CN113155720A - Application verification method of multi-series thermal shrinkage sealing protective material for helicopter - Google Patents
Application verification method of multi-series thermal shrinkage sealing protective material for helicopter Download PDFInfo
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- 239000000463 material Substances 0.000 title claims abstract description 36
- 238000007789 sealing Methods 0.000 title claims abstract description 36
- 230000001681 protective effect Effects 0.000 title claims abstract description 29
- 238000000034 method Methods 0.000 title claims abstract description 27
- 238000012795 verification Methods 0.000 title claims abstract description 25
- 238000012360 testing method Methods 0.000 claims abstract description 170
- 238000001228 spectrum Methods 0.000 claims abstract description 34
- 238000013461 design Methods 0.000 claims abstract description 23
- 230000007613 environmental effect Effects 0.000 claims abstract description 18
- 238000004519 manufacturing process Methods 0.000 claims abstract description 14
- 150000003839 salts Chemical class 0.000 claims description 25
- 239000007921 spray Substances 0.000 claims description 24
- 238000001514 detection method Methods 0.000 claims description 14
- FAPWRFPIFSIZLT-UHFFFAOYSA-M Sodium chloride Chemical compound [Na+].[Cl-] FAPWRFPIFSIZLT-UHFFFAOYSA-M 0.000 claims description 8
- 238000010998 test method Methods 0.000 claims description 7
- 239000002253 acid Substances 0.000 claims description 6
- 230000007935 neutral effect Effects 0.000 claims description 6
- 238000011056 performance test Methods 0.000 claims description 4
- 239000011780 sodium chloride Substances 0.000 claims description 4
- 238000005299 abrasion Methods 0.000 claims description 3
- 238000011161 development Methods 0.000 claims description 3
- 230000005855 radiation Effects 0.000 claims description 3
- 238000001556 precipitation Methods 0.000 claims description 2
- 239000004020 conductor Substances 0.000 claims 1
- 238000009413 insulation Methods 0.000 description 3
- 230000032683 aging Effects 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical group [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002654 heat shrinkable material Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000004062 sedimentation Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N17/00—Investigating resistance of materials to the weather, to corrosion, or to light
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N17/00—Investigating resistance of materials to the weather, to corrosion, or to light
- G01N17/004—Investigating resistance of materials to the weather, to corrosion, or to light to light
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/56—Investigating resistance to wear or abrasion
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R27/00—Arrangements for measuring resistance, reactance, impedance, or electric characteristics derived therefrom
- G01R27/02—Measuring real or complex resistance, reactance, impedance, or other two-pole characteristics derived therefrom, e.g. time constant
- G01R27/20—Measuring earth resistance; Measuring contact resistance, e.g. of earth connections, e.g. plates
- G01R27/205—Measuring contact resistance of connections, e.g. of earth connections
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/50—Testing of electric apparatus, lines, cables or components for short-circuits, continuity, leakage current or incorrect line connections
- G01R31/58—Testing of lines, cables or conductors
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Abstract
The invention belongs to the technical field of helicopter sealing protective materials, and particularly relates to an application verification method of a multi-series thermal shrinkage sealing protective material for a helicopter. The method is characterized by comprising the following steps: s1: typical test piece design; s2: manufacturing a typical test piece; s3: detecting the initial performance; s4: determining an accelerated test environment spectrum and a test program; s5: carrying out an environmental test; s6: and (5) detecting and verifying the performance. The invention creates a complete application verification method of the multi-series heat-shrinkable sealing protective material for the helicopter, fills the blank of the prior art, and realizes the application verification of the multi-series heat-shrinkable sealing protective material for the helicopter.
Description
Technical Field
The invention belongs to the technical field of helicopter sealing protective materials, and particularly relates to an application verification method of a multi-series thermal shrinkage sealing protective material for a helicopter.
Background
The application amount of the electric wire and the cable in aviation equipment, particularly in a helicopter is huge, the electric wire and the cable for the whole helicopter are a system engineering, and once a problem occurs, the realization of the normal function of the helicopter and the electromagnetic compatibility of each system and even the whole helicopter are influenced. In order to meet the functional requirements of ship surface complex environment protection of a full-machine wire and cable system on wear resistance, insulation, corrosion resistance, medium resistance and the like, protective materials are required to be used in the aspects of wire marking, wire end processing, plug and socket assembly, cable manufacturing, cable installation and the like, the protective materials mainly used by the existing aircraft weaponry are heat shrinkable materials, and the protective materials are mainly used for wire and cable insulation protection, wear resistance and the like in the manufacturing and installation processes of wires and cables and are core key materials of an electrical system. The comprehensive protection of the electric wire, the connection part, the terminal joint, the terminal and the like is realized through the characteristics of wear resistance, insulation, environment resistance, medium resistance and the like of the thermal shrinkage protective material product.
