CN112526210B - Real-time monitoring test system and method for thermal vibration combined insulativity of aircraft cable assembly - Google Patents
Real-time monitoring test system and method for thermal vibration combined insulativity of aircraft cable assembly Download PDFInfo
- Publication number
- CN112526210B CN112526210B CN202011241562.7A CN202011241562A CN112526210B CN 112526210 B CN112526210 B CN 112526210B CN 202011241562 A CN202011241562 A CN 202011241562A CN 112526210 B CN112526210 B CN 112526210B
- Authority
- CN
- China
- Prior art keywords
- vibration
- insulation
- test
- heating box
- mounting platform
- 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.)
- Active
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 117
- 238000012544 monitoring process Methods 0.000 title claims abstract description 34
- 238000000034 method Methods 0.000 title claims abstract description 27
- 238000009413 insulation Methods 0.000 claims abstract description 88
- 238000010438 heat treatment Methods 0.000 claims abstract description 83
- 239000012774 insulation material Substances 0.000 claims abstract description 9
- 238000009434 installation Methods 0.000 claims description 20
- 230000004044 response Effects 0.000 claims description 11
- 238000010998 test method Methods 0.000 claims description 9
- 230000008569 process Effects 0.000 claims description 7
- 230000001133 acceleration Effects 0.000 claims description 4
- 230000003595 spectral effect Effects 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- 239000004020 conductor Substances 0.000 claims description 2
- 230000032683 aging Effects 0.000 description 5
- 230000000712 assembly Effects 0.000 description 4
- 238000000429 assembly Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 238000012986 modification Methods 0.000 description 4
- 230000004048 modification Effects 0.000 description 4
- 229920000742 Cotton Polymers 0.000 description 2
- 239000011111 cardboard Substances 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000011056 performance test Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 230000008054 signal transmission Effects 0.000 description 2
- 230000003321 amplification Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002301 combined effect Effects 0.000 description 1
- 238000012790 confirmation Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000004703 cross-linked polyethylene Substances 0.000 description 1
- 229920003020 cross-linked polyethylene Polymers 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000010453 quartz Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
-
- 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
- G01R27/025—Measuring very high resistances, e.g. isolation resistances, i.e. megohm-meters
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/04—Monodirectional test stands
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention provides a real-time monitoring test system and a method for thermal vibration combined insulativity of an aircraft cable assembly, wherein the system comprises a mounting platform, a heating box control device, a vibrating table, a vibration control acquisition device, a temperature data acquisition device and a cable insulation test device; the mounting platform is fixed on the vibrating table, a test piece and a temperature sensor are arranged on the mounting platform, a flexible heat insulation material is filled between the opening and the mounting platform and covers the mounting platform, the temperature in the heating box is controlled by the heating box control device, the position of the heating box is adjusted, vibration data of the vibrating table are collected by the vibration control collecting device, the temperature sensor data in the heating box are collected by the temperature data collecting device, and the insulation property of the test piece is monitored in real time by a cable insulation testing device and one end of the test piece extending out of the heating box. The invention can monitor the insulation performance of the aircraft cable assembly on line and in real time under the severe high-temperature vibration condition.
Description
Technical Field
The invention belongs to the technical field of performance test of aircraft cable assemblies, and particularly relates to a thermal vibration combined test system and a thermal vibration combined test method suitable for a cable assembly.
Background
As aircraft flight mach numbers increase, the combined effects of severe aerodynamic thermal and vibratory loads present challenges for the laying, deployment, and thermal protection design of aircraft cable assemblies. Also, cabling and electrical connector arrangements are often less than ideal due to space constraints in the aircraft structural design. Thus, the adaptability of the cable assembly to thermal shock environments is a technical risk point. The cable assembly is monitored in real time on line in insulation by adopting a proper heat vibration combined test method, and plays a very critical role in ensuring flight safety.
The ground heat vibration combined test technology plays an important role in the environmental adaptability assessment of the aircraft structure and equipment. However, in general, the heating mode such as quartz lamp is adopted, and the heating requirement on uniformity of the cable and the electric connector cannot be met on the vibrating table. And the cable and the electric connector are arranged in various forms, which are different from the installation form of the conventional structure. The general structural heat and vibration combined test method is not applicable, and a heat and vibration combined test method applicable to the aircraft cable assembly needs to be developed.
