CN1904577A - Automatic test device and method of aviation circuit breaker fatigue life - Google Patents
Automatic test device and method of aviation circuit breaker fatigue life Download PDFInfo
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- CN1904577A CN1904577A CNA2006100152974A CN200610015297A CN1904577A CN 1904577 A CN1904577 A CN 1904577A CN A2006100152974 A CNA2006100152974 A CN A2006100152974A CN 200610015297 A CN200610015297 A CN 200610015297A CN 1904577 A CN1904577 A CN 1904577A
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- isolating switch
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Abstract
The invention discloses a kind of fatigue and life automatic tester of the aviation breaker and its method. It belongs to the fatigue and life testing technique of the breaker. The tester includes a worktable, a base board, a servo system, a reducer, a lead screw, a slide block, a clamp holding the aviation breaker, a photoelectricity switch, a spacing switch, a computer, a clock and a data collecting card. The test method is as follows. Determine the test starting location of different type aviation breaker; carry out the fatigue and life test on the same type aviation breaker at the same time at certain time domain; carry out the fatigue and life test on the same type aviation breaker at the same time at different time domain; carry out the fatigue and life test on the novel type aviation breaker. The invention can carry out multi-specs aviation breaker test. The flexibility of the tester is perfect; the test is convenient and complete; the test speed and the precise are high. The automatic control simplifies the test process greatly and prevents the waste of manpower and material resources.
Description
Technical field
The present invention relates to a kind of aviation circuit breaker fatigue life automatic test equipment and method, belong to the circuit breaker fatigue life experimental technique.
Background technology
The aviation isolating switch is one of visual plant in the electrical system of Aeronautics and Astronautics device; bearing control and protection dual role; by it promptly and accurately be switched on or switched off response; can realize overload or equipment protection or control automatically during short circuit; its reliability directly has influence on the safe operation of Aeronautics and Astronautics device power system; the important indicator of reliability is mechanical life and electric life, and it is manufacturer and one of parameter of using the user to pay close attention to most.
The aviation isolating switch has branch, two operating states close a floodgate, the purpose of fatigue life test is connected repeatedly-is locked-the Tuo lock-disconnection course of work with given pace between these two states exactly, till the number of times of regulation, judge that product whether still can operate as normal, thereby determine that whether qualified the life-span is.The fatigue life test of aviation isolating switch is taked the method for pick test, and test method commonly used at present has 1. manual mode of operation, and the manual operation handle closes repeatedly, sub-switching operation; 2. electromechanical means circulates repeatedly with driven by motor cam or slider-crank mechanism and to realize test; 3. pneumatic mode, pneumatic actuation aviation circuit breaker handle closes, sub-switching operation.Because aviation circuit breaker fatigue life test number (TN) will reach more than thousands of times, the test period is long, and manual type labour intensity is big, easily produces fatigue, misremembers number of times easily, is difficult to accurately control test sequential, when carrying out electrical endurance test, also may produce Danger Electric shock risk; Electromechanical means can only be at single product, and test unit is flexible poor, and mechanism's complexity can not automatic connection after the abort; Pneumatic mode needs source of the gas, and mechanism's complexity is difficult for accurately location, impacts greatly during operation, and noise is big, can not automatic connection after the abort.Therefore, develop a fatigue life test stand that can adapt to many aviation isolating switchs parallel high precision, robotization and the high flexibility of many specifications, to reducing labour intensity, improve test efficiency, accurately assess reliability of products, guarantee product quality, improve the aviation breaker reliability and have crucial meaning, can satisfy the market demand of producing in batches and enlarging day by day.
Summary of the invention
The object of the present invention is to provide a kind of aviation circuit breaker fatigue life from dynamic test and method, the device performance that the present invention uses is reliable, and the process of the test flexibility is good, experiment automatized degree and precision height.
The present invention is realized by the following technical programs; a kind of aviation circuit breaker fatigue life automatic test equipment; this device comprises a worktable 1; installation base plate 2 on the worktable; a side is installed servo-drive system 3 connection speed reduction units 4 and is promoted leading screws 5 motions on the substrate; connect slide block 7 directed movement on guide rail 6 on the leading screw top; leading screw; slide block and guide rail constitute the kinematic pair of test unit; at least 4 parallel pull bars 8 are installed on the slide block to link to each other with the handle of each aviation isolating switch 10 respectively; opposite side is installed the clamp base of testing simultaneously for the aviation isolating switch of many same models on the substrate; cooperate the anchor clamps gland to form anchor clamps 9; the school benchmark protective device of being made up of a correlation optoelectronic switch 11 and initial point limit switch 15 also is installed on the substrate, and they link to each other with data collecting card 12.Go back erector's control computer 13 on the worktable, clock 14 and installation data capture card 12 wherein are set, data collecting card 12 is gathered clock 14 signals and also is connected with servo-drive system 3 and is connected with school benchmark protective device; Under the control of industrial computer 13, the moment of torsion of servo-drive system 3 outputs reaches 13.8Nm by speed reduction unit 4, and kinematic pair to-and-fro movement stroke resolution is 50nm, and reciprocating repetitive positioning accuracy is 10 μ m.
Adopt said apparatus to realize the automatic test method of aviation circuit breaker fatigue life, it is characterized in that comprising following process:
1. determine the test reference position of the aviation isolating switch of different model:
When anchor clamps 9 are not installed the aviation isolating switch, industrial computer 13 drives kinematic pair by data collecting card 12 Control Servo System 3 and speed reduction unit 4 and is moved to limit switch 15 (reference position) by the optional position, in touching, limit switch 15 sends impulse level to data collecting card 12 this moment, industrial computer 13 Control Servo System 3 drive the kinematic pair counter motion, return corresponding fixed range according to the model of in computing machine, having set before the test, be parked in the test reference position, this reference position is defined as the test reference position of aviation isolating switch.When mistake in the baseline process of school is placed in aviation isolating switch 10 in the anchor clamps 9; can cause pull bar to drive handle motion and exceed stroke damage aviation isolating switch by force; therefore at the anchor clamps two ends correlation optoelectronic switch 11 is installed; when on anchor clamps 9, aviation isolating switch 10 being installed; the light signal of correlation optoelectronic switch 11 is cut off, and the output high level is given data collecting card 12, and industrial computer 13 is forbidden school benchmark operation; operation interface ejects " taking off product " prompting simultaneously, thereby the protection product is not damaged.
2. simultaneously the aviation circuit breaker fatigue life of same model is tested in a certain time domain:
After the test reference position of the aviation isolating switch of a certain model that step 1 is determined, 1～4 of the aviation isolating switch of this model is installed on the anchor clamps 9, by industrial computer 13 control data capture cards 12, the train of impulses that sends corresponding certain displacement drives servo-drive system 3 and speed reduction unit 4 drive kinematic pair rectilinear motions, the driving pulse frequency f has determined servo-drive system travelling speed v, test trip s is by reduction gear ratio and screw mandrel helical pitch t decision, data collecting card 12 sends high-low level switching positive-negative rotation state and makes the kinematic pair to-and-fro movement, pull bar 8 provides driving force to make a match to the handle of aviation isolating switch 10, the separating brake action, by Automatic Cycle realize " the aviation circuit breaker handle advances---the aviation closing of power circuit breaker---locking of aviation isolating switch---time-delay keeps---the aviation circuit breaker handle is pulled out---the aviation isolating switch takes off lock---Automatic Cycle that the aviation isolating switch disconnects---time-delay keeps---" the durability test process, fixed and disconnect having or not of back " time-delay keeps " period by aviation lock for circuit breaker in the industrial computer 13 control test, fatigue life test is divided into intermittently and two kinds of methods of operation at the uniform velocity.
3, simultaneously the aviation circuit breaker fatigue life of same model is tested in different time domain:
Test and can not finish in a certain time domain when the aviation circuit breaker fatigue life, when then next time domain was proceeded, before being about to finish this time domain test, industrial computer 13 was noted down test number (TN) and model automatically by database program; When next time domain restarted operation interface and tests, whether industrial computer 13 is searched at first automatically was the test of branch time domain, then accessed test number (TN) and model last time then, began the test of a new time domain, thereby realized dividing a time domain long run test.
4. the aviation circuit breaker fatigue life of new model is tested:
When following new model aviation isolating switch carries out durability test, the aviation isolating switch is not installed earlier in anchor clamps 9, access " reference position " and " stroke " two parameters by " newly-increased model " function on industrial computer 13 operation interfaces, the reference position of the acquiescence aviation isolating switch of having set according to industrial computer 13 carry out step 1, if aviation isolating switch 10 clampings are not gone up on the reference position, then revise " reference position " parameter on the interface, carry out step 1 again, by repeatedly revising " reference position " parameter and operating procedure 1 on the interface, till on the product energy clamping, " reference position " parameter modification is correct at this moment, has determined the reference position of new model aviation isolating switch; Then, the aviation isolating switch 10 of new model is installed in the anchor clamps 9, industrial computer 13 carry out step 2 according to the acquiescence of having set " stroke " value, when finding to advance to " stroke " value of having set, aviation isolating switch 10 can not lock, then revise " stroke " parameter on the interface, carry out step 2 again, by repeatedly revising " stroke " parameter and operating procedure 2 on the interface, till product can lock, " stroke " parameter modification is correct at this moment, by on the operation interface being prompted to the typing number, and automatically preserve " reference position " and " stroke " these two parameters and in the new model program of industrial computer 13, promptly become the product of known models, from now on set by step 1, step 2, step 3 is carried out fatigue life test and is got final product.
The invention has the advantages that: can carry out the test of plurality of specifications aviation isolating switch, the test unit flexibility is good, and test is convenient, test speed and precision height, and test is comprehensive, and process of the test has been simplified in robotization control greatly, avoids the waste of human and material resources.
Description of drawings
Fig. 1 is the structured flowchart of pick-up unit of the present invention.
Among the figure: 1-worktable, 2-substrate, 3-servo-drive system, 4-speed reduction unit, 5-screw mandrel, 6-guide rail, 7-slide block, 8-pull bar, 9-anchor clamps, 10-aviation isolating switch, 11-correlation optoelectronic switch, 12-data collecting card, 13-industrial computer, 14-clock, 15-limit switch
Fig. 2 is a test unit physical construction of the present invention photo in kind.
Fig. 3 is test unit computer operation of the present invention interface.
Embodiment
Before the aviation circuit-breaker testing of a model of every beginning; do not installing on the anchor clamps under the situation of aviation isolating switch; at first on the operation interface of industrial computer IPC-610H, select school benchmark operation; test unit is the reference position with the initial point limit switch TZ-5101 of distance anchor clamps fixed range; the computer control kinematic pair reaches the reference position from the optional position; return corresponding distance according to selected different model then, be parked in the test reference position of this model.Only needing to carry out once the school benchmark for same type product gets final product.In order to prevent maloperation school benchmark step in process of the test; cause pull bar to drive the motion of aviation circuit breaker handle by force and exceed stroke damage product; the correlation optoelectronic switch E3Z-T61 that install at the anchor clamps two ends judges whether the aviation isolating switch has been installed on the anchor clamps; when judgement has installation; then forbid the school benchmark, eject " taking off product " prompting simultaneously on the operation interface.
Behind the benchmark of school, product begins test, by clamp aviation isolating switch; on operation interface, set parameters; as aviation isolating switch model, test number (TN), movement velocity, switching retention time etc., select mechanical life or electric life mode of operation, and starting characteristics test.At this moment, the data collecting card PCI-6620 train of impulses that riches all the way goes out corresponding certain displacement drives servo-drive system MINAS A4/200W and speed reduction unit NMRV-40-10 drives the kinematic pair rectilinear motion, riches all the way in addition, and high-low level switches positive-negative rotation state, pulse divides the frequency multiplication initial value according to servo-drive system, the required command pulse of servo-drive system revolution is 10000, by conversion, obtain respective rate, delay time and test trip, automatically realize " the aviation circuit breaker handle advances---the aviation closing of power circuit breaker---locking of aviation isolating switch---time-delay keeps---the aviation circuit breaker handle is pulled out---the aviation isolating switch takes off lock---Automatic Cycle that the aviation isolating switch disconnects---time-delay keeps---" the durability test process.When test number (TN) very long, a working day is in the time of can not finishing test, need test stage by stage, one stage off-test computing machine was noted down test number (TN) and model automatically by database program before withdrawing from operation interface, when restarting the operation interface test, whether computing machine is searched at first automatically for testing stage by stage, and access test number (TN) and model last time, and the test that begins to continue, thus realize long run test stage by stage.The measurement mechanism safeguard protection is all arranged in the measuring process at any time.Can carry out the parameter setting to new product, and automatic corresponding new model, the retention parameter setting, process of the test is the same with existing model convenient from now on.
Claims (2)
1. aviation circuit breaker fatigue life automatic test equipment, this device comprises a worktable (1), installation base plate on the worktable (2), a side is installed servo-drive system (3) connection speed reduction unit (4) and is promoted leading screw (5) motion on the substrate, connect slide block (7) on the leading screw top and go up directed movement at guide rail (6), leading screw, slide block and guide rail constitute the kinematic pair of test unit, at least 4 parallel pull bars (8) are installed on the slide block to link to each other with the handle of each aviation isolating switch (10) respectively, opposite side is installed for many clamp base that same model aviation isolating switch is tested simultaneously on the substrate, cooperate the anchor clamps gland to form anchor clamps (9), the school benchmark protective device of being made up of a correlation optoelectronic switch (11) and initial point limit switch (15) also is installed on the substrate, and they link to each other with data collecting card (12); Go back erector's control computer (13) on the worktable, clock (14) and installation data capture card (12) wherein are set, data collecting card (12) is gathered clock (14) signal and also is connected with servo-drive system (3) and is connected with school benchmark protective device; Under the control of industrial computer (13), the moment of torsion of servo-drive system (3) output reaches 13.8Nm by speed reduction unit (4), and kinematic pair to-and-fro movement stroke resolution is 50nm, and reciprocating repetitive positioning accuracy is 10 μ m.
2. an employing is carried out the automatic test method of aviation circuit breaker fatigue life by the described device of claim 1, it is characterized in that comprising following process:
1). the test reference position of the aviation isolating switch of different model:
When anchor clamps (9) are not installed the aviation isolating switch, industrial computer (13) drives kinematic pair by data collecting card (12) Control Servo System (3) and speed reduction unit (4) and is moved to limit switch (15) by the optional position, in touching, limit switch (15) sends impulse level to data collecting card (12) this moment, industrial computer Control Servo System (3) drives the kinematic pair counter motion, return corresponding fixed range according to the model of in industrial computer, having set before the test, be parked in the test reference position, this reference position is defined as the test reference position of aviation isolating switch, when mistake in the baseline process of school is placed in aviation isolating switch (10) in the anchor clamps (9), can cause pull bar to drive handle motion and exceed stroke damage aviation isolating switch by force, correlation optoelectronic switch (11) therefore is installed at the anchor clamps two ends, when anchor clamps (9) are gone up installation aviation isolating switch (10), the light signal of correlation optoelectronic switch (11) is cut off, the output high level is given data collecting card (12), industrial computer (13) is forbidden school benchmark operation, operation interface ejects " taking off product " prompting simultaneously, thereby the protection product is not damaged;
2). simultaneously the aviation circuit breaker fatigue life of same model is tested in a certain time domain:
After the test reference position of the aviation isolating switch of a certain model that step 1) is determined, 1～4 of the aviation isolating switch of this model is clipped on the anchor clamps (9), by industrial computer (13) control data capture card (12), the train of impulses that sends corresponding certain displacement drives servo-drive system (3) and speed reduction unit (4) drive kinematic pair rectilinear motion, the driving pulse frequency f has determined servomotor travelling speed v, test trip s is by reduction gear ratio and screw mandrel helical pitch t decision, data collecting card (12) sends high-low level switching positive-negative rotation state and makes the kinematic pair to-and-fro movement, pull bar (8) provides driving force to make a match to the handle of aviation isolating switch (10), the separating brake action, by Automatic Cycle realize " the aviation circuit breaker handle advances---the aviation closing of power circuit breaker---locking of aviation isolating switch---time-delay keeps---the aviation circuit breaker handle is pulled out---the aviation isolating switch takes off lock---Automatic Cycle that the aviation isolating switch disconnects---time-delay keeps---" the durability test process, fixed and disconnect having or not of back " time-delay keeps " period by aviation lock for circuit breaker in computing machine (13) the control test, fatigue life test is divided into intermittently and two kinds of methods of operation at the uniform velocity;
3). simultaneously the aviation circuit breaker fatigue life of same model is tested in different time domain:
Test and can not finish in a certain time domain when the aviation circuit breaker fatigue life, when then next time domain was proceeded, before being about to finish this time domain test, industrial computer (13) was noted down test number (TN) and model automatically by database program; When next time domain restarted operation interface and tests, whether industrial computer (13) is searched at first automatically was the test of branch time domain, then accessed test number (TN) and model last time then, began the test of a new time domain, thereby realized dividing a time domain long run test;
4). the aviation circuit breaker fatigue life to new model is tested:
When following new model aviation isolating switch carries out durability test, the aviation isolating switch is not installed earlier in anchor clamps (9), access " reference position " and " stroke " two parameters by " newly-increased model " function on industrial computer (13) operation interface, the reference position of the acquiescence aviation isolating switch of having set according to industrial computer (13) is carried out step 1), if test aviation isolating switch (10) clamping is not gone up on the reference position, then revise " reference position " parameter on the interface, carry out step 1) again, by repeatedly revising " reference position " parameter and operating procedure 1 on the interface), till on the product energy clamping, " reference position " parameter modification is correct at this moment, has determined the reference position of the aviation isolating switch of new model; Then, the aviation isolating switch (10) of new model is installed in the anchor clamps (9), industrial computer (13) carry out step 2 according to the acquiescence of having set " stroke " value), when finding to advance to " stroke " value of having set, aviation isolating switch (10) can not lock, then revise " stroke " parameter on the interface, carry out step 2 again), by repeatedly revising " stroke " parameter and operating procedure 2 on the interface), till product can lock, " stroke " parameter modification is correct at this moment, by on the operation interface being prompted to the typing number, and automatically preserve " reference position " and " stroke " these two parameters and in the new model program of industrial computer (13), promptly become the product of known models, from now on set by step 1), step 2), step 3) is carried out fatigue life test and is got final product.
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| Application Number | Priority Date | Filing Date | Title |
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| CNB2006100152974A CN100445722C (en) | 2006-08-10 | 2006-08-10 | Automatic test device and method of aviation circuit breaker fatigue life |
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| CNB2006100152974A CN100445722C (en) | 2006-08-10 | 2006-08-10 | Automatic test device and method of aviation circuit breaker fatigue life |
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| CN1904577A true CN1904577A (en) | 2007-01-31 |
| CN100445722C CN100445722C (en) | 2008-12-24 |
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| CN101806860A (en) * | 2010-03-30 | 2010-08-18 | 哈尔滨工业大学 | Adjustable-assembly parameter endurance testing device for electromagnetic relay |
| CN101430353B (en) * | 2007-11-09 | 2012-05-30 | 英华达(上海)电子有限公司 | Device lifetime test device |
| CN102565466A (en) * | 2010-12-29 | 2012-07-11 | 北京市电力公司 | Control method and device for clamp of switch circuit breaker detection equipment |
| CN103292989A (en) * | 2013-06-17 | 2013-09-11 | 广州供电局有限公司 | Breaker mechanical characteristic performance testing method and system |
| CN107037357A (en) * | 2017-05-31 | 2017-08-11 | 中国电力科学研究院 | A kind of full-automatic circuit breaker chassis mechanical endurance test system and method |
| CN107271176A (en) * | 2017-08-04 | 2017-10-20 | 江苏省电力试验研究院有限公司 | The standard movement device and method of testing driven based on linear electric motors |
| CN110657967A (en) * | 2019-09-16 | 2020-01-07 | 上海钧正网络科技有限公司 | Lock testing device and testing method thereof |
| CN110988534A (en) * | 2019-12-03 | 2020-04-10 | 北京特种机械研究所 | Performance test method for universal servo system |
| CN112485663A (en) * | 2020-11-26 | 2021-03-12 | 国营芜湖机械厂 | Online detection device and detection method for aircraft circuit breaker |
| CN117169709A (en) * | 2023-10-09 | 2023-12-05 | 中国民航大学 | Aviation relay fatigue performance testing method, device and storage medium |
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| GB427989A (en) * | 1933-12-22 | 1935-05-03 | Gen Electric Co Ltd | Improvements in fatigue testing machines |
| CN87206633U (en) * | 1987-04-17 | 1988-06-29 | 徐国献 | Vacuum breaker electrical life-testing instrument |
| CN1410852A (en) * | 2001-10-08 | 2003-04-16 | 高浪舟 | Micro computer disconnector mechanical performance testing apparatus |
| CN100348994C (en) * | 2005-04-05 | 2007-11-14 | 天津大学 | Automatic detector and method for mechanical performance of push-pull circuit breaker |
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- 2006-08-10 CN CNB2006100152974A patent/CN100445722C/en not_active Expired - Fee Related
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| CN101430353B (en) * | 2007-11-09 | 2012-05-30 | 英华达(上海)电子有限公司 | Device lifetime test device |
| CN101806860A (en) * | 2010-03-30 | 2010-08-18 | 哈尔滨工业大学 | Adjustable-assembly parameter endurance testing device for electromagnetic relay |
| CN102565466A (en) * | 2010-12-29 | 2012-07-11 | 北京市电力公司 | Control method and device for clamp of switch circuit breaker detection equipment |
| CN103292989A (en) * | 2013-06-17 | 2013-09-11 | 广州供电局有限公司 | Breaker mechanical characteristic performance testing method and system |
| CN103292989B (en) * | 2013-06-17 | 2015-07-08 | 广州供电局有限公司 | Breaker mechanical characteristic performance testing method and system |
| CN107037357B (en) * | 2017-05-31 | 2024-03-15 | 中国电力科学研究院 | Full-automatic breaker chassis vehicle mechanical life test system and method |
| CN107037357A (en) * | 2017-05-31 | 2017-08-11 | 中国电力科学研究院 | A kind of full-automatic circuit breaker chassis mechanical endurance test system and method |
| CN107271176A (en) * | 2017-08-04 | 2017-10-20 | 江苏省电力试验研究院有限公司 | The standard movement device and method of testing driven based on linear electric motors |
| CN110657967A (en) * | 2019-09-16 | 2020-01-07 | 上海钧正网络科技有限公司 | Lock testing device and testing method thereof |
| CN110988534A (en) * | 2019-12-03 | 2020-04-10 | 北京特种机械研究所 | Performance test method for universal servo system |
| CN110988534B (en) * | 2019-12-03 | 2022-09-16 | 北京特种机械研究所 | Performance test method for universal servo system |
| CN112485663A (en) * | 2020-11-26 | 2021-03-12 | 国营芜湖机械厂 | Online detection device and detection method for aircraft circuit breaker |
| CN117169709A (en) * | 2023-10-09 | 2023-12-05 | 中国民航大学 | Aviation relay fatigue performance testing method, device and storage medium |
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| CN100445722C (en) | 2008-12-24 |
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