CN117885256A - Part curing temperature monitoring method for temperature hysteresis area in margin line - Google Patents
Part curing temperature monitoring method for temperature hysteresis area in margin line Download PDFInfo
- Publication number
- CN117885256A CN117885256A CN202410292201.7A CN202410292201A CN117885256A CN 117885256 A CN117885256 A CN 117885256A CN 202410292201 A CN202410292201 A CN 202410292201A CN 117885256 A CN117885256 A CN 117885256A
- Authority
- CN
- China
- Prior art keywords
- thermocouple
- hysteresis
- temperature
- thermocouples
- area
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 24
- 238000012544 monitoring process Methods 0.000 title claims abstract description 17
- 238000012360 testing method Methods 0.000 claims abstract description 28
- 238000004519 manufacturing process Methods 0.000 claims abstract description 8
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 239000002131 composite material Substances 0.000 abstract description 3
- 238000000465 moulding Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 3
- 239000004744 fabric Substances 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000004806 packaging method and process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000805 composite resin Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
- B29C35/0288—Controlling heating or curing of polymers during moulding, e.g. by measuring temperatures or properties of the polymer and regulating the process
-
- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
-
- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Oral & Maxillofacial Surgery (AREA)
- Thermal Sciences (AREA)
- Moulding By Coating Moulds (AREA)
- Heating, Cooling, Or Curing Plastics Or The Like In General (AREA)
Abstract
The invention discloses a part curing temperature monitoring method of a temperature hysteresis region in a margin line, which belongs to the technical field of composite material curing molding, and is characterized in that a plurality of thermocouples are arranged in the temperature hysteresis region in the margin line of a part during a thermal distribution test; and placing a plurality of thermocouples wrapped by prepreg on the surface area of the tooling at the downstream of the part allowance line in the air flow direction. Then, determining a part hysteresis thermocouple in a margin line according to the curing temperature data of the part obtained by the thermal distribution test; and taking the thermocouple which is close to the temperature of the part hysteresis thermocouple in the surface area of the tool outside the part allowance line as an equivalent hysteresis thermocouple of the part. And during part production, an equivalent hysteresis thermocouple is placed in the area of the surface of the tooling to replace a part hysteresis thermocouple in a part allowance line. According to the invention, the thermocouple in the temperature hysteresis region inside the part allowance region is equivalent to the tool surface outside the part allowance region through the heat distribution test, so that the temperature of all regions in the part curing process is monitored, the situation that the thermocouple cannot be placed in the allowance region due to the temperature hysteresis region is avoided, and the method has good practicability.
Description
Technical Field
The invention belongs to the technical field of composite material molding, and particularly relates to a part curing temperature monitoring method in a residual line in a temperature hysteresis area.
Background
Resin-based composite materials are widely used in the aerospace field, and the manufacturing process mainly comprises laying, packaging and curing. The laying is to lay the prepreg layer by layer on the tooling, the packaging is to use vacuum auxiliary materials such as a vacuum bag, an airfelt, a separation film and the like to package the laid parts on the tooling, and the curing is to place the parts packaged on the tooling in an autoclave to be cured and formed under high temperature and high pressure environment. To ensure that the parts are fully cured in each region, thermocouples are placed in the lead and lag regions of the part temperature to monitor the temperature during curing.
As shown in FIG. 1, the specific locations of the lead and lag regions of the part are determined by thermal profile testing. If the lead thermocouple and the lag thermocouple determined by the heat distribution test are respectively positioned outside the margin line of the part, the lead thermocouple and the lag thermocouple can be placed at corresponding positions during the production of the formal part, and the temperature of the part curing process is monitored. For most honeycomb core sandwich parts, the part temperature rising hysteresis area is often positioned at the bottom of the honeycomb core due to the lower heat conduction coefficient of the honeycomb core, but in the process of producing a formal part, the thermocouple cannot be placed in the part allowance line, otherwise, foreign matters exist in the part, so that the strength is reduced.
