CN113602522B - Maintenance method for humidity control device of environment control system of aviation aircraft - Google Patents
Maintenance method for humidity control device of environment control system of aviation aircraft Download PDFInfo
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- CN113602522B CN113602522B CN202110956693.1A CN202110956693A CN113602522B CN 113602522 B CN113602522 B CN 113602522B CN 202110956693 A CN202110956693 A CN 202110956693A CN 113602522 B CN113602522 B CN 113602522B
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- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000012423 maintenance Methods 0.000 title claims abstract description 20
- 238000003466 welding Methods 0.000 claims abstract description 24
- 229910001220 stainless steel Inorganic materials 0.000 claims abstract description 20
- 239000010935 stainless steel Substances 0.000 claims abstract description 20
- 238000012545 processing Methods 0.000 claims abstract description 15
- 239000000463 material Substances 0.000 claims abstract description 11
- 230000008569 process Effects 0.000 claims abstract description 9
- 238000005498 polishing Methods 0.000 claims abstract description 6
- 239000002184 metal Substances 0.000 claims description 28
- 238000010329 laser etching Methods 0.000 claims description 14
- 238000005520 cutting process Methods 0.000 claims description 10
- 238000005530 etching Methods 0.000 claims description 9
- 210000001503 joint Anatomy 0.000 claims description 9
- 101000623895 Bos taurus Mucin-15 Proteins 0.000 claims description 4
- 238000003892 spreading Methods 0.000 claims description 4
- 230000007480 spreading Effects 0.000 claims description 4
- 238000012360 testing method Methods 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 6
- 239000010410 layer Substances 0.000 description 5
- 230000007613 environmental effect Effects 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 239000002356 single layer Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000012549 training Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0662—Environmental Control Systems with humidity control
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Filtering Materials (AREA)
Abstract
The invention relates to the technical field of maintenance of humidity control devices of aviation aircrafts, in particular to a maintenance method of a humidity control device of an environment control system of an aviation aircrafts, which comprises the following specific steps: dismantling the gasket A and the gasket B on the condenser; taking down the cone net and the cylinder net by a polishing machine, and polishing the welding spot positions of the flange and the fairing; processing the parts A and B by adopting stainless steel belts which are the same as the silk screen A in material and thickness; processing a stainless steel belt with the thickness of 0.71mm into a part C and a part D by adopting the same material as that of the silk screen A; a strip E having a width of 8mm was processed using a stainless steel strip having a thickness of 0.45 mm. The invention solves the problems of poor silk screen welding process and low yield; the welding operability is enhanced, and the manufacturability is improved; the flow characteristics of the product before and after maintenance still meet the product specification requirements; no additional operation equipment is needed, and the implementation cost is low; the method is beneficial to improving the timeliness of equipment delivery, and the comprehensive guarantee capability of the equipment is enhanced.
Description
Technical Field
The invention relates to the technical field of maintenance of humidity control devices of aviation aircrafts, in particular to a maintenance method of a humidity control device of an environment control system of an aviation aircrafts.
Background
Currently, environmental control systems for both civilian and military aircraft remain based on air circulation systems. The dehydrator is a main humidity control device of the environment control system, and has the main functions of separating free water micro-clusters which are aggregated into large particles from high-speed air flow in the whole system operation process, so that the comfort of a cockpit pilot and the requirement of electronic equipment cabin cooling on air supply humidity are ensured.
The existing dehydrator (shown in figure 1) for a military aircraft environment control system consists of an inlet pipe 1, a condenser 2, a safety valve 3, a cyclone 4, a shell 5, a water collecting cavity 6, an outlet pipe 7 and the like. The condenser 2 comprises a gasket A21, a cone net 22, a condenser skeleton 23, a cylinder net 24 and a gasket B25. The cone net 22 is composed of a net A221 and a net B222, wherein the net A221 is a single-layer metal net, and the multi-layer non-metal net B222 is wrapped in the middle to form a sandwich structure, so that the net B222 is protected from being damaged. Cylinder 24 is also comprised of screen A221 and screen B222, where screen A221 is a single layer wire mesh, wrapping multiple layers of non-wire mesh B222 in between, forming a "sandwich" structure that protects screen B222 from damage. The condenser skeleton 23 is composed of a fairing 231, a short pipe 232, ribs 233, spokes 234, a ring 235, and a flange 236.
Spokes 234 and flanges 236 in the condenser skeleton 23 are welded and fixed with the fairing 231, the spokes 234 and rings 235 are welded and fixed, and two ends of the ribs 233 are respectively welded with the fairing 231 and short pipes 232 to fix all parts into a whole. The cone net 22 and the cylinder net 24 connect the screen a221 and the screen B222 by electric welding. The difficulty of the welding process is considerable, the welding temperature is too high, and the screen structures of the screen a221 and the screen B222 may be blown or severely oxidized, so that the yield is low. Secondly, because the upper limit of the air flow passing through the dehydrator exceeds 2000kg/h, failures such as wire mesh A221 unwelding, hole breaking and wire mesh B222 hole breaking and the like often occur to the condenser under the complex use environment condition of the airplane. When the damaged condenser 2 is returned to the maintenance unit, it is difficult to perform maintenance although it is a simple structure. Frequent faults, difficult processing and maintenance and other factors have serious influence on the maintenance and guarantee work of the whole aircraft, and are unfavorable for combat training and combat force generation.
Disclosure of Invention
In order to solve the technical problems, the invention provides a maintenance method of a humidity control device of an environment control system of an aircraft.
The technical problems to be solved by the invention are realized by adopting the following technical scheme:
a maintenance method for a humidity control device of an environment control system of an aviation aircraft comprises the following specific steps:
firstly, removing a gasket A and a gasket B on the condenser;
secondly, taking down the cone net and the cylinder net by a polishing machine, and polishing the welding spot positions of the flange and the fairing;
thirdly, processing the parts A and B by adopting stainless steel belts which are the same as the silk screen A in material and thickness;
fourthly, processing a stainless steel belt with the thickness of 0.71mm into a part C and a part D by adopting the same material as that of the silk screen A;
(V) processing the stainless steel strip with the thickness of 0.45mm into a strip E with the width of 8 mm;
sleeving the part A and the part B together, putting 6 layers of silk screens B in the middle, filling gaps at two ends with strips E, and welding the strips into a whole to form a component I;
sleeving the part C and the part D together, putting 6 layers of silk screens B in the middle, filling gaps at two ends with strips E, and welding the strips into a whole to form a component II;
welding the condenser skeleton, the component I and the component II into a new condenser;
and (nine) reassembling the dehydrator and completing the test.
Preferably, the machining process of the part A in the step (three) is specifically as follows:
(A) Cutting a sheet metal part A with a spreading angle of 180 DEG, an outer diameter of 182.32mm and an inner diameter of 98.32mm by adopting a stainless steel belt which is the same as the silk screen A in material and thickness;
(B) The sheet metal part A is curled by 360 degrees, and the butt joint is welded to form a part A;
(C) And (3) etching square holes with the array distance of 1.2mm by adopting a laser etching machine, wherein the square holes are 0.9mm multiplied by 0.9mm, and the whole part A is fully covered.
Preferably, the processing procedure of the part B in the step (three) is specifically as follows:
(a) Cutting out a sheet metal part B with a spreading angle of 180 DEG, an outer diameter of 180mm and an inner diameter of 96mm by adopting a stainless steel belt which is the same as the silk screen A in material and thickness;
(b) The sheet metal part B is curled by 360 degrees, and the butt joint is welded to form a part B;
(c) And (3) etching square holes with the array distance of 1.2mm by adopting a laser etching machine, wherein the square holes are 0.9mm multiplied by 0.9mm, and the whole part B is fully covered.
Preferably, the processing procedure of the part C in the step (four) is specifically as follows:
(S1) cutting a rectangular sheet metal part C with the thickness of 58mm multiplied by 217.55mm by adopting a stainless steel belt with the thickness of 0.71mm, which is the same as that of the silk screen A;
(S2) curling the sheet metal part C by 360 degrees, and welding the butt joint to form a part C;
and (S3) etching square holes with the array distance of 1.2mm by using a laser etching machine, wherein the square holes are 0.9mm multiplied by 0.9mm, and the whole part C is fully covered.
