CN206170665U - Unmanned aerial vehicle fuselage and wing thereof - Google Patents
Unmanned aerial vehicle fuselage and wing thereof Download PDFInfo
- Publication number
- CN206170665U CN206170665U CN201621091278.5U CN201621091278U CN206170665U CN 206170665 U CN206170665 U CN 206170665U CN 201621091278 U CN201621091278 U CN 201621091278U CN 206170665 U CN206170665 U CN 206170665U
- Authority
- CN
- China
- Prior art keywords
- aerial vehicle
- unmanned aerial
- carbon fiber
- fiber layer
- resin
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Moulding By Coating Moulds (AREA)
Abstract
The utility model discloses an unmanned aerial vehicle fuselage and wing thereof, the unmanned aerial vehicle fuselage including the hollow resin frame frame of piling up technological integrated into one piece and cladding receive press in the outer fibre layers of resin frame frame, fibre layers is the carbon cloth of preimpregnation resin. The utility model discloses effectively solved unmanned aerial vehicle's molding difficulty, unable balanced between each wing, the unable installation in the angle of elevation of terminal motor is accurate, and a great deal of technical problem such as the unable assurance of precision have successfully accomplished the accuracy, and are balanced, and the accuracy is stable, can effectively promote unmanned aerial vehicle power percent 40. Its mode of utilizing the evacuation makes fibre layers compaction in integrated into one piece's frame surfaces, and the simple preparation is effective. The utility model discloses the manufacturing cost who makes unmanned aerial vehicle reduces percent 50, and the time limit for a project shortens more than the twice. Additionally, the utility model provides a but material recycle to has the environmental protection advantage.
Description
Technical field
The utility model is related to unmanned plane field, unmanned plane machine of specifically a kind of wing diagonal more than one meter
Body and its wing.
Background technology
Traditional unmanned aerial vehicle body manufacture is first to do mould or mold, and carbon fiber is pasted on mould or mold and tree is brushed
Fat liquid, has done again one layer of brush, then pastes one layer of carbon fiber, finally deviates from mould, and time-consuming to take a lot of work, low precision also has environment
The problem of pollution, the unmanned plane main screw lift of this method manufacture cannot be reduced, and cost of labor is high, and venue cost is big.
Utility model content
The purpose of this utility model is just to provide a kind of unmanned plane and its wing, is manufactured with solving unmanned plane in the prior art
Flow is complicated, the low technical problem of work efficiency.
What the utility model was realized in：
A kind of unmanned aerial vehicle body, includes the integrally formed hollow resin framework of accumulation technology and cladding receipts are pressed on institute
State the carbon fiber layer outside resin thin-walled framework；The carbon fiber layer is the carbon cloth of pre-soaked resin.
Under above-mentioned technical proposal, the utility model can be achieved in that：
The carbon fiber layer is the single-layer bidirectional carbon cloth of pre-soaked resin.
The carbon fiber layer outside is formed with smooth surface resin decorating layer.
The manufacture method of unmanned aerial vehicle body, comprises the following steps：
A. integrally formed hollow resin framework is prepared using accumulation molding technology；
B. hollow resin frame outer surface will be covered on by the two-way carbon cloth of resin impregnated, forms carbon fiber layer；
C. the solid object surface for making the carbon fiber layer be compacted at the resinous framework being in contact with it obtains early-products；
In the manufacture method of described unmanned aerial vehicle body, the carbon fiber layer is set to be compacted at the resinous framework that is in contact with it
Solid object surface obtains early-products, is realized by following steps：
A. in the carbon fiber layer outer cover sack type film material；
B. the sack to the sack type film material is vacuumized, and film material and carbon fiber layer is received successively and is pressed on institute