Aiming at the parts, the traditional part hysteresis thermocouple placement method is that thermocouples are placed at the bottoms of the tools corresponding to the honeycomb cores when a heat distribution test is carried out, in order to ensure that the thermocouples placed at the bottoms of the tools are equivalent to the part hysteresis thermocouples, the thermocouples at the bottoms of the tools are required to be wrapped with air guide glass cloth with a certain thickness, and then the thermocouples wrapped with the air guide glass cloth are installed at the bottoms of the tools corresponding to the honeycomb cores in a tape or mechanical connection mode. However, the hysteresis thermocouple mounted at the bottom of the tooling in the manner described above suffers from the following significant drawbacks:
① In the autoclave curing process, the thermocouple is easy to fall off due to high-temperature air flow in the autoclave, so that curing data is distorted, and the temperature of a part temperature lag area cannot be monitored.
② The thermocouple is installed in the frock bottom, and the operation is very difficult, especially reaches tens meters to large-scale composite material part frock size, and the frock bottom is the bulkhead structure, and operating space is less, has very big potential safety hazard.
Disclosure of Invention
The invention aims to provide a part curing temperature monitoring method with a temperature hysteresis area in a margin line, and aims to solve the problems.
The invention is realized mainly by the following technical scheme:
A part curing temperature monitoring method with a temperature hysteresis area in a margin line comprises the following steps:
step S100: performing a heat distribution test to determine an equivalent hysteresis thermocouple of the part;
Firstly, in a thermal distribution test, placing a plurality of thermocouples in a temperature hysteresis area in a part allowance line; placing a plurality of thermocouples wrapped by prepreg in the surface area of the tooling at the downstream of the part allowance line in the air flow direction, wherein the number of wrapped layers is L/2+4i;
Wherein i is the placement number of the thermocouple, and i=0, 1,2,3 … m,
L is the number of layers of the part prepreg;
Then, determining a part hysteresis thermocouple in a margin line according to the curing temperature data of the part obtained by the thermal distribution test; taking a thermocouple which is close to the temperature of the part hysteresis thermocouple in the surface area of the tool outside the part allowance line as an equivalent hysteresis thermocouple of the part;
Step S200: and during part production, an equivalent hysteresis thermocouple is placed in the area of the surface of the tooling to replace a part hysteresis thermocouple in a part allowance line.
In order to better implement the present invention, further, in the step S100, a plurality of thermocouples are placed at any one or more areas of the honeycomb core bottom, the prepreg layup, and the downstream position in the airflow direction within the part margin line.
In order to better implement the present invention, further, the step S100 includes the steps of:
step S110: in the heat distribution test, thermocouples are arranged at different positions outside the part allowance line at the upstream of the air flow direction and are used for determining a part temperature lead area;
Step S120: thermocouples are arranged at different positions on the top of the honeycomb core in the part allowance line and are used for determining a part temperature hysteresis area;
step S130: thermocouples are arranged at different positions at the bottom of the honeycomb core in the part allowance line and are used for determining a part temperature hysteresis area;
Step S140: thermocouples are placed at different positions of the prepreg layer at the bottom of the honeycomb core in the part allowance line and used for determining a part temperature hysteresis area;
Step S150: outside the part allowance line, thermocouples are arranged at different positions in the downstream area of the tool part allowance line in the air flow direction and are used for determining equivalent hysteresis thermocouples of the part;
step S160: taking the thermocouple with the fastest temperature change in the step S110 as a leading thermocouple of the part; taking the thermocouple with the slowest temperature change in the steps S120-S140 as a part hysteresis thermocouple; and (3) taking the thermocouple with the temperature similar to that of the part hysteresis thermocouple in the step S150 as an equivalent hysteresis thermocouple of the part.
In order to better implement the present invention, further, in the step S110, several thermocouples are placed in the depth direction of the top prepreg.
In order to better implement the present invention, further, in the step S120, several thermocouples are placed in the depth direction between the honeycomb core and the upper prepreg.
To better implement the present invention, further, in the step S130, several thermocouples are placed in the depth direction between the honeycomb core and the lower prepreg; in the step S140, a plurality of thermocouples are placed in the depth direction of the honeycomb core bottom 4-layer prepreg height.
In order to better implement the present invention, further, in the step S200, thermocouples are placed according to the positions of the leading thermocouple and the equivalent lagging thermocouple of the part in the heat distribution test at the time of the production of the part.
The beneficial effects of the invention are as follows:
According to the invention, the thermocouple in the temperature hysteresis region inside the part allowance region is equivalent to the tool surface outside the part allowance region through the thermal distribution test, so that the monitoring of the temperatures of all regions in the part curing process is realized, the situation that the thermocouple cannot be placed in the allowance region due to the temperature hysteresis region is avoided, and the thermocouple has good practicability and good application prospect.
Drawings
FIG. 1 is a schematic diagram of a prior art part curing;
FIG. 2 is a schematic diagram of the placement of a thermocouple in a thermal profile test according to the present invention;
FIG. 3 is a top view of FIG. 2;
fig. 4 is a schematic diagram of the curing of the part of the present invention.
Wherein: 1-autoclave, 2-advanced thermocouple, 3-equivalent retarded thermocouple, 4-honeycomb core and 6-allowance line.
Detailed Description
Example 1:
A method for monitoring the solidifying temp of part with temp delaying area in the residual line features that several thermocouples are arranged in the residual line 6 of part, which is composed of the bottom of honeycomb core 4, thicker prepreg layer and downstream in airflow direction.
And placing a thermocouple wrapped by adopting the corner residual prepreg at the N position in the surface area of the tooling at the downstream of the part allowance line 6 in the air flow direction, wherein the wrapped layer number is L/2+4i (i=0, 1,2,3 …), and L is the layer number of the part prepreg.
And determining the part hysteresis thermocouple in the margin line 6 according to the part curing temperature data obtained by the thermal distribution test. And then, finding out an equivalent hysteresis thermocouple 3 which is close to the temperature of the part hysteresis thermocouple in the thermocouples in the area outside the part on the surface of the tool. When the parts are produced, the equivalent hysteresis thermocouple 3 is placed in the area of the surface of the tooling to replace the part hysteresis thermocouple in the part allowance area, so that the aim of monitoring the curing temperature of the whole area of the part is fulfilled.
Preferably, the invention comprises the following steps:
Step one: in the heat distribution test, the simulated part lead thermocouple 2 is placed at different positions at the part allowance zone 5 at the upstream of the air flow direction, and the placed position in the thickness direction is on the last 1-layer prepreg for simulating the temperature change in the part curing process. Specifically, as shown in FIGS. 2 and 3, the simulated part lead thermocouple 2 is placed in sequence at positions 1-1, 1-2, 1-3, 1-4, 1-5 outside the part margin area upstream in the gas flow direction for determining the part temperature lead area.
Step two: in the heat distribution test, the simulated part hysteresis thermocouple was placed at different positions on the top 5 of the honeycomb core 4, and the depth direction of placement was between the honeycomb core 4 and the upper-stage prepreg. Specifically, as shown in FIGS. 2 and3, simulated part hysteresis thermocouples are placed in sequence at the positions 3-1, 3-2, 3-3, 3-4, 3-5 on top of the honeycomb core 4 in the part margin area for determining the part temperature hysteresis area.
Step three: in the heat distribution test, the dummy part hysteresis thermocouple was placed at a different position at the bottom 5 of the honeycomb core 4, and the position in the depth direction of placement was between the honeycomb core 4 and the lower prepreg. Specifically, as shown in FIGS. 2 and 3, simulated part hysteresis thermocouples are placed at the positions 2-1, 2-2, 2-3, 2-4, 2-5, respectively, of the bottom of the honeycomb core 4 in the part margin area for determining the part temperature hysteresis area.