Preferably, the machining process of the part D in the step (four) is specifically as follows:
(s 1) cutting a rectangular sheet metal part D with the thickness of 58mm multiplied by 209.38mm by adopting a stainless steel belt with the thickness of 0.71mm, which is the same as that of the silk screen A;
(s 2) curling the sheet metal part D by 360 degrees, and welding the butt joint to form a part D;
and (s 3) etching square holes with the array distance of 1.2mm by using a laser etching machine, wherein the square holes are 0.9mm multiplied by 0.9mm, and the whole part D is fully covered.
The beneficial effects of the invention are as follows:
the invention solves the problems of poor silk screen welding process and low yield; the operability is enhanced, and the manufacturability is improved; the whole net is of an integral structure, uniformly distributed stress is rapidly distributed on the whole net structure, and the service time is longer; the porosity of the repaired net is consistent with the porosity of the original silk screen structure, the thickness of the sheet metal material is consistent with the silk screen structure, and the flow characteristics of the product before and after maintenance still meet the product specification requirements; in addition, the invention can be used for maintaining the on-site silk screen structure condenser and can also be used as a retrofit design idea of the whole dehydrator product; the sheet metal material and the laser etching machine used in the invention are widely used in aviation host, accessory manufacturing and maintenance units, the etching depth is within the range of the laser etching depth, no additional operation equipment is needed, and the implementation cost is low; the laser etching device has high laser etching efficiency, does not have periodical purchasing work, can be quickly maintained by adopting the existing equipment after the product returns to the factory, is beneficial to improving the equipment delivery timeliness, and enhances the comprehensive guarantee capability of the equipment.
Drawings
The invention is further illustrated by the following examples in conjunction with the accompanying drawings:
FIG. 1 is a schematic diagram of a water trap for a military aircraft environmental control system;
FIG. 2 is a schematic structural view of a coalescer;
FIG. 3 is a schematic view of the structure of a cone net;
FIG. 4 is a schematic structural view of a coalescer skeleton;
FIG. 5 is a schematic view of a cylindrical net;
FIG. 6 is an expanded schematic view of sheet metal part A;
FIG. 7 is an expanded schematic view of sheet metal part B;
FIG. 8 is a schematic cross-sectional view of assembly I;
fig. 9 is a schematic cross-sectional view of the assembly ii.
In the figure: 1. an inlet pipe; 2. a condenser; 21. a gasket A; 22. conical net; 221. a silk screen A; 222. a silk screen B; 23. a coalescer skeleton; 231. a fairing; 232. a short pipe; 233. a rib; 234. spokes; 235. a ring; 236. a flange; 24. a cylindrical net; 25. a pad B; 3. a safety valve; 4. a cyclone; 5. a housing; 6. a water collecting cavity; 7. an outlet tube.
Detailed Description
In order that the manner in which the invention is attained, as well as the features and advantages thereof, will be readily understood, a more particular description of the invention will be rendered by reference to the appended drawings.
As shown in fig. 1 to 9, a maintenance method for a humidity control device of an environment control system of an aircraft comprises the following specific steps:
referring to fig. 2, the gaskets a21 and B25 of the condenser 2 are removed.
(II) referring to FIGS. 1 and 2, the cone net 22 and the cylinder net 24 are removed by a polisher, and the welding spot positions of the flange 236 and the fairing 231 are polished. So as to facilitate re-welding after maintenance.
And thirdly, cutting out sheet metal parts A and B with the spreading angle of 180 degrees, the outer diameter of 182.32mm and 180mm and the inner diameter of 98.32mm and 96mm by adopting stainless steel belts which are made of the same materials and have the same thickness as the silk screen A221, as shown in fig. 6 and 7.
The cone net 22 and the cylinder net 24 manufactured by the silk screen structure in the original product are changed into metal pore plates; the thickness of the adopted metal pore plate is consistent with that of a silk screen used in the current product, so that the size of a condenser component of the dehydrator is unchanged after maintenance.
Fourthly, the sheet metal part A and the sheet metal part B are curled by 360 degrees, and the butt joint is welded to form a part A and a part B.
And fifthly, cutting a rectangular sheet metal part C and a rectangular sheet metal part D which are 58mm multiplied by 217.55mm and 58mm multiplied by 209.38mm by using a stainless steel belt with the thickness of 0.71mm, which is the same as that of the silk screen A221.
And (six) curling the sheet metal part C and the sheet metal part D by 360 degrees, and welding the opposite openings to form a part C and a part D.
And (seventh) respectively adopting a laser etching machine to etch square holes with the array distance of 1.2mm and 0.9mm multiplied by 0.9mm on the four parts, and fully distributing the whole parts.
Because the porosity of the silk screen A221 is particularly large, the holes are very dense, the diameter of the silk screen is only 0.355, and a laser etching technology is adopted to precisely process rectangular holes with the diameter of 0.9mm multiplied by 0.9mm, the porosity of the structure is ensured to be unchanged before and after maintenance, and the flow characteristic of the dehydrator is further ensured; and the water removal efficiency of the water remover can still meet the product specification.
Eighth, a stainless steel strip with a thickness of 0.45mm was used to cut out a strip E with a width of 8 mm.
And (nine) sleeving the part A and the part B together, putting 6 layers of silk screens B222 in the middle, filling gaps at two ends with strips E, and welding the strips into a whole to form the assembly I.
And (ten) sleeving the part C and the part D together, putting 6 layers of silk screens B222 in the middle, filling gaps at two ends with strips E, and welding the strips into a whole to form the assembly II.
Eleventh, the condenser frame 23, the components I and II are welded to form a new condenser 2.
(twelve) referring to fig. 1, the dehydrator is reassembled and the test is completed.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (5)
1. A maintenance method of a humidity control device of an environment control system of an aviation aircraft is characterized by comprising the following steps of: the method comprises the following specific steps:
firstly, removing a gasket A (21) and a gasket B (25) on the condenser (2);
secondly, taking down the cone net (22) and the cylinder net (24) by a polishing machine, and polishing the welding spot positions of the flange (236) and the fairing (231);
thirdly, processing the parts A and B by adopting stainless steel belts with the same material and thickness as the silk screen A (221);
fourthly, processing a stainless steel belt with the thickness of 0.71mm into a part C and a part D by adopting the same material as that of the silk screen A (221);
(V) processing the stainless steel strip with the thickness of 0.45mm into a strip E with the width of 8 mm;
sleeving the part A and the part B together, putting 6 layers of silk screens B (222) in the middle, filling gaps at two ends with strips E, and welding the strips E into a whole to form a component I;
fitting part C and part D together, placing 6 layers of silk screens B (222) in the middle, filling gaps at two ends with strips E, and welding the strips into a whole to form a component II;
welding the condenser skeleton (23), the component I and the component II into a new condenser (2);
and (nine) reassembling the dehydrator and completing the test.
2. A method of servicing a humidity control apparatus of an aircraft environment control system of claim 1, wherein: the processing process of the part A in the step (III) is specifically as follows:
(A) Cutting a sheet metal part A with the expansion angle of 180 DEG, the outer diameter of 182.32mm and the inner diameter of 98.32mm by adopting a stainless steel belt which is the same as the silk screen A (221) in material and thickness;
(B) The sheet metal part A is curled by 360 degrees, and the butt joint is welded to form a part A;
(C) And (3) etching square holes with the array distance of 1.2mm by adopting a laser etching machine, wherein the square holes are 0.9mm multiplied by 0.9mm, and the whole part A is fully covered.
3. A method of servicing a humidity control apparatus of an aircraft environment control system of claim 1, wherein: the processing process of the part B in the step (III) is specifically as follows:
(a) Cutting out a sheet metal part B with a spreading angle of 180 DEG, an outer diameter of 180mm and an inner diameter of 96mm by adopting a stainless steel belt which is the same as the silk screen A (221) in material and thickness;
(b) The sheet metal part B is curled by 360 degrees, and the butt joint is welded to form a part B;
(c) And (3) etching square holes with the array distance of 1.2mm by adopting a laser etching machine, wherein the square holes are 0.9mm multiplied by 0.9mm, and the whole part B is fully covered.
