CN109703771A - Unmanned plane shock mitigation system and unmanned plane - Google Patents
Unmanned plane shock mitigation system and unmanned plane Download PDFInfo
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- CN109703771A CN109703771A CN201811412662.4A CN201811412662A CN109703771A CN 109703771 A CN109703771 A CN 109703771A CN 201811412662 A CN201811412662 A CN 201811412662A CN 109703771 A CN109703771 A CN 109703771A
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Abstract
The present invention discloses a kind of unmanned plane shock mitigation system and unmanned plane, the unmanned plane includes unmanned plane main body and carry device, the unmanned plane main body includes the fuselage with inner cavity and the control circuit board for being set to fuselage inner cavity, the unmanned plane shock mitigation system includes providing the second damping module of damping to the carry device and the control circuit board respectively, the second damping module includes the second loading plate for connecting the unmanned plane main body, it is separately connected the second vibration damper plate of the carry device Yu the control circuit board, and the second elastic component of connection second loading plate and the second vibration damper plate.The damping to winged control circuit board or carry device is realized using the second loading plate, the second vibration damper plate and the second elastic component of the second damping module.
Description
Technical field
The present invention relates to vehicle technology fields, and in particular to a kind of unmanned plane shock mitigation system and unmanned plane.
Background technique
The remote controlled drone of the prior art includes multiple sensors, motor and propeller, by motor and propeller and fuselage
Rigid connection provides flying power, and multiple sensors incude various data of the unmanned plane in flight and controlled；But motor
The precision and performance of multiple sensors have been seriously affected with vibration of the propeller in flight course, or has seriously affected carry
It takes photo by plane module, so that expected performance is not achieved in unmanned plane.
Therefore, it is necessary to provide a kind of unmanned plane shock mitigation system, with improve the stability of unmanned plane in the process of running and
Safety reduces vibration of the carry device in unmanned plane operational process.
Summary of the invention
The main object of the present invention is to provide that a kind of structure is simple, the unmanned plane shock mitigation system of good damping effect, to improve
The vibration of stability and safety or reduction carry device in unmanned plane operational process of unmanned plane in the process of running.
To achieve the above object, a kind of unmanned plane shock mitigation system proposed by the present invention, the unmanned plane include unmanned owner
Body and carry device, the unmanned plane main body include the fuselage with inner cavity and the control circuit board for being set to fuselage inner cavity, institute
Stating unmanned plane shock mitigation system includes providing the second damping module of damping to the carry device and the control circuit board respectively,
The second damping module include the second loading plate for connecting the unmanned plane main body, be separately connected the carry device with it is described
Second vibration damper plate of control circuit board and the second elastic component of connection second loading plate and the second vibration damper plate.
Preferably, the unmanned plane shock mitigation system further includes providing the first damping mould of level-one damping to the carry device
Block, the second damping module provide second level damping to the carry device.
Preferably, the first damping module includes the first vibration damper plate for connecting the carry device, connection described second
First loading plate of vibration damper plate and the first elastic component of connection first vibration damper plate and first loading plate.
Preferably, the fuselage bottom plate of second loading plate system unmanned plane, second vibration damper plate are set to the fuselage
Inner cavity, the control circuit board are fixed on second vibration damper plate, and second vibration damper plate is equipped with to be connected with first loading plate
The carry interconnecting piece connect, and the damping interconnecting piece being connect with second elastic component, on gravity direction, second elasticity
The opposite end of part is connect with the damping interconnecting piece and the fuselage bottom plate respectively, and described in the connection of second elastic component
One end of damping interconnecting piece is located at the top for connecting the other end of the fuselage bottom plate.
Preferably, the carry interconnecting piece is all provided with the damping interconnecting piece is set to multiple, and the carry interconnecting piece is each other
It is connected and constitutes main frame, the damping interconnecting piece is connected with the carry interconnecting piece constitutes sub-frame, each carry connection
Portion is connect at least two damping interconnecting pieces.
Preferably, the damping interconnecting piece system of first vibration damper plate connects the tool connection jaggy of second elastic component
Through-hole, the multiple damping interconnecting piece is circumferentially distributed around the center of the machine body base, in the circumferential direction, each adjacent two
The notch of damping interconnecting piece towards angle be 90 degree.
Preferably, carry device system has the module of taking photo by plane of holder and camera, and first vibration damper plate is provided with company
The multiple linking arms for connecing the holder interconnecting piece of the holder and being extended centered on the holder interconnecting piece to external radiation, in gravity
On direction, the opposite end of first elastic component is connect with the linking arm and first loading plate respectively, and described
One end that one elastic component connects the linking arm is located at the top for connecting the other end of first loading plate；First carrying
Plate is folded upward at the box body for extending to form the opening upwards with accommodating chamber, including cassette bottom and box wall, the cloud by plate body
The bottom end of platform interconnecting piece is pierced by the cassette bottom of the first loading plate and is fixed with installing with the camera, and first loading plate is around described
Holder interconnecting piece is provided with the damping interconnecting piece for connecting first elastic component and connects the fixed part of second vibration damper plate.
Preferably, the unmanned plane further includes the battery module with battery compartment, and the battery compartment is arranged described first
Between damping module and the second damping module, the carry interconnecting piece of second vibration damper plate and consolidating for first loading plate
Determine portion to be fixedly connected with the top of the battery compartment and bottom end respectively, the battery compartment is by triangle or polygon engraved structure
The outer framework of composition.
To achieve the above object, another unmanned plane shock mitigation system proposed by the present invention, the unmanned plane includes unmanned plane
Main body, battery module and carry device, the unmanned plane shock mitigation system include the first damping module and the second damping module, institute
State the second damping that the second damping module includes the second loading plate for connecting the unmanned plane main body, the connection battery module
Second elastic component of plate and connection second loading plate and the second vibration damper plate, the first damping module include connection institute
The first vibration damper plate for stating carry device connects the first loading plate and connection first vibration damper plate and the of the battery module
First elastic component of one loading plate.
In addition, the unmanned plane includes above-mentioned unmanned plane shock mitigation system the present invention also provides a kind of unmanned plane.
In technical solution of the present invention, the second loading plate, the second vibration damper plate and the second elastic component of the second damping module are utilized
Realize the damping to winged control circuit board or carry device.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
The structure shown according to these attached drawings obtains other attached drawings.
Fig. 1 is the decomposition diagram of unmanned plane shock mitigation system of the invention；
Fig. 2 is the further decomposition diagram of unmanned plane shock mitigation system shown in Fig. 1；
Fig. 3 is the schematic cross-sectional view of unmanned plane shock mitigation system of the invention at the first elastic component and the second elastic component, is used
To illustrate the connection structure of the first elastic component, the second elastic component respectively；
The embodiments will be further described with reference to the accompanying drawings for the realization, the function and the advantages of the object of the present invention.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiment is only a part of the embodiments of the present invention, instead of all the embodiments.Base
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts it is all its
His embodiment, shall fall within the protection scope of the present invention.
It is to be appreciated that the directional instruction (such as up, down, left, right, before and after ...) of institute is only used in the embodiment of the present invention
In explaining in relative positional relationship, the motion conditions etc. under a certain particular pose (as shown in the picture) between each component, if should
When particular pose changes, then directionality instruction also correspondingly changes correspondingly.In the description of the present invention, " multiple " contain
Justice is at least two, such as two, three etc., unless otherwise specifically defined.
In the present invention unless specifically defined or limited otherwise, term " connection ", " fixation " etc. shall be understood in a broad sense,
For example, " fixation " may be a fixed connection, it may be a detachable connection, or integral；It can be mechanical connection, be also possible to
Electrical connection；It can be directly connected, the connection inside two elements or two can also be can be indirectly connected through an intermediary
The interaction relationship of a element, unless otherwise restricted clearly.It for the ordinary skill in the art, can basis
Concrete condition understands the concrete meaning of above-mentioned term in the present invention.
In addition, the description for being such as related to " first ", " second ", " level-one ", " second level " in the present invention is only used for description mesh
, it is not understood to indicate or imply its relative importance or implicitly indicates the quantity of indicated technical characteristic.As a result,
Define " first ", " second ", " level-one ", the feature of " second level " can explicitly or implicitly include at least one of the features.
The present invention proposes a kind of unmanned plane shock mitigation system, to reduce the vibration of motor and propeller in flight course to whole
The adverse effect of a unmanned plane.