Step four: in the heat distribution test, the simulated part hysteresis thermocouple is placed at different positions at 5 positions where the prepreg at the bottom of the honeycomb core 4 is thicker, and the placed position in the depth direction is the position of the prepreg at the bottom 4 layers of the honeycomb core 4. Specifically, as shown in FIGS. 2 and 3, simulated part hysteresis thermocouples were placed at the 4-1, 4-2, 4-3, 4-4, 4-5 locations of the honeycomb core 4 bottom prepreg layup thicker region within the part margin zone, respectively, for determining the part temperature hysteresis region.
Step five: in the heat distribution test, an analog part equivalent hysteresis thermocouple 3 of L/2+4i (i=0, 1,2,3, 4) layer prepreg was wrapped at a different position at 10 places of the tooling surface area downstream in the gas flow direction outside the part. Specifically, as shown in fig. 2 and 3, in the area outside the tooling part and at the downstream of the air flow direction, two groups of dummy part equivalent hysteresis thermocouples 3 are symmetrically arranged at two ends, wherein the dummy part equivalent hysteresis thermocouples 3 are respectively arranged at different positions of 5-1, 5-2, 5-3, 5-4 and 5-5, wherein the number of layers of the thermocouple-wrapped prepreg at the 5-1 position is L/2+4, the number of layers of the thermocouple-wrapped prepreg at the 5-2 position is L/2+8, the number of layers of the thermocouple-wrapped prepreg at the 5-3 position is L/2+12, the number of layers of the thermocouple-wrapped prepreg at the 5-4 position is L/2+16, and the number of layers of the thermocouple-wrapped prepreg at the 5-5 position is L/2+20.
Step six: according to the curing temperature data of the parts obtained by the thermal distribution test, the thermocouple with the fastest temperature change in the 1-1, 1-2, 1-3, 1-4 and 1-5 positions of the simulated part lead thermocouples is taken as the part lead thermocouple 2, the thermocouple with the slowest temperature change in the 2-1, 2-2, 2-3, 2-4, 2-5, 3-1, 3-2, 3-3, 3-4, 3-5, 4-1, 4-2, 4-3, 4-4 and 4-5 positions of the simulated part lag thermocouples is taken as the part lag thermocouple, and the thermocouple with the temperature close to the part lag thermocouple in the two groups of 5-1, 5-2, 5-3, 5-4 and 5-5 positions of the simulated part lag thermocouples is taken as the part equivalent lag thermocouple 3.
Step six: in the production of the official parts, as shown in fig. 4, thermocouples were placed at positions of the leading thermocouple 2 and the equivalent lagging thermocouple 3 in the heat distribution test, and the depth position of placement of each thermocouple and the prepreg wrapping method were identical to those in the heat distribution test. Then, the parts packaged on the tool are placed in an autoclave 1 to be cured and molded at high temperature and high pressure.
According to the invention, the thermocouple in the temperature hysteresis region inside the part allowance region is equivalent to the tool surface outside the part allowance region through the thermal distribution test, so that the monitoring of the temperatures of all regions in the part curing process is realized, the situation that the thermocouple cannot be placed in the allowance region due to the temperature hysteresis region is avoided, and the thermocouple has good practicability and good application prospect.
The foregoing description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and any simple modification, equivalent variation, etc. of the above embodiment according to the technical matter of the present invention fall within the scope of the present invention.
Claims (7)
1. The part curing temperature monitoring method for the temperature hysteresis region in the margin line is characterized by comprising the following steps of:
Step S100: performing a heat distribution test to determine an equivalent hysteresis thermocouple (3) of the part;
firstly, in a heat distribution test, placing a plurality of thermocouples in a temperature hysteresis area in a part allowance line (6); placing a plurality of thermocouples wrapped by prepreg in the surface area of the tooling at the downstream of the part allowance line (6) in the air flow direction, wherein the number of wrapped layers is L/2+4i;
Wherein i is the placement number of the thermocouple, and i=0, 1,2,3 … m,
L is the number of layers of the part prepreg;
then, determining a part hysteresis thermocouple in a margin line (6) according to the curing temperature data of the part obtained by the thermal distribution test; taking a thermocouple which is close to the temperature of the part hysteresis thermocouple in the surface area of the tool except for the part allowance line (6) as an equivalent hysteresis thermocouple (3) of the part;
step S200: and during part production, an equivalent hysteresis thermocouple (3) is placed in the area of the tool surface to replace the part hysteresis thermocouple in the part allowance line (6).
