CN106956767A - Aircraft - Google Patents
Aircraft Download PDFInfo
- Publication number
- CN106956767A CN106956767A CN201710301968.1A CN201710301968A CN106956767A CN 106956767 A CN106956767 A CN 106956767A CN 201710301968 A CN201710301968 A CN 201710301968A CN 106956767 A CN106956767 A CN 106956767A
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- CN
- China
- Prior art keywords
- framework
- axle
- main body
- aircraft
- aircraft according
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/006—Safety devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Body Structure For Vehicles (AREA)
- Tires In General (AREA)
Abstract
The application provides a kind of aircraft, including：Main body with propeller；Around the first framework of the main body, first framework and the main body are pivotally connected by first axle, with so as to be overturn relative to the main body；It is symmetrically disposed on the second framework and the 3rd framework on the outside of first framework, second framework and the 3rd framework are pivotally connected by the second axle perpendicular to the first axle and first framework, are enabled them to each leisure and are rotated in the plane of second axle；The edge of second framework and the 3rd framework exceeds the edge of first framework in the same direction.The application provide aircraft can be completed " to walk " by means of framework and " climbing wall " action, reduce the crash probability of aircraft, aircraft is not limited and can be arbitrarily risen and fallen by landform.
Description
Technical field
The present embodiments relate to technical field of aerospace, more particularly to a kind of aircraft.
Background technology
With the development of multiaxis unmanned vehicle, in the market occurs in that a variety of multiaxis unmanned vehicles come in every shape,
But they are all based on traditional, pneumatic power layout and change structure.
The motor of existing aircraft is installed and is all perpendicular to ground, has the disadvantage such as to run into external force in the air, it is easy to flying
Row attitude is impacted.
In addition, existing aircraft is only used for aerial work, it is impossible to touch wall, it can not be led in ground moving
Cause the inadequate diversification of application purpose.
Therefore it provides a kind of flight attitude is more stable, and has in road surface operation, climb flying for the functions such as wall and security protection
Row device turns into urgent problem to be solved.
The content of the invention
In view of problems of the prior art, the present invention provides a kind of aircraft, including：
Main body with propeller；
Around the first framework of the main body, first framework and the main body are pivotally connected by first axle, so that
Obtaining it can overturn relative to the main body；
It is symmetrically disposed on the second framework and the 3rd framework on the outside of first framework, second framework and described
Three frameworks are pivotally connected by the second axle perpendicular to the first axle and first framework, enable them to each leisure
Rotated in the plane of second axle；
The edge of second framework and the 3rd framework exceeds the edge of first framework in the same direction.
First framework of the aircraft that the present invention is provided can be relative to 360 ° of upsets of main body, the second framework and the 3rd framework
Then can planar it rotate, therefore the aircraft whether touches ground or touches wall, all without as existing
Aircraft is equally turned on one's side or crashed, but continues to move by said frame, completes to be similar to " walking " and the action of " climbing wall ".
The probability of aircraft crash so can be not only reduced, aircraft is not limited and can be arbitrarily risen and fallen by landform.
In certain embodiments of the present invention, second framework and the 3rd framework include：
The connecting portion being pivotally connected by the second axle and first framework；And
Around the peripheral frame of first framework；
The peripheral frame and the connecting portion are connected by spoke, to enable the peripheral frame perpendicular to
Rotated in the plane of two axles.
This kind design can provide support by force by spoke while aircraft overall weight is mitigated for peripheral frame
Degree.When aircraft touches wall or landing, spoke also acts the effect of protection, damping, and can protect winged
The important core part of row device.Shot in addition, this kind is designed with beneficial to the camera device for being installed on main body, do not interfere with its vision
Angle.Also act as the effect of the important core part of protection aircraft.
In certain embodiments of the present invention, the spoke is bent so that one part is in the peripheral frame institute
Locate the more lateral of plane, further to form reliable protecting screen structure.
In certain embodiments of the present invention, the spoke have it is a plurality of, its be evenly distributed in the connecting portion and
Between the peripheral frame.
In certain embodiments of the present invention, the first axle through the main body and its two ends respectively with described first
Framework is pivotally connected；First framework has the symmetry axis weight of axisymmetric shape, the first axle and first framework
Close.
In certain embodiments of the present invention, second framework and the 3rd framework are in annular.
In certain embodiments of the present invention, the first end of second axle be used for connect the second framework connecting portion and
First framework, the second end of second axle is used for the connecting portion and the first framework for connecting the 3rd framework：The institute of second axle
State the part between first end and second end expand outwardly with formed can surround the main body arc frame.
Because the first framework can be overturn along first axle relative to main body, in order to avoid the second axle is for above-mentioned flip-flop movement
Interference, the second axle can be set to two sections, be respectively used to being pivotally connected and the first frame for the first framework and the second framework
Being pivotally connected for frame and the 3rd framework, can also will be designed as special arc as present embodiment in the middle part of the second axle
Frame, from relative both direction surround main body, no matter how the first framework overturns, can retainer body be located at arc frame it
It is interior.In addition, the second axle actually also acts the effect of reinforcement for the first framework.
In certain embodiments of the present invention, to penetrate the connecting portion backward the first end of second axle and the second end
The direction for the peripheral frame is bent, and the end at the first end and second end is fixedly connected with the peripheral frame.
Present embodiment is extended using the second the tip of the axis, is formd two extra spokes, is further improved external surrounding frame
The intensity and cushioning effect of frame.
In certain embodiments of the present invention, described aircraft can also include：
It is fixedly arranged at the supporting part of the bottom part body；
It is arranged at the driver element for driving the propeller rotational on the supporting part；And
It is arranged at control unit, power supplier unit and sensor unit on the supporting part.
The aircraft that present embodiment is provided supplies power to unit, sensor unit, control unit installed in main body bottom
On the supporting part in portion, make it that they and main body have certain distance, and then realize that the center of gravity for keeping aircraft is on central shaft
But positioned at the lower section of body, this makes it possible to make it be similar to the attitude stabilization that tumbler equally remains aircraft, carry
The quality of high Aerial photography.
In certain embodiments of the present invention, the bottom surface of the driver element and the main body angularly cloth
Put.
Driver element can use motor, and it can be angled with ground, and the angle can be less than or equal to 20 °, tool
Depending on the body number of degrees are according to type, overall weight, special circumstances can also exceed this numerical value, and the benefit so designed is motor angulation
Degree layout is conducive to the stabilization of aircraft.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
The accompanying drawing to be used needed for having technology description is briefly described, it should be apparent that, drawings in the following description are this hairs
Some bright embodiments, for those of ordinary skill in the art, on the premise of not paying creative work, can be with root
Other accompanying drawings are obtained according to these accompanying drawings.
The schematic diagram at the visual angle of aircraft first that Fig. 1 provides for an embodiment of the present invention；
Fig. 2 is the schematic diagram at the second visual angle of shown aircraft in Fig. 1；
Fig. 3 is the top view of shown aircraft in Fig. 1.
Embodiment
To make the purpose, technical scheme and advantage of the embodiment of the present invention clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
A part of embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
It should be noted that in the case where not conflicting, the embodiment in the present invention and the feature in embodiment can phases
Mutually combination.Describe the present invention in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Shown in reference picture 1~3, the aircraft that an embodiment of the present invention is provided mainly includes main body 1, the first framework 2, the
Two frameworks 3, the 3rd framework 4, the axle 6 of first axle 5 and second.
Specifically, main body 1 has multiple propellers, and the propeller can be evenly distributed in main body 1, to offset mutually
Between the moment of torsion that produces.First framework 2 is completely in the inside of the first framework 2 around main body 1, i.e. main body 1.The He of first framework 2
Main body 1 is pivotally connected by first axle 5, to enable the first framework 2 to be overturn relative to main body 1.Second framework 3 and the 3rd frame
Frame 4 is symmetrically disposed on the outside of the first framework 2, and by with the framework pivot 2 of orthogonal second axle of first axle 56 and first
Turn connection, enable them to each leisure and rotated in the plane of the second axle 6.Second framework 3 and the 3rd framework 4 can be with
In flake (being different from the shape shown in Fig. 1~3), their edge exceeds the edge of the first framework in the same direction.
According to above-mentioned setting, the first framework 2 can be overturn relative to main body 1, and the second framework 3 and the second framework 4 can be
Rotated on first framework 2, above-mentioned upset and rotary motion are each independent, are independent of each other.Also, due to the second framework 3 and the 3rd
The edge of framework 4 exceeds the edge of the first framework 2 in the same direction, therefore the second framework 3 and the 3rd framework 4 are used as and mainly connect
Touch the position of wall or bottom surface.In addition, those skilled in the art are it should be understood that the second axle 6 can be one whole axle, it
First framework 2 and the second framework 3 are pivotally connected by one end, and the first framework 2 and the 3rd framework 4 are pivotally connected by the other end.Second
Axle 6 can also be two axles, be respectively used to be pivotally connected the first framework 2 and the second framework 3 and the first framework 2 and the 3rd framework
4。
In embodiment as shown in Figures 1 to 3, the second framework 3 and the 3rd framework 4 include connecting portion 31,41 and outer
Peripheral frame frame 32,42, they are symmetrically dispersed in the both sides of the first framework 2, and are identical structures, therefore hereafter with
Illustrated exemplified by the connecting portion 31 and peripheral frame 32 of two frameworks 3.
The framework 2 of connecting portion 31 and first is pivotally connected by the second axle 6, and peripheral frame 32 is then arranged around the first framework 2.
Peripheral frame 32 and connecting portion 31 are connected by spoke 33, to enable peripheral frame 32 in the plane perpendicular to the second axle 6
Interior rotation.This kind of set-up mode can enter one relative to the above-mentioned mode that second framework 3 and the 3rd framework 4 are designed as into thin slice
The weight of the whole aircraft of step reduction, obtains higher intensity, and enable to when installation settings has camera device in main body 1
With the broader visual field.
In certain embodiments of the present invention, spoke 33 is in bending, and one part is relative to where peripheral frame 32
Plane be in more outside, with cause spoke 33 not only have structural strengthening act on, and can the second framework 3 outside shape
Into catch net, it is to avoid object collides the second framework 3 by side.Spoke 33 can have a plurality of, and be evenly distributed in connecting portion
Between 31 and peripheral frame 32, so that the second framework 3 constitutes the shape similar to cycle wheel.
In certain embodiments of the present invention, first axle 5 runs through main body 1, and its two ends is pivoted with the first framework 2 respectively to be connected
Connect.First framework 2 then has axisymmetric shape, the symmetrical overlapping of axles of the framework 2 of first axle 5 and first, for example, the first framework 2
The axisymmetric shape similar to butterfly's wing as illustrated in figures 1-3 can be showed, but is not limited to this.The He of second framework 3
3rd framework 4 can then show annular as illustrated in figures 1-3, and the second framework 3 and the 3rd framework 4 are in whole aircraft
Front and rear direction on exceed the edge of the first framework 2, i.e. their edge is beyond the side of the first framework in the same direction
Edge.
With continued reference to shown in Fig. 1~3, in another embodiment of the invention, the second axle 6 can as it is described above that
Sample, its first end 61 is used for the framework 2 of connecting portion 31 and first for being pivotally connected the second framework 3, and its second end 62 is used for the company of pivot
Connect the framework 2 of connecting portion 41 and first of the 3rd framework 4.Different from described above, the second axle 6 is located at first end 61 and the
Part between two ends 62 is expanded towards outside can surround the arc frame 63 of main body 1 to be formed.Therefore, no matter the first framework 2
How to be overturn relative to main body 1, the second axle 6 will not hinder its motion.In addition, the second axle 6 of this kind of shape also becomes
The reinforcement of first framework 2.
The end 62 of first end 61 and second of second axle 6 is penetrated after connecting portion 31,41 towards the side of peripheral frame 32,42 respectively
To bending, their end is finally fixedly connected with peripheral frame 32,42 respectively, and their degree of crook can be with the phase of spoke 33
Together.In fact, spoke is regarded in this part that completely them can be bent.For the ease of processing, the second axle 6 can be used as schemed
The shape being put together by symmetrical two parts shown in 1~3.
In certain embodiments of the present invention, the aircraft can also include being fixedly arranged at holding for the bottom of main body 1
Load portion, be arranged on supporting part for the control unit that drives the driver element of propeller rotational and be arranged on supporting part
And power supplier unit.This kind of design is in order to by the decentralization of whole aircraft so that aircraft is in flight, touching
Soon flight attitude can be adjusted to when wall or ground to steady attitude, then coordinate the turnover He of first framework 2
The rotatable framework 4 of second framework 3 and the 3rd forms a kind of structure similar to tumbler.
In certain embodiments of the present invention, the bottom surface of driver element and main body 1 is angled, i.e., when main body 1
When bottom surface is parallel with ground, driver element and ground are angled.
Finally it should be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although
The present invention is described in detail with reference to the foregoing embodiments, it will be understood by those within the art that：It still may be used
To be modified to the technical scheme described in foregoing embodiments, or to which part technical characteristic progress equivalent；
And these modification or replace, do not make appropriate technical solution essence depart from various embodiments of the present invention technical scheme spirit and
Scope.
Claims (10)
1. aircraft, it is characterised in that including：
Main body with propeller；
Around the first framework of the main body, first framework and the main body are pivotally connected by first axle, to cause it
It can be overturn relative to the main body；
It is symmetrically disposed on the second framework and the 3rd framework on the outside of first framework, second framework and the 3rd frame
Frame is pivotally connected by the second axle perpendicular to the first axle and first framework, is enabled them to each comfortable vertical
In rotation in the plane of second axle；
The edge of second framework and the 3rd framework exceeds the edge of first framework in the same direction.
2. aircraft according to claim 1, it is characterised in that second framework and the 3rd framework include：
The connecting portion being pivotally connected by the second axle and first framework；And
Around the peripheral frame of first framework；
The peripheral frame and the connecting portion are connected by spoke, to enable the peripheral frame perpendicular to the second axle
Plane in rotate.
3. aircraft according to claim 2, it is characterised in that：
The spoke is bent so that one part is in the more lateral of plane residing for the peripheral frame.
4. the aircraft according to any one of Claims 2 or 3, it is characterised in that：
The spoke has a plurality of, and it is evenly distributed between the connecting portion and the peripheral frame.
5. aircraft according to claim 1, it is characterised in that：
The first axle runs through the main body and its two ends is pivotally connected with first framework respectively；
First framework has the symmetrical overlapping of axles of axisymmetric shape, the first axle and first framework.
6. aircraft according to claim 5, it is characterised in that：
Second framework and the 3rd framework are in annular.
7. aircraft according to claim 2, it is characterised in that：
The first end of second axle is used for the connecting portion and the first framework for connecting the second framework, and the second end of second axle is used
In the connecting portion and the first framework that connect the 3rd framework：
Part between the first end of second axle and second end is expanded outwardly can surround the master to be formed
The arc frame of body.
8. aircraft according to claim 7, it is characterised in that：
The first end of second axle and the second end penetrated and bent after the connecting portion towards the direction of the peripheral frame, described
The end at first end and second end is fixedly connected with the peripheral frame.
9. aircraft according to claim 1, it is characterised in that including：
It is fixedly arranged at the supporting part of the bottom part body；
It is arranged at the driver element for driving the propeller rotational on the supporting part；And
It is arranged at control unit, power supplier unit and sensor unit on the supporting part.
10. aircraft according to claim 9, it is characterised in that：
The bottom surface of the driver element and the main body is angularly arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710301968.1A CN106956767B (en) | 2017-05-02 | 2017-05-02 | Aircraft with a flight control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710301968.1A CN106956767B (en) | 2017-05-02 | 2017-05-02 | Aircraft with a flight control device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106956767A true CN106956767A (en) | 2017-07-18 |
| CN106956767B CN106956767B (en) | 2020-06-02 |
Family
ID=59481719
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710301968.1A Active CN106956767B (en) | 2017-05-02 | 2017-05-02 | Aircraft with a flight control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106956767B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109159894A (en) * | 2018-08-09 | 2019-01-08 | 北京理工大学 | A kind of air-ground amphibious spherical unmanned plane |
| US20230373616A1 (en) * | 2020-09-30 | 2023-11-23 | Nippon Telegraph And Telephone Corporation | Propeller guard, flying body, and rod-shaped body |
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| CN102849210A (en) * | 2012-10-08 | 2013-01-02 | 西北工业大学 | Spherical small unmanned aircraft |
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| US20230373616A1 (en) * | 2020-09-30 | 2023-11-23 | Nippon Telegraph And Telephone Corporation | Propeller guard, flying body, and rod-shaped body |
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| Publication number | Publication date |
|---|---|
| CN106956767B (en) | 2020-06-02 |
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Effective date of registration: 20190801 Address after: 518054 Virtual University Park C505, No. 2 Sandao, Yuexing Street, Nanshan District, Shenzhen City, Guangdong Province Applicant after: Shenzhen Ruihe Aircraft Intelligent Equipment Co., Ltd. Address before: 100191 Beijing, Zhichun Road, College of International Building, No. 912,, 1 Applicant before: Sharp Defense Technology (Beijing) Co., Ltd. |
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