CN112362277B - Comprehensive test method for aircraft - Google Patents
Comprehensive test method for aircraft Download PDFInfo
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- CN112362277B CN112362277B CN202011173672.4A CN202011173672A CN112362277B CN 112362277 B CN112362277 B CN 112362277B CN 202011173672 A CN202011173672 A CN 202011173672A CN 112362277 B CN112362277 B CN 112362277B
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- 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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/005—Testing of complete machines, e.g. washing-machines or mobile phones
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
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- 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
Abstract
The invention relates to an aircraft comprehensive test method, belongs to the technical field of aircraft stress tests, and solves the problem that the existing aircraft temperature test, vibration test and comprehensive stress test need to be separately tested. The method comprises the following steps: acquiring a standard low-temperature test temperature and a standard high-temperature test temperature of an aircraft temperature test; obtaining a standard vibration magnitude of an aircraft vibration test; acquiring a standard measurement process of an aircraft comprehensive stress test; adjusting the low temperature value, the high temperature value and the heat preservation time in the standard measurement process; setting the vibration condition in the standard measurement process as a standard vibration magnitude, and adjusting the vibration time; and taking the adjusted standard measurement process as an actual comprehensive stress test process. The invention replaces the original three tests with one test, solves the problem of time and labor consumption of a plurality of tests, greatly improves the test efficiency, and can be popularized to the large-scale ground tests of various aircrafts.
Description
Technical Field
The invention relates to the technical field of aircraft stress testing, in particular to an aircraft comprehensive test method.
Background
In the development process of the aircraft, large ground tests such as aircraft temperature tests, vibration tests, comprehensive stress tests and the like are required, the aircraft temperature tests are carried out according to test methods specified by GJB150.3A-2009 and GJB150.4A-2009, and the temperature value of the high-low temperature working test is an aircraft working temperature extreme value; the aircraft vibration test is carried out according to a test method specified by GJB150.16A, wherein the vibration test condition is the maximum vibration value experienced by the aircraft; the comprehensive stress test has no special standard, and the test conditions are generally determined by referring to the method specified by GJB 899A-2009. The three tests have different purposes and different test conditions and cannot be replaced mutually, so that three test projects of the aircraft are required. With the increasing importance of aircraft development on ground test verification, each aircraft generally needs to be verified by three tests in a new model, the cost of the test period and the test experience is very high, and a large amount of manpower and material resources are wasted.
Disclosure of Invention
In view of the above analysis, the present invention aims to provide a comprehensive test method for an aircraft, which is used to solve the problem that the existing aircraft temperature test, vibration test and comprehensive stress test need to be separately tested.
The purpose of the invention is mainly realized by the following technical scheme:
in the technical scheme of the invention, the comprehensive test method of the aircraft is used for completing the temperature test, the vibration test and the comprehensive stress test of the aircraft by one-time test, and comprises the following steps:
step 1, acquiring a standard low-temperature test temperature and a standard high-temperature test temperature of an aircraft temperature test;
step 2, obtaining a standard vibration magnitude of an aircraft vibration test;
step 3, acquiring a standard measurement process of the aircraft comprehensive stress test;
step 4, setting the low temperature value in the standard measurement process as a standard low temperature test temperature, and adjusting the heat preservation time after the temperature is reduced to the standard low temperature test temperature; setting a high temperature value in a standard measurement process as a standard high temperature test temperature, and adjusting the heat preservation time after the temperature rises to the standard high temperature test temperature;
step 5, setting the vibration condition in the standard measurement process as a standard vibration magnitude and adjusting the vibration time;
and 6, taking the standard measurement process adjusted in the steps 4 and 5 as an actual comprehensive stress test process, carrying out an aircraft comprehensive stress test according to the actual comprehensive stress test process, and obtaining test results of an aircraft temperature test, a vibration test and a comprehensive stress test.
In the technical scheme of the invention, in the step 3, the standard measurement process comprises the following steps:
firstly, the temperature is reduced to a low temperature value, and after heat preservation, the aircraft is vibrated according to vibration conditions.
In the technical scheme of the invention, in the step 3, the standard measurement process further comprises: and after the vibration is finished, heating to a high temperature value, after heat preservation, vibrating the aircraft again according to the vibration condition, and finishing the test after the vibration is finished.
