CN109352963A - A kind of Aircraft Canopy Transparencies refractive power improvement and manufacturing process - Google Patents
A kind of Aircraft Canopy Transparencies refractive power improvement and manufacturing process Download PDFInfo
- Publication number
- CN109352963A CN109352963A CN201811205723.XA CN201811205723A CN109352963A CN 109352963 A CN109352963 A CN 109352963A CN 201811205723 A CN201811205723 A CN 201811205723A CN 109352963 A CN109352963 A CN 109352963A
- Authority
- CN
- China
- Prior art keywords
- transparent parts
- transparencies
- aircraft canopy
- manufacturing process
- refractive power
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C51/00—Shaping by thermoforming, i.e. shaping sheets or sheet like preforms after heating, e.g. shaping sheets in matched moulds or by deep-drawing; Apparatus therefor
- B29C51/10—Forming by pressure difference, e.g. vacuum
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C51/00—Shaping by thermoforming, i.e. shaping sheets or sheet like preforms after heating, e.g. shaping sheets in matched moulds or by deep-drawing; Apparatus therefor
- B29C51/26—Component parts, details or accessories; Auxiliary operations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C51/00—Shaping by thermoforming, i.e. shaping sheets or sheet like preforms after heating, e.g. shaping sheets in matched moulds or by deep-drawing; Apparatus therefor
- B29C51/26—Component parts, details or accessories; Auxiliary operations
- B29C51/42—Heating or cooling
- B29C51/421—Heating or cooling of preforms, specially adapted for thermoforming
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3079—Cockpits, canopies
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Re-Forming, After-Treatment, Cutting And Transporting Of Glass Products (AREA)
Abstract
The present invention relates to a kind of Aircraft Canopy Transparencies refractive power improvement and manufacturing process, belong to Aircraft Canopy Transparencies manufacturing technology field.Aircraft Canopy Transparencies optical distortion ameliorative way scheme is will be after production with side clout but optical distortion Transparent Parts to be improved in two sides are heated to organic glass softening temperature by former vacuum bag method in baking oven and partially carry out compacting improvement to distortion using the external pressure being vacuum formed.The improvement problem for solving to generate optical distortion after Aircraft Canopy Transparencies produce may be implemented in the process that the invention patent proposes；Transparent Parts forming technology can realize thin wall thickness, large scale, complicated multi-curvature Aircraft Canopy Transparencies manufacture.
Description
Technical field
The present invention relates to a kind of Aircraft Canopy Transparencies refractive power improvement and manufacturing process, belong to Aircraft Canopy Transparencies manufacture
Technical field.
Background technique
Canopy transparent materials are the critical structural components of aircraft, are normally at the forebody of aircraft, and structure is mostly deep camber class
Bubble type, as pilot's watch window, it needs to have excellent optical property.Military war craft compares civil aircraft,
Canopy transparent materials size is bigger, shape and shape curvature are more complicated, often by use material, production technology etc. control in it is unfavorable
It influences, generates optical distortion after leading to production, seriously affect service performance.Thus, it is tight to occurring after canopy transparent materials production
The product to distort again need to carry out optical property improvement.Current method be to optical distortion position carry out sanding and polishing processing, but
Only small to optical distortion, thicker canopy transparent materials product can place under repair, for relatively thin (5mm and below), distortion compared with
Greatly, the current method of the serious appearance undulatory product of " skirt " shape cannot improve distortion.
Summary of the invention
Present invention aims at large scale, the complicated multi-curvature shapes for a kind of 5mm and following Aircraft Canopy Transparencies
Feature proposes a kind of aircraft cockpit perspex transparent part optical distortion improvement and manufacturing process.It may be implemented by this method
The improvement problem of optical distortion is generated after solving Aircraft Canopy Transparencies production, and forms a kind of 5mm and following military operation and flies
The secondary forming process of machine canopy transparent materials.
The present invention to achieve the goals above, adopts the following technical scheme that
Aircraft Canopy Transparencies optical distortion ameliorative way scheme of the present invention is that have side clout but two sides after producing
Optical distortion Transparent Parts to be improved are heated to organic glass softening temperature by former vacuum bag method in baking oven and utilize vacuum
The external pressure of formation carries out compacting improvement to distortion part.
