CN111098532B - Method for assembling and molding aircraft cockpit glass and cockpit special-shaped mouth frame - Google Patents
Method for assembling and molding aircraft cockpit glass and cockpit special-shaped mouth frame Download PDFInfo
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- CN111098532B CN111098532B CN201811263489.6A CN201811263489A CN111098532B CN 111098532 B CN111098532 B CN 111098532B CN 201811263489 A CN201811263489 A CN 201811263489A CN 111098532 B CN111098532 B CN 111098532B
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- 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
- B29C71/00—After-treatment of articles without altering their shape; Apparatus therefor
- B29C71/02—Thermal after-treatment
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- 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
- B29C71/00—After-treatment of articles without altering their shape; Apparatus therefor
- B29C71/02—Thermal after-treatment
- B29C2071/027—Tempering, i.e. heating an object to a high temperature and quenching it
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Abstract
The invention belongs to a method for assembling and molding airplane cockpit glass and a special-shaped opening frame of a cockpit, which is mainly used for process control of replacing and manufacturing new cockpit glass in the process of overhaul of an airplane. According to the invention, through statistical analysis of technical states of different overhaul interval cockpit hatch frames and research on heating tempering compensation sizes and shapes of aviation organic glass with different shapes and thicknesses, the glass personalized assembling and forming process method and the requirements suitable for the glass personalized assembling and forming process method in the aircraft overhaul process are determined, and the problems of poor cockpit sealing effect, glass stress assembly and other potential safety hazards existing for a long time in the aircraft overhaul are solved. The method has low basic investment, simple process method and process control and good popularization and application value in the overhaul of various military and civil aviation airplanes.
Description
Technical Field
The invention relates to a method for assembling and molding a glass of a cockpit of an aircraft and a special-shaped cockpit hatch frame deviating from the design technical state.
Background
Every time the aircraft is used for a period of time, the aircraft body and the driving hatch frame can deform in different degrees, the shapes of the driving hatch frames are different, and most of the driving hatch frames deviate from the designed state. If the cockpit glass produced and molded according to the design pattern is directly installed, a gap is inevitably formed between the glass and the cockpit hatch frame, so that the sealing performance of the cockpit cannot be ensured; the forced assembly for eliminating the gap can cause assembly stress, the assembly stress can be from several megapascals to dozens of megapascals, the reliability and the service life of the cockpit glass can be directly influenced, and the potential safety hazard is very large.
In addition, each cockpit mouth frame of the flying airplane has different deformation conditions, the shape requirements of glass to be installed are different during trimming, and the requirement of individuation exists.
Therefore, the invention needs to invent a method for assembling and molding the aircraft cockpit glass and the special-shaped mouth frame, which can make corresponding 'personalized' glass according to the 'personalized' requirement of each aircraft, so that the two are mutually matched, and the generation of excessive assembly stress is avoided.
Disclosure of Invention
The invention aims to solve the existing problems and provides a method for assembling and forming the glass of the airplane cockpit and the special-shaped opening frame of the cockpit, which is mainly used for controlling the process of replacing and assembling new cockpit glass in the overhaul process of the airplane, realizing the coincidence of the new cockpit glass and the opening frames of different shapes, avoiding the assembly stress, meeting the requirements of assembly tightness and the like.
