CN206407115U - A kind of many rotor unmanned aircrafts of heavy－duty - Google Patents
A kind of many rotor unmanned aircrafts of heavy－duty Download PDFInfo
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- CN206407115U CN206407115U CN201621244577.8U CN201621244577U CN206407115U CN 206407115 U CN206407115 U CN 206407115U CN 201621244577 U CN201621244577 U CN 201621244577U CN 206407115 U CN206407115 U CN 206407115U
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Abstract
A kind of many rotor unmanned aircrafts of heavy－duty, body cover board is the box structure of regular polygon, and multiple horn connectors are fixed inside the body cover board, and respectively on each angle of body cover board.One end of each horn connecting rod is connected with horn connector, and the other end is provided with motor.Fuselage upper plate and fuselage lower plate lay battery.Effect load single of the present utility model can reach more than 20kg, and the dismounting again with cruising time length, fuselage horn is quick and convenient, and flexibly and easily, the characteristics of environmental suitability is wide.
Description
Technical field
The present invention relates to aircraft field of mechanical structure design, in particular to a kind of six rotations of loading capacity up to 20kg
Wing heavy－duty unmanned vehicle.
Background technology
Unmanned plane application is very wide, has been directed to many-sided field at present, including video display are taken photo by plane, ground mapping, geological exploration, gas
As detection, environment detection, agricultural plant protection etc..As a flying platform, unmanned plane can not only realize the recreational use taken photo by plane,
Distinct device can more importantly be carried and complete particular industry task.Unmanned plane combined with industry will be increasingly closer, including
Effective combination in the field such as mapping, agricultural, electric power, gradually becomes an instrument in solution, plays bigger value.
In commercial Application, it would be desirable to which aircraft loading capacity is big, and the flight time is long, to complete particular job, such as sprinkling agriculture
Medicine, mapping etc..Multi-rotor unmanned aerial vehicle is due to VTOL, without runway, has a smooth flight, the characteristics of spot hover,
Sector application is wider.But prior art is limited by the unit mass energy storage intensity of battery, the flight of long endurance needs many carrying electricity
Pond, the weight of battery in itself greatly limit the lifting capacity of aircraft, seriously limit the sector application of multi-rotor unmanned aerial vehicle.
In the prior art, consumer level UAV system weight is smaller, carries equipment of taking photo by plane, loading capacity is within 2kg；Technical grade
Unmanned plane, loading capacity is typically between 5-15kg.For example, agricultural plant protection class unmanned plane, by taking MG-1 agricultural plant protection machines as an example, it is marked
Quasi- load-carrying is 10kg or so, and the normal hovering time only has 10min under standard load-carrying, and practical application is poor.It is used as important ginseng
Number, loading capacity is small, the flight time is short, and drawbacks described above limits the sector application of unmanned plane.
To solve the above problems, patent CN 203078754U propose a kind of many rotor unmanned helicopters of heavy－duty.Including
The rotor in groups of fuselage, 4 or more than 4, it is characterised in that the rotor drives by motor, and the power supply of motor is by position
Power supply in ground passes through cable transmission.The technical scheme effectively alleviates the weight that unmanned plane carries battery, can be at nobody
Heavier instrument and equipment is placed on machine.But this technical scheme is restricted in practical application, two aspects are mainly manifested in：
One is length restriction of the flying radius by ground cable of unmanned plane, and flying radius is small, and flying height is low；Two be to operating environment
Have higher requirements, it is desirable to ground clear in flight range.
The content of the invention
To overcome the shortcomings of that loading capacity present in prior art is small, the flight time is short, the present invention proposes a kind of big carry
Many rotor unmanned aircrafts of weight.
The present invention includes body cover board, undercarriage, two battery cases, battery, multiple horn connectors, the connections of multiple horns
Bar, multiple motors, multigroup propeller and motor cabinet retaining ring.Wherein, the body cover board is the box structure of regular hexagon, institute
Multiple horn connectors are stated to fix inside the body cover board, and respectively on each angle of body cover board regular polygon.It is described
One end of each horn connecting rod is connected with horn connector, and the other end is cantilever end.Each motor passes through motor cabinet retaining ring
The cantilever end of fixed each horn connecting rod.Each group propeller is separately mounted to the upper surface of each motor.Two battery difference
It is placed in each battery case bearing wall and frame structure positioned at fuselage upper plate upper surface geometric center and fuselage lower plate lower surface geometric center
Undercarriage by undercarriage fixed landing gear connector be arranged on the fuselage lower plate lower surface.Described regular polygon is just
Hexagon or octagon.
The body cover board includes fuselage upper plate, the fuselage lower plate being parallel to each other, and connects the fuselage upper plate and fuselage
The edge dam of lower plate；It is solid between fuselage upper plate lower surface and fuselage lower plate upper surface in the body cover board at geometric center
Surely there is central supported frame.
The horn connector is sub-assembly, including horn joint, axle sleeve and locking nut.Horn joint therein is by two
The individual square supporting plate being parallel to each other and a sleeve composition.On symmetrical two side surfaces of described two supporting plates respectively
There is connecting hole.The geometric center of each supporting plate has the through hole for fixing the sleeve.The external diameter of the sleeve with each
The internal diameter of through hole is identical on frame plate；The internal diameter of the sleeve is identical with the external diameter of axle sleeve.Cylindrical weekly form in the sleeve outer end
Face is flank, and the end face of the sleeve outer end is provided with axial locating slot.
The horn connecting rod is hollow cylindrical carbon pipe, and one end is extend into inside horn connector, by locking nut
Tighten, the other end extend into motor cabinet retaining ring, is tightened by lock screw.
The motor cabinet retaining ring is cylindrical shape.The motor cabinet retaining ring is cut vertically, to facilitate wing connecting rod to hang
The arm end quick insertion retaining ring；There is radially protruding in the axial joint-cutting both sides of the motor cabinet retaining ring external peripheral surface one end
Locking auricle, have concentric connecting hole on the auricle；After the motor cabinet retaining ring is inserted in horn connecting rod one end, pass through spiral shell
Bolt fastens auricle, so that horn connecting rod and motor mechanism be connected.Motor cabinet and motor cabinet retaining ring are integral type structure.
Fuselage upper plate and fuselage lower plate structure size all same in the body cover board, are regular polygon carbon plate.It is polygon
Each angle of shape carries out chamfered, and chamfering edge lengths match with horn joint length.Organic arm connection on the inside of bevel edge
Connecting hole.The fuselage upper plate it is each while edge and fuselage lower plate it is each while edge have respectively for being embedded in edge dam
Neck.Undercarriage mounting hole is distributed with the fuselage lower plate.
The fixture block for protruding the side surface is symmetrically distributed with the side surface on two long sides of edge dam；The side on each long side
There are two fixture blocks on surface, when the fuselage upper plate in the edge dam and body cover board and the cooperation of fuselage lower plate, the fixture block point
It is not embedded in the neck of fuselage upper cover plate and fuselage lower cover.
The profile of the central supported frame is identical with the profile of fuselage upper plate and fuselage lower plate.The central supported frame each
There is the groove for flying control circuit for arranging on the underframe of side.The height of the central supported frame and the height of the edge dam
Degree is identical.There is the screw for being fixedly connected with fuselage upper plate and fuselage lower plate respectively on each angle of the central supported frame.
Horn joint includes two supports and a sleeve.Symmetrical surface in the frame of the square box of described two supports
It is upper to have supporting table respectively；It is interference fits between the sleeve and axle sleeve.In described sleeve one end, end face is provided with axial positioning
Groove.The external peripheral surface for having locating slot one end sleeve is flank.Locking nut is passed through outside axle sleeve, its internal thread and sleeve
Screw thread is matched, and axle sleeve is fixedly connected with horn joint.
The propeller is made with wood materials with the carbon fiber for being wrapped in wooden material surface, is the center pair of integral type
Claim structure, and the symmetrical centre of the propeller is propeller hub；Described propeller hub is groove-like, and the both sides of the groove are propeller oar
Leaf.The length of the propeller is 760mm, wherein propeller hub length 115mm.The pitch of the propeller is 240mm.The oar
The thickness of hub is 3mm.The upper surface of the propeller hub and lower surface are plane.
The thickness of the blade root of the propeller blade is 7mm, and the thickness of blade tip is between 2mm, and blade root and blade tip
Upper surface is that a curve linear is thinned；The tangential of the blade from blade root to blade tip is conic section, the wherein string at blade root
Chord length at a length of 70mm, blade tip is 30mm.It is that conic section connects between 70mm, and propeller hub and blade root that chord length at propeller hub, which is,
Connect.The thickness of the propeller hub is the 8% of the propeller hub chord length；The thickness of blade root is the 10% of the blade root chord length；The thickness of blade tip is
The 6% of the blade tip chord length.
The present invention can effectively solve the problem that traditional unmanned vehicle loading capacity from the real angle of unmanned plane sector application
It is small, the problem of flight time is short.
Have the following advantages that：
(1) loading capacity is big, payload single can reach 20kg and more than.