2. The method for monitoring the curing temperature of a part with a temperature hysteresis area within a margin line according to claim 1, wherein in the step S100, a plurality of thermocouples are placed in any one or more areas among the bottom of the honeycomb core (4), the prepreg layup, and the downstream position in the airflow direction within the part margin line (6).
3. The method for monitoring the curing temperature of a part with a temperature hysteresis area within a margin line according to claim 1, wherein said step S100 comprises the steps of:
step S110: in the heat distribution test, thermocouples are arranged at different positions outside the part allowance line (6) at the upstream of the air flow direction and are used for determining the part temperature lead area;
step S120: thermocouples are arranged at different positions on the top of the honeycomb core (4) in the part allowance line (6) and are used for determining a part temperature hysteresis area;
step S130: thermocouples are arranged at different positions at the bottom of the honeycomb core (4) in the part allowance line (6) and are used for determining a part temperature hysteresis area;
Step S140: thermocouples are arranged at different positions of the prepreg layer at the bottom of the honeycomb core (4) in the part allowance line (6) and are used for determining a part temperature hysteresis area;
Step S150: outside the part allowance line (6), thermocouples are arranged at different positions in the downstream area of the tool part allowance line (6) in the air flow direction and are used for determining equivalent hysteresis thermocouples (3) of the part;
Step S160: taking the thermocouple with the fastest temperature change in the step S110 as a leading thermocouple (2) of the part; taking the thermocouple with the slowest temperature change in the steps S120-S140 as a part hysteresis thermocouple; the thermocouple with the temperature close to that of the part hysteresis thermocouple in the step S150 is taken as an equivalent hysteresis thermocouple (3) of the part.
4. A method for monitoring the curing temperature of a part with a temperature hysteresis area within a margin line according to claim 3, wherein in step S110, several thermocouples are placed in the depth direction of the prepreg of the top layer.
5. A method of monitoring the curing temperature of a part with a temperature hysteresis zone within a margin line according to claim 3, characterized in that in step S120, several thermocouples are placed in the depth direction between the honeycomb core (4) and the upper prepreg.
6. A method of monitoring the curing temperature of a part with a temperature hysteresis zone within a margin line according to claim 3, characterized in that in step S130, several thermocouples are placed in the depth direction between the honeycomb core (4) and the lower prepreg; in the step S140, a plurality of thermocouples are placed in the depth direction of the height of the 4-layer prepreg at the bottom of the honeycomb core (4).
7. A method for monitoring the curing temperature of a part with a temperature hysteresis zone in margin line according to any one of claims 3-6, characterized in that in step S200 thermocouples are placed according to the positions of the leading thermocouple (2) and the equivalent lagging thermocouple (3) of the part in the heat distribution test at the time of the production of the part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410292201.7A CN117885256B (en) | 2024-03-14 | 2024-03-14 | Part curing temperature monitoring method for temperature hysteresis area in margin line |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410292201.7A CN117885256B (en) | 2024-03-14 | 2024-03-14 | Part curing temperature monitoring method for temperature hysteresis area in margin line |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117885256A true CN117885256A (en) | 2024-04-16 |
| CN117885256B CN117885256B (en) | 2024-07-12 |
Family
ID=90652052
