CN107021204A - A kind of multi-rotor unmanned aerial vehicle frame based on contignation - Google Patents
A kind of multi-rotor unmanned aerial vehicle frame based on contignation Download PDFInfo
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- CN107021204A CN107021204A CN201710374162.5A CN201710374162A CN107021204A CN 107021204 A CN107021204 A CN 107021204A CN 201710374162 A CN201710374162 A CN 201710374162A CN 107021204 A CN107021204 A CN 107021204A
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- China
- Prior art keywords
- fuselage
- crossbeam
- horn
- supporting plate
- foothold
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/064—Stringers; Longerons
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- 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
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
Abstract
The invention belongs to unmanned air vehicle technique field, more particularly to a kind of multi-rotor unmanned aerial vehicle frame based on contignation, its fuselage and supporting plate are integrally formed structure, and fuselage has higher intensity and security；Support frame based on contignation can offset the deformation torque of the part longitudinal direction of fuselage, prevent frame from occurring obvious deformation；Above-mentioned fuselage and supporting plate constitute the frame based on contignation, the intensity of frame is higher, simultaneously, frame using the combination of crossbeam and sheet material due to being built, crossbeam and sheet material space-consuming are few, can carry out regular partition to the space in frame, and more spaces for being used to carry load can be provided for frame, and the easy perforate of sheet material, sheet material opens up the equipment that can be carried after mounting hole by frame and provides more tie points.To sum up, the multi-rotor unmanned aerial vehicle frame of the invention based on contignation has the advantages that Stability Analysis of Structures, safe, lift-launch amount are big relative to the unmanned plane frame of prior art.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, more particularly to a kind of multi-rotor unmanned aerial vehicle frame based on contignation.
Background technology
Traditional unmanned plane frame is largely to be fitted together by parts such as fuselage, horn and support frames with screw, this
The loosening of screw occurs in class connected mode under unmanned plane during flying jitter conditions, so that the unstable of frame is caused, if inspection
The disintegration for being likely to result in fuselage not in time is looked into, or even is had an accident；Also, many part combination forms are very numerous in fit on
It is trivial, inconvenience is dismantled repeatedly.In addition, the frame design existing defects of traditional unmanned plane, do not reduce or offset setting for stress concentration
Meter, causes the discontinuity of frame, such as stress is easily concentrated at screw connection, causes screw connection to loosen, Huo Zheji
In junction between part and part, cause frame to be broken in stress raiser.Furthermore, traditional frame design can not have
Enough spaces and method are gone to carry various loads.
Accordingly, it would be desirable to which a kind of new design evades the shortcoming of the above.
The content of the invention
(1) technical problem to be solved
It is an object of the invention to provide a kind of Stability Analysis of Structures, the safe multi-rotor unmanned aerial vehicle based on contignation
Frame.
(2) technical scheme
In order to achieve the above object, the invention provides a kind of multi-rotor unmanned aerial vehicle frame based on contignation, it is wrapped
Include the fuselage of platy structure and be arranged on the support frame of the lower section of the fuselage, support frame as described above includes the vertical of multiple platy structures
Pin and the crossbeam being connected between described keep a foothold, to constitute the support frame based on contignation；The described of support frame as described above stands
Pin is connected with the fuselage, to constitute the frame based on contignation.
Further, the fuselage includes fuselage body and from the outwardly directed multiple horns of the fuselage body, described
Central point Central Symmetry of multiple horns on the fuselage body, the fuselage body is formed in one with the multiple horn
Platy structure；Support frame as described above includes connected multiple supporting plates, and each supporting plate is each perpendicular to the plate of the fuselage
Face, each supporting plate includes the crossbeam and kept a foothold positioned at described in two of the crossbeam two ends, the crossbeam and position
The contignation being formed in one in being kept a foothold described in two of its two ends.
Further, the fuselage includes fuselage body and from outwardly directed four horns of the fuselage body, described
Central point Central Symmetry of four horns on the fuselage body, the fuselage body is formed in one with four horns
Platy structure；Support frame as described above includes two supports arranged in a crossed manner perpendicular to the lower surface of the fuselage and mutually in X-shaped
Plate, each supporting plate includes crossbeam and kept a foothold positioned at two of the crossbeam two ends, the crossbeam with positioned at its two ends
Two described in keep a foothold the contignation being formed in one, the upper end kept a foothold is connection end, and the lower end kept a foothold is station
Vertical end；The middle part of the crossbeam of described two supporting plates is connected with each other, four of support frame as described above keep a foothold respectively with the fuselage
Four horn correspondences, four connection ends of support frame as described above are connected with four horns respectively.
Further, the horn is provided with the mounting groove of its thickness direction of insertion, the connection end bag kept a foothold
A connecting portion is included, the connecting portion passes through the mounting groove from the bottom up, and the connecting portion stretches out in the upper table of the horn
The part in face is provided with the dismountable card of clamping one in neck, the neck, and the horn is sandwiched in the connection end and institute
State between card, described keep a foothold is relatively fixed with the horn.
Further, arm is provided with the mounting groove of at least two insertion its thickness direction, is kept a foothold described in each
The connection end is provided with connecting portion described at least two, and each described connecting portion stretches out in the portion of the upper surface of the horn
Divide and be provided with the neck and dismountable card.
Further, card fixed structure is provided between the card and the horn, makes the card and the machine
Arm is relatively fixed.
Further, described two supporting plates are respectively the first supporting plate and the second supporting plate, first supporting plate
The centre of crossbeam is provided with the first link slot up extended from lower edge, and the centre of the crossbeam of second supporting plate is provided with
The second link slot down extended from top edge, first link slot and second link slot are in the crossbeam above-below direction
Width on locally extend, the crossbeam of first supporting plate sticks into downwards described from the top of second supporting plate
Two link slots, and the crossbeam of second supporting plate sticks into first link slot, makes the connection end of support frame as described above equal
The standing end being generally aligned in the same plane with support frame as described above is respectively positioned on same plane.
Further, the junction of the horn and the fuselage body uses arc transition.
Further, the supporting plate is provided with least one through hole of its thickness direction of insertion, and/or the fuselage sheet
Body is provided with least one through hole of its thickness direction of insertion, and/or the horn is provided with insertion its thickness direction at least
One through hole.
Further, in addition to the fixing device for being fixedly mounted on various kinds of equipment on unmanned plane, the fuselage is set
The mounting hole of its thickness direction of insertion is equipped with, the fixing device is provided with fixing device mounting hole, is arranged through the installation
The retaining element of hole and the fixing device mounting hole makes the fixing device be relatively fixed with the fuselage
Further, the material of the fuselage is one kind in carbon fiber board, aluminium alloy plate, acrylic board, plastic plate, institute
The material for stating support frame is one kind in carbon fiber board, aluminium alloy plate, acrylic board, plastic plate, metallic plate.
(3) beneficial effect
Compared with prior art, the invention has the advantages that：The present invention many rotors based on contignation without
Man-machine frame, its fuselage and supporting plate are integrally formed structure, and the fuselage relative to the unmanned plane of prior art uses spiral shell
Nail is attached, and tie point is not present in integrally formed fuselage between fuselage body and horn, fuselage body and horn it
Between will not occur connection loosen so that fuselage have higher intensity and security；Support frame based on contignation can be offset
The deformation torque of the part longitudinal direction of fuselage, prevents frame from occurring obvious deformation；Above-mentioned fuselage and supporting plate, which are constituted, is based on beam
The frame of hardened structure, the intensity of frame is higher, meanwhile, frame due to being built using the combination of crossbeam and sheet material, crossbeam with
Sheet material space-consuming is few, can carry out regular partition to the space in frame, can provide more for carrying load for frame
Space, and the easy perforate of sheet material, sheet material opens up the equipment that can be carried after mounting hole by frame and provides more connections
Point.To sum up, the multi-rotor unmanned aerial vehicle frame of the invention based on contignation has relative to the unmanned plane frame of prior art
The big advantage of Stability Analysis of Structures, safe, lift-launch amount.
Brief description of the drawings
Fig. 1 is structural representation when multi-rotor unmanned aerial vehicle frame of the invention is provided with propeller；
Fig. 2 is the structural representation of fuselage；
Fig. 3 is the structural representation of support frame；
Fig. 4 is the structural representation of the first supporting plate；
Fig. 5 is the structural representation of the second supporting plate；
Fig. 6 is the structural representation of the junction of supporting plate and horn；
Fig. 7 is the structural representation of autopilot fixing device；
Fig. 8 is the structural representation of power source fixing device.
【Description of reference numerals】
1- fuselages；11- fuselage bodies；12- horns；121- mounting grooves；14- propellers；The mounting holes of 15- first；16- second
Mounting hole；
2- support frames；21- supporting plates；The supporting plates of 211- first；The supporting plates of 212- second；22- crossbeams；221- first is connected
Groove；The link slots of 222- second；23- keeps a foothold, 231- connection ends；232- connecting portions；233- necks；234- standings end；24- cards are determined
Position hole；
3- cards, 31- grooves；
4- autopilot fixing devices；41- autopilot fixing device mounting holes；
5- power source fixing devices；51- power source fixing device mounting holes.
Embodiment
Describe illustrative embodiments, feature and the aspect of the present invention in detail below with reference to accompanying drawing.Identical in accompanying drawing
Reference represents the same or analogous element of function.Although the various aspects of embodiment are shown in the drawings, remove
Non-specifically is pointed out, it is not necessary to accompanying drawing drawn to scale.
Directionality used in the present invention indicates that (as above, inferior) is for for explaining under a certain particular pose (such as
Shown in Fig. 1) relative position relation, motion conditions between each part etc., if the particular pose changes, the direction
Property indicate also accordingly change therewith.
The invention provides a kind of multi-rotor unmanned aerial vehicle frame based on contignation, as shown in Figures 1 to 8, it includes
The fuselage 1 of platy structure and the plate face perpendicular to fuselage 1, be arranged on fuselage 1 lower section support frame 2.
Fuselage 1 includes fuselage body 11 and from 11 outwardly directed four horns 12 of fuselage body, and fuselage body 11 is plate
Shape structure, forms the load support plane of spaciousness in its upper surface, while forming the carry plane of spaciousness in its lower surface.Each
Horn 12 is the platy structure extended in the same plane with fuselage body 11, fuselage body 11 and four one of horns 12 into
Type.Propeller 14 is arranged on the end of each horn 12 when assembling unmanned plane.Fuselage 1 can use carbon fiber board, aluminium alloy plate, Asia
Light weights such as gram force plate, plastic plate, the metallic plate and sheet material of high intensity is made, it is preferred to use carbon fiber board.
Support frame 2 includes two supporting plates 21, and supporting plate 21 is contignation, and two supporting plates 21 are intersected in X-shaped to be set
Put.It is pointed out that the angle between the supporting plate 21 of X-type cross is chosen as vertical, i.e., cross intersection, similarly hereinafter.Together
Sample, supporting plate 21 can be made of the sheet material of the high intensity such as carbon fiber board, aluminium alloy plate, acrylic board, plastic plate, it is preferred to use
Carbon fiber board.
Each supporting plate 21 includes two keep a foothold 23, crossbeam 22 of crossbeam 22 and the platy structure positioned at the two ends of crossbeam 22
With two 23 composition contignations of keeping a foothold.It is in X-type cross shape, support frame that the middle part of the crossbeam 22 of two supporting plates 21, which is connected with each other,
Four of 2,23 four horns 12 respectively with fuselage 1 of keeping a foothold are corresponding, after assembling, plane where keeping a foothold and corresponding machine
Plane where arm is mutually perpendicular to.Keep a foothold 23 upper end be connection end 231, keep a foothold 23 lower end be standing end 234.Support frame 2
Four connection ends 231 are connected with four horns 12 respectively, and four standing ends 234 are suitable to smoothly by a planar support, for example
Ground.After support frame 2 based on contignation is connected with fuselage 1, the machine in four pin midstances based on contignation is constituted
Frame.
Crossbeam 22 and keep a foothold 23 connecting portion be preferably located in middle part so that when being installed in place between crossbeam 22 and fuselage body
Every a segment distance, the installation space for providing abundance for load, it is to avoid interference, while being also offer buckling preventing support of keeping a foothold.It is horizontal
Beam 22 has a width in the direction perpendicular to fuselage body, forms attachment structure each other in the direction of the width.
Situation when fuselage 1 is provided with four horns 12, in actual applications, fuselage are only gived in the present embodiment
1 horn 12 can also be 6, the even numbers such as 8, while the quantity of the supporting plate 21 of support frame 2 also should accordingly change
Become 3,4 etc.；Above-mentioned replacement is each fallen within protection scope of the present invention.
Based on said structure, the multi-rotor unmanned aerial vehicle frame of the invention based on contignation, its fuselage and supporting plate are equal
The structure being formed in one, the fuselage relative to the unmanned plane of prior art is attached using screw, integrally formed fuselage
Tie point is not present between fuselage body and horn, connection will not occur between fuselage body and horn and loosen so that machine
Body has higher intensity and security；Support frame based on contignation can offset the deformation torque of the part longitudinal direction of fuselage,
Prevent frame from occurring obvious deformation；Above-mentioned fuselage and supporting plate constitute the frame based on contignation, the intensity of frame compared with
Height, meanwhile, frame using the combination of crossbeam and sheet material due to being built, and crossbeam and sheet material space-consuming are few, can be in frame
Space carry out regular partition, can be provided for frame more is used for the spaces that carrying is loaded, and the easy perforate of sheet material, plate
Material opens up the equipment that can be carried after mounting hole by frame and provides more tie points.To sum up, it is of the invention based on beam slab knot
The multi-rotor unmanned aerial vehicle frame of structure has Stability Analysis of Structures, safe, lift-launch amount big relative to the unmanned plane frame of prior art
Advantage.
In the present embodiment, as shown in Fig. 2, Fig. 3 and Fig. 6, horn 12 is provided with the mounting groove of its thickness direction of insertion
121,23 connection end 231 of keeping a foothold includes connecting portion 232, and connecting portion 232 passes through mounting groove 121 from the bottom up, and connecting portion 232 stretches
Part for the upper surface of horn 12 is provided with the dismountable card 3 of clamping one in neck 233, neck 233, and horn 12 is pressed from both sides
Between connection end 231 and card 3, make to keep a foothold 23 is relatively fixed with horn 12.Can be support frame 2 by above-mentioned attachment structure
Installed in the lower section of fuselage 1, this kind of attachment structure assembling is simple, and connecting portion 232 is integrally formed with supporting plate 21, be also ensure that
The stability of connection.It is of course also possible to use other modes are such as spirally connected, welded, being bonded mode support frame 2 is connected with fuselage 1
It is connected together.
Preferably, as shown in Figures 3 to 6, each horn 12 is provided with the mounting groove of two insertion its thickness directions
121, each 23 connection end 231 of keeping a foothold is provided with two connecting portions 232, and each connecting portion 232 stretches out in the upper of horn 12
The part on surface is provided with neck 233 and is connected with card 3.So, i.e., there are four between one piece supporting plate 21 and fuselage 1
Tie point, and because supporting plate 21 is rigid structure, fuselage 1 is also rigid structure, this four points of connection causes whole machine jointly
Frame is more stable.Certainly, the quantity of the mounting groove 121 of each horn 12 can also be three or more, the quantity of connecting portion 232 with
The quantity correspondence of mounting groove 121.
Preferably, the fixed structure of card 3 is provided between card 3 and horn 12, card 3 is relatively fixed with horn 12.
Preferably, as shown in fig. 6, the both sides of card 3 set fluted 31, and set on horn 12 with the corresponding position of groove 31
There are two card positioning holes 24, band can be used to pass through two card positioning holes 24 and groove 31, card 3 is tightened in horn
On 12.It is of course also possible to use other modes are such as spirally connected, welded, being bonded mode card 3 is fixed on horn 12, it is above-mentioned to replace
Change and each fall within protection scope of the present invention.
In the present embodiment, as shown in Figures 3 to 5, two supporting plates are respectively the first supporting plate 211 and the second support
Plate 212.As shown in figure 4, the centre of the crossbeam of the first supporting plate 211 is provided with the first link slot up extended from lower edge
221, as shown in figure 5, the centre of the crossbeam of the second supporting plate 212 is provided with the second link slot 222 down extended from top edge,
First link slot 221 and the second link slot 222 locally extend on the width of crossbeam above-below direction, the first supporting plate 211
Crossbeam stick into the second link slot 222 downwards from the top of the second supporting plate 212, and the crossbeam of the second supporting plate 212 sticks into
One link slot 221, said structure makes that the connection end 231 of support frame 2 is respectively positioned on same plane and the standing end 234 of support frame 2 is equal
It is generally aligned in the same plane, while the support frame 2 of said structure composition is symmetrical structure, Stability Analysis of Structures is effectively reduced stress concentration
Situation occur.Certainly, when the material of the first supporting plate 211 and the second supporting plate 212 is metallic plate, it can also use as welded
Mode the first supporting plate 211 and the second supporting plate 212 are linked together；When the first supporting plate 211 and the second supporting plate 212
Material be plastic plate when, can also use as bonding the first supporting plate 211 and the second supporting plate 212 were connected to one at that time
Rise；Similar replacement is each fallen within protection scope of the present invention.
In the present embodiment, as shown in Fig. 2 the junction of horn 12 and fuselage body 11 uses arc transition, can have
Effect reduces the stress concentration on the horizontal direction of fuselage 1.
In the present embodiment, as shown in Figures 1 to 6, supporting plate 21 is provided with least one of insertion its thickness direction
Through hole, and/or fuselage body 11 are provided with least one through hole of its thickness direction of insertion, and/or horn 12 is provided with insertion
At least one through hole of its thickness direction.When needed, can on supporting plate 21, fuselage body 11 or horn 12 opened hole,
The presence of these through holes can mitigate the weight of whole frame, while when these through holes can also be as follow-up UAV flight's load
Tie point；Certainly, these through holes can not also be opened on supporting plate 21, fuselage body 11 and horn 12.
In the present embodiment, as shown in Figure 1, Figure 2 and Figure 7, unmanned plane frame also includes autopilot fixing device 4, machine
Body 1 is provided with the first mounting hole 15 of its thickness direction of insertion, and autopilot fixing device 4 is provided with the installation of autopilot fixing device
Hole 41, being arranged through the band of the first mounting hole 15 and autopilot fixing device mounting hole 41 makes autopilot fixing device 4 and machine
Body 1 is relatively fixed.It is of course also possible to use other modes are such as spirally connected, welded, being bonded mode autopilot fixing device 4 is consolidated
It is scheduled on fuselage 1.
In the present embodiment, as shown in Figure 1, Figure 2 with shown in Fig. 8, unmanned plane frame also includes power source fixing device 5, fuselage 1
The second mounting hole 16 of its thickness direction of insertion is provided with, power source fixing device 5 is provided with power source fixing device mounting hole 51, if
The band put through the second mounting hole 16 and power source fixing device mounting hole 51 makes power source fixing device 5 be relatively fixed with fuselage 1.
It is of course also possible to use other modes are such as spirally connected, welded, being bonded mode power source fixing device 5 is fixed on fuselage 1.Certainly,
Also settable other fixing devices, such as camera fixing device, laboratory apparatus fixing device in unmanned plane frame, these are consolidated
Determining device can be also fixed using above-mentioned fixing means.
In the case where not conflicting, the feature in above-mentioned embodiment and embodiment can be mutually combined.
Finally it should be noted that：Above-described each embodiment is merely to illustrate technical scheme, rather than right
It is limited；Although the present invention is described in detail with reference to aforementioned embodiments, one of ordinary skill in the art should
Understand：It can still modify to the technical scheme described in aforementioned embodiments, or to which part or whole skills
Art feature carries out equivalent substitution；And these modifications or substitutions, the essence of appropriate technical solution is departed from each implementation of the present invention
The scope of mode technical scheme.
Claims (11)
1. a kind of multi-rotor unmanned aerial vehicle frame based on contignation, it is characterised in that：Fuselage and setting including platy structure
Support frame in the lower section of the fuselage,
Support frame as described above includes the crossbeam kept a foothold and be connected between described keep a foothold of multiple platy structures, and beam is based on to constitute
The support frame of hardened structure；
Described keep a foothold of support frame as described above is connected with the fuselage, to constitute the frame based on contignation.
2. multi-rotor unmanned aerial vehicle frame according to claim 1, it is characterised in that：The fuselage include fuselage body and from
The outwardly directed multiple horns of fuselage body, central point Central Symmetry of the multiple horn on the fuselage body,
The platy structure that the fuselage body is formed in one with the multiple horn；
Support frame as described above includes connected multiple supporting plates, and each supporting plate is each perpendicular to the plate face of the fuselage, each
The supporting plate includes the crossbeam and kept a foothold positioned at described in two of the crossbeam two ends, and the crossbeam is with being located at its two ends
Two described in keep a foothold the contignation being formed in one.
3. multi-rotor unmanned aerial vehicle frame according to claim 1, it is characterised in that：The fuselage include fuselage body and from
Outwardly directed four horns of fuselage body, central point Central Symmetry of four horns on the fuselage body,
The platy structure that the fuselage body is formed in one with four horns；
Support frame as described above includes two supporting plates arranged in a crossed manner perpendicular to the lower surface of the fuselage and mutually in X-shaped, each
The supporting plate includes crossbeam and kept a foothold positioned at two of the crossbeam two ends, the crossbeam and two institutes positioned at its two ends
The contignation kept a foothold and be formed in one is stated, the upper end kept a foothold is connection end, and the lower end kept a foothold is standing end；
The middle part of the crossbeam of described two supporting plates is connected with each other, four of support frame as described above keep a foothold respectively with the fuselage four
Individual horn correspondence, four connection ends of support frame as described above are connected with four horns respectively.
4. multi-rotor unmanned aerial vehicle frame according to claim 3, it is characterised in that：The horn is provided with insertion its thickness
The mounting groove in direction, the connection end kept a foothold includes a connecting portion, and the connecting portion passes through the peace from the bottom up
Tankage, the connecting portion stretches out in the part of the upper surface of the horn, and to be provided with clamping one in neck, the neck detachable
Card, the horn is sandwiched between the connection end and the card, described keep a foothold is relatively fixed with the horn.
5. multi-rotor unmanned aerial vehicle frame according to claim 4, it is characterised in that：Each described horn is provided with least
The mounting groove of two insertion its thickness directions, the connection end kept a foothold described in each, which is provided with described at least two, to be connected
Socket part, the part for the upper surface that each described connecting portion stretches out in the horn is provided with the neck and described detachable
Card.
6. multi-rotor unmanned aerial vehicle frame according to claim 4, it is characterised in that：Set between the card and the horn
Card fixed structure is equipped with, the card is relatively fixed with the horn.
7. multi-rotor unmanned aerial vehicle frame according to claim 3, it is characterised in that：Described two supporting plates are respectively first
Supporting plate and the second supporting plate, the centre of the crossbeam of first supporting plate are provided with the first connection up extended from lower edge
Groove, the centre of the crossbeam of second supporting plate is provided with the second link slot down extended from top edge, first connection
Groove and second link slot locally extend on the width of the crossbeam above-below direction, the crossbeam of first supporting plate
Second link slot is sticked into downwards from the top of second supporting plate, and the crossbeam of second supporting plate sticks into described
One link slot, makes that the connection end of support frame as described above is respectively positioned on same plane and the standing end of support frame as described above is respectively positioned on
Same plane.
8. multi-rotor unmanned aerial vehicle frame as claimed in any of claims 2 to 7, it is characterised in that：The horn with
The junction of the fuselage body uses arc transition.
9. multi-rotor unmanned aerial vehicle frame as claimed in any of claims 2 to 7, it is characterised in that：The supporting plate
It is provided with least one through hole of its thickness direction of insertion, and/or the fuselage body is provided with insertion its thickness direction extremely
A few through hole, and/or the horn are provided with least one through hole of its thickness direction of insertion.
10. multi-rotor unmanned aerial vehicle frame as claimed in any of claims 2 to 7, it is characterised in that：Also include being used for
Various kinds of equipment is fixedly mounted on to the fixing device on unmanned plane, the fuselage is provided with the mounting hole of its thickness direction of insertion,
The fixing device is provided with fixing device mounting hole, is arranged through the fixation of the mounting hole and the fixing device mounting hole
Element makes the fixing device be relatively fixed with the fuselage.
11. multi-rotor unmanned aerial vehicle frame as claimed in any of claims 2 to 7, it is characterised in that：The fuselage
Material is one kind in carbon fiber board, aluminium alloy plate, acrylic board, plastic plate, and the material of support frame as described above is carbon fiber board, aluminium
One kind in alloy sheets, acrylic board, plastic plate, metallic plate.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710374162.5A CN107021204A (en) | 2017-05-24 | 2017-05-24 | A kind of multi-rotor unmanned aerial vehicle frame based on contignation |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710374162.5A CN107021204A (en) | 2017-05-24 | 2017-05-24 | A kind of multi-rotor unmanned aerial vehicle frame based on contignation |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107672780A (en) * | 2017-11-08 | 2018-02-09 | 沈阳旋飞航空技术有限公司 | A kind of load configuration structure of the dynamic unmanned plane of oil |
| CN109733590A (en) * | 2019-03-22 | 2019-05-10 | 天津天航智远科技有限公司 | A kind of connection structure between unmanned plane main wing and outer wing |
| 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 |
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| CN116080946B (en) * | 2022-12-19 | 2023-09-29 | 深圳技术大学 | Unmanned aerial vehicle frame and unmanned aerial vehicle |
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