In the technical scheme of the invention, in the step 4, the heat preservation time after the temperature is reduced to the standard low-temperature test temperature is set to be at least 2 hours.
In the technical scheme of the invention, in the step 4, the heat preservation time after the temperature is raised to the standard high-temperature test temperature is set to be at least 2h.
In the technical scheme of the invention, in the step 5, the vibration condition comprises 1 or more vibration magnitudes.
In the technical scheme of the invention, in the step 5, the aircraft is vibrated according to each vibration magnitude, and the vibration magnitude in the vibration time is kept unchanged.
In the technical scheme of the invention, in the step 5, the vibration time after the temperature is reduced to the standard low-temperature test temperature is reduced by 1/2.
In the technical scheme of the invention, in the step 5, the vibration time after the temperature is raised to the standard high-temperature test temperature is reduced by 1/2.
In the technical scheme of the invention, in step 6, a comprehensive stress test of the aircraft is carried out according to the actual comprehensive stress test process, and test results of a temperature test, a vibration test and a comprehensive stress test of the aircraft are obtained.
The technical scheme of the invention can at least realize one of the following effects:
according to the invention, according to the existing aircraft temperature test, aircraft vibration test and aircraft comprehensive stress test, through adjusting the test conditions, a brand new comprehensive stress test is used for replacing the original three tests, and the three tests are combined into one test, so that the problem of time and labor consumption of a plurality of tests is solved, the test efficiency is greatly improved, and the achievement can be popularized to large-scale ground tests of various aircrafts.
In the invention, the technical schemes can be combined with each other to realize more preferable combination schemes. Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention, wherein like reference numerals are used to designate like parts throughout.
FIG. 1 is a cross-sectional view of a standard measurement process for a composite stress test of an aircraft;
fig. 2 is a cross-sectional view of an actual integrated stress test process according to an embodiment of the present invention.
Detailed Description
The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which form a part hereof, and which together with the embodiments of the invention serve to explain the principles of the invention and not to limit its scope.
In the description of the embodiments of the present invention, it should be noted that, unless otherwise explicitly stated or limited, the term "connected" should be interpreted broadly, and may be, for example, a fixed connection, a detachable connection, or an integral connection, which may be a mechanical connection, an electrical connection, which may be a direct connection, or an indirect connection via an intermediate medium. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The terms "top," "bottom," "above … …," "down," and "above … …" as used throughout the description are relative positions with respect to components of the device, such as the relative positions of the top and bottom substrates inside the device. It will be appreciated that the devices are multifunctional, regardless of their orientation in space.
The invention provides an aircraft comprehensive test method, which is used for completing an aircraft temperature test, a vibration test and a comprehensive stress test through one-time test, and the aircraft comprehensive test method comprises the following steps:
step 1, acquiring a standard low-temperature test temperature and a standard high-temperature test temperature of an aircraft temperature test; according to the specifications of GJB150.3A-2009 and GJB150.4A-2009, the aircraft working temperature extreme values, namely the standard low-temperature test temperature and the standard high-temperature test temperature, can be obtained.
Step 2, obtaining a standard vibration magnitude of an aircraft vibration test; according to the specification GJB150.16A, the maximum vibration magnitude value experienced by the aircraft can be obtained, and according to the maximum vibration magnitude value, the standard vibration magnitude value can be obtained, wherein the standard vibration magnitude value comprises a plurality of vibration magnitude values which gradually change so as to represent different vibration states of the aircraft between 0 vibration magnitude value and the maximum vibration magnitude value.
Step 3, acquiring a standard measurement process of the aircraft comprehensive stress test; there are no special criteria, and the test conditions are generally determined with reference to the method specified by GJB899A-2009, and standard measurement procedures are determined, including:
s01, reducing the working temperature to a low temperature value, keeping the working temperature unchanged, and keeping the temperature for a heat preservation time;
s02, enabling the aircraft to vibrate according to vibration conditions, wherein different vibration magnitudes correspond to different vibration times;
s03, raising the working temperature to a high temperature value, keeping the working temperature unchanged, and keeping the temperature for a holding time;
s04, vibrating the aircraft again according to the vibration condition, wherein different vibration magnitudes correspond to different vibration times;
and S05, completing the test.
