CN209258372U - A kind of unmanned aerial vehicle body bearing structure - Google Patents
A kind of unmanned aerial vehicle body bearing structure Download PDFInfo
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- CN209258372U CN209258372U CN201822181288.3U CN201822181288U CN209258372U CN 209258372 U CN209258372 U CN 209258372U CN 201822181288 U CN201822181288 U CN 201822181288U CN 209258372 U CN209258372 U CN 209258372U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
A kind of unmanned aerial vehicle body bearing structure, the fuselage support including a full symmetrical configuration, the fuselage support have the lateral symmetry axis for being transversely to the machine direction the axis of symmetry；The fuselage support includes two carbon fiber girders for being symmetrical with longitudinal asymmetric axis setting, and two are symmetrical with the engine bearing floor of lateral symmetry axis setting, undercarriage carrying floor, cantilever carrying floor and end carrying floor；Engine bearing floor, undercarriage carrying floor, cantilever carrying floor and end carrying floor slave body bracket the two sides of the symmetrical centre axis of symmetry along longitudinal direction be arranged successively.The fuselage bearing structure of the application can obtain enough torsional properties and intensity by the full carbon fuselage support of full symmetrical configuration, and by the web structure of more low clearance, while can reject existing metal component, significantly mitigation construction weight.And lower fuselage height can be obtained, windage is reduced, covering area is reduced, there is excellent weight loss effect.
Description
Technical field
The utility model relates to air vehicle technique field more particularly to a kind of unmanned aerial vehicle body bearing structures.
Background technique
Existing unmanned plane generallys use motor or fuel engines driving.Electronic unmanned plane structure is simply easily fabricated,
But voyage is shorter, load level is lower, can not be applied to military big load scout-attack field.Present applicant exists
In the Chinese patent application 201711089304.X applied before, a kind of load configuration structure of unmanned plane, including one are disclosed
To main bearing frame, first bearing frame and the second bearing frame, the front of the first bearing frame are each provided with before and after main bearing frame
One head bearing frame is set, and a tail bearing frame is arranged in the rear of the second bearing frame, and described two main bearing frames, first are held
Frame, the second bearing frame, head bearing frame and tail bearing frame is carried to be connected as one by four main support rods.The prior art
Above-mentioned load configuration structure be parallel to longitudinal main support rods of the axis of symmetry around foring by multiple bearing frames and four
One supporting and space, can be arranged drive mechanism wherein, provide protection to the various moving components to drive mechanism, and lead to
Cross the supporting and space and separate various load with drive mechanism, allow load it is more flexible configuration without regard to
The influence of drive mechanism.
The prior art effectively overcomes the defect of the prior art, but still has room for improvement.Especially need
Structural strength, torsional property are further increased, while mitigating construction weight, reduces resistance.
Utility model content
The technical problem to be solved by the present invention is to provide a kind of unmanned aerial vehicle body bearing structures, before being reduced or avoided
The problem of face is previously mentioned.
In order to solve the above technical problems, the utility model proposes a kind of unmanned aerial vehicle body bearing structure, the unmanned plane
Fuselage there is a longitudinal asymmetric axis, the head and tail of the unmanned plane are each provided with two, and to be symmetrical with the longitudinal direction right
Claim the cantilever of axis arrangement, in which: the unmanned aerial vehicle body bearing structure includes the fuselage support of a full symmetrical configuration, described
Fuselage support has the lateral symmetry axis perpendicular to the longitudinal asymmetric axis；The fuselage support includes two and is symmetrical with institute
The carbon fiber girder of longitudinal asymmetric axis setting is stated, two are symmetrical with the engine bearing rib of the lateral symmetry axis setting
Plate, two are symmetrical with the undercarriage carrying floor of the lateral symmetry axis setting, and two are symmetrical with the lateral symmetry axis
The cantilever carrying floor of setting and two ends for being symmetrical with the lateral symmetry axis setting carry floor；The engine
It carries floor, undercarriage carrying floor, cantilever carrying floor and end and carries symmetrical centre of the floor from the fuselage support
Two sides along the longitudinal asymmetric axis are arranged successively.
Preferably, the cross section of the carbon fiber girder is I-shaped, and the cross section of the carbon fiber girder is from the machine
The symmetrical centre of body bracket is gradually reduced along the two sides of the longitudinal asymmetric axis.
Preferably, the engine bearing floor, undercarriage carrying floor, cantilever carrying floor and end carry floor
End be provided with the reinforcement support plate being fixedly connected with the carbon fiber girder.
Preferably, four points that two engine bearing floors are connect with two carbon fiber girders are set respectively
It is equipped with four foot props for supporting the engine.
Preferably, carry is provided with below the installation point of four foot props on two carbon fiber girders
The carry frame of arm discharge cylinder.
Preferably, the cantilever is fixedly connected on the pole bracket on the carbon fiber girder, and the pole bracket is set
It sets at the connection point of the carbon fiber girder and cantilever carrying floor.
Preferably, the outside of the fuselage skin below the carbon fiber girder is arranged in the undercarriage, and by described
Fall the stress that frame carrying floor transmits the undercarriage.
Preferably, a fuel tank braced frame is respectively arranged with above two undercarriage carrying floors.
Preferably, the upper end of described two fuel tank braced frames is respectively connected with the carrying stretched out to the outside of the fuselage
Arm, bearing diagonal arm is provided with below the load bearing arm, and the lower end of the bearing diagonal arm is arranged in two end carrier ribs
At plate and the carbon fiber girder link position.
The fuselage bearing structure of the application can be by the full carbon fuselage support of full symmetrical configuration, and passes through more low clearance
Web structure obtains enough torsional properties and intensity, while can reject existing metal component, significantly mitigation construction weight.
And lower fuselage height can be obtained, windage is reduced, covering area is reduced, there is excellent weight loss effect.
Detailed description of the invention
Following drawings are only intended to schematically illustrate and explain the present invention, does not limit the model of the utility model
It encloses.Wherein,
The structural schematic diagram of the unmanned plane of a specific embodiment according to the application is shown in Fig. 1；
Structural schematic diagram after the part-structure removal of unmanned plane shown in Fig. 1 that Fig. 2 is shown；
The fuselage interior structural schematic diagram of unmanned plane is shown in Fig. 3；
The housing construction schematic diagram of unmanned plane is shown in Fig. 4；
The fuselage bearing structure schematic diagram on the basis of housing construction shown in Fig. 4 is shown in Fig. 5；
Fig. 6 is the decomposition perspective view of fuselage bearing structure shown in Fig. 5.
Specific embodiment
For a clearer understanding of the technical features, objectives and effects of the utility model, now compareing Detailed description of the invention
Specific embodiment of the present utility model.Wherein, identical component uses identical label.
As described in background, the utility model is directed to the deficiency of the load configuration structure of the unmanned plane of the prior art,
A kind of improvement structure is proposed, so that the unmanned plane of the prior art has a higher structural strength, torsional property, while can be with
Lighter construction weight is obtained, and shape is more succinct, can further decrease outer form drag.
Specifically, the unmanned aerial vehicle body bearing structure of the utility model is the load configuration knot in 201711089304.X
The further improvement proposed on the basis of structure, text of the statement quote the prior art, and those skilled in the art can be based on
The prior art disclosure understands the other structures in relation to unmanned plane.As shown in Figs. 1-2, wherein basis is shown in Fig. 1
The schematic perspective view of the unmanned plane of one specific embodiment of the utility model；The portion of unmanned plane shown in Fig. 1 that Fig. 2 is shown
Structural schematic diagram after separation structure removal.
Same as the prior art referring to Fig. 1-2, the unmanned plane of the application equally includes 2, four fuselage 1, undercarriage cantilevers
3 and four rotors 5, fuselage 1 connects four cantilevers 3, and each cantilever 3 is supported by the rotor 5 of a same diameter.Fuselage 1
For the strip of bilateral symmetry, fuselage 1 has a longitudinal asymmetric axis 6, and fuselage 1 is generally elongated to be parallel to institute
State the setting of the axis of symmetry 6.The head and tail of unmanned plane are each provided with two and are symmetrical with the rotor 5 that the axis of symmetry 6 is arranged.
The load such as photoelectric nacelle 7 and arm discharge cylinder 8 are provided with below fuselage 1.The shuttle shape structure of the substantially strip of fuselage 1, machine
The width constriction of head and tail, middle part width maximum is convenient for setting engine 99.The front end of fuselage 1 be provided with can carry photoelectricity hang
The gondola hanging structure in cabin 7, the lower section of fuselage 1 be provided with can carry arm discharge cylinder 8 carry frame.Each rotor 5 surrounds
It is provided with the pod 4 of the identical circular ring shape of a shape.
The specific feature of the fuselage bearing structure of the application is further described referring to Fig. 3-6, wherein Fig. 3 is aobvious
What is shown is the fuselage interior structural schematic diagram according to the unmanned plane of another specific embodiment of the application；Root is shown in Fig. 4
According to the housing construction schematic diagram of the unmanned plane of the specific embodiment of the application；Housing construction base shown in Fig. 4 is shown in Fig. 5
Fuselage bearing structure schematic diagram on plinth；Fig. 6 is the decomposition perspective view of fuselage bearing structure shown in Fig. 5.
As schemed, just it has been observed that the unmanned plane of the application includes fuselage 1, undercarriage 2 and the fuselage 1 for being mounted on unmanned plane
Internal engine 99, fuselage 1 have a longitudinal asymmetric axis 6, and the head and tail of unmanned plane are each provided with two symmetrically
In the cantilever 3 that the axis of symmetry 6 is arranged, each cantilever 3 is supported by a rotor 5.
In diagram specific embodiment, the unmanned aerial vehicle body bearing structure of the application includes the fuselage of a full symmetrical configuration
Bracket 20, fuselage support 20 have the lateral symmetry axis 10 for being transversely to the machine direction the axis of symmetry 6.Also that is, the fuselage branch of the application
Frame 20 is symmetrical relative to longitudinal asymmetric axis 6, is also symmetrical relative to lateral symmetry axis 10.Such knot
The benefit of structure setting is it will be apparent that the fuselage support 20 being completed can be carried out regardless of front-rear direction using can be with
As shown in Figure 5 it is left front it is right after carry out using may be reversed, installation pressure can be mitigated significantly, improve installation effectiveness.
Further, fuselage support 20 include two be symmetrical with longitudinal asymmetric axis 6 setting carbon fiber girders 201, two
A engine bearing floor 202 for being symmetrical with lateral symmetry axis 10 and being arranged, two are symmetrical with what lateral symmetry axis 10 was arranged
Undercarriage carries floor 203, and two cantilever carrying floors 204 for being symmetrical with the lateral symmetry setting of axis 10 and two are symmetrical with
The end that lateral symmetry axis 10 is arranged carries floor 205；Engine bearing floor 202, undercarriage carry floor 203, cantilever
Carry floor 204 and end carry floor 205 from the symmetrical centre of fuselage support 20 along longitudinal direction the axis of symmetry 6 two sides successively
Arrangement.In the present embodiment, fuselage support 20 is the full carbon structure component of full symmetrical configuration, relative to existing technologies, carbon fiber
Dimension girder 201 and each floor 202,203,204,205 are all made of carbon fibre composite and are made, lightweight construction, loss of weight effect
Fruit is obvious.The prior art only has rod-like structure component using carbon fibre composite, and each frame structure is due to antitorque needs, no
Obtaining does not use metal to be made, and construction weight is larger.In a specific embodiment, in order to improve torsional property, the carbon of the application
The cross section of fiber girder 201 be it is I-shaped, each floor 202,203,204,205 also uses box-like structure, can be significantly
The moment of inertia for enhancing fuselage support 20 improves the torsional property of structure, while the thin-wall construction weight of full carbon is lighter, and intensity is more
Greatly.
In a preferred embodiment, the cross section of carbon fiber girder 201 from the symmetrical centre of fuselage support 20 along longitudinal direction
The two sides of the axis of symmetry 6 are gradually reduced, and more balanced strength structure can be obtained with this, can further be obtained more
Excellent weight loss effect, and keep design strength.
The above-mentioned fuselage bearing structure of the application passes through the full carbon fuselage support of full symmetrical configuration, can pass through more low clearance
Web structure obtain enough torsional properties and intensity, while existing metal component can be rejected, significantly mitigation structure weight
Amount.The web structure of more low clearance can obtain lower fuselage height, reduce windage, reduce covering area, have excellent
Weight loss effect.In addition, various parts, can be set to the top of fuselage support, be easily installed by the fuselage support of more low clearance
Maintenance.
Further, as shown, engine bearing floor 202, undercarriage carrying floor 203, cantilever carry floor 204
And the end of end carrying floor 205 is provided with the reinforcement support plate 206 being fixedly connected with carbon fiber girder 201.It is each to add
Strong support plate 206 is the box part of full carbon structure, comparable torsional property can be kept by thin-wall construction, and without load
The heart increases excessive construction weight.
In addition, in a specific embodiment, two engine bearing floors 202 are connect with two carbon fiber girders 201
Four points be respectively arranged with support engine 99 four foot props 991.Namely for entire airframe structure, engine
99 be most heavy single component, and engine 99 is preferably arranged in the center of fuselage support 20, and is carbon fiber girder
The maximum position in 201 cross section, and also further foot prop 991 is arranged in engine bearing floor 202 and two carbon fibers
Four points that girder 201 connects are tieed up, to obtain bigger support strength.
In another specific embodiment of the application, the installation of four foot props 991 is located on two carbon fiber girders 201
The carry frame 81 of carry arm discharge cylinder 8 is provided with below point.Due to the weight such as rocket projectile of carry in arm discharge cylinder 8
It is very big, therefore position identical with the support point of engine 99 is arranged in carry frame 81, it can use same place position and set
It sets and reinforces support plate 206, avoid that reinforcement structure wasting space is respectively set in more multiposition and increase weight.
In another specific embodiment of the application, cantilever 3 is fixedly connected on the pole bracket on carbon fiber girder 201
On 31, pole bracket 31 is arranged at the connection point of carbon fiber girder 201 and cantilever carrying floor 204.
In another specific embodiment of the application, the fuselage skin below carbon fiber girder 201 is arranged in undercarriage 2
Outside, and by undercarriage carrying floor 203 transmit undercarriage 2 stress.
In addition, also with the reinforcement structure of two undercarriage carrying floors 203 floor 203 can be carried in undercarriage
Top be respectively arranged with a fuel tank braced frame 207, to support the fuel tank of two weight balancings.
In addition, just it has been observed that two ends carry due to the full symmetrical configuration that the fuselage support 20 of the application uses
Floor 205 can arbitrarily be set as the bearing structure of head or tail position, can install fuselage load on fuselage support 20
When, regardless of front-rear direction, improve the convenience of operation.
Further, the upper end of two fuel tank braced frames 207 is respectively connected with the load bearing arm stretched out to the outside of fuselage 1
208, the lower section of load bearing arm 208 is provided with bearing diagonal arm 209, and the lower end setting of bearing diagonal arm 209 carries floor two ends
205 with 201 link position of carbon fiber girder at, as shown in the figure.
In conclusion the fuselage bearing structure of the application can be by the full carbon fuselage support of full symmetrical configuration, and pass through
The web structure of more low clearance obtains enough torsional properties and intensity, while can reject existing metal component, subtracts significantly
Light construction weight.And lower fuselage height can be obtained, windage is reduced, covering area is reduced, there is excellent weight loss effect.
The above descriptions are merely exemplary embodiments of the present utility model, the model being not intended to limit the utility model
It encloses.Any those skilled in the art, under the premise of not departing from the conceptions and principles of the utility model made equivalent variations,
Modification and combination, should belong to the range of the utility model protection.
Claims (9)
1. a kind of unmanned aerial vehicle body bearing structure, the fuselage (1) of the unmanned plane has a longitudinal asymmetric axis (6), described
The head and tail of unmanned plane are each provided with two cantilevers (3) for being symmetrical with the longitudinal asymmetric axis (6) arrangement, and feature exists
In: the unmanned aerial vehicle body bearing structure includes the fuselage support (20) of a full symmetrical configuration, fuselage support (20) tool
There is the lateral symmetry axis (10) perpendicular to the longitudinal asymmetric axis (6)；The fuselage support (20) includes two and is symmetrical with
The carbon fiber girder (201) of longitudinal asymmetric axis (6) setting, two are symmetrical with lateral symmetry axis (10) setting
Engine bearing floor (202), two are symmetrical with undercarriage carrying floor (203) of lateral symmetry axis (10) setting,
It is right that two cantilevers carryings floor (204) for being symmetrical with the lateral symmetry axis (10) setting and two are symmetrical with the transverse direction
The end of axis (10) setting is claimed to carry floor (205)；The engine bearing floor (202), undercarriage carry floor
(203), cantilever carrying floor (204) and end carrying floor (205) are from the symmetrical centre of the fuselage support (20) along institute
The two sides for stating longitudinal asymmetric axis (6) are arranged successively.
2. unmanned aerial vehicle body bearing structure as described in claim 1, which is characterized in that the carbon fiber girder (201) it is transversal
Face be it is I-shaped, the cross section of the carbon fiber girder (201) is from the symmetrical centre of the fuselage support (20) along the longitudinal direction
The two sides of the axis of symmetry (6) are gradually reduced.
3. unmanned aerial vehicle body bearing structure as claimed in claim 2, which is characterized in that the engine bearing floor (202) is risen
The end for falling frame carrying floor (203), cantilever carrying floor (204) and end carrying floor (205) is provided with and the carbon
The reinforcement support plate (206) that fiber girder (201) is fixedly connected.
4. unmanned aerial vehicle body bearing structure as claimed in claim 3, which is characterized in that two engine bearing floors
(202) four points connecting with two carbon fiber girders (201) are respectively arranged with the engine for supporting the unmanned plane
(99) four foot props (991).
5. unmanned aerial vehicle body bearing structure as claimed in claim 4, which is characterized in that on two carbon fiber girders (201)
The carry frame (81) of carry arm discharge cylinder (8) is provided with below the installation point of four foot props (991).
6. unmanned aerial vehicle body bearing structure as claimed in claim 5, which is characterized in that the cantilever (3) is fixedly connected on described
On pole bracket (31) on carbon fiber girder (201), the pole bracket (31) setting the carbon fiber girder (201) with
At the connection point of cantilever carrying floor (204).
7. unmanned aerial vehicle body bearing structure as claimed in claim 6, which is characterized in that the undercarriage (2) is arranged in the carbon
The outside of fuselage skin below fiber girder (201), and the undercarriage is transmitted by undercarriage carrying floor (203)
(2) stress.
8. unmanned aerial vehicle body bearing structure as claimed in claim 7, which is characterized in that two undercarriages carry floor
(203) top is respectively arranged with a fuel tank braced frame (207).
9. unmanned aerial vehicle body bearing structure as claimed in claim 8, which is characterized in that described two fuel tank braced frames (207)
Upper end be respectively connected with to the outside of the fuselage (1) stretch out load bearing arm (208), the load bearing arm (208) lower section setting
Have bearing diagonal arm (209), the setting of the lower end of the bearing diagonal arm (209) two ends carryings floor (205) with it is described
At carbon fiber girder (201) link position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822181288.3U CN209258372U (en) | 2018-12-24 | 2018-12-24 | A kind of unmanned aerial vehicle body bearing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822181288.3U CN209258372U (en) | 2018-12-24 | 2018-12-24 | A kind of unmanned aerial vehicle body bearing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209258372U true CN209258372U (en) | 2019-08-16 |
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ID=67561253
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822181288.3U Active CN209258372U (en) | 2018-12-24 | 2018-12-24 | A kind of unmanned aerial vehicle body bearing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209258372U (en) |
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2018
- 2018-12-24 CN CN201822181288.3U patent/CN209258372U/en active Active
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