CN102180272A - Method for evaluating adaptability of aerospace component to thermal environment - Google Patents
Method for evaluating adaptability of aerospace component to thermal environment Download PDFInfo
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- CN102180272A CN102180272A CN2011100938032A CN201110093803A CN102180272A CN 102180272 A CN102180272 A CN 102180272A CN 2011100938032 A CN2011100938032 A CN 2011100938032A CN 201110093803 A CN201110093803 A CN 201110093803A CN 102180272 A CN102180272 A CN 102180272A
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Abstract
The invention relates to a method for evaluating the adaptability of an aerospace component to a thermal environment, which comprises the following steps of: 1, judging whether test evaluation is needed to be performed or not, namely judging whether a thermal environment adaptability verification test is needed to be performed or not according to the category and application requirement level of the component; 2, determining a test item, namely analyzing the thermal sensitive element of the component comprehensively, and determining the test item; 3, determining the test stress level, namely analyzing the stress level of the thermal environment in which the component in specific application is positioned, and determining the test stress level on the basis; 4, performing a thermal environment application verification test on the component; and 5, evaluating a test result, namely determining the applicability of the component in a specific aerospace product according to the determined evaluation criteria. The method has the advantages that: the evaluation test has higher reasonableness and pertinence and high operability.
Description
Affiliated technical field
The present invention relates to a kind of aerospace component thermal compatible with environment evaluation method, this method is mainly based on verification experimental verification, and the concrete test method of its thermal environment comformability application verification when the components and parts aerospace applications is provided, be devoted to guarantee correct reliable use of components and parts in the aerospace environment, reduce components and parts in aerospace environmental applications risk, belong to the component reliability field of engineering technology.
Background technology
In the engineering reality, aerospace is mainly carried out according to GJB548B-2005 standards such as " microelectronic component Test Methods And Procedures " with the correlation test in the component quality assurance work at present.But in traditional components and parts standard test method components and parts are often taked identical test requirements document, concrete components and parts classification and application requirements are lacked the actv. specific aim.The components and parts that also continuous appearance has been tested and appraised in the actual engineering are in the installation use still situation of frequent failure.
On the other hand, heat is the key factor that influences components and parts and even equipment work reliability, and the thermal environment of components and parts mainly comprises two parts: the heat that external heat environment and self energising work produce.And in the test of traditional components and parts level, except that aging, life test, all to be in off working state be that components and parts are in not febrile state to components and parts in other tests, this for the check components and parts whether can reliable operation under corresponding thermal environment be exist not enough.Therefore, how in conjunction with the analysis of components and parts and application requirements thereof, its aerospace thermal environment comformability being carried out verification experimental verification, and then judge the applicability of components and parts in space technology, is urgent problem in the aerospace component reliability engineering.
Summary of the invention
The objective of the invention is: provide a kind of workable, at the aerospace component thermal compatible with environment evaluation method of concrete application, with the applicability of checking components and parts under concrete application requirements.
Technical scheme of the present invention:
Aerospace of the present invention component thermal compatible with environment evaluation method, it sets up aerospace component thermal compatible with environment ranking test scheme based on the analysis of responsive key element of component thermal and application requirements, and these method concrete steps are as follows:
Step 1: determine whether to carry out verification experimental verification: determine whether to carry out thermal environment comformability certification testing according to components and parts classification and application requirements grade;
Step 2: confirmed test project: the thermo-responsive key element to components and parts is analyzed, confirmed test project behind the comprehensive analyses;
Step 3: confirmed test stress level: the analysis elements device is residing thermal environment stress level, confirmed test stress level on this basis in concrete the application;
Step 4: the enforcement of component thermal environmental applications certification testing: test according to step 2 and 3 Test item and the proof stresses of determining, test is the test of plate level verification, wherein components and parts should be in normal working, and require in the process of the test components and parts function and shell temperature are monitored in real time; Test article requires: through identifying, screening up-to-standard components and parts, quantity is 2～5;
Step 5: evaluation of test result: judge the applicability of components and parts in concrete aerospace product according to the evaluation criteria of determining.
Wherein, tabulate 1 and table 2 as follows in the components and parts classification described in the step 1 and application level.According to the classification of table 1 and table 2, tabulation 3 determines whether to carry out test evaluation under the basis again.
