CN110562470A - Unmanned aerial vehicle protection device that falls - Google Patents
Unmanned aerial vehicle protection device that falls Download PDFInfo
- Publication number
- CN110562470A CN110562470A CN201910963563.3A CN201910963563A CN110562470A CN 110562470 A CN110562470 A CN 110562470A CN 201910963563 A CN201910963563 A CN 201910963563A CN 110562470 A CN110562470 A CN 110562470A
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- CN
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- unmanned aerial
- aerial vehicle
- fuselage
- protection device
- gas generator
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- 241000883990 Flabellum Species 0.000 claims abstract description 3
- 230000005540 biological transmission Effects 0.000 claims abstract description 3
- 238000004891 communication Methods 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 abstract description 2
- 230000008439 repair process Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000001174 ascending effect Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 241001465754 Metazoa Species 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
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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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention relates to the technical field of unmanned aerial vehicle equipment, in particular to an unmanned aerial vehicle falling protection device. Unmanned aerial vehicle includes the fuselage, the fuselage outside equidistance is provided with the wing, the wing tip is provided with the flabellum, the fuselage inner chamber is provided with the circuit board, the receiver, a single-chip microcomputer, gas generator and power, the receiver is used for receiving remote control instruction, and give the singlechip with the instruction transmission, the singlechip is used for receiving the instruction and starts gas generator, the fuselage outer bottom is provided with the holding chamber that comprises bounding wall and baffle, the holding intracavity is provided with the gasbag, gas generator connecting pipe, open the through-hole that supplies the pipe to pass through on the fuselage diapire, the pipe accesss to inside the gasbag. The unmanned aerial vehicle falling protection device can provide timely and effective protection when the unmanned aerial vehicle falls, reduces the collision impact force when the unmanned aerial vehicle contacts the ground, reduces the collision loss of the unmanned aerial vehicle, and reduces the maintenance and repair cost.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle equipment, in particular to an unmanned aerial vehicle falling protection device.
Background
An unmanned aircraft, referred to as "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. The unmanned aerial vehicle is divided according to the application field, and can be divided into military and civil unmanned aerial vehicles. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle is widely applied to the fields of aerial photography, agriculture, plant protection, miniature 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, the application of the unmanned aerial vehicle is greatly expanded, and the developed countries also actively expand the industrial application and develop the unmanned aerial vehicle technology.
The four-axis aircraft is one of unmanned aerial vehicles, also known as four-rotor aircraft, four-rotor helicopter, for short four-axis and four-rotor, and four-axis aircraft is a many-rotor aircraft, and four propellers of four-axis aircraft all are the simple mechanism that the motor directly links, and crisscross overall arrangement allows the aircraft to obtain the power of rotatory fuselage through changing the motor speed to adjust self gesture, stable four-axis aircraft has obtained extensive concern, and application prospect is very considerable. The four-axis aircraft can freely realize hovering and free movement in space, has great flexibility, and in addition, because its simple structure, mechanical stability is good, so low cost, price/performance ratio are very high. But unmanned aerial vehicle receives external environment's influence very easily when using, perhaps leads to the crash because the trouble of maloperation or machine itself, and current unmanned aerial vehicle does not have any safeguard procedures and equipment, in case the collision just can destroy the machine, influences follow-up work, causes certain economic loss.
Disclosure of Invention
Aiming at the defects, the invention provides the falling protection device for the unmanned aerial vehicle, which solves the problem that the unmanned aerial vehicle is easy to damage when falling, lightens the collision impact force when the unmanned aerial vehicle contacts the ground, reduces the collision loss of the unmanned aerial vehicle, and reduces the maintenance and repair cost.
The technical scheme of the invention is as follows:
The utility model provides an unmanned aerial vehicle protection device that falls, unmanned aerial vehicle includes the fuselage, fuselage outside equidistance is provided with the wing, the wing tip is provided with the flabellum, a serial communication port, the fuselage inner chamber is provided with circuit board, receiver, singlechip, gas generator and power, the receiver is used for receiving the remote control instruction to give the singlechip with the instruction transmission, the singlechip is used for receiving the instruction and starts gas generator, the fuselage outer bottom is provided with the holding chamber that comprises bounding wall and baffle, the holding intracavity is provided with the gasbag, gas generator connecting tube, it has the through-hole that supplies the pipe to pass through to open on the fuselage diapire, the pipe accesss to inside the gasbag.
supporting legs are symmetrically arranged around the containing cavity at the outer bottom of the machine body.
