioning pin (20) is of a hollow structure, the bottom of the positioning pin (20) is rotatably connected with a second threaded rod (23) through a second rotating member (22), the second threaded rod (23) is arranged by penetrating through the upper end side wall of the positioning pin (20), the inner wall of the positioning pin (20) is rotatably connected with two third threaded rods (25) through third rotating members (24), the third threaded rods (25) are respectively positioned at two sides of the second threaded rod (23), one ends of the two third threaded rods (25) far away from the third rotating members (24) are respectively provided with second bevel gears (26) matched with the second threaded rods (23), the side walls of the two third threaded rods (25) are respectively sleeved with second nuts (27) matched with the second threaded rods, and the side walls of the second nuts (27) are provided with clamping rods (28), and kelly (28) run through the lateral wall setting of locating pin (20), the lateral wall of second support arm (21) is equipped with second draw-in groove (29) that matches with kelly (28), the one end that first support arm (19) were kept away from in second support arm (21) is equipped with mount pad (30), mount pad (30) are hollow structure, be equipped with driving motor (31) in mount pad (30), driving motor (31) are connected with roating seat (33) through drive shaft (32), and drive shaft (32) run through the lateral wall setting of mount pad (30), the lateral wall of roating seat (33) is equipped with rotor motor (34), and is equipped with rotor (35) on rotor motor (34).
2. The unmanned aerial vehicle with auxiliary buoyancy lifting as claimed in claim 1, wherein an inflator pump is arranged in the unmanned aerial vehicle (1), and the inflator pump is connected with the airbag (4) through an inflation tube (36).
3. The buoyancy assisted lifting unmanned aerial vehicle of claim 1, wherein the upper end side wall of the unmanned aerial vehicle (1) is provided with a placing cavity.
4. The buoyancy assisted lifting unmanned aerial vehicle according to claim 1, wherein the lower end of the unmanned aerial vehicle (1) is provided with a hanging rack.
5. The buoyancy assisted unmanned aerial vehicle as claimed in claim 1, wherein the opening of the mounting groove (5) is sleeved with a dust cover.
6. The unmanned aerial vehicle with auxiliary buoyancy lifting function according to claim 1, wherein the side wall of the groove (6) is provided with two sliding grooves (37), the sliding grooves (37) are respectively located on two sides of the groove (6), and the two sliding grooves (37) are both connected with the clamping block (8) in a sliding mode through sliding blocks (38).
7. The unmanned aerial vehicle with auxiliary buoyancy lifting as claimed in claim 1, wherein the rotating rod (12) is wrapped with a rubber protective sleeve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711170530.0A CN107985574B (en) | 2017-11-22 | 2017-11-22 | Buoyancy assisted lifting unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711170530.0A CN107985574B (en) | 2017-11-22 | 2017-11-22 | Buoyancy assisted lifting unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN107985574A CN107985574A (en) | 2018-05-04 |
| CN107985574B true CN107985574B (en) | 2021-03-26 |
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| CN201711170530.0A Active CN107985574B (en) | 2017-11-22 | 2017-11-22 | Buoyancy assisted lifting unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109353493A (en) * | 2018-09-28 | 2019-02-19 | 许剑聪 | A kind of self-rescue device of drowning unmanned plane equipped with gas generation buoyancy |
| CN109353507B (en) * | 2018-10-17 | 2021-08-24 | 杭州木书科技有限公司 | Portable multi-functional individual soldier unmanned aerial vehicle of fighting |
| CN110303840B (en) * | 2019-06-28 | 2020-12-18 | 左红 | Rotor of bicycle flight device |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1834198A1 (en) * | 1991-01-02 | 1995-06-19 | Авиационный научно-технический комплекс им.А.Н.Туполева | Flying vehicle ramjet engine |
| CN104386249B (en) * | 2014-11-17 | 2016-03-30 | 马鞍山市靓马航空科技有限公司 | The mapping method of the many rotor wing unmanned aerial vehicles of a kind of quick mapping |
| CN104608927B (en) * | 2015-02-13 | 2016-09-07 | 李潋崴 | Auxiliary liter of unmanned plane of buoyancy |
| US10703459B2 (en) * | 2015-08-03 | 2020-07-07 | X-Control System Co., Ltd. | Unmanned helicopter |
| CN205366047U (en) * | 2016-01-27 | 2016-07-06 | 湖南云顶智能科技有限公司 | A collapsible horn for unmanned aerial vehicle |
| CN205381395U (en) * | 2016-01-29 | 2016-07-13 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| JP2017165195A (en) * | 2016-03-15 | 2017-09-21 | 三菱電機株式会社 | Unmanned aircraft auxiliary device and unmanned aircraft |
| CN106219286B (en) * | 2016-08-30 | 2018-10-26 | 安徽省中阳管业有限公司 | A kind of adjustable Steel Tape Recoiler of diameter |
| CN206437210U (en) * | 2016-12-26 | 2017-08-25 | 国网辽宁省电力有限公司检修分公司 | A kind of rotor Laser Radar Scanning unmanned plane |
| CN106828900A (en) * | 2017-01-17 | 2017-06-13 | 珠海卡特瑞科农林航空装备研究所有限公司 | A kind of unmanned plane with Fu Sheng mechanisms |
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