State hollow resin framework layer surface；
C. insert solidification case elevated cure and remove sack type film material again and obtain early-products.
In the manufacture method of described unmanned aerial vehicle body, the carbon fiber layer is set to be compacted at the resinous framework that is in contact with it
Solid object surface obtains early-products, it is also possible to realized by following steps：
A. heat-shrinkage material is swathed outside the carbon fiber layer；
B. a step products are placed in heating space and are heated, shrink the heat-shrinkage material, by carbon fiber layer compacting
In the hollow resin framework layer surface；
C. removal heat-shrinkage material obtains final product early-products.
In the manufacture method of described unmanned aerial vehicle body, hollow tree will be covered on by the two-way carbon cloth of resin impregnated
Fat frame outer surface formed carbon fiber layer the step of be：
The carbon fiber layer is by the two-way carbon cloth some sheet material groups corresponding with the hollow resin frame shape
Into some sheet material edges overlap to form cladding carbon fiber layer；
Or：The correct formation of the two-way carbon fiber of monoblock is coated on outside the hollow resin framework, excess stock is wiped out,
Make to overlap formation cladding carbon fiber layer between each adjacent sheared edge.
In the manufacture method of described unmanned aerial vehicle body, incrustation is carried out to the early-products surface and processes to obtain unmanned plane
Fuselage.
Refer to that two-way carbon is fine by the two-way carbon cloth of resin impregnated in the preparation method of described unmanned aerial vehicle body
Wei Bu is padded in single component epoxy and is rolled except Excess resin by double roller again, and pick-up 25-35wt%, then two-sided envelope is not glued
Film clot is standby.
Described unmanned plane wing, includes the integrally formed hollow resin framework of accumulation technology and cladding receipts are pressed on institute
State the carbon fiber layer outside resinous framework；The carbon fiber layer is the carbon cloth of pre-soaked resin.
Described unmanned plane wing, the carbon fiber layer is the single-layer bidirectional carbon cloth of pre-soaked resin.
Described unmanned plane wing, the carbon fiber layer outside is formed with smooth surface resin decorating layer.
The manufacture method of unmanned plane wing, comprises the following steps：
A. integrally formed hollow resin wing framework is prepared using accumulation molding technology；
B. hollow resin wing frame outer surface is covered on by the two-way carbon cloth of resin impregnated, forms carbon fiber
Layer；
C. the solid object surface for making the carbon fiber layer compacting be covered on the resinous framework being in contact with it obtains early-products；
D. the early-products are carried out with incrustation and processes to obtain unmanned plane wing.
The utility model patent carries out unmanned machine frame and is integrally formed using 3D printing technique, by artificial after framework shaping
Some resin prepreg carbon cloths that the drawing for being provided according to three-dimensional data in advance is cut are attached to frame outer surface, by film
The form or the form of winding fillet line class heat-shrinkage material that shape material is vacuumized compress carbon cloth and then make it viscous with framework
Connect closely, place into solidification case elevated cure, you can produce it is firm precision unmanned plane semi-finished product, then by surface aesthetic at
Reason gets product.
The manufacture method of unmanned aerial vehicle body of the present utility model, the moulding for efficiently solving unmanned plane is difficult, each wing it
Between cannot balance, the elevation angle of end motor cannot install accurately, many technical problems such as precision cannot ensure, successfully realize standard
Really, balance, accurately, stabilization can effectively lift unmanned mechanomotive force 40 percent.It makes carbon fiber using the mode for vacuumizing
Layer is compacted at integrally formed framework surface, and method is simple and effective.The utility model makes the manufacturing cost reduction percentage of unmanned plane
50, the duration shorten twice more than.In addition, the material recoverable in the utility model, so as to have environment-friendly advantage.
Brief description of the drawings
Fig. 1 is the structural representation of unmanned plane of the present utility model.
Specific embodiment
Below in conjunction with the accompanying drawings, the utility model is illustrated, but the explanation does not constitute any limitation to the utility model.
