CN208393615U - The fuselage ring and aircraft of aircraft - Google Patents
The fuselage ring and aircraft of aircraft Download PDFInfo
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- CN208393615U CN208393615U CN201820459105.7U CN201820459105U CN208393615U CN 208393615 U CN208393615 U CN 208393615U CN 201820459105 U CN201820459105 U CN 201820459105U CN 208393615 U CN208393615 U CN 208393615U
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- transverse arm
- fuselage ring
- aircraft
- arm
- central frame
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Abstract
The embodiment of the present application discloses the fuselage ring and aircraft of aircraft.One specific embodiment of the fuselage ring includes: transverse arm, linking arm and central frame；Transverse arm includes the first transverse arm and the second transverse arm；First transverse arm and the second transverse arm are arranged oppositely relative to central frame, and are fixedly connected respectively by linking arm with central frame；It is provided with mounting base on first transverse arm and the second transverse arm, for installing power part.The embodiment can help improve the integrally-built robustness of aircraft.
Description
Technical field
The invention relates to vehicle technology fields, and in particular to the fuselage ring and aircraft of aircraft.
Background technique
UAV can referred to as " unmanned plane ", english abbreviation UAV.Unmanned plane is usually to utilize wireless remotecontrol
The not manned vehicle of equipment and the presetting apparatus provided for oneself manipulation.Can also by car-mounted computer fully or intermittently from
It operates mainly.
With the development of science and technology, unmanned plane is all widely applied at dual-use aspect.Such as civilian side
Face, unmanned plane can be used for express transportation.For large-scale rotor wing unmanned aerial vehicle, horn is mostly used to be mounted directly to ontology, this
Body lower part hangs foot prop, and on foot prop carry container structure.
Utility model content
The embodiment of the present application proposes the fuselage ring and aircraft of aircraft.
In a first aspect, the embodiment of the present application proposes a kind of fuselage ring of aircraft, comprising: transverse arm, linking arm and in
Between frame；Transverse arm includes the first transverse arm and the second transverse arm；First transverse arm and the second transverse arm are arranged oppositely relative to central frame, and
It is fixedly connected respectively by linking arm with central frame；It is provided with mounting base on first transverse arm and the second transverse arm, for installing
Power part.
In some embodiments, the first transverse arm and the second transverse arm pass through at least two linking arms respectively and fix with central frame
Connection.
In some embodiments, the both ends of the first transverse arm are respectively arranged with mounting base, and the intermediate position of the first transverse arm with
Linking arm is fixedly connected；The both ends of second transverse arm are respectively arranged with mounting base, and the intermediate position of the second transverse arm and linking arm are solid
Fixed connection.
In some embodiments, linking arm includes at least two tubing fixed side by side；One end of at least two root canal materials is equal
It is fixedly connected with transverse arm, and the other end is fixedly connected with central frame, wherein fixed form includes welding.
In some embodiments, central frame is square body structure, and the inside of square body structure is formed with accommodation space.
In some embodiments, which further includes foot prop, is used to support fuselage ring；Foot prop and central frame connect
It connects, and is arranged oppositely with transverse arm, wherein connection type includes being detachably connected.
In some embodiments, which is made of hard tubing, and the shape of hard tubing includes round and/or side
Shape.
In some embodiments, it is additionally provided with connecting component on the fuselage ring, for installing the shell of aircraft.
Second aspect, the embodiment of the present application propose any in a kind of aircraft, including power part and such as first aspect
Fuselage ring described in embodiment；Power part is mounted in the mounting base of fuselage ring, for providing flight to aircraft
Required power, wherein power part includes rotor.
In some embodiments, aircraft further includes shell, and shell is fixed with fuselage ring, and covers at least partly fuselage
Frame；The inside of fuselage ring is formed with accommodation space, for loading cargo.
The fuselage ring and aircraft for the aircraft that the embodiment of the present application proposes, may include transverse arm, linking arm and centre
Frame.Wherein, transverse arm may include the first transverse arm and the second transverse arm.First transverse arm and the second transverse arm can be relative to central frames
It is arranged oppositely, and is fixedly connected respectively by linking arm with central frame.Meanwhile first is respectively provided on transverse arm and the second transverse arm
There is mounting base.Here mounting base can be used for installing power part.Due to during flight, the whole stress of aircraft
It can all may finally concentrate on central frame, so the fuselage ring of this structure helps to improve the overall structure of aircraft
Robustness.And firm structure can also advantageously ensure that the steady row of aircraft flight, convenient for operation control.
Detailed description of the invention
By reading a detailed description of non-restrictive embodiments in the light of the attached drawings below, the application's is other
Feature, objects and advantages will become more apparent upon:
Fig. 1 is the structural schematic diagram of one embodiment of fuselage ring provided by the present application；
Fig. 2 is the structure front view of fuselage ring shown in FIG. 1；
Fig. 3 is the structure right view of fuselage ring shown in FIG. 1；
Fig. 4 is the structure top view of fuselage ring shown in FIG. 1；
Fig. 5 is the structure bottom view of fuselage ring shown in FIG. 1.
Specific embodiment
The principle of the application and feature are described in further detail with reference to the accompanying drawings and examples.It is understood that
It is that specific embodiment described herein is used only for explaining relevant utility model, rather than the restriction to the utility model.In addition
It should also be noted that, illustrating only part relevant to utility model for ease of description, in attached drawing.
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The application is described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Shown in Figure 1, it illustrates the structures of one embodiment of the fuselage ring of aircraft provided by the present application
Schematic diagram.Wherein, aircraft here may include (but being not limited to) unmanned plane.The fuselage ring of aircraft in the present embodiment
It may include transverse arm, linking arm 2 and central frame 3.
As shown in Figure 1, transverse arm may include the first transverse arm 11 and the second transverse arm 12.Wherein, the first transverse arm 11 and second is horizontal
Arm 12 can be fixedly connected by linking arm 2 with central frame 3 respectively.And the first transverse arm 11 and the second transverse arm 12 can be opposite
It is arranged oppositely in central frame 3.That is the first transverse arm 11 and the second transverse arm 12 are symmetrical arranged centered on central frame 3.
In the present embodiment, mounting base 4 can be set on the first transverse arm 11 and the second transverse arm 12.Mounting base 4 can be with
For installing power part, to provide power for the flight of aircraft.It should be noted that installation of the mounting base 4 on transverse arm
Position and installation number can be arranged according to the actual situation.Such as it can be according to the overall weight of aircraft and moving for selection
The model parameter of power component determines the quantity of mounting base.And the smooth flight in order to realize aircraft, each power part are logical
Often to be symmetrically installed.Therefore, each mounting base 4 on transverse arm can be generally symmetrical arranged.
Central frame 3 in the present embodiment can (but not limiting) as steel structure frame.Wherein, steel construction generally refer to by
The structure of steel material composition.The main component groups such as the girder steel made of fashioned iron and steel plate etc., steel column, steel truss of this structure
At can usually use weld seam, bolt or rivet interlacement between each component or component.It is high with intensity, from heavy and light, overall stiffness
Well, deformability is strong, and the features such as easy construction.That is, each frame of central frame 3 is steel material, and each frame
Between can using welding, riveting etc. connection types.
It is understood that the power part being mounted in mounting base 4 can drive transverse arm during flight, into
And central frame 3 can be driven by linking arm 2, to realize the sporting flying of aircraft.In this way, the whole stress of aircraft
It can all may concentrate on central frame 3, so the fuselage ring of this structure helps to improve the integrally-built of aircraft
The biggish aircraft of robustness, especially Large Scale Space Vehicle or load-carrying.And firm structure can also advantageously ensure that it is winged
The steady row of row device flight, convenient for operation control.
It should be noted that central frame here can also be using the metal or nonmetallic that other are light-weight, intensity is high
Material.And it in order to further increase the fastness of central frame, can be used between each frame of central frame non-dismountable
The connection type of connection connects, such as welding, bonding, hot-melt adhesive paste.
In the present embodiment, the first transverse arm can be fixedly connected by least one linking arm with central frame.And second
Transverse arm can also be fixedly connected by least one linking arm with central frame.
Optionally, the first transverse arm can be fixedly connected by least two linking arms with central frame.Second transverse arm can also
To be fixedly connected by least two linking arms with central frame.In addition, the stress balance in order to guarantee fuselage ring, with first
At least two linking arms of transverse arm connection are symmetrical arranged usually relative to the middle section of the first transverse arm；And it is connect with the second transverse arm
At least two linking arms usually relative to the second transverse arm middle section be symmetrical arranged.And it is connect at least with the first transverse arm
Two linking arms and at least two linking arms connecting with the second transverse arm can be generally also symmetrical arranged relative to central frame.
Further, as shown in Figure 1, the intermediate position of the first transverse arm 11 can be fixedly connected with a linking arm 2.That is the company
The intermediate position of one end and the first transverse arm 11 for connecing arm 2 is fixedly connected, and the middle part of a frame of the other end and central frame 3
Position is fixedly connected.In order to make the two sides stress of central frame 3 reach balance, the intermediate position of the second transverse arm 12 can also connect with one
Arm 2 is connect to be fixedly connected.That is one end of the linking arm 2 and the intermediate position of the second transverse arm 12 is fixedly connected, and the other end and centre
The intermediate position of another frame of frame 3 is fixedly connected.
At this point, from figure 1 it appears that the both ends of the first transverse arm 11 can be respectively arranged with mounting base 4.And second transverse arm
12 both ends can also be respectively arranged with mounting base 4.As shown in Figure 2 and Figure 5, which respectively show fuselage rings shown in FIG. 1
Structure front view and structure bottom view.Transverse arm can be fixedly connected with mounting base 4 by bolt and clip, in this way convenient for peace
Fill the dismounting of seat 4.Meanwhile the part that mounting base 4 is arranged in transverse arm can be cylinder, it, can in this way by rotation clip
Adjust setting angle of the mounting base 4 on transverse arm.The adjustable connection of mounting base and transverse arm can be thus achieved, thus lift fuselage frame
The flexibility of frame installation, expands the scope of application of fuselage ring.
Optionally, in order to improve the robustness of fuselage ring entirety, linking arm may include at least two fixed side by side
Tubing.It is shown in Figure 1, linking arm 2 can be by three root canal materials side by side (lining up a word) fixation formed.This three root canals material
One end is fixedly connected with the one end of transverse arm (the first transverse arm 11 or the second transverse arm 12), and the other end and central frame of three root canal materials
It is fixedly connected.It can not only guarantee support strength in this way, but also can achieve the effect of resistance to deformation.
Here fixed form (fixation of fixation and linking arm and transverse arm, central frame i.e. between tubing) is in this Shen
Please in be not intended to limit, such as can be bolt and fix.In order to increase the solidness of linking arm, as shown in Figure 1, this three root canals material can be with
Using being welded and fixed.And in order to increase the solidness of fuselage ring entirety, linking arm 2 can also be adopted with transverse arm, central frame 3
With being welded and fixed.In addition, the overall weight of fuselage ring, linking arm 2 can be mitigated as much as possible while increasing solidness
In be located at two sides the diameter of tubing can be less than and be located in the middle the diameter of tubing.And the material for being located at the tubing of two sides can be with
It is different from the material for being located in the middle tubing.
It is understood that since the central frame in the embodiment of the present application is tower structure, so this frame-type
Structure can form accommodation space in inside.As an example, shown in Figure 1, central frame 3 can be square body (cuboid
Or square) structure.In this way, could be formed with accommodation space in the inside of square body structure (central frame 3).The accommodation space
It can be used for loading cargo.So as to realize the loading function of aircraft, facilitate the scope of application of lift fuselage frame.Separately
Outside, in order to further increase the robustness of central frame 3, reinforcing rib also can be set between the part frame of central frame 3
Or connecting rod.
In application scenes, fuselage ring can also include foot prop, be used to support fuselage ring.As shown in Figure 1, foot
Frame 5 can equally be connect with central frame 3.Here connection type is not intended to limit in this application.For the ease of fuselage ring
Maintenance, or foot prop is replaced according to use environment, the connection type between foot prop 5 and central frame 3 may include removable
Unload connection, such as bolt, clip.
In addition, since foot prop 5 is used to support fuselage ring, and the transverse arm of power part is installed for driving fuselage ring
Flight, so as shown in Figure 1, foot prop 5 can be arranged oppositely with transverse arm.That is the lower end surface that is set to central frame 3 of foot prop 5,
Transverse arm is set to the upper surface of central frame 3.Wherein, lower end surface can be the end face towards ground, and upper surface can be with
The opposite end face in lower end surface.
Further, as can be seen that foot prop 5 is also provided with cross bar 6 from Fig. 1 and Fig. 2.Foot prop can be improved in this way
5 support strength, avoids that the span of 5 two sides of foot prop is larger, whole load-carrying is larger or the reasons such as loading is heavier, and shape occurs for foot prop 5
Become, to ensure that the stability of foot prop.It should be noted that the structure and installation site of foot prop 5 are only schematic in Fig. 1
's.
And as shown in Figure 4, it illustrates the structure top views of fuselage ring shown in FIG. 1.In order to be put in fuselage ring
When setting or when aircraft lands, guarantee whole stability, the area that the orthographic projection of foot prop 5 on the ground is surrounded is usually big
In the area that the orthographic projection of central frame 3 on the ground is surrounded.So, it can reduce because gravity center instability leads to fuselage frame
The phenomenon that frame is toppled over.
It is understood that the fuselage ring in above-described embodiment can be made of hard tubing, such as metal tube, plastics
Pipe etc..From figure 1 it appears that the shape of hard tubing may include round and/or rectangular.It not only can guarantee fuselage
The resistance to deformation characteristic of frame, increases whole firmness, can also suitably mitigate the weight of fuselage ring entirety.To in phase
Under homodynamic effect, more cargos can be loaded.The fuselage ring of this structure be more applicable for volume it is larger or carry
The aircraft increased again.
Optionally, the fuselage ring in the embodiment of the present application is also provided with connecting component.As shown in figures 1 and 3, exist
Connecting component 7 can be set on first transverse arm 11, the second transverse arm 12 and central frame 3.Connecting component 7 can be used for installing winged
The shell of row device.Wherein, Fig. 3 shows the structure right view of the fuselage ring in Fig. 1.It should be noted that interconnecting piece in figure
The structure of part, quantity and installation site are only schematical.It can adjust according to the actual situation.
The embodiment of the present application also provides a kind of aircraft, which may include power part and the various embodiments described above
Described in fuselage ring.
In the present embodiment, power part may be mounted in the mounting base of fuselage ring.By the various embodiments described above it is found that
Mounting base can be set on the transverse arm of fuselage ring.Here needed for power part can be used for providing flight to aircraft
Power.As an example, power part may include rotor.
Rotor is usually to be made of propeller hub and several pieces blades.Propeller hub is mounted in rotor shaft, the blade shaped like slender wing
Then it is connected on propeller hub.It interacts when blade rotates with surrounding air, can produce the pulling force along rotor shaft.If relative wind
Direction or the pitch of each blade be asymmetric with rotor shaft, the component perpendicular to rotor shaft can also be generated.On helicopter,
Rotor axis direction is bordering on vertically, therefore rotor has the function of wing first, generates upward power.Secondly also have to be similar to and fly
The function of machine propulsion device generates forward power.It also has the function similar to aircraft control surface, generates and changes body posture
Pitching moment or rolling moment.
Optionally, the aircraft in the present embodiment can also include shell.The shell can be fixed with fuselage ring, and be covered
Lid at least partly fuselage ring.In this way, can not only play a protective role to fuselage ring, the shape of aircraft can also be risen
To beautification function.Simultaneously as the inside of fuselage ring is formed with accommodation space, it is possible to which fuselage ring is designed to goods
Case, for loading cargo.
It is understood that the aircraft in the present embodiment, by using fuselage frame described in the various embodiments described above
Frame can advantageously ensure that the robustness and stability of entire aircraft, so as to promote the delivered payload capability of aircraft.
Above description is only the preferred embodiment of the application and the explanation to institute's application technology principle.Those skilled in the art
Member is it should be appreciated that utility model range involved in the application, however it is not limited to made of the specific combination of above-mentioned technical characteristic
Technical solution, at the same should also cover do not depart from the utility model design in the case where, by above-mentioned technical characteristic or its be equal
Feature carries out any combination and other technical solutions for being formed.Such as features described above and (but being not limited to) disclosed herein have
The technical solution for thering is the technical characteristic of similar functions to be replaced mutually and being formed.
Claims (10)
1. a kind of fuselage ring of aircraft, which is characterized in that the fuselage ring includes: transverse arm, linking arm (2) and middle boxes
Frame (3)；
The transverse arm includes the first transverse arm (11) and the second transverse arm (12)；
First transverse arm (11) and second transverse arm (12) are arranged oppositely relative to the central frame (3), and are led to respectively
The linking arm (2) is crossed to be fixedly connected with the central frame (3)；
Mounting base (4) are provided on first transverse arm (11) and second transverse arm (12), for installing power part.
2. fuselage ring according to claim 1, wherein first transverse arm (11) and second transverse arm (12) are respectively
It is fixedly connected by least two linking arms (2) with the central frame (3).
3. fuselage ring according to claim 1, wherein the both ends of first transverse arm (11) are respectively arranged with the peace
It fills seat (4), and the intermediate position of first transverse arm (11) is fixedly connected with the linking arm (2)；
The both ends of second transverse arm (12) are respectively arranged with the mounting base (4), and the middle part of second transverse arm (12)
Position is fixedly connected with the linking arm (2).
4. fuselage ring according to claim 1, wherein the linking arm (2) includes at least two pipes fixed side by side
Material；
One end of at least two root canal materials is fixedly connected with the transverse arm, and the other end is solid with the central frame (3)
Fixed connection, wherein fixed form includes welding.
5. fuselage ring according to claim 1, wherein the central frame (3) is square body structure, the square body
The inside of structure is formed with accommodation space.
6. fuselage ring according to claim 1, wherein the fuselage ring further includes foot prop (5), is used to support described
Fuselage ring；
The foot prop (5) connect with the central frame (3), and is arranged oppositely with the transverse arm, wherein connection type includes can
Dismantling connection.
7. fuselage ring according to claim 1, wherein the fuselage ring is made of hard tubing, the stereoplasm tube
The shape of material includes round and/or rectangular.
8. fuselage ring described in one of -7 according to claim 1, wherein be additionally provided with connecting component on the fuselage ring
(7), for installing the shell of aircraft.
9. a kind of aircraft, which is characterized in that the aircraft includes power part and machine as described in one of claim 1-8
Body frame；
The power part is mounted in the mounting base of the fuselage ring, for providing flight required power to aircraft,
Wherein, the power part includes rotor.
10. aircraft according to claim 9, wherein the aircraft further includes shell, the shell and the fuselage
Frame is fixed, and covers at least partly described fuselage ring；
The inside of the fuselage ring is formed with accommodation space, for loading cargo.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820459105.7U CN208393615U (en) | 2018-04-03 | 2018-04-03 | The fuselage ring and aircraft of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820459105.7U CN208393615U (en) | 2018-04-03 | 2018-04-03 | The fuselage ring and aircraft of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208393615U true CN208393615U (en) | 2019-01-18 |
Family
ID=65064666
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820459105.7U Active CN208393615U (en) | 2018-04-03 | 2018-04-03 | The fuselage ring and aircraft of aircraft |
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| Country | Link |
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| CN (1) | CN208393615U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114193990A (en) * | 2022-01-27 | 2022-03-18 | 广东汇天航空航天科技有限公司 | Horn and hovercar |
-
2018
- 2018-04-03 CN CN201820459105.7U patent/CN208393615U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114193990A (en) * | 2022-01-27 | 2022-03-18 | 广东汇天航空航天科技有限公司 | Horn and hovercar |
| CN114193990B (en) * | 2022-01-27 | 2023-04-18 | 广东汇天航空航天科技有限公司 | Arm and aerocar |
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Effective date of registration: 20210305 Address after: 101, 1st floor, building 2, yard 20, Suzhou street, Haidian District, Beijing 100080 Patentee after: Beijing Jingbangda Trading Co.,Ltd. Address before: 100195 Beijing Haidian Xingshikou Road 65 West Cedar Creative Garden 4 District 11 Building East 1-4 Floor West 1-4 Floor Patentee before: BEIJING JINGDONG SHANGKE INFORMATION TECHNOLOGY Co.,Ltd. Patentee before: BEIJING JINGDONG CENTURY TRADING Co.,Ltd. Effective date of registration: 20210305 Address after: Room a1905, 19 / F, building 2, No. 18, Kechuang 11th Street, Daxing Economic and Technological Development Zone, Beijing 100176 Patentee after: Beijing Jingdong Qianshi Technology Co.,Ltd. Address before: 101, 1st floor, building 2, yard 20, Suzhou street, Haidian District, Beijing 100080 Patentee before: Beijing Jingbangda Trading Co.,Ltd. |
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