阅读说明：本技术 一种航空飞行器环境控制系统湿度控制装置维修方法 (Maintenance method for humidity control device of aviation aircraft environment control system ) 是由 薛继鹏 齐慧英 刘锐 班超 王亚龙 罗雁 宋冬 乐婷 张睿 于 2021-08-19 设计创作，主要内容包括：本发明涉及航空飞行器湿度控制装置维修技术领域,具体为一种航空飞行器环境控制系统湿度控制装置维修方法,具体步骤如下：将凝聚器上的衬垫A、衬垫B拆除；用抛光机将锥网和圆筒网取下,并对法兰和整流罩的焊点位置进行打磨抛光；采用与丝网A材质相同、厚度相同的不锈钢带加工成零件A和零件B；采用与丝网A材质相同,厚度为0.71mm的不锈钢带加工成零件C和零件D；采用厚度为0.45mm的不锈钢带加工成宽度为8mm的带材E。本发明解决了丝网焊接工艺差,成品率低的问题；焊接可操作性增强,工艺性变好；保证了维修前后产品的流量特性依然满足产品规范要求；不需要额外投入操作设备,实施成本低；有利于提高装备交付时效性,装备综合保障能力得到加强。(The invention relates to the technical field of maintenance of a humidity control device of an aviation aircraft, in particular to a maintenance method of a humidity control device of an environment control system of an aviation aircraft, which comprises the following steps: removing the gasket A and the gasket B on the coagulator; taking down the conical net and the cylindrical net by using a polishing machine, and polishing the welding spot positions of the flange and the fairing; processing a stainless steel belt which is the same as the silk screen A in material and thickness into a part A and a part B; processing a stainless steel belt which is made of the same material as the silk screen A and has the thickness of 0.71mm into a part C and a part D; a stainless steel strip with a thickness of 0.45mm is processed into a strip E with a width of 8 mm. The invention solves the problems of poor silk screen welding process and low yield; welding operability is enhanced, and manufacturability is improved; the flow characteristics of the product before and after maintenance are ensured to still meet the product specification requirements; no additional investment in operating equipment is needed, and the implementation cost is low; the equipment delivery timeliness is improved, and the comprehensive guarantee capability of the equipment is enhanced.)

1. A maintenance method for a humidity control device of an environmental control system of an aviation aircraft is characterized by comprising the following steps: the method comprises the following specific steps:

firstly, removing a gasket A (21) and a gasket B (25) on the coalescer (2);

secondly, the conical net (22) and the cylindrical net (24) are taken down by a polishing machine, and the welding point positions of the flange (236) and the fairing (231) are polished;

thirdly, processing a part A and a part B by adopting a stainless steel belt which is the same as the silk screen A (221) in material and thickness;

fourthly, a stainless steel belt which is made of the same material as the silk screen A (221) and has the thickness of 0.71mm is processed into a part C and a part D;

fifthly, a stainless steel band with the thickness of 0.45mm is processed into a band material E with the width of 8 mm;

sixthly, 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;

seventhly, sleeving the part C and the part D together, putting a 6-layer silk screen B (222) in the middle, filling gaps at two ends with a strip E, and welding the gaps into a whole to form a component II;

welding a coagulator framework (23), a component I and a component II into a new coagulator (2);

and (ninthly) reassembling the dehydrator and completing the test.

2. The method of servicing an aircraft environmental control system humidity control device of claim 1, wherein: the machining process of the part A in the step (III) is as follows:

(A) cutting a sheet metal part A with an angle of spread of 180 degrees, an outer diameter of 182.32mm and an inner diameter of 98.32mm by using a stainless steel belt which is the same in material and thickness as the silk screen A (221);

(B) curling the sheet metal part A for 360 degrees, and welding the butt joint to form a part A;

(C) and etching square holes with the array distance of 1.2mm and the length of 0.9mm multiplied by 0.9mm by adopting a laser etching machine, and fully distributing the whole part A.