A kind of Aircraft Canopy Transparencies refractive power improvement and manufacturing process, method and step are as follows:
A, to shaping, there are the processing of the edges of the Transparent Parts of deformations to reserve surplus；
B, it is laid with flannelette on the concave surface on mold, is drawn in theoretical Transparent Parts on the flannelette laid using standard jig
Heart line and contours profiles line；
C, the center line long to end face is drawn on the inner surface near the front and back ends of optical distortion Transparent Parts to be improved, with
Transparent Parts center line and contours profiles line are positioned, and Transparent Parts are put into mold；
D, the edge of the flannelette package Transparent Parts of Transparent Parts will be stretched out；
E, sealant item, covering vacuum bag film are placed, and vacuum nozzle vacuum bag is installed to rout up die tip plane；
F, mold is pushed into baking oven after getting out above-mentioned work, vacuum nozzle is connected into the vacuum system in baking oven, but close true
Empty channel；
G, perspex transparent part is made to reach softening using baking oven heating, the temperature that baking oven is set is the softening temperature of organic glass
It is kept the temperature after angle value, soaking time is carried out by Transparent Parts forming technology plate pre-heating mean；
H, continue heat-insulation pressure keeping 10min~30min after close baking oven, to Transparent Parts cool to the furnace 60 DEG C or less take out it is transparent
Part.
Further, in step A: it is within 50mm that the edge processing of Transparent Parts, which reserves surplus,.
Further, in step B: flannelette is a kind of resistance to 150 DEG C of high temperature, and surface have the aircraft transparencies of fine hair at
Shape cloth.
Further, in step C: Transparent Parts center line is 50~100mm.
Further, in step D: the edge length of the flannelette package Transparent Parts of Transparent Parts will be stretched out are as follows: 50~100mm.
Further, in step G: so that perspex transparent part is reached softening, the temperature of baking oven setting using baking oven heating
For the softening temperature value of organic glass: YB-3 organic glass D softening temperature value is 115-125 DEG C.
Further, in step G: soaking time is carried out by Transparent Parts forming technology plate pre-heating mean: the organic glass of 3mm
Glass, soaking time are t=5 × 3min；5mm organic glass soaking time is t=5 × 5min, and vacuum passage is opened after heat preservation, is guaranteed
Vacuum pressure is in 0.06 MPa~0.09MPa.
Further, by the semi-finished articles for first vacuum contact forming technology being used to manufacture flat organic glass, so
Semi-finished articles are placed in mold afterwards and are shaped again once by the optical distortion ameliorative way that step A to G is proposed.
Beneficial effects of the present invention:
The process that the invention patent proposes may be implemented to generate changing for optical distortion after solving Aircraft Canopy Transparencies production
Kind problem；Transparent Parts forming technology can realize thin wall thickness, large scale, complicated multi-curvature Aircraft Canopy Transparencies manufacture.
Detailed description of the invention
Fig. 1 is the specific implementation structural schematic diagram that Aircraft Canopy Transparencies optical distortion of the invention improves；
Fig. 2 is the schematic diagram of step B of the invention；
Fig. 3 is the schematic diagram of step C of the invention；
Fig. 4 is the schematic diagram of step D of the invention；
Fig. 5 is the schematic diagram of step E of the invention.
