CN205978246U - Damping device and aircraft - Google Patents
Damping device and aircraft Download PDFInfo
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- CN205978246U CN205978246U CN201620650300.9U CN201620650300U CN205978246U CN 205978246 U CN205978246 U CN 205978246U CN 201620650300 U CN201620650300 U CN 201620650300U CN 205978246 U CN205978246 U CN 205978246U
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- support
- magnet
- connecting shaft
- buffer unit
- damping device
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Abstract
The utility model discloses a damping device and aircraft. Damping device includes first support and second support, first support with the second support passes through the unsteady connection of buffer unit. The buffer unit is magnetism buffer unit and/or springiness cushioning part. The magnetism buffer unit includes homopolar relative first magnet and second magnet, the springiness cushioning part is spring or elastic rubber. The aircraft includes aircraft main part and camera, the aircraft main part with pass through between the camera if preceding damping device connects. The utility model discloses the vibrations of equipment can be reduced widely, the normal work of equipment is ensured. The aircraft is at the in -process of flight, and the vibrations of camera reduce widely, are favorable to shooting clear stable picture.
Description
Technical field
This utility model is related to a kind of cushioning product, more particularly, to a kind of damping device for aircraft and equipped with needs
The aircraft of shock-absorption.
Background technology
Aircraft (as unmanned plane etc.) is commonly installed shockproof equipment (as video camera, gun post etc.) in need, needs
Shockproof equipment, without preferable precautions against earthquakes, just cannot be carried out normally working.In prior art, video camera (or
By head) directly it is fixedly connected with aircraft.Because aircraft can produce very big vibrations in the process of flight, so,
Video camera acts as very big vibrations also with aircraft one, and the picture that the video camera of significant shock is shot is it is difficult to ensure that clearly steady
Fixed.Similarly, if gun post is fixedly connected with aircraft, then it is also difficult to ensure the accuracy of shooting.
Utility model content
First technical problem to be solved in the utility model is to provide a kind of damping device for aircraft, using this
Damping device will need shockproof equipment to be connected with aircraft body, can greatly reduce the vibrations of equipment it is ensured that equipment
Normal work.
Second technical problem to be solved in the utility model is to provide a kind of aircraft equipped with video camera, this aircraft
During flight, the vibrations of video camera greatly reduce, and are conducive to shooting steady and audible picture.
For device, in order to solve above-mentioned first technical problem, this utility model provides a kind of damping device, bag
Include first support and second support, described first support and described second support pass through buffer unit floating connection.
Described buffer unit is magnetic cushion part, and/or, described buffer unit is elastic buffer unit.
Described magnetic cushion part includes the first Magnet being connected with first support and the second magnetic being connected with second support
Ferrum, described first Magnet is relative with described second Magnet homopolarity.
Described first Magnet is provided with projection, and correspondingly, described second Magnet is provided with recess, and described projection can be deep into
In described recess；Or, described first Magnet is provided with recess, and described second Magnet is provided with projection, and described projection can be goed deep into
To in described recess.
First support and/or described second support are distributed with axis hole, logical between described first support and described second support
Cross connecting shaft to be connected with described shaft hole matching, be slidably connected between one end of described connecting shaft and described first support, described company
Be fixedly connected between the other end of spindle and described first support, or, one end of described connecting shaft and described first support it
Between be fixedly connected, be slidably connected between the other end of described connecting shaft and described second support, or, one end of described connecting shaft
It is slidably connected and described first support between, and, be slidably connected between the other end of described connecting shaft and described second support.
Described first Magnet and described second Magnet are equipped with connecting shaft hole, and are slidably enclosed within by described connecting shaft hole
In described connecting shaft.
Described first support is distributed with the first buffer unit seat, and described first Magnet is located at described first buffer unit seat
Interior；Described second support is distributed with the second buffer unit seat, and described second Magnet is located in described second buffer unit seat.
In described connecting shaft, at least one end is provided with limited shoulder.
Damping device of the present utility model compared with prior art has the advantages that.
1st, the technical program passes through buffer unit floating connection due to employing described first support and described second support
Technological means, so, shockproof equipment will be needed to be connected with aircraft body using this damping device, can greatly reduce
The vibrations of equipment are it is ensured that the normal work of equipment.
2nd, the technical program is magnetic cushion part due to employing described buffer unit, and/or, elastic buffer unit
Technological means, so, the damping device of multiple aircraft can be produced according to the different demands of client.
3rd, the technical program includes the first relative Magnet of homopolarity and the second magnetic due to employing described magnetic cushion part
The technological means of ferrum, homopolarity relatively, produces the active force that repels each other, shakes between abatement first support and second support.
4th, the technical program is provided with recess due to the central authorities employing described second Magnet upper surface, correspondingly, described
The central authorities of the first Magnet lower surface are provided with projection, and described projection can be deep in described recess, or, on described second Magnet
The central authorities of end face are provided with projection, and correspondingly, the central authorities of described first Magnet lower surface are provided with recess, and described projection can be goed deep into
Technological means in described recess, so, it is to avoid the first Magnet and the second Magnet significantly shake.
5th, first support and/or described second support are distributed with axis hole, between described first support and described second support
It is connected with described shaft hole matching by connecting shaft, be slidably connected between one end of described connecting shaft and described first support, described
It is fixedly connected between the other end of connecting shaft and described first support, or, one end of described connecting shaft and described first support
Between be fixedly connected, be slidably connected between the other end of described connecting shaft and described second support, or, the one of described connecting shaft
It is slidably connected between end and described first support, and, the company of slip between the other end of described connecting shaft and described second support
Connect, so, be conducive to moving back and forth with facing between first support second support, simultaneously, it is to avoid significantly shake.
6th, the technical program is equipped with connecting shaft hole due to employing described first Magnet and described second Magnet, and passes through
Described connecting shaft hole is slidably enclosed within the technological means in described connecting shaft, so, be conducive to the assembling of damping device.
7th, the technical program is distributed with the first buffer unit seat, described first Magnet position due to employing described first support
In described first buffer unit seat；Described second support is distributed with the second buffer unit seat, and described second Magnet is located at described
Technological means in second buffer unit seat, so it can be ensured that the stability of the first Magnet and the installation of the second Magnet.
8th, the technical program is provided with the technological means of limited shoulder, institute due to employing at least one end in described connecting shaft
Can avoid crossing between first support and second support and significantly to shake.
For aircraft, in order to solve above-mentioned second technical problem, this utility model provides a kind of aircraft, bag
Include damping device as elucidated before, described first support is relative up and down with described second support, described second support is located at institute
State the lower section of first support, described second support is fixedly linked with described aircraft body, described first support and camera head
It is connected.
Described second support is provided with upwardly extending cantilever, and described cantilever is fixedly linked with described aircraft body, institute
State second support and be provided with installing hole, one end of described camera head is connected with described first support through described installing hole.
This utility model compared with prior art has the advantages that equipped with the aircraft of camera head.
1st, the technical program is fixedly linked with described aircraft body due to employing described second support, described first
The technological means that frame is connected with camera head, so, during flight, the vibrations of video camera greatly reduce aircraft,
Be conducive to shooting steady and audible picture.
2nd, the technical program is provided with upwardly extending cantilever due to employing described second support, described cantilever with described
Aircraft body is fixedly linked, and described second support is provided with installing hole, one end of described camera head pass through described installing hole with
The technological means that described first support is connected, so, it is not only advantageous to be fixedly connected between second support and aircraft body, and
And, it is also beneficial to dismounting and the replacing of video camera.
Brief description
Fig. 1 is aircraft perspective structure schematic diagram (after assembling) equipped with video camera for this utility model.
Fig. 2 is aircraft perspective structure schematic diagram (after decomposition) equipped with video camera for this utility model.
Fig. 3 is damping device magnification fluoroscopy structural representation (after assembling) of aircraft in Fig. 2.
Fig. 4 is the partial enlargement structural representation in A portion in Fig. 3.
Fig. 5 is the magnification fluoroscopy structural representation of the second Magnet in Fig. 2.
Fig. 6 is the magnification fluoroscopy structural representation of the first Magnet in Fig. 2.
Fig. 7 is the magnification fluoroscopy structural representation of connecting shaft in Fig. 2.
Fig. 8 is the damping device structural representation of another kind of aircraft.
Description of symbols in accompanying drawing is as follows.
1～aircraft body
2～video camera
3～damping device
3-1～second support
3-1-1～installing hole
3-1-2～the second buffer unit seat
3-1-2-1～connecting shaft hole
3-1-2-2～counterbore
3-1-3～cantilever
3-1-4～fixing hole
3-2～first support
3-2-1～head mounting seat
3-2-2～fixing hole
3-2-3～the first buffer unit seat
3-2-3-1～connecting shaft hole
3-2-3-2～counterbore
3-3～buffer unit
3-3-1～the second Magnet
3-3-1-1～recess
3-3-1-2～connecting shaft hole
3-3-2～the first Magnet
3-3-2-1～projection
3-3-2-2～connecting shaft hole
3-3-3～connecting shaft
3-3-3-1～first annular plane shoulder
3-3-3-2～the second planar annular shoulder
3-3-3-3～butt conical surface shoulder
3-3-3-4～annular groove
3-4～head
3-4-1～threaded securing bores
Specific embodiment
As shown in Fig. 2 to Fig. 3 and Fig. 7, present embodiments provide for a kind of damping device 3 for aircraft, including
Two support 3-1 and first support 3-2, described second support 3-1 and described first support 3-2 are passed through buffer unit 3-3 and are floated even
Connect.
Present embodiment passes through buffer unit floating connection due to employing described second support and described first support
Technological means, so, shockproof equipment will be needed to be connected with aircraft body using this damping device, can greatly reduce and set
Standby vibrations are it is ensured that the normal work of equipment.
The first step as present embodiment is improved, and as shown in Figure 2 to Figure 3, described buffer unit 3-3 is magnetic cushion portion
Part 3-3-1,3-3-2.It is of course also possible to be as shown in fig. 7, described buffer unit 3-3 is elastic buffer unit.
Present embodiment is due to employing the technology that described buffer unit is magnetic cushion part and/or elastic buffer unit
Means, so, the damping device of multiple aircraft can be produced according to the different demands of client.
Second step as present embodiment improves, as shown in Figure 2 to Figure 3, described magnetic cushion part 3-3-1,3-3-2
Including homopolarity the second relative Magnet 3-3-1 and the first Magnet 3-3-2.As shown in fig. 7, described elastic buffer unit is spring.
It is of course also possible to be, described elastic buffer unit is gum elastic.
Present embodiment includes the second relative Magnet of homopolarity and the first Magnet due to employing described magnetic cushion part
Technological means, so, be conducive to avoiding the deformation fatigue damage of buffer unit.When being spring using described elastic buffer unit
Or the technological means of gum elastic, then advantageously reduce the cost of manufacture of damping device.
The 3rd step as present embodiment is improved, and as shown in Figure 2 to Figure 3, the shape of described second Magnet 3-3-1 is in circle
Cylinder, correspondingly, the shape of described first Magnet 3-3-2 is in cylinder.As shown in fig. 7, described spring is post spring.Certainly,
Can be that described spring is tower spring.Described gum elastic is elastic rubber column.It is of course also possible to be, described gum elastic is to cut
Head gum elastic cone.
Present embodiment is in cylinder, correspondingly, described first Magnet due to employing the shape of described second Magnet
Shape is in cylinder, and described spring is post spring or tower spring, and described gum elastic is elastic rubber column or butt gum elastic cone
Technological means, so, the damping device of multiple aircraft can be produced according to practical situation.