Shown in Fig. 1, unmanned plane includes fuselage 1 and wing 2.Fuselage 1 is identical with the shell structure of wing 2, is by piling up
The integrally formed hollow resin thin-walled framework of technology and cladding receive the carbon fiber layer composition being pressed on outside the resin thin-walled framework.
Carbon fiber layer is the single-layer bidirectional carbon cloth of pre-soaked resin.Single-layer bidirectional carbon cloth can be from longitude and latitude carbon fiber layer outside
It is formed with smooth surface resin decorating layer.With reference to Fig. 1, the shell structure of wing is from inside to outside hollow resin thin-walled framework 21, carbon fiber
Layer 22 and smooth surface resin decorating layer 23 are constituted.
Embodiment 1
The two-way carbon cloth of thread count identical is padded in single component epoxy and is rolled except unnecessary by double roller again
Mucous membrane clot is not standby for resin, pick-up 25wt%, then two-sided envelope.
Unmanned aerial vehicle body, wing and upper lid, the manufacture method of lower cover are comprised the following steps：
A. it is that 3D printing technique prepares integrally formed hollow resin thin-walled framework using accumulation molding technology；
B. converted according to computer（Automatic computing）The drawing for being given cuts result, will be fine by the two-way carbon of resin impregnated
Wei Bu is cut into several cut-parts corresponding with the hollow resin thin-walled frame shape, after removing two-sided not mucous membrane, pastes
In hollow resin thin-walled frame outer surface, each adjacent materials edge overlaps the carbon to be formed and be coated on outside hollow resin thin-walled framework
Fibrage.
C. in the carbon fiber layer outer cover sack type film material；Sack to the sack type film material is vacuumized,
Film material and carbon fiber layer is received successively and be pressed on the hollow resin thin-walled ccf layer surface；Solidification case is inserted to heat up admittedly
Change, solidification temperature is 100~120 DEG C, hardening time is 1~3 hour.Sack type film material is removed again obtains early-products.To institute
Obtaining early-products surface carries out incrustation treatment.
D. fuselage, wing and propeller are assembled after the completion of incrustation, and circuit control is installed in casing
Plate, battery, install motor, propeller outside casing, complete all manufactures.
Embodiment 2
The two-way carbon cloth of thread count identical is padded in single component epoxy and is rolled except unnecessary by double roller again
Mucous membrane clot is not standby for resin, pick-up 35wt%, then two-sided envelope.
The manufacture method of unmanned aerial vehicle body is comprised the following steps：
A. it is that 3D printing technique prepares integrally formed hollow resin thin-walled framework using accumulation molding technology；
B. by after the two-way carbon cloth of the monoblock of resin impregnated removes two-sided not mucous membrane, enemy forms and is coated on institute
State outside hollow resin framework, wipe out excess stock, make to overlap formation cladding carbon fiber layer between each adjacent sheared edge.
C. heat-shrinkage material is swathed outside the carbon fiber layer；Be placed in heating in heating space, heating-up temperature for 100~
120 DEG C, the time is 1~3 hour.Shrink the heat-shrinkage material and be compacted at the hollow resin with by the carbon fiber layer
Thin-walled ccf layer surface；Removal heat-shrinkage material obtains final product early-products.Incrustation treatment is carried out to gained early-products surface, is completed
The manufacture of fuselage.
Claims (6)
1. a kind of unmanned aerial vehicle body, it is characterised in that include the integrally formed hollow resin framework of accumulation technology and cladding
Receipts are pressed on the carbon fiber layer outside the resinous framework；The carbon fiber layer is the carbon cloth of pre-soaked resin.
2. unmanned aerial vehicle body according to claim 1, it is characterised in that the carbon fiber layer is double for the individual layer of pre-soaked resin
To carbon cloth.
3. unmanned aerial vehicle body according to claim 1, it is characterised in that the carbon fiber layer outside is formed with smooth surface resin dress
Decorations layer.
4. a kind of unmanned plane wing, it is characterised in that include the integrally formed hollow resin framework of accumulation technology and cladding
Receipts are pressed on the carbon fiber layer outside the resinous framework；The carbon fiber layer is the carbon cloth of pre-soaked resin.
5. unmanned plane wing according to claim 4, it is characterised in that the carbon fiber layer is double for the individual layer of pre-soaked resin
To carbon cloth.
6. unmanned plane wing according to claim 4, it is characterised in that the carbon fiber layer outside is formed with smooth surface resin dress
Decorations layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621091278.5U CN206170665U (en) | 2016-09-29 | 2016-09-29 | Unmanned aerial vehicle fuselage and wing thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621091278.5U CN206170665U (en) | 2016-09-29 | 2016-09-29 | Unmanned aerial vehicle fuselage and wing thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206170665U true CN206170665U (en) | 2017-05-17 |
Family
ID=58676931
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621091278.5U Expired - Fee Related CN206170665U (en) | 2016-09-29 | 2016-09-29 | Unmanned aerial vehicle fuselage and wing thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206170665U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106217894A (en) * | 2016-09-29 | 2016-12-14 | 河北大艾智能科技股份有限公司 | A kind of big-and-middle-sized unmanned aerial vehicle body and fuselage, the manufacture method of wing |
-
2016
- 2016-09-29 CN CN201621091278.5U patent/CN206170665U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106217894A (en) * | 2016-09-29 | 2016-12-14 | 河北大艾智能科技股份有限公司 | A kind of big-and-middle-sized unmanned aerial vehicle body and fuselage, the manufacture method of wing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103962510B (en) | Dead size core mould moulding process | |
| CN105346105B (en) | The making mould and preparation method of a kind of wind electricity blade | |
| CN104385624A (en) | Forming method for composite material barrel shell employing horizontal installation | |
| CN104669626A (en) | Combined line printing method and device for three-dimensional line printing objects | |
| CN206170665U (en) | Unmanned aerial vehicle fuselage and wing thereof | |
| CN105437537A (en) | Assembling method for airfoil total composite transonic flutter model | |
| CN109551789A (en) | A kind of preparation method that stickup angle is supported with polyurethane of blade of MW class wind turbine | |
| CN106670390B (en) | A kind of solvable sand core forming method of band Dome winding shell | |
| CN204773155U (en) | Combined material paddle forming die | |
| CN106945212B (en) | A kind of casting process method for assembling calcium alginate hydrogel CAH artificial-muscle | |
| CN106217894A (en) | A kind of big-and-middle-sized unmanned aerial vehicle body and fuselage, the manufacture method of wing | |
| CN105484456B (en) | A kind of preparation method of the compact-panel twisted plate of architectural decoration | |
| CN113021916A (en) | Bonding module and size design method thereof, wind power blade and bonding method thereof | |
| CN204526187U (en) | A kind of hermetically-sealed construction of wind electricity blade pre-embedded bolt cover termination | |
| CN106363927A (en) | Shell structure and manufacturing method thereof | |
| CN107364049B (en) | Wind electricity blade girder mold rib production method and wind electricity blade girder mold | |
| CN106644935A (en) | Method and apparatus for measuring bonding force between graphite and binder of negative electrode of lithium battery | |
| CN206106487U (en) | Hollow helix oar | |
| CN109291466A (en) | A kind of forming method of big chamfering honeycomb sandwich construction part | |
| CN104260353A (en) | Rapid molding system and rapid molding method | |
| CN103434079A (en) | Machining method for mobile phone model product part having carbon-fiber effect | |
| CN206673787U (en) | A kind of insulation system at die stamping insulation motor bar and head | |
| CN207337283U (en) | A kind of notebook cover | |
| CN101934564A (en) | Shearing rib male die, manufacture method thereof, female die and blades | |
| CN109591347B (en) | Method for manually processing honeycomb chamfer |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170517 Termination date: 20210929 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |