CN104787298B - Aircraft - Google Patents
Aircraft Download PDFInfo
- Publication number
- CN104787298B CN104787298B CN201510162607.4A CN201510162607A CN104787298B CN 104787298 B CN104787298 B CN 104787298B CN 201510162607 A CN201510162607 A CN 201510162607A CN 104787298 B CN104787298 B CN 104787298B
- Authority
- CN
- China
- Prior art keywords
- support element
- aircraft
- sensing component
- bottom wall
- mounting plate
- 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.)
- Expired - Fee Related
Links
- 238000013016 damping Methods 0.000 claims description 19
- 230000035939 shock Effects 0.000 claims description 17
- 239000006096 absorbing agent Substances 0.000 claims description 16
- 239000011229 interlayer Substances 0.000 claims description 16
- 238000005259 measurement Methods 0.000 claims description 9
- 230000000712 assembly Effects 0.000 claims description 7
- 238000000429 assembly Methods 0.000 claims description 7
- 239000010410 layer Substances 0.000 claims 1
- 239000000306 component Substances 0.000 description 33
- 239000006260 foam Substances 0.000 description 13
- 239000000463 material Substances 0.000 description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 3
- 239000000084 colloidal system Substances 0.000 description 3
- 239000000741 silica gel Substances 0.000 description 3
- 229910002027 silica gel Inorganic materials 0.000 description 3
- 229920002379 silicone rubber Polymers 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 239000013013 elastic material Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000012858 resilient material Substances 0.000 description 2
- 239000004945 silicone rubber Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 229920002943 EPDM rubber Polymers 0.000 description 1
- 229920005830 Polyurethane Foam Polymers 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 125000003342 alkenyl group Chemical group 0.000 description 1
- -1 aminomethyl phenyl Chemical group 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- HIHIPCDUFKZOSL-UHFFFAOYSA-N ethenyl(methyl)silicon Chemical compound C[Si]C=C HIHIPCDUFKZOSL-UHFFFAOYSA-N 0.000 description 1
- 229920005560 fluorosilicone rubber Polymers 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 150000002825 nitriles Chemical class 0.000 description 1
- 239000005060 rubber Substances 0.000 description 1
Landscapes
- Gyroscopes (AREA)
- Vibration Prevention Devices (AREA)
Abstract
A kind of aircraft, including fuselage and the sensing component and support element that are set in the fuselage, the fuselage includes main casing.The main casing includes bottom wall and the side wall that is connected with the bottom wall, and the side wall surrounds receiving space jointly with the bottom wall.The sensing component and support element are contained in the receiving space, and the support element is connected on the bottom wall, and the sensing component is set on the support element and has gap between the side wall.The sensing component will be set on the bottom wall of fuselage using support element and the side wall of the sensing component and fuselage is made to keep gap by the aircraft, can effectively reduce or eliminate that the sensing component is subject to is parallel to shaking for the bottom wall direction.
Description
Technical field
The present invention relates to aircraft field more particularly to a kind of aircraft for having sensing component.
Background technology
Sensing component, such as Inertial Measurement Unit（Inertial Measurement Unit, IMU）, it is the important of aircraft
Element, flight attitude, orientation and other environmental information for perceiving aircraft.Existing aircraft is generally by the sensing group
On the body shell of the directly fixed aircraft of part, however, since aircraft can be because of motor, turn of propeller in flight course
It moves and/or meets with air-flow and generate vibrations, this vibrations can be transferred to the sensing component by the fuselage special body size, to shadow
The perceived accuracy for ringing the sensing component, further influences the execution of the normal tasks of the aircraft, severe patient it will cause
The damage of the sensing component.
Invention content
In view of this, it is necessary to provide a kind of aircraft that can effectively reduce the vibrations that sensing component is subjected to.
A kind of aircraft, including fuselage and the sensing component and support element that are set in the fuselage, the fuselage packet
Include main casing.The main casing includes bottom wall and the side wall that is connected with the bottom wall, and the side wall encloses jointly with the bottom wall
At receiving space.The sensing component and support element are contained in the receiving space, and the support element is connected to the bottom wall
On, the sensing component is set on the support element and has gap between the side wall.
Further, the aircraft further includes shock absorber part, and the shock absorber part is set to the sensing component and the branch
Between support member.
Further, the shock absorber part includes damping interlayer, the damping interlayer, the support element include top plate and with
The side plate of the top plate connection, the top plate include towards the top surface of the sensing component, and the damping interlayer is set to described
On top surface.
Further, the sensing component includes connector, and the sensing component is connected to the branch by the connector
In support member, the shock absorber part includes the first beam, and first beam is sheathed on the corresponding connector and is arranged
Between the sensing component and the support element.
Further, the sensing component includes connector, and the sensing component is connected to the branch by the connector
In support member, the shock absorber part includes the second beam corresponding to the connector, and second beam is arranged corresponding institute
It states on connector and is set to the sensing component on a side surface of the support element.
Further, the sensing component includes mounting plate and the sensing element that is fixed on the mounting plate, the peace
Loading board is connect with the support element.
Further, the sensing element is Inertial Measurement Unit.
Further, it is provided with damper element in the Inertial Measurement Unit.
Further, the first connecting hole is offered on the bottom wall, is offered on the support element corresponding to described first
Second connecting hole of connecting hole passes through first connecting hole and second connecting hole between the support element and the bottom wall
Cooperation be connected with each other.
Further, the aircraft is the rotor craft with rotor assemblies, and the fuselage includes multiple support arm shells
Body, the branch arm housing are set to around the main casing, are used to support the rotor assemblies of the aircraft.
Compared with the existing technology, the sensing component will be set on the bottom wall of fuselage by the aircraft using support element
And the side wall of the sensing component and fuselage is made to keep gap, it can effectively reduce or eliminate that the sensing component is subject to is flat
Row is in the vibrations in the bottom wall direction.
Description of the drawings
Fig. 1 is the stereogram exploded view of the aircraft of embodiment of the present invention.
Fig. 2 is another angular views of the aircraft of Fig. 1.
Fig. 3 and Fig. 4 is the assembling schematic diagram of the aircraft of Fig. 1.
Main element symbol description
| Aircraft | 100 |
| Fuselage | 10 |
| Main casing | 11 |
| Bottom wall | 111 |
| First connecting hole | 1111 |
| Side wall | 112 |
| Receiving space | 113 |
| Branch arm housing | 12 |
| Landing chassis | 13 |
| Inertial Measurement Unit component | 20 |
| Sensing element | 21 |
| Mounting plate | 22 |
| First surface | 221 |
| Second surface | 222 |
| First through hole | 223 |
| Support element | 23 |
| Top plate | 231 |
| Top surface | 2311 |
| Connecting pole | 2312 |
| Internal thread hole | 2312a |
| Side plate | 232 |
| Connection sheet | 233 |
| Second connecting hole | 2331 |
| Shock absorber part | 24 |
| Damping interlayer | 241 |
| First beam | 242 |
| Second through-hole | 2421 |
| Second beam | 243 |
| Third through-hole | 2431 |
| Connector | 25 |
| Bar portion | 251 |
| Cap portion | 252 |
| Rotor assemblies | 30 |
| Colloid | 40 |
Following specific implementation mode will be further illustrated the present invention in conjunction with above-mentioned attached drawing.
Specific implementation mode
It please refers to Fig.1 and Fig. 2, the aircraft 100 described in embodiment of the present invention includes fuselage 10, sensing component 20, branch
Support member 23 and shock absorber part 24.
The fuselage 10 is the load bearing component of the aircraft 100, and 10 outer surface of the fuselage and/or inside are for carrying
The function module of the aircraft 100, the function module can include but is not limited to the Inertial Measurement Unit（It is not shown）、
Image acquiring module（It is not shown）, rotor assemblies 30, height sensor（It is not shown）, temperature sensor（It is not shown）Deng.
The fuselage 10 includes main casing 11, branch arm housing 12 and landing chassis 13.The main casing 11 and the branch
Arm housing 12 is all made of the structure that upper and lower two parts mutually fasten, and the main casing 11 and the branch arm housing are only shown in figure
12 lower half portion.In present embodiment, the main casing 11 is an integral molding structure with the branch arm housing 12, Ke Yili
Removably interconnection may be used with the branch arm housing 12 in solution, in other implementations, the main casing 11,
Such as it is threadedly coupled, is connected together, welding, riveting, glued connection etc..
The main casing 11 includes bottom wall 111 and the side wall 112 being connected with the bottom wall.The bottom wall 111 is for connecting
It connects and carries the sensing component 20.The bottom wall 111 is parallel with the plane where the X of coordinate system, Y-axis in figure.The bottom wall
The first connecting hole 1111 for connecting the sensing component 20 is offered on 111.The side wall 112 surrounds the bottom wall 111
And be arranged, the side wall 112 surrounds a receiving space 113 for accommodating the sensing component 20 jointly with the bottom wall 111.
The branch arm housing 12 is used to support the rotor assemblies 30.In present embodiment, the aircraft 100 is four rotations
Rotor aircraft, therefore the quantity of the branch arm housing 12 is four.It is appreciated that according to different demands, the branch arm housing 12
Quantity can make different variations according to the difference of the type of the aircraft 100, for example, six, eight, 12
Deng, even, the aircraft 100 be non-rotor craft in the case of, the branch arm housing 12 can also omit.
The landing chassis 13 when the aircraft 100 lands for supporting the aircraft 100.In present embodiment,
The quantity of the landing chassis 13 is two, and each described landing chassis is substantially in " U " shapes.
The sensing component 20 includes sensing element 21 and mounting plate 22.The sensing element 21 is the sensing component
20 core component may include inside acceleration transducer, gyroscope（Figure does not indicate）And/or or other are described for perceiving
The sensor of aircraft ambient parameters.In present embodiment, the sensing element 21 is Inertial Measurement Unit.The sensing
Element 21 is set to electrically on the mounting plate 22.The mounting plate 22 is used for the sensing component and outer member
（It is not shown）Electrical connection.The mounting plate 22 includes first surface 221 and the second surface opposite with the first surface 221
222, the sensing element 21 is set on the first surface 221.It is offered on the mounting plate 22 multiple through described the
The first through hole 223 of one surface 221 and the second surface 222.In present embodiment, the quantity of the first through hole 223
It is four.
The support element 23 is used to the sensing component 20 being supported in the bottom wall 111 of the fuselage 10.It is described
Support element 23 includes top plate 231 and the side plate 232 being connected with the top plate 231.The top plate 231 includes described in a direction
The top surface 2311 of mounting plate 22 is provided with multiple connecting poles 2312 corresponding to the first through hole 223 on the top surface 2311.
The connecting pole 2312 is convexly equipped on the top surface 2311.Each described connecting pole 2312 is opened up there are one internal thread hole
2312a, the internal thread hole 2312a approximately axially perpendicular to the top surface 2311.In present embodiment, each described company
It is in hollow cylindrical to connect column 2312 substantially.It is appreciated that each described connecting pole 2312 or hollow elliptic cylindrical shape,
Hollow prism shape etc., moreover, the shape of multiple connecting poles 2312 can be the same or different.The support element 23 also may be used
To be made of elastic material, to achieve the effect that bumper and absorbing shock, shock absorber part 24 can be saved at this time.Certainly also can be in support element 23
When elastic material, shock absorber part 24 is still used, coordinates damping by multiple shock-damping structures.
The side plate 232 substantially falls in the side that the top surface 2311 is connected to the top plate 231.Each described side plate
A connection sheet 233 is arranged in 232 one end far from the top plate 231.The connection sheet 233 is approximately perpendicular to corresponding side plate
232 protrude from the outer surface of corresponding side plate.The connection sheet 233 offers corresponding to first connecting hole 1111
Two connecting holes 2331.
The shock absorber part 24 is used to reducing or eliminating the unexpected vibrations suffered by the sensing component 20.It is described to subtract
It includes damping interlayer 241, the first beam 242 and the second beam 243 to shake part 24.The damping interlayer 241, the first damping
Pad 242 and second beam 243 are made of flexible resilient material, and specifically, the flexible resilient material can be
Foam, foam, silica gel, rubber etc., for example, PU foams, EPE foams, XPE foams, EPP foams, IXPE foams, PORON foams,
CR foams, EVA foams, bridge formation PE foams, SBR foams, EPDM foams, silica gel are methyl vinyl silicone rubber, aminomethyl phenyl second
Alkenyl silicon rubber, fluorine silicone rubber, nitrile silicone rubber etc..The damping interlayer 241, first beam 242 and described second
The material selection of beam 243 is according to depending on different demands, such as the vibroseis that is subjected to according to the aircraft 100 shakes
Frequency and vibration amplitude select suitable vibration-absorptive material.In present embodiment, the material of the damping interlayer 241 be foam,
The material of first beam 242 and second beam 243 is silica gel.
The damping interlayer 241 avoids the mounting plate 22 for dividing the mounting plate 22 and the support element 23
Directly it is in contact with the support element 23.In present embodiment, the damping interlayer 241 is substantially in square frame-shaped.It is appreciated that
Other embodiments, the damping interlayer can be circular, rectangular plate, oval plate, polygon plate etc..In addition,
The damping interlayer 241 can also be made of multiple parts being separated from each other.In present embodiment, the damping interlayer 241 is logical
It is viscous on the top surface 2311 of the support element 23 to cross colloid 40.
First beam 242 and second beam 243 both correspond to the first through hole 223 and are arranged.
Wherein, the first beam 242 corresponds to 222 side of second surface that the first through hole 223 is set to the mounting plate 22, and described
Two beams 243 correspond to 221 side of first surface that the first through hole 223 is set to the mounting plate 22.Each described
One beam 242 is opened up there are one the second through-hole 2421, each described second beam 243 opens up that there are one third through-holes
2431.In present embodiment, first beam 242 and second beam 243 are in hollow cylindrical, Ke Yili
Solution, each described first beam 242 and second beam 243 or hollow elliptic cylindrical shape, hollow prism
Shape etc., moreover, the shape of multiple first beam, 242 and/or second beams 243 can be the same or different.
The connector 25 is used to the mounting plate 22 being fixedly connected on the support element 23.In present embodiment,
The connector 25 is bolt comprising bar portion 251 and the cap portion 252 positioned at 251 one end of the bar portion.The bar portion 251
It is equipped with external screw thread compatible with the internal thread hole 2312a（It does not indicate）, the diameter of the bar portion 251 is less than described first
The internal diameter of beam 242 and second beam 243, and the diameter in the cap portion 252 is more than second beam 243
Diameter.
Also referring to Fig. 3 and Fig. 4, when assembling, the damping interlayer 241 is set to the support by the colloid 40
On the top surface 2311 of part 23；Between the support element 23 and the bottom wall 111 by first connecting hole 1111 and
The mutual cooperation of second connecting hole 2331 is attached, and specifically, bolt part may be used（It is not shown）It is each passed through
The support element 23 and the bottom wall 111 are connected with each other by two connecting holes 2331 and corresponding first connecting hole 1111；The company
Fitting 25 passes through the of the third through-hole 2431 of corresponding second beam 243, first through hole 223 and the first beam 242
Two through-holes 2421 are threadedly coupled with corresponding connecting pole 2312, the mounting plate 22 are connected on the support element 23, together
When first beam 242 is located between the corresponding connecting pole 2312 and the second surface 222 of the mounting plate 22,
Second beam 243 is and described between the corresponding cap portion 252 and the first surface 221 of the mounting plate 22
Mounting plate 22 is not contacted with the generation of the side wall 112, i.e., has gap between the described mounting plate and the side wall 112；It is described to subtract
Shake interlayer 241 is located between the top surface 2311 and the second surface 222 of the mounting plate 22 of the support element 23.
When the aircraft 100 works, the bottom wall 111 will not amplify the vibrations for being parallel to X, Y-axis place plane, by
It is set on the bottom wall 111 and not with the side wall 112 and is contacted by the support element 23 in the mounting plate 22, therefore can
Effectively reduce or eliminate the sensing element 21 of the sensing component 20 on the mounting plate 22 and the mounting plate 22 be subjected to it is flat
The vibrations of row plane where X, Y-axis；Additionally by the shock absorber part 24, it can reduce or eliminate described in the mounting plate 22
What is be subjected to is parallel to shaking for Z-direction, moreover, first beam 242 and second beam 243 can be reduced
Or the transmission of the vibrations caused by the mechanical connection between the elimination mounting plate 22 and the support element 23.
It is appreciated that first connecting hole 1111 is not required with second connecting hole 2331, the bottom wall 111
And the modes such as welding, riveting, engaging can also be used to be connected with each other between the support element 23.
It is appreciated that the first through hole 223, first beam 242, second beam 243 and described
The quantity of connecting pole 2312 can make different variations depending on actual demand.
It is appreciated that the quantity and shape of the landing chassis 13 can change or even the landing chassis 13 can be omitted, and
Support when being landed using the bottom wall 111 as the aircraft.
It is understood that those skilled in the art can also do other variations etc. in spirit of that invention is used in the present invention's
Design, without departing from the technique effect of the present invention.These variations that spirit is done according to the present invention, should all be included in
Within scope of the present invention.
Claims (8)
1. a kind of aircraft, it is characterised in that including fuselage and the sensing component and support element that are set in the fuselage, institute
It includes main casing to state fuselage, and the main casing includes bottom wall and the side wall that is connected with the bottom wall, the side wall and the bottom
Wall surrounds receiving space jointly, and the sensing component and support element are contained in the receiving space, and the support element is connected to
On the bottom wall, the sensing component includes mounting plate and the sensing element that is fixed on the mounting plate, and sensing element is electrically connected
Ground connection is set to the mounting plate, and the mounting plate is connect with the support element, and the mounting plate is set to institute by support element
It states and is contacted on bottom wall and not with the side wall；
The aircraft further includes shock absorber part, and the shock absorber part is set between the sensing component and the support element.
2. aircraft as described in claim 1, it is characterised in that：The shock absorber part includes damping interlayer, the support element packet
The side plate for including top plate and being connect with the top plate, the top plate include towards the top surface of the sensing component, the damping every
Layer is set on the top surface.
3. aircraft as described in claim 1, it is characterised in that：The sensing component includes connector, and the connector will
The sensing component is connected on the support element, and the shock absorber part includes the first beam, and first beam is sheathed on
On the corresponding connector and it is set between the sensing component and the support element.
4. aircraft as described in claim 1, it is characterised in that：The sensing component includes connector, and the connector will
The sensing component is connected on the support element, and the shock absorber part includes the second beam corresponding to the connector, institute
It states the second beam and is sheathed on the corresponding connector and is set to the side that the sensing component deviates from the support element
On surface.
5. the aircraft as described in any one of Claims 1-4, it is characterised in that：The sensing element is inertia measurement
Unit.
6. aircraft as claimed in claim 5, it is characterised in that：It is provided with damper element in the Inertial Measurement Unit.
7. aircraft as described in claim 1, it is characterised in that：The first connecting hole, the support element are offered on the bottom wall
On offer the second connecting hole corresponding to first connecting hole, pass through described first between the support element and the bottom wall
The cooperation of connecting hole and second connecting hole is connected with each other.
8. aircraft as described in claim 1, it is characterised in that：The aircraft is the rotor craft with rotor assemblies,
The fuselage includes multiple arm housings, and the branch arm housing is set to around the main casing, is used to support the aircraft
Rotor assemblies.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510162607.4A CN104787298B (en) | 2015-04-08 | 2015-04-08 | Aircraft |
| CN201810504362.2A CN108750068B (en) | 2015-04-08 | 2015-04-08 | Aircraft with a flight control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510162607.4A CN104787298B (en) | 2015-04-08 | 2015-04-08 | Aircraft |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810504362.2A Division CN108750068B (en) | 2015-04-08 | 2015-04-08 | Aircraft with a flight control device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104787298A CN104787298A (en) | 2015-07-22 |
| CN104787298B true CN104787298B (en) | 2018-07-24 |
Family
ID=53552584
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510162607.4A Expired - Fee Related CN104787298B (en) | 2015-04-08 | 2015-04-08 | Aircraft |
| CN201810504362.2A Expired - Fee Related CN108750068B (en) | 2015-04-08 | 2015-04-08 | Aircraft with a flight control device |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810504362.2A Expired - Fee Related CN108750068B (en) | 2015-04-08 | 2015-04-08 | Aircraft with a flight control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN104787298B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105509741B (en) * | 2016-01-29 | 2019-02-01 | 深圳市大疆创新科技有限公司 | Fly control component and unmanned vehicle |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102771201A (en) * | 2009-11-13 | 2012-11-07 | 鹦鹉股份有限公司 | Electronic navigation card holder for a rotor drone |
| CN102980584A (en) * | 2011-09-02 | 2013-03-20 | 深圳市大疆创新科技有限公司 | Inertia measuring module of unmanned aircraft |
| CN103818544A (en) * | 2014-01-24 | 2014-05-28 | 深圳一电科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle body and manufacturing method thereof |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100037694A1 (en) * | 2008-08-15 | 2010-02-18 | Honeywell International Inc. | Snubbing system for a suspended body |
| CN102121829B (en) * | 2010-08-09 | 2013-06-12 | 汪滔 | Miniature inertia measurement system |
| CN202274882U (en) * | 2011-09-02 | 2012-06-13 | 深圳市大疆创新科技有限公司 | Unmanned aircraft inertia measuring module |
| CN102991678A (en) * | 2011-09-09 | 2013-03-27 | 中国航天科工集团第三研究院第八三五七研究所 | Novel vibration damper applied to unmanned aerial vehicle automatic pilot |
| CN102636164B (en) * | 2012-04-18 | 2015-01-07 | 北京航空航天大学 | Fiber-optic gyroscope IMU (inertial measurement unit) combination for high-precision strap-down systems |
| CN102694351B (en) * | 2012-06-06 | 2015-05-13 | 长春理工大学 | High voltage overhead transmission line line-inspection unmanned aerial vehicle photoelectric detection device |
| CN203105021U (en) * | 2012-09-07 | 2013-07-31 | 天津市松正电动汽车技术股份有限公司 | Damping structure for PCB pads of controller |
| CN203047531U (en) * | 2012-11-15 | 2013-07-10 | 深圳市大疆创新科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CA2997790C (en) * | 2013-05-15 | 2021-06-29 | Autel Robotics Usa Llc | Compact unmanned rotary aircraft |
| CN103963985B (en) * | 2014-04-16 | 2016-05-18 | 徐鹏 | A kind of external hanging type high-altitude high-speed aircraft is taken the photograph platform |
| CN204121762U (en) * | 2014-09-23 | 2015-01-28 | 彭信泉 | A multi-rotor aircraft |
| CN204548475U (en) * | 2015-04-08 | 2015-08-12 | 深圳市大疆创新科技有限公司 | Aircraft |
-
2015
- 2015-04-08 CN CN201510162607.4A patent/CN104787298B/en not_active Expired - Fee Related
- 2015-04-08 CN CN201810504362.2A patent/CN108750068B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102771201A (en) * | 2009-11-13 | 2012-11-07 | 鹦鹉股份有限公司 | Electronic navigation card holder for a rotor drone |
| CN102980584A (en) * | 2011-09-02 | 2013-03-20 | 深圳市大疆创新科技有限公司 | Inertia measuring module of unmanned aircraft |
| CN103818544A (en) * | 2014-01-24 | 2014-05-28 | 深圳一电科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle body and manufacturing method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108750068B (en) | 2021-01-05 |
| CN108750068A (en) | 2018-11-06 |
| CN104787298A (en) | 2015-07-22 |
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