3. The method of servicing an aircraft environmental control system humidity control device of claim 1, wherein: the machining process of the part B in the step (III) is as follows:

(a) cutting a sheet metal part B with an angle of spread of 180 degrees, an outer diameter of 180mm and an inner diameter of 96mm by using a stainless steel belt which is the same as the material of the silk screen A (221) and has the same thickness;

(b) curling the sheet metal part B for 360 degrees, and welding the butt joint to form a part B;

(c) and etching square holes with the array distance of 1.2mm and the length of 0.9mm multiplied by 0.9mm by adopting a laser etching machine, and fully distributing the whole part B.

4. The method of servicing an aircraft environmental control system humidity control device of claim 1, wherein: the machining process of the part C in the step (IV) is as follows:

(S1) cutting a rectangular sheet metal part C with the thickness of 58mm multiplied by 217.55mm from a stainless steel belt which is made of the same material as the silk screen A (221) and has the thickness of 0.71 mm;

(S2) curling the sheet metal part C by 360 degrees, and welding the opposite openings to form a part C;

(S3) etching square holes with the array distance of 1.2mm and the dimension of 0.9mm multiplied by 0.9mm by adopting a laser etching machine, and fully distributing the whole part C.

5. The method of servicing an aircraft environmental control system humidity control device of claim 1, wherein: the machining process of the part D in the step (IV) is as follows:

(s1) cutting a rectangular sheet metal part D of 58mm multiplied by 209.38mm by a stainless steel belt which is made of the same material as the silk screen A (221) and has the thickness of 0.71 mm;

(s2) curling the sheet metal part D for 360 degrees, and welding the opposite openings to form a part D;

(s3) etching square holes with the array distance of 1.2mm and the dimension of 0.9mm multiplied by 0.9mm by using a laser etching machine, and fully distributing the whole part D.

Technical Field

The invention relates to the technical field of maintenance of a humidity control device of an aviation aircraft, in particular to a maintenance method of a humidity control device of an environment control system of an aviation aircraft.

Background

Currently, environmental control systems for both civil and military aircraft remain dominated by air circulation systems. The dehydrator is a main humidity control device of the environment control system, and in the operation process of the whole system, the dehydrator mainly has the function of separating free water micelles which are agglomerated into large particles from high-speed airflow, so that the comfort of a pilot in a cockpit and the requirement of cooling of an electronic equipment cabin on the air supply humidity are ensured.

At present, a dehydrator (shown in figure 1) for an environmental control system of a certain military aircraft is composed of an inlet pipe 1, a coalescer 2, a safety valve 3, a cyclone 4, a shell 5, a water collecting cavity 6, an outlet pipe 7 and the like. The coalescer 2 is composed of a gasket a21, a conical net 22, a coalescer frame 23, a cylindrical net 24, and a gasket B25. The conical 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. The cylindrical net 24 is also composed of a net a221 and a net B222, wherein the net a221 is a single-layer wire net, and a plurality of layers of non-metal nets B222 are wrapped in the middle to form a "sandwich" structure, so as to protect the net B222 from being damaged. The coalescer framework 23 is comprised of a fairing 231, spool 232, ribs 233, spokes 234, ring 235, and flange 236.

The spokes 234 and the flange 236 in the coalescer frame 23 are fixed with the fairing 231 by welding, the spokes 234 and the ring 235 are fixed by welding, and the two ends of the rib 233 are respectively welded with the fairing 231 and the short pipe 232 to fix all parts into a whole. The conical net 22 and the cylindrical net 24 connect the net a221 and the net B222 by electric welding. The welding process is difficult, the welding temperature is too high, and the screen structures of the screen a221 and the screen B222 may be blown or heavily oxidized, so that the yield is low. Secondly, because the upper limit of the air flow passing through the dehydrator exceeds 2000kg/h, the silk screen A221 is frequently detached from the condenser and broken, and further the silk screen B222 is broken and other faults are caused in the complex use environment condition of the airplane. When the damaged condenser 2 returns to the maintenance of the security unit, it looks like a simple structure, but is difficult to perform maintenance. Frequent faults, difficulty in processing and maintenance and other factors seriously affect the maintenance and guarantee work of the whole airplane, and are not beneficial to combat training and combat effectiveness generation.

Disclosure of Invention

In order to solve the technical problem, the invention provides a maintenance method for a humidity control device of an environmental control system of an aircraft.

The technical problem to be solved by the invention is realized by adopting the following technical scheme:

a maintenance method for a humidity control device of an environmental control system of an aviation aircraft comprises the following specific steps:

firstly, removing a gasket A and a gasket B on the coalescer;

secondly, taking down the conical net and the cylindrical net by using a polishing machine, and polishing the welding spot positions of the flange and the fairing;

thirdly, processing a stainless steel belt which is the same as the silk screen A in material and thickness into a part A and a part B;

fourthly, processing a stainless steel belt which is made of the same material as the silk screen A and has the thickness of 0.71mm into a part C and a part D;

fifthly, a stainless steel band with the thickness of 0.45mm is processed into a band material E with the width of 8 mm;

sixthly, sleeving the part A and the part B together, placing 6 layers of silk screens B in the middle, filling gaps at two ends with strips E, and welding the strips E into a whole to form a component I;

seventhly, sleeving the part C and the part D together, placing 6 layers of silk screens B in the middle, filling gaps at two ends with the belt materials E, and welding the gaps into a whole to form a component II;

welding the framework of the coagulator, the component I and the component II into a new coagulator;

and (ninthly) reassembling the dehydrator and completing the test.

Preferably, the machining process of the part a in the step (three) is as follows:

(A) cutting a sheet metal part A with an angle of spread of 180 degrees, an outer diameter of 182.32mm and an inner diameter of 98.32mm by using a stainless steel belt which is the same in material and thickness as the silk screen A;

(B) curling the sheet metal part A for 360 degrees, and welding the butt joint to form a part A;

(C) and etching square holes with the array distance of 1.2mm and the length of 0.9mm multiplied by 0.9mm by adopting a laser etching machine, and fully distributing the whole part A.

Preferably, the processing procedure of the part B in the step (three) is as follows:

(a) cutting a stainless steel belt which is the same as the silk screen A in material and thickness to form a sheet metal part B with an angle of spread of 180 degrees, an outer diameter of 180mm and an inner diameter of 96 mm;

(b) curling the sheet metal part B for 360 degrees, and welding the butt joint to form a part B;

(c) and etching square holes with the array distance of 1.2mm and the length of 0.9mm multiplied by 0.9mm by adopting a laser etching machine, and fully distributing the whole part B.

Preferably, the machining process of the part C in the step (iv) is 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 which is the same as the material of the silk screen A and has the thickness of 0.71 mm;

(S2) curling the sheet metal part C by 360 degrees, and welding the opposite openings to form a part C;

(S3) etching square holes with the array distance of 1.2mm and the dimension of 0.9mm multiplied by 0.9mm by adopting a laser etching machine, and fully distributing the whole part C.

Preferably, the machining process of the part D in the step (iv) is specifically as follows:

(s1) cutting a rectangular sheet metal part D with the thickness of 58mm multiplied by 209.38mm by adopting a stainless steel belt which is the same as the material of the silk screen A and has the thickness of 0.71 mm;

(s2) curling the sheet metal part D for 360 degrees, and welding the opposite openings to form a part D;

(s3) etching square holes with the array distance of 1.2mm and the dimension of 0.9mm multiplied by 0.9mm by using a laser etching machine, and fully distributing the whole part D.

The invention has the beneficial effects that:

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, the uniform distribution stress is quickly distributed on the whole net structure, and the service life is longer; the porosity of the net repaired by the method is consistent with the porosity of the original silk net structure, the thickness of the sheet metal material is consistent with that of the silk net structure, and the flow characteristics of products before and after maintenance are ensured to still meet the product specification requirements; in addition, the invention can be used for maintaining the on-site silk screen structural condenser and can also be used as a design idea for modifying the whole dehydrator product; the sheet metal material and the laser etching machine used in the invention are widely used in aeronautical mainframes and accessory manufacturing and maintenance units, the etching depth is in the laser etching depth range, no additional operation equipment is required, and the implementation cost is low; the laser etching method 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 a factory, is favorable for improving the delivery timeliness of the equipment, and enhances the comprehensive guarantee capability of the equipment.

Drawings

The invention is further illustrated with reference to the following figures and examples:

FIG. 1 is a schematic structural view of a dehydrator for an environmental control system of a military aircraft;

FIG. 2 is a schematic diagram of a coalescer;

FIG. 3 is a schematic structural view of a conical net;

FIG. 4 is a schematic structural view of a coalescer framework;

FIG. 5 is a schematic view of a cylinder net structure;

FIG. 6 is a schematic view of the expanded sheet metal part A;

FIG. 7 is a schematic view of the sheet metal part B in an unfolded state;

FIG. 8 is a schematic cross-sectional view of module I;

FIG. 9 is a schematic cross-sectional view of module II.

In the figure: 1. an inlet pipe; 2. a coalescer; 21. a gasket A; 22. a conical net; 221. a silk screen A; 222. a screen B; 23. a coalescer framework; 231. a cowling; 232. a short pipe; 233. a rib; 234. spokes; 235. a ring; 236. a flange; 24. a cylindrical net; 25. a gasket B; 3. a safety valve; 4. a swirler; 5. a housing; 6. a water collection cavity; 7. an outlet pipe.

Detailed Description

In order to make the technical means, the creation features, the achievement purposes and the effects of the invention easy to understand, the invention is further explained in the following with the accompanying drawings and the embodiments.

As shown in fig. 1 to 9, a method for maintaining a humidity control device of an environmental control system of an aircraft includes the following steps:

referring to fig. 2, the gasket a21 and the gasket B25 of the coalescer 2 were removed.

Referring to fig. 1 and 2, the conical net 22 and the cylindrical net 24 are removed by a polishing machine, and the welding points of the flange 236 and the fairing 231 are polished. So as to be convenient for re-welding after maintenance.

And (III) cutting out a sheet metal part A and a sheet metal part B which have the same material and thickness as those of the silk screen A221, have the spread angle of 180 degrees, the outer diameters of 182.32mm and 180mm and the inner diameters of 98.32mm and 96mm, and are shown in fig. 6 and 7.

In the invention, the conical net 22 and the cylindrical net 24 which are manufactured by the silk screen structure in the original product are changed into metal hole plates; the thickness of the adopted metal pore plate is consistent with that of the silk screen used in the existing product, so that the size of a coagulator assembly of the dehydrator is kept unchanged after maintenance.

And (IV) curling the sheet metal part A and the sheet metal part B for 360 degrees, and welding the butt ends to form the part A and the part B.

And (V) cutting the rectangular sheet metal parts C and D with the thickness of 58mm multiplied by 217.55mm and 58mm multiplied by 209.38mm by using a stainless steel belt which is made of the same material as the silk screen A221 and has the thickness of 0.71 mm.

And (VI) curling the sheet metal part C and the sheet metal part D for 360 degrees, and welding the opposite openings to form a part C and a part D.

And seventhly, etching square holes with the array distance of 1.2mm and the length of 0.9mm multiplied by 0.9mm by etching the four parts respectively by using a laser etching machine, and fully distributing the whole parts.

Because the porosity of the silk screen A221 is extremely large, the holes are very dense, and the diameter of the silk screen is only 0.355, rectangular holes with the diameter of 0.9mm multiplied by 0.9mm are precisely machined by adopting a laser etching technology, the porosity of the structure before and after maintenance is ensured to be kept unchanged, and the flow characteristic of the dehydrator is further ensured; and the dewatering efficiency of the water eliminator can still meet the product specification.

(VIII) cutting a stainless steel belt with the thickness of 0.45mm to obtain a belt material E with the width of 8 mm.

And (ninthly), sleeving the part A and the part B together, putting 6 layers of wire meshes B222 in the middle, filling gaps at two ends with a strip E, and welding the strip E into a whole to form the component 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 the strip E, and welding the strip E into a whole to form an assembly II.

Welding the coalescer framework 23, the component I and the component II into a new coalescer 2.

(twelfth) referring to fig. 1, the dehydrator was reassembled and the test was completed.

The foregoing shows and describes the general principles, essential 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, which are merely illustrative of the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.