The classification of table 1 aerospace component thermal compatible with environment
The classification of table 2 aerospace components and parts application level
Table 3 aerospace component thermal compatible with environment is estimated matrix
Wherein, tabulate 4 as follows in the thermo-responsive key element described in the step 2.Principle according to table 4 confirmed test project is as follows:
(1) as long as have one to be 3 for certain class environment sensitive degree in three of encapsulation or basis material, mounting means, the electrical quantitys, then the cooresponding test of these class environmental facies must be carried out;
(2) for each class thermal environment, if components and parts material, mounting means, electrical quantity three parts to the sensitivity sum of such thermal environment more than or equal to 6, then corresponding Test item must be carried out; If less than 6, then cooresponding Test item can not carried out to the sensitivity sum of such thermal environment for components and parts material, mounting means, electrical quantity three parts;
(3) encourage to increase relevant Test item according to the analysis of concrete components and parts and applied environment.
The responsive key element of table 4 aerospace component thermal compatible with environment
Wherein, can obtain by simulation analysis at the residing thermal environment stress level in concrete application of the components and parts described in the step 3, it also can be the measured result of like product, mainly refer to limit high temperature and low temperature in the components and parts working environment, on the high low temperature of this limit basis, increase the bound that 10～20 ℃ allowance is test temperature stress; Test duration determines that according to product test electric stress section is consistent with real work electric stress section mission time.
Wherein, be development voluntarily, require breadboard that the electric stress and the convenient function test that realizes components and parts on the plate of components and parts real work can be provided at the breadboard described in the step 4.
Requirement such as test facility, operation can be with reference to the requirement of components and parts and assembly correlation test among GJB548B-2005 " microelectronic component Test Methods And Procedures " and the GJB1027A-2005 " vehicle, top level and spacecraft test requirements document ".And must electrical property, outward appearance, the mechanical characteristics of components and parts be detected before and after the test.
Wherein, satisfying the evaluation criteria that thermal environment comformability application verification requires at the components and parts described in the step 5 is: in the process of the test: the components and parts function is normal, and shell Wen Wei exceeds the design allowed band; Test back components and parts detect (relatively preceding with test): in the performance parameter variations standard allowed band, and outward appearance, structure no change.Otherwise, think that these components and parts do not satisfy the requirement of thermal environment comformability application verification.
The invention provides a kind of aerospace component thermal compatible with environment evaluation method based on components and parts self attributes and application requirements analysis, its advantage mainly contains:
(1) ranking test has more reasonableness and specific aim based on the concrete components and parts attribute and the analysis of application requirements;
(2) save engineering cost: the classification of component thermal compatible with environment and application requirements is provided,, can carried out thermal environment compatibility test evaluation for insensitive device of portion of hot or the good device of applied environment;
(3) workable: component thermal compatible with environment and application requirements are classified, determining whether and must test, proposed components and parts to three class thermal environment sensitivitys with the confirmed test project.
Description of drawings
Fig. 1 is the FB(flow block) of the method for the invention
The specific embodiment
Below in conjunction with concrete case study on implementation, to aerospace of the present invention component thermal compatible with environment evaluation method, i.e. aerospace based on components and parts self attributes and application requirements analysis is elaborated with component thermal compatible with environment evaluation method.
Case: the DC/DC conv that is applied to spacecraft
The present invention is an example with the DC/DC conv that is applied to spacecraft, and the aerospace component thermal compatible with environment evaluation method based on components and parts self attributes and application requirements analysis is described.
DC/DC conv and application requirements thereof are as follows:
(1) DC/DC conv: thick-film technique, metal lead wire encapsulation, the work power consumption is expected to be 5W;
(2) application requirements: work life, non-pass heavy mail more than 5 years are-10 ℃～95 ℃ through ambient temperature range in its life cycle of simulation analysis, are applied in the spacecraft.
Aerospace of the present invention is with component thermal compatible with environment evaluation method, sees shown in Figure 1ly, and these method concrete steps are as follows:
Step 1: determine whether to carry out verification experimental verification: according to the classification situation of table 1, this circuit belongs to I class device.According to the regulation of table 2, application level is 2 grades again.According to the regulation of table 3, determine that this DC/DC conv must carry out thermal environment compatibility test evaluation at last.