The reasonable application verification of the multiple series of heat-shrinkable sealing protective materials in helicopter equipment is critical, application evaluation methods, data and comprehensive assessment data are lacked in China at present, and the performance of various heat-shrinkable sealing protective materials in the service environment of the helicopter is difficult to accurately and quantitatively compare and research. At present, multi-series thermal shrinkage sealing protective material application verification for helicopters to be solved is still in a blank stage.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a method for verifying the application of a multi-series thermal shrinkage sealing protective material for a helicopter, which is characterized in that an outline is compiled based on the use characteristics and requirements of the helicopter, a main rotor area of the helicopter is used as a typical use part, a typical test piece is designed and manufactured, an accelerated test environment spectrum is designed, and comprehensive protection application verification and evaluation of a multi-series thermal shrinkage protective material product for aviation is developed through an accelerated aging environment test, an atmospheric natural aging test, a rain test and a performance test, so that the application verification of the multi-series thermal shrinkage sealing protective material for the helicopter is realized, and the domestic blank is filled.
The technical scheme of the invention is as follows: in order to achieve the purpose, the invention provides an application verification method of a multi-series thermal shrinkage sealing protective material for a helicopter, which is characterized by comprising the following steps of:
s1: typical test piece design; the test piece design comprises typical helicopter use part selection and typical test piece design;
s2: manufacturing a typical test piece; manufacturing a typical test piece according to the typical test piece design in the step S1;
s3: and (3) initial performance detection: carrying out appearance, working performance, sealing performance, wear resistance, mechanical property and electrical property detection tests on a typical test piece;
s4: determining an accelerated test environment spectrum and a test program; designing an accelerated test environment spectrum and a test program according to the use environment of the helicopter;
s5: and (3) carrying out an environmental test: performing an environmental test on the typical test piece according to the accelerated test environmental spectrum and the test program determined in the step S4;
s6: and (3) performance detection and verification: after the environmental test is performed on the typical test piece, the test piece is subjected to appearance, working performance, sealing performance, wear resistance, mechanical performance and electrical performance detection tests, and is compared with the initial performance in the step S3 for verification.
In a possible embodiment, in step S1, the selecting of the typical usage location of the helicopter and the designing of the typical test piece specifically include the following steps:
aiming at the application and development design of a thermal shrinkage product on a helicopter, selecting a main rotor area of the helicopter as a typical use part;
designing a typical test piece of the cable assembly for comprehensive examination; the typical test piece of the cable assembly adopts a heat shrinkable tube to protect a cable, one end of the two ends of the typical test piece is a plug end, the other end of the typical test piece is a socket end, and the typical test piece of the cable assembly respectively adopts a mold shrinkage sleeve to seal the connection between the cable and the plug, the socket and the tail accessory.
In one possible embodiment, in the step S2, a typical test piece manufacturing process includes the following steps:
s2.1, selecting a single-core wire, and manufacturing a plurality of wires, wherein the length of each wire is 1 meter;
s2.2, forming 1 group of cable harnesses A by half of the number of the wires, and sleeving a first type of heat-shrinkable tube on the cable harnesses A, wherein the length of the heat-shrinkable tube is 0.9 m; forming another group of cable harnesses B by using the other half of the wires, and sleeving a second type of heat-shrinkable tube on the cable harnesses B, wherein the length of the heat-shrinkable tube is 0.9 m; respectively carrying out complete thermal shrinkage on the thermal shrinkage pipes on the cable harnesses A, B;
s2.3, sequentially sleeving 3 sections of heat shrinkable tubes with the length of 0.15 meter on the cable harness A, B, wherein the heat shrinkable tubes are respectively a third heat shrinkable tube, a fourth heat shrinkable tube and a fifth heat shrinkable tube; and performing complete thermal shrinkage on the thermal shrinkage pipe;
s2.4, one end of a cable harness A, B is connected with a plug and is marked as a plug end, a straight type shrinkage sleeve is sleeved on the plug end, and the plug, the tail accessory and the harness are wrapped together by the straight type shrinkage sleeve; completely thermal shrinking and tightening the die shrinkage sleeve;
s2.5, the other end of the cable harness A, B is connected with a socket and is marked as a socket end, the cable harness A, B respectively penetrates through a Y-shaped shrinkage sleeve and a socket tail accessory, and the socket, the tail accessory and the harness are wrapped together by the Y-shaped shrinkage sleeve; and completely thermally shrinking and tightening the die shrinkage sleeve.