At present, corresponding heat vibration combined aging test devices are mainly developed for underground laying power cable lines, overhead cables, underwater cables and the like at home and abroad. Such as a thermal-vibration combined aging test device (CN 206399790U) for a cable sample, a thermal-vibration combined aging test device (CN 205262935U) for an XLPE insulation sample section, a test device (CN 202939241U) for electric, thermal and vibration combined aging of an umbilical cable unit and the like, mainly researching the aging phenomenon of the cable.
The aircraft cable assembly is different from the cable in the aspects of service environment, cable characteristics, failure modes and the like, so that the system research on the insulativity of the aircraft cable assembly under the heat vibration combined condition is difficult to realize by adopting the test device: firstly, the pneumatic heating condition is harsh, and the service temperature of the aircraft cable assembly is far higher than that of the cable; secondly, the characteristics of the cable assembly are different, the aircraft cable generally comprises a cable net composed of a plurality of different types of wires with insulating layers, and special design is carried out on the cable assembly to meet the temperature resistance requirement; and thirdly, the insulation performance of the cable assembly is possibly reduced in the thermal vibration test process, and the insulation performance is recovered after the thermal vibration test is finished, if the cable assembly is only tested, the risk of sudden air leakage is difficult to detect. Therefore, performance tests are performed on the aircraft cable assembly under severe thermal shock conditions, and a high-precision control method and a monitoring test means are required to be adopted.
Disclosure of Invention
Aiming at the technical problem that the aircraft cable assembly in the prior art cannot monitor the insulation performance change in real time under the heat vibration combined condition, the invention provides a real-time monitoring test system and a real-time monitoring test method for the heat vibration combined insulation performance of the aircraft cable assembly, which can monitor the insulation performance of the aircraft cable assembly in real time on line under the severe high-temperature vibration condition.
The technical scheme adopted for solving the technical problems is as follows:
a real-time monitoring test system for thermal vibration combined insulativity of an aircraft cable assembly comprises a mounting platform, a heating box control device, a vibrating table, a vibration control acquisition device, a temperature data acquisition device and a cable insulation test device; the mounting platform is fixed on the vibrating table, test pieces and temperature sensors are arranged on the mounting platform, the mounting platform is covered by the opening at the bottom of the heating box, flexible heat insulation materials are filled between the opening and the mounting platform, the heating box control device controls the temperature in the heating box and adjusts the position of the heating box, the vibration control acquisition device acquires vibration data of the vibrating table, the temperature data acquisition device acquires temperature sensor data in the heating box, and the cable insulation test device is connected with one end of the test piece, which extends out of the heating box, so that the insulation property of the test pieces is monitored in real time.
Further, the test piece comprises a group of connected electric connectors and a section of cables carried by two ends of each electric connector, one end of each cable extends out of the heating box to be insulated by the heat shrinkage tube, and the other end of each cable extends out of the heating box to be connected with the cable insulation testing device.
Further, a plurality of sleeves, clamping plates and clamping clamps for installing test pieces are arranged on the upper surface of the installation platform.
Further, the non-checking section of the test piece positioned in the heating box is wrapped by the heat insulation layer, and the non-checking section positioned outside the heating box is fixed on the mounting platform by the fixing belt.
Furthermore, the bottom of the mounting platform is close to the position connected with the vibrating table, and the vibrating table is protected in a water cooling mode.
A real-time monitoring test method for thermal vibration combined insulation of an aircraft cable assembly comprises the following steps:
s1, assembling a thermal vibration combined insulation real-time monitoring test system, mounting a test piece on a mounting platform, and checking the insulation performance of the test piece by adopting a cable insulation test device;
s2, performing normal-temperature vibration debugging on the vibration table and the mounting platform by adopting a response control method, and enabling a vibration measuring point on the upper surface of the mounting platform to meet a vibration test condition by debugging a control point on the vibration table outside the heating zone;
s3, controlling the heating box to rise to the test temperature according to the maximum temperature rise rate, controlling the heating box to descend to the mounting platform by the heating box control device, and plugging a gap between the heating box and the mounting platform by adopting a flexible heat insulation material;
s4, starting the vibration table to perform a test piece heat vibration combined test, and performing vibration control according to the vibration conditions of the vibration table debugged in the step S2;
s5, monitoring the insulation performance of the cable assembly by adopting a cable insulation testing device in the whole test process, and closing the cable insulation testing device after the heat vibration combined test is finished for a period of time;
s6, judging whether the cable assembly has an internal conductor insulation layer failure or not by monitoring whether insulation resistance values between any two wire pairs in each cable assembly are lower than allowable values in real time.