The electronic speed regulator is characterized in that an electronic speed regulator and a driving motor are arranged inside the wing, the single chip microcomputer is connected with the electronic speed regulator and used for receiving instructions and sending rotating speed instructions to the electronic speed regulator, and the electronic speed regulator controls the driving motor to work according to the rotating speed instructions to drive the fan blades to rotate.
The front of the machine body is provided with a top cover in threaded connection, and grooves are symmetrically formed in the outer surface of the top cover.
The circuit board, the receiver, the single chip microcomputer and the gas generator are arranged on the bottom wall of the inner cavity of the machine body, and the power supply is arranged on the top wall of the inner cavity of the machine body.
The fuselage is circular.
The power supply is a storage battery or a solar battery.
The inner cavity of the unmanned aerial vehicle body is provided with the circuit board, the receiver, the single chip microcomputer and the gas generator, the receiver can receive a remote control command and send the remote control command to the single chip microcomputer, the single chip microcomputer receives the command and starts the gas generator, the gas generator generates gas which enters the air bag through the guide pipe to inflate the gas generator, the baffle and the coaming plate are opened from inside to outside along with expansion of the air bag, the air bag is ejected to cover the bottom of the unmanned aerial vehicle, so that the unmanned aerial vehicle is buffered when contacting the ground, collision impact force applied to the unmanned aerial vehicle when falling is reduced, and collision damage applied to the unmanned aerial vehicle is reduced.
In addition, an electronic speed regulator and a driving motor are arranged inside the wing, the single chip microcomputer is further used for being connected with the electronic speed regulator, received remote control instructions are converted into rotating speed instructions to be sent to the electronic speed regulator, and the electronic speed regulator controls the driving motor to work according to the rotating speed instructions, so that the fan blades are driven to rotate, and the unmanned aerial vehicle is enabled to obtain ascending or descending flight power. Therefore, the single chip microcomputer and the receiver can simultaneously execute the ascending and descending flight of the unmanned aerial vehicle and trigger the air bag to inflate and pop up before falling, so that two functions of landing protection and the like are provided for the unmanned aerial vehicle, control parts do not need to be additionally arranged, the number of the control parts is reduced, and the cost of the unmanned aerial vehicle is reduced. Simultaneously, it is comparatively accurate effective that the gasbag is aerifyd for controlling to explode, ensures that the gasbag can in time aerify and pop out, for unmanned aerial vehicle provides in time the protection of falling to the ground, avoids causing the protection inefficacy because of aerifing delay, causes unmanned aerial vehicle to receive the collision damage.
Drawings
Fig. 1 is a top view of the drone of the present invention;
Fig. 2 is a front cross-sectional view of the fuselage of the drone of the present invention.
Detailed Description
The conception, the specific structure and the technical effects of the present invention will be further described with reference to the accompanying drawings to fully understand the objects, the features and the effects of the present invention.
Referring to fig. 1 and 2, the unmanned aerial vehicle of the invention comprises a vehicle body 10, the vehicle body 10 is a circular body, wings 20 are arranged on the periphery of the vehicle body 10 at equal intervals, fan blades 21 are arranged at the end parts of the wings 20, a circuit board 11, a receiver 12, a single chip microcomputer 13 and a gas generator 14 are arranged on the bottom wall of an inner cavity of the vehicle body 10, a power supply 15 is arranged on the top wall of the inner cavity of the vehicle body 10 and is used for providing power supply for electronic devices such as the receiver 12 and the single chip microcomputer 13, the power supply 15 is a storage battery or a solar battery, and the solar battery can absorb solar energy in the flight process of the unmanned aerial vehicle and. The fuselage 10 is openly provided with threaded connection's top cap 16, can rotate top cap 16 and open unmanned aerial vehicle fuselage 10 to the electronic components inside fuselage 10 maintain or change. In order to facilitate the taking and placing of the unmanned aerial vehicle, grooves 161 are symmetrically formed in the outer surface of the top cover 16.
The outer bottom of fuselage 10 is provided with the holding chamber that comprises bounding wall 31 and baffle 32, is provided with gasbag 33 in the holding chamber, and gas generator 14 connects pipe 16, and it has the through-hole that supplies pipe 16 to pass through to open on the fuselage 10 diapire, and pipe 16 leads to inside gasbag 33. In order to provide standing supporting force for the unmanned aerial vehicle when falling to the ground, supporting legs 34 are symmetrically arranged around the accommodating cavity at the outer bottom of the machine body 10. An electronic governor 22 and a driving motor 23 are arranged inside the wing 20, and the singlechip 13 is connected with the electronic governor 22. In the daily flight process, the receiver 12 can receive a remote control command sent by a remote controller and send the command to the single chip microcomputer 13, the single chip microcomputer 13 receives the command and sends a rotating speed command to the electronic speed regulator 22, and the electronic speed regulator 22 controls the driving motor 23 to work according to the rotating speed command to drive the fan blades 21 to rotate, so that the unmanned aerial vehicle is controlled to ascend or descend for flight, and corresponding flight tasks are executed.
Feel unmanned aerial vehicle and break down when the operator, can't control the flight direction, or the unmanned aerial vehicle collides other buildings when flying, when about to fall, can utilize the remote controller to send the instruction to receiver 12, singlechip 13 receives the instruction and starts gas generator 14, gas generator 14 produces gas, enter into gasbag 33 through pipe 16, inflate gasbag 33, aerify the inflation back of gasbag 33, prop baffle 32 from inside to outside broken, or prop broken baffle 32 and bounding wall 31 simultaneously, gasbag 33 pops out and covers in the unmanned aerial vehicle bottom, play the cushioning effect when unmanned aerial vehicle strikes ground, collision impact force when lightening unmanned aerial vehicle contact ground, reduce unmanned aerial vehicle's collision damage.
The single chip microcomputer and the receiver can simultaneously execute the two functions of controlling the unmanned aerial vehicle to ascend and descend and triggering the air bag to inflate and pop out before falling, the landing protection is provided for the unmanned aerial vehicle, additional control parts are not needed, the number of the control parts is reduced, and the cost of the unmanned aerial vehicle is reduced. Simultaneously, it is comparatively accurate effective that the gasbag is aerifyd for controlling to explode, ensures that the gasbag can in time aerify and pop out, for unmanned aerial vehicle provides in time the protection of falling to the ground, avoids causing the protection inefficacy because of aerifing delay, causes unmanned aerial vehicle to receive the collision damage.
The above disclosure is only an example of the present invention, but the present invention is not limited thereto, and any variations that can be made by those skilled in the art should fall within the scope of the present invention.
Claims (7)
1. The utility model provides an unmanned aerial vehicle protection device that falls, unmanned aerial vehicle includes fuselage (10), fuselage (10) outside equidistance is provided with wing (20), wing (20) tip is provided with flabellum (21), a serial communication port, fuselage (10) inner chamber is provided with circuit board (11), receiver (12), singlechip (13), gas generator (14) and power (15), receiver (12) are used for receiving remote control instruction to give singlechip (13) with the instruction transmission, singlechip (13) are used for receiving the instruction and start gas generator (14), fuselage (10) outer bottom is provided with the holding chamber that comprises bounding wall (31) and baffle (32), the holding intracavity is provided with gasbag (33), gas generator (14) connecting tube (16), open the through-hole that supplies pipe (16) to pass through on fuselage (10) diapire, the catheter (16) opens into the interior of the balloon (33).
2. The unmanned aerial vehicle fall protection device of claim 1, wherein the supporting legs (34) are symmetrically arranged around the accommodating cavity at the outer bottom of the fuselage (10).
3. The unmanned aerial vehicle fall protection device of claim 1, wherein an electronic governor (22) and a driving motor (23) are arranged inside the wing (20), the single chip microcomputer (13) is connected with the electronic governor (22), the single chip microcomputer (13) is used for receiving instructions and sending rotating speed instructions to the electronic governor (22), and the electronic governor (22) controls the driving motor (23) to work according to the rotating speed instructions to drive the fan blades (21) to rotate.
4. The unmanned aerial vehicle fall protection device of claim 1, wherein the fuselage (10) is provided with a screwed top cover (17) on the front surface, and grooves (171) are symmetrically formed on the outer surface of the top cover (17).
5. The unmanned aerial vehicle fall protection device of claim 1, wherein the circuit board (11), the receiver (12), the single chip microcomputer (13) and the gas generator (14) are disposed on a bottom wall of an inner cavity of the fuselage (10), and the power supply (15) is disposed on a top wall of the inner cavity of the fuselage (10).
6. The unmanned aerial vehicle fall protection device of claim 1, wherein the fuselage (10) is a circular body.
7. The unmanned aerial vehicle fall protection device of claim 1, wherein the power source (15) is a battery or a solar cell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910963563.3A CN110562470A (en) | 2019-10-11 | 2019-10-11 | Unmanned aerial vehicle protection device that falls |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910963563.3A CN110562470A (en) | 2019-10-11 | 2019-10-11 | Unmanned aerial vehicle protection device that falls |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110562470A true CN110562470A (en) | 2019-12-13 |
Family
ID=68784473
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910963563.3A Pending CN110562470A (en) | 2019-10-11 | 2019-10-11 | Unmanned aerial vehicle protection device that falls |
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| Country | Link |
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| CN (1) | CN110562470A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112572814A (en) * | 2020-12-31 | 2021-03-30 | 南京宏光通用航空装备技术有限公司 | Novel damping air bag system adopting inflation mode |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005451A (en) * | 2016-08-03 | 2016-10-12 | 安徽钰龙信息科技有限公司 | Water travel protection system for shipborne unmanned aerial vehicle based on Internet of Things |
| CN205971873U (en) * | 2016-08-23 | 2017-02-22 | 成都翼高九天科技有限公司 | Many rotor unmanned aerial vehicle prevent crashing |
| CN206171828U (en) * | 2016-10-31 | 2017-05-17 | 山西万立科技有限公司 | Unmanned aerial vehicle safety arrangement that falls |
| KR20170129528A (en) * | 2016-05-17 | 2017-11-27 | 엘지이노텍 주식회사 | Airbag Unit and Drone having the same |
| CN108341066A (en) * | 2018-03-30 | 2018-07-31 | 贵州大鸟创新科技有限公司 | Unmanned plane falling protecting device |
| US20190138005A1 (en) * | 2017-11-09 | 2019-05-09 | Arthur Wigell | Unmanned Aerial Vehicle Damage Mitigation System |
| CN210653671U (en) * | 2019-10-11 | 2020-06-02 | 复旦大学 | Unmanned aerial vehicle protection device that falls |
-
2019
- 2019-10-11 CN CN201910963563.3A patent/CN110562470A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20170129528A (en) * | 2016-05-17 | 2017-11-27 | 엘지이노텍 주식회사 | Airbag Unit and Drone having the same |
| CN106005451A (en) * | 2016-08-03 | 2016-10-12 | 安徽钰龙信息科技有限公司 | Water travel protection system for shipborne unmanned aerial vehicle based on Internet of Things |
| CN205971873U (en) * | 2016-08-23 | 2017-02-22 | 成都翼高九天科技有限公司 | Many rotor unmanned aerial vehicle prevent crashing |
| CN206171828U (en) * | 2016-10-31 | 2017-05-17 | 山西万立科技有限公司 | Unmanned aerial vehicle safety arrangement that falls |
| US20190138005A1 (en) * | 2017-11-09 | 2019-05-09 | Arthur Wigell | Unmanned Aerial Vehicle Damage Mitigation System |
| CN108341066A (en) * | 2018-03-30 | 2018-07-31 | 贵州大鸟创新科技有限公司 | Unmanned plane falling protecting device |
| CN210653671U (en) * | 2019-10-11 | 2020-06-02 | 复旦大学 | Unmanned aerial vehicle protection device that falls |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112572814A (en) * | 2020-12-31 | 2021-03-30 | 南京宏光通用航空装备技术有限公司 | Novel damping air bag system adopting inflation mode |
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