CN205491484U - Fly to control subassembly and unmanned vehicles - Google Patents
Fly to control subassembly and unmanned vehicles Download PDFInfo
- Publication number
- CN205491484U CN205491484U CN201620091449.8U CN201620091449U CN205491484U CN 205491484 U CN205491484 U CN 205491484U CN 201620091449 U CN201620091449 U CN 201620091449U CN 205491484 U CN205491484 U CN 205491484U
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- Prior art keywords
- fly
- control assembly
- shock
- damping
- hole
- Prior art date
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- Expired - Fee Related
Links
- 230000035939 shock Effects 0.000 claims abstract description 65
- 230000003139 buffering effect Effects 0.000 claims abstract description 4
- 238000013016 damping Methods 0.000 claims description 104
- 239000006096 absorbing agent Substances 0.000 claims description 39
- 239000000463 material Substances 0.000 claims description 23
- 238000010521 absorption reaction Methods 0.000 claims description 18
- 239000000872 buffer Substances 0.000 claims description 7
- 239000006260 foam Substances 0.000 claims description 6
- 230000005484 gravity Effects 0.000 claims 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
- 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
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
Abstract
The utility model provides a fly to control the subassembly, its include the interface board and connect in the interface board fly to control the board. Fly to control the subassembly still including connect in the shock -absorbing structure of interface board, it passes through to fly to control the subassembly shock -absorbing structure connects in the carrier, shock -absorbing structure is used for the buffering coming from that the subassembly received fly to control the vibrations of carrier realize fly to control the whole shock attenuation of subassembly. The utility model discloses still relate to and having fly to control the unmanned vehicles of subassembly.
Description
Technical field
This utility model relates to aircraft field, flies to control assembly and unmanned vehicle particularly to one.
Background technology
The inertia measuring module flying to control assembly needs to take glissando to reduce the external shock impact on described inertia measuring module, often arranges vibration-absorptive material when flying described in described inertia measuring module is assembled into control on the circuit board of assembly and between described circuit board.Owing to the deadweight of described inertia measuring module is smaller so that the soft durometer of the vibration-absorptive material of described inertia measuring module, to damp isoparametric requirement 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.
Utility model content
In view of this, it is necessary to provide a kind of simple and convenient assembly fly control assembly and fly the unmanned vehicle of sky assembly described in having.
One flies to control assembly, it include interface board and be connected to described interface board fly control plate, described in fly to control on plate and be provided with at least one sensor assembly.The described control assembly that flies also includes being connected to the shock-damping structure of described interface board, the described control assembly that flies is connected to carrier by described shock-damping structure, described shock-damping structure flies to control the shaking from described carrier that assembly entirety is subject to described in can buffering, and then buffers the vibrations that described sensor assembly is subject to.
Further, described interface board offer the groove that groove is connected with described groove, described groove and described groove be used for housing described in fly to control plate.
Further, described shock-damping structure include connecting described carrier and described in fly to control the shock absorber part of plate, described shock absorber part be described in fly to 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 by the way of compressing or the mode that is stretched be described in fly to control assembly and carry out integral shock-absorbing.
Further, described shock-damping structure also includes 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 includes that connecting plate, described support are connected to described carrier by described connecting plate.
Further, described shock absorber part includes that the first connecting portion, described first connecting portion are connected to described connecting plate.
Further, described support also include from the two ends of described connecting plate be respectively facing described in fly control plate extend extension, described extension offers connecting hole；Described first connecting portion includes the first stopper section and is connected to the first supporting part of described first stopper section, and described first supporting part is housed in described connecting hole, and described first stopper section breasting is on the bracket.
Further, the size of described first stopper section is more than the size of described connecting hole.
Further, described shock absorber part also includes second connecting portion opposing with described first connecting portion, described second connecting portion be connected to described in fly control plate.
Further, described shock absorber part also includes that damping portion, described damping portion offer host cavity, and described host cavity is used for housing damping shock absorption material.
Further, described damping shock absorption part material is foam.
Further, the sidewall of described damping portion includes curved-surface structure.
Further, described shock absorber part offers the first through hole and/or the second through hole being connected with described host cavity, can be changed the described damping shock absorption material being filled in described host cavity by described first through hole and/or described second through hole.
Further, the central shaft of described first through hole substantially overlaps with the central shaft of 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, described interface board offers accepting hole；Described second connecting portion includes the second stopper section and connects second supporting part of Ei and described second stopper section, and described second supporting part is housed in described accepting hole, makes described second connecting portion be connected to described interface board.
Further, the size of described second stopper section is more than the size of described accepting hole.
Further, described in fly to control plate and also include being connected to circuit board and the functional module of described interface board, 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 interface board respectively, described in fly control plate between two described shock-damping structures.
Further, described functional module includes that described sensor assembly, described sensor assembly include inertia measuring module.
A kind of unmanned vehicle, it includes fuselage and flies as above to control assembly, described in fly to control assembly and be connected to described carrier.
Further, fly to control assembly and be arranged at above described carrier, and because the weight of self applies one along the pressure of gravity direction to described carrier described in.
Further, described carrier is fuselage, described in fly control assembly be connected to described fuselage.
Of the present utility model flying is used to control assembly, the described control plate that flies is connected with described shock-damping structure, described fly to control assembly and be connected to carrier by described shock-damping structure, described shock-damping structure can buffer described in fly the control vibrations that are subject to of assembly entirety, and then buffer the vibrations that described sensor assembly is subject to.Assembling process flies to control the assembly precision between plate and described shock-damping structure, simple and convenient assembly described in considering.
Accompanying drawing explanation
Fig. 1 is the schematic perspective view flying to control assembly that this utility model one embodiment provides.
Fig. 2 is the decomposing schematic representation that flying in Fig. 1 controls assembly.
Fig. 3 is to have flying in Fig. 1 to control the partial exploded view of the unmanned vehicle of assembly.
Fig. 4 is the sectional view that flying in Fig. 1 controls the shock absorber part of assembly.
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 |
| Connecting plate | 311 |
| Installing hole | 3111 |
| Extension | 312 |
| Connecting hole | 313 |
| Shock absorber part | 32 |
| First connecting portion | 321 |
| First stopper section | 3211 |
| First supporting part | 3212 |
| First through hole | 3213 |
| Second connecting portion | 322 |
| Second stopper section | 3221 |
| Second supporting part | 3222 |
| Second through hole | 3223 |
| Damping portion | 323 |
| Host cavity | 3231 |
| Damping shock absorption material | 324 |
| Unmanned vehicle | 200 |
| Carrier | 201 |
| Mounting post | 202 |
Following detailed description of the invention will further illustrate this utility model in conjunction with above-mentioned accompanying drawing.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is clearly and completely described, it is clear that described embodiment is only a part of embodiment of this utility model rather than whole embodiments.Based on the embodiment in this utility model, the every other embodiment that those of ordinary skill in the art are obtained under not making creative work premise, broadly fall into the scope of this utility model protection.
It should be noted that be referred to as " being fixed on " another assembly when assembly, it can be directly on another assembly or can also there is assembly placed in the middle.When an assembly is considered as " connection " another assembly, and it can be directly to another assembly or may be simultaneously present assembly placed in the middle.When an assembly is considered as " being arranged at " another assembly, and it can be to be set directly on another assembly or may be simultaneously present assembly placed in the middle.
Unless otherwise defined, all of technology used herein and scientific terminology are identical with belonging to the implication that those skilled in the art of the present utility model are generally understood that.It is intended merely to describe the purpose of specific embodiment at term used in the description of the present utility model herein, it is not intended that in limiting this utility model.Term as used herein " and/or " include the arbitrary and all of combination of one or more relevant Listed Items.
Below in conjunction with the accompanying drawings, embodiments more of the present utility model are elaborated.In the case of not conflicting, the feature in following embodiment and embodiment can be mutually combined.
Seeing also Fig. 1 to Fig. 4, the one that this utility model one embodiment provides flies to control assembly 100, described in fly to control assembly 100 include 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 buffer the shaking from described carrier that described interface board 10 is subject to, described shock-damping structure 30 be described in fly control assembly 100 carry out integral shock-absorbing.Being appreciated that in other embodiments, described interface board 10 flies to 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.
Described interface board 10 flies to control plate 20 described in can carrying, it addition, described interface board 10 can also fly to control plate 20 electrically connect described with other elements, it is achieved described in fly the communication of control plate 20 and other elements.Described interface board 10 flies to control plate 20 and described shock-damping structure 30 described in connecting.Described interface board 10 includes 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 flies to control plate 20 described in being used for housing, described in fly to control plate 20 and be arranged on described cascaded surface 14.Described interface board 10 is further opened with several accepting hole (not shown), and described interface board 10 is connected together with described shock-damping structure 30 by described several accepting holes.Being appreciated that in other embodiments, described interface board 10 can also be connected with described shock-damping structure 30 by other means, 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 holes is four, and two in four described accepting holes are positioned at one end of described interface board 10, and two other in four described accepting holes is positioned at the other end of described interface board 10；Being appreciated that in other embodiments, the quantity of described accepting hole can increase according to actual needs or reduce.
Described flying controls plate 20 for controlling the flight of unmanned vehicle.The described control plate 20 that flies also includes circuit board 21 and is arranged on described circuit board 21 for realizing the functional module 22 of predetermined function, and described functional module 22 can include controller module, processor module, sensor assembly etc..Further, described sensor assembly can include inertia measuring module, temperature sensor module, Height sensor module, distance sensor module etc..Described inertia measuring module includes that acceleration transducer and gyroscope, 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 service life, described inertia measuring module to avoid the impact of unexpected vibrations.In present embodiment, described circuit board 21 and described interface board 10 are provided commonly for doing counterweight for described functional module 22, with reduce described functional module 22 to the soft durometer of its vibration-absorptive material, damp isoparametric requirement, and preferable damping effect can be reached.Described shock-damping structure 30 is connected with described interface board 10, in an assembling process without considering the assembly precision between described shock-damping structure 30 and described functional module 22, simple and convenient assembly.Being appreciated that in other embodiments, described functional module 22 can use other objects to do counterweight, such as metallic plate 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；Described flying controls plate 20 between two described shock-damping structures 30.Described shock-damping structure 30 includes 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.Being appreciated that in other embodiments, described support 31 can omit, and described shock absorber part 32 can be directly connected to described carrier.
Described support 31 includes connecting plate 311, and the two ends of described connecting plate 311 have each extended over extension 312 towards described interface board 10, and described shock-damping structure 30 is connected to described carrier by described connecting plate 311.Described support 31 is connected to described shock absorber part 32 by described extension 312.Described connecting plate 311 offers several installing hole 3111, and described connecting plate 311 is connected to described carrier by described several installing holes 3111.In present embodiment, the quantity of described several installing holes 3111 is two, and two described installing hole 3111 intervals are arranged；Being appreciated that in other embodiments, the quantity of described several installing holes 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.
Described shock absorber part 32 flies to control the shaking from described carrier that assembly 100 is subject to described in buffering.Described shock absorber part 32 includes the first connecting portion 321 second connecting portion 322 opposing with described first connecting portion 321 and is connected described first connecting portion 321 and the damping portion 323 of described second connecting portion 322.Described first connecting portion 321 includes the first stopper section 3211 and is connected to the first supporting part 3212 of described first stopper section 3211, described first supporting part 3212 is housed in described connecting hole 313, makes the first connecting portion 321 of described shock absorber part 32 be connected with described support 31.
In present embodiment, described first supporting part 3212 extends away from the direction of described first stopper section 3211 towards a table of described interface board 10 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 supporting part 3212.The size of described first stopper section 3211, more than the size of described connecting hole 313, to prevent described first supporting part 3212 from departing from from described connecting hole 313, and then prevents described first connecting portion 321 to be disconnected with described connecting plate 311.
Described second connecting portion 322 is connected to described interface board 10.Described second connecting portion 322 includes the second stopper section 3221 and is connected to the second supporting part 3222 of described second stopper section 3221, and described second supporting part 3222 is housed in a described accepting hole, makes described second connecting portion 322 be connected with described interface board 10.Described second stopper section 3221 is connected to the end of described second supporting part 3222, and the size of described second stopper section 3221 is more than the size of described accepting hole, to prevent described second connecting portion 322 to be disconnected with described interface board 10.
It is 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, the spheroid that described damping portion 323 is made up of rubber, according to concrete shock attenuation needs, intended damping effect can be reached easily and efficiently by the regulation wall thickness of described damping portion 323, shape, size etc., and the damping debugging time is shorter；Being appreciated that in other embodiments, described damping portion 323 can be made up of other elastomeric materials, such as silica gel etc..
Being 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, such 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 being 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 less than or equal to the diameter of described first through hole 3213, departs from described damping portion 323 from described second through hole 3223 under gravity to prevent from being filled in the damping shock absorption material 324 in described damping portion 323.
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 described in can be opened in the first connecting portion 321 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 substantially overlap.
Described damping portion 323 offers the host cavity 3231 being connected with described first through hole 3213 and described second through hole 3223, and described host cavity 3231 is used for housing described damping shock absorption material 324.It is housed in the damping shock absorption material in described host cavity 3231 and 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 includes 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 also can a face in curved surface, another face is plane；Or two faces are the most in curved surface.Described curved surface can be the structure such as cambered surface, wavy surfaces.It is appreciated that the sidewall of described damping portion 323 is alternatively 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, it will be understood that in other embodiments, and described damping shock absorption material can be Cotton Gossypii, foam plastics, compound PE Foam, sponge, Cotton Gossypii etc..Described damping portion 323 and described damping shock absorption material 324 cooperatively form combined type damping by rubber and foam, make described shock absorber part 32 be adapted to the shock attenuation needs under 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；Being appreciated that in other embodiments, described shock absorber part 32 can use other damper elements to substitute, such as spring etc..
In present embodiment, described shock absorber part 32 by the way of being compressed be described in fly control assembly 100 carry out integral shock-absorbing；Being appreciated that in other embodiments, described shock absorber part 32 can carry out damping by the way of being stretched.
The unmanned vehicle 200 that this utility model one embodiment provides, described unmanned vehicle 200 include carrier 201 and be connected to described carrier 201 fly control assembly 100, described in fly to control assembly 100 and 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；Being appreciated that in other embodiments, described carrier 201 can be other parts, the bracing frame etc. in fuselage as described in be arranged at.
Being additionally provided with several mounting post 202 on described carrier 201, described carrier 201 is connected with two described shock-damping structures 30 by described several mounting posts 202.In present embodiment, the quantity of described several mounting posts 202 is four, and four described mounting post 202 installing holes 3111 described with four of two described shock-damping structures 30 respectively match, and make described carrier 201 be connected with two described shock-damping structures 30.Being appreciated that in other embodiments, the quantity of described several mounting posts 202 can increase according to actual needs or reduce.
Described fly to control assembly 100 and be arranged at above described carrier 201, and because of the weight of self, described carrier 201 is applied one along the pressure of gravity direction.Specifically, fly to control assembly 100 fly to control plate 20 or fly to 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, between control plate 20 and interface board 10, to play 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 connect, snap connection.
Of the present utility model flying is used to control assembly, the described control plate that flies is connected with described shock-damping structure, described fly to control assembly and be connected to carrier by described shock-damping structure, described shock-damping structure can buffer described in fly the control vibrations that are subject to of assembly entirety, and then buffer the vibrations that described sensor assembly is subject to.Assembling process flies to control the assembly precision between plate and described shock-damping structure, simple and convenient assembly described in considering.
Additionally; those skilled in the art will be appreciated that; above embodiment is intended merely to this utility model is described; and it is not used as to restriction of the present utility model; as long as within spirit of the present utility model, made above example suitably change and change all falls within the scope of this utility model is claimed.
Claims (25)
1. one kind flies to control assembly, it include interface board and be connected to described interface board fly control plate, described flying is provided with at least one sensor assembly on control plate, it is characterized in that: described in fly to control assembly and also include being connected to the shock-damping structure of described interface board, the described control assembly that flies is connected to carrier by described shock-damping structure, described shock-damping structure flies to control the shaking from described carrier that assembly entirety is subject to described in can buffering, and then buffers the vibrations that described sensor assembly is subject to.
Fly the most as claimed in claim 1 to control assembly, it is characterised in that: described interface board offer the groove that groove is connected with described groove, described groove and described groove be used for housing described in fly control plate.
Fly the most as claimed in claim 1 to control assembly, it is characterised in that: described shock-damping structure include connecting described carrier and described in fly to control the shock absorber part of plate, described shock absorber part be described in fly to control assembly and carry out integral shock-absorbing.
Fly the most as claimed in claim 3 to control assembly, it is characterised in that: described shock absorber part is rubber damper；Or, described shock absorber part is spring.
Fly the most as claimed in claim 3 to control assembly, it is characterised in that: described shock absorber part by by by the way of compressing or the mode that is stretched be described in fly to control assembly and carry out integral shock-absorbing.
Fly the most as claimed in claim 3 to control assembly, it is characterised in that: described shock-damping structure also includes 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.
Fly the most as claimed in claim 6 to control assembly, it is characterised in that: described support includes that connecting plate, described support are connected to described carrier by described connecting plate.
Fly the most as claimed in claim 7 to control assembly, it is characterised in that: described shock absorber part includes that the first connecting portion, described first connecting portion are connected to described connecting plate.
The most as claimed in claim 8 fly control assembly, it is characterised in that: described support also include from the two ends of described connecting plate be respectively facing described in fly control plate extend extension, described extension offers connecting hole；Described first connecting portion includes the first stopper section and is connected to the first supporting part of described first stopper section, and described first supporting part is housed in described connecting hole, and described first stopper section breasting is on the bracket.
Fly the most as claimed in claim 9 to control assembly, it is characterised in that: the size of described first stopper section is more than the size of described connecting hole.
11. as claimed in claim 8 fly control assembly, it is characterised in that: described shock absorber part also includes second connecting portion opposing with described first connecting portion, described second connecting portion be connected to described in fly control plate.
12. fly to control assembly as claimed in claim 11, it is characterised in that: described shock absorber part also includes that damping portion, described damping portion offer host cavity, and described host cavity is used for housing damping shock absorption material.
13. fly to control assembly as claimed in claim 12, it is characterised in that: described damping shock absorption part material is foam.
14. fly to control assembly as claimed in claim 12, it is characterised in that: the sidewall of described damping portion includes curved-surface structure.
15. fly to control assembly as claimed in claim 12, it is characterized in that: described shock absorber part offers the first through hole and the second through hole being connected with described host cavity, the described damping shock absorption material being filled in described host cavity can be changed by described first through hole and/or described second through hole.
16. fly to control assembly as claimed in claim 15, it is characterised in that: the central shaft of described first through hole substantially overlaps with the central shaft of described second through hole.
17. fly to control assembly as claimed in claim 15, it is characterised 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.
18. fly to control assembly as claimed in claim 17, it is characterised in that: described interface board offers accepting hole；Described second connecting portion includes the second stopper section and connects second supporting part of Ei and described second stopper section, and described second supporting part is housed in described accepting hole, makes described second connecting portion be connected to described interface board.
19. fly to control assembly as claimed in claim 18, it is characterised in that: the size of described second stopper section is more than the size of described accepting hole.
20. fly to control assembly as claimed in claim 1, it is characterised in that flying to control plate described in: and also include being connected to circuit board and the functional module of described interface board, described functional module is arranged on described circuit board.
21. as claimed in claim 20 fly control assembly, it is characterised in that: the quantity of described shock-damping structure is two, and two described shock-damping structures connect the two ends of described interface board respectively, described in fly control plate between two described shock-damping structures.
22. fly to control assembly as claimed in claim 20, it is characterised in that: described functional module includes that described sensor assembly, described sensor assembly include inertia measuring module.
23. 1 kinds of unmanned vehicles, it include fuselage and as described in any one of claim 1-22 flying control assembly, described in fly control assembly be connected to described carrier.
24. unmanned vehicles as claimed in claim 23, it is characterised in that fly to control assembly described in: and be arranged at above described carrier, and because the weight of self applies one along the pressure of gravity direction to described carrier.
25. unmanned vehicles as claimed in claim 24, it is characterised in that: described carrier is fuselage, described in fly control assembly be connected to described fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620091449.8U CN205491484U (en) | 2016-01-29 | 2016-01-29 | Fly to control subassembly and unmanned vehicles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620091449.8U CN205491484U (en) | 2016-01-29 | 2016-01-29 | Fly to control subassembly and unmanned vehicles |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205491484U true CN205491484U (en) | 2016-08-17 |
Family
ID=56671666
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620091449.8U Expired - Fee Related CN205491484U (en) | 2016-01-29 | 2016-01-29 | Fly to control subassembly and unmanned vehicles |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205491484U (en) |
-
2016
- 2016-01-29 CN CN201620091449.8U patent/CN205491484U/en not_active Expired - Fee Related
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