CN207208469U - Foldable propeller arrangement and four-axle aircraft - Google Patents
Foldable propeller arrangement and four-axle aircraft Download PDFInfo
- Publication number
- CN207208469U CN207208469U CN201721176526.0U CN201721176526U CN207208469U CN 207208469 U CN207208469 U CN 207208469U CN 201721176526 U CN201721176526 U CN 201721176526U CN 207208469 U CN207208469 U CN 207208469U
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- control box
- propeller
- connecting rod
- load bearing
- bearing seat
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Abstract
The utility model discloses foldable propeller arrangement and four-axle aircraft, four-axle aircraft includes control box and two pieces of putting parts, the both ends of putting part are provided with circular hollow-out parts, load bearing seat is installed in hollow-out parts, propeller component is installed on load bearing seat, each putting part forms the accommodation space to relative inner opening between two circular hollow-out parts, control box top two side can be provided with one end of four connecting rods rotation-limited, the other ends of four connecting rods accordingly can rotation-limited be arranged on accommodation space on the relative inner wall of aperture position.The utility model connects control box so as to form a four-axle aircraft entirety using the putting part of two separation by connecting rod, the accommodation space of accommodating control box is set on putting part, when putting part folds, control box is accommodated in accommodation space, so as to have compressed space after folding to greatest extent, it is allowed to become to be readily able to the object carried and shape is regular, during use, easily spread out, direct use.
Description
Technical field
It the utility model is related to vehicle technology field, and in particular to a kind of foldable propeller arrangement and four axles flight
Device.
Background technology
Four-axle aircraft in the market uses stationary structure, and the space-consuming of aircraft expansion is larger, is not easy
In carrying.Because existing technical staff is fixed in propeller blade design for the Design Thinking of propeller, it is more
Want to lift flight performance and stability, therefore, the propeller arrangement designed is fixed forgiving structure, whole so as to cause
The space-consuming of individual aircraft also increases therewith.
Utility model content
The utility model provides a kind of foldable propeller arrangement and four-axle aircraft, to solve the above problems.
A kind of foldable propeller arrangement provided by the utility model, including base portion, base portion centre, which is provided with, to be used to hold
The circular hollow-out parts of propeller rotation are put, in addition to two blade propeller component and are held for what two blade propeller component was installed on it
Seat is carried, the load bearing seat both ends are installed in rotation on circular hollow-out parts madial wall, and load bearing seat can be accommodated in circular hollow-out parts
Propeller shaft axis are perpendicular to circular hollow out facial planes when 90 ° of inner side and drops down.
Preferably, load bearing seat is semicircular arc connecting rod, and two blade propeller component includes two blade propeller and motor,
Centre position is provided with motor mounting seat on the inside of semicircular arc connecting rod, when motor is fixed on motor mounting seat,
The center of circle direction of semicircular arc connecting rod is pointed in motor rotating shaft.
Four-axle aircraft provided by the utility model, including control box and two pieces of putting parts, the both ends of each putting part are set
There are the circular hollow-out parts for housing propeller rotation, the carrying being installed on it for propeller component is installed in hollow-out parts
, propeller component is installed, propeller component includes propeller and motor, and each putting part is circular positioned at two on load bearing seat
The accommodation space for being used to house control box to relative inner opening is formed between hollow-out parts, control box top two side can be spacing
Be rotatably mounted one end of four connecting rods, the other ends of four connecting rods accordingly can rotation-limited opened installed in accommodation space
On the relative inner wall of mouth position.
Preferably, the load bearing seat both ends are installed in rotation on circular hollow-out parts madial wall, and load bearing seat can be accommodated in
Propeller shaft axis are perpendicular to circular hollow out facial planes, propeller component bag on the inside of circular hollow-out parts and during 90 ° of drops down
Include two blade propeller and motor.
Preferably, load bearing seat is semicircular arc connecting rod, and semicircular arc connecting rod inner side centre position is provided with motor
Mounting seat, when motor is fixed on motor mounting seat, the center of circle side of semicircular arc connecting rod is pointed in motor rotating shaft
To.
Preferably, one end of four connecting rods is articulated in control box respectively, the pivoted nose of the connecting rod in control box
Provided with the first spacing preiection, the position in control box between two first spacing preiections of the same side be provided with it is two first spacing
First limited impression of projection matching, when the first spacing preiection is placed in the first limited impression, control box is deployed into operating position.
Preferably, the position in control box between two first spacing preiections of the same side sets a raised line, raised line
First limited impression is formed on two side.
Preferably, the other end of four connecting rods is articulated on accommodation space madial wall respectively, the company at accommodation space
The pivoted nose of bar is provided with the second spacing preiection, and second matched with the second spacing preiection is correspondingly provided with accommodation space madial wall
Limited impression, when the second spacing preiection is placed in the second limited impression, two putting parts are deployed into conplane operating position.
Preferably, it is provided with control module in control box, control module includes control unit and power supply, in control unit
A controlling switch is connected, controlling switch is arranged on control box housing.
Preferably, control module also includes the camera for being connected to control unit, and camera is arranged on control box housing.
Preferably, connecting rod is using connecting rod hollow or with inner groovy.
Above-mentioned technical proposal can be seen that to be controlled because the utility model is connected using the putting part of two separation by connecting rod
Box processed sets the accommodation space of accommodating control box, when putting part folds so as to form a four-axle aircraft entirety on putting part
When, control box is accommodated in accommodation space, so as to have compressed space after folding to greatest extent, is allowed to become to be readily able to carry
And the object that shape is regular, in use, easily spreading out, direct use.
The load bearing seat of semicircular arc is then employed for foldable propeller arrangement, the circle that can be accommodated in base portion is engraved
90 ° are downwardly turned in empty portion, during use and realizes that propeller component deploys and can enter work, after further have compressed folding
Space, and do not interfere with the profile of whole propeller arrangement.
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 these accompanying drawings.
Fig. 1 is structural representation when aircraft expansion is in running order in the present embodiment；
Fig. 2 is A portions mplifying structure schematic diagram in Fig. 1；
Fig. 3 is B portions structure enlargement diagram in Fig. 1；
Fig. 4 is the structural representation at another visual angle of aircraft in the present embodiment；
Fig. 5 is the structural representation at visual angle below aircraft in the present embodiment；
Fig. 6 is the structural representation of aircraft folding storage state in the present embodiment.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the embodiment of the utility model is carried out
Clearly and completely describing, it is clear that described embodiment is only the utility model part of the embodiment, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The all other embodiment obtained, belong to the scope of the utility model protection.
Embodiment：
The utility model embodiment provides a kind of four-axle aircraft, with reference to shown in Fig. 1 to Fig. 6, including control box 1 and two pieces
Putting part 2, the both ends of each putting part 2 are provided with the circular hollow-out parts 21 for being used for housing the rotation of propeller 3, installed in hollow-out parts 21
There is the load bearing seat 22 being installed on it for propeller component, propeller component is installed on load bearing seat 22, propeller component includes spiral shell
Oar 3 and motor 31 are revolved, each putting part 2 is formed between two circular hollow-out parts 21 to be used to hold to relative inner opening
The accommodation space 23 of control box is put, the top two side of control box 1 can be provided with one end 111 of four connecting rods 11 rotation-limited,
The other end 112 of four connecting rods 11 accordingly can rotation-limited be arranged on accommodation space 23 aperture position relative inner wall
On.Because one end of connecting rod is rotatably connected on the outside of control box, the other end of connecting rod is then rotatably connected in accommodation space
Inner side, therefore can realize that two putting parts and the storage folded against of a control box are integrated, after being greatly reduced folding
Space, consequently facilitating transhipment, also allow for user carrying.
In a further embodiment, load bearing seat can be integrally fixed at the mounting bracket of the madial wall of hollow-out parts 21, and the mounting bracket can
Using be yi word pattern or cross or other using machine shaft as circular diverging ray shape supports dissipated to hollow-out parts madial wall, from
And propeller component is installed on it, still, because the motor in propeller component has certain height, hollow-out parts need
The installation requirement of propeller component can be met with certain thickness, therefore, the load bearing seat in this embodiment can not incite somebody to action
The most thinning of whole product collapsible.Therefore, in the present embodiment in order to further by the integral thickness of aircraft product
Most thinning is realized, is made that further following improvement, i.e., the described both ends of load bearing seat 22 can engrave installed in circle rotation-limited
On the empty madial wall of portion 21, propeller shaft axis hang down when load bearing seat can be accommodated in 90 ° of the inner side of circular hollow-out parts 21 and drops down
Directly include two blade propeller and motor in circular hollow out facial planes, i.e., the position shown in Fig. 1, propeller component.Can be with
Understand, " can install " refers to that a part is installed in rotation on another part rotation-limited, and sets spacing
Structure, make a part be not relative to another part be unconfined rotation, but meeting when turning to some position
It is limited on the position, such as increase locating part or position limiting structure, to those skilled in the art, it can pacify rotation-limited
Dress is the technical scheme that can be realized by prior art, and here is omitted.Installed in the present embodiment in hollow-out parts madial wall
The lower position in hole sets limited impression/spacing preiection, and spacing preiection/spacing is set in the outside relevant position at load bearing seat both ends
Groove i.e. can be achieved can rotation-limited, certainly position limiting structure in other embodiments be not limited to lift this.Obviously, originally
Propeller arrangement in embodiment is foldable propeller arrangement, and it includes base portion (i.e. one end part of putting part, if will
Putting part in the present embodiment is changed to a hollow-out parts, then is single axle helical paddle structure), base portion centre, which is provided with, to be used to house spiral shell
Revolve the circular hollow-out parts of oar rotation, in addition to two blade propeller component and the carrying that is installed on it for two blade propeller component
Seat, the load bearing seat both ends can be arranged on circular hollow-out parts madial wall rotation-limited, and load bearing seat can be accommodated in circular hollow out
Propeller shaft axis are perpendicular to circular hollow out facial planes on the inside of portion and during 90 ° of drops down.Load bearing seat connects for semicircular arc
Bar, two blade propeller component include two blade propeller and motor, and centre position is provided with driving on the inside of semicircular arc connecting rod
Motor mount, when motor is fixed on motor mounting seat, the circle of semicircular arc connecting rod is pointed in motor rotating shaft
Heart direction.If designing single shaft aircraft, the foldable propeller arrangement in the present embodiment can be also applicable, it is achieved thereby that
The single shaft aircraft of most thinning, or twin shaft aircraft can also use the foldable propeller arrangement.
Similarly for for can the installing of connecting rod rotation-limited, and in this way, in the present embodiment four connecting rods 11 one
End 111 is articulated in control box 1 respectively, and the pivoted nose of the connecting rod in control box 1 is provided with the first spacing preiection 113, control
Position between two first limit convexes 113 on box 1 processed positioned at the same side rise is provided with the matched with two first spacing preiections 113
One limited impression, when the first spacing preiection is placed in the first limited impression, control box is deployed into operating position, i.e., shown in Fig. 1
Position.
Position in the present embodiment in control box 1 between two first spacing preiections 113 of the same side sets a raised line
114, first limited impression is formed on the two side of raised line 114.One raised line realizes two stopper slots, maximized to utilize
The confined space, save consumptive material use.
The other end 112 of four connecting rods 11 is articulated on the madial wall of accommodation space 23 respectively, at accommodation space 23
The pivoted nose of connecting rod is provided with the second spacing preiection 115, is correspondingly provided with and the second spacing preiection 115 on the madial wall of accommodation space 23
Second limited impression of matching, when the second spacing preiection 115 is placed in the second limited impression, two putting parts 2 are deployed into same flat
The operating position in face, i.e., the position shown in Fig. 1.
When being rotated in the present embodiment with load bearing seat 22 to 2 same plane of putting part, load bearing seat is in 0 ° of position, that is, stores
Folding position, now propeller rotating shaft is also parallel with putting part plane, and propeller uses two blade propeller, also can be by this pair
Vane propeller is rotated to the position parallel to putting part plane, so as to fully achieve the effect of multi-part folding storage, is reached
The design of whole product most thinning.
In order to mitigate product weight, connecting rod uses hollow connecting rod in the present embodiment, and the hollow connecting rod is not only able to subtract
Light weight, and can also be used to the cabling of signal wire, makes that the wiring of product is cleaner and tidier, and wire rod is not exposed, in other implementations
Connecting rod can also use the connecting rod with inner groovy that side wall concaves in example, have same effect with hollow connecting rod.Can
With understanding, the wiring for whole circuit, it is by putting part, connecting rod interior cabling so as to ensureing that all wire rods are not outer
Dew.
Specifically, load bearing seat 22 is semicircular arc connecting rod in the present embodiment, can be matched with hollow-out parts, Ci Zhongjie
Structure can then ensure that the height of motor can be higher, as long as being no more than hollow-out parts radius, in semicircular arc connecting rod
Side centre position is provided with motor mounting seat 32, and when motor 31 is fixed on motor mounting seat 32, motor turns
Axle points to the center of circle direction of semicircular arc connecting rod.
Control module is provided with the present embodiment in control box 1, control module includes control unit and power supply, and control is single
A controlling switch 12 is connected in member, controlling switch 12 is arranged on the housing of control box 1.
Control module also includes the camera 13 for being connected to control unit, and camera 13 is arranged on the housing of control box 1.When
So, it is more multi-functional in order to realize, corresponding circuit function module can be increased as needed, such as control module can include leading to
Unit is interrogated, so that control box can communicate with mobile phone, so as to realize more controls, the control module in control box is this
The circuit structure that neck technical staff can be known by prior art, is also repeated no more herein.
In use, four-axle aircraft is expanded into state shown in Fig. 1, presses controlling switch and connect power supply, control mould
BOB(beginning of block) works, and can control camera photographed, when being not used and needing to carry, then state shown in folding shrinking to Fig. 6.
A kind of four-axle aircraft provided above the utility model embodiment is described in detail, used herein
Specific case is set forth to principle of the present utility model and embodiment, and the explanation of above example is only intended to help
Understand core concept of the present utility model；Meanwhile for those of ordinary skill in the art, according to thought of the present utility model and
Method, there will be changes in specific embodiments and applications, in summary, this specification content should not be construed as
To limitation of the present utility model.
Claims (11)
1. foldable propeller arrangement, it is characterised in that be provided with including base portion, among base portion and be used to house propeller rotation
Circular hollow-out parts, in addition to two blade propeller component and the load bearing seat that is installed on it for two blade propeller component are described to hold
Carrying seat both ends can be arranged on circular hollow-out parts madial wall rotation-limited, load bearing seat can be accommodated on the inside of circular hollow-out parts and to
It is lower expansion 90 ° when propeller shaft axis perpendicular to circular hollow out facial planes.
2. foldable propeller arrangement as claimed in claim 1, it is characterised in that load bearing seat is semicircular arc connecting rod, double
Vane propeller component includes two blade propeller and motor, and centre position is pacified provided with motor on the inside of semicircular arc connecting rod
Seat is filled, when motor is fixed on motor mounting seat, the center of circle direction of semicircular arc connecting rod is pointed in motor rotating shaft.
3. four-axle aircraft, it is characterised in that including control box and two pieces of putting parts, the both ends of each putting part, which are provided with, to be used to hold
The circular hollow-out parts of propeller rotation are put, the load bearing seat being installed on it for propeller component, load bearing seat are installed in hollow-out parts
Upper installation propeller component, propeller component include propeller and motor, each putting part be located at two circular hollow-out parts it
Between formed to relative inner opening be used for house the accommodation space of control box, control box top two side can pacify rotation-limited
One end equipped with four connecting rods, the other ends of four connecting rods accordingly can rotation-limited be arranged on accommodation space in aperture position
On relative inner wall.
4. four-axle aircraft as claimed in claim 3, it is characterised in that the load bearing seat both ends can be arranged on rotation-limited
On circular hollow-out parts madial wall, load bearing seat can be accommodated on the inside of circular hollow-out parts and propeller shaft axis during 90 ° of drops down
Perpendicular to circular hollow out facial planes, propeller component includes two blade propeller and motor.
5. four-axle aircraft as claimed in claim 4, it is characterised in that load bearing seat is semicircular arc connecting rod, semicircular arc
Centre position is provided with motor mounting seat, when motor is fixed on motor mounting seat, motor on the inside of connecting rod
The center of circle direction of semicircular arc connecting rod is pointed in rotating shaft.
6. four-axle aircraft as claimed in claim 3, it is characterised in that one end of four connecting rods is articulated in control box respectively
On, the pivoted nose of the connecting rod in control box is provided with the first spacing preiection, is limited in control box positioned at the two first of the same side
Position between position is raised is provided with the first limited impression matched with two first spacing preiections, and the first spacing preiection is placed in the first limit
When in the groove of position, control box is deployed into operating position.
7. four-axle aircraft as claimed in claim 6, it is characterised in that be located at two first limit convexes of the same side in control box
Position between rising sets a raised line, and first limited impression is formed on the two side of raised line.
8. the four-axle aircraft as described in claim 3 or 7, it is characterised in that the other end of four connecting rods is articulated in appearance respectively
It is empty on a madial wall, the pivoted nose of the connecting rod at accommodation space is provided with the second spacing preiection, accommodation space madial wall
On be correspondingly provided with the second limited impression matched with the second spacing preiection, when the second spacing preiection is placed in the second limited impression,
Two putting parts are deployed into conplane operating position.
9. four-axle aircraft as claimed in claim 3, it is characterised in that be provided with control module, control module bag in control box
Control unit and power supply are included, a controlling switch is connected in control unit, controlling switch is arranged on control box housing.
10. four-axle aircraft as claimed in claim 9, it is characterised in that control module also includes being connected to control unit
Camera, camera are arranged on control box housing.
11. four-axle aircraft as claimed in claim 3, it is characterised in that connecting rod is using connecting rod hollow or with inner groovy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721176526.0U CN207208469U (en) | 2017-09-13 | 2017-09-13 | Foldable propeller arrangement and four-axle aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721176526.0U CN207208469U (en) | 2017-09-13 | 2017-09-13 | Foldable propeller arrangement and four-axle aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207208469U true CN207208469U (en) | 2018-04-10 |
Family
ID=61824837
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721176526.0U Expired - Fee Related CN207208469U (en) | 2017-09-13 | 2017-09-13 | Foldable propeller arrangement and four-axle aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207208469U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525629A (en) * | 2019-07-26 | 2019-12-03 | 广东工业大学 | One kind can bending unmanned plane horn and unmanned plane |
| WO2021053406A1 (en) * | 2019-09-18 | 2021-03-25 | Uab "Sg Consulting Baltics & By" | Folding drone |
| CN113859525A (en) * | 2021-11-16 | 2021-12-31 | 山东省国土测绘院 | High remote sensing survey and drawing unmanned aerial vehicle of security |
-
2017
- 2017-09-13 CN CN201721176526.0U patent/CN207208469U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525629A (en) * | 2019-07-26 | 2019-12-03 | 广东工业大学 | One kind can bending unmanned plane horn and unmanned plane |
| WO2021053406A1 (en) * | 2019-09-18 | 2021-03-25 | Uab "Sg Consulting Baltics & By" | Folding drone |
| CN113859525A (en) * | 2021-11-16 | 2021-12-31 | 山东省国土测绘院 | High remote sensing survey and drawing unmanned aerial vehicle of security |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180410 Termination date: 20190913 |