Optimize aircaft configuration, realize that loading capacity is big.Compared with general unmanned aerial vehicle body structure, the present invention has to be improved at two,
One is to have increased central supported frame newly.The use of central supported frame considerably increases the rigidity of structure of fuselage, particularly when big weight
Load suspension is when body cover board lower plate, and fuselage lower plate deflection is greatly reduced, for the fuselage lower plate of same thickness, center branch
The use of support frame may be such that suspended load amount increases to 20kg by 10kg, but central supported frame almost may be used for whole system weightening
To ignore.If being proof strength requirement, body cover in the case where loading equal load without using central supported frame
Plate will thicken 1 times, and weight increase is more；Two be the optimization design of horn connector.Spiral shell between horn connector and body cover board
Line is connected, it is ensured that fuselage possesses enough rigidity, in favor of hanging heavier load, passes through lock between horn connector and horn
Tight nut connection, the same effect with horn convenient disassembly.
(2) cruising time is long.When payload is 10kg, cruising time 35min, when payload is 20kg, during continuation of the journey
Between can reach 20min, meet most of real needs.
In the design, the advantage for the propeller that blade is used is embodied in structure and the aspect of material two.In structure, propeller
Section at blade root is most thick, is gradually thinned with to displacement at blade tip；Blade thickness is about the 14% of chord length at blade root.Blade tip
Chord length it is smaller, thickness is about the 10% of chord length.Blade tip part is relatively thin, in order to reduce resistance.The linear velocity of blade root part is small,
Inefficiency, the need for this part propeller-blade section should mainly obey holding strength and stiffness.In addition, blade is integrally in distortion
It is plane at arc above and below sheet, propeller hub, it is ensured that the contact strength with motor cabinet；From material, propeller uses composite,
Light and intensity is high.Inside is wooden, keeps the shape of propeller, superficies are carbon fibre materials, can keep propeller
Intensity.
(3) dismounting again of fuselage horn is quick and convenient：By taking six gyroplanes of the present invention as an example, conventionally, need
Lower plate and all bolts of horn joint with demountor are wanted, 8X6=48 is individual altogether, in terms of the progress in 10 seconds of each screw dismounting
Calculate, 8min is needed altogether.The present invention only needs to install once, again during installing/dismounting, only need to unclamp locking nut, and need not appoint
What instrument, free-hand to complete, 6 locking nuts were calculated by each 5 seconds, only needed 0.5min.The time effectively is saved, and not
Any instrument is needed to complete.
(4) operating environment influence is small.Cable transmission of electricity is high to environmental requirement, and the present invention uses conventional on-board battery system, tool
Have flexible, the characteristics of environmental suitability is wide.
Brief description of the drawings
Fig. 1 is the dimensional structure diagram of the present invention；
Fig. 2 is the cooperation schematic diagram of body cover board, center bulkhead and horn connector；
Fig. 3 is the cooperation schematic diagram of body cover board, horn connector and horn connecting rod；
Fig. 4 is the cooperation schematic diagram of horn connecting rod, motor and propeller；
Fig. 5 is the cooperation schematic diagram of undercarriage, battery case and edge dam；
Fig. 6 is body cover board structural representation；
Fig. 7 is edge dam structural representation；
Fig. 8 is central supported mount structure schematic diagram.
Fig. 9 is horn connecting-piece structure schematic diagram, wherein, Fig. 9 a are axonometric drawings, and Fig. 9 b are the structural representations of axle sleeve, figure
9c is the structural representation of locking nut；
Figure 10 is horn connecting rod structural representation；
Figure 11 is landing gear structure schematic diagram；
Figure 12 is undercarriage connecting-piece structure schematic diagram；
Figure 13 is motor cabinet and motor cabinet retaining ring structural representation.
Figure 14 is along any pair of propeller schematic cross-sectional view；
Figure 15 is along any single propeller schematic cross-sectional view；
Figure 16 is horn bindiny mechanism sectional view；
Figure 17 is propeller arrangement schematic diagram, and wherein Figure 17 a are front view, and Figure 17 b are top view.In figure：
1. body cover board；2. edge dam；3. central supported frame；4. horn connector；5. horn connecting rod；6. motor；
7. propeller；8. undercarriage；9. battery case；10. battery；11. horn joint；12. axle sleeve；13. locking nut；14. motor cabinet
Retaining ring；15. motor cabinet；16. neck；17. central supported frame mounting hole；18. undercarriage mounting hole；19. rise and fall frame connector；
20. propeller hub；21. blade root；22. blade tip.
Embodiment
To overcome the shortcoming that multi-rotor unmanned aerial vehicle load-carrying is small, cruising time is short, and cable electrical transfer mode pair at present
Flying field requires high, and the small present situation of flying radius.Real angle of the present invention from unmanned plane sector application, it is proposed that
A kind of heavy－duty unmanned vehicle of many rotors.
The present invention includes body cover board 1, edge dam 2, central supported frame 3, undercarriage 8, battery case 9, battery 10, many
Individual horn connector 4, multiple horn connecting rods 5, multiple motors 6 and multigroup propeller 7.Wherein, the body cover board 1 is positive six
The box structure of side shape, by be parallel to each other fuselage upper plate, fuselage lower plate, and connect the side of the fuselage upper plate and fuselage lower plate
Portion's baffle plate 2 is constituted；The central supported frame is located at the geometric center in the body cover board 1, is fixed on the following table of plate with described
Between face and fuselage lower plate upper surface.The multiple horn connector 4 is fixed inside the body cover board, and is located at fuselage respectively
On each angle of cover plate regular hexagon；Horn connecting rod is had on the edge dam corresponding with each horn connector
5 mounting hole.One end of each horn connecting rod 5 is extend into inside horn connector 4, and is fastened by locking nut, separately
One end is cantilever end.Each motor 6 fixes the cantilever end of each horn connecting rod by motor cabinet retaining ring 14.
Each group propeller 7 is separately mounted to the upper surface of each motor.Battery case 9 has two, is separately fixed at fuselage
The geometric center of upper plate upper surface and the geometric center of fuselage lower plate lower surface.Battery 10 is placed in the battery case.Framework knot
The undercarriage 8 of structure is arranged on the fuselage lower plate lower surface by undercarriage fixed landing gear connector.
Fuselage upper plate and fuselage lower plate structure size all same in the body cover board 1, are regular polygon carbon plate.It is just many
Each angle of side shape carries out chamfered, and chamfering edge lengths match with horn joint length.4 phases are respectively provided with the inside of bevel edge
The screwed hole of same size, square arrangement, the position of screwed hole and horn joint are corresponded.The mode being bolted will
Two layers of body cover board is fixedly connected with horn connector up and down.At the edge and fuselage lower plate of the polygon edge of the fuselage upper plate
The edge of polygon edge have neck 16 for being embedded in edge dam 2 respectively, the quantity of the neck and position with the side
The quantity and position consistency of fixture block on portion's baffle plate.Undercarriage mounting hole 18 is distributed with the fuselage lower plate.It is described just
Polygon is regular hexagon or octagon.Have respectively in hexagon in the inner surface of the fuselage upper plate and the inner surface of lower plate
Distribution or the central supported frame mounting hole 17 of octagonal distribution.
In the present embodiment, fuselage upper plate and fuselage lower plate are regular hexagon.
The edge dam is rectangular slab.Protrusion is symmetrically distributed with the side surface on two long sides of the edge dam should
The fixture block of side surface；Have two fixture blocks on the side surface on each long side, when the fuselage upper plate in the edge dam and body cover board 1 and
When fuselage lower plate coordinates, the fixture block is embedded in the neck of fuselage upper cover plate and fuselage lower cover respectively.
The horn connector 4 is sub-assembly, including horn joint 11, axle sleeve 12 and locking nut 13.The horn connects
First 11 generally cuboid formula structures, are made up of two supporting plates being parallel to each other and a sleeve.The supporting plate to be square,
There is connecting hole respectively on symmetrical two side surfaces of two supporting plates, by the connecting hole by two side tables of two supporting plates
Face is fixedly connected with fuselage upper plate and fuselage lower plate respectively.The geometric center of each supporting plate has for fixing the sleeve
Through hole.The external diameter of the sleeve is identical with the internal diameter of through hole on each supporting plate；The external diameter phase of the internal diameter of the sleeve and axle sleeve 12
Together.External peripheral surface in the sleeve outer end is flank, and the end face of the sleeve outer end is provided with axial locating slot.
During assembling, the horn joint 11 is fixed between fuselage upper plate and fuselage lower plate.Axle sleeve 12 loads the sleeve of horn joint 11
Interior, wing connecting rod 5 loads in the axle sleeve and locked by locking nut 13.Horn joint includes two supports and a set
Cylinder.The structure of described two supports is identical, is square mount structure.It is symmetrical in the frame of the square box of described two supports
There is a supporting table on surface respectively；It is interference fits between the sleeve and axle sleeve.In described sleeve one end, end face is provided with axle
To locating slot.The external peripheral surface for having locating slot one end sleeve is flank.Locking nut passes through axle sleeve, its internal thread
With the matching of sleeve external screw thread, axle sleeve is fixedly connected with horn joint.
The central supported frame 3 is frame structure, and profile and the fuselage upper plate and the shape of fuselage lower plate of the framework
It is identical.In the present embodiment, the central supported frame is regular hexagon.
There is the groove for flying control circuit for arranging on the underframe of six sides of central supported frame.The central supported
The height of frame is identical with the height of the edge dam.Having respectively on six angles on positive six side of the central supported frame is used for and machine
The screw that plate is fixedly connected with fuselage lower plate with it.Central supported frame 3 is metal aluminium material, lightweight and durable.
The horn connecting rod 5 is hollow cylindrical carbon pipe, and one end is extend into inside horn connector 4, by locking screw
Mother tightens, and the other end extend into motor cabinet retaining ring 14, is tightened by lock screw.
The motor cabinet retaining ring 14 is cylindrical shape.The motor cabinet retaining ring is cut vertically, to facilitate wing connecting rod
The cantilever end quick insertion retaining ring；There is radial convex in the axial joint-cutting both sides of the motor cabinet retaining ring external peripheral surface one end
There is concentric connecting hole on the locking auricle gone out, the auricle；After the motor cabinet retaining ring is inserted in horn connecting rod one end, pass through
Bolt fastens auricle, so that horn connecting rod and motor mechanism be connected.Motor cabinet and motor cabinet retaining ring are integral type knot
Structure, motor cabinet is prior art, and ellipsoidal structure is matched with motor W110-25.
Such as the structural representation that Figure 17 is propeller.The propeller 7 is the centrosymmetric structure of integral type, and the spiral shell
The symmetrical centre for revolving oar is propeller hub 20.
The propeller hub of the propeller symmetrical centre is groove-like, and the both sides of the groove are blade.The blade blade root 21
Thickness is 7mm, and the thickness of blade tip 22 be that a curve linear is thinned for the upper surface between 2mm, and blade root and blade tip.
The length of the propeller is 760mm, wherein propeller hub length 115mm.The pitch of the propeller is 240mm.Institute
The thickness for stating propeller hub is 3mm.
The blade it is tangential from blade root 21 to blade tip 22 be conic section, wherein the chord length at blade root be 70mm, blade tip
The chord length at place is 30mm.It is conic section connection between 70mm, and propeller hub and blade root that chord length at propeller hub 20, which is,.
The thickness of the propeller hub is the 8% of the propeller hub chord length；The thickness of blade root is the 10% of the blade root chord length；The thickness of blade tip
Spend for the 6% of the blade tip chord length.
The upper surface of the propeller hub and lower surface are plane；Connecting screw hole is distributed with propeller hub.
The propeller is composite construction, and its inside is wooden, to keep the shape of propeller；Superficies are that carbon is fine
Dimension, can keep the intensity of propeller.The propeller pulling force is up to 16kg.
During installation, the lower surface of propeller hub be placed on motor cabinet upper surface, and be connected by screw with motor cabinet.This implementation
In example：
Body cover board is regular hexagon, and horn connecting hole is provided with each regular hexagon corner inner side, is passed through
Bolted mode two layers of body cover board 1 will be fixedly connected with horn connector 4 up and down.Horn connecting rod 5 is hollow cylinder
Shape carbon pipe, one end is extend into inside horn connector 4, by locking nut screwing, and the other end extend into motor cabinet retaining ring 14,
Tightened by lock screw.The generally rectangular parallelepiped structure of horn connector 4, by horn joint 11, axle sleeve 12,13 groups of locking nut
Into the geometric center of the supporting plate of horn joint 11 has sleeve, and axle sleeve 12 penetrates sleeve formation interference fits.Horn connecting rod 5
Penetrate and interference fit is formed in axle sleeve, internal thread and the external screw thread of axle sleeve 12 of locking nut 13 coordinate, and complete the He of horn connector 4
The fixation of horn connecting rod 5.The other end of horn connecting rod 5 is stretched into motor 6, is connected the horn by motor cabinet retaining ring 14
Extension bar 5 and motor 6 are connected.Motor 6 includes motor cabinet retaining ring 14, motor cabinet 15, motor 6 and propeller 7, and propeller 7 is pacified
On motor shaft.Undercarriage 8 is located at fuselage lower plate lower central position, by undercarriage connecting-piece structure by the He of undercarriage 8
Lower fuselage cover plate is fixedly connected.Battery case 9 is provided with two, respectively positioned at the upper of fuselage upper plate lower surface center and fuselage lower plate
Centre of surface, is respectively to load 4 pieces of batteries 10 in hollow rectangular parallelepiped structure, each battery case, for the flight of heavy－duty unmanned plane.