The 4th step as present embodiment is improved, as shown in figure 4, the central authorities of described second Magnet 3-3-1 upper surface set
It is equipped with recess 3-3-1-1.Figure 4, it is seen that the shape of described recess 3-3-1-1 is in cylindrical space.Correspondingly, as schemed
Shown in 5, the central authorities of described first Magnet 3-3-2 lower surface are provided with raised 3-3-2-1.Described projection 3-3-2-1 shape be in
Hemispherical.Described projection 3-3-2-1 can be deep in described recess 3-3-1-1.It is of course also possible to be, described second Magnet 3-
The central authorities of 3-1 upper surface are provided with projection, and correspondingly, the central authorities of described first Magnet 3-3-2 lower surface are provided with recess, described
Projection can be deep in described recess.
Present embodiment is provided with recess due to the central authorities employing described second Magnet upper surface, correspondingly, described
The central authorities of one Magnet lower surface are provided with projection, and described projection can be deep in described recess, or, described second Magnet upper end
The central authorities in face are provided with projection, and correspondingly, the central authorities of described first Magnet lower surface are provided with recess, and described projection can be deep into
Technological means in described recess, so, be conducive to the second Magnet and the first Magnet to move back and forth with facing.
The 5th step as present embodiment is improved, as shown in figure 4, described second Magnet 3-3-1 is provided with connecting shaft hole
3-3-1-2, correspondingly, as shown in figure 5, described first Magnet 3-3-2 is provided with connecting shaft hole 3-3-2-2.
Present embodiment is provided with connecting shaft hole due to employing described second Magnet, and correspondingly, described first Magnet sets
It is equipped with the technological means of connecting shaft hole, so, be conducive to the company between second support, the second Magnet, the first Magnet, first support
Connect.
The 6th step as present embodiment is improved, and as shown in Figure 2 to Figure 3, the shape of described second support 3-1 is in rectangular
Shape plate.It is of course also possible to be, the shape of described second support 3-1 is in regular polygon plate, elliptical flat-plate or circular slab.Correspondingly,
The shape of described first support 3-2 is rectangle plate.It is of course also possible to be, the shape of described first support 3-2 is in regular polygon
Plate, elliptical flat-plate or circular slab.
Present embodiment is rectangle plate, regular polygon plate, elliptical flat-plate due to the shape employing described second support
Or circular slab, correspondingly, the shape of described first support is rectangle plate, the skill of regular polygon plate, elliptical flat-plate or circular slab
Art means, so, be conducive to material-saving, reduce production cost.
The 7th step as present embodiment is improved, and as shown in Figure 2 to Figure 3, the central authorities of described second support 3-1 are provided with
The installing hole 3-1-1 penetrating for head 3-4 top, correspondingly, on the mediad of described first support 3-2, protuberance formation is convex
Recessed cylinder chamber constitutes head mounting seat 3-2-1, and the top surface of described head mounting seat 3-2-1 is distributed with fixing hole 3-2-2, institute
State the top that first support 3-2 is located at described second support 3-1, the shaped upper part of described head 3-4 is in the form of a column, described head 3-
The fixing hole 3-2-2 of corresponding described head mounting seat 3-2-1 of 4 top surface is distributed with threaded securing bores 3-4-1, described head 3-4
Top pass through installing hole 3-1-1 from bottom to top and embed in head mounting seat 3-2-1, described head 3-4 and described first
It is fixedly connected by screw between frame 3-2.
Present embodiment is provided with, due to the central authorities employing described second support, the installing hole penetrating for head top,
Correspondingly, on the mediad of described first support, protuberance forms convex recessed cylinder chamber composition head mounting seat, described head
The top surface of mounting seat is distributed with fixing hole, and described first support is located at the top of described second support, the top shape of described head
Shape is in the form of a column, and the fixing hole of the corresponding described head mounting seat of top surface of described head is distributed with threaded securing bores, described head
Top passes through in installing hole embedded head mounting seat from bottom to top, passes through screw solid between described head and described first support
The fixed technological means connecting, so, it is greatly improved the safety of damping device.
The 8th step as present embodiment is improved, and as shown in Figure 2 to Figure 3, the edge of described second support 3-1 is at least
After upwardly extending at one, outward bending forms cantilever 3-1-3 again, and there is fixing hole in the top surface branch of described cantilever 3-1-3.
Present embodiment due to employ upwardly extend at the edge at least of described second support after outward bending again
Form cantilever, there are the technological means of fixing hole in the top surface branch of described cantilever, so, be conducive to second support and aircraft body
Between be fixedly connected.
The 9th step as present embodiment is improved, and as shown in Figure 2 to Figure 3, described cantilever 3-1-3 has two, two institutes
State cantilever 3-1-3 and be located at the relative both sides of described second support 3-1 respectively.
Present embodiment has two due to employing described cantilever, and two described cantilevers are located at described second support phase respectively
To both sides technological means, so it can be ensured that second support install stability.
The tenth step as present embodiment is improved, and as shown in Figure 2 to Figure 3, the top surface of described second support 3-1 is circumferentially
Second buffer unit seat 3-1-2 is distributed with, correspondingly, the bottom surface of described first support 3-2 is circumferentially distributed the first buffer part
Part seat 3-2-3.
Present embodiment has the second buffer unit seat because the top surface that employs described second support is circumferentially distributed, accordingly
Ground, the circumferentially distributed technological means having the first buffer unit seat in the bottom surface of described first support, so, be conducive to improving first
The motility that support floats.
The 11st step as present embodiment is improved, and as shown in Figure 2 to Figure 3, the bottom surface of described second support 3-1 corresponds to
The position of described second buffer unit seat 3-1-2 is downwardly extending projection, and described second buffer unit seat 3-1-2 is recessed institute
State the blind cylindrical hole of second support 3-1 top surface, the bottom of described buffer unit 3-3 is located in this blind cylindrical hole, correspondingly,
The position of the corresponding described first buffer unit seat 3-2-3 of the top surface of described first support 3-2 upwardly extends formation projection, and described the
One buffer unit seat 3-2-3 is the blind cylindrical hole of recessed described first support 3-2 bottom surface, the top of described buffer unit 3-3
In this blind cylindrical hole.
Present embodiment due to the corresponding described second buffer unit seat in bottom surface that employs described second support position to
Lower extension forms projection, and described second buffer unit seat is the blind cylindrical hole of recessed described second support top surface, described buffering
The bottom of part is located in this blind cylindrical hole, and correspondingly, the top surface of described first support corresponds to described first buffer unit seat
Position upwardly extend formation projection, described first buffer unit seat is the blind cylindrical hole of recessed described first support bottom surface,
The technological means that the top of described buffer unit is located in this blind cylindrical hole, so, be conducive to fixing and protect buffer unit.
The 12nd step as present embodiment is improved, as shown in Figure 2 to Figure 3, the projection bottom of described second support 3-1
Central authorities are provided with counterbore 3-1-2-2, the axis of the axis of described counterbore 3-1-2-2 and described second support 3-1 blind cylindrical hole
Coincide, the bottom center of described counterbore 3-1-2-2 offers connecting shaft hole 3-1-2-1, correspondingly, described first support 3-2
Projection center of top be provided with counterbore 3-2-3-2, the axis of described counterbore 3-2-3-2 is cylindrical with described first support 3-2
The axis of blind hole coincides, and the bottom center of described counterbore 3-2-3-2 offers connecting shaft hole 3-2-3-1.
Present embodiment is provided with counterbore, the axle of described counterbore due to the projection bottom center employing described second support
Line is coincided with the axis of described second support blind cylindrical hole, and the bottom center of described counterbore offers connecting shaft hole, accordingly
Ground, the projection center of top of described first support is provided with counterbore, and the axis of described counterbore is blind with described first support cylinder
The axis in hole coincides, and the bottom center of described counterbore offers the technological means of connecting shaft hole, so, further for below
Improvement provides advantage.
The 13rd step as present embodiment is improved, as shown in Figure 2 to Figure 3, the bottom margin of described second support 3-1
It is downwardly extending reinforcement, correspondingly, the top of described first support 3-2 upwardly extends formation reinforcement.
Present embodiment is downwardly extending reinforcement due to the bottom margin employing described second support, correspondingly,
The top of described first support upwardly extends the technological means forming reinforcement, so, second support and the can be improved
The rigidity of one support and intensity.
The 14th step as present embodiment is improved, and as shown in Figure 2 to Figure 3, described second support 3-1 is by aluminium alloy system
Form, correspondingly, described first support 3-2 is made by aluminium alloy.
Present embodiment is made by aluminium alloy due to employing described second support, correspondingly, described first support
The technological means being made by aluminium alloy, so, rigidity and the intensity of second support and first support can be improved further.
The 15th step as present embodiment is improved, and as shown in Figure 2 to Figure 3, described buffer unit 3-3 includes connecting shaft
3-3-3, described connecting shaft 3-3-3 sequentially pass through from bottom to up second support 3-1, the second Magnet 3-3-1, the first Magnet 3-3-2,
First support 3-2.
Present embodiment includes connecting shaft due to employing described buffer unit, and described connecting shaft sequentially passes through from bottom to up
Second support, the second Magnet, the first Magnet, the technological means of first support, so, it is more beneficial for the second Magnet and the first Magnet
Move back and forth with facing.
The 16th step as present embodiment is improved, as shown in fig. 6, the tail end side of described connecting shaft 3-3-3 is along footpath
Form first annular plane shoulder 3-3-3-1 to stretching out, described connecting shaft 3-3-3 is near the middle part side of head end radially
Stretch out two shoulders of formation, and wherein, the shoulder towards tail end is the second planar annular shoulder 3-3-3-2, towards head end
Shoulder is butt conical surface shoulder 3-3-3-3, and the cervical region of the second planar annular shoulder 3-3-3-2 offers annular groove 3-3-3-4.
Present embodiment is first annular flat because the tail end side employing described connecting shaft extends radially outward formation
Face shoulder, described connecting shaft extends radially outward two shoulders of formation near the middle part side of head end, wherein, towards tail end
Shoulder is the second planar annular shoulder, and the shoulder towards head end is butt conical surface shoulder, and the cervical region of the second planar annular shoulder is opened
It is provided with the technological means of annular groove, so, be conducive to the assembling of damping device.
The 17th step as present embodiment is improved, as shown in fig. 6, described connecting shaft 3-3-3 is by silica gel material or rubber
Glue material is made.
Present embodiment due to employing the technological means that described connecting shaft is made by silica gel material or elastomeric material,
So, be conducive to the vibrations in the horizontal direction of reduction equipment.
As shown in Figure 1 to Figure 2, present embodiments provide for a kind of aircraft equipped with video camera, including aircraft body 1
With video camera 2, pass through the damping device 3 of aircraft as previously described between described aircraft body 1 and described video camera 2 even
Connect.
When aircraft flight, aircraft body can produce vibrations, when vibrations are delivered to damping device from aircraft body
Afterwards, the elastic nature of the repulsive force between the first Magnet and the second Magnet and connecting shaft can go up inferior multiple side all around
To forming buffering, filter out the vibrations that aircraft body transmits, maintain stablizing of head and video camera.
Present embodiment is passed through between described aircraft body and described video camera to fly as previously described due to employing
The technological means that the damping device of device connects, so, during flight, the vibrations of video camera greatly reduce aircraft,
Be conducive to shooting steady and audible picture.
Further improve as present embodiment, as shown in Fig. 2 described second support 3-1 pass through screw or bolt with
Described aircraft body 1 is fixedly connected, and described video camera 2 is fixedly connected with described first support 3-2 by described head 3-4.
Due to employing, described second support passes through screw or bolt to present embodiment and described aircraft body is fixing even
Connect, the technological means that described video camera is fixedly connected with described first support by described head, so, be conducive to video camera
Dismounting and replacing.
Claims (9)
1. a kind of damping device it is characterised in that：Including first support and second support, described first support and described second
Frame passes through buffer unit floating connection；
Described buffer unit is magnetic cushion part, or, described buffer unit is magnetic cushion part and elastic buffer unit.
2. damping device according to claim 1 it is characterised in that：Described magnetic cushion part includes and first support phase
The first Magnet even and the second Magnet being connected with second support, described first Magnet is relative with described second Magnet homopolarity.
3. damping device according to claim 2 is it is characterised in that described first Magnet is provided with projection, correspondingly, institute
State the second Magnet and be provided with recess, described projection can be deep in described recess；Or, described first Magnet is provided with recess,
Described second Magnet is provided with projection, and described projection can be deep in described recess.
4. the damping device according to Claims 2 or 3 is it is characterised in that described first support and/or described second support
Axis hole is distributed with, is connected with described shaft hole matching by connecting shaft between described first support and described second support,
Be slidably connected between one end of described connecting shaft and described first support, the other end of described connecting shaft with described first
It is fixedly connected between frame, or,
Be fixedly connected between one end of described connecting shaft and described first support, the other end of described connecting shaft with described second
It is slidably connected between frame, or,
Be slidably connected between one end of described connecting shaft and described first support, and, the other end of described connecting shaft with described
It is slidably connected between second support.
5. damping device according to claim 4 is it is characterised in that described first Magnet and described second Magnet are equipped with
Connecting shaft hole, and be slidably enclosed within described connecting shaft by described connecting shaft hole.
6. according to claim 5 damping device it is characterised in that described first support is distributed with the first buffer unit seat,
Described first Magnet is located in described first buffer unit seat；Described second support is distributed with the second buffer unit seat, and described
Two Magnet are located in described second buffer unit seat.
7. according to claim 6 damping device it is characterised in that in described connecting shaft at least one end be provided with limited shoulder.
8. a kind of aircraft, including the damping device as described in claim 1-7 any one, described first support and described
Up and down relatively, described second support is located at the lower section of described first support to two supports, and described second support is with described aircraft originally
Body is fixedly linked, and described first support is connected with camera head.
9. aircraft according to claim 8 is it is characterised in that described second support is provided with upwardly extending cantilever,
Described cantilever is fixedly linked with described aircraft body, and described second support is provided with installing hole, and one end of described camera head is worn
Cross described installing hole to be connected with described first support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620650300.9U CN205978246U (en) | 2016-06-27 | 2016-06-27 | Damping device and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620650300.9U CN205978246U (en) | 2016-06-27 | 2016-06-27 | Damping device and aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN205978246U true CN205978246U (en) | 2017-02-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620650300.9U Expired - Fee Related CN205978246U (en) | 2016-06-27 | 2016-06-27 | Damping device and aircraft |
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| CN (1) | CN205978246U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106686317A (en) * | 2017-03-09 | 2017-05-17 | 温州大学 | Oblique photographing device for high-definition unmanned aerial vehicle |
| CN106671691A (en) * | 2017-03-23 | 2017-05-17 | 大连大学 | Movable damping operation table for painting and application method |
| CN107734237A (en) * | 2017-11-15 | 2018-02-23 | 深圳市道通智能航空技术有限公司 | Picture shooting assembly and the unmanned vehicle with this picture shooting assembly |
-
2016
- 2016-06-27 CN CN201620650300.9U patent/CN205978246U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106686317A (en) * | 2017-03-09 | 2017-05-17 | 温州大学 | Oblique photographing device for high-definition unmanned aerial vehicle |
| CN106671691A (en) * | 2017-03-23 | 2017-05-17 | 大连大学 | Movable damping operation table for painting and application method |
| CN107734237A (en) * | 2017-11-15 | 2018-02-23 | 深圳市道通智能航空技术有限公司 | Picture shooting assembly and the unmanned vehicle with this picture shooting assembly |
| CN107734237B (en) * | 2017-11-15 | 2020-10-23 | 深圳市道通智能航空技术有限公司 | Shooting assembly and unmanned aerial vehicle with same |
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