As shown in Figure 1, unmanned plane includes the unmanned plane main body and connection unmanned plane main body for being provided with motor and propeller
Carry device.Unmanned plane main body includes having the fuselage 1 of inner cavity 10 and being assemblied in the control circuit board of fuselage inner cavity 10 (not scheme
Show), fuselage 1 includes the fuselage roof (not shown) and fuselage bottom plate 11 for forming inner cavity 10；Control circuit board carries out unmanned plane
Control, including acceleration transducer, processing unit, flight control modules and gyro sensor etc..Carry device system is according to nothing
Man-machine practical application area is selected, and can be aerial device, extinguishing device, spraying device etc..At of the invention one
In embodiment, carry device system takes photo by plane module 2, including holder 21 and connects the camera 22 of holder 21.
Please further as shown in connection with fig. 2, unmanned plane shock mitigation system includes the first damping module 3 and the second damping module 4.?
On gravity direction, the first damping module 3 is located at the lower section of the second damping module 4.
First damping module system gives holder 21 damping, the second damping of the first vibration damper plate 31 and connection including connecting holder 21
First loading plate 33 of module 4, and the first elastic component 32 of connection the first vibration damper plate 31 and the first loading plate 33.
First vibration damper plate 31 is provided with the holder interconnecting piece 310 of connection holder 21 and centered on the holder interconnecting piece 310
The multiple linking arms 311 extended to external radiation.On gravity direction, the opposite end of the first elastic component 32 respectively with linking arm
311 and first loading plate 33 connect, and the one end of the first elastic component 32 being connected with linking arm 311 positioned at and the first loading plate 33
The top of the connected other end.Therefore, under the gravity of carry device, the first elastic component 32 is squeezed.
Specifically, the free end of the separate holder interconnecting piece 310 of each linking arm 311 is equipped with damping interconnecting piece 3110, subtracts
Shake interconnecting piece 3110 is connect with the first elastic component 32.Each linking arm 311 is connect with two the first elastic components 32.First vibration damper plate
31 top view is in cross, and there are four linking arm 311, the structure systems of four linking arms 311 to be with holder interconnecting piece 310 for setting
Center is centrosymmetric setting, and the top of four linking arms 311 system from holder interconnecting pieces 310 extends outwardly.From the foregoing, it will be observed that first
Elastic component 32 is provided with eight.
Specifically, the bottom end of holder interconnecting piece 310 is pierced by the first loading plate 33 and is fixed with installing with camera 22, accordingly,
First loading plate 33 is centrally formed with the abdicating through hole 330 stepped down to holder interconnecting piece 310.First loading plate 33 allows around this
Position through-hole 330 is provided with the fixed part 332 of the second damping module 4 of damping interconnecting piece 331 and connection of the first elastic component 32 of connection.
The number of damping interconnecting piece 331 is corresponding with the first elastic component 32.First loading plate, 33 system is folded upward at by plate body to be extended to form
The box body of opening upwards with accommodating chamber 335, including cassette bottom 333 and box wall 334.By damping interconnecting piece 331, the first elastic component
32 and first vibration damper plate 31 linking arm 311 constitute elastic shock attenuation component be arranged in accommodating chamber 335.332 system of fixed part is certainly
The cassette bottom 333 of first loading plate 33 extends upwardly to other than accommodating chamber 335, forms the column for being higher than box wall 334.Fixed part
332 are disposed adjacent with damping interconnecting piece 331, and specifically, fixed part 332 is arranged to four, are equipped between every two fixed part 332
Two damping interconnecting pieces 331.
Please further as shown in connection with fig. 3,32 system of the first elastic component shock-absorbing ball made of the flexible materials such as rubber or silica gel,
To improve damping effect, the first elastic component 32 is recessed inwardly from periphery is formed with the first connecting groove 321, the second connecting groove
323, positioned at shock reducing structure 322 between the two, and limited respectively to the first connecting groove 321 and the second connecting groove 323
Limit top 324 and limit bottom 325.The damping interconnecting piece 3110 of each linking arm 311 is set there are two through-hole is connected, and is covered respectively
In the first connecting groove 321 of two the first elastic components 32, upper surface of the limit top 324 downwardly against linking arm 311
To form fixation.It please join shown in Fig. 3, recess forms accommodating groove 3310, accommodating groove to the cassette bottom 333 of the first loading plate 33 upwards
3310 upper cell wall is formed there through connection through-hole 3311, and the damping interconnecting piece 331 includes the accommodating groove 3310 and described
Through-hole 3311 is connected, connection through-hole 3311 is sheathed in the second connecting groove 323 of shock-absorbing ball, the insertion storage of limit bottom 325
Slot 3310 and upper cell wall upwards against accommodating groove 3310, make shock-absorbing ball be fixedly mounted on damping interconnecting piece through the above arrangement
On 331.On gravity direction, shock reducing structure 322 is held on the first damping interconnecting piece 331 of loading plate 33 and subtracting for linking arm 311
It shakes between interconnecting piece 3110.For the elasticity for improving the first elastic component 32, shock reducing structure 322 uses hollow structure.In the present embodiment,
Limit top 324 is all made of circular design with limit bottom 325.
Second damping module, 4 system gives holder 22 and control circuit board damping simultaneously, the including the first loading plate 33 of connection
Second loading plate 43 of two vibration damper plates 41 and connection unmanned plane main body, and the second vibration damper plate 41 of connection and the second loading plate 43
Second elastic component 42.In one embodiment of the invention, the second loading plate 43 is the fuselage bottom plate 11 of unmanned plane.
Second vibration damper plate 41 be equipped with the first loading plate 33 be connected carry interconnecting piece 410, and with the second elastic component 42
Connected damping interconnecting piece 411, on gravity direction, the opposite end of the second elastic component 42 respectively with damping interconnecting piece 411 and
Fuselage bottom plate 11 connects, and the one end of the second elastic component 42 being connected with damping interconnecting piece 411 with fuselage bottom plate 11 positioned at being connected
The other end top.Therefore, under the gravity of carry device, the second elastic component 42 is squeezed.
The carry interconnecting piece 410 be all provided with the damping interconnecting piece 411 be set to it is multiple, the carry interconnecting piece 410 that
This, which is connected, constitutes main frame, and the damping interconnecting piece 411 is connected with the carry interconnecting piece 410 constitutes sub-frame, each described
Carry interconnecting piece 410 is connect at least two damping interconnecting pieces 411.
Specifically, the carry interconnecting piece 410 of the second vibration damper plate 41 is arranged to four, and each carry interconnecting piece 410 has spiral shell
Pit.The fixed part 332 of first loading plate 33 also has threaded hole, corresponds with about 410 carry interconnecting piece, passes through screw
Two threaded holes are connected and are locked by 5.The connection structure being made of two threaded holes and screw 5 is through fuselage bottom plate 11.Second damping
The damping interconnecting piece 411 of plate 41 is arranged to eight, and there are two connect with the carry for the opposite sides setting of each carry interconnecting piece 410
The damping interconnecting piece 411 that socket part 410 connects.
Specifically, the second vibration damper plate 41 includes linking arm 413 and connecting rod 412, is passed through between two carry interconnecting pieces 410
Connecting rod 412 connects, and is connected between damping interconnecting piece 411 and carry interconnecting piece 410 by linking arm 413.412 head and the tail of connecting rod
It is connected and constitutes tool there are four the quadrilateral frame (main frame) at turning, two linking arms 413 extends outward to form certainly from a turning
By holding (sub-frame), therefore, the second vibration damper plate 41 is whole in the quadrilateral frame (main frame+sub-frame) with eight pawls.Also
It is to say, carry interconnecting piece 410 is set to corner, and damping interconnecting piece 411 is set to the free end of linking arm 413, carry connection
Portion 410 is equidistant to two damping interconnecting pieces 411 being attached thereto.Preferably, damping interconnecting piece 411 and carry interconnecting piece
410 are centrosymmetric centered on the geometric center of the second vibration damper plate 41 distribution respectively.
It is easily understood that the second vibration damper plate 41 is additionally provided with the connection structure of connection control circuit board, control circuit board
Can directly be connect with the second vibration damper plate 41, can also by between third elastic component (not shown) and the second vibration damper plate 41 in succession
It connects, to form second level damping, the 4th elastic component (not shown) can also be added certainly, this is not restricted.Second vibration damper plate
41 can use the prior art with the connection structure of control circuit board, and no further details to be given herein.
It please join shown in Fig. 3, fuselage bottom plate 11 is equipped with the damping interconnecting piece 110 being connected with the second elastic component 42.
It please join shown in Fig. 2, the second elastic component 42 is similar to the structure of the first elastic component 32.Specifically, the second elastic component 42
It is the shock-absorbing ball made of the flexible materials such as rubber or silica gel, to improve damping effect, the second elastic component 42 concaves from periphery
It falls into and is formed with the first connecting groove 421, the second connecting groove 423, positioned at shock reducing structure 422 between the two, and respectively to the
The limit top 424 and limit bottom 425 of one connecting groove 421 and the limit of the second connecting groove 423.On gravity direction, subtract
Shake body 422 is held between the damping interconnecting piece 411 of the second vibration damper plate 41 and the damping interconnecting piece 110 of fuselage bottom plate 11.
Second elastic component 42 and the first elastic component 32 the difference is that, in order to easy to assembly, the second vibration damper plate 41
Damping interconnecting piece 411 is arranged to the connection through-hole with notch 414, and 424 use and first at the top of the limit of the second elastic component 42
The identical circular design of elastic component 32, and limit bottom 425 and use error-proof structure or use the elastic construction for being easy to compressive deformation,
Such as ellipse, rectangle etc..
Accordingly with the error-proof structure, the damping interconnecting piece 110 of fuselage bottom plate 11 is disposed through fuselage bottom plate 11
Fool proof hole, shape are adapted with limit bottom 425.Associated assembling process is as follows: firstly, the limit of the second elastic component 42
Position bottom 425 be aligned with fool proof hole after to lower loading fuselage bottom plate 11, enable fool proof hole be caught in the second of the second elastic component 42 and connect
Groove 423, limit bottom 425 form fixation upwards against the lower surface of fuselage bottom plate 11, secondly, rotating horizontally the second bullet
Property the appropriate angle of part 42, such as 90 degree, until limit bottom 425 because with fool proof hole dislocation due to must not be upwardly separated from fuselage bottom plate 11,
Finally, the damping interconnecting piece 411 of the second vibration damper plate 41 to be sheathed on to the first connection of the second elastic component 42 by 414 level of notch
In groove 421, top 424 is limited downwardly against the upper surface of damping interconnecting piece 411 to form fixation.
Accordingly with the elastic construction for being easy to compressive deformation, the damping interconnecting piece 110 of fuselage bottom plate 11 can use
General structure, such as circular through hole, at this point, the limit bottom 425 of the second elastic component 42 deforms under external force and is pressed directly into this
In circular through hole.Optionally, the limit bottom 425 of the second elastic component 42 increases elasticity by the way that groove 4250 is arranged more to hold
Easily in the circular through hole of indentation fuselage bottom plate 11, which does not need above-mentioned rotation process.
Preferably, the damping interconnecting piece 411 of the second vibration damper plate 41 is circumferentially distributed around the center of the machine body base 11,
In the circumferential direction, the notch of each adjacent two damping interconnecting piece 411 is 90 degree towards angle, is on the one hand convenient for the second vibration damper plate 41
On the other hand unmanned plane can effectively be avoided (to fly as reversed, putting down) when executing maneuver with the assembling of the second elastic component 42,
The opposition that carry device is formed enables the damping interconnecting piece 411 of the second vibration damper plate 41 be detached from the second elastic component 42.
Second elastic component 42 also differ in that with the first elastic component 32,422 system of shock reducing structure of the second elastic component 42
Solid construction, to increase mechanical strength.
Second vibration damper plate 41 is set to the fuselage inner cavity 10, and the control circuit board is fixed on second damping
Plate 41.By the second vibration damper plate 41, the elastic shock attenuation component that the second elastic component 42 and the second loading plate 43 are constituted is located in fuselage 1
(on).
In summary, the first damping module 3 plays level-one cushioning effect to module 2 of taking photo by plane, and the second damping module 4 is to taking photo by plane
Module 2 plays second level cushioning effect.Second damping module 4 also plays cushioning effect to control circuit board.
The shock attenuation needs of control circuit board are integrated to the second damping module 4 to be realized, enormously simplify unmanned plane
The structure of shock mitigation system, it is ingenious in design.Specific reason is as follows:
Due to control circuit board lighter in weight itself, additional increase counterweight is needed to can be only achieved better damping effect,
Due to unmanned aerial vehicle body narrow space, and the lift of small drone is smaller, and the additional counterweight that increases also will increase fuselage weight, leads to
Above-mentioned design is crossed, the first damping module 3 and module 2 of taking photo by plane are fixedly connected on the second vibration damper plate 41, as a part of damping,
Counterweight effect is played, the setting of additional weight has not only been eliminated, but also realizes damping effect.
In another embodiment of the invention, please join shown in Fig. 1 to Fig. 3, unmanned plane further includes being provided with battery (not scheme
Show) and storage battery battery compartment 6 battery module, the battery module be arranged in the first damping module 3 and the second damping module 4
Between, specifically, the fixed part 332 of the carry interconnecting piece 410 of the second vibration damper plate 41 and the first loading plate 33 respectively with battery compartment 6
Top 61 be fixedly connected with bottom end 62.The outer framework that 6 system of battery compartment is made of triangle or polygon engraved structure, the outline border
Frame, which encloses, is set as rectangular intracoelomic cavity to accommodate high capacity cell, so set, when unmanned plane work (hovering/maneuver),
Battery compartment 6 can lay down the strong torsion and vibration of a part, so further improve picture figure of the module 2 when taking photo by plane of taking photo by plane
The stability of picture.
Specifically, battery compartment 6 protrudes upward the first mounting portion 610 to be formed with threaded hole from top 61, and battery compartment 6 is certainly
Bottom end 62 protrudes out downwards the second mounting portion 620 to be formed with threaded hole.Respectively by screw 5, by the first mounting portion 610 and
410 locked and fixed of carry interconnecting piece of two vibration damper plates 41, the fixed part 332 of the second mounting portion 620 and the first loading plate 33 is locked
It is dead fixed.Preferably, pre-determined distance, such as 2.5mm are provided between the top 61 and fuselage bottom plate 11 of battery compartment 6.This it is default away from
From being to be closed according to the second vibration damper plate 41 and the snap-in structure of the second elastic component 42 and the coefficient of elasticity of the second elastic component 42
Reason setting.Because unmanned plane (flies) when executing maneuver as reversed, putting down, the opposition that carry device is formed passes through
Battery compartment 6 passes to the second vibration damper plate 41, and opposite second elastic component 42 of 41 damping interconnecting piece of the second vibration damper plate 411 is enabled to twist
Or offset, when the opposition is large enough to zero that enables the second vibration damper plate 41 be detached from the second elastic component 42 or be attached thereto
When part damages, serious consequence will be caused to unmanned plane during flying.It is provided between the top 61 and fuselage bottom plate 11 of battery compartment 6 above-mentioned
On the one hand pre-determined distance provides the deformation space of the second elastic component 42, its shock absorbing effect is played, on the other hand when second subtracts
When shake plate 41 reverses relative to the second elastic component 42 or deviates excessive, timely and effective it can prevent.
Specifically, battery module further includes battery compartment shield (not shown), which can be with the first loading plate 33
Cooperation up and down, is assembled into one.
The above is only a preferred embodiment of the present invention, is not intended to limit the scope of the invention, all in the present invention
Design under, using equivalent structure transformation made by description of the invention and accompanying drawing content, or directly/be used in other phases indirectly
The technical field of pass is included in scope of patent protection of the invention.
Claims (10)
1. a kind of unmanned plane shock mitigation system, for giving unmanned plane damping, which is characterized in that the unmanned plane includes unmanned plane main body
With carry device, the unmanned plane main body includes the fuselage with inner cavity and the control circuit board for being set to fuselage inner cavity, described
Unmanned plane shock mitigation system includes providing the second damping module of damping, institute to the carry device and the control circuit board respectively
The second damping module is stated to include the second loading plate for connecting the unmanned plane main body, be separately connected the carry device and the control
Second vibration damper plate of circuit board processed and the second elastic component of connection second loading plate and the second vibration damper plate.
2. unmanned plane shock mitigation system as described in claim 1, which is characterized in that the unmanned plane shock mitigation system further includes to institute
It states carry device and the first damping module of level-one damping is provided, the second damping module provides second level to the carry device and subtracts
Shake.
3. unmanned plane shock mitigation system as claimed in claim 2, which is characterized in that the first damping module includes described in connection
First vibration damper plate of carry device connects the first loading plate of second vibration damper plate and connects first vibration damper plate and institute
State the first elastic component of the first loading plate.
4. unmanned plane shock mitigation system as claimed in claim 3, which is characterized in that the fuselage of second loading plate system unmanned plane
Bottom plate, second vibration damper plate are set to the fuselage inner cavity, and the control circuit board is fixed on second vibration damper plate, described
Second vibration damper plate is equipped with the carry interconnecting piece connecting with first loading plate, and the damping connecting with second elastic component
Interconnecting piece, on gravity direction, the opposite end of second elastic component respectively with the damping interconnecting piece and the fuselage bottom
Plate connection, and one end of the connection damping interconnecting piece of second elastic component is located at the other end for connecting the fuselage bottom plate
Top.
5. unmanned plane shock mitigation system as claimed in claim 4, which is characterized in that the carry interconnecting piece is connect with the damping
Portion, which is all provided with, to be set to multiple, and the carry interconnecting piece, which is connected with each other, constitutes main frame, and the damping interconnecting piece is connect with the carry
Portion, which is connected, constitutes sub-frame, and each carry interconnecting piece is connect at least two damping interconnecting pieces.
6. unmanned plane shock mitigation system as claimed in claim 5, which is characterized in that the damping interconnecting piece system of first vibration damper plate
The tool connection through-hole jaggy of second elastic component is connected, the multiple damping interconnecting piece is in the machine body base
The heart is circumferentially distributed, in the circumferential direction, the notch of each adjacent two damping interconnecting piece towards angle be 90 degree.
7. unmanned plane shock mitigation system as claimed in claim 3, which is characterized in that carry device system has holder and camera
Module of taking photo by plane, first vibration damper plate, which is provided with the holder interconnecting piece for connecting the holder and with the holder interconnecting piece, is
Multiple linking arms that the heart extends to external radiation, on gravity direction, the opposite end of first elastic component respectively with the company
It connects arm to connect with first loading plate, and first elastic component connects one end of the linking arm positioned at connection described first
The top of the other end of loading plate；First loading plate is folded upward at by plate body extends to form the opening with accommodating chamber
Upward box body, including cassette bottom and box wall, the bottom end of the holder interconnecting piece be pierced by the cassette bottom of the first loading plate with the phase
Machine installation is fixed, and first loading plate is provided with the damping connection for connecting first elastic component around the holder interconnecting piece
Portion and the fixed part for connecting second vibration damper plate.
8. unmanned plane shock mitigation system as claimed in claim 7, which is characterized in that the unmanned plane further includes having battery compartment
Battery module, the battery compartment are arranged between the first damping module and the second damping module, second damping
The fixed part of the carry interconnecting piece of plate and first loading plate is fixedly connected with the top of the battery compartment and bottom end respectively, institute
State the outer framework that battery compartment is made of triangle or polygon engraved structure.
9. a kind of unmanned plane shock mitigation system, for giving unmanned plane damping, which is characterized in that the unmanned plane includes unmanned owner
Body, battery module and carry device, the unmanned plane shock mitigation system includes the first damping module and the second damping module, described
Second damping module include the second loading plate for connecting the unmanned plane main body, the second vibration damper plate of the connection battery module,
And the second elastic component of connection second loading plate and the second vibration damper plate, the first damping module include connecting the extension
The first vibration damper plate set is carried, the first loading plate and connection first vibration damper plate for connecting the battery module are held with first
First elastic component of support plate.
10. a kind of unmanned plane, which is characterized in that the unmanned plane includes unmanned plane as claimed in any one of claims 1-9 wherein
Shock mitigation system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811412662.4A CN109703771A (en) | 2018-11-23 | 2018-11-23 | Unmanned plane shock mitigation system and unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811412662.4A CN109703771A (en) | 2018-11-23 | 2018-11-23 | Unmanned plane shock mitigation system and unmanned plane |
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| Publication Number | Publication Date |
|---|---|
| CN109703771A true CN109703771A (en) | 2019-05-03 |
Family
ID=66255139
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811412662.4A Pending CN109703771A (en) | 2018-11-23 | 2018-11-23 | Unmanned plane shock mitigation system and unmanned plane |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN114183494A (en) * | 2021-12-06 | 2022-03-15 | 中国科学院长春光学精密机械与物理研究所 | Passive self-stabilizing vibration reduction platform for aerial downward-looking camera |
| CN114183494B (en) * | 2021-12-06 | 2024-01-26 | 中国科学院长春光学精密机械与物理研究所 | Passive self-stabilizing vibration reduction platform for aviation downward-looking camera |
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