Further, the method also comprises the following steps of
If the cable assembly has the condition that the insulation layer of the internal lead fails, the insulation property of the cable assembly is monitored in real time through a pure heating test and a normal-temperature vibration test, and the reason of the insulation failure is determined.
Further, the step S2 specifically includes the following steps:
s2.1, arranging vibration sensors on the vibration table and the upper surface of the mounting platform, and connecting with a vibration control acquisition device;
s2.2, taking a vibration sensor on the upper surface of the mounting platform as a control point, taking the vibration sensor on the vibration table as a measuring point, performing vibration debugging, and stopping debugging after confirming that the vibration sensor on the upper surface of the mounting platform meets the vibration condition;
s2.3, collecting vibration response of the vibration sensor of the vibration table as a newly set vibration condition, taking the vibration sensor of the vibration table as a control point, and performing vibration debugging again by taking the vibration sensor on the upper surface of the mounting platform as a measuring point to confirm that the vibration sensor on the upper surface of the mounting platform meets the original vibration condition;
s2.4, removing a vibration sensor positioned on the installation platform in the heating zone, and performing a thermal vibration combined test by only controlling the vibration sensor on the vibration table.
Further, the step S2.2 vibration debugging includes two times, namely-6 dB condition vibration debugging and 0dB condition vibration debugging, and the vibration debugging in the step S2.3 is the 0dB condition.
Further, the vibration condition control requirements satisfied by the vibration sensor on the upper surface of the mounting platform in the step S2.2 and the vibration response requirements satisfied by the vibration sensor on the upper surface of the mounting platform in the step S2.3 are specifically: the deviation of the acceleration power spectral density is controlled within +/-3 dB.
Compared with the prior art, the invention has the beneficial effects that:
1) The invention provides a real-time monitoring test system and method for thermal vibration combined insulativity of an aircraft cable assembly. The test piece comprises a group of connected electric connectors, two ends of each electric connector carry a section of cable, one end of each cable extends out of the heating box and is subjected to insulation treatment by adopting the heat shrinkage tube, the other end of each cable extends out of the heating box and is connected with the cable insulation test device, and the cable insulation test device is far away from the vibration heating device by arranging a non-checking section long enough. Secondly, on the premise of ensuring heat sealing and vibration signal transmission, the installation platform is designed into a cable wiring space, so that on one hand, the insulation property of the non-checking end is ensured when the heat shrinkage pipe end appears outside the heating area, and on the other hand, the cable is connected with the insulation testing device. And thirdly, the insulation testing system is started in advance before the thermal vibration to monitor the insulation property, and the insulation testing system is closed after the thermal vibration is finished for a period of time, so that the occurrence time of faults is accurately positioned, and the phenomenon of missing detection is avoided. Whether the insulation layer failure of the inner wire is generated in the cable assembly is judged by monitoring whether the insulation resistance value between every two wire pairs with the insulation layers in the cable assemblies is lower than an allowable value in real time.
2) According to the real-time monitoring test system and method for the thermal vibration combined insulation of the aircraft cable assembly, the simulation of the real installation form and the fitting size of the cable assembly on the aircraft is realized through the design of the installation platform. The sleeve with different sizes simulates the tight degree of the fitting of the cable in the tunnel pipe, and the sleeve is matched with the cable wiring space on the mounting platform, so that the cable cannot be damaged under the vibration condition due to the fact that the clamp is self, and the phenomenon of vibration amplification of the cable is avoided by the fixing belt of the mounting platform. The clamps with different specifications and distances are arranged through the mounting platform, so that the real fixing mode of the real cable is simulated. The card board is used to simulate a particular cable or electrical connector fixture.
3) The invention provides a system-level method for monitoring and testing the thermal-vibration combined insulativity of an aircraft cable assembly in real time, which can realize high-precision vibration control on the cable assembly through a vibration response control method.