Wherein the heat preservation time in S01 and S03 is the same, the vibration condition in S02 and S04 is the same, and the corresponding relation between the vibration magnitude and the vibration time is the same.
The idea of the embodiment of the invention is to improve the standard measurement process so that the aircraft temperature test, the vibration test and the comprehensive stress test can be simultaneously realized.
Step 4, setting the low temperature value in the standard measurement process as the standard low-temperature test temperature, and setting the heat preservation time after the temperature is reduced to the standard low-temperature test temperature to be at least 2h; and setting the high temperature value in the standard measurement process as the standard high temperature test temperature, and setting the heat preservation time after the temperature rises to the standard high temperature test temperature to be at least 2h. I.e. an improvement to S01 and S03 of the standard measurement procedure.
Because the standard low-temperature test temperature in the temperature test process of the aircraft is lower than the low-temperature value in the standard measurement process, and the standard high-temperature test temperature is higher than the high-temperature value in the standard measurement process, the test temperature condition of the embodiment of the invention is more severe than the temperature test temperature condition in the standard measurement process.
Therefore, the test conditions of the embodiment of the invention can realize the temperature test of the aircraft, and the comprehensive performance of the aircraft is more obviously represented when the comprehensive stress test is realized. In the embodiment of the invention, the heat preservation time is prolonged, and the aircraft stress data collected in the prolonged heat preservation time is used as the data of the aircraft temperature test.
And 5, setting the vibration condition in the standard measurement process as a standard vibration magnitude, adjusting the vibration time, reducing the vibration time after the temperature is reduced to the standard low-temperature test temperature by 1/2, and reducing the vibration time after the temperature is increased to the standard high-temperature test temperature by 1/2. I.e. an improvement to S02 and S04 of the standard measurement procedure.
Because the vibration magnitude of the aircraft vibration test is larger than that in the standard measurement process, the vibration condition of the embodiment of the invention is severer than that in the standard measurement process, so that the representation of the vibration condition of the embodiment of the invention on the comprehensive performance of the aircraft is more obvious. And because the vibration magnitude is improved, the vibration time can be shortened, and the test efficiency is improved.
And 6, taking the standard measurement process adjusted in the steps 4 and 5 as an actual comprehensive stress test process, carrying out an aircraft comprehensive stress test according to the actual comprehensive stress test process, and obtaining test results of an aircraft temperature test, a vibration test and a comprehensive stress test.
Taking the test of a certain type of aircraft as an example
Step 1, the standard high-temperature test temperature is 60 ℃, the duration time is 2 hours after the temperature is stable, the standard low-temperature test temperature is-45 ℃, and the duration time is 2 hours after the temperature is stable;
step 2, the vibration magnitude of 5g lasts for 1min, the vibration magnitude of 3g lasts for 122min, and the vibration magnitude of 15g lasts for 2min;
step 3, as shown in fig. 1, the standard measurement process is: cooling to-40 deg.C, maintaining the temperature for 30min, performing ground work simulation for 60min, and vibrating; heating to 50 deg.C, maintaining the temperature for 30min, performing ground work simulation for 60min, and vibrating. The vibration conditions were: vibration magnitude of 2g lasts for 1min, vibration magnitude of 1.5g lasts for 122min, and vibration magnitude of 8g lasts for 2min.
And 4, replacing-40 ℃ with-45 ℃, replacing 50 ℃ with 60 ℃, and setting the heat preservation time to be 120min.
The temperature value is changed because the temperature value in the three-in-one test is ensured to cover the temperature values in the aircraft temperature test and the comprehensive stress test, the duration time is the same, the duration time of the aircraft temperature test requires that the temperature is kept for 120min after being stabilized, and the temperature of the aircraft comprehensive stress test only requires the time (less than 120 min) required by the test after being stabilized, so the temperature keeping time of the three-in-one test is 120min.
And 5, setting the vibration conditions as follows: the vibration magnitude of 5g lasts for 0.5min, the vibration magnitude of 3g lasts for 61min, and the vibration magnitude of 15g lasts for 1min.