In a possible embodiment, in the step S4, the accelerated test environment spectrum sequentially includes 4 spectrum blocks of a damp heat exposure test, an ultraviolet irradiation test, a low temperature vibration test and a salt spray test in one cycle; the test procedure described carries out ten cycles of accelerated testing, corresponding to a field of use of 1 year.
In one possible embodiment, in the step S5, the damp heat exposure test spectrum block environment parameter is determined as: the test temperature T is 43 ℃, the test humidity RH is 95%, and the test time T is 7 days.
In one possible embodiment, in the step S5, the ultraviolet irradiation test spectrum block environment parameter is determined as: radiation intensity Q ═ 60 +/-10W/m2The temperature T is 55 ℃, and the test time T is 3 days.
In one possible embodiment, in step S5, the environmental parameters of the low-temperature vibration test spectrum block are determined as follows: the test temperature T is (-45 +/-2) DEG C, and the test time T is 30 minutes.
Preferably, the low temperature vibration test spectrum block is performed according to GJB150.16A procedure i.
In one possible embodiment, in the step S5, the salt spray test spectrum block environment parameter is determined as: exposure time: 11 days, wherein the neutral salt spray test is carried out for 8 days, and the acid salt spray test is carried out for 3 days; the pH range of the neutral salt spray test is (6.5-7.2), the sedimentation amount of the salt spray is (1-2) ml/80cm in a 5% NaCl solution2H; the temperature is (35 +/-2) DEG C; acid salt spray test with pH of 4.5-5, 5% NaCl solution and salt spray settling amount of 1-2 ml/80cm2H; the temperature is (35 +/-2) DEG C.
In one possible embodiment, in the steps S3 and S6, the basic operation performance test determines the basic operation performance of the test piece by measuring the contact resistance value of the typical test; and recording the basic working performance detection comparison data of the typical test piece before and after the test.
In one possible embodiment, in the steps S3 and S6, the wear resistance test is performed according to GJB17.9-1984 abrasion test by aviation wire and cable test method.
In one possible embodiment, in said steps S3 and S6, the mechanical properties are measured according to ASTM D2671 and the electrical properties are measured according to ASTM D149.
The invention has the beneficial effects that: the invention designs a complete application verification method of the multi-series thermal shrinkage sealing protective material for the helicopter, fills the blank of the prior art, and realizes the application verification of the multi-series thermal shrinkage sealing protective material on the helicopter; the invention is based on the protection design and comprehensive application examination of the cable in the main rotor area, and realizes the application verification of the multi-series thermal shrinkage sealing protective material on the helicopter; the test piece design, the typical test piece manufacturing flow, the test design and the test design in the application verification process of the multi-series thermal shrinkage sealing protective material are completed innovatively; the method realizes the effect which can not be achieved by the existing traditional method: the application verification of the multi-series thermal shrinkage sealing protective material for the helicopter is realized; provides a new flow verification method and fills the domestic blank.
Drawings
FIG. 1 is a flow chart of the method of the present invention
FIG. 2 is a design drawing of a typical test piece of the present invention
FIG. 3 is a schematic diagram of the test environment spectrum and test program flow of the preferred embodiment of the present invention
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, a method for verifying the application of a plurality of series of thermal shrinkage sealing protective materials for a helicopter is characterized by comprising the following steps:
s1: typical test piece design; the test piece design comprises typical helicopter use part selection and typical test piece design;
s2: manufacturing a typical test piece; manufacturing a typical test piece according to the typical test piece design in the step S1;
s3: detecting the initial performance; carrying out appearance, working performance, sealing performance, wear resistance, mechanical property and electrical property detection tests on a typical test piece;
s4: determining an accelerated test environment spectrum and a test program; designing an accelerated test environment spectrum and a test program according to the use environment of the helicopter;
s5: carrying out an environmental test; performing an environmental test on the typical test piece according to the accelerated test environmental spectrum and the test program determined in the step S4;
s6: performance detection and verification; after the environmental test is performed on the typical test piece, the test piece is subjected to appearance, working performance, sealing performance, wear resistance, mechanical performance and electrical performance detection tests, and is compared with the initial performance in the step S3 for verification.
In a possible embodiment, in step S1, the selecting of the typical usage location of the helicopter and the designing of the typical test piece specifically include the following steps:
aiming at the application and development design of a thermal shrinkage product on a helicopter, selecting a main rotor area of the helicopter as a typical use part;
designing a typical test piece of the cable assembly for comprehensive examination; the typical test piece of the cable assembly adopts a heat shrinkable tube to protect a cable, the total length of the typical test piece is about 1.05 m, the typical test piece comprises an electric connector at two ends, one end of each end of the electric connector is a plug end, the other end of each end of the electric connector is a socket end, the electric connector and the tail accessory are respectively sealed by adopting a mold shrinkage sleeve to be connected with the plug, the socket and the tail accessory, and the electric connector and the tail accessory are in accordance with GJB599 III series.
As shown in fig. 2, in one possible embodiment, in the step S2, a typical test piece manufacturing process includes the following steps:
s2.1, selecting single-core 600V silver-plated copper wire core No. 20 wire gauge wires, and manufacturing 32 wires, wherein the length of each wire is 1 meter;
s2.2, forming 1 group of cable harness A by 16 leads, sleeving a domestic heat shrinkable tube CRT-218-1/2-0 on the cable harness A, wherein the length of the heat shrinkable tube is 0.9 meter; another 16 leads form another group of cable harness B, and a domestic heat shrinkable tube CRT-220-1/2-0 is sleeved on the cable harness B, and the length of the heat shrinkable tube is 0.9 m; respectively carrying out complete thermal shrinkage on the thermal shrinkage pipes on the cable harnesses A, B;
s2.3, sequentially sleeving 3 sections of 0.15-meter-long heat-shrinkable tubes with the models of CRT-770-1-0, CRT-780-1-0 and CRT-790-1-0 on the cable harness A, B; and performing complete thermal shrinkage on the thermal shrinkage pipe;
s2.4, one end of a cable harness A, B is connected with a plug and is marked as a plug end, a straight type shrinkage sleeve R202D163-25/86-0 is sleeved at the plug end, and the plug, a tail accessory and the harness are wrapped together by the straight type shrinkage sleeve; completely thermal shrinking and tightening the die shrinkage sleeve;
s2.5, the other end of the cable harness A, B is connected with a socket and is marked as a socket end, the cable harness A, B respectively passes through a Y-shaped shrinkage sleeve R381A302-71/97-0 and a socket tail accessory, and the socket, the tail accessory and the cable harness are wrapped together by the Y-shaped shrinkage sleeve; and completely thermally shrinking and tightening the die shrinkage sleeve.
As shown in fig. 3, in a possible embodiment, in the step S4, the accelerated test environment spectrum includes 4 spectrum blocks of damp-heat exposure, ultraviolet irradiation, low-temperature vibration, and salt fog for one cycle; the test procedure described carries out ten cycles of accelerated testing, corresponding to a field of use of 1 year.
In a possible embodiment, in the step S4, the accelerated test environment spectrum sequentially includes 4 spectrum blocks of a damp heat exposure test, an ultraviolet irradiation test, a low temperature vibration test and a salt spray test in one cycle; the test procedure described carries out ten cycles of accelerated testing, corresponding to a field of use of 1 year.
In one possible embodiment, in the step S5, the damp heat exposure test spectrum block environment parameter is determined as: the test temperature T is 43 ℃, the test humidity RH is 95%, and the test time T is 7 days.
In one possible embodiment, in the step S5, the ultraviolet irradiation test spectrum block environment parameter is determined as: radiation intensity Q ═ 60 +/-10W/m2The temperature T is 55 ℃, and the test time T is 3 days.
In one possible embodiment, in step S5, the environmental parameters of the low-temperature vibration test spectrum block are determined as follows: the test temperature T is (-45 +/-2) DEG C, and the test time T is 30 minutes.
Preferably, the low temperature vibration test spectrum block is performed according to GJB150.16A procedure i.
In one possible embodiment, in the step S5, the salt spray test spectrum block environment parameter is determined as: exposure time: 11 days, wherein the neutral salt spray test is carried out for 8 days, and the acid salt spray test is carried out for 3 days; the pH range of the neutral salt spray test is 6.5-7.2, the precipitation amount of the salt spray is (1-2) ml/80cm2H; the temperature is (35 +/-2) DEG C; acid salt spray test with pH of 4.5-5, 5% NaCl solution and salt spray settling amount of 1-2 ml/80cm2H; the temperature is (35 +/-2) DEG C.
In one possible embodiment, in the steps S3 and S6, the basic operation performance test determines the basic operation performance of the test piece by measuring the contact resistance value of the typical test; and recording the basic working performance detection comparison data of the typical test piece before and after the test.
In one possible embodiment, in the steps S3 and S6, the wear resistance test is performed according to GJB17.9-1984 abrasion test by aviation wire and cable test method.
In one possible embodiment, in said steps S3 and S6, the mechanical properties are measured according to ASTM D2671 and the electrical properties are measured according to ASTM D149.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. A multi-series thermal shrinkage sealing protective material application verification method for a helicopter is characterized by comprising the following steps:
s1: typical test piece design; the test piece design comprises typical helicopter use part selection and typical test piece design;
s2: manufacturing a typical test piece; manufacturing a typical test piece according to the typical test piece design in the step S1;
s3: and (3) initial performance detection: carrying out appearance, working performance, sealing performance, wear resistance, mechanical property and electrical property detection tests on a typical test piece;
s4: determining an accelerated test environment spectrum and a test program; designing an accelerated test environment spectrum and a test program according to the use environment of the helicopter;
s5: and (3) carrying out an environmental test: performing an environmental test on the typical test piece according to the accelerated test environmental spectrum and the test program determined in the step S4;
s6: and (3) performance detection and verification: after the environmental test is performed on the typical test piece, the test piece is subjected to appearance, working performance, sealing performance, wear resistance, mechanical performance and electrical performance detection tests, and is compared with the initial performance in the step S3 for verification.
2. The method for verifying the application of the multiple series of heat-shrinkable sealing and protecting materials for the helicopter according to claim 1, wherein in the step S1, the selection of the typical usage position and the design of the typical test piece of the helicopter specifically comprise the following steps:
aiming at the application and development design of a thermal shrinkage product on a helicopter, selecting a main rotor area of the helicopter as a typical use part;
designing a typical test piece of the cable assembly for comprehensive examination; the typical test piece of the cable assembly adopts a heat shrinkable tube to protect a cable, one end of the two ends of the typical test piece is a plug end, the other end of the typical test piece is a socket end, and the typical test piece of the cable assembly respectively adopts a mold shrinkage sleeve to seal the connection between the cable and the plug, the socket and the tail accessory.
3. The method for verifying the application of the multi-series thermal shrinkage sealing protective material for the helicopter of claim 1, wherein in the step S4, the accelerated test environment spectrum sequentially comprises 4 spectrum blocks of a damp-heat exposure test, an ultraviolet irradiation test, a low-temperature vibration test and a salt spray test in one cycle; the test procedure described carries out ten cycles of accelerated testing, corresponding to a field of use of 1 year.
4. The method for verifying the application of the multiple series of heat-shrinkable sealing and protecting materials for the helicopter of claim 3, wherein in the step S5, the environmental parameters of the wet heat exposure test spectrum block are determined as follows: the test temperature T is 43 ℃, the test humidity RH is 95%, and the test time T is 7 days.
5. A plurality of lines for helicopters in accordance with claim 4The column shrinkage sealing protective material application verification method is characterized in that in the step S5, the ultraviolet irradiation test spectrum block environment parameters are determined as follows: radiation intensity Q ═ 60 +/-10W/m2The temperature T is 55 ℃, and the test time T is 3 days.
6. The method for verifying the application of the multiple series of heat-shrinkable sealing and protecting materials for the helicopter of claim 5, wherein in the step S5, the environmental parameters of the low-temperature vibration test spectrum block are determined as follows: the test temperature T is (-45 +/-2) DEG C, and the test time T is 30 minutes.
7. The method for verifying the application of the multiple series of heat-shrinkable sealing protective materials for the helicopter of claim 6, wherein in the step S5, the environmental parameters of the salt spray test spectrum block are determined as follows: exposure time: 11 days, wherein the neutral salt spray test is carried out for 8 days, and the acid salt spray test is carried out for 3 days; the pH range of the neutral salt spray test is 6.5-7.2, the precipitation amount of the salt spray is (1-2) ml/80cm2H; the temperature is (35 +/-2) DEG C; acid salt spray test with pH of 4.5-5, 5% NaCl solution and salt spray settling amount of 1-2 ml/80cm2H; the temperature is (35 +/-2) DEG C.
8. The method for verifying the application of the heat-shrinkable sealing and shielding material for helicopters according to claim 1, wherein in the steps S3 and S6, the basic working performance test determines the basic working performance of the test piece by measuring the contact resistance value between the front and rear conductors of the typical test piece; and recording the basic working performance detection comparison data of the typical test piece before and after the test.
9. The method for verifying the application of the heat-shrinkable sealing and protecting material for the helicopters according to claim 1, wherein the wear resistance test is performed according to GJB17.9-1984 abrasion test of aviation wire and cable test method in steps S3 and S6.
10. The method for verifying the application of the multi-series heat-shrinkable sealing and shielding material for the helicopter of claim 1, wherein in the steps S3 and S6, the mechanical properties are tested according to ASTM D2671, and the electrical properties are tested according to ASTM D149.
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101482484A (en) * | 2009-01-21 | 2009-07-15 | 中国兵器工业第五九研究所 | Simulated acceleration test method for coating |
| CN103852411A (en) * | 2012-12-04 | 2014-06-11 | 天津市电力公司 | Method for evaluating running aging of thermal shrinkage insulating material |
| CN106290126A (en) * | 2016-07-29 | 2017-01-04 | 中车青岛四方机车车辆股份有限公司 | A kind of environmental suitability evaluation methodology of rail vehicle amortisseur elastomeric material |
| CN206283073U (en) * | 2016-11-29 | 2017-06-27 | 中国直升机设计研究所 | A kind of lifting airscrew accordion cable |
| CN208109937U (en) * | 2018-04-02 | 2018-11-16 | 国网江西省电力有限公司电力科学研究院 | A kind of measurement of soft graphite grounding body ground resistance and accelerated corrosion experimental rig |
| CN111551464A (en) * | 2020-04-14 | 2020-08-18 | 中国石油天然气集团有限公司 | Accelerated test method for testing aging performance of non-metallic material for oil and gas transmission |
| CN111896465A (en) * | 2020-08-14 | 2020-11-06 | 中国兵器工业第五九研究所 | Evaluation and verification method for corrosion protection measures of coupling parts in atmospheric environment of south sea island |
| CN112666003A (en) * | 2020-12-04 | 2021-04-16 | 中国航发北京航空材料研究院 | Accelerated test method for simulating coupling effect of carrier-based platform multi-element environmental factors |
-
2021
- 2021-04-20 CN CN202110427425.0A patent/CN113155720A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101482484A (en) * | 2009-01-21 | 2009-07-15 | 中国兵器工业第五九研究所 | Simulated acceleration test method for coating |
| CN103852411A (en) * | 2012-12-04 | 2014-06-11 | 天津市电力公司 | Method for evaluating running aging of thermal shrinkage insulating material |
| CN106290126A (en) * | 2016-07-29 | 2017-01-04 | 中车青岛四方机车车辆股份有限公司 | A kind of environmental suitability evaluation methodology of rail vehicle amortisseur elastomeric material |
| CN206283073U (en) * | 2016-11-29 | 2017-06-27 | 中国直升机设计研究所 | A kind of lifting airscrew accordion cable |
| CN208109937U (en) * | 2018-04-02 | 2018-11-16 | 国网江西省电力有限公司电力科学研究院 | A kind of measurement of soft graphite grounding body ground resistance and accelerated corrosion experimental rig |
| CN111551464A (en) * | 2020-04-14 | 2020-08-18 | 中国石油天然气集团有限公司 | Accelerated test method for testing aging performance of non-metallic material for oil and gas transmission |
| CN111896465A (en) * | 2020-08-14 | 2020-11-06 | 中国兵器工业第五九研究所 | Evaluation and verification method for corrosion protection measures of coupling parts in atmospheric environment of south sea island |
| CN112666003A (en) * | 2020-12-04 | 2021-04-16 | 中国航发北京航空材料研究院 | Accelerated test method for simulating coupling effect of carrier-based platform multi-element environmental factors |
Non-Patent Citations (1)
| Title |
|---|
| 袁猛等 * |
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