In order to achieve the purpose, the technical solution provided by the invention is as follows:
a method for assembling and molding aircraft cockpit glass and a special-shaped opening frame of a cockpit is characterized by comprising the following steps:
step 1) manufacturing a tempering mold
Manufacturing a tempering frame by taking the average radian of old pieces of glass of a plurality of airplanes as a reference;
step 2) manufacturing a marking template
Sampling according to the average appearance of a plurality of old pieces of airplane glass, and manufacturing a marking template;
step 3) manufacturing the adjusting shim
According to empirical data after trial assembly of the mold tire forming glass, the maximum non-fitting degree of the glass and a plurality of airplane cockpit special-shaped mouth frame frameworks is not more than 15mm, so that the adjusting gasket is manufactured according to the following specifications:
no. 1: the length is 30mm, the width is 25mm, and the thickness is 1 mm;
no. 2: the length is 60mm, the width is 25mm, and the thickness is 2 mm;
no. 3: the length is 90mm, the width is 25mm, and the thickness is 3 mm;
no. 4: the length is 120mm, the width is 25mm, and the thickness is 4 mm;
no. 5: the length is 150mm, the width is 25mm, and the thickness is 5 mm;
no. 6: the length is 180mm, the width is 25mm, and the thickness is 6 mm;
no. 7: the length is 210mm, the width is 25mm, and the thickness is 7 mm;
no. 8: the length is 240mm, the width is 25mm, and the thickness is 8 mm;
step 4) scribing
Carrying out shape scribing processing on the glass blank formed according to the mould blank by using the scribing sample plate in the step 2), and cutting off redundant glass;
step 5) trial assembly
5.1) trial assembling the scribed glass blank, and recording the assembling clearance (namely the non-fitting amount);
5.2) selecting and matching a corresponding type of adjusting gasket according to the size of the assembly gap of the glass blank with the special-shaped opening frame framework of the cockpit, wherein the assembly gap of the glass blank is larger than 2.0mm, and carrying out step 6);
directly assembling the glass blank with the assembly clearance of the special-shaped mouth frame framework of the cockpit, which is less than or equal to 2.0mm, in the step 8) without correcting the shape;
step 6) calibrating
The selected adjusting shim is padded on the edge of the tempering frame according to the assembly gap and the length of the glass and the special-shaped mouth frame framework of the cockpit; tempering and correcting the glass blank subjected to trial assembly and scribing, correcting the radian of the glass to ensure that the non-bonding amount generated by the glass is consistent with the non-bonding amount of the glass at the corresponding position of the driving hatch frame, cooling the glass to room temperature along with a furnace, and taking out the glass;
step 7) trial fitting again
Trial assembling the glass blank after the shape correction in the step 6) again, and repeating the step 5);
step 8) assembling and forming
And assembling the glass meeting the requirements into the corresponding special-shaped opening frame of the cockpit.
Further, the dimensional parameters of the temper fixture, the scribe template, and the trim shim are determined by statistical analysis of historical data of the overhauled aircraft cockpit mouth frame for at least 50 different overhaul intervals.
Further, in 5.2), selecting and matching corresponding gaskets for the glass blank with the assembly clearance of more than 2.0mm with the special-shaped mouth frame framework of the cockpit according to the following mode;
when the assembly clearance is larger than 2.0mm and smaller than or equal to 6.0mm, the corresponding gasket selected is No. 1 to No. 4;
when the assembly clearance is larger than 6.0mm and smaller than or equal to 9.0mm, the corresponding gasket selected is No. 2 to No. 6;
when the assembly clearance is larger than 9.0mm and smaller than or equal to 12.0mm, the corresponding gasket selected is No. 3 to No. 7;
when the assembly clearance is larger than 12.0mm and smaller than or equal to 15.0mm, the corresponding gaskets are selected from No. 4 to No. 8.
Further, in the step 6), the tempering temperature is 70-80 ℃ and the time is 4-6 hours.
Further, in step 7), the number of times of repeating step 5) is at most 2, that is, the number of times of tempering and shape correction is at most 3 for the same piece of glass.
Further, in the step 3), the adjusting gasket is a wood gasket.
The invention has the beneficial effects that:
1. the method has the advantages of strong convenience and practicability, low resource input requirement, simple process flow and easy operation, and can be completed by personnel with basic professional skills; the used process equipment is conventional universal equipment and tools, and the operation and maintenance are simple; the whole production process is safe and environment-friendly; the potential quality safety hazard existing for a long time is solved, and the production operation efficiency is improved.
2. The invention is mainly used for the process control of replacing and manufacturing new cockpit glass in the process of overhaul of an airplane, and the size and the shape of aviation organic glass with different shapes and different thicknesses are compensated by heating and tempering so as to adapt to the 'individuation' requirement of a deformed cockpit mouth frame on the cockpit glass, thereby achieving the purposes of ensuring the sealing effect and avoiding the existence of assembly stress after the cockpit glass is assembled.
Drawings
FIG. 1 is a schematic view of the assembly of the present invention during glass sizing;
FIG. 2 is an enlarged view taken at A in FIG. 1;
FIG. 3 is a schematic view of a scribing template of the present invention;
fig. 4 is a cross-sectional view of a scribing template of the present invention.
The reference numbers are as follows:
1-glass; 2-adjusting the spacer; 3-tempering a fixture; 4-marking out the template.
Detailed Description
The invention is described in further detail below with reference to the following figures and specific examples:
the invention is based on the aviation organic glass heating tempering batch forming technology, and fully demonstrates the optimization and adjustment of the cooperative process flow and determines and provides the cockpit glass manufacturing, assembling and forming control technology in the aircraft overhaul process by counting, analyzing and summarizing the deformation condition of a cockpit hatch frame in the aircraft overhaul process and researching the glass personalized forming tooling requirement, process method, process control and the like.
Wherein, the 'personalized' assembling and forming process method comprises the following steps: according to the actual shape and size of the cockpit mouth frame of the single-time airplane, in the cockpit glass forming process, gaskets with different specifications and sizes are paved at different positions of the fixed tempering frame for heating rebound treatment, namely, the glass is made to generate adaptive and proper rebound amount according to different personalized shape requirements.
Optimizing a synergistic process flow: under the conditions that original machine glass is not decomposed and the shape of the cockpit mouth frame cannot be determined in time, adaptive marking and processing methods such as a tempering frame, a marking template and 8 groups of adjusting gaskets are determined through statistical analysis of historical data of 50 overhauled aircraft cockpit mouth frames at different overhaul intervals, equivalent batch processing and pre-manufacturing preparation are realized, and the production operation efficiency is greatly improved.
The invention discloses a method for assembling and molding aircraft cockpit glass and a special-shaped mouth frame, which comprises the following specific steps: the method comprises the following steps of processing and forming a glass blank, manufacturing a tempering frame, manufacturing a marking template, manufacturing an adjusting gasket, marking the appearance of the glass blank, selecting a gasket group, trial assembling, tempering and correcting, trial assembling again, tempering and supplementing correction if necessary, assembling and testing the sealing property.
Step 1) manufacturing a tempering mold
Statistical analysis is carried out on historical data of the overhauled airplane cockpit mouth frame with at least 50 different overhaul intervals, and a tempering frame 3 is manufactured according to the average radian of old airplane glass as a reference, as shown in figure 1;
step 2) manufacturing a marking template
Statistically analyzing historical data of the overhauled airplane cockpit mouth frame with at least 50 different overhaul intervals, sampling according to the average appearance of old airplane glass, and manufacturing a marking template 4 as shown in figures 3 and 4;
step 3) manufacturing the adjusting shim
According to empirical data after trial assembly of the mold tire forming glass, the maximum non-fitting degree of the glass and a plurality of airplane cockpit special-shaped mouth frame frameworks is not more than 15mm, a wooden adjusting gasket 2 is manufactured, and the model is as follows:
| adjusting shim | Length of | Width of | Thickness of |
| |
30mm | 25mm | 1mm |
| Number 2 | 60mm | 25mm | 2mm |
| No. 3 | 90mm | | 3mm |
| Number | |||
| 4 | 120mm | 25mm | 4mm |
| Number 5 | 150mm | 25mm | 5mm |
| Number 6 | 180mm | 25mm | 6mm |
| No. 7 | 210mm | 25mm | 7mm |
| Number 8 | 240mm | 25mm | 8mm |