The invention provides a new test method for the adaptability monitoring of the aircraft cable assembly under the severe high-temperature vibration condition, plays a verification role for the selection, the thermal protection scheme and the constraint mode of the cable assembly, and provides guarantee for flight safety.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 is a schematic diagram of an aircraft cable assembly thermal-vibration combined insulation real-time monitoring test system provided by an embodiment of the invention;
fig. 2 is a schematic structural view of an aircraft cable assembly mounting platform according to an embodiment of the present invention.
Wherein, 1 is mounting platform, 2 is the cable, 3 is the pyrocondensation pipe, 4 is the insulating layer, 5 is thermal-insulated cotton blanket, 6 is the fixed band, 7 is the sleeve, 8 is the cardboard.
Detailed Description
Specific embodiments of the present invention are described in detail below. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.
It should be noted here that, in order to avoid obscuring the present invention due to unnecessary details, only the device structures and/or processing steps closely related to the solution according to the present invention are shown in the drawings, while other details not greatly related to the present invention are omitted.
The invention provides a real-time monitoring test system for thermal vibration combined insulativity of an aircraft cable assembly, which comprises a mounting platform 1, a heating box control device, a vibrating table, a vibration control acquisition device, a temperature data acquisition device and a cable insulation test device, wherein the mounting platform is fixed on the vibrating table, a test piece is arranged on the mounting platform, wiring spaces are arranged on two sides of the mounting platform according to cable sizes, an opening at the bottom of the heating box covers the mounting platform, flexible insulation materials are filled between the opening and the mounting platform, the heating box control device controls the temperature of the heating box and adjusts the position of the heating box, the vibration control acquisition device acquires vibration data of the vibrating table and the mounting platform, the temperature data acquisition device acquires and records temperature sensor data in the heating box, the cable insulation test device is connected with one end of the test piece extending out of the heating box, and the insulativity of the test piece is monitored in real time. The invention relates to an aircraft cable assembly test piece participating in a test, which comprises a cable and electric connectors, wherein after a group of electric connectors are connected, two ends of the electric connectors respectively carry a section of cable, one end of the cable extends out of a heating box to be insulated by adopting a heat shrinkage tube 3, and the other end of the cable extends out of the heating box to be connected with a cable insulation test device, so that the insulation performance of the cable is monitored on line in real time.
The mounting platform 1 adopts a T-shaped structure and is mounted on a vibrating table, and the vibrating table adopts a vertical table for transmitting vibration signals. Because the thermal load is severe, the vibration table is protected by adopting a water cooling mode at the bottom of the mounting platform and near the position connected with the vibration table.
The upper surface of the mounting platform 1 is provided with sleeves 7, clamping plates 8, clamping clamps and the like with different sizes, which are used for simulating the real mounting form of cables and electric connectors on an aircraft and the fitting size with the surroundings, as shown in fig. 2. Specifically, the sleeves 7 with different sizes are used for simulating the fitting state of the cable and the pipe wall in the oil tank tunnel pipe, and the sleeve size needs to be designed according to the real gap; the clamping plate 8 is used for fixing special cables or electric connectors to the mounting platform; the clamp is used for simulating the fixing mode of a conventional cable, and the clamp type, the interval and the cable length between the clamps are consistent with the actual state. The assessment sections of the cable and the electric connector are respectively arranged in the sleeve and the clamping plate according to the actual installation form, or are fixed by the clamping hoop, the non-assessment sections of the cable 2 positioned in the heating box are wrapped by the heat insulation layer 4, and the non-assessment sections positioned outside the heating box are fixed on the cylindrical surfaces of the installation platform positioned outside the heating zone by the fixing belt, as shown in fig. 1.
The heating box is an automatic temperature control heating box, an opening of the heating box is downward, after the heating box is preheated to a test temperature, the heating box control device controls the heating box to descend to the level of the upper plane of the opening and the upper plane of the installation platform, gaps around the opening and the installation platform are plugged by flexible heat insulation materials such as heat insulation cotton felt 5, and the heating box is used for heating and controlling a cable and an electric connector. In the vibration loading process of the mounting platform, the lifting position of the heating box does not change along with vibration, and the heating box is blocked by adopting a flexible heat insulation material between the heating box and the mounting platform, so that the heating box is prevented from leaking heat in the vibration process.
The temperature sensor is arranged on the upper surface of the mounting platform, is arranged in the air of the same horizontal plane near the cable assembly in a bracket and other modes, is connected with the temperature data acquisition device and is used for carrying out real-time on-line monitoring on the temperature around the test piece in the heating box.
The invention provides a real-time monitoring test method for heat vibration combined insulation of an aircraft cable assembly, which comprises the following steps:
1. the thermal vibration combined insulation real-time monitoring test system is assembled, a test piece is mounted on the mounting platform, and the locking positions of the sleeve, the clamping plate, the clamping hoop and other connecting pieces of the mounting platform are marked for judging whether the connecting pieces are loose or not after the test. One end of the cable of the test piece is subjected to insulation treatment by adopting the heat shrinkage pipe, the cable is fixed outside the heating area of the mounting platform, the other end of the cable is also fixed outside the heating area of the mounting platform, the cable insulation testing system is communicated, and the cable insulation testing device is used for checking the insulation performance of the cable assembly.
2. And the vibration table and the mounting platform are subjected to normal-temperature vibration debugging by adopting a response control method, and the mounting platform needs to be ensured to meet vibration test conditions due to poor high-frequency signal transmission in connection relation, so that high-precision vibration control on cables and electric connectors is realized. The method comprises the following specific steps:
and 2.1, arranging vibration sensors on the vibration table and the upper surface of the mounting platform, and connecting with a vibration control acquisition device.
2.2, taking the vibration sensor on the upper surface of the mounting platform as a control point, taking the vibration sensor on the vibration table as a measuring point, performing vibration debugging, respectively performing-6 dB condition vibration debugging and 0dB condition vibration debugging, and stopping debugging after confirming that the vibration sensor on the upper surface of the mounting platform meets the vibration condition. In this embodiment, the control requirements of the vibration conditions are specifically: the deviation of the acceleration power spectral density is controlled within +/-3 dB.
And 2.3, collecting vibration response of the vibration sensor of the vibration table as a newly set vibration condition, taking the vibration sensor of the vibration table as a control point, and debugging again by taking the vibration sensor on the upper surface of the mounting platform as a measuring point. And (3) performing vibration debugging under the condition of 0dB, and confirming that the vibration sensor on the upper surface of the mounting platform meets the original vibration condition, wherein the vibration response requirement is specifically as follows: the deviation of the acceleration power spectral density is controlled within +/-3 dB. After confirmation, a formal thermal vibration test is performed by using a vibration sensor on the vibration table as a control point.
In this embodiment, the newly set vibration conditions are: 2.2, vibration response of the sensor position of the vibrating table during vibration debugging of the 0dB condition; the original vibration conditions are as follows: vibration conditions in step 2.2.
And 2.4, removing the vibration sensor positioned on the installation platform in the heating zone, and performing a heat vibration combined test by only adopting the vibration sensor on the vibration table for control.
The vibration sensor on the upper surface of the mounting platform can meet the vibration test condition by debugging the control point on the vibration table outside the heating zone, and only the data of the vibration sensor on the vibration table is controlled and monitored in the formal heat and vibration combined test process, so that the vibration sensor is not required to be added on the mounting platform.
3. Controlling the heating box to rise to the test temperature according to the maximum temperature rise rate, controlling the heating box to drop to the mounting platform according to the speed of 0.05m/s by the heating box control device, and plugging a gap between the heating box and the mounting platform by adopting a flexible heat insulation material;
4. and (3) starting the vibration table to perform a formal heat vibration combined test of the cable assembly, and performing vibration control according to the vibration conditions of the vibration table debugged in the step 2.3.
5. The cable insulation testing device is adopted in the whole test process to monitor the insulation performance of the cable assembly, and the cable insulation testing device is closed after the thermal vibration is finished for a period of time.
6. Whether the insulation layer failure of the inner wire is generated in the cable assembly is judged by monitoring whether the insulation resistance value between every two wire pairs with the insulation layers in the cable assemblies is lower than an allowable value in real time. If the condition that the insulation layer of the internal lead fails, the test system is adopted, the insulation of the cable assembly is monitored in real time through a pure heating test and the insulation of the cable assembly is monitored in real time through a normal-temperature vibration test, and whether the reason of the insulation failure is a thermal condition or a vibration condition is positioned. The cable assembly may be dissected for inspection after testing.
Features that are described and/or illustrated above with respect to one embodiment may be used in the same way or in a similar way in one or more other embodiments and/or in combination with or instead of the features of the other embodiments.
It should be emphasized that the term "comprises/comprising" when used herein is taken to specify the presence of stated features, integers, steps or components but does not preclude the presence or addition of one or more other features, integers, steps, components or groups thereof.
The many features and advantages of the embodiments are apparent from the detailed specification, and thus, it is intended by the appended claims to cover all such features and advantages of the embodiments which fall within the true spirit and scope thereof. Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the embodiments of the invention to the exact construction and operation illustrated and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope thereof.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
The invention is not described in detail in a manner known to those skilled in the art.
Claims (8)
1. The real-time monitoring test method for the thermal vibration combined insulation performance of the aircraft cable assembly is characterized by comprising the following steps of:
s1, assembling a thermal vibration combined insulation real-time monitoring test system, mounting a test piece on a mounting platform, and checking the insulation performance of the test piece by adopting a cable insulation test device;
the thermal vibration combined insulation real-time monitoring test system comprises a mounting platform, a heating box control device, a vibration table, a vibration control acquisition device, a temperature data acquisition device and a cable insulation test device; the installation platform is fixed on the vibration table, a test piece and a temperature sensor are arranged on the installation platform, an opening at the bottom of the heating box covers the installation platform, a flexible heat insulation material is filled between the opening and the installation platform, the heating box control device controls the temperature in the heating box and adjusts the position of the heating box, the vibration control acquisition device acquires vibration data of the vibration table, the temperature data acquisition device acquires temperature sensor data in the heating box, the cable insulation test device is connected with one end of the test piece extending out of the heating box through a cable, and the insulation property of the test piece is monitored in real time;
s2, performing normal-temperature vibration debugging on the vibration table and the mounting platform by adopting a response control method, and enabling a vibration measuring point on the upper surface of the mounting platform to meet a vibration test condition by debugging a control point on the vibration table outside the heating zone;
the step S2 specifically includes the following steps:
s2.1, arranging vibration sensors on the vibration table and the upper surface of the mounting platform, and connecting with a vibration control acquisition device;
s2.2, taking a vibration sensor on the upper surface of the mounting platform as a control point, taking the vibration sensor on the vibration table as a measuring point, performing vibration debugging, and stopping debugging after confirming that the vibration sensor on the upper surface of the mounting platform meets the vibration condition;
s2.3, collecting vibration response of the vibration sensor of the vibration table as a newly set vibration condition, taking the vibration sensor of the vibration table as a control point, and performing vibration debugging again by taking the vibration sensor on the upper surface of the mounting platform as a measuring point to confirm that the vibration sensor on the upper surface of the mounting platform meets the original vibration condition;
s2.4, removing a vibration sensor positioned on a mounting platform in the heating zone, and performing a heat vibration combined test by controlling only the vibration sensor on the vibration table;
s3, controlling the heating box to rise to the test temperature according to the maximum temperature rise rate, controlling the heating box to descend to the mounting platform by the heating box control device, and plugging a gap between the heating box and the mounting platform by adopting a flexible heat insulation material;
s4, starting the vibration table to perform a test piece heat vibration combined test, and performing vibration control according to the vibration conditions of the vibration table debugged in the step S2;
s5, monitoring the insulation performance of the cable assembly by adopting a cable insulation testing device in the whole test process, and closing the cable insulation testing device after the heat vibration combined test is finished for a period of time;
s6, judging whether the cable assembly has an internal conductor insulation layer failure or not by monitoring whether insulation resistance values between any two wire pairs in each cable assembly are lower than allowable values in real time.
2. The method for real-time monitoring and testing of heat and vibration combined insulation of an aircraft cable assembly according to claim 1, further comprising the steps of:
if the cable assembly has the condition that the insulation layer of the internal lead fails, the insulation property of the cable assembly is monitored in real time through a pure heating test and a normal-temperature vibration test, and the reason of the insulation failure is determined.
3. The method for real-time monitoring and testing of thermal vibration combined insulation of an aircraft cable assembly according to claim 1, wherein the step S2.2 of vibration debugging comprises two times of-6 dB condition vibration debugging and 0dB condition vibration debugging, respectively, and the vibration debugging in the step S2.3 is 0dB condition.
4. The method for real-time monitoring and testing of heat and vibration combined insulation of an aircraft cable assembly according to claim 1, wherein vibration condition control requirements met by a vibration sensor on the upper surface of the installation platform in step S2.2 and vibration response requirements met by the vibration sensor on the upper surface of the installation platform in step S2.3 are specifically as follows: the deviation of the acceleration power spectral density is controlled within +/-3 dB.
5. The method for monitoring and testing the thermal vibration combined insulation performance of the aircraft cable assembly in real time according to claim 1, wherein the test piece comprises a group of connected electric connectors and a section of cable carried by two ends of each electric connector, one end of the cable extends out of the heating box to be insulated by adopting a heat shrinkage tube, and the other end of the cable extends out of the heating box to be connected with a cable insulation testing device.
6. The method for real-time monitoring and testing of heat and vibration combined insulation of an aircraft cable assembly according to claim 1, wherein a plurality of sleeves, clamping plates and clamping clamps for installing test pieces are arranged on the upper surface of the installation platform.
7. The method for real-time monitoring and testing of heat and vibration combined insulation of an aircraft cable assembly according to claim 1, wherein the non-checking section of the test piece positioned in the heating box is wrapped by a heat insulation layer, and the non-checking section positioned outside the heating box is fixed on the mounting platform by a fixing belt.
8. The method for real-time monitoring and testing of heat and vibration combined insulation of an aircraft cable assembly according to claim 1, wherein the vibration table is protected by water cooling at the bottom of the installation platform and near the connection position of the installation platform and the vibration table.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011241562.7A CN112526210B (en) | 2020-11-09 | 2020-11-09 | Real-time monitoring test system and method for thermal vibration combined insulativity of aircraft cable assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011241562.7A CN112526210B (en) | 2020-11-09 | 2020-11-09 | Real-time monitoring test system and method for thermal vibration combined insulativity of aircraft cable assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112526210A CN112526210A (en) | 2021-03-19 |
| CN112526210B true CN112526210B (en) | 2023-11-03 |
Family
ID=74980694
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011241562.7A Active CN112526210B (en) | 2020-11-09 | 2020-11-09 | Real-time monitoring test system and method for thermal vibration combined insulativity of aircraft cable assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112526210B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113804379B (en) * | 2021-08-20 | 2024-04-02 | 北京工业大学 | Composite material ultra-high temperature vibration fatigue test method |
| CN113701974B (en) * | 2021-09-13 | 2023-10-03 | 安徽中邦特种电缆科技有限公司 | Cable assembly vibration test device |
| CN114325410B (en) * | 2021-11-22 | 2023-10-13 | 北京机电工程研究所 | Thermovibration and electricity combined test method for battery |
| CN114200233B (en) * | 2021-12-06 | 2023-10-10 | 国网浙江省电力有限公司舟山供电公司 | Electrical-thermal-vibration combined aging device and method for intermediate joint of bridge-following cable |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007248399A (en) * | 2006-03-17 | 2007-09-27 | Sharp Corp | Vibration testing device |
| JP2012078314A (en) * | 2010-10-06 | 2012-04-19 | Railway Technical Research Institute | Vibration testing apparatus for cable connecting section of ground coil for superconducting magnetic levitation type railway |
| CN102954865A (en) * | 2011-08-26 | 2013-03-06 | 上海移远通信技术有限公司 | Highly accelerated life testing system for electronic products and method using same |
| CN103162926A (en) * | 2013-02-06 | 2013-06-19 | 济南大学 | Cable-heating device and test device and test method |
| CN106855594A (en) * | 2015-12-09 | 2017-06-16 | 中国电力科学研究院 | Heat-vibrating the ageing test apparatus and method of a kind of XLPE insulation sample section |
| CN106969826A (en) * | 2017-04-10 | 2017-07-21 | 西安航天动力试验技术研究所 | The calibrating installation and calibration method of a kind of vibrating sensor |
| CN110895186A (en) * | 2019-11-28 | 2020-03-20 | 北京机电工程研究所 | Vibration system comprising a plurality of vibration tables and vibration test method |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4831670B2 (en) * | 2006-02-24 | 2011-12-07 | 富士通株式会社 | Sample resistance measuring device |
| US8479597B2 (en) * | 2011-04-29 | 2013-07-09 | Michael B. Pickel | Thermal test chamber |
-
2020
- 2020-11-09 CN CN202011241562.7A patent/CN112526210B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007248399A (en) * | 2006-03-17 | 2007-09-27 | Sharp Corp | Vibration testing device |
| JP2012078314A (en) * | 2010-10-06 | 2012-04-19 | Railway Technical Research Institute | Vibration testing apparatus for cable connecting section of ground coil for superconducting magnetic levitation type railway |
| CN102954865A (en) * | 2011-08-26 | 2013-03-06 | 上海移远通信技术有限公司 | Highly accelerated life testing system for electronic products and method using same |
| CN103162926A (en) * | 2013-02-06 | 2013-06-19 | 济南大学 | Cable-heating device and test device and test method |
| CN106855594A (en) * | 2015-12-09 | 2017-06-16 | 中国电力科学研究院 | Heat-vibrating the ageing test apparatus and method of a kind of XLPE insulation sample section |
| CN106969826A (en) * | 2017-04-10 | 2017-07-21 | 西安航天动力试验技术研究所 | The calibrating installation and calibration method of a kind of vibrating sensor |
| CN110895186A (en) * | 2019-11-28 | 2020-03-20 | 北京机电工程研究所 | Vibration system comprising a plurality of vibration tables and vibration test method |
Non-Patent Citations (3)
| Title |
|---|
| XLPE电缆的热振动联合老化试验测试与分析;张振鹏等;《高电压技术》;20181126(第11期);全文 * |
| 热振联合环境试验技术研究;张治君等;《实验力学》;20121221(第04期);全文 * |
| 航天器电线电缆寿命预测模型研究;潘江江等;《宇航计测技术》;20191215(第06期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112526210A (en) | 2021-03-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112526210B (en) | Real-time monitoring test system and method for thermal vibration combined insulativity of aircraft cable assembly | |
| US20140328030A1 (en) | Electrical harness connector | |
| CN108169606A (en) | High voltage direct current converter system simulates live detection complexes and its detection method | |
| Bhatti et al. | Simulation of temperature distribution behavior of high voltage cable joints with typical defects | |
| CN110220808B (en) | Method and device for detecting explosion-proof performance of cable intermediate joint explosion-proof box based on interface arc combustion | |
| CN112964431A (en) | Method and device for improving waterproof test accuracy of power cable intermediate joint | |
| CN116381358A (en) | Online detection method and device for local defects of high-voltage power cable | |
| CN206515365U (en) | Bushing for transformer monitoring device | |
| CN110702338A (en) | Method for testing defects of low-voltage cable insulating material | |
| CN110491227A (en) | Cable fault simulation device | |
| CN105388354A (en) | Mounting assembly for all-optical overvoltage sensor for overvoltage measurement | |
| CN215730318U (en) | Airplane EWIS wiring harness laying practical training platform | |
| AU2007265746A1 (en) | A method and a device for diagnosing an on-line high voltage component | |
| CN213337871U (en) | High-voltage oil-filled cable terminal fault prediction simulation device | |
| CN114200233B (en) | Electrical-thermal-vibration combined aging device and method for intermediate joint of bridge-following cable | |
| Nakanishi et al. | Development of prefabricated joint for 275-kV XLPE cable | |
| Suzuki et al. | Installation of the world's first 500-kV XLPE cable with intermediate joints | |
| CN208366565U (en) | The system that a kind of pair of contact net clue is vibrated, current-carrying is tested | |
| Arif et al. | Novel evaluation and testing of technology qualification process of subsea oil and gas products | |
| EP4215745A1 (en) | Wind turbine cable connector monitoring method and device | |
| Matamwe et al. | Review of on-site testing and partial discharge diagnosis of power cables | |
| CN108801571A (en) | It is a kind of contact net clue is vibrated, current-carrying experiment system and method | |
| CN220136925U (en) | Oilpaper insulating sleeve fault simulation device | |
| Sheng et al. | PD detection and localisation in cross-bonded HV cable systems | |
| CN114172085A (en) | Construction method of electric cable |
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 | ||
| GR01 | Patent grant |