Because the vibration magnitude in the aircraft vibration test is greater than the vibration magnitude in the aircraft comprehensive stress test, therefore the vibration magnitude goes on according to the vibration condition of big magnitude in the trinity test, test time also carries out according to a large number of levels, but because there are two stages of high temperature and low temperature in the trinity test, for guaranteeing not to cause the over test (guarantee that the vibration can not produce the harm to the aircraft promptly), carry out vibration time average distribution to two stages, in addition, the vibration magnitude in the trinity test is great, can guarantee to cover the long-time vibration condition of low magnitude of aircraft comprehensive stress test.
Step 6, as shown in fig. 2, the adjusted actual comprehensive test process is as follows: cooling to-45 deg.C, maintaining the temperature for 120min, performing ground work simulation for 60min, and vibrating; heating to 60 deg.C, maintaining the temperature for 120min, performing ground work simulation for 60min, and vibrating. The vibration conditions were: vibration magnitude of 5g lasts for 0.5min, vibration magnitude of 3g lasts for 61min, and vibration magnitude of 15g lasts for 1min.
And carrying out a test once according to the actual comprehensive test process to obtain the results of the temperature test, the vibration test and the comprehensive stress test of the aircraft.
Tests were conducted using the method of the present invention examples, as compared to existing test methods, as shown in table 1.
TABLE 1
The temperature test and the vibration test of the aircraft are two independent test items specified by standards at present and are used for checking the working performance of the aircraft in the temperature and vibration environment, the comprehensive stress test of the aircraft is slowly developed in the last decade, the test items of the aircraft faults are eliminated through the comprehensive action of the temperature and the vibration, and the three test items have different purposes, so the test is always carried out independently.
In conclusion, the invention provides a comprehensive test method for an aircraft, according to the existing temperature test, vibration test and comprehensive stress test of the aircraft, a brand new comprehensive stress test is used for replacing the original three tests by adjusting the test conditions, and the three tests are combined into one test, so that the problem of time and labor consumption of a plurality of tests is solved, 2/3 of preparation time before the test and detection time after the test can be saved, 1/2 of test time can be reduced, two times of test cost can be saved, the test efficiency is greatly improved, and the results can be popularized to large-scale ground tests of various aircrafts.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Claims (4)
1. The comprehensive test method of the aircraft is used for testing and completing an aircraft temperature test, a vibration test and a comprehensive stress test in one step and is characterized by comprising the following steps of:
step 1, acquiring a standard low-temperature test temperature and a standard high-temperature test temperature of an aircraft temperature test;
step 2, obtaining a standard vibration magnitude of an aircraft vibration test;
step 3, acquiring a standard measurement process of the aircraft comprehensive stress test;
step 4, setting the low temperature value in the standard measurement process as a standard low temperature test temperature, and adjusting the heat preservation time after the temperature is reduced to the standard low temperature test temperature; setting a high temperature value in a standard measurement process as a standard high temperature test temperature, and adjusting the heat preservation time after the temperature rises to the standard high temperature test temperature;
step 5, setting the vibration condition in the standard measurement process as a standard vibration magnitude and adjusting the vibration time;
step 6, taking the standard measurement process adjusted in the steps 4 and 5 as an actual comprehensive stress test process, and carrying out an aircraft comprehensive stress test according to the actual comprehensive stress test process to obtain test results of an aircraft temperature test, a vibration test and a comprehensive stress test;
in the step 4, the standard low-temperature test temperature is-45 ℃;
in the step 4, the heat preservation time after the temperature is reduced to the standard low-temperature test temperature is set to be at least 2 hours;
in the step 4, the heat preservation time after the temperature is increased to the standard high-temperature test temperature is set to be at least 2 hours;
in the step 5, the aircraft is vibrated according to each vibration magnitude, and the vibration magnitude in the vibration time is kept unchanged;
in the step 5, the vibration time after the temperature is reduced to the standard low-temperature test temperature is reduced by 1/2;
in the step 5, the vibration time after the temperature is increased to the standard high-temperature test temperature is reduced by 1/2;
the vibration conditions in the step 5 are as follows: the vibration magnitude of 5g lasts for 0.5min, the vibration magnitude of 3g lasts for 61min, and the vibration magnitude of 15g lasts for 1min;
the actual comprehensive test process adjusted in the step 6 is as follows: cooling to-45 deg.C, maintaining the temperature for 120min, performing ground work simