CN107972880A - Multi-rotor unmanned aerial vehicle protective device - Google Patents
Multi-rotor unmanned aerial vehicle protective device Download PDFInfo
- Publication number
- CN107972880A CN107972880A CN201711266046.8A CN201711266046A CN107972880A CN 107972880 A CN107972880 A CN 107972880A CN 201711266046 A CN201711266046 A CN 201711266046A CN 107972880 A CN107972880 A CN 107972880A
- Authority
- CN
- China
- Prior art keywords
- aerial vehicle
- unmanned aerial
- rotor unmanned
- bilateral
- bracket
- 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.)
- Pending
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Classifications
-
- 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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- 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
Abstract
The present invention provides a kind of multi-rotor unmanned aerial vehicle protective device.It includes circular fender bracket, multiple connecting brackets and multiple bilateral connectors；Connecting bracket is long strip shape structure, and middle part is fixed in multi-rotor unmanned aerial vehicle between the outer end face of a piece of rack and motor lower end formed with lightening hole, one end of each connecting bracket, and another end surfaces are provided with a bilateral connector；Bilateral connector is round tube shape structure, its both ends is located at the left and right sides of connecting bracket；Circular fender bracket is circular pin, while is inserted in inside multiple bilateral connectors.The agent structure of the present invention is made of carbon fibre material, therefore intensity is high, light-weight.In addition; when being rotated at a high speed due to propeller all in circular fender bracket protection domain; therefore when aircraft collision to wall is when barrier; since circular fender bracket has cushioning effect; therefore propeller and gyroplane body can be prevented to be damaged; aircraft maintenance cost can be greatly reduced, while the people of surrounding can be protected, security is good.
Description
Technical field
The invention belongs to technical field of aerospace, more particularly to a kind of multi-rotor unmanned aerial vehicle protective device.
Background technology
At present, multi-rotor unmanned aerial vehicle take photo by plane, rescue, forest fire protection, many fields such as security protection are widely used,
It is mainly made of rotor fuselage, multiple electric motors and multi-blade propeller, is wherein arranged radially with gyroplane with multi-disc
Rack, every rack outer end upper surface is provided with a motor, and a leaf spiral shell is connected on the output shaft of every motor upper end
Revolve paddle.But there are following point for the multi-rotor unmanned aerial vehicle of this structure：Due under normal circumstances on this unmanned plane without special
The fender bracket of door, therefore during outer flight indoors, high-speed rotating propeller is probably struck on barrier, so not only
Larger damage can be caused to the mechanical structure of aircraft, so that increase maintenance cost, but also can be to the artificial Cheng Bu little of surrounding
Security risk.
The content of the invention
To solve the above-mentioned problems, it is an object of the invention to provide one kind can reduce aircraft accidental damage probability, because
This can reduce maintenance cost, and the multi-rotor unmanned aerial vehicle protective device that security is good.
In order to achieve the above object, multi-rotor unmanned aerial vehicle protective device provided by the invention includes circular fender bracket, multiple
Connecting bracket and multiple bilateral connectors；Wherein connecting bracket is long strip shape structure, middle part made of carbon fibre material
Formed with lightening hole, one end of each connecting bracket is fixed in multi-rotor unmanned aerial vehicle under the outer end face and motor of a piece of rack
Between end, another end surfaces are provided with a bilateral connector；Bilateral connector is round tube shape structure, its both ends is positioned at connection branch
The left and right sides of frame；Circular fender bracket is circular pin, while is inserted in the inside of above-mentioned multiple bilateral connectors.
The circular fender bracket is to be sequentially connected by more arc carbon fiber rod head and the tail and formed, and adjacent two carbon
The junction of fiber rod is located at the inside of bilateral connector, while the middle part of bilateral connector is formed with a screw hole, and utilizes
Screw fixes carbon fiber rod end through the method for screw hole.
The distance between rotor fuselage center is more than propeller in connecting bracket outermost end to the multi-rotor unmanned aerial vehicle
The distance between outer end to rotor fuselage center.
The agent structure of multi-rotor unmanned aerial vehicle protective device provided by the invention is made of carbon fibre material, therefore intensity
Height, light-weight, grammes per square metre only more than 60, and it is versatile.Further, since all in circular fender bracket when propeller rotates at a high speed
, can since circular fender bracket has cushioning effect within protection domain, therefore when aircraft collision to wall is when barrier
Prevent propeller and gyroplane body to be damaged, aircraft maintenance cost can be greatly reduced, and aircraft still can continue to fly
OK, while the people of surrounding can be protected, security is good.In addition, whole protective device uses Structured Design, therefore replace damage
Accessory it is also very easy.
Brief description of the drawings
Fig. 1 is multi-rotor unmanned aerial vehicle protective device use state dimensional structure diagram provided by the invention.
Fig. 2 is connection mounting structure schematic diagram in multi-rotor unmanned aerial vehicle protective device provided by the invention.
Fig. 3 is bilateral connector in multi-rotor unmanned aerial vehicle protective device provided by the invention and circular fender bracket connecting portion
Enlarged drawing.
Embodiment
Multi-rotor unmanned aerial vehicle protective device provided by the invention is carried out specifically with specific embodiment below in conjunction with the accompanying drawings
It is bright.
As shown in Fig. 1-Fig. 3, multi-rotor unmanned aerial vehicle protective device provided by the invention includes circular fender bracket 1, Duo Gelian
Connect stent 2 and multiple bilateral connectors 3；Wherein connecting bracket 2 is long strip shape structure, middle part made of carbon fibre material
Formed with lightening hole 4, one end of each connecting bracket 2 is fixed on the outer end face and electricity of a piece of rack 5 in multi-rotor unmanned aerial vehicle
Between 6 lower end of machine, another end surfaces are provided with a bilateral connector 3；Bilateral connector 3 is round tube shape structure, its both ends position
In the left and right sides of connecting bracket 2；Circular fender bracket 1 is circular pin, while is inserted in the interior of above-mentioned multiple bilateral connectors 3
Portion.
The circular fender bracket 1 is to be sequentially connected by more arc carbon fiber rod head and the tail and formed, and adjacent two
The junction of carbon fiber rod is located at the inside of bilateral connector 3, while the middle part of bilateral connector 3 is formed with a screw hole 7, and
Carbon fiber rod end is fixed using method of the screw through screw hole 7.
2 outermost end of connecting bracket to the distance between rotor fuselage center in multi-rotor unmanned aerial vehicle is more than propeller
The distance between 8 outer ends to rotor fuselage center.
Now multi-rotor unmanned aerial vehicle protective device installation method provided by the invention is described below：First will by staff
One end of each connecting bracket 2 is fixed on the outer end face of a piece of rack 5 in multi-rotor unmanned aerial vehicle, is then installed on the end
One motor 6；One end of an arc carbon fiber rod is inserted in inside one end of a bilateral connector 3, then will afterwards
One end of another arc carbon fiber rod is inserted in inside the other end of the bilateral connector 3, and using screw through screw hole 7
Method fixes the end of two arc carbon fiber rods, and circular fender bracket is formed after all arc carbon fiber rods install
1。
Claims (3)
- A kind of 1. multi-rotor unmanned aerial vehicle protective device, it is characterised in that：It includes circular fender bracket (1), multiple connecting brackets (2) With multiple bilateral connectors (3)；Wherein connecting bracket (2) is long strip shape structure, middle part shape made of carbon fibre material Into there is lightening hole (4), one end of each connecting bracket (2) is fixed on the outer end face of a piece of rack (5) in multi-rotor unmanned aerial vehicle Between motor (6) lower end, another end surfaces are provided with a bilateral connector (3)；Bilateral connector (3) is circular tube shaped knot Structure, its both ends are located at the left and right sides of connecting bracket (2)；Circular fender bracket (1) is circular pin, while is inserted in above-mentioned multiple double The inside of connectors (3).
- 2. multi-rotor unmanned aerial vehicle protective device according to claim 1, it is characterised in that：The circular fender bracket (1) It is to be sequentially connected by more arc carbon fiber rod head and the tail and formed, and the junction of adjacent two carbon fiber rods is located at bilateral company The inside of device (3) is connect, while screw hole (7) is run through in the middle part of bilateral connector (3) formed with a screw hole (7), and using screw Method carbon fiber rod end is fixed.
- 3. multi-rotor unmanned aerial vehicle protective device according to claim 1, it is characterised in that：The connecting bracket (2) is most The distance between rotor fuselage center is more than propeller (8) outer end between rotor fuselage center in outer end to multi-rotor unmanned aerial vehicle Distance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711266046.8A CN107972880A (en) | 2017-12-05 | 2017-12-05 | Multi-rotor unmanned aerial vehicle protective device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711266046.8A CN107972880A (en) | 2017-12-05 | 2017-12-05 | Multi-rotor unmanned aerial vehicle protective device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107972880A true CN107972880A (en) | 2018-05-01 |
Family
ID=62009302
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711266046.8A Pending CN107972880A (en) | 2017-12-05 | 2017-12-05 | Multi-rotor unmanned aerial vehicle protective device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107972880A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018390A (en) * | 2018-09-27 | 2018-12-18 | 中国工程物理研究院总体工程研究所 | Small-sized fixed-wing unmanned plane head restraint |
| CN111516888A (en) * | 2020-03-31 | 2020-08-11 | 深圳市青之鸟科技有限公司 | Unmanned aerial vehicle prevents falling device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203544368U (en) * | 2013-11-06 | 2014-04-16 | 中国民航大学 | Protection device for multi-rotor-wing unmanned plane |
| CN106005393A (en) * | 2016-06-29 | 2016-10-12 | 汇星海科技（天津）有限公司 | Unmanned multi-rotor aircraft protecting cover protection device |
| CN106741990A (en) * | 2016-12-28 | 2017-05-31 | 玉环天润航空机械制造有限公司 | A kind of full machine sheet of helicopter and helicopter protection device |
| CN107200142A (en) * | 2017-05-18 | 2017-09-26 | 东南大学 | Four rotor wing unmanned aerial vehicle protection devices |
| CN206679252U (en) * | 2017-02-22 | 2017-11-28 | 宁夏灏铭科技有限公司 | A kind of multi-rotor unmanned aerial vehicle |
-
2017
- 2017-12-05 CN CN201711266046.8A patent/CN107972880A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203544368U (en) * | 2013-11-06 | 2014-04-16 | 中国民航大学 | Protection device for multi-rotor-wing unmanned plane |
| CN106005393A (en) * | 2016-06-29 | 2016-10-12 | 汇星海科技（天津）有限公司 | Unmanned multi-rotor aircraft protecting cover protection device |
| CN106741990A (en) * | 2016-12-28 | 2017-05-31 | 玉环天润航空机械制造有限公司 | A kind of full machine sheet of helicopter and helicopter protection device |
| CN206679252U (en) * | 2017-02-22 | 2017-11-28 | 宁夏灏铭科技有限公司 | A kind of multi-rotor unmanned aerial vehicle |
| CN107200142A (en) * | 2017-05-18 | 2017-09-26 | 东南大学 | Four rotor wing unmanned aerial vehicle protection devices |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018390A (en) * | 2018-09-27 | 2018-12-18 | 中国工程物理研究院总体工程研究所 | Small-sized fixed-wing unmanned plane head restraint |
| CN109018390B (en) * | 2018-09-27 | 2023-11-10 | 中国工程物理研究院总体工程研究所 | Head protection device of small fixed wing unmanned aerial vehicle |
| CN111516888A (en) * | 2020-03-31 | 2020-08-11 | 深圳市青之鸟科技有限公司 | Unmanned aerial vehicle prevents falling device |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180501 |