CN206797690U - The Multi-axis aircraft that can freely assemble - Google Patents
The Multi-axis aircraft that can freely assemble Download PDFInfo
- Publication number
- CN206797690U CN206797690U CN201720312226.4U CN201720312226U CN206797690U CN 206797690 U CN206797690 U CN 206797690U CN 201720312226 U CN201720312226 U CN 201720312226U CN 206797690 U CN206797690 U CN 206797690U
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- CN
- China
- Prior art keywords
- connector
- horn
- cylinder
- battery module
- ring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
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Abstract
The utility model discloses a kind of Multi-axis aircraft that can freely assemble, it includes：Fly control module, battery module, some rotor assemblies, some linking arms, some connectors and the first protection ring.Each rotor assemblies include：Horn, motor, motor cabinet.The porous strip structure part that horn, linking arm form side by side by the cylinder of some hollow settings, the first protection ring is by some cylinders porous ring structural member arranged in a ring formed.Connector detachably coordinates with cylinder, and its end may pass through cylinder and snap onto on cylinder.Positioned at flying to control between module and battery module, it is detachably connected horn by connector and winged control module.Linking arm is located at the bottom of battery module, and it is detachably connected by connector and battery module.First protection ring ring is located at battery module surrounding, and linking arm is detachably connected with horn by connector and the first protection ring.
Description
Technical field
The technical field of aircraft is the utility model is related to, more particularly to a kind of Multi-axis aircraft that can freely assemble.
Background technology
More rotors are to realize the aircraft of acceleration, retarded motion by controlling different motor speeds.In the market it is more
Axle rotor craft, usually fixed or foldable type Multi-axis aircraft, fuselage Each part is complex and connects
Closely, can not substantially dismantle or not easy to remove, overall airframe structure is substantially stationary.It is existing that there is also some parts to enter
The assembled aircraft of row, but complexity is dismounted, part is not easy to be changed, and can only realize the replacement of original part, it is impossible to
Free expansion is carried out to the airframe structure of aircraft, it is impossible to add other structures part to improve the operability of aircraft and work(
Energy property, it is impossible to provide the user with more preferable DIY spaces.
Utility model content
The problem of existing for prior art, it is of the present utility model mainly to propose a kind of multiaxis flight that freely assemble
Device, each module or component of the Multi-axis aircraft are attached by identical attachment structure, and assembling is simple, and can be free
It is assembled into 4 axles, 6 axles or 8 axle Multi-axis aircrafts.
To achieve the above object, the utility model proposes the Multi-axis aircraft that can freely assemble, it includes：Fly control mould
Block, battery module, some rotor assemblies, some linking arms, some connectors and the first protection ring.Each rotor assemblies bag
Include：Horn, motor, motor cabinet and by motor-driven propeller, motor is arranged on motor cabinet.It is equal to fly control module, motor
Electrically connected with battery module.
The porous strip structure part that horn, linking arm form side by side by the cylinder of some hollow settings, the first protection ring
By some cylinders porous ring structural member arranged in a ring formed.The both ends of connector are symmetrical set, and it is removable with cylinder
Cooperation is unloaded, and its end may pass through cylinder and snap onto on cylinder.
Fly control module and be provided with some the first mounting holes detachably coordinated with connector, and the first mounting hole and horn one
One correspondence.The first end of horn is between winged control module and battery module, and its first end passes through connector with flying control module
It is detachably connected.
Battery module is provided with some the second mounting holes detachably coordinated with connector, and the second mounting hole and linking arm
Correspond.Linking arm is located at the bottom of battery module, and its first end is detachably connected by connector and battery module.
First protection ring ring is located at battery module surrounding, and linking arm is removable by connector and the first protection ring with horn
Unload connection.
Preferably, horn, linking arm are equipped with first reinforcement and second reinforcement perpendicular with its respective cylinder,
And first reinforcement be mutually perpendicular to the second reinforcement, to form cross-rib reinforcement structure.
Preferably, the end of connector is provided with annular back-off, and intermediate position is provided with along the circumferentially disposed annular of its side wall
It is raised；The aperture of the first side of the through hole three of first mounting hole, the second mounting hole and cylinder is equipped with to match with annular back-off
The first annular groove closed, the aperture of the second side of its three, which is equipped with, is engaged the second annular groove with annular protrusion.
Preferably, connector is in the cylindric of hollow setting, and its both ends is respectively to the recessed U-type groove of its annular protrusion or V-type
Groove.
Preferably, the side wall of connector is provided with two the 3rd reinforcements.
Preferably, motor cabinet has first adjutage perpendicular with its side wall, and first adjutage is by some cylinder groups
Into it is detachably connected by the second end of connector and horn.