As shown in Fig. 2 for body cover board 1, central supported frame 3, horn connector 4 assembling schematic diagram.Wherein, horn connects
Fitting 4 is located on the inside of the chamfering position of body cover board 1, and four screw threads are one group, and horn connector 4 is fixedly connected on above and below fuselage
Between plate；Central supported frame 3 is located at the center position of body cover board 1, and central supported frame 3 is regular hexagon shape, hexagon
Six points be located at body cover board sideline where perpendicular bisector on.By the mode of threaded connection, central supported frame 3 is fixed on
Between fuselage upper and lower plates.Edge dam 2 is stuck in body cover board edge and stayed inside the rectangle neck set, and fuselage above and below being fixed on
Between cover plate 1.The central supported frame 3, horn connector 4, edge dam 2 are highly consistent.
Fig. 3 is body cover board 1, horn connector 4, the assembling schematic diagram of horn connecting rod 5.Horn connector 4 relies on spiral shell
The mode of line connection is connected between fuselage upper plate and fuselage lower plate.Horn connector is made up of three parts：Horn joint 11, axle
Set 12, locking nut 13.During assembling, axle sleeve 12 is stretched into inside horn joint 11, interference fits, by fixture block radially in locating slot
It is internal.The one end of horn connecting rod 4 is extend into inside axle sleeve 12, interference fit；Locking nut 13 passes through sleeve, its internal thread and set
Cylinder outer nut coordinates, and body cover board 1 is connected with horn connecting rod 4.
As shown in Figure 10, horn connecting rod 4 is hollow cylindrical, and sleeve is stretched into one end, is interference fitted；The other end stretches into electricity
In machine base locking ring 14.
As shown in figure 4, motor is made up of motor cabinet retaining ring 14, motor cabinet 15, motor 6, propeller 7.Motor cabinet is locked
Ring 14 and motor cabinet 15 are integral type structure, and motor locking ring internal diameter is slightly larger than horn connecting rod external diameter, retaining ring radial direction bottom
Locking screw is installed, by locking screw by horn connecting rod and motor connection.Motor cabinet 15 and motor 6 are prior art, its
In, motor cabinet and electric drilling match, motor select W110-25 motors.The type selecting of motor is calculated according to optimizing design scheme.Spiral shell
Rotation oar 7 is composite construction, and its inside is wooden, and outer surface is carbon fibre materials, it is ensured that the intensity of propeller.It is wooden compared to complete
Propeller, the present embodiment use integral type propeller have the advantages that lightweight, intensity is high.
As shown in figure 11, undercarriage 8 is located at the fuselage lower plate center, generally rod-like structure, is welded using hollow aluminum pipe
Connect and form.Two aluminum pipes of the undercarriage bottom in the direction of the width, stretch out along respective direction both sides, collectively constitute unmanned plane
Aircraft landing gear.The undercarriage is mounted on the undercarriage mounting hole 18 in fuselage lower plate by the frame connector that rises and falls
On.
Figure 12 is the structural representation of frame connector of rising and falling.It is to coordinate with undercarriage aluminum pipe in the middle part of the frame connector that rises and falls
Semicircle.The two ends of semicircle are to have mounting hole on the installing plate of the level of radially protruding, the installing plate.During installation, it will rise and fall
The semicircle of frame connector is stuck on undercarriage upper level aluminum pipe external diameter, and installing plate is bolted in fuselage lower plate
The heart.
Battery case 9 has two, is body structure.Each battery case is fixed on the upper surface of fuselage upper plate by angle bar respectively
With the lower surface of fuselage lower plate.
Claims (10)
1. a kind of many rotor unmanned aircrafts of heavy－duty, it is characterised in that including body cover board, undercarriage, two battery cases,
Battery, multiple horn connectors, multiple horn connecting rods, multiple motors, multigroup propeller and motor cabinet retaining ring；Wherein, institute
The box structure that body cover board is regular polygon is stated, the multiple horn connector is fixed inside the body cover board, and position respectively
In on each angle of body cover board regular polygon；One end of each horn connecting rod is connected with horn connector, and the other end is
Cantilever end；Each motor fixes the cantilever end of each horn connecting rod by motor cabinet retaining ring；Each group propeller is respectively mounted
In the upper surface of each motor；Two batteries are respectively placed under fuselage upper plate upper surface geometric center and fuselage lower plate
The undercarriage of each battery case bearing wall and frame structure at surface geometry center is arranged on described by undercarriage fixed landing gear connector
Fuselage lower plate lower surface；Described regular polygon is regular hexagon or octagon.
2. many rotor unmanned aircrafts of heavy－duty as claimed in claim 1, it is characterised in that the body cover board includes mutual
Parallel fuselage upper plate, fuselage lower plate, and connect the fuselage upper plate and the edge dam of fuselage lower plate；In the body cover board
Central supported frame is fixed between fuselage upper plate lower surface and fuselage lower plate upper surface at geometric center.
3. many rotor unmanned aircrafts of heavy－duty as claimed in claim 1, it is characterised in that the horn connector is combination
Part, including horn joint, axle sleeve and locking nut；The square supporting plate and one that horn joint therein is parallel to each other by two
Individual sleeve composition；There is connecting hole respectively on symmetrical two side surfaces of described two supporting plates；The geometry of each supporting plate
There is the through hole for fixing the sleeve at center；The external diameter of the sleeve is identical with the internal diameter of through hole on each supporting plate；The set
The internal diameter of cylinder is identical with the external diameter of axle sleeve；External peripheral surface in the sleeve outer end is flank, and the sleeve outer end
End face be provided with axial locating slot.
4. many rotor unmanned aircrafts of heavy－duty as claimed in claim 1, it is characterised in that the horn connecting rod is hollow
Cylindric carbon pipe, one end is extend into inside horn connector, by locking nut screwing, and the other end extend into motor cabinet locking
Ring, is tightened by lock screw.
5. many rotor unmanned aircrafts of heavy－duty as claimed in claim 1, it is characterised in that the motor cabinet retaining ring is circle
Tubular；The motor cabinet retaining ring is cut vertically, to facilitate the wing connecting rod cantilever end quick insertion retaining ring；In the motor
The axial joint-cutting both sides of seat retaining ring external peripheral surface one end, which have on the locking auricle of radially protruding, the auricle, concentric company
Connect hole；After the motor cabinet retaining ring is inserted in horn connecting rod one end, auricle is fastened by bolt, so that by horn connecting rod
With motor mechanism connection；Motor cabinet and motor cabinet retaining ring are integral type structure.
6. many rotor unmanned aircrafts of heavy－duty as claimed in claim 1, it is characterised in that the propeller wood materials
Be made with the carbon fiber for being wrapped in wooden material surface, be the centrosymmetric structure of integral type, and the propeller it is symmetrical in
The heart is propeller hub；Described propeller hub is groove-like, and the both sides of the groove are propeller blade；The length of the propeller is 760mm, its
The length 115mm of middle propeller hub；The pitch of the propeller is 240mm；The thickness of the propeller hub is 3mm；The upper surface of the propeller hub
It is plane with lower surface；
The thickness of the blade root of the propeller blade is 7mm, and the thickness of blade tip is the upper table between 2mm, and blade root and blade tip
Face is that a curve linear is thinned；The tangential of the blade from blade root to blade tip is conic section, and the wherein chord length at blade root is
Chord length at 70mm, blade tip is 30mm；It is conic section connection between 70mm, and propeller hub and blade root that chord length at propeller hub, which is,；
The thickness of the propeller hub is the 8% of the propeller hub chord length；The thickness of blade root is the 10% of the blade root chord length；The thickness of blade tip is the leaf
The 6% of sharp chord length.
7. many rotor unmanned aircrafts of heavy－duty as claimed in claim 2, it is characterised in that the fuselage in the body cover board
Upper plate and fuselage lower plate structure size all same, are regular polygon carbon plate；Each angle of regular polygon carries out chamfered, chamfering
Edge lengths match with horn joint length；The connecting hole of organic arm connection on the inside of bevel edge；In each of the fuselage upper plate
While edge and fuselage lower plate it is each while edge have neck for being embedded in edge dam respectively；Divide in the fuselage lower plate
It is furnished with undercarriage mounting hole.
8. many rotor unmanned aircrafts of heavy－duty as claimed in claim 2, it is characterised in that described two long sides of edge dam
Side surface be symmetrically distributed with protrude the side surface fixture block；There are two fixture blocks on the side surface on each long side, when edge gear
When plate is with the fuselage upper plate in body cover board and the cooperation of fuselage lower plate, the fixture block is embedded in into positioned at fuselage upper cover plate and fuselage respectively
In the neck of lower cover.
9. many rotor unmanned aircrafts of heavy－duty as claimed in claim 2, it is characterised in that the profile of the central supported frame
It is identical with the profile of the fuselage upper plate and fuselage lower plate；Have on the underframe of each side of central supported frame for arranging
Fly the groove of control circuit；The height of the central supported frame is identical with the height of the edge dam；It is each in the central supported frame
There is the screw for being fixedly connected with fuselage upper plate and fuselage lower plate on the angle on side respectively.
10. many rotor unmanned aircrafts of heavy－duty as claimed in claim 3, it is characterised in that horn joint includes two branch
Frame and a sleeve；There is supporting table respectively on symmetrical surface in the frame of the square box of described two supports；The sleeve with
It is interference fits between axle sleeve；In described sleeve one end, end face is provided with axial locating slot；It is described to have locating slot one end sleeve
External peripheral surface is flank；Locking nut passes through axle sleeve, its internal thread and the matching of sleeve external screw thread, by axle sleeve and horn joint
It is fixedly connected.
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|---|---|---|---|
| CN201621244577.8U CN206407115U (en) | 2016-11-21 | 2016-11-21 | A kind of many rotor unmanned aircrafts of heavy－duty |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621244577.8U CN206407115U (en) | 2016-11-21 | 2016-11-21 | A kind of many rotor unmanned aircrafts of heavy－duty |
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| CN206407115U true CN206407115U (en) | 2017-08-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201621244577.8U Expired - Fee Related CN206407115U (en) | 2016-11-21 | 2016-11-21 | A kind of many rotor unmanned aircrafts of heavy－duty |
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| CN106741825A (en) * | 2016-11-21 | 2017-05-31 | 西安三翼航空科技有限公司 | A kind of six rotor unmanned aircrafts |
| CN107902070A (en) * | 2017-10-27 | 2018-04-13 | 陈淇健 | A kind of frame central part and the multi-rotor unmanned aerial vehicle based on the frame central part |
| CN108502136A (en) * | 2018-05-14 | 2018-09-07 | 天长市星舟航空技术有限公司 | A kind of horizontal landing-type multi-rotor unmanned aerial vehicle fuselage box |
| CN108557066A (en) * | 2017-12-29 | 2018-09-21 | 广州亿航智能技术有限公司 | A kind of unmanned plane being easily installed and unload cantilever |
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| CN108622395A (en) * | 2018-05-14 | 2018-10-09 | 天长市星舟航空技术有限公司 | Multi-rotor unmanned aerial vehicle fuselage box |
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| WO2019227439A1 (en) * | 2018-05-31 | 2019-12-05 | 深圳市大疆创新科技有限公司 | Fuselage, vehicle arm, rotor assembly, airframe, and multi-rotor unmanned aerial vehicle |
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| CN106741825A (en) * | 2016-11-21 | 2017-05-31 | 西安三翼航空科技有限公司 | A kind of six rotor unmanned aircrafts |
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| CN107902070B (en) * | 2017-10-27 | 2024-06-11 | 陈淇健 | Rack center piece and multi-rotor unmanned aerial vehicle based on same |
| CN108557066A (en) * | 2017-12-29 | 2018-09-21 | 广州亿航智能技术有限公司 | A kind of unmanned plane being easily installed and unload cantilever |
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| CN108622395A (en) * | 2018-05-14 | 2018-10-09 | 天长市星舟航空技术有限公司 | Multi-rotor unmanned aerial vehicle fuselage box |
| CN108502136B (en) * | 2018-05-14 | 2023-12-22 | 天长市星舟航空技术有限公司 | Horizontally-falling type multi-rotor unmanned aerial vehicle body box |
| WO2019227439A1 (en) * | 2018-05-31 | 2019-12-05 | 深圳市大疆创新科技有限公司 | Fuselage, vehicle arm, rotor assembly, airframe, and multi-rotor unmanned aerial vehicle |
| CN108791846A (en) * | 2018-06-04 | 2018-11-13 | 西北工业大学 | A kind of six rotor unmanned plane and fire-extinguishing of single-shot |
| CN108591388A (en) * | 2018-07-16 | 2018-09-28 | 飞瑞航空科技（江苏）有限公司 | A kind of unmanned plane belt drive system adjustable tensioning mechanism |
| CN109774948A (en) * | 2019-02-13 | 2019-05-21 | 山东蜂巢航空科技有限公司 | It is a kind of can a variety of load of carry oil electricity mixing multi-rotor unmanned aerial vehicle |
| CN110040242A (en) * | 2019-03-15 | 2019-07-23 | 湖北文理学院 | Four axis unmanned planes of one kind and flight instruments |
| WO2023033758A1 (en) * | 2021-09-04 | 2023-03-09 | Yavuz Davut | An unmanned aerial vehicle |
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