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410292201.7A Active CN117885256B (en) | 2024-03-14 | 2024-03-14 | Part curing temperature monitoring method for temperature hysteresis area in margin line |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117885256B (en) |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5885504A (en) * | 1995-10-25 | 1999-03-23 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Process for moulding high strength elongated parts made of a fibre-resin composite |
| US6391456B1 (en) * | 2000-08-08 | 2002-05-21 | Engineering Mechanics Corporation Of Columbus | Thermoplastic composite lumber having reinforcing laminate of unidirectional fibers |
| DE10352964B3 (en) * | 2003-11-13 | 2004-10-07 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Removing matrix resins from fiber-reinforced plastic components, preparatory to repair or joining, subjects defined region to microwave radiation |
| US20110121479A1 (en) * | 2008-02-27 | 2011-05-26 | Airbus Operations Gmbh | Forming Device for Manufacturing Profiled Semifinished Products, System with such a Forming Device and Method for Manufacturing Profiled Semifinished Products |
| CN103843460A (en) * | 2011-10-12 | 2014-06-04 | Dialog半导体有限公司 | Controllers for solid state light bulb assemblies |
| US20170232641A1 (en) * | 2016-02-12 | 2017-08-17 | The Boeing Company | Enhanced systems that facilitate vacuum bag curing of composite parts |
| CN206519899U (en) * | 2017-03-10 | 2017-09-26 | 成都联科航空技术有限公司 | A kind of modularization installs the frock of thermocouple |
| CN107391819A (en) * | 2017-07-07 | 2017-11-24 | 东南大学 | A kind of Forecasting Methodology of the hot relevant parameter of suture type thermal protection structure |
| CN109556877A (en) * | 2018-12-21 | 2019-04-02 | 成都飞机工业（集团）有限责任公司 | A kind of exhaust temperature of aircraft engine scaling method |
| CN112792391A (en) * | 2021-04-12 | 2021-05-14 | 成都飞机工业（集团）有限责任公司 | Inner-groove milling cutter and honeycomb material machining method based on inner-groove milling cutter |
| CN113203489A (en) * | 2021-03-31 | 2021-08-03 | 成都飞机工业（集团）有限责任公司 | Method for installing thermocouple on back of tool |
| CN113733600A (en) * | 2021-07-30 | 2021-12-03 | 昌河飞机工业（集团）有限责任公司 | Method for improving air tightness of autoclave molding thermocouple |
| US20220032560A1 (en) * | 2020-07-28 | 2022-02-03 | University Of South Carolina | 3D Printed Water Cooled Tow Guide for Fiber Placement Machine |
| CN115648666A (en) * | 2022-11-10 | 2023-01-31 | 江西昌河航空工业有限公司 | Method for determining optimal curing parameters of resin-based composite material |
| CN115758921A (en) * | 2022-10-27 | 2023-03-07 | 沈阳飞机工业（集团）有限公司 | Method for accurately controlling autoclave curing temperature rise |
-
2024
- 2024-03-14 CN CN202410292201.7A patent/CN117885256B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5885504A (en) * | 1995-10-25 | 1999-03-23 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Process for moulding high strength elongated parts made of a fibre-resin composite |
| US6391456B1 (en) * | 2000-08-08 | 2002-05-21 | Engineering Mechanics Corporation Of Columbus | Thermoplastic composite lumber having reinforcing laminate of unidirectional fibers |
| DE10352964B3 (en) * | 2003-11-13 | 2004-10-07 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Removing matrix resins from fiber-reinforced plastic components, preparatory to repair or joining, subjects defined region to microwave radiation |
| US20110121479A1 (en) * | 2008-02-27 | 2011-05-26 | Airbus Operations Gmbh | Forming Device for Manufacturing Profiled Semifinished Products, System with such a Forming Device and Method for Manufacturing Profiled Semifinished Products |
| CN103843460A (en) * | 2011-10-12 | 2014-06-04 | Dialog半导体有限公司 | Controllers for solid state light bulb assemblies |
| US20170232641A1 (en) * | 2016-02-12 | 2017-08-17 | The Boeing Company | Enhanced systems that facilitate vacuum bag curing of composite parts |
| CN206519899U (en) * | 2017-03-10 | 2017-09-26 | 成都联科航空技术有限公司 | A kind of modularization installs the frock of thermocouple |
| CN107391819A (en) * | 2017-07-07 | 2017-11-24 | 东南大学 | A kind of Forecasting Methodology of the hot relevant parameter of suture type thermal protection structure |
| CN109556877A (en) * | 2018-12-21 | 2019-04-02 | 成都飞机工业（集团）有限责任公司 | A kind of exhaust temperature of aircraft engine scaling method |
| US20220032560A1 (en) * | 2020-07-28 | 2022-02-03 | University Of South Carolina | 3D Printed Water Cooled Tow Guide for Fiber Placement Machine |
| CN113203489A (en) * | 2021-03-31 | 2021-08-03 | 成都飞机工业（集团）有限责任公司 | Method for installing thermocouple on back of tool |
| CN112792391A (en) * | 2021-04-12 | 2021-05-14 | 成都飞机工业（集团）有限责任公司 | Inner-groove milling cutter and honeycomb material machining method based on inner-groove milling cutter |
| CN113733600A (en) * | 2021-07-30 | 2021-12-03 | 昌河飞机工业（集团）有限责任公司 | Method for improving air tightness of autoclave molding thermocouple |
| CN115758921A (en) * | 2022-10-27 | 2023-03-07 | 沈阳飞机工业（集团）有限公司 | Method for accurately controlling autoclave curing temperature rise |
| CN115648666A (en) * | 2022-11-10 | 2023-01-31 | 江西昌河航空工业有限公司 | Method for determining optimal curing parameters of resin-based composite material |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117885256B (en) | 2024-07-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Graziani et al. | An experimental study of endwall and airfoil surface heat transfer in a large scale turbine blade cascade | |
| CN104267062B (en) | A kind of method that in Aerodynamic Heating simulated test, cold wall hot-fluid is converted to hot wall hot-fluid | |
| CN103294050B (en) | A kind of method of testing the antiskid braking control box high temperature limit | |
| CN107944137A (en) | The thermographic curve computing technique of hypersonic aircraft trajectory state multi- scenarios method | |
| BR102016022390B1 (en) | CURING SYSTEM FOR COMPOSITE STRUCTURE AND METHOD FOR CONTROLLING CURING TEMPERATURE OF A COMPOSITE STRUCTURE | |
| CN117885256B (en) | Part curing temperature monitoring method for temperature hysteresis area in margin line | |
| CN109960878A (en) | A kind of active/passive thermal protection system coupling design method towards hypersonic aircraft totality | |
| WO2021207953A1 (en) | Workbench-based low-temperature carbonization furnace oxygen content distribution simulation method | |
| Rozant et al. | Manufacturing of three dimensional sandwich parts by direct thermoforming | |
| Glass et al. | Aerothermal tests of spherical dome protuberances on a flat plate at a Mach number of 6.5 | |
| CN107992709A (en) | Thermal-structure model modification method based on intermediate function | |
| CN107121452A (en) | Resin base heat insulation material carburization zone high temperature dynamic thermal conductivity measurement apparatus and method | |
| CN115493722A (en) | Calibration system and method for measuring total temperature of high-speed gas by using probe | |
| CN114347505B (en) | Method for controlling curing temperature of composite material workpiece with super thickness ratio in split mode | |
| CN115758921A (en) | Method for accurately controlling autoclave curing temperature rise | |
| CN113733600A (en) | Method for improving air tightness of autoclave molding thermocouple | |
| CN207036455U (en) | A kind of test platform of SVG heat-pipe radiators dynamic characteristic | |
| CN111024270A (en) | Correction method for measurement error of embedded heat flow sensor | |
| CN113681939A (en) | Equivalent substitution method for composite material thermocouple | |
| CN101089862A (en) | Simulating method for resin flow and fibre dense in resin-base composite equal thick laminate forming | |
| Zhang et al. | Enhancing the Forming Accuracy of CFRP through a Global Compensation Method by Introducing an Optimal Profile | |
| Sun et al. | Modeling and control of the in-situ thermoplastic composite tape-laying process | |
| Lineberger | Structural tests and development of a laminar flow control wing surface composite chordwise joint | |
| Salek et al. | Development of low cost fuselage frames by resin transfer molding | |
| CN114480829B (en) | Method for simulating heat treatment process of process equipment with different thicknesses by using heat treatment test plate |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant |