CN108116670A - A kind of portable high-strength type multi-rotor unmanned aerial vehicle and its manufacturing method - Google Patents
A kind of portable high-strength type multi-rotor unmanned aerial vehicle and its manufacturing method Download PDFInfo
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- CN108116670A CN108116670A CN201711418543.5A CN201711418543A CN108116670A CN 108116670 A CN108116670 A CN 108116670A CN 201711418543 A CN201711418543 A CN 201711418543A CN 108116670 A CN108116670 A CN 108116670A
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- aerial vehicle
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- 229920000049 Carbon (fiber) Polymers 0.000 claims description 10
- 239000004917 carbon fiber Substances 0.000 claims description 10
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 10
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- 238000003754 machining Methods 0.000 claims description 3
- 229910001148 Al-Li alloy Inorganic materials 0.000 claims description 2
- FCVHBUFELUXTLR-UHFFFAOYSA-N [Li].[AlH3] Chemical compound [Li].[AlH3] FCVHBUFELUXTLR-UHFFFAOYSA-N 0.000 claims description 2
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 239000001989 lithium alloy Substances 0.000 claims description 2
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Classifications
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- 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
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- 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
- B64C1/069—Joining arrangements therefor
-
- 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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/28—Collapsible or foldable blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
-
- 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
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a kind of portable high-strength type multi-rotor unmanned aerial vehicle and its manufacturing methods, unmanned plane includes fuselage, cantilever, propeller unit and undercarriage, fuselage is in rectangular parallelepiped structure, four cantilevers are symmetrically mounted on by axis pin on fuselage respectively, four cantilevers can rotate and can be locked around respective installation axis pin, so as in the operating position gone of stretching and turn back and be close to be converted between its stored position of fuselage side wall.Propeller unit described in four groups is connected to the other end of four cantilevers by motor rack respectively, and four undercarriages are mounted on the lower part of the propeller unit with the cantilever vertical respectively, and the undercarriage is foldable to parallel with the cantilever.The entire unmanned plane structure of the present invention is fabricated using various material rational deployment, not only ensure that the structural strength of unmanned plane but also has been significantly reduced the construction weight of unmanned plane, help is provided for the long endurance of unmanned plane carry big load.
Description
Technical field
The present invention relates to unmanned plane manufacturing field, more particularly to a kind of big load long endurance unmanned aircraft structure manufacturer
Method.By the way that engineering plastics, carbon fibre composite and metal to be reasonably applied to the manufacture of parts, unmanned plane can be met
High structural strength can significantly decrease the construction weight of unmanned plane again.
Background technology
Multi-rotor unmanned aerial vehicle due to its is simple in structure, manufacture it is at low cost, have a wide range of application the advantages that in recent years become nobody
The research hotspot of machine industry.Compared to fixed-wing unmanned plane and single-rotor helicopter, multi-rotor unmanned aerial vehicle is easily manipulated and flies
Steadily, it can be achieved that small space flight, VTOL and fixed point are spiraled.Multi-rotor unmanned aerial vehicle is detectd in military field available for military affairs
Look into, the criminal of enemy tracking and frontier defense monitoring, can also be used for forest fire protection, oil and power-line patrolling, ground mapping etc. in industrial circle.
Its shortcoming of multi-rotor unmanned aerial vehicle is that cruising time is short, and carry weight is small, this also becomes limitation multi-rotor unmanned aerial vehicle
Break through a bottleneck of development.Multi-rotor unmanned aerial vehicle, as the energy, is driven, itself energy using lithium ion battery compared to fuel oil
Amount is smaller, and the cruising ability of unmanned plane also can be significantly reduced in the case of carry big load.To meet prolonged continuation of the journey,
The battery of large capacity is not only needed to also need to reduce airframe structure weight as far as possible.The increase of battery capacity also brings along battery
The rising of weight, the rising of battery weight propose the structural strength of unmanned plane higher requirement again, structural strength, endurance,
Weight three mutually restricts, therefore realizes that long cruising time must optimize the structure of unmanned plane under conditions of big load is met
Intensity optimizes the structure design of unmanned plane.
Strength of Metallic Materials is big, has excellent mechanical property, and right unmanned plane is integrally manufactured using metal, and weight is big, meeting
It is significant to reduce cruising time.Carbon fibre composite has small proportion, high intensity, and so it is difficult to use in complicated abnormal shape structure
The manufacture of part influences the aesthetics of unmanned plane.Using engineering plastics injection molding unmanned plane shell, there is precision height, aesthetic appearance
The advantages of good, its right poor mechanical property are not suitable for use in stress members.
The content of the invention
The problems such as present invention is short for multi-rotor unmanned aerial vehicle cruising time, and structural strength is poor in the case of big load, using carbon
Fibrous composite, engineering plastics and metal are respectively used to the manufacture of unmanned plane difference parts, and unmanned plane has excellent knot
Structure intensity, and with light construction weight, it can be achieved that unmanned plane big load is flown for a long time.
The portable high-strength type multi-rotor unmanned aerial vehicle of the present invention includes fuselage, cantilever, propeller unit and undercarriage, described
Fuselage is in rectangular parallelepiped structure, and the cantilever includes suspended wall after two front booms and two, one end difference of two preceding spiral arms
The front upper part of the fuselage two side walls is symmetrically mounted on by axis pin, one end of two rear suspended walls passes through axis pin pair respectively
Claim the rear lower mounted on the fuselage two side walls, four cantilevers can rotate around respective installation axis pin and can
It is locked, so as to be close to be converted between its stored position of fuselage side wall stretching out the operating position gone and turn back, four
The group propeller unit is connected to the other end of four cantilevers, four undercarriage difference by motor rack respectively
The lower part of the propeller unit is mounted on the cantilever vertical, the undercarriage is foldable to parallel with the cantilever.
It is preferred that the propeller unit includes two groups of propellers and motor, two groups of propellers configure up and down, respectively by upper
Lower tooth sector is meshed with the output gear of the motor on the motor rack, under the action of the motor,
The rotation reversely with each other of upper and lower two tooth sectors, so as to drive, propeller rotation reversely with each other, the undercarriage are mounted on up and down
At the axle center of downside propeller.
It is preferred that the propeller blade can carry out doubling centered on rotation axis, in order to folding and unfolding.
The axis pin for being preferred for installing the preceding spiral arm is connected by two auricles being separately mounted on upper and lower fuselage
It is connected on the fuselage, the propeller, undercarriage and preceding spiral arm after folding can be collapsed between upper and lower auricle, for installing
Two auricles that the axis pin of spiral arm by configuring up and down is mounted on lower fuselage after described are connected on the fuselage, are rolled over
Propeller, undercarriage and the rear spiral arm of poststack can be collapsed between two auricles of lower fuselage.
It is preferred that the fuselage includes composite material framework skeleton and wraps the plastics shell of the framework skeleton, institute
Stating shell includes upper shell, lower housing and rear cover, and the framework skeleton is connected to by bolt and screw on lower housing, it is described on
Housing is mounted on by buckle and screw on lower housing, and the rear cover is mounted on by buckle on upper-lower casing.
It is preferred that all auricles are made of metal material machining, and it is fixed on by bolt through plastics shell
On the framework skeleton, the framework skeleton is by grafting and cementing connection after composite board adds according to design size machine
It forms, the motor rack is molded for integral molded plastic, and the cantilever and propeller blade are wound using carbon fiber one-way prepreg
Shaping, and using solidification of hot-press tank.
It is preferred that the composite material is carbon fiber enhancement resin base composite material, the plastics are PC/ABS composite plastics
Material, the metal material is 2196-T62 aluminium lithium alloys.
The portable high-strength type multi-rotor unmanned aerial vehicle being used to manufacture any one of above-mentioned technical proposal of the present invention
Manufacturing method includes：Step 1: manufacture carbon fibre composite plate；Step 2: according to design size to composite board into
Row machining, and framework skeleton is made by grafting and cementing mode；Step 3: body shell is divided according to fuselage outer profile
For three upper shell, lower housing and rear cover parts, global formation is carried out to the three parts by injection molding process respectively；Step
4th, the body shell is assembled on the framework skeleton, and covers the framework skeleton, fuselage main body is made；Step 5:
It is Wrapping formed using carbon fiber one-way prepreg, and cantilever and propeller blade are made using the method for solidification of hot-press tank；Step
6th, using metal and processing and fabricating attachment lug and undercarriage；Step 7: motor rack is made using PC/ABS injection moldings；Step
Rapid eight, each component is assembled in portable high-strength type multi-rotor unmanned aerial vehicle with it.
It is preferred that the composite board uses carbon fiber one-way prepreg autoclave molding.
It is preferred that the step 8 includes：(1) each connection is fixed on auricle on fuselage, and (2) pass through one end of each cantilever
Axis pin is connected with corresponding auricle, and (3) install the motor rack in the other end of each cantilever；(4) motor is fixed on motor rack,
(5) tooth sector in the rotation axis of propeller is installed, and upper and lower propeller is mounted on the motor rack, while is made up and down
Gear is meshed with the output gear of motor；(6) undercarriage is mounted at the axle center of downside propeller, completes the group of unmanned plane
Dress.
The advantage of the invention is that：
1) different parts reasonably optimize layout using different materials and are manufactured, and unmanned plane has excellent structure
Intensity, fatigue life and appearance, and the construction weight of unmanned plane is reduced to greatest extent.
2) excellently structural strength can realize unmanned plane installation large capacity or polylith battery, when improving the continuation of the journey of unmanned plane
Between, and can the big load of carry.
3) lift that unmanned plane generates propeller in flight course is conducted on framework skeleton, and framework skeleton is main
Load component effectively prevents motor and rotates influence of the vibrations brought to housing construction.
4) a variety of manufacturing process reasonable combinations greatly reduce the manufacturing cycle of unmanned plane.
5) unmanned plane produced by the present invention can be applied to the demand field of the long endurance of big load, with good economic efficiency
And social benefit.
Description of the drawings
Fig. 1 is airframe structure schematic diagram.
Fig. 2 is the unmanned plane constructional appearance schematic diagram after the completion of assembling.
Fig. 3 is propeller scheme of installation.
Fig. 4 is landing gear collapsed state schematic diagram.
Fig. 5 is propeller blade folded state schematic diagram.
Fig. 6 is the schematic diagram for packing up cantilever, propeller and undercarriage.
Specific embodiment
Below in conjunction with attached drawing, to the unmanned plane structure in the present invention and its specific embodiment work is manufactured specifically
It is bright.
As shown in Figure 1, 2, fuselage 5 includes composite material framework skeleton and wraps the plastics shell of framework skeleton,
Shell splits into upper shell 51, lower housing 52 and rear cover 53, and framework skeleton is connected to by bolt and screw on lower housing 52, on
Housing 51 is mounted on by buckle and screw on lower housing 52, and rear cover 53 is mounted on by buckle on upper-lower casing, and composition is entire
Fuselage 5.Attachment lug 54 for connecting cantilever 6 is installed on fuselage 5.All attachment lugs 54 are added using metal material machine
Work is made, and is fixed on by bolt through plastics shell on framework skeleton.
As illustrated in figures 3-6, portable high-strength type multi-rotor unmanned aerial vehicle of the invention include undercarriage 1, propeller blade 2,
Gear set 3, motor 4, fuselage 5 and cantilever 6, fuselage 5 are in rectangular parallelepiped structure, and cantilever 6 includes two front booms and two back booms,
One end of two preceding spiral arms is symmetrically mounted on the attachment lug 54 of front upper part of 5 two side walls of fuselage respectively by axis pin, and two
One end of suspended wall is symmetrically mounted on the attachment lug 54 of rear lower of 5 two side walls of fuselage respectively by axis pin after a, four
Cantilever 6 can rotate and can be locked around respective installation axis pin, so as to stretch out the operating position gone and turning back
It is close to be converted between its stored position of 5 side wall of fuselage, the other end of four cantilevers 6 is equipped with electricity by motor rack respectively
Machine 4 is equipped with two groups of propellers on each motor rack symmetrical above and belowly, and propeller includes propeller blade 2 and rotation axis, each
The end of rotation axis is both provided with tooth sector, and two tooth sectors are respectively from the output gear set up and down with motor output shaft end
Wheel is meshed, and forms gear set 3.The cooperation rotation of gear set 5, upper and lower two tooth sectors one are so driven by a motor 4
It is a clockwise, one rotate reversely with each otherly counterclockwise, so as to drive propeller blade negative direction rotation up and down, it is possible thereby to put down
Weigh torque, reduces the moment of flexure of fuselage connection shaft.Propeller blade 2 can carry out doubling centered on rotation axis, in order to receive
It puts.Four undercarriages 1 are vertically installed at respectively with cantilever 6 at the axle center of downside propeller, and undercarriage 1 is located at downside propeller
Below blade rotation axis, not as blade rotates, undercarriage 1 is foldable to parallel with cantilever 6.
Unmanned plane is in the task of execution, until rotation cantilever 6 extend out to work, opens the propeller blade 2 to that of folding
, into 180 degree angle, opening undercarriage 1 is in and 6 plumbness of cantilever for this.Start to take off.After the completion of task, undercarriage, doubling are packed up
Propeller blade rotates cantilever to fuselage side and is locked.The unmanned plane collapsed is small, just to carry and store.With
Two attachment lugs 54 of spiral arm are connected on fuselage up and down before installation, propeller, undercarriage and preceding rotation after folding
Arm can be collapsed between auricle is vertically connected with, and connected with configuring up and down for two attachment lugs of the axis pin of spiral arm after installation
On lower fuselage, propeller, undercarriage and rear spiral arm after folding can be collapsed between two attachment lugs of lower fuselage.
The present invention by using the different variant positions of material manufacture unmanned plane parts so that unmanned plane have it is excellent
Different structural strength, and with light construction weight, it can be achieved that unmanned plane big load is flown for a long time.Specific implementation process is such as
Under：
1) entire unmanned plane structure is divided into three different structural systems：Airframe structure system, cantilever design system
With landing gear structure system.
2) carbon fibre composite part manufactures
Composite board is made using T700 carbon fiber one-ways prepreg and autoclave forming process, on plane aluminium sheet
Order according to [45 °/90 °/- 45 °/0 °/0 °/- 45 °/90 °/45 °] s carries out laying, and one layer of demoulding is laid with after the completion of one layer of paving
Cloth, and vacuum bag is made, solidification of hot-press tank shaping is transferred to after vacuumizing, primary curing technological parameter is：Solidifying pressure is
0.6MPa, solidification temperature are 130 DEG C, hardening time 120min.
Composite material cantilever is made using T700 carbon fiber one-ways prepreg and autoclave forming process, in round metal bars
Order according to [45 °/90 °/- 45 °/0 °/0 °/- 45 °/90 °/45 °] s is wound laying, and one layer is wound after the completion of one layer of paving
Release cloth, and vacuum bag is made, solidification of hot-press tank shaping is transferred to after vacuumizing, primary curing technological parameter is：Solidifying pressure
For 0.6MPa, solidification temperature is 130 DEG C, hardening time 120min.
Plate and cantilever thickness after the curing molding are 1mm.
3) framework skeleton manufactures
Composite board carries out machine according to design structure and adds, and is connected multiple plates using riveting and/or cementation method
Into framework skeleton, the structure glue used in connection procedure is J133 glue, and fastener is TITAIUM ALLOY RIVETS, and framework skeleton structure is such as
Shown in Fig. 1.
4) moulding manufactures
The injection mold of upper shell 51, lower housing 52, rear cover 53 and motor rack is designed according to structure size, using PC/
ABS alloy pellet injection molding structural member, crucial injection molding technology parameter are：Drying temperature is 80 DEG C, mold temperature for 60~
80 DEG C, melt adhesive temperature is 250~280 DEG C, and injection pressure is 80~140MPa.
The thickness of above-mentioned body shell is 1mm, and reinforcing rib is set in housing many places, wherein up and down at fuselage attachment lug
Thickness is 2mm, and injection airframe structure is as shown in Figure 2.
The motor rack wall thickness is 1.5mm, and sets reinforcing rib in privileged site.
5) machine adds part to manufacture
It is added using 2A12 aluminium machines and makes attachment lug 54,54 wall thickness of attachment lug is 1.5mm.
6) unmanned plane assembles
Above-mentioned framework skeleton is connected to by bolt and screw on lower housing, in the good upper shell of lower housing over-assemble with after
Lid, auricle is fixedly connected on assembled fuselage.One end of cantilever is mounted on by axis pin on attachment lug, and motor passes through electricity
Rack is mounted on cantilever one end using bolt, and in motor rack over-assemble propeller, undercarriage is installed on the downside of propeller, is completed whole
The manufacture and assembly of a unmanned plane.
Claims (10)
1. a kind of portable high-strength type multi-rotor unmanned aerial vehicle, it is characterised in that：Including fuselage, cantilever, propeller unit and rise and fall
Frame, the fuselage are in rectangular parallelepiped structure, and the cantilever includes suspended wall after two front booms and two, and the one of two preceding spiral arms
End is symmetrically mounted on the front upper part of the fuselage two side walls by axis pin respectively, and one end of two rear suspended walls passes through respectively
Axis pin is symmetrically mounted on the rear lower of the fuselage two side walls, and four cantilevers are around respective installation axis pin rotation and energy
It is enough locked, so as to be close to be converted between its stored position of fuselage side wall stretching out the operating position gone and turning back, four groups
The propeller unit is connected to the other end of four cantilevers by motor rack respectively, four undercarriages respectively with
It is mounted on the lower part of the propeller unit, the undercarriage is foldable to the position parallel with the cantilever cantilever vertical
It puts.
2. portable high-strength type multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：The propeller unit bag
Two groups of propellers and motor are included, two groups of propellers configure up and down, respectively by upper and lower tooth sector with being mounted on the motor rack
On the output gear of the motor be meshed, under the action of the motor, upper and lower two tooth sectors constant speed reversely with each other
Rotation, so as to drive propeller rotation reversely with each other up and down, the undercarriage is mounted at the axle center of downside propeller.
3. portable high-strength type multi-rotor unmanned aerial vehicle according to claim 2, it is characterised in that：The propeller blade energy
It is enough that doubling is carried out centered on rotation axis, in order to folding and unfolding.
4. portable high-strength type multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：For installing the preceding rotation
The axis pin of arm is connected to by two auricles being separately mounted on upper and lower fuselage on the fuselage, the spiral after folding
Paddle, undercarriage and preceding spiral arm are collapsed between upper and lower auricle, for installing the axis pin of the rear spiral arm by matching somebody with somebody up and down
Two auricles being mounted on lower fuselage with putting are connected on the fuselage, propeller, undercarriage and rear spiral arm after folding
It collapses between two auricles of lower fuselage.
5. portable high-strength type multi-rotor unmanned aerial vehicle according to claim 4, it is characterised in that：The fuselage includes compound
Material framework skeleton and the plastics shell for wrapping the framework skeleton, the shell include upper shell, lower housing and after
Lid, the lower housing are connected to by bolt and screw on framework skeleton, and the upper shell is installed respectively by buckle and screw
On lower housing and framework skeleton, the rear cover is mounted on by buckle on framework skeleton.
6. portable high-strength type multi-rotor unmanned aerial vehicle according to claim 5, it is characterised in that：All auricles are using gold
Belong to material machining to be made, and be fixed on by bolt through plastics shell on the framework skeleton, the framework skeleton
For composite material one-pass molding part by riveting and/or it is cementing be formed by connecting, the motor rack for integral molded plastic shaping, it is described
Cantilever and propeller blade are Wrapping formed using carbon fiber one-way prepreg, and using solidification of hot-press tank.
7. portable high-strength type multi-rotor unmanned aerial vehicle according to claim 5, it is characterised in that：The composite material is
Carbon fiber enhancement resin base composite material, the plastics are PC/ABS composite plastics, and the metal material is 2196-T62
Aluminium lithium alloy material, fastener are titanium alloy material.
8. a kind of manufacturing method of portable high-strength type multi-rotor unmanned aerial vehicle, for any one of manufacturing claims 1-7
Unmanned plane, which is characterized in that including：
Step 1: manufacture carbon fibre composite plate；
Step 2: framework skeleton is made by riveting and cementing mode according to design；
Step 3: body shell is divided into three upper shell, lower housing and rear cover parts according to fuselage outer profile, pass through note respectively
It moulds moulding process and global formation is carried out to the three parts；
Step 4: the body shell is assembled on the framework skeleton, and the framework skeleton is covered, fuselage master is made
Body；
Step 5: it is Wrapping formed using carbon fiber one-way prepreg, and cantilever and spiral are made using the method for solidification of hot-press tank
Paddle blade；
Attachment lug and undercarriage are made Step 6: being machined using metal；
Motor rack is made Step 7: being molded using PC/ABS material injections；
Step 8: each component is assembled to form multi-rotor unmanned aerial vehicle.
9. the manufacturing method of portable high-strength type multi-rotor unmanned aerial vehicle according to claim 8, it is characterised in that：It is described multiple
Condensation material plate uses carbon fiber one-way prepreg autoclave molding.
10. the manufacturing method of portable high-strength type multi-rotor unmanned aerial vehicle according to claim 8, which is characterized in that described
Step 8 includes：
(1) each connection is fixed on auricle on fuselage,
(2) one end of each cantilever is connected by axis pin with corresponding auricle,
(3) motor rack is installed in the other end of each cantilever；
(4) motor is fixed on motor rack；
(5) tooth sector in the rotation axis of propeller is installed, and upper and lower propeller is mounted on the motor rack, is made simultaneously
Upper lower gear is meshed with the output gear of motor；
(6) undercarriage is mounted at the axle center of downside propeller, completes the assembling of unmanned plane.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110001080A (en) * | 2019-05-07 | 2019-07-12 | 航天神舟飞行器有限公司 | A kind of special-shaped support construction method for manufacturing parts applied to unmanned plane |
| CN110962284A (en) * | 2018-09-28 | 2020-04-07 | 温州塔罗航空科技有限公司 | Processing method of wire joint fixing seat |
| CN111086640A (en) * | 2020-03-06 | 2020-05-01 | 国网福建省电力有限公司三明供电公司 | Automatic inspection unmanned aerial vehicle based on visual identification |
| WO2022257050A1 (en) * | 2021-06-09 | 2022-12-15 | 深圳市大疆创新科技有限公司 | Structural component and propeller protection support for multi-rotor unmanned aerial vehicle, and multi-rotor unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2234915Y (en) * | 1995-08-19 | 1996-09-11 | 江富余 | Rotor for aircraft |
| CN205574265U (en) * | 2015-12-29 | 2016-09-14 | 深圳曼塔智能科技有限公司 | Rotor unmanned aerial vehicle |
| CN206407119U (en) * | 2016-12-19 | 2017-08-15 | 昊翔电能运动科技(昆山)有限公司 | Folding multi-rotor unmanned aerial vehicle with undercarriage |
| CN206485568U (en) * | 2017-02-22 | 2017-09-12 | 天津曙光天成科技有限公司 | A kind of many rotor unmanned aircrafts |
| CN207902743U (en) * | 2017-12-25 | 2018-09-25 | 航天神舟飞行器有限公司 | A kind of portable high-strength type multi-rotor unmanned aerial vehicle |
-
2017
- 2017-12-25 CN CN201711418543.5A patent/CN108116670A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2234915Y (en) * | 1995-08-19 | 1996-09-11 | 江富余 | Rotor for aircraft |
| CN205574265U (en) * | 2015-12-29 | 2016-09-14 | 深圳曼塔智能科技有限公司 | Rotor unmanned aerial vehicle |
| CN206407119U (en) * | 2016-12-19 | 2017-08-15 | 昊翔电能运动科技(昆山)有限公司 | Folding multi-rotor unmanned aerial vehicle with undercarriage |
| CN206485568U (en) * | 2017-02-22 | 2017-09-12 | 天津曙光天成科技有限公司 | A kind of many rotor unmanned aircrafts |
| CN207902743U (en) * | 2017-12-25 | 2018-09-25 | 航天神舟飞行器有限公司 | A kind of portable high-strength type multi-rotor unmanned aerial vehicle |
Non-Patent Citations (2)
| Title |
|---|
| 中国工程塑料工业协会加工应用专委会: "《2009年中国工程塑料复合材料技术研讨会论文集》", 31 July 2009, 《工程塑料应用》杂志社, pages: 206 - 208 * |
| 张玉龙等: "《高技术复合材料制备手册》", 国防工业出版社, pages: 206 - 208 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110962284A (en) * | 2018-09-28 | 2020-04-07 | 温州塔罗航空科技有限公司 | Processing method of wire joint fixing seat |
| CN110001080A (en) * | 2019-05-07 | 2019-07-12 | 航天神舟飞行器有限公司 | A kind of special-shaped support construction method for manufacturing parts applied to unmanned plane |
| CN111086640A (en) * | 2020-03-06 | 2020-05-01 | 国网福建省电力有限公司三明供电公司 | Automatic inspection unmanned aerial vehicle based on visual identification |
| WO2022257050A1 (en) * | 2021-06-09 | 2022-12-15 | 深圳市大疆创新科技有限公司 | Structural component and propeller protection support for multi-rotor unmanned aerial vehicle, and multi-rotor unmanned aerial vehicle |
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