Step 2: confirmed test project: determine that according to table 4 the DC/DC conv is to three class thermal environment sensitivity---steady temperatures: 3 (metals), 1 (lead-in wire), 3 (electrical quantitys); Temperature cycle: 3 (metals), 2 (lead-in wires), 1 (electrical quantity); Thermovacuum: 3 (metals), 2 (lead-in wires), 1 (electrical quantity).Can determine all that according to the principle (1) of confirmed test project in the step 2 and (2) steady temperature (comprising high and low temperature), temperature cycle, these three tests of thermovacuum must carry out.
Step 3: confirmed test stress level: on simulation analysis result's-10 ℃～95 ℃ basis, increase the range of temperatures that 15 ℃ allowance obtains testing :-25 ℃～110 ℃.And the product task service life is more than 5 years, and the time is longer, and is as follows in conjunction with engineering experience and relevant criterion (Test item steady state life, temperature cycle among the GJB548B-2005, the thermal vacuum test of assembly among the GJB1027A-2005) confirmed test stress level:
Low temperature :-25 ℃, 1000 hours, the work electric stress;
High temperature: 110 ℃, 1000 hours, the work electric stress;
Temperature cycle :-25 ℃～110 ℃, at least 20 times, the work electric stress;
Thermovacuum :-25 ℃～110 ℃, at least 10 times, work electric stress, test pressure≤6.65 * 10
-3Pa.
Step 4: the enforcement of component thermal environmental applications certification testing: according to the definite proof stress of step 3, the key step of test following (correlation test equipment and operation requirements with reference to Test item steady state life, temperature cycle among the GJB548B-2005, the thermal vacuum test of assembly among the GJB1027A-2005):
(1) develop corresponding breadboard, requirement can provide the electric stress and the convenient function test that realizes components and parts on the plate of components and parts real work.
(2) test article (3) is chosen in sampling in two sieve acceptable product.
(3) detect before the test: components and parts are carried out electrical property and outward appearance detection, and record data.
(4) device simulation actual installation state is installed on breadboard.
(5) low temperature test :-25 ℃, 1000 hours, work electric stress, real-time monitoring circuit function and surperficial shell temperature.
(6) high temperature test: 110 ℃, 1000 hours, work electric stress, real-time monitoring circuit function and surperficial shell temperature.
(7) temperature cycle :-25 ℃～110 ℃, at least 20 times, work electric stress, real-time monitoring circuit function and surperficial shell temperature.
(8) thermovacuum :-25 ℃～110 ℃, at least 10 times, work electric stress, test pressure≤6.65 * 10
-3Pa, real-time monitoring circuit function and surperficial shell temperature.
(9) behind the end of test, take off components and parts and components and parts electrical property, outward appearance are detected record data from breadboard.
Step 5: evaluation of test result: the thermal environment comformability of circuit in corresponding aerospace product estimated according to evaluation criteria.
Claims (6)
1. aerospace is with component thermal compatible with environment evaluation method, and it is characterized in that: these method concrete steps are as follows:
Step 1: determine whether and to test: determine whether to carry out thermal environment comformability certification testing according to components and parts classification and application requirements grade;
Step 2: confirmed test project: the thermo-responsive key element to components and parts is analyzed, confirmed test project behind the comprehensive analyses;
Step 3: confirmed test stress level: the analysis elements device is residing thermal environment stress level, confirmed test stress level on this basis in concrete the application;
Step 4: the enforcement of component thermal environmental applications certification testing: test according to step 2 and 3 Test item and the proof stresses of determining, test is the test of plate level verification, wherein components and parts should be in normal working, and require in the process of the test components and parts function and shell temperature are monitored in real time; Test article requires: through identifying, screen up-to-standard components and parts;
Step 5: evaluation of test result: judge the applicability of components and parts in concrete aerospace product according to the evaluation criteria of determining.
2. aerospace according to claim 1 is characterized in that with component thermal compatible with environment evaluation method: tabulate 1 and table 2 as follows in the components and parts classification described in the step 1 and application level; According to the classification of table 1 and table 2, tabulation 3 determines whether to carry out test assessment under the basis again:
Table 1 aerospace is classified with the component thermal compatible with environment
Table 2 aerospace is classified with the components and parts application level
Table 3 aerospace component thermal compatible with environment evaluating matrix
3. aerospace according to claim 1 component thermal compatible with environment evaluation method is characterized in that: tabulate 4 as follows in the thermo-responsive key element described in the step 2, as follows according to the principle of table 4 confirmed test project:
(1) as long as have one to be 3 for certain class environment sensitive degree in three of encapsulation or basis material, mounting means, the electrical quantitys, then the cooresponding test of these class environmental facies must be carried out;
(2) for each class thermal environment, if components and parts material, mounting means, electrical quantity three parts to the sensitivity sum of such thermal environment more than or equal to 6, then corresponding Test item must be carried out; If less than 6, then cooresponding Test item can not carried out to the sensitivity sum of such thermal environment for components and parts material, mounting means, electrical quantity three parts;
(3) encourage to increase relevant Test item according to the analysis of concrete components and parts and applied environment.
The responsive key element of table 4 aerospace component thermal compatible with environment
4. aerospace according to claim 1 component thermal compatible with environment evaluation method, it is characterized in that: obtain by simulation analysis or like product actual measurement at the residing thermal environment stress level in concrete application of the components and parts described in the step 3, this stress level comprises limit high temperature and the low temperature in the components and parts working environment, increases the bound that 10～20 ℃ allowance is test temperature stress on the high low temperature of this limit basis; Test duration determines that according to product test electric stress section is consistent with real work electric stress section mission time.
5. aerospace according to claim 1 component thermal compatible with environment evaluation method, it is characterized in that: be development voluntarily at the breadboard described in the step 4, require breadboard that the electric stress and the convenient function test that realizes components and parts on the plate of components and parts real work can be provided.
6. aerospace according to claim 1 component thermal compatible with environment evaluation method, it is characterized in that: satisfying the evaluation criteria that thermal environment comformability application verification requires at the components and parts described in the step 5 is: in the process of the test: the components and parts function is normal, and shell Wen Wei exceeds the design allowed band; Components and parts compare before detecting and testing after the test: in the performance parameter variations standard allowed band, and outward appearance, structure no change, otherwise, think that these components and parts do not satisfy the requirement of thermal environment comformability application verification.
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Cited By (5)
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| CN102565596A (en) * | 2012-02-08 | 2012-07-11 | 电子科技大学 | Method for temperature stress limit evaluation of electronic component |
| CN102608449A (en) * | 2012-02-08 | 2012-07-25 | 电子科技大学 | Electric stress limit evaluation method for gallium arsenide monolithic microwave power amplifier |
| CN104007351A (en) * | 2014-06-17 | 2014-08-27 | 北京航空航天大学 | Method for determining spacecraft electronic assembly heat cycle test scheme |
| CN107856889A (en) * | 2017-10-27 | 2018-03-30 | 北京空间技术研制试验中心 | The method of production that spacecraft platform is mutually matched with loading device |
| CN113051770A (en) * | 2021-04-09 | 2021-06-29 | 江苏徐工工程机械研究院有限公司 | Paint film corrosion resistance comprehensive evaluation method based on environmental factors |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105371892B (en) * | 2015-10-21 | 2016-09-28 | 中国人民解放军国防科学技术大学 | Inferior grade screening of electric components method and device thereof for satellite |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102565596A (en) * | 2012-02-08 | 2012-07-11 | 电子科技大学 | Method for temperature stress limit evaluation of electronic component |
| CN102608449A (en) * | 2012-02-08 | 2012-07-25 | 电子科技大学 | Electric stress limit evaluation method for gallium arsenide monolithic microwave power amplifier |
| CN102565596B (en) * | 2012-02-08 | 2014-08-06 | 电子科技大学 | Method for temperature stress limit evaluation of electronic component |
| CN102608449B (en) * | 2012-02-08 | 2014-08-06 | 电子科技大学 | Electric stress limit evaluation method for gallium arsenide monolithic microwave power amplifier |
| CN104007351A (en) * | 2014-06-17 | 2014-08-27 | 北京航空航天大学 | Method for determining spacecraft electronic assembly heat cycle test scheme |
| CN107856889A (en) * | 2017-10-27 | 2018-03-30 | 北京空间技术研制试验中心 | The method of production that spacecraft platform is mutually matched with loading device |
| CN113051770A (en) * | 2021-04-09 | 2021-06-29 | 江苏徐工工程机械研究院有限公司 | Paint film corrosion resistance comprehensive evaluation method based on environmental factors |
| CN113051770B (en) * | 2021-04-09 | 2023-07-04 | 江苏徐工工程机械研究院有限公司 | Paint film corrosion resistance comprehensive evaluation method based on environmental factors |
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