CN105509741A - Flight control assembly and unmanned aerial vehicle - Google Patents
Flight control assembly and unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105509741A CN105509741A CN201610062737.5A CN201610062737A CN105509741A CN 105509741 A CN105509741 A CN 105509741A CN 201610062737 A CN201610062737 A CN 201610062737A CN 105509741 A CN105509741 A CN 105509741A
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- Prior art keywords
- fly
- control assembly
- shock
- damping
- hole
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title abstract 9
- 238000013016 damping Methods 0.000 claims abstract description 111
- 230000035939 shock Effects 0.000 claims description 61
- 239000006096 absorbing agent Substances 0.000 claims description 39
- 239000000463 material Substances 0.000 claims description 22
- 238000010521 absorption reaction Methods 0.000 claims description 18
- 239000006260 foam Substances 0.000 claims description 5
- 230000005484 gravity Effects 0.000 claims description 4
- 230000010354 integration Effects 0.000 claims description 4
- 230000003139 buffering effect Effects 0.000 claims description 2
- 230000001276 controlling effect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 229920000742 Cotton Polymers 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000004698 Polyethylene Substances 0.000 description 1
- 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
- 238000005259 measurement Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- -1 polyethylene Polymers 0.000 description 1
- 229920000573 polyethylene Polymers 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 239000012858 resilient material Substances 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
Abstract
The invention provides a flight control assembly. The flight control assembly comprises a flight control board, and further comprises damping structures connected to the flight control assembly; the flight control assembly is connected with a supporting body through the damping structures; the damping structures are used for damping vibration of the flight control assembly from the supporting body to realize overall damping of the flight control assembly. The invention further relates to an unmanned aerial vehicle employing the flight control assembly.
Description
Technical field
The present invention relates to aircraft field, particularly one flies control assembly and unmanned vehicle.
Background technology
The inertia measuring module flying to control assembly needs to take glissando to reduce the impact of external shock on described inertia measuring module, arranges vibration-absorptive material time often on the circuit board flying control assembly described in described inertia measuring module is assembled into and between described circuit board.Because the deadweight of described inertia measuring module is smaller, make the soft durometer of the vibration-absorptive material of described inertia measuring module, the isoparametric requirement of damping higher; And owing to needing to consider the assembly precision requirement between described inertia measuring module, described circuit board and described vibration-absorptive material three when assembling, cause assembling difficulty higher.
Summary of the invention
In view of this, a kind of unmanned vehicle flying to control assembly and fly sky assembly described in having of simple and convenient assembly is provided to provide.
One fly control assembly, it comprise fly control plate, described in fly control plate on be provided with at least one sensor assembly.Described fly to control assembly also comprise be connected to described in fly to control the shock-damping structure of plate, the described control assembly that flies is connected to carrier by described shock-damping structure, described shock-damping structure by flying described in buffering to control the vibrations from described carrier that are subject to of component integration, and then cushions the vibrations that described sensor assembly is subject to.
Further, described shock-damping structure comprise connect described carrier and described in fly to control the shock absorber part of plate, described shock absorber part for described in fly control assembly and carry out integral shock-absorbing.
Further, described shock absorber part is rubber damper; Or described shock absorber part is spring.
Further, described shock absorber part by by the mode compressed or the mode be stretched for described in fly control assembly and carry out integral shock-absorbing.
Further, described shock-damping structure also comprises support, and described support connects described carrier and described shock absorber part, and described shock-damping structure is connected to described carrier by described support.
Further, described support comprises web joint, and described support is connected to described carrier by described web joint.
Further, described shock absorber part comprises the first connecting portion, and described first connecting portion is connected to described web joint.
Further, described support also comprises from the two ends of described web joint respectively towards the described extension flying to control plate extension, and described extension offers connecting hole; Described first connecting portion comprises the first stopper section and is connected to the first support portion of described first stopper section, and described first support portion is housed in described connecting hole, and described first stopper section breasting on the bracket.
Further, the size of described first stopper section is greater than the size of described connecting hole.
Further, described shock absorber part also comprises second connecting portion opposing with described first connecting portion, flies to control plate described in described second connecting portion is connected to.
Further, described shock absorber part also comprises damping portion, and described damping portion offers host cavity, and described host cavity is for accommodating damping shock absorption material.
Further, described damping shock absorption part material is foam.
Further, the sidewall of described damping portion comprises curved-surface structure.
Further, described shock absorber part offers the first through hole and/or the second through hole that are connected with described host cavity, can be changed the described damping shock absorption material be filled in described host cavity by described first through hole and/or described second through hole.
Further, described damping portion connects described first connecting portion and described second connecting portion, and described first through hole is opened in described first connecting portion, and described second through hole is opened in described second connecting portion.
Further, the central shaft of described first through hole roughly overlaps with the central shaft of described second through hole.
Further, described in fly control plate also comprise the circuit board and functional module that are connected to described shock-damping structure, described functional module is arranged on described circuit board.
Further, the quantity of described shock-damping structure is two, and two described shock-damping structures connect the two ends of described circuit board respectively.
Further, device module, described sensor assembly comprises inertia measuring module.
A kind of unmanned vehicle, it comprises carrier and flies as above to control assembly, described in fly control assembly and be connected to described carrier.
Further, described in fly control assembly and be arranged at above described carrier, and one is applied along the pressure of gravity direction to described carrier because of the weight of self.
Further, described carrier is fuselage, described in fly control assembly be connected to described fuselage.
Of the present invention flying is adopted to control assembly, the described control plate that flies is connected with described shock-damping structure, the described control assembly that flies is connected to carrier by described shock-damping structure, flies to control the vibrations that are subject to of component integration described in described shock-damping structure can cushion, and then cushions the vibrations that described sensor assembly is subject to.Fly to control the assembly precision between plate and described shock-damping structure, simple and convenient assembly in assembling process described in considering.
Accompanying drawing explanation
Fig. 1 is the schematic perspective view flying to control assembly that an embodiment of the present invention provides.
Fig. 2 is the decomposing schematic representation that flying in Fig. 1 controls assembly.
Fig. 3 is the partial exploded view flying the unmanned vehicle controlling assembly had in Fig. 1.
Fig. 4 is the cut-open view flying the shock absorber part controlling assembly in Fig. 1.
Main element symbol description
| Fly to control assembly | 100 |
| Interface board | 10 |
| First surface | 11 |
| Second surface | 12 |
| Step trough | 13 |
| Cascaded surface | 14 |
| Fly to control plate | 20 |
| Circuit board | 21 |
| Functional module | 22 |
| Shock-damping structure | 30 |
| Support | 31 |
| Web joint | 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 |
| Host cavity | 3231 |
| Damping shock absorption material | 324 |
| Unmanned vehicle | 200 |
| Carrier | 201 |
| Erection column | 202 |
Following embodiment will further illustrate the present invention in conjunction with above-mentioned accompanying drawing.
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, be clearly and completely described the technical scheme in the embodiment of the present invention, obviously, described embodiment is only the present invention's part embodiment, instead of whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.
It should be noted that, when assembly is called as " being fixed on " another assembly, directly can there is assembly placed in the middle in it on another assembly or also.When an assembly is considered to " connection " another assembly, it can be directly connected to another assembly or may there is assembly placed in the middle simultaneously.When an assembly is considered to " being arranged at " another assembly, it can be set directly on another assembly or may there is assembly placed in the middle simultaneously.
Unless otherwise defined, all technology used herein and scientific terminology are identical with belonging to the implication that those skilled in the art of the present invention understand usually.The object of term used in the description of the invention herein just in order to describe specific embodiment, is not intended to be restriction the present invention.Term as used herein " and/or " comprise arbitrary and all combinations of one or more relevant Listed Items.
Below in conjunction with accompanying drawing, some embodiments of the present invention are elaborated.When not conflicting, the feature in following embodiment and embodiment can combine mutually.
See also Fig. 1 to Fig. 4, the one that an embodiment of the present invention provides flies to control assembly 100, described in fly to control assembly 100 comprise interface board 10, be arranged at described interface board 10 fly control plate 20 and be connected to the shock-damping structure 30 of described interface board 10.The described control assembly 100 that flies is connected to carrier by described shock-damping structure 30.Described shock-damping structure 30 can cushion the vibrations from described carrier that described interface board 10 is subject to, described shock-damping structure 30 for described in fly control assembly 100 carry out integral shock-absorbing.Be appreciated that in other embodiments, described interface board 10 flies control plate 20 can be integrated with described, or described interface board 10 can omit, described in fly to control plate 20 and be directly connected in described shock-damping structure 30.
