CN105509741B - Fly control component and unmanned vehicle - Google Patents
Fly control component and unmanned vehicle Download PDFInfo
- Publication number
- CN105509741B CN105509741B CN201610062737.5A CN201610062737A CN105509741B CN 105509741 B CN105509741 B CN 105509741B CN 201610062737 A CN201610062737 A CN 201610062737A CN 105509741 B CN105509741 B CN 105509741B
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- Prior art keywords
- control component
- shock
- damping
- carrier
- winged control
- Prior art date
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- Expired - Fee Related
Links
- 238000013016 damping Methods 0.000 claims abstract description 112
- 230000035939 shock Effects 0.000 claims description 56
- 239000006096 absorbing agent Substances 0.000 claims description 36
- 239000000463 material Substances 0.000 claims description 20
- 238000010521 absorption reaction Methods 0.000 claims description 16
- 239000006260 foam Substances 0.000 claims description 4
- 230000005484 gravity Effects 0.000 claims description 4
- 230000003139 buffering effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 description 5
- 229920000742 Cotton Polymers 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 239000013013 elastic material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/10—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration
- G01C21/12—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning
- G01C21/16—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation
- G01C21/18—Stabilised platforms, e.g. by gyroscope
Landscapes
- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Automation & Control Theory (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Vibration Dampers (AREA)
Abstract
The present invention provides a kind of winged control component comprising flies control plate.The winged control component further includes the shock-damping structure for being connected to the winged control plate, the winged control component is connected to carrier by the shock-damping structure, the shock-damping structure is used to buffer the vibration from the carrier that the winged control component is subject to, and realizes the integral shock-absorbing of the winged control component.The invention further relates to the unmanned vehicles with the winged control component.
Description
Technical field
The present invention relates to aircraft fields, in particular to a kind of to fly control component and unmanned vehicle.
Background technique
The inertia measuring module for flying control component needs to take glissando to reduce external shock to the inertia measurement mould
The influence of block, often when on the circuit board that the inertia measuring module is assembled into the winged control component between the circuit board
Vibration-absorptive material is set.Since the self weight of the inertia measuring module is smaller, so that the vibration-absorptive material of the inertia measuring module
The parameters such as hardness, damping it is more demanding；And due to needing to consider the inertia measuring module, the circuit in assembling
Assembly precision requirement between plate and the vibration-absorptive material three, causes assembling difficulty higher.
Summary of the invention
In view of this, it is necessary to provide a kind of winged control component easy for assembly and the unmanned flight with the winged empty component
Device.
One kind flying control component comprising flies control plate, is provided at least one sensor module on the winged control plate.It is described to fly
Control component further includes the shock-damping structure for being connected to the winged control plate, and the winged control component is connected to load by the shock-damping structure
Body, the vibration from the carrier that the shock-damping structure is integrally subject to by buffering the winged control component, and then described in buffering
The vibration that sensor module is subject to.
Further, the shock-damping structure includes the shock absorber part for connecting the carrier and the winged control plate, the shock absorber part
Integral shock-absorbing is carried out for the winged control component.
Further, the shock absorber part is rubber damper；Or, the shock absorber part is spring.
Further, the shock absorber part is that the winged control component carries out by compressed mode or the mode being stretched
Integral shock-absorbing.
Further, the shock-damping structure further includes bracket, and the bracket connects the carrier and the shock absorber part, described
Shock-damping structure is connected to the carrier by the bracket.
Further, the bracket includes connecting plate, and the bracket is connected to the carrier by the connecting plate.
Further, the shock absorber part includes first connecting portion, and the first connecting portion is connected to the connecting plate.
Further, the bracket further includes the extension for being respectively facing the winged control plate from the both ends of the connecting plate and extending
Portion, the extension offer connecting hole；The first connecting portion is including the first stopper section and is connected to first stopper section
The first support portion, first support portion is housed in the connecting hole, and first stopper section is born against on the bracket.
Further, the size of first stopper section is greater than the size of the connecting hole.
Further, the shock absorber part further includes the second connecting portion opposite with the first connecting portion, and described second connects
Socket part is connected to the winged control plate.
Further, the shock absorber part further includes damping portion, and the damping portion offers accommodating chamber, and the accommodating chamber is used for
Accommodate damping shock absorption material.
Further, the damping shock absorption part material is foam.
Further, the side wall of the damping portion includes curved-surface structure.
Further, the shock absorber part offers the first through hole being connected with the accommodating chamber and/or the second through-hole, leads to
The damping shock absorption material being filled in the accommodating chamber can be replaced by crossing the first through hole and/or second through-hole.
Further, the damping portion connects the first connecting portion and the second connecting portion, the first through hole are opened
Set on the first connecting portion, second through-hole is opened in the second connecting portion.
Further, the central axis of the first through hole and the central axis of second through-hole substantially overlap.
Further, the winged control plate further includes the circuit board and functional module for being connected to the shock-damping structure, the function
Energy module is set on the circuit board.
Further, the quantity of the shock-damping structure is two, and two shock-damping structures are separately connected the circuit board
Both ends.
Further, device module, the sensor module include inertia measuring module.
A kind of unmanned vehicle comprising carrier and winged control component as described above, the winged control component is connected to described
Carrier.
Further, the winged control component is set to above the carrier, and because the weight of itself applies the carrier
One along gravity direction pressure.
Further, the carrier is fuselage, and the winged control component is connected to the fuselage.
Using winged control component of the invention, the winged control plate is connected with the shock-damping structure, and the winged control component passes through
The shock-damping structure is connected to carrier, and the shock-damping structure can buffer the vibration that the winged control component is integrally subject to, Jin Erhuan
Rush the vibration that the sensor module is subject to.Without considering the group between the winged control plate and the shock-damping structure in assembling process
Precision is filled, it is easy for assembly.
Detailed description of the invention
Fig. 1 is the stereoscopic schematic diagram for the winged control component that an embodiment of the present invention provides.
Fig. 2 is the decomposition diagram of the winged control component in Fig. 1.
Fig. 3 is the partial exploded view with the unmanned vehicle of the winged control component in Fig. 1.
Fig. 4 is the cross-sectional view of the shock absorber part of the winged control component in Fig. 1.
Main element symbol description
| Fly control component | 100 |
| Interface board | 10 |
| First surface | 11 |
| Second surface | 12 |
| Stepped groove | 13 |
| Cascaded surface | 14 |
| Fly control plate | 20 |
| Circuit board | 21 |
| Functional module | 22 |
| Shock-damping structure | 30 |
| Bracket | 31 |
| Connecting plate | 311 |
| Mounting hole | 3111 |
| Extension | 312 |
| Connecting hole | 313 |
| Shock absorber part | 32 |
| First connecting portion | 321 |
| First stopper section | 3211 |
| First support portion | 3212 |
| First through hole | 3213 |
| Second connecting portion | 322 |
| Second stopper section | 3221 |
| Second support portion | 3222 |
| Second through-hole | 3223 |
| Damping portion | 323 |
| Accommodating chamber | 3231 |
| Damping shock absorption material | 324 |
| Unmanned vehicle | 200 |
| Carrier | 201 |
| Mounting post | 202 |
The present invention that the following detailed description will be further explained with reference to the above drawings.
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 embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
It should be noted that it can be directly on another component when component is referred to as " being fixed on " another component
Or there may also be components placed in the middle.When a component is considered as " connection " another component, it, which can be, is directly connected to
To another component or it may be simultaneously present component placed in the middle.When a component is considered as " being set to " another component, it
It can be and be set up directly on another component or may be simultaneously present component placed in the middle.
Unless otherwise defined, all technical and scientific terms used herein and belong to technical field of the invention
The normally understood meaning of technical staff is identical.Term as used herein in the specification of the present invention is intended merely to description tool
The purpose of the embodiment of body, it is not intended that in the limitation present invention.Term " and or " used herein includes one or more phases
Any and all combinations of the listed item of pass.
With reference to the accompanying drawing, it elaborates to some embodiments of the present invention.In the absence of conflict, following
Feature in embodiment and embodiment can be combined with each other.
Also referring to Fig. 1 to Fig. 4, one kind that an embodiment of the present invention provides flies control component 100, the winged control component
100 include interface board 10, be set to the winged control plate 20 of the interface board 10 and be connected to the shock-damping structure 30 of the interface board 10.
The winged control component 100 is connected to carrier by the shock-damping structure 30.The shock-damping structure 30 can buffer the interface board
10 vibrations from the carrier being subject to, the shock-damping structure 30 are that the winged control component 100 carries out integral shock-absorbing.It can manage
Solution, in other embodiments, the interface board 10 can be integrated with the winged control plate 20 or the interface board 10 can be with
It omits, the winged control plate 20 is directly connected in the shock-damping structure 30.
The interface board 10 can carry the winged control plate 20, in addition, the interface board 10 can also be by the winged control plate
20 are electrically connected with other elements, realize the communication of winged the control plate 20 and other elements.The interface board 10 connects the winged control
Plate 20 and the shock-damping structure 30.The interface board 10 includes first surface 11 and second table opposite with the first surface 11
Face 12, the interface board 10 offer the stepped groove 13 through the second surface 12 and the first surface 11, the ladder
Slot 13 includes the cascaded surface 14 far from the second surface 12.The stepped groove 13 is described for accommodating the winged control plate 20
Fly control plate 20 to be arranged on the cascaded surface 14.The interface board 10 is also provided with several accepting hole (not shown), the interface
Plate 10 is connected together by several accepting holes with the shock-damping structure 30.It is appreciated that in other embodiments, it is described
Interface board 10 can also be connected with the shock-damping structure 30 by other means, such as by bolt, pin element with it is described
Shock-damping structure 30 is connected.In present embodiment, the quantity of several accepting holes is four, two in four accepting holes
A one end positioned at the interface board 10, other two in four accepting holes are located at the other end of the interface board 10；
It is appreciated that in other embodiments, the quantity of the accepting hole can increase or reduce according to actual needs.
The winged control plate 20 is used to control the flight of unmanned vehicle.The winged control plate 20 further includes circuit board 21 and sets
It is placed in the functional module 22 on the circuit board 21 for realizing predetermined function, the functional module 22 may include controller mould
Block, processor module, sensor module etc..Further, the sensor module may include inertia measuring module, temperature biography
Sensor module, Height sensor module, distance sensor module etc..The inertia measuring module include acceleration transducer and
Gyroscope, the inertia measuring module can measure the flight attitude information of the unmanned vehicle.In practical work process,
For the accurate and service life for guaranteeing measurement result, the inertia measuring module will avoid the influence of unexpected vibration.This
In embodiment, the circuit board 21 and the interface board 10 are provided commonly for doing counterweight for the functional module 22, to reduce
Requirement of the functional module 22 to parameters such as hardness, the dampings of its vibration-absorptive material is stated, and preferable damping effect can be reached.Institute
It states shock-damping structure 30 to be connected with the interface board 10, in an assembling process without considering the shock-damping structure 30 and the function
Assembly precision between module 22, it is easy for assembly.It is appreciated that in other embodiments, the functional module 22 can adopt
Counterweight, such as metal plate are done with other objects.
The shock-damping structure 30 can connect the interface board 10 and the carrier.In present embodiment, the damping knot
The quantity of structure 30 is two, and two shock-damping structures 30 are connected to the opposite both ends of the interface board 10；It is described to fly
Plate 20 is controlled to be located between two shock-damping structures 30.The shock-damping structure 30 includes bracket 31 and the connection bracket 31 and institute
The shock absorber part 32 of interface board 10 is stated, the shock-damping structure 30 is connected to the carrier by the bracket 31.It is appreciated that at it
In his embodiment, the bracket 31 be can be omitted, and the shock absorber part 32 can be directly connected to the carrier.
The bracket 31 includes connecting plate 311, and the both ends of the connecting plate 311 have been each extended over towards the interface board 10
Extension 312, the shock-damping structure 30 are connected to the carrier by the connecting plate 311.The bracket 31 is prolonged by described
Extending portion 312 is connected to the shock absorber part 32.The connecting plate 311 offers several mounting holes 3111, and the connecting plate 311 passes through
Several mounting holes 3111 are connected to the carrier.In present embodiment, the quantity of several mounting holes 3111 is two,
Two interval of mounting hole 3111 settings；It is appreciated that in other embodiments, the quantity of several mounting holes 3111
It can increase or reduce according to actual needs.The extension 312 offers connecting hole 313, and the extension 312 passes through institute
It states connecting hole 313 and is connected to the shock absorber part 32.
The shock absorber part 32 is used to buffer the vibration from the carrier that the winged control component 100 is subject to.The damping
Part 32 includes that first connecting portion 321, the second connecting portion 322 opposite with the first connecting portion 321 and connection described first connect
The damping portion 323 of socket part 321 and the second connecting portion 322.The first connecting portion 321 includes the first stopper section 3211 and connects
It is connected to the first support portion 3212 of first stopper section 3211, first support portion 3212 is housed in the connecting hole 313
It is interior, so that the first connecting portion 321 of the shock absorber part 32 is connected with the bracket 31.
In present embodiment, first support portion 3212 is from first stopper section 3211 towards the interface board 10
One table extends away from the direction of first stopper section 3211, and first stopper section 3211 bears against the bracket 31
Extension 312 on.First stopper section 3211 is connected to the end of first support portion 3212.First stopper section
3211 size is greater than the size of the connecting hole 313, to prevent first support portion 3212 de- from the connecting hole 313
From, and then the first connecting portion 321 is prevented to be disconnected with the connecting plate 311.
The second connecting portion 322 is connected to the interface board 10.The second connecting portion 322 includes the second stopper section
3221 and it is connected to the second support portion 3222 of second stopper section 3221, second support portion 3222 is housed in an institute
It states in accepting hole, the second connecting portion 322 is made to be connected with the interface board 10.Second stopper section 3221 is connected to institute
The end of the second support portion 3222 is stated, the size of second stopper section 3221 is greater than the size of the accepting hole, to prevent
Second connecting portion 322 is stated to be disconnected with the interface board 10.
It is appreciated that the first connecting portion 321 and the second connecting portion 322 can be omitted, and by the damping portion
323 both ends are connected respectively on the extension 312 and the interface board 10.In present embodiment, the damping portion 323 is
Orbicule made of rubber, according to specific shock attenuation needs, i.e. by wall thickness, shape, size of the adjusting damping portion 323 etc.
Expected damping effect can easily and efficiently be reached, and damping debug time is shorter；It is appreciated that in other embodiments,
The damping portion 323 can be made of other elastic materials, such as silica gel.
It is appreciated that in other embodiments, damping shock absorption material 324 can be filled in the damping portion 323, it is described
Damping shock absorption material 324 and the damping portion 323 form combined type damping.The first connecting portion 321 can offer first
Through-hole 3213, the first through hole 3213 run through the first connecting portion 321.The first through hole 3213 can for circular hole or
Any other suitable shape, such as square hole, slotted eye.The second connecting portion 322 offers the second through-hole 3223, described
Second through-hole 3223 runs through the second connecting portion 322, and the damping shock absorption material being housed in the damping portion 323 can
The damping shock absorption material of different damping coefficient is replaced by by the first through hole 3213 and second through-hole 3223.It is described
Second through-hole 3223 can be stepped hole, and the ladder aperture of second through-hole 3223 is less than or equal to the first through hole 3213
Diameter, to prevent the damping shock absorption material 324 being filled in the damping portion 323 under the effect of gravity from second through-hole
3223 are detached from the damping portion 323.
It is appreciated that the first through hole 3213 and second through-hole 3223 can be opened in its of the shock absorber part 32
His position, as described in can be opened in the side of first connecting portion 321 and the second connecting portion 322, in the damping portion 323
Deng.The central axis of the central axis of the first through hole 3213 and second through-hole 3223 substantially overlaps.
The damping portion 323 offers the accommodating chamber being connected with the first through hole 3213 and second through-hole 3223
3231, the accommodating chamber 3231 is for accommodating the damping shock absorption material 324.The damping being housed in the accommodating chamber 3231 subtracts
Blanket can be subtracted by the damping that the first through hole 3213 and second through-hole 3223 are replaced by different damping coefficient
Blanket makes the shock absorber part 32 adapt to different shock attenuation needs.The side wall of the damping portion 323 includes curved-surface structure, at this
In embodiment, the interior and exterior of the side wall of the damping portion 323 is in cambered surface.
Two sides of the side wall of the damping portion 323 can also a face it is in curved surface, another face be in plane；Or two
Face is in curved surface.The curved surface can be the structures such as cambered surface, wavy surfaces.It is appreciated that the side wall of the damping portion 323 can also
It is in plane for two faces, and the damping portion 323 can be cylindric, rectangular-shape, pyramidal etc..
In present embodiment, the damping shock absorption material 324 is foam, it will be understood that in other embodiments, described
Damping shock absorption material can be cotton, foamed plastics, compound pearl cotton, sponge, cotton etc..The damping portion 323 with it is described
Damping shock absorption material 324 cooperatively forms combined type damping by rubber and foam, and the shock absorber part 32 is made to be adapted to difference
Shock attenuation needs in the case of mass loading.
In present embodiment, the quantity of the shock absorber part 32 is two, and one end of two shock absorber parts 32 is separately connected
In two extensions 312, the other end is connected to the interface board 10.
In present embodiment, the shock absorber part 32 is shock-absorbing ball；It is appreciated that in other embodiments, the damping
Part 32 can be substituted using other damper elements, such as spring.
In present embodiment, the shock absorber part 32 is that the winged control component 100 carries out whole subtract by compressed mode
Shake；It is appreciated that in other embodiments, the shock absorber part 32 can carry out damping by way of being stretched.
The unmanned vehicle 200 that an embodiment of the present invention provides, the unmanned vehicle 200 include carrier 201 and connect
It is connected to the winged control component 100 of the carrier 201, the winged control component 100 is connected to described by two shock-damping structures 30
Carrier 201.In present embodiment, the carrier 201 is the fuselage of the unmanned vehicle 200；It is appreciated that in other implementations
In mode, the carrier 201 can be other components, the support frame as described in being set in fuselage.
Be additionally provided with several mounting posts 202 on the carrier 201, the carrier 201 by several mounting posts 202 with
Two shock-damping structures 30 are connected.In present embodiment, the quantity of several mounting posts 202 is four, described in four
Mounting post 202 is matched with four mounting holes 3111 of two shock-damping structures 30 respectively, makes the carrier 201 and two
A shock-damping structure 30 is connected.It is appreciated that in other embodiments, the quantity of several mounting posts 202 can be with
Increase according to actual needs or reduces.
The winged control component 100 is set to 201 top of carrier, and applies because of the weight of itself to the carrier 201
Add the pressure along gravity direction.Specifically, the winged control plate 20 of winged control component 100 or winged control plate 20 and interface board 10 pass through itself
Weight carries out counterweight, and shock absorber part 32 is set to the carrier 201 and flies control plate 20 or carrier 201 and fly control plate 20 and interface board 10
Between, play the role of damping.
Certainly, in other embodiments, the shock-damping structure 30 can connect by other means with the carrier 201
It connects, such as is bolted, pin connection, snaps connection.
Using winged control component of the invention, the winged control plate is connected with the shock-damping structure, and the winged control component passes through
The shock-damping structure is connected to carrier, and the shock-damping structure can buffer the vibration that the winged control component is integrally subject to, Jin Erhuan
Rush the vibration that the sensor module is subject to.Without considering the group between the winged control plate and the shock-damping structure in assembling process
Precision is filled, it is easy for assembly.
In addition, those skilled in the art it should be appreciated that more than embodiment be intended merely to illustrate this
Invention, and be not used as limitation of the invention, as long as within spirit of the invention, to above embodiments institute
The appropriate change and variation made all are fallen within the scope of protection of present invention.
Claims (20)
1. one kind flies control component comprising fly control plate, be provided at least one sensor module on the winged control plate, feature exists
In: the winged control component further includes the shock-damping structure for being connected to the winged control plate, and the winged control component passes through the shock-damping structure
It is connected to the carrier for carrying the winged control plate, the winged control plate further includes the circuit board and function mould for being connected to the shock-damping structure
Block, the functional module are set on the circuit board, and the quantity of the shock-damping structure is two, two shock-damping structures point
The both ends of the circuit board are not connected, and the shock-damping structure comes from the carrier by what the buffering winged control component was integrally subject to
Vibration, and then buffer the vibration that the sensor module is subject to；
The winged control component further includes interface board, and the interface board is for carrying the winged control plate.
2. as described in claim 1 fly control component, it is characterised in that: the shock-damping structure includes connecting the carrier and described
Fly the shock absorber part of control plate, the shock absorber part is that the winged control component carries out integral shock-absorbing.
3. as claimed in claim 2 fly control component, it is characterised in that: the shock absorber part is rubber damper；Or, the damping
Part is spring.
4. as claimed in claim 2 fly control component, it is characterised in that: the shock absorber part is by compressed mode or is drawn
The mode stretched is that the winged control component carries out integral shock-absorbing.
5. as claimed in claim 2 fly control component, it is characterised in that: the shock-damping structure further includes bracket, and the bracket connects
The carrier and the shock absorber part are connect, the shock-damping structure is connected to the carrier by the bracket.
6. as claimed in claim 5 fly control component, it is characterised in that: the bracket includes connecting plate, and the bracket passes through institute
It states connecting plate and is connected to the carrier.
7. as claimed in claim 6 fly control component, it is characterised in that: the shock absorber part includes first connecting portion, and described first
Interconnecting piece is connected to the connecting plate.
8. as claimed in claim 7 fly control component, it is characterised in that: the bracket further includes from the both ends of the connecting plate point
The extension not extended towards the winged control plate, the extension offer connecting hole；The first connecting portion is stopped including first
Stopper and the first support portion for being connected to first stopper section, first support portion is housed in the connecting hole, described
First stopper section is born against on the bracket.
9. as claimed in claim 8 fly control component, it is characterised in that: the size of first stopper section is greater than the connecting hole
Size.
10. as claimed in claim 7 fly control component, it is characterised in that: the shock absorber part further includes and the first connecting portion
Opposite second connecting portion, the second connecting portion are connected to the winged control plate.
11. as claimed in claim 2 fly control component, it is characterised in that: the shock absorber part further includes damping portion, the damping portion
Accommodating chamber is offered, the accommodating chamber is for accommodating damping shock absorption material.
12. as claimed in claim 11 fly control component, it is characterised in that: the damping shock absorption part material is foam.
13. as claimed in claim 11 fly control component, it is characterised in that: the side wall of the damping portion includes curved-surface structure.
14. as claimed in claim 11 fly control component, it is characterised in that: the shock absorber part is offered to be connected with the accommodating chamber
Logical first through hole and/or the second through-hole can be replaced by the first through hole and/or second through-hole described in being filled in
The damping shock absorption material in accommodating chamber.
15. the winged control component as described in claim 10 or 14, it is characterised in that: the damping portion connects the first connecting portion
And the second connecting portion, the first through hole are opened in the first connecting portion, second through-hole is opened in described second
Interconnecting piece.
16. as claimed in claim 14 fly control component, it is characterised in that: the central axis of the first through hole is logical with described second
The central axis in hole substantially overlaps.
17. as described in claim 1 fly control component, it is characterised in that: the functional module includes the sensor module, institute
Stating sensor module includes inertia measuring module.
18. a kind of unmanned vehicle comprising carrier and such as described in any item winged control components of claim 1-17, the winged control
Component is connected to the carrier.
19. unmanned vehicle as claimed in claim 18, it is characterised in that: the winged control component is set on the carrier
Side, and because the weight of itself applies the pressure along gravity direction to the carrier.
20. unmanned vehicle as claimed in claim 19, it is characterised in that: the carrier is fuselage, and the winged control component connects
It is connected to the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610062737.5A CN105509741B (en) | 2016-01-29 | 2016-01-29 | Fly control component and unmanned vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610062737.5A CN105509741B (en) | 2016-01-29 | 2016-01-29 | Fly control component and unmanned vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105509741A CN105509741A (en) | 2016-04-20 |
| CN105509741B true CN105509741B (en) | 2019-02-01 |
Family
ID=55717898
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610062737.5A Expired - Fee Related CN105509741B (en) | 2016-01-29 | 2016-01-29 | Fly control component and unmanned vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105509741B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106015424A (en) * | 2016-06-21 | 2016-10-12 | 深圳市高巨创新科技开发有限公司 | Shock absorption device of unmanned aerial vehicle |
| CN108513565B (en) * | 2017-06-27 | 2021-11-23 | 深圳市大疆创新科技有限公司 | Unmanned plane |
| CN107628261B (en) * | 2017-09-20 | 2024-04-05 | 歌尔科技有限公司 | IMU barometer subassembly and unmanned aerial vehicle |
| CN108698703B (en) * | 2017-11-13 | 2022-08-26 | 深圳市大疆创新科技有限公司 | Motion sensor subassembly and unmanned aerial vehicle |
| WO2019148430A1 (en) * | 2018-02-01 | 2019-08-08 | 深圳市固胜智能科技有限公司 | Mounting structure for inertial measurement unit and pan-tilt device |
| CN108601281B (en) * | 2018-04-24 | 2020-11-03 | 赫星科技有限公司 | A damping device, circuit board and flight unmanned aerial vehicle for unmanned aerial vehicle |
| CN108839808A (en) * | 2018-07-05 | 2018-11-20 | 上海歌尔泰克机器人有限公司 | Flight control assemblies and unmanned vehicle |
| WO2020118628A1 (en) * | 2018-12-13 | 2020-06-18 | 深圳市大疆创新科技有限公司 | Vibration-reducing structure, installation method, and electronic device |
| CN112243328A (en) * | 2020-11-10 | 2021-01-19 | 萧晓玥 | Sensor high-frequency vibration conduction blocking method for unmanned vehicle controller |
| CN114745887B (en) * | 2022-04-08 | 2023-09-22 | 四川傲势科技有限公司 | Flight control device with secondary vibration reduction and aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203037259U (en) * | 2012-11-22 | 2013-07-03 | 深圳市大疆创新科技有限公司 | Control module for aircraft |
| CH708275A2 (en) * | 2013-07-04 | 2015-01-15 | Marco Tausel | airtight inflatable support structure for unmanned aerial vehicles. |
| WO2015149263A1 (en) * | 2014-03-31 | 2015-10-08 | 深圳市大疆创新科技有限公司 | Damping device and aircraft using damping device |
| CN204553674U (en) * | 2015-03-31 | 2015-08-12 | 深圳市大疆创新科技有限公司 | Damping device, sensing equipment and there is the aircraft of this sensing equipment |
| CN204692419U (en) * | 2015-04-08 | 2015-10-07 | 深圳市大疆创新科技有限公司 | Shock bracket and apply the flight equipment of this shock bracket |
| CN104787298B (en) * | 2015-04-08 | 2018-07-24 | 深圳市大疆创新科技有限公司 | Aircraft |
| CN104776141B (en) * | 2015-04-08 | 2017-04-19 | 深圳市大疆创新科技有限公司 | Damping bracket and flight equipment applying same |
| CN204956943U (en) * | 2015-07-13 | 2016-01-13 | 深圳一电科技有限公司 | Unmanned vehicles's shock -absorbing structure and unmanned vehicles |
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2016
- 2016-01-29 CN CN201610062737.5A patent/CN105509741B/en not_active Expired - Fee Related
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| CN105509741A (en) | 2016-04-20 |
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