4. A method of servicing a humidity control apparatus of an aircraft environment control system of claim 1, wherein: the processing process of the part C in the step (IV) is specifically as follows:
(S1) cutting a rectangular sheet metal part C with the thickness of 58mm multiplied by 217.55mm by adopting a stainless steel belt with the thickness of 0.71mm, which is the same as that of the silk screen A (221);
(S2) curling the sheet metal part C by 360 degrees, and welding the butt joint to form a part C;
and (S3) etching square holes with the array distance of 1.2mm by using a laser etching machine, wherein the square holes are 0.9mm multiplied by 0.9mm, and the whole part C is fully covered.
5. A method of servicing a humidity control apparatus of an aircraft environment control system of claim 1, wherein: the processing process of the part D in the step (IV) is specifically as follows:
(s 1) cutting a rectangular sheet metal part D with the thickness of 58mm multiplied by 209.38mm by adopting a stainless steel belt with the thickness of 0.71mm, which is the same as that of the silk screen A (221);
(s 2) curling the sheet metal part D by 360 degrees, and welding the butt joint to form a part D;
and (s 3) etching square holes with the array distance of 1.2mm by using a laser etching machine, wherein the square holes are 0.9mm multiplied by 0.9mm, and the whole part D is fully covered.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110956693.1A CN113602522B (en) | 2021-08-19 | 2021-08-19 | Maintenance method for humidity control device of environment control system of aviation aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110956693.1A CN113602522B (en) | 2021-08-19 | 2021-08-19 | Maintenance method for humidity control device of environment control system of aviation aircraft |
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| Publication Number | Publication Date |
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| CN113602522A CN113602522A (en) | 2021-11-05 |
| CN113602522B true CN113602522B (en) | 2023-12-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110956693.1A Active CN113602522B (en) | 2021-08-19 | 2021-08-19 | Maintenance method for humidity control device of environment control system of aviation aircraft |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102679031A (en) * | 2011-03-15 | 2012-09-19 | 全龙浩 | Temperature control valve capable of being cleaned and maintained on line |
| CN107617851A (en) * | 2017-09-19 | 2018-01-23 | 成都成发泰达航空科技有限公司 | A kind of method for maintaining of aviation auxiliary power unit stator support ring |
| CN210179124U (en) * | 2019-06-15 | 2020-03-24 | 陈鉴 | Temperature control valve convenient to maintain |
| CN211869726U (en) * | 2018-09-30 | 2020-11-06 | 浙江虹湾通用航空工程技术有限公司 | Universal composite material repairing instrument for aviation and aircraft |
| FR3103790A1 (en) * | 2019-11-29 | 2021-06-04 | Airbus | ARRANGEMENT OF ROBOTS TO WORK ON AN AIRCRAFT STRUCTURE |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11891174B2 (en) * | 2020-02-05 | 2024-02-06 | The Boeing Company | Repair of structures using unmanned aerial vehicles |
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2021
- 2021-08-19 CN CN202110956693.1A patent/CN113602522B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102679031A (en) * | 2011-03-15 | 2012-09-19 | 全龙浩 | Temperature control valve capable of being cleaned and maintained on line |
| CN107617851A (en) * | 2017-09-19 | 2018-01-23 | 成都成发泰达航空科技有限公司 | A kind of method for maintaining of aviation auxiliary power unit stator support ring |
| CN211869726U (en) * | 2018-09-30 | 2020-11-06 | 浙江虹湾通用航空工程技术有限公司 | Universal composite material repairing instrument for aviation and aircraft |
| CN210179124U (en) * | 2019-06-15 | 2020-03-24 | 陈鉴 | Temperature control valve convenient to maintain |
| FR3103790A1 (en) * | 2019-11-29 | 2021-06-04 | Airbus | ARRANGEMENT OF ROBOTS TO WORK ON AN AIRCRAFT STRUCTURE |
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| Publication number | Publication date |
|---|---|
| CN113602522A (en) | 2021-11-05 |
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