Fly described in described interface board 10 can carry to control plate 20, in addition, the described control plate 20 that flies can also be electrically connected with other elements by described interface board 10, flies the communication controlling plate 20 and other elements described in realization.Control plate 20 and described shock-damping structure 30 is flown described in described interface board 10 connects.Described interface board 10 comprises first surface 11 and the second surface 12 opposing with described first surface 11, described interface board 10 offers the step trough 13 running through described second surface 12 and described first surface 11, and described step trough 13 includes the cascaded surface 14 away from described second surface 12.Described step trough 13 controls plate 20 for flying described in accommodating, described in fly control plate 20 and be arranged on described cascaded surface 14.Described interface board 10 also offers several accepting hole (not shown), and described interface board 10 is connected together by described several accepting hole and described shock-damping structure 30.Be appreciated that in other embodiments, described interface board 10 can also be connected with described shock-damping structure 30 by other means, as by the element such as bolt, pin with as described in shock-damping structure 30 be connected.In present embodiment, the quantity of described several accepting hole is four, two in four described accepting holes one end being positioned at described interface board 10, and two other in four described accepting holes is positioned at the other end of described interface board 10; Be appreciated that in other embodiments, the quantity of described accepting hole can increase according to actual needs or reduce.
The described control plate 20 that flies is for controlling the flight of unmanned vehicle.The described control plate 20 that flies also comprises circuit board 21 and is arranged at for realizing the functional module 22 of predetermined function on described circuit board 21, and described functional module 22 can comprise controller module, processor module, sensor assembly etc.Further, described sensor assembly can comprise inertia measuring module, temperature sensor module, Height sensor module, distance sensor module etc.Described inertia measuring module comprises acceleration transducer and gyroscope, and described inertia measuring module can measure the flight attitude information of described unmanned vehicle.In practical work process, for ensureing the accurate of measurement result and serviceable life, described inertia measuring module will avoid the impact of unexpected vibrations.In present embodiment, described circuit board 21 and described interface board 10 are common for doing counterweight for described functional module 22, to reduce described functional module 22 to the soft durometer of its vibration-absorptive material, the isoparametric requirement of damping, and can reach good damping effect.Described shock-damping structure 30 is connected with described interface board 10, in an assembling process without the need to considering the assembly precision between described shock-damping structure 30 and described functional module 22, simple and convenient assembly.Be appreciated that in other embodiments, described functional module 22 can adopt other objects to do counterweight, as sheet metal etc.
Described shock-damping structure 30 can connect described interface board 10 and described carrier.In present embodiment, the quantity of described shock-damping structure 30 is two, and two described shock-damping structures 30 are connected to the relative two ends of described interface board 10; The described control plate 20 that flies is between two described shock-damping structures 30.Described shock-damping structure 30 comprises support 31 and connects the shock absorber part 32 of described support 31 and described interface board 10, and described shock-damping structure 30 is connected to described carrier by described support 31.Be appreciated that in other embodiments, described support 31 can omit, and described shock absorber part 32 can be directly connected in described carrier.
Described support 31 comprises web joint 311, and the two ends of described web joint 311 are extended with extension 312 respectively towards described interface board 10, and described shock-damping structure 30 is connected to described carrier by described web joint 311.Described support 31 is connected to described shock absorber part 32 by described extension 312.Described web joint 311 offers several mounting hole 3111, and described web joint 311 is connected to described carrier by described several mounting hole 3111.In present embodiment, the quantity of described several mounting hole 3111 is two, and two described mounting hole 3111 intervals are arranged; Be appreciated that in other embodiments, the quantity of described several mounting hole 3111 can increase according to actual needs or reduce.Described extension 312 offers connecting hole 313, and described extension 312 is connected to described shock absorber part 32 by described connecting hole 313.
The vibrations from described carrier that described shock absorber part 32 is subject to for flying to control assembly 100 described in cushioning.Described shock absorber part 32 comprises the first connecting portion 321, second connecting portion 322 opposing with described first connecting portion 321 and is connected the damping portion 323 of described first connecting portion 321 and described second connecting portion 322.Described first connecting portion 321 comprises the first stopper section 3211 and is connected to the first support portion 3212 of described first stopper section 3211, described first support portion 3212 is housed in described connecting hole 313, and the first connecting portion 321 of described shock absorber part 32 is connected with described support 31.
In present embodiment, described first support portion 3212 extends towards a surface of described interface board 10 to the direction away from described first stopper section 3211 from described first stopper section 3211, and described first stopper section 3211 bears against on the extension 312 of described support 31.Described first stopper section 3211 is connected to the end of described first support portion 3212.The size of described first stopper section 3211 is greater than the size of described connecting hole 313, to prevent described first support portion 3212 from departing from from described connecting hole 313, and then prevents from described first connecting portion 321 from departing from described web joint 311 being connected.
Described second connecting portion 322 is connected to described interface board 10.Described second connecting portion 322 comprises the second stopper section 3221 and is connected to the second support portion 3222 of described second stopper section 3221, described second support portion 3222 is housed in a described accepting hole, and described second connecting portion 322 is connected with described interface board 10.Described second stopper section 3221 is connected to the end of described second support portion 3222, and the size of described second stopper section 3221 is greater than the size of described accepting hole, to depart from be connected to prevent described second connecting portion 322 with described interface board 10.
Be appreciated that described first connecting portion 321 and described second connecting portion 322 can omit, and the two ends of described damping portion 323 are connected respectively on described extension 312 and described interface board 10.In present embodiment, described damping portion 323 is the spheroidites be made up of rubber, according to concrete shock attenuation needs, by the damping effect regulating the wall thickness, shape, size etc. of described damping portion 323 can reach expection easily and efficiently, and damping debug time is shorter; Be appreciated that in other embodiments, described damping portion 323 can be made up of other resilient materials, as silica gel etc.
Be appreciated that in other embodiments, can fill damping shock absorption material 324 in described damping portion 323, described damping shock absorption material 324 forms combined type damping with described damping portion 323.Described first connecting portion 321 can offer the first through hole 3213, and described first through hole 3213 runs through described first connecting portion 321.Described first through hole 3213 can be the shape of circular hole or other any appropriate, as square hole, slotted eye etc.Described second connecting portion 322 offers the second through hole 3223, described second through hole 3223 runs through described second connecting portion 322, and the described damping shock absorption material be housed in described damping portion 323 can be replaced by the damping shock absorption material of different damping coefficient by described first through hole 3213 and described second through hole 3223.Described second through hole 3223 can be shoulder hole, the ladder aperture of described second through hole 3223 is less than or equal to the diameter of described first through hole 3213, departs from described damping portion 323 under gravity to prevent the damping shock absorption material 324 be filled in described damping portion 323 from described second through hole 3223.
Be appreciated that described first through hole 3213 and described second through hole 3223 can be opened in other positions of described shock absorber part 32, as the first connecting portion 321 as described in can being opened in and as described in the second connecting portion 322 sidepiece, as described in damping portion 323 first-class.The central shaft of described first through hole 3213 and the central shaft of described second through hole 3223 roughly overlap.
Described damping portion 323 offers the host cavity 3231 be connected with described first through hole 3213 and described second through hole 3223, and described host cavity 3231 is for accommodating described damping shock absorption material 324.The damping shock absorption material be housed in described host cavity 3231 can be replaced by the damping shock absorption material of different damping coefficient by described first through hole 3213 and described second through hole 3223, make described shock absorber part 32 adapt to different shock attenuation needs.The sidewall of described damping portion 323 comprises curved-surface structure, and in the present embodiment, the interior outside of the sidewall of described damping portion 323 is all in cambered surface.
Two sides of the sidewall of described damping portion 323 can a face be also curved surface, and another face is plane; Or two faces are all in curved surface.Described curved surface can be the structure such as cambered surface, wavy surfaces.Be appreciated that the sidewall of described damping portion 323 also can be two faces all in plane, and described damping portion 323 can be cylindric, rectangular-shaped, frustum etc.
In present embodiment, described damping shock absorption material 324 is foam, is appreciated that in other embodiments, and described damping shock absorption material can be cotton, polyfoam, compound expanded polyethylene foam, sponge, cotton etc.Described damping portion 323 forms combined type damping by rubber with coordinating of foam with described damping shock absorption material 324, the shock attenuation needs under making described shock absorber part 32 can adapt to Different Weight loading condition.
In present embodiment, the quantity of described shock absorber part 32 is two, and one end of two described shock absorber parts 32 is connected to two described extensions 312, and the other end is connected to described interface board 10.
In present embodiment, described shock absorber part 32 is shock-absorbing ball; Be appreciated that in other embodiments, described shock absorber part 32 can adopt other damper elements to substitute, as spring etc.
In present embodiment, described shock absorber part 32 by by the mode compressed for described in fly control assembly 100 and carry out integral shock-absorbing; Be appreciated that in other embodiments, described shock absorber part 32 can carry out damping by the mode be stretched.
The unmanned vehicle 200 that an embodiment of the present invention provides, described unmanned vehicle 200 comprise carrier 201 and be connected to described carrier 201 fly control assembly 100, described in fly control assembly 100 be connected to described carrier 201 by two described shock-damping structures 30.In present embodiment, described carrier 201 is the fuselage of described unmanned vehicle 200; Be appreciated that in other embodiments, described carrier 201 can be other parts, as the bracing frame etc. in fuselage as described in being arranged at.
Described carrier 201 is also provided with several erection column 202, and described carrier 201 is connected with two described shock-damping structures 30 by described several erection column 202.In present embodiment, the quantity of described several erection column 202 is four, and four described mounting holes 3111 of four described erection columns 202 shock-damping structure 30 described with two respectively match, and described carrier 201 is connected with two described shock-damping structures 30.Be appreciated that in other embodiments, the quantity of described several erection column 202 can increase according to actual needs or reduce.
The described control assembly 100 that flies is arranged at above described carrier 201, and applies one along the pressure of gravity direction because of the weight of self to described carrier 201.Particularly, fly control assembly 100 fly control plate 20 or fly control plate 20 and interface board 10 carry out counterweight by own wt, shock absorber part 32 is arranged at described carrier 201 and flies control plate 20 or carrier 201 and fly to control between plate 20 and interface board 10, plays the effect of damping.
Certainly, in other embodiments, described shock-damping structure 30 can be connected by other means with described carrier 201, as bolt connection, pin connection, buckle connection etc.
Of the present invention flying is adopted to control assembly, the described control plate that flies is connected with described shock-damping structure, the described control assembly that flies is connected to carrier by described shock-damping structure, flies to control the vibrations that are subject to of component integration described in described shock-damping structure can cushion, and then cushions the vibrations that described sensor assembly is subject to.Fly to control the assembly precision between plate and described shock-damping structure, simple and convenient assembly in assembling process described in considering.
In addition; those skilled in the art will be appreciated that; above embodiment is only used to the present invention is described; and be not used as limitation of the invention; as long as within spirit of the present invention, the suitable change do above embodiment and change all drop within the scope of protection of present invention.
Claims (22)
1. one kind flies to control assembly, it comprise fly control plate, control plate is provided with at least one sensor assembly to described flying, it is characterized in that: described in fly to control assembly also comprise be connected to described in fly to control the shock-damping structure of plate, the described control assembly that flies is connected to the carrier flying to control plate described in carrying by described shock-damping structure, described shock-damping structure by flying described in buffering to control the vibrations from described carrier that are subject to of component integration, and then cushions the vibrations that described sensor assembly is subject to.
2. fly as claimed in claim 1 to control assembly, it is characterized in that: described shock-damping structure comprise connect described carrier and described in fly to control the shock absorber part of plate, described shock absorber part for described in fly control assembly and carry out integral shock-absorbing.
3. fly as claimed in claim 2 to control assembly, it is characterized in that: described shock absorber part is rubber damper; Or described shock absorber part is spring.
4. fly as claimed in claim 2 to control assembly, it is characterized in that: described shock absorber part by by the mode compressed or the mode be stretched for described in fly control assembly and carry out integral shock-absorbing.
5. fly as claimed in claim 2 to control assembly, it is characterized in that: described shock-damping structure also comprises support, described support connects described carrier and described shock absorber part, and described shock-damping structure is connected to described carrier by described support.
6. fly as claimed in claim 5 to control assembly, it is characterized in that: described support comprises web joint, described support is connected to described carrier by described web joint.
7. fly as claimed in claim 6 to control assembly, it is characterized in that: described shock absorber part comprises the first connecting portion, described first connecting portion is connected to described web joint.
8. fly as claimed in claim 7 to control assembly, it is characterized in that: described support also comprises from the two ends of described web joint respectively towards the described extension flying to control plate extension, and described extension offers connecting hole; Described first connecting portion comprises the first stopper section and is connected to the first support portion of described first stopper section, and described first support portion is housed in described connecting hole, and described first stopper section breasting on the bracket.
9. fly as claimed in claim 8 to control assembly, it is characterized in that: the size of described first stopper section is greater than the size of described connecting hole.
10. fly as claimed in claim 7 to control assembly, it is characterized in that: described shock absorber part also comprises second connecting portion opposing with described first connecting portion, fly described in described second connecting portion is connected to control plate.
11. fly to control assembly as claimed in claim 2, and it is characterized in that: described shock absorber part also comprises damping portion, described damping portion offers host cavity, and described host cavity is for accommodating damping shock absorption material.
12. fly to control assembly as claimed in claim 11, it is characterized in that: described damping shock absorption part material is foam.
13. fly to control assembly as claimed in claim 11, it is characterized in that: the sidewall of described damping portion comprises curved-surface structure.
14. fly to control assembly as claimed in claim 11, it is characterized in that: described shock absorber part offers the first through hole and/or the second through hole that are connected with described host cavity, the described damping shock absorption material be filled in described host cavity can be changed by described first through hole and/or described second through hole.
15. flying as described in claim 10 or 14 control assembly, it is characterized in that: described damping portion connects described first connecting portion and described second connecting portion, and described first through hole is opened in described first connecting portion, and described second through hole is opened in described second connecting portion.
16. fly to control assembly as claimed in claim 14, it is characterized in that: the central shaft of described first through hole roughly overlaps with the central shaft of described second through hole.
17. fly as claimed in claim 1 control assembly, it is characterized in that: described in fly control plate also comprise the circuit board and functional module that are connected to described shock-damping structure, described functional module is arranged on described circuit board.
18. fly to control assembly as claimed in claim 17, it is characterized in that: the quantity of described shock-damping structure is two, and two described shock-damping structures connect the two ends of described circuit board respectively.
19. fly to control assembly as claimed in claim 17, and it is characterized in that: described functional module comprises described sensor assembly, described sensor assembly comprises inertia measuring module.
20. 1 kinds of unmanned vehicles, it comprise carrier and as described in any one of claim 1-19 flying control assembly, described in fly control assembly be connected to described carrier.
21. unmanned vehicles as claimed in claim 20, is characterized in that: described in fly control assembly and be arranged at above described carrier, and one is applied along the pressure of gravity direction to described carrier because of the weight of self.
22. unmanned vehicles as described in 21, is characterized in that: described carrier is fuselage, described in fly control assembly and be connected to described 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 |
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| CN105509741A true CN105509741A (en) | 2016-04-20 |
| CN105509741B CN105509741B (en) | 2019-02-01 |
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| 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 |
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Cited By (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 |
| CN107628261A (en) * | 2017-09-20 | 2018-01-26 | 歌尔科技有限公司 | A kind of IMU barometers component and unmanned plane |
| CN108513565A (en) * | 2017-06-27 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Unmanned plane |
| CN108601281A (en) * | 2018-04-24 | 2018-09-28 | 赫星科技有限公司 | Damping device, circuit board and the flight unmanned plane for being provided with the circuit board |
| CN108698703A (en) * | 2017-11-13 | 2018-10-23 | 深圳市大疆创新科技有限公司 | Motion-sensing device assembly and unmanned plane |
| 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 |
| 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 |
| CN110876271A (en) * | 2018-12-13 | 2020-03-10 | 深圳市大疆创新科技有限公司 | Shock absorption structure, mounting method and electronic equipment |
| CN112243328A (en) * | 2020-11-10 | 2021-01-19 | 萧晓玥 | Sensor high-frequency vibration conduction blocking method for unmanned vehicle controller |
| CN114745887A (en) * | 2022-04-08 | 2022-07-12 | 沃飞长空科技(成都)有限公司 | Flight control device with two-stage vibration reduction and aircraft |
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| CN107628261A (en) * | 2017-09-20 | 2018-01-26 | 歌尔科技有限公司 | A kind of IMU barometers component and unmanned plane |
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| CN108601281A (en) * | 2018-04-24 | 2018-09-28 | 赫星科技有限公司 | Damping device, circuit board and the flight unmanned plane for being provided with the circuit board |
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| CN110876271A (en) * | 2018-12-13 | 2020-03-10 | 深圳市大疆创新科技有限公司 | Shock absorption structure, mounting method and electronic equipment |
| 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 |
| CN114745887A (en) * | 2022-04-08 | 2022-07-12 | 沃飞长空科技(成都)有限公司 | Flight control device with two-stage vibration reduction and aircraft |
| 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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