Specific embodiment
Present invention will now be described in detail with reference to the accompanying drawings.:
(1) specific implementation method that Aircraft Canopy Transparencies optical distortion of the present invention improves:
To have side clout but two sides the optics canopy transparent materials to be improved that distort to pass through former vacuum bag method and drying after production
It is heated to softening temperature in case, compacting improvement is carried out to distortion part using the external pressure being vacuum formed, principle is as shown in Figure 1.It is grasped
Make process are as follows:
1. being reserved within theoretical surplus 50mm to being processed there are 6 edge of Transparent Parts of deformations for shaping；
2. as shown in Fig.1 and Fig.2, being laid with flannelette 5 on the concave surface on mold 1, flannelette is a kind of resistance to 150 DEG C of high temperature, and surface
Aircraft transparencies with fine hair shape dedicated cloth.The transparent of theory is drawn using standard jig on the flannelette laid
Part center line 8 and contours profiles line 9；
3. drawn on the inner surface near the front and back ends of optical distortion Transparent Parts 6 to be improved to end face and be about 50~
Then as shown in Figure 3 the center line of 100mm is positioned with center line 8 and contours profiles line 9, Transparent Parts 6 are put into mold
It is interior；
4. pressing Fig. 1, shown in Fig. 4, the flannelette 5 for stretching out Transparent Parts is wrapped up into 6 50~100mm of edge of Transparent Parts；
5. pressing Fig. 1, position shown in Fig. 5 places sealant item 3, covering vacuum bag film 4, and installs vacuum nozzle 7.Vacuum bag is answered
Rout up die tip plane, see Fig. 1,10 in Fig. 5 shown in；
6. mold is pushed into baking oven after getting out above-mentioned work, vacuum nozzle 7 is connected into the vacuum system in baking oven, but close
Vacuum passage；
7. making perspex transparent part reach softening using baking oven heating, the temperature that baking oven is set is the softening temperature of organic glass
Angle value (such as YB-3 organic glass is 115-125 DEG C) is kept the temperature afterwards, and soaking time presses Transparent Parts forming technology plate pre-heating mean
Carry out (such as: 3mm organic glass, soaking time are t=5 × 3min；5mm organic glass soaking time is t=5 × 5min), it protects
Vacuum passage is opened after temperature, guarantees vacuum pressure in 0.06 MPa~0.09MPa；
8. continue heat-insulation pressure keeping 10min~30min after close baking oven, to Transparent Parts cool to the furnace 60 DEG C or less take out it is transparent
Part 6.
(2) aircraft transparencies manufacturing process of the present invention is first to use vacuum contact forming technology by the organic glass of plate
Glass manufactures the semi-finished articles 6 for substantially conforming to shape, then semi-finished articles 6 is placed in mold 1 abnormal by optics proposed by the present invention
Become ameliorative way to shape again once.
It although an embodiment of the present invention has been shown and described, for the ordinary skill in the art, can be with
A variety of variations, modification, replacement can be carried out to these embodiments without departing from the principles and spirit of the present invention by understanding
And modification, the scope of the present invention is defined by the appended.
Claims (8)
1. a kind of Aircraft Canopy Transparencies refractive power improvement and manufacturing process, method and step are characterized in that:
A, to shaping, there are the processing of the edges of the Transparent Parts of deformations (6) to reserve surplus；
B, flannelette (5) are laid on the concave surface on mold (1), draw theory using standard jig on the flannelette (5) laid
Transparent Parts center line (8) and contours profiles line (9)；
C, the center line long to end face is drawn on the inner surface near the front and back ends of optical distortion Transparent Parts to be improved (6),
It is positioned with Transparent Parts center line (8) and contours profiles line (9), Transparent Parts (6) is put into mold；
D, the edge of flannelette (5) package Transparent Parts (6) of Transparent Parts will be stretched out；
E, sealant item (3), covering vacuum bag film (4) are placed, and vacuum nozzle (7) vacuum bag is installed should to rout up die tip flat
Face (10)；
F, mold is pushed into baking oven after getting out above-mentioned work, vacuum nozzle (7) are connected into the vacuum system in baking oven, but close
Vacuum passage；
G, perspex transparent part is made to reach softening using baking oven heating, the temperature that baking oven is set is the softening temperature of organic glass
It is kept the temperature after angle value, soaking time is carried out by Transparent Parts forming technology plate pre-heating mean；
H, baking oven is closed after continuing heat-insulation pressure keeping 10min~30min, cools to 60 DEG C or less taking-up Transparent Parts with the furnace to Transparent Parts
(6).
2. Aircraft Canopy Transparencies refractive power improvement according to claim 1 and manufacturing process, it is characterised in that: in step A:
It is within 50mm that the edge processing of Transparent Parts (6), which reserves surplus,.
3. Aircraft Canopy Transparencies refractive power improvement according to claim 1 and manufacturing process, it is characterised in that: in step B:
Flannelette (5) is a kind of resistance to 150 DEG C of high temperature, and there are the aircraft transparencies of fine hair to shape cloth on surface.
4. Aircraft Canopy Transparencies refractive power improvement according to claim 1 and manufacturing process, it is characterised in that: in step C:
Transparent Parts center line (8) is 50~100mm.
5. Aircraft Canopy Transparencies refractive power improvement according to claim 1 and manufacturing process, it is characterised in that: in step D:
The edge length of flannelette (5) package Transparent Parts (6) of Transparent Parts will be stretched out are as follows: 50~100mm.
6. Aircraft Canopy Transparencies refractive power improvement according to claim 1 and manufacturing process, it is characterised in that: in step G:
Perspex transparent part is set to reach softening using baking oven heating, the temperature that baking oven is set is the softening temperature value of organic glass:
YB-3 organic glass D softening temperature value is 115-125 DEG C.
7. Aircraft Canopy Transparencies refractive power improvement according to claim 1 and manufacturing process, it is characterised in that: in step G:
Soaking time is carried out by Transparent Parts forming technology plate pre-heating mean: 3mm organic glass, and soaking time is t=5 × 3min；5mm
Organic glass soaking time is t=5 × 5min, opens vacuum passage after heat preservation, guarantee vacuum pressure 0.06 MPa~
0.09MPa。
8. Aircraft Canopy Transparencies refractive power improvement according to claim 1 and manufacturing process, it is characterised in that: by first
Then semi-finished articles are placed in mold (1) by the semi-finished articles for being manufactured flat organic glass using vacuum contact forming technology
It is shaped again once by the optical distortion ameliorative way that step A to G is proposed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811205723.XA CN109352963A (en) | 2018-10-17 | 2018-10-17 | A kind of Aircraft Canopy Transparencies refractive power improvement and manufacturing process |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811205723.XA CN109352963A (en) | 2018-10-17 | 2018-10-17 | A kind of Aircraft Canopy Transparencies refractive power improvement and manufacturing process |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109352963A true CN109352963A (en) | 2019-02-19 |
Family
ID=65349353
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811205723.XA Pending CN109352963A (en) | 2018-10-17 | 2018-10-17 | A kind of Aircraft Canopy Transparencies refractive power improvement and manufacturing process |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109352963A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114147942A (en) * | 2021-10-18 | 2022-03-08 | 大连长丰实业总公司 | Manufacturing method of glass forming plate of aircraft canopy |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB762863A (en) * | 1953-07-17 | 1956-12-05 | Gen Electric Co Ltd | Improvements in or relating to methods of treating thermoplastic material |
| JPH0615731A (en) * | 1992-07-03 | 1994-01-25 | Copal Co Ltd | Warp correction method for carbon fiber reinforced composite resin sheet |
| CN101823335A (en) * | 2010-05-13 | 2010-09-08 | 苏州利盾航空材料有限公司 | High-pressure double-sided die hot bending process of aviation organic glass |
| CN101920558A (en) * | 2010-05-28 | 2010-12-22 | 北京航空航天大学 | Process window optimization method of resin-base composite curvature laminate in autoclave molding |
| JP5954700B2 (en) * | 2011-11-22 | 2016-07-20 | 福村 三樹郎 | Apparatus and method for thermoforming |
-
2018
- 2018-10-17 CN CN201811205723.XA patent/CN109352963A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB762863A (en) * | 1953-07-17 | 1956-12-05 | Gen Electric Co Ltd | Improvements in or relating to methods of treating thermoplastic material |
| JPH0615731A (en) * | 1992-07-03 | 1994-01-25 | Copal Co Ltd | Warp correction method for carbon fiber reinforced composite resin sheet |
| CN101823335A (en) * | 2010-05-13 | 2010-09-08 | 苏州利盾航空材料有限公司 | High-pressure double-sided die hot bending process of aviation organic glass |
| CN101920558A (en) * | 2010-05-28 | 2010-12-22 | 北京航空航天大学 | Process window optimization method of resin-base composite curvature laminate in autoclave molding |
| JP5954700B2 (en) * | 2011-11-22 | 2016-07-20 | 福村 三樹郎 | Apparatus and method for thermoforming |
Non-Patent Citations (2)
| Title |
|---|
| 吴兴敏 等: "《汽车整形与美容》", 31 August 2015, 北京理工大学出版社 * |
| 李在田: "《检验技术手册 第5分册 装配、试验及其他检验》", 30 October 1994, 国防工业出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114147942A (en) * | 2021-10-18 | 2022-03-08 | 大连长丰实业总公司 | Manufacturing method of glass forming plate of aircraft canopy |
| CN114147942B (en) * | 2021-10-18 | 2024-03-08 | 大连长丰实业总公司 | Manufacturing method of glass forming plate for aircraft cabin cover |
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| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190219 |
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| RJ01 | Rejection of invention patent application after publication |