Preferably, motor cabinet is additionally provided with the second adjutage being oppositely arranged with the first adjutage, and if the second adjutage by
Dry cylinder composition.
Preferably, the Multi-axis aircraft also includes being looped around the second protection ring on the outside of each motor cabinet, and it is by some circles
Cylinder composition arranged in a ring, and be detachably connected by the second adjutage of connector and each motor cabinet.
The beneficial effects of the utility model are：1st, battery module, it is logical to fly control module, rotor assemblies and structural member
Cross identical connector and carry out snapping, it is very flexible to spell assembly and disassembly.2nd, the quantity of horn can change, and it can freely be assembled
It is workable into Multi-axis aircrafts such as 4 axles, 6 axles or 8 axles.3rd, horn, linking arm and the structural members such as the first protection ring use
Cylinder adds cross-rib reinforcement structure, can both ensure aircraft bulk strength, can mitigate the overall weight of aircraft again.Meanwhile circle
The through hole of cylinder is in upper and lower direction, during aircraft vertical lifts, can also reduce flight resistance, make lifting more smooth.
Brief description of the drawings
, below will be to embodiment in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
Or the required accompanying drawing used is briefly described in description of the prior art, it should be apparent that, drawings in the following description are only
It is some embodiments of the utility model, for those of ordinary skill in the art, is not paying the premise of creative work
Under, other accompanying drawings can also be obtained according to the structure shown in these accompanying drawings.
Fig. 1 is the structural representation of the utility model first embodiment；
Fig. 2 is Fig. 1 explosive view；
Fig. 3 is the structural representation of rotor assemblies in first embodiment；
Fig. 4 is the structural representation of the connector in first embodiment；
Fig. 5 is the structural representation of second embodiment of the present utility model；
Fig. 6 is the structural representation of rotor assemblies in second embodiment.
Realization, functional characteristics and the advantage of the utility model purpose will be described further referring to the drawings in conjunction with the embodiments.
Embodiment
The utility model proposes a kind of Multi-axis aircraft that can freely assemble.
Reference picture 1-2, Fig. 1 are the structural representation of the utility model first embodiment, and Fig. 2 is Fig. 1 explosive view.
As shown in Figure 1-2, in the utility model first embodiment, the Multi-axis aircraft that can freely assemble includes：Fly
Control module 1, battery module 2, four rotor assemblies 3, four linking arms 4, some protection rings 5 of connector 6 and first.Each rotation
Wing component 3 includes：Horn 31, motor, motor cabinet 32 and by motor-driven propeller, motor is arranged on motor cabinet 32,
Fly control module 1, motor electrically connects with battery module 2.
Four horns 31 annularly arrange, and the first end of each horn 31 be respectively positioned on fly control module 1 and battery module 2 it
Between.Fly control module 1 provided with the first mounting hole 11 is corresponded with four horns 31, the first end of each horn 31 passes through company respectively
Fitting 6 is snapped onto on its each self-corresponding first mounting hole 11.First protection ring 5 is looped around the surrounding of battery module 2, with protection
Battery module.The arm body of each horn 31 is also snapped onto on the first protection ring 5 by connector 6 respectively.Four horns 31 and first
Protection ring 5 constitutes the profile stent of aircraft.
Four linking arms 4 annularly arrange, and the first end of each linking arm 4 is respectively positioned on the bottom of battery module 2.Battery mould
The side wall of the surrounding of block 2 is provided with to be distinguished with four linking arms, 4 one-to-one second mounting hole 21, the first end of each linking arm 4
Snapped onto by connector 6 on its each self-corresponding second mounting hole 21.Each arm body of linking arm 4 also passes through connector 6 respectively
It is connected with the first protection ring 5 so that battery module 2 is fixed on the profile stent of aircraft.In the present embodiment, Mei Yilian
The second end for connecing arm 4 is additionally provided with feet 41, avoids aircraft landing from making directly to contact with ground.
As Figure 2-3, in the present embodiment, horn 31, linking arm 4 are arranged side by side by the cylinder 311 of some hollow settings
The porous strip structure part of composition, the porous ring structural member that the first protection ring 5 is made up of some annular arrays of cylinder 311.For
Strengthen horn 31, the structural strength of the protection ring 5 of linking arm 4 and first, it is preferable that horn 31, linking arm 4 are equipped with each with it
From perpendicular the first reinforcement 312 and the second reinforcement 313 of cylinder 311, and the first reinforcement 312 and the second reinforcement
313 are mutually perpendicular to, and constitute cross-rib reinforcement structure.
As shown in figure 4, the both ends of connector 6 are symmetrical set, itself and the first mounting hole 11, the second mounting hole 21 and circle
Cylinder 311 is detachable cooperation, and its end may pass through and snap onto on the first mounting hole 11 or the second mounting hole or cylinder 311.
Specifically, the end of connector 6 is provided with annular back-off 61, and intermediate position is provided with along the circumferentially disposed annular protrusion of its side wall
62.First mounting hole 11, the second mounting hole 21 and the aperture of the first side of the through hole three of cylinder 311 are equipped with and annular back-off
The 61 first annular grooves 3111 being engaged, the aperture of the second side of its three is equipped with is engaged the second ring with annular protrusion 62
Connected in star.When the through hole of cylinder 311 is inserted in the end of connector 6, its annular back-off 61 is pressed on first annular groove 3111, its
Annular protrusion 62 is pressed on the second annular groove, so that connector 6 is snapped onto on the through hole of cylinder 311.Similarly, when even
When fitting 6 is inserted in the first mounting hole 11 or the second mounting hole 21, the end of connector 6 passes through its annular back-off 61 and annular
Projection 62 can be snapped onto in the first mounting hole 11 or the second mounting hole 21.
As shown in figure 4, in the present embodiment, the connector 6 is the hollow cylinder of hollow setting, can mitigate connector 6
Weight.Quick in order to facilitate connector 6 disconnects, it is preferable that the both ends of the connector 6 are recessed to its annular protrusion 62 respectively
U-type groove 63 or V-groove.In the present embodiment, the connector 6 is provided that U-type groove 63.When user is needed the slave of connector 6
When being disassembled on arm 31, the protection ring 5 of linking arm 4 or first, the both sides of U-type groove 63 need to be only pinched, by the annular of connector 6
Back-off 61 is pinched into U-type groove 63 so that the annular back-off 61 of connector 6 departs from first annular groove 3111, thus can be fast
Speed extracts connector 6 out out of horn 31 (or linking arm 4, first protection ring 5) cylinder 311.
In order to ensure bonding strength, the side wall of the connector 6 is provided with two the 3rd reinforcements 64.Because propeller is in flight course
In horn 31 can be driven to shake, this can cause connector 6 to be rocked in the cylinder 311 of horn 31.By setting the 3rd reinforcement
64, the structural strength for improving connector 6 can be mentioned, and connector 6 is coordinated closely with cylinder 311, it is not easy to loosen, so as to
Ensure the overall bonding strength of aircraft.
In the present embodiment, motor cabinet 32 has first adjutage 321 perpendicular with its side wall, first adjutage
321 are made up of some cylinders 311, and the second end of horn 31 is snapped onto by connector 6.It is so easy to disassemble, repair or replace
Change impaired motor or motor cabinet 32.
The technical solution of the utility model is to form aircraft by porous strip structure part and porous annular structural member
Profile stent, and flying control module 1, pore structure be set on battery module 2 so that can pass through identical connector 6 will
Fly control module 1, battery module 2 is connected on the profile stent of aircraft.Compared with prior art, the beneficial effects of the utility model
It is：1st, battery module 2, fly control module 1, rotor assemblies 3 and structural member and snapping is carried out by identical connector 6, spell
Assembly and disassembly are very flexible.2nd, the quantity of horn 31 can change, and it can freely be assembled into the multiaxises such as 4 axles, 6 axles or 8 axles and fly
Row device, it is workable.3rd, horn 31, linking arm 4 and the structural members such as the first protection ring 5 are added using cylinder 311 plus cross-rib
It strong structure, can both ensure aircraft bulk strength, the overall weight of aircraft can be mitigated again.Meanwhile the through hole of cylinder 311 is presented
Lower direction, during aircraft vertical lifts, flight resistance can be also reduced, makes lifting more smooth.
Reference picture 5, Fig. 5 are the structural representation of second embodiment of the present utility model.
As shown in figure 5, in the utility model second embodiment, the Multi-axis aircraft that can freely assemble includes eight rotations
Wing component 3, eight rotor assemblies 3 annularly arrange, and are snapped onto by connector 6 on the first protection ring 5, to form eight
The profile stent of axle aircraft.
As shown in fig. 6, in the present embodiment, the motor cabinet 32 of the rotor assemblies 3 is also including relative with the first adjutage 321
The second adjutage 322 set, and second adjutage 322 is equally made up of some cylinders 311.User can be in motor cabinet 32
Propeller fender bracket is set on the second adjutage 322, to avoid propeller from being hit in flight course with other objects.
As shown in figure 5, in a second embodiment, the Multi-axis aircraft also includes being looped around the of each outside of motor cabinet 32
Two protection rings 7.Second protection ring 7 is made up of some annular arrays of cylinder 311, and it passes through eight connectors 6 and each motor cabinet
32 the second adjutage 322 connects.Because the structure for the outer that can cause aircraft fuselage after increase horn 31 becomes loose, lead to
Cross the structural strength for setting the second protection ring 7 to ensure aircraft outer.Meanwhile second protection ring 7 can also protection fly
The integral body structure of device, improve the security of aircraft.
Preferred embodiment of the present utility model is these are only, not thereby limits the scope of the claims of the present utility model, it is every
Under utility model of the present utility model design, the equivalent structure made using the utility model specification and accompanying drawing content is become
Change, or directly/be used in other related technical areas indirectly and be included in scope of patent protection of the present utility model.
Claims (8)
1. a kind of Multi-axis aircraft that can freely assemble, it includes：Fly control module, battery module, some rotor assemblies, Mei Yisuo
Stating rotor assemblies includes：Horn, motor, for installing the motor cabinet of the motor and by the motor-driven propeller；
The winged control module, motor electrically connect with the battery module；
Characterized in that, also include：Some linking arms located at the bottom of the battery module, some both ends are symmetrical set
Connector, and ring is located at the first protection ring of the battery module surrounding；
The porous strip structure part that the horn, linking arm form side by side by the cylinder of some hollow settings, described first protects
Retaining ring is by some cylinders porous ring structural member arranged in a ring formed；The connector is detachably matched somebody with somebody with the cylinder
Close, its end may pass through the cylinder and snap onto on the cylinder；
The winged control module is provided with some the first mounting holes detachably coordinated with the connector, and first mounting hole
Corresponded with the horn；The first end of the horn is detachably connected by the connector and the winged control module；
The battery module is provided with some the second mounting holes detachably coordinated with the connector, and second mounting hole
Corresponded with the linking arm；The first end of the linking arm is detachably connected by the connector and the battery module
Connect；
The linking arm is detachably connected with the horn by the connector and first protection ring.
2. the Multi-axis aircraft that can freely assemble as claimed in claim 1, it is characterised in that the horn, linking arm are all provided with
There are first reinforcement and second reinforcement perpendicular with its respective cylinder, and first reinforcement is strengthened with described second
Muscle is mutually perpendicular to.
3. the Multi-axis aircraft that can freely assemble as claimed in claim 1, it is characterised in that the end of the connector is provided with
Annular back-off, intermediate position are provided with along the circumferentially disposed annular protrusion of its side wall；First mounting hole, the second mounting hole with
The aperture of the first side of the through hole three of the cylinder is equipped with the first annular groove being engaged with the annular back-off, thirdly
The aperture of the second side of person is equipped with is engaged the second annular groove with the annular protrusion.
4. the Multi-axis aircraft that can freely assemble as claimed in claim 3, it is characterised in that the connector is in hollow setting
It is cylindric, its both ends is respectively to the recessed U-type groove of its annular protrusion or V-groove.
5. the Multi-axis aircraft that can freely assemble as claimed in claim 4, it is characterised in that the side wall of the connector is provided with
Two the 3rd reinforcements.
6. the Multi-axis aircraft that can freely assemble as claimed in any one of claims 1 to 5, wherein, it is characterised in that the motor
Seat tool has first adjutage perpendicular with its side wall, and first adjutage is made up of some cylinders, and it passes through described
Second end of connector and the horn is detachably connected.
7. the Multi-axis aircraft that can freely assemble as claimed in claim 6, it is characterised in that the motor cabinet is additionally provided with and institute
The second adjutage that the first adjutage is oppositely arranged is stated, and second adjutage is made up of some cylinders.
8. the Multi-axis aircraft that can freely assemble as claimed in claim 7, it is characterised in that also each described including being looped around
The second protection ring on the outside of motor cabinet, it is formed by some cylinders are arranged in a ring, and by the connector with it is each
Second adjutage of the motor cabinet is detachably connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720312226.4U CN206797690U (en) | 2017-03-28 | 2017-03-28 | The Multi-axis aircraft that can freely assemble |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720312226.4U CN206797690U (en) | 2017-03-28 | 2017-03-28 | The Multi-axis aircraft that can freely assemble |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206797690U true CN206797690U (en) | 2017-12-26 |
Family
ID=60730881
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720312226.4U Withdrawn - After Issue CN206797690U (en) | 2017-03-28 | 2017-03-28 | The Multi-axis aircraft that can freely assemble |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206797690U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828863A (en) * | 2017-03-28 | 2017-06-13 | 深圳市创客火科技有限公司 | The Multi-axis aircraft that can freely assemble |
-
2017
- 2017-03-28 CN CN201720312226.4U patent/CN206797690U/en not_active Withdrawn - After Issue
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828863A (en) * | 2017-03-28 | 2017-06-13 | 深圳市创客火科技有限公司 | The Multi-axis aircraft that can freely assemble |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20171226 Effective date of abandoning: 20230602 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20171226 Effective date of abandoning: 20230602 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |