CN109703056A - A kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft - Google Patents
A kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft Download PDFInfo
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- CN109703056A CN109703056A CN201811475060.3A CN201811475060A CN109703056A CN 109703056 A CN109703056 A CN 109703056A CN 201811475060 A CN201811475060 A CN 201811475060A CN 109703056 A CN109703056 A CN 109703056A
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Abstract
The invention discloses a kind of production methods of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft, including molding die design, die surface processing, special-shaped airbag design, material selection, Lay up design and curing process parameter to set several big steps.The present invention using material property, sandwich sandwich, optimization design, using the interior moulding process for setting special-shaped airbag and combining molding, air pressure and hot press pressure collective effect are injected to special-shaped airbag by the external world, the equipment hatchcover of manufacture has high intensity, high rigidity, light-weight advantage, so that having great castering action to the safety of aerocraft system, protection, reliability using the product.
Description
Technical field
The present invention relates to unmanned vehicle technical field, the sandwich sandwich of specially a kind of multi-rotor aerocraft is set
The production method of standby hatchcover.
Background technique
In recent years, China's Aviation Industry technology development is advanced by leaps and bounds, and new material, new process, new equipment are improved day by day, fixed
Wing aircraft type, quantity gradually increase, and are commonly used for the fields such as national military affairs, civil aviaton's airline.And in power industry, fire-fighting
How efficiently, high-quality, rapid acquisition investigation information, dangerous situation letter industry, police's law enforcement, forest fire protection, agricultural such as are spread pesticides at the fields,
Breath, is sprayed insecticide at illegal record, and the significant problem that people need to solve is become.
The one kind of multi-rotor unmanned aerial vehicle as aviation aircraft is taken the photograph because its is small in size, flight is flexible, can carry various take photo by plane
Camera, extinguishing device, sprays insecticide device, structure is relatively easy, manufacturing cost is relatively small, using field than wide, and by
Institution of higher learning researcher, enterprise technology personnel pay high attention to.Currently, the flight control system of multi-rotor aerocraft, circuit system, behaviour
The electronic systems such as vertical system are all placed in fuselage interior, and the design and reasonable Arrangement of equipment hatchcover, to the safety of aerocraft system
Property, protection, reliability have significant impact.
Therefore, it is proposed that a kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft.
Summary of the invention
The purpose of the present invention is to provide a kind of production sides of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft
Method, the equipment hatchcover of manufacture have high intensity, high rigidity, light-weight advantage, so that using the product to aerocraft system
Safety, protection, reliability have great castering action, to solve the problems mentioned in the above background technology.
To achieve the above object, the invention provides the following technical scheme: a kind of sandwich interlayer knot of multi-rotor aerocraft
The production method of structure equipment hatchcover, comprising the following steps:
S1, molding die design:
Mold design is the combination die of upper mold and lower die cooperation, and tail portion design has inlet channel, and upper mold is equipped with positioning and leads
Column is provided with the fastening bolt holes matched with positioning guide column in lower die；
S2, die surface processing:
After the completion of Mold Making, die surface is cleared up using air gun, removal dust and remaining resin reuse
Detergent wipes die surface, spontaneously dries 5~10min at room temperature, is put into heating, temperature in baking oven and is set as 45~55 DEG C,
Time is set as 10~20min, reuses release agent brushing in die surface；
S3, special-shaped airbag design:
According to the structure of molding die inside cavity, special-shaped airbag shape is designed, special-shaped airbag is equipped with to be connected with inlet channel
The pipeline connect；
S4, material selection:
Select high intensity M30 fibre reinforced medium temperature system epoxy prepreg, establishment type 3K fibre reinforced medium temperature
System epoxy prepreg prepreg and PMI foam；
S5, Lay up design:
Using bottom mold surface as reference standard, first layer selects establishment type 3K fibre reinforced medium temperature system epoxy prepreg
Prepreg, middle layer select PMI foam, and being finally bonded angle is+45 °, -45 ° of selection high intensity M30 fibre reinforced medium temperature bodies
It is epoxy prepreg, ply angles are designed as the sandwich sandwich with foam layer；
S6, curing process parameter setting:
Hot press molding and the interior pressure for setting special-shaped airbag gas injection generation is selected to press in fact jointly, realization acts on equipment hatchcover
The temperature and pressure of product surface completes curing molding, and solidification temperature is 145~155 DEG C, and curing time is 45~55min, cold
But temperature is 10~20 DEG C, and cooling time is 25~35min.
Preferably, the material of the upper mold in the S1 and lower die is P20 steel.
Preferably, the detergent in the S2 is any one in MEK solvent and spirit solvent.
Preferably, the release agent in the S2 is brushed by the way of X, is brushed 3 times, every 10~20min of minor tick.
Preferably, the special-shaped airbag the selection of material in the S3 is high-temperature-resnylont nylont material.
Preferably, the FAW of the 3K fibre reinforced medium temperature system epoxy prepreg prepreg in the S4 is 198g/m2With
RC is 37%, and the FAW of high-intensitive M30 fibre reinforced medium temperature system epoxy prepreg is 75g/m2It is 37%, PMI with RC
Foam with a thickness of 0.5mm, density 80kg/m2。
Preferably, the hot press molding in the S6 is 35~45kg/cm2。
Preferably, in the S6 in set special-shaped airbag injection pressure as 150PSI.
Compared with prior art, the beneficial effects of the present invention are: the present invention using material property, sandwich sandwich,
Optimization design sets special-shaped airbag in conjunction with the moulding process of molding using interior, injects air pressure and hot pressing to special-shaped airbag by the external world
Machine pressure collective effect, the equipment hatchcover of manufacture has high intensity, high rigidity, light-weight advantage, so that using the product pair
The safety of aerocraft system, protection, reliability have great castering action.
Detailed description of the invention
Fig. 1 is equipment hatchcover structural schematic diagram of the invention；
Fig. 2 is another visual angle equipment hatchcover structural schematic diagram of the invention；
Fig. 3 is the molding die schematic diagram of equipment hatchcover of the invention；
Fig. 4 is the lower die schematic diagram of equipment hatchcover molding die of the invention；
Fig. 5 is the upper mold schematic diagram of equipment hatchcover molding die of the invention；
Special-shaped airbag schematic diagram is set in equipment compartment box cover die Fig. 6 of the invention
Fig. 7 is that six rotor unmanned aircraft equipment compartments of the invention assemble effect picture.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, below in conjunction with specific embodiment, to this
Invention is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, not
For limiting the present invention.
Embodiment 1
A kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft, comprising the following steps:
S1, molding die design:
Mold design is the combination die of upper mold and lower die cooperation, and tail portion design has inlet channel, and upper mold is equipped with positioning and leads
Column is provided with the fastening bolt holes matched with positioning guide column in lower die；
S2, die surface processing:
After the completion of Mold Making, die surface is cleared up using air gun, removal dust and remaining resin reuse
Detergent wipes die surface, spontaneously dries 5min at room temperature, is put into heating in baking oven, and temperature is set as 45 DEG C, time setting
For 10min, release agent brushing is reused in die surface；
S3, special-shaped airbag design:
According to the structure of molding die inside cavity, special-shaped airbag shape is designed, special-shaped airbag is equipped with to be connected with inlet channel
The pipeline connect；
S4, material selection:
Select high intensity M30 fibre reinforced medium temperature system epoxy prepreg, establishment type 3K fibre reinforced medium temperature
System epoxy prepreg prepreg and PMI foam；
S5, Lay up design:
Using bottom mold surface as reference standard, first layer selects establishment type 3K fibre reinforced medium temperature system epoxy prepreg
Prepreg, middle layer select PMI foam, and being finally bonded angle is+45 °, -45 ° of selection high intensity M30 fibre reinforced medium temperature bodies
It is epoxy prepreg, ply angles are designed as the sandwich sandwich with foam layer；
S6, curing process parameter setting:
Hot press molding and the interior pressure for setting special-shaped airbag gas injection generation is selected to press in fact jointly, realization acts on equipment hatchcover
The temperature and pressure of product surface completes curing molding, and solidification temperature is 145 DEG C, curing time 45min, and cooling temperature is
10 DEG C, cooling time 25min.
Specifically, the material of upper mold and lower die in the S1 is P20 steel.
Specifically, the detergent in the S2 is any one in MEK solvent and spirit solvent.
Specifically, the release agent in the S2 is brushed by the way of X, brush 3 times, every 10~20min of minor tick.
Specifically, the special-shaped airbag the selection of material in the S3 is high-temperature-resnylont nylont material.
Specifically, the FAW of the 3K fibre reinforced medium temperature system epoxy prepreg prepreg in the S4 is 198g/m2With
RC is 37%, and the FAW of high-intensitive M30 fibre reinforced medium temperature system epoxy prepreg is 75g/m2It is 37%, PMI with RC
Foam with a thickness of 0.5mm, density 80kg/m2。
Specifically, the hot press molding in the S6 is 35kg/cm2。
Specifically, in the S6 in set special-shaped airbag injection pressure as 150PSI.
Embodiment 2
A kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft, comprising the following steps:
S1, molding die design:
Mold design is the combination die of upper mold and lower die cooperation, and tail portion design has inlet channel, and upper mold is equipped with positioning and leads
Column is provided with the fastening bolt holes matched with positioning guide column in lower die；
S2, die surface processing:
After the completion of Mold Making, die surface is cleared up using air gun, removal dust and remaining resin reuse
Detergent wipes die surface, spontaneously dries 7min at room temperature, is put into heating in baking oven, and temperature is set as 50 DEG C, time setting
For 15min, release agent brushing is reused in die surface；
S3, special-shaped airbag design:
According to the structure of molding die inside cavity, special-shaped airbag shape is designed, special-shaped airbag is equipped with to be connected with inlet channel
The pipeline connect；
S4, material selection:
Select high intensity M30 fibre reinforced medium temperature system epoxy prepreg, establishment type 3K fibre reinforced medium temperature
System epoxy prepreg prepreg and PMI foam；
S5, Lay up design:
Using bottom mold surface as reference standard, first layer selects establishment type 3K fibre reinforced medium temperature system epoxy prepreg
Prepreg, middle layer select PMI foam, and being finally bonded angle is+45 °, -45 ° of selection high intensity M30 fibre reinforced medium temperature bodies
It is epoxy prepreg, ply angles are designed as the sandwich sandwich with foam layer；
S6, curing process parameter setting:
Hot press molding and the interior pressure for setting special-shaped airbag gas injection generation is selected to press in fact jointly, realization acts on equipment hatchcover
The temperature and pressure of product surface completes curing molding, and solidification temperature is 150 DEG C, curing time 50min, and cooling temperature is
15 DEG C, cooling time 30min.
Specifically, the material of upper mold and lower die in the S1 is P20 steel.
Specifically, the detergent in the S2 is any one in MEK solvent and spirit solvent.
Specifically, the release agent in the S2 is brushed by the way of X, brush 3 times, every minor tick 15min.
Specifically, the special-shaped airbag the selection of material in the S3 is high-temperature-resnylont nylont material.
Specifically, the FAW of the 3K fibre reinforced medium temperature system epoxy prepreg prepreg in the S4 is 198g/m2With
RC is 37%, and the FAW of high-intensitive M30 fibre reinforced medium temperature system epoxy prepreg is 75g/m2It is 37%, PMI with RC
Foam with a thickness of 0.5mm, density 80kg/m2。
Specifically, the hot press molding in the S6 is 40kg/cm2。
Specifically, in the S6 in set special-shaped airbag injection pressure as 150PSI.
Embodiment 3
A kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft, comprising the following steps:
S1, molding die design:
Mold design is the combination die of upper mold and lower die cooperation, and tail portion design has inlet channel, and upper mold is equipped with positioning and leads
Column is provided with the fastening bolt holes matched with positioning guide column in lower die；
S2, die surface processing:
After the completion of Mold Making, die surface is cleared up using air gun, removal dust and remaining resin reuse
Detergent wipes die surface, spontaneously dries 10min at room temperature, is put into heating in baking oven, and temperature is set as 55 DEG C, time setting
For 20min, release agent brushing is reused in die surface；
S3, special-shaped airbag design:
According to the structure of molding die inside cavity, special-shaped airbag shape is designed, special-shaped airbag is equipped with to be connected with inlet channel
The pipeline connect；
S4, material selection:
Select high intensity M30 fibre reinforced medium temperature system epoxy prepreg, establishment type 3K fibre reinforced medium temperature
System epoxy prepreg prepreg and PMI foam；
S5, Lay up design:
Using bottom mold surface as reference standard, first layer selects establishment type 3K fibre reinforced medium temperature system epoxy prepreg
Prepreg, middle layer select PMI foam, and being finally bonded angle is+45 °, -45 ° of selection high intensity M30 fibre reinforced medium temperature bodies
It is epoxy prepreg, ply angles are designed as the sandwich sandwich with foam layer；
S6, curing process parameter setting:
Hot press molding and the interior pressure for setting special-shaped airbag gas injection generation is selected to press in fact jointly, realization acts on equipment hatchcover
The temperature and pressure of product surface completes curing molding, and solidification temperature is 155 DEG C, curing time 55min, and cooling temperature is
20 DEG C, cooling time 35min.
Specifically, the material of upper mold and lower die in the S1 is P20 steel.
Specifically, the detergent in the S2 is any one in MEK solvent and spirit solvent.
Specifically, the release agent in the S2 is brushed by the way of X, brush 3 times, every minor tick 20min.
Specifically, the special-shaped airbag the selection of material in the S3 is high-temperature-resnylont nylont material.
Specifically, the FAW of the 3K fibre reinforced medium temperature system epoxy prepreg prepreg in the S4 is 198g/m2With
RC is 37%, and the FAW of high-intensitive M30 fibre reinforced medium temperature system epoxy prepreg is 75g/m2It is 37%, PMI with RC
Foam with a thickness of 0.5mm, density 80kg/m2。
Specifically, the hot press molding in the S6 is 45kg/cm2。
Specifically, in the S6 in set special-shaped airbag injection pressure as 150PSI.
In summary: the present invention using material property, sandwich sandwich, optimization design, using interior set special-shaped airbag
In conjunction with the moulding process of molding, air pressure and hot press pressure collective effect, the equipment of manufacture are injected to special-shaped airbag by the external world
Hatchcover has high intensity, high rigidity, light-weight advantage so that using the product to the safety of aerocraft system, protection,
Reliability has great castering action.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
Anyone skilled in the art in the technical scope disclosed by the present invention, according to the technique and scheme of the present invention and its
Inventive concept is subject to equivalent substitution or change, should be covered by the protection scope of the present invention.
Claims (8)
1. a kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft, which is characterized in that including following
Step:
S1, molding die design:
Mold design is the combination die of upper mold and lower die cooperation, and tail portion design has inlet channel, and upper mold is equipped with positioning guide column, under
The fastening bolt holes matched with positioning guide column are provided on mould；
S2, die surface processing:
After the completion of Mold Making, die surface is cleared up using air gun, removal dust and remaining resin reuse cleaning
Agent wipes die surface, spontaneously dries 5~10min at room temperature, is put into heating, temperature in baking oven and is set as 45~55 DEG C, the time
It is set as 10~20min, reuses release agent brushing in die surface；
S3, special-shaped airbag design:
According to the structure of molding die inside cavity, design special-shaped airbag shape, special-shaped airbag is equipped with to be connect with inlet channel
Pipeline；
S4, material selection:
Select high intensity M30 fibre reinforced medium temperature system epoxy prepreg, establishment type 3K fibre reinforced medium temperature system
Epoxy prepreg prepreg and PMI foam；
S5, Lay up design:
Using bottom mold surface as reference standard, first layer selects the preimpregnation of establishment type 3K fibre reinforced medium temperature system epoxy prepreg
Material, middle layer select PMI foam, and being finally bonded angle is+45 °, -45 ° of selection high intensity M30 fibre reinforced medium temperature system rings
Oxygen resin prepreg material, ply angles are designed as the sandwich sandwich with foam layer；
S6, curing process parameter setting:
Hot press molding and the interior pressure for setting special-shaped airbag gas injection generation is selected to press in fact jointly, realization acts on equipment hatchcover product
The temperature and pressure on surface completes curing molding, and solidification temperature is 145~155 DEG C, and curing time is 45~55min, cooling temperature
Degree is 10~20 DEG C, and cooling time is 25~35min.
2. a kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft according to claim 1,
It is characterized by: the material of upper mold and lower die in the S1 is P20 steel.
3. a kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft according to claim 1,
It is characterized by: the detergent in the S2 is any one in MEK solvent and spirit solvent.
4. a kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft according to claim 1,
It is characterized by: the release agent in the S2 is brushed by the way of X, brush 3 times, every 10~20min of minor tick.
5. a kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft according to claim 1,
It is characterized by: the special-shaped airbag the selection of material in the S3 is high-temperature-resnylont nylont material.
6. a kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft according to claim 1,
It is characterized by: the FAW of the 3K fibre reinforced medium temperature system epoxy prepreg prepreg in the S4 is 198g/m2It is with RC
37%, the FAW of high-intensitive M30 fibre reinforced medium temperature system epoxy prepreg is 75g/m2It is 37%, PMI foam with RC
With a thickness of 0.5mm, density 80kg/m2。
7. a kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft according to claim 1,
It is characterized by: the hot press molding in the S6 is 35~45kg/cm2。
8. a kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft according to claim 1,
It is characterized by: in the S6 in set special-shaped airbag injection pressure as 150PSI.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811475060.3A CN109703056A (en) | 2018-12-04 | 2018-12-04 | A kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft |
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| CN201811475060.3A CN109703056A (en) | 2018-12-04 | 2018-12-04 | A kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft |
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| CN201811475060.3A Pending CN109703056A (en) | 2018-12-04 | 2018-12-04 | A kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111002603A (en) * | 2019-12-12 | 2020-04-14 | 江苏亨睿碳纤维科技有限公司 | Manufacturing method of integrally formed automobile rear wing |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105563851A (en) * | 2016-02-04 | 2016-05-11 | 上海晋飞新材料科技有限公司 | Moulding process for fuselage of UAV (Unmanned Aerial Vehicle) |
| CN107738457A (en) * | 2017-11-02 | 2018-02-27 | 中广核俊尔新材料有限公司 | A kind of integrated forming technique of unmanned aerial vehicle body |
-
2018
- 2018-12-04 CN CN201811475060.3A patent/CN109703056A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105563851A (en) * | 2016-02-04 | 2016-05-11 | 上海晋飞新材料科技有限公司 | Moulding process for fuselage of UAV (Unmanned Aerial Vehicle) |
| CN107738457A (en) * | 2017-11-02 | 2018-02-27 | 中广核俊尔新材料有限公司 | A kind of integrated forming technique of unmanned aerial vehicle body |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111002603A (en) * | 2019-12-12 | 2020-04-14 | 江苏亨睿碳纤维科技有限公司 | Manufacturing method of integrally formed automobile rear wing |
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Application publication date: 20190503 |