CN205916330U - Safety cover of aircraft and take aircraft of safety cover - Google Patents
Safety cover of aircraft and take aircraft of safety cover Download PDFInfo
- Publication number
- CN205916330U CN205916330U CN201620571563.0U CN201620571563U CN205916330U CN 205916330 U CN205916330 U CN 205916330U CN 201620571563 U CN201620571563 U CN 201620571563U CN 205916330 U CN205916330 U CN 205916330U
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- aircraft
- fixed arm
- protective cover
- fixed
- connecting rod
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- 238000009434 installation Methods 0.000 claims abstract description 43
- 230000001681 protective effect Effects 0.000 claims description 57
- 238000000465 moulding Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000004069 differentiation Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/30—Constructional aspects of UAVs for safety, e.g. with frangible components
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model relates to a safety cover of aircraft and take aircraft of safety cover, the safety cover of aircraft include shield ontology and set up in fixed arm in the shield ontology, the first end of fixed arm with shield ontology fixed connection, the second end of fixed arm is equipped with the first connecting portion of being connected with the aircraft. The protection cover structural of this aircraft is simple, and the safety of revolving the oar of aircraft is guaranteed to the erection joint of be convenient for aircraft and safety cover, enlarges the applied scene of aircraft, this aircraft of taking the safety cover can effectively improve the safety of revolving the oar of aircraft through the installation safety cover, enlarges the applied scene of aircraft.
Description
Technical field
This utility model is related to vehicle technology field, more particularly to a kind of protective cover of aircraft and with protective cover
Aircraft.
Background technology
The rotation oar great majority of existing aircraft expose, and the rotation oar of the high-speed rotation exposing is easy to hurt people or hurts
The article of surrounding, after colliding, rotation oar is easy to damage simultaneously, or even causes aircraft body to fall and lead to damage.
Minority aircraft protects rotation oar by arranging protection device, but it there is also protection device complex structure, installs
Waste time and energy, protected by multiple guard rings of setting simultaneously, increase the take-off weight of aircraft on the contrary, waste aircraft
Kinetic energy, be unfavorable for the long-time use of aircraft.
Content of the invention
Based on this it is necessary to provide a kind of protective cover of aircraft and the aircraft with protective cover, the protection of this aircraft
Cover structure is simple, is easy to aircraft and is connected with the installation of protective cover it is ensured that the safety of the rotation oar of aircraft, expands answering of aircraft
Use scene；This aircraft with protective cover passes through to install the safety of the rotation oar that protective cover can effectively improve aircraft, expands flight
The application scenarios of device.
Its technical scheme is as follows:
A kind of protective cover of aircraft, including protection cover body and be arranged at the intrinsic fixed arm of described protective cover, institute
State fixed arm first end to be fixedly connected with described protection cover body, the second end of described fixed arm is provided with the being connected with aircraft
One connecting portion.
Below further technical scheme is illustrated:
Wherein in an embodiment, described first connecting portion is provided with motor installation through-hole and fixture installing hole, described
Motor installation through-hole and fixture installing hole interval setting.
Wherein in an embodiment, described first connecting portion is additionally provided with the draw-in groove of the horn installing aircraft, described card
The bottom of groove is provided with described motor installation through-hole and described fixture installing hole.
Wherein in an embodiment, described protection cover body is provided with multiple connectors and multiple connecting rod, described connection
Part is provided with least three installation portions, and a described installation portion corresponds to a described connecting rod, one end of described connecting rod with wherein
The installation portion of one described connector connects, the other end is connected with the installation portion of connector another described；One described connection
All installation portions of part respectively with the cooperation of a corresponding described connecting rod, realize this connector and other at least three institutes
State connector to connect, a described installation portion corresponds to a described connector；Multiple described connectors and multiple described connecting rods
Connection cooperatively form polyhedral structure.
Wherein in an embodiment, described fixed arm one end is connected with connecting rod at least one described.
Wherein in an embodiment, described fixed arm includes the first fixed arm and the second fixed arm, and described first is fixing
The first end of arm is connected with least one connecting rod, and the first end of described second fixed arm is connected with least three connecting rods.
Wherein in an embodiment, also include installed part, described fixed arm passes through this installed part with described connecting rod even
Connect.
Wherein in an embodiment, described installed part is integrally formed with described fixed arm.
Wherein in an embodiment, described fixed arm at least two, described at least two, fixed arm interval is fixed on
In described protection cover body.
Wherein in an embodiment, described fixed arm at least three, fixed arm uniform intervals described at least three are solid
In described protection cover body.
Wherein in an embodiment, described fixed arm is four, and four described fixed arm circumference uniform intervals are fixed on
The middle part of described protection cover body, and the centrage of two described fixed arms being oppositely arranged is in same straight line.
The technical program additionally provides a kind of aircraft with protective cover, including the protective cover of above-mentioned aircraft, also wraps
Include aircraft body, described aircraft body is provided with the second connecting portion being connected with described first connecting portion.
Below further technical scheme is illustrated:
Wherein in an embodiment, described aircraft body is additionally provided with four rotor arms, and described fixed arm is four, and one
Individual described rotor arm is connected with a described fixed arm, and four described rotor arms are equipped with described second connecting portion.
Wherein in an embodiment, described aircraft body is additionally provided with the fixed plate for carrying head, described fixation
Plate is fixed with described protection cover body by described connecting rod.
" first " described in above-mentioned this utility model, " second " do not represent specific quantity and order, are only used for name
The differentiation claiming.
Above-mentioned the beneficial effects of the utility model:
When the protective cover of above-mentioned aircraft uses, aircraft is fixedly connected with the first connecting portion of fixed arm, and by being somebody's turn to do
Fixed arm is connected with described protection cover body, and then aircraft is fixed in protective cover, can be prevented effectively from using this protective cover
The rotation oar of aircraft hurts people or the article hurting surrounding；Realize the company of aircraft and protective cover using fixed arm simultaneously
Connect, simplify the mounting structure of the guarantee device of aircraft, reduce the take-off weight of aircraft as far as possible, improve aircraft band and protect
The time that guard shield runs.The protection cover structure of this aircraft is simple, is easy to aircraft and is connected it is ensured that flying with the installation of protective cover
The safety of the rotation oar of device, expands the application scenarios of aircraft.
When above-mentioned aircraft with protective cover uses, by the rotation oar that this protective cover can be prevented effectively from aircraft hurt people or
Hurting the article of surrounding it is ensured that revolving the safety of oar when aircraft runs, expanding the application scenarios of aircraft.
Brief description
Fig. 1 is the structural representation of the protective cover of aircraft described in the utility model；
Fig. 2 is the half-section diagram that fixed arm described in the utility model is connected with aircraft；
Fig. 3 is the structural representation of the aircraft with protective cover described in the utility model.
Description of reference numerals:
100th, protect cover body, 110, connector, 112, installation portion, 120, connecting rod, 200, fixed arm, 202, first
End, the 204, second end, 210, first connecting portion, 212, motor installation through-hole, 214, fixture installing hole, 216, draw-in groove, 220,
First fixed arm, the 230, second fixed arm, 240, installed part, 300, aircraft body, 310, second connecting portion, 320, rotor
Arm, 330, motor, 340, fixture, 350, fixed plate, 360, head.
Specific embodiment
For making the purpose of this utility model, technical scheme and advantage become more apparent, below in conjunction with accompanying drawing and specifically in fact
Apply mode, this utility model is described in further detail.It should be appreciated that specific embodiment described herein
Only in order to explain this utility model, do not limit protection domain of the present utility model.
As shown in figure 1, a kind of protective cover of aircraft described in the utility model, including protection cover body 100 and setting
Fixed arm 200 in protection cover body 100, fixed arm 200 first end 202 is fixedly connected with protection cover body 100, fixed arm
200 the second end 204 is provided with the first connecting portion 210 being connected with aircraft.
As shown in Figures 1 to 3, when the protective cover of this aircraft uses, the first connecting portion 210 of aircraft and fixed arm 200
It is fixedly connected, and is connected with protection cover body 100 by this fixed arm 200, and then aircraft is fixed in protective cover, utilize
The rotation oar that this protective cover can be prevented effectively from aircraft hurts people or the article hurting surrounding；Utilize fixed arm 200 simultaneously
Realize the connection of aircraft and protective cover, simplify the mounting structure of the guarantee device of aircraft, improve installation rate, to the greatest extent simultaneously
The take-off weight of aircraft may be reduced, improve the time that aircraft runs with protective cover.The protection cover structure letter of this aircraft
Single, it is easy to aircraft and is connected with the installation of protective cover it is ensured that the safety of the rotation oar of aircraft, expand the application scenarios of aircraft.
This fixed arm 200 can be detachable split type fixation side with the mode that is fixedly connected of protection cover body 100
Formula, the integrated connection mode also being formed in one；The mode that is fixedly connected of this first connecting portion 210 and aircraft, Ke Yishi
Be screwed connection, buckle is fixedly connected, sells and be admittedly fixedly connected, and riveting is fixedly connected etc. is fixedly connected mode.As Fig. 1 and 3 institute
Show, first connecting portion 210 is provided with motor installation through-hole 212 and fixture installing hole 214, motor installation through-hole 212 and fixture
The rotation oar motor of aircraft is fixed on first connecting portion 210 using this motor installation through-hole 212 by installing hole 214 interval setting
On, and by fixture and this fixture installing hole 214, aircraft is fixed in first connecting portion 210, and then achieve winged
Row device is fixedly connected with fixed arm 200, simultaneously without interference with the operation of rotation oar；This fixture can be latch or bolt, excellent
Choosing, fixture is bolt, and fixture passes through fixture installing hole 214 and aircraft bolt connection；Further, first even
Socket part 210 is additionally provided with the draw-in groove 216 of the horn installing aircraft, and the bottom of draw-in groove 216 is provided with motor installation through-hole 212 and fixes
Part installing hole 214, by the cooperation of this draw-in groove 216 and the horn of aircraft, outside the motor of motor installation through-hole 212 and aircraft
The cooperation of shell, realizes the horn of this aircraft and installs positioning with fixed arm 200, recycles bolt to be locked it is ensured that aircraft
It is connected reliability with protective cover, when aircraft runs, will not rock.
This protection cover body 100 can be any stereochemical structure with multiple through holes, and this through hole can be polygon, circle
Shape, ellipse etc., this protection cover body 100 can be assembled by summit connector 110 and rod-shaped material or by carving
The integrally formed other modes such as carve or be molded to be made；Preferably, as shown in Fig. 1 and 2, protection cover body 100 is provided with many
Individual connector 110 and multiple connecting rod 120, connector 110 is provided with least three installation portions 112, an installation portion 112 corresponding
Individual connecting rod 120, one end of connecting rod 120 is connected with the installation portion 112 of one of connector 110, the other end and another
The installation portion 112 of connector 110 connects, all installation portions 112 of a connector 110 respectively with a corresponding connecting rod
120 cooperation, realize this connector 110 and be connected with least three other connectors 110, corresponding one of installation portion 112
Connector 110；Multiple connectors 110 cooperatively form polyhedral structure with the connection of multiple connecting rods 120, using aircraft when,
It is easy to user combined connection component 110 and connecting rod 120 forms this protection cover body 100, when carrying aircraft, be easy to user
This connector 110 of disassembly ＆ recycling and connecting rod 120, this polyhedral structure is preferably spherical shape polyhedral structure, and this polyhedron is tied
Through hole be shape changeable, preferably triangle, the polyhedral structure stability now constituting preferably, improves protection cover body 100
Impact strength it is ensured that aircraft rotation oar safety；Further, described fixed arm one end and at least one described connecting rod
Connect, further, fixed arm 200 includes the first fixed arm 220 and the second fixed arm 230, the first of the first fixed arm 220
End is connected with least one connecting rod 120, and the first end of the second fixed arm 230 is connected with least three connecting rods 120, utilizes the
The first end of two fixed arms 230 substitutes connector 110 and forms this protection cover body 100 to combine, you can strengthen the second fixed arm
230 with protection cover body 100 bonding strength, again can be lifted protection cover body 100 overall aesthetics it is preferred that this first
The first end of the first end of fixed arm 220 and the second fixed arm 230 is all connected with six connecting rods 120；In another embodiment
In, the protective cover of this aircraft also includes installed part 240, and fixed arm 200 is connected with connecting rod 120 by this installed part 240, profit
Fixed it is preferred that installed part 240 and fixed arm with the installation that this installed part 240 facilitates implementation fixed arm 200 and connecting rod 120
200 are integrally formed, and are easy to obtain installed part 240 and fixed arm 200 using integral molding techniques manufacture, and reduce assembly process,
Preferably this installed part 240 is connected with six connecting rods 120, substitutes one of connector 110, the now company of fixed arm 200
Connect the most reliable, and protect cover body more attractive in appearance.
This fixed arm 200 at least two, at least two fixed arm 200 interval is fixed in protection cover body 100, according to
The feature of aircraft and need to arrange quantity and the position of this fixed arm 200；Further, fixed arm 200 at least three, extremely
Few three fixed arm 200 uniform intervals are fixed in protection cover body 100, above fixed arm 200 and aircraft casing, at least
Three fixed arms 200 are connected the balance it is ensured that between aircraft and protective cover with the casing of aircraft；Preferably, consolidate for four
Determine the middle part that the circumferential uniform intervals of arm 200 are fixed on protection cover body 100, and the center of two fixed arms being oppositely arranged 200
In same straight line, such as quadrotor is provided with four rotor arms 320 to line, and fixed arm 200 is four, rotor arm 320 with
One fixed arm 200 connects, and this aircraft can be made to be arranged at the center of protective cover, make center and the protective cover of aircraft as far as possible
Center superposition, make the process of aircraft flight more steady.
As shown in Fig. 1 and 2, in a preferred embodiment, the protective cover of this quadrotor include protect cover body 100 and
It is arranged at the fixed arm 200 in protection cover body 100；Protection cover body 100 is provided with multiple connectors 110 and multiple connecting rod
120, connector 110 is provided with six installation portions 112, and an installation portion 112 corresponds to a connecting rod 120, one end of connecting rod 120
It is connected with the installation portion 112 of one of connector 110, the other end is connected with the installation portion 112 of another connector 110, one
The cooperation with corresponding connecting rod 120 respectively of six installation portions 112 of individual connector 110, realizes this connector 110 and other six
Individual connector 110 connects, and an installation portion 112 corresponds to a connector 110；Multiple connectors 110 and multiple connecting rods 120
Connect and cooperatively form Globate polyhedron structure, the through hole of this Globate polyhedron structure is triangle；Fixed arm 200 includes two
One fixed arm 220 and two the second fixed arms 230, the first end of the first fixed arm 220 is connected with a connecting rod 120, and second
The first end of fixed arm 230 is connected with six connecting rods 120, and two the first fixed arms 220 and two the second fixed arms 230 are circumferential
Uniform intervals are fixed on the middle part of protection cover body 100, and the centrage of two the first relative fixed arms 220 is with always
, in same straight line, a rotor arm 320 and a fixed arm 200 are even for line, the centrage of two the second relative fixed arms 230
Connect it is ensured that this aircraft is arranged at the center of protective cover, make the center of aircraft and the center superposition of protective cover as far as possible, make
The process of aircraft flight is more steady.
As shown in Figures 1 to 3, a kind of aircraft with protective cover described in the utility model, including above-mentioned aircraft
Protective cover, also includes aircraft body 300, and aircraft body 300 is provided with the second connecting portion being connected with first connecting portion 210
310.
As shown in Figure 2,3, when this aircraft with protective cover uses, the rotation of aircraft can be prevented effectively from by this protective cover
Oar hurt people or the article that hurt surrounding it is ensured that when aircraft runs rotation oar safety, expand the applied field of aircraft
Scape.
Preferably, this aircraft body 300 is additionally provided with four rotor arms 320, and fixed arm 200 is four, four fixed arms
200 circumferential uniform intervals are fixed on the middle part of protection cover body 100, and the centrage of two arms 200 that are relatively fixed is same
Straight line, a rotor arm 320 is connected with a fixed arm 200, and four rotor arms 320 are equipped with second connecting portion 310, by
One connecting portion 210 is connected, with second connecting portion 310, the center making this aircraft be arranged at protective cover, makes as far as possible in aircraft
The heart and the center superposition of protective cover, make the process of aircraft flight more steady；Further, aircraft body 300 is provided with use
In the fixed plate 350 carrying head, fixed plate 350 is passed through connecting rod 210 and is fixed with protection cover body 100, realizes this head
Install and carry.
Each technical characteristic of embodiment described above can arbitrarily be combined, for making description succinct, not to above-mentioned reality
The all possible combination of each technical characteristic applied in example is all described, as long as however, the combination of these technical characteristics is not deposited
In contradiction, all it is considered to be the scope of this specification record.
Embodiment described above only have expressed several embodiments of the present utility model, and its description is more concrete and detailed,
But therefore can not be interpreted as the restriction to utility model patent scope.It should be pointed out that the common skill for this area
For art personnel, without departing from the concept of the premise utility, some deformation can also be made and improve, these broadly fall into
Protection domain of the present utility model.Therefore, the protection domain of this utility model patent should be defined by claims.
Claims (13)
1. a kind of protective cover of aircraft is it is characterised in that include protection cover body and to be arranged at described protective cover intrinsic
Fixed arm, described fixed arm first end is fixedly connected with described protection cover body, and the second end of described fixed arm is provided with and flies
The first connecting portion that device connects.
2. the protective cover of aircraft according to claim 1 is it is characterised in that described first connecting portion is provided with motor installation
Through hole and fixture installing hole, described motor installation through-hole and fixture installing hole interval setting.
3. aircraft according to claim 2 protective cover it is characterised in that described first connecting portion be additionally provided with installation fly
The draw-in groove of the horn of row device, the bottom of described draw-in groove is provided with described motor installation through-hole and described fixture installing hole.
4. the protective cover of aircraft according to claim 1 is it is characterised in that described protection cover body is provided with multiple connections
Part and multiple connecting rod, described connector is provided with least three installation portions, and a described installation portion corresponds to a described connecting rod,
One end of described connecting rod is connected with the installation portion of one of described connector, the peace of the other end and another described connector
Dress portion connects；All installation portions of one described connector respectively with the cooperation of a corresponding described connecting rod, realize this company
Fitting is connected with connector described in other at least three, and a described installation portion corresponds to a described connector；Multiple described
Connector cooperatively forms polyhedral structure with the connection of multiple described connecting rods.
5. the protective cover of aircraft according to claim 4 is it is characterised in that described fixed arm one end and at least one institute
State connecting rod to connect.
6. it is characterised in that also including installed part, described fixed arm leads to the protective cover of aircraft according to claim 4
Cross this installed part to be connected with described connecting rod.
7. the protective cover of aircraft according to claim 6 is it is characterised in that described installed part and described fixed arm one
Molding.
8. the protective cover of the aircraft according to any one of claim 1-7 is it is characterised in that described fixed arm is at least two
Individual, fixed arm interval described at least two is fixed in described protection cover body.
9. the protective cover of aircraft according to claim 8 is it is characterised in that described fixed arm is at least three, at least
Three described fixed arm uniform intervals are fixed in described protection cover body.
10. the protective cover of aircraft according to claim 8 is it is characterised in that described fixed arm is four, described in four
Fixed arm circumference uniform intervals are fixed on the middle part of described protection cover body, and in two described fixed arms being oppositely arranged
Heart line is in same straight line.
A kind of 11. aircraft with protective cover are it is characterised in that include the guarantor of the aircraft described in any one of claim 1-8
Guard shield, also includes aircraft body, and described aircraft body is provided with the second connecting portion being connected with described first connecting portion.
12. aircraft with protective cover according to claim 11 are it is characterised in that described aircraft body is additionally provided with four
Individual rotor arm, described fixed arm is four, and a described rotor arm is connected with a described fixed arm, and four described rotor arms are equal
It is provided with described second connecting portion.
13. aircraft with protective cover according to claim 11 or 12 are it is characterised in that described aircraft body also sets
There is the fixed plate for carrying head, described fixed plate is fixed with described protection cover body by described connecting rod.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620571563.0U CN205916330U (en) | 2016-06-14 | 2016-06-14 | Safety cover of aircraft and take aircraft of safety cover |
| PCT/CN2017/087894 WO2017215550A1 (en) | 2016-06-14 | 2017-06-12 | Safety cover of aircraft and aircraft with safety cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620571563.0U CN205916330U (en) | 2016-06-14 | 2016-06-14 | Safety cover of aircraft and take aircraft of safety cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205916330U true CN205916330U (en) | 2017-02-01 |
Family
ID=57877514
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620571563.0U Active CN205916330U (en) | 2016-06-14 | 2016-06-14 | Safety cover of aircraft and take aircraft of safety cover |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN205916330U (en) |
| WO (1) | WO2017215550A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107161344A (en) * | 2017-05-09 | 2017-09-15 | 渤海大学 | It is a kind of to realize the quadrotor that six degree of freedom is controlled entirely |
| WO2017215550A1 (en) * | 2016-06-14 | 2017-12-21 | 亿航智能设备（广州）有限公司 | Safety cover of aircraft and aircraft with safety cover |
| CN108082506A (en) * | 2018-01-26 | 2018-05-29 | 锐合防务技术（北京）有限公司 | Unmanned vehicle |
| CN108706095A (en) * | 2018-04-16 | 2018-10-26 | 国网浙江省电力有限公司 | A kind of miniature multi-rotor unmanned aerial vehicle with anticollision device, collision-prevention device of applicable raceway groove inspection |
| CN109533333A (en) * | 2018-09-05 | 2019-03-29 | 徐州万科标识系统工程有限公司 | Primary-secondary type unmanned plane believes lodge and its sends part method |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202686759U (en) * | 2012-06-26 | 2013-01-23 | 防灾科技学院 | Four-wing flight vehicle |
| CN104129497A (en) * | 2013-05-03 | 2014-11-05 | 湖北文理学院 | Multi-rotor aircraft with ball-shaped external protective bracket |
| CN203318681U (en) * | 2013-05-29 | 2013-12-04 | 南京信息工程大学 | Four-rotor unmanned aerial vehicle provided with spheroidal protection cover |
| US9457901B2 (en) * | 2014-04-22 | 2016-10-04 | Fatdoor, Inc. | Quadcopter with a printable payload extension system and method |
| CN204726663U (en) * | 2015-06-15 | 2015-10-28 | 汕头市亨迪实业有限公司 | Universal gravity aircraft |
| CN205916330U (en) * | 2016-06-14 | 2017-02-01 | 广州亿航智能技术有限公司 | Safety cover of aircraft and take aircraft of safety cover |
-
2016
- 2016-06-14 CN CN201620571563.0U patent/CN205916330U/en active Active
-
2017
- 2017-06-12 WO PCT/CN2017/087894 patent/WO2017215550A1/en active Application Filing
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017215550A1 (en) * | 2016-06-14 | 2017-12-21 | 亿航智能设备（广州）有限公司 | Safety cover of aircraft and aircraft with safety cover |
| CN107161344A (en) * | 2017-05-09 | 2017-09-15 | 渤海大学 | It is a kind of to realize the quadrotor that six degree of freedom is controlled entirely |
| CN108082506A (en) * | 2018-01-26 | 2018-05-29 | 锐合防务技术（北京）有限公司 | Unmanned vehicle |
| CN108706095A (en) * | 2018-04-16 | 2018-10-26 | 国网浙江省电力有限公司 | A kind of miniature multi-rotor unmanned aerial vehicle with anticollision device, collision-prevention device of applicable raceway groove inspection |
| CN109533333A (en) * | 2018-09-05 | 2019-03-29 | 徐州万科标识系统工程有限公司 | Primary-secondary type unmanned plane believes lodge and its sends part method |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2017215550A1 (en) | 2017-12-21 |
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