Step 4) scribing
Carrying out shape scribing on the glass blank formed according to the mould blank by using the scribing sample plate 2 in the step 2), and cutting off redundant glass;
step 5) trial assembly
5.1) trial assembling the scribed glass blank, and recording the assembling clearance (namely the non-fitting amount);
5.2) selecting and matching a wood adjusting gasket with a corresponding type according to the size of the assembling clearance for a glass 1 blank with the assembling clearance of the special-shaped mouth frame framework of the cockpit being larger than 2.0mm, and carrying out step 6); the specific matching method is carried out in the following way:
when the assembly clearance is larger than 2.0mm and smaller than or equal to 6.0mm, the corresponding gasket selected is No. 1 to No. 4;
when the assembly clearance is larger than 6.0mm and smaller than or equal to 9.0mm, the corresponding gasket selected is No. 2 to No. 6;
when the assembly clearance is larger than 9.0mm and smaller than or equal to 12.0mm, the corresponding gasket selected is No. 3 to No. 7;
when the assembly clearance is larger than 12.0mm and smaller than or equal to 15.0mm, the corresponding gasket selected is No. 4 to No. 8;
and directly carrying out step 8) assembly on the glass blank with the assembly clearance of the special-shaped mouth frame framework of the cockpit being less than or equal to 2.0 mm;
step 6) calibrating
The edge of the tempering frame is padded with the selected adjusting gasket according to the assembly gap and the length of the glass and the special-shaped opening frame framework of the cockpit, and the glass is clamped on the tempering frame, as shown in figures 1 and 2; tempering and correcting the shape, wherein the tempering temperature is 70-80 ℃, the time is 4-6 hours, the radian of the glass is corrected, the non-bonding amount generated by the glass is consistent with the non-bonding amount of the corresponding position of the glass and a driving hatch frame, the glass is cooled to room temperature along with a furnace, and the glass is taken out;
step 7) trial fitting again
Trial assembling the glass subjected to the shape correction in the step 6) again, and repeating the step 5); wherein, the number of times of tempering and shape correction is at most 3 times aiming at the same piece of glass.
Step 8) assembling and forming
And assembling the glass meeting the requirements into the corresponding special-shaped opening frame of the cockpit.
And a sealing test is carried out after the assembling and forming so as to ensure the safety.
The reliability of the method is fully verified after a plurality of tests are carried out by adopting the method; through a large number of tests, the method is proved to carry out personalized correction on the glass, the production efficiency of the assembled glass is greatly improved, meanwhile, the density loss of a cabin and the fault repair rate of glass cracks are greatly reduced, and the production cost and the maintenance cost are effectively controlled.
While the invention has been described with reference to specific embodiments, the invention is not limited thereto, and various equivalent modifications or substitutions can be easily made by those skilled in the art within the technical scope of the present disclosure.
Claims (6)
1. A method for assembling and molding aircraft cockpit glass and a special-shaped opening frame of a cockpit is characterized by comprising the following steps:
step 1) manufacturing a tempering mold
Manufacturing a tempering frame by taking the average radian of old pieces of glass of a plurality of airplanes as a reference;
step 2) manufacturing a marking template
Sampling according to the average appearance of a plurality of old pieces of airplane glass, and manufacturing a marking template;
step 3) manufacturing the adjusting shim
Manufacturing an adjusting gasket according to the following specifications:
no. 1: the length is 30mm, the width is 25mm, and the thickness is 1 mm;
no. 2: the length is 60mm, the width is 25mm, and the thickness is 2 mm;
no. 3: the length is 90mm, the width is 25mm, and the thickness is 3 mm;
no. 4: the length is 120mm, the width is 25mm, and the thickness is 4 mm;
no. 5: the length is 150mm, the width is 25mm, and the thickness is 5 mm;
no. 6: the length is 180mm, the width is 25mm, and the thickness is 6 mm;
no. 7: the length is 210mm, the width is 25mm, and the thickness is 7 mm;
no. 8: the length is 240mm, the width is 25mm, and the thickness is 8 mm;
step 4) scribing
Carrying out shape scribing processing on the glass blank formed according to the mould blank by using the scribing sample plate in the step 2);
step 5) trial assembly
5.1) trial assembling the scribed glass blank, and recording the assembling clearance;
5.2) selecting and matching a corresponding type of adjusting gasket according to the size of the assembly gap of the glass blank with the special-shaped opening frame framework of the cockpit, wherein the assembly gap of the glass blank is larger than 2.0mm, and carrying out step 6);
selecting corresponding gaskets for a glass blank with an assembly clearance larger than 2.0mm with a special-shaped mouth frame framework of a cockpit according to the following mode;
when the assembly clearance is larger than 2.0mm and smaller than or equal to 6.0mm, the corresponding gasket selected is No. 1 to No. 4;
when the assembly clearance is larger than 6.0mm and smaller than or equal to 9.0mm, the corresponding gasket selected is No. 2 to No. 6;
when the assembly clearance is larger than 9.0mm and smaller than or equal to 12.0mm, the corresponding gasket selected is No. 3 to No. 7;
when the assembly clearance is larger than 12.0mm and smaller than or equal to 15.0mm, the corresponding gasket selected is No. 4 to No. 8;
carrying out step 8) on the glass blank with the assembly clearance with the special-shaped mouth frame framework of the cockpit being less than or equal to 2.0 mm;
step 6) calibrating
The selected adjusting shim is padded on the edge of the tempering frame according to the assembly gap and the length of the glass and the special-shaped mouth frame framework of the cockpit; tempering and correcting the glass blank subjected to trial assembly and scribing, correcting the radian of the glass, cooling to room temperature along with a furnace, and taking out;
step 7) trial fitting again
Trial assembling the glass blank after the shape correction in the step 6) again, and repeating the step 5);
step 8) assembling and forming
And assembling the glass meeting the requirements into the corresponding special-shaped opening frame of the cockpit.
2. The method of claim 1, wherein: and determining the size parameters of the tempering fixture, the marking template and the adjusting shim by performing statistical analysis on historical data of the overhauled airplane cockpit mouth frame of at least 50 different overhaul intervals.
3. The method according to claim 1 or 2, characterized in that: in the step 6), the tempering temperature is 70-80 ℃ and the time is 4-6 hours.
4. The method of claim 1, wherein: in step 7), the number of times of repeating step 5) is at most 2 times.
5. The method of claim 3, wherein: in step 7), the number of times of repeating step 5) is at most 2 times.
6. The method of claim 1, wherein: in the step 3), the adjusting gasket is a wood gasket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811263489.6A CN111098532B (en) | 2018-10-28 | 2018-10-28 | Method for assembling and molding aircraft cockpit glass and cockpit special-shaped mouth frame |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811263489.6A CN111098532B (en) | 2018-10-28 | 2018-10-28 | Method for assembling and molding aircraft cockpit glass and cockpit special-shaped mouth frame |
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|---|---|
| CN111098532A CN111098532A (en) | 2020-05-05 |
| CN111098532B true CN111098532B (en) | 2021-06-11 |
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| CN206243441U (en) * | 2016-09-07 | 2017-06-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of airplane windscreen mounting structure |
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2018
- 2018-10-28 CN CN201811263489.6A patent/CN111098532B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2003051772A1 (en) * | 2001-12-13 | 2003-06-26 | Graftech Inc. | Improved area weight uniformity flexible graphite sheet material |
| JP2010195080A (en) * | 2009-02-23 | 2010-09-09 | Central Glass Co Ltd | Method and device for bonding molding to glass sheet surface |
| CN102529127A (en) * | 2011-12-13 | 2012-07-04 | 江西洪都航空工业集团有限责任公司 | Adjustable organic glass annealing shaping frame |
| CN104854043A (en) * | 2012-12-14 | 2015-08-19 | Ppg工业俄亥俄公司 | Bending device for shaping glass for use in aircraft transparencies |
| CN105752312A (en) * | 2016-03-04 | 2016-07-13 | 江西洪都航空工业集团有限责任公司 | Glass compartment door structure of agriculture and forestry plane |
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| CN111098532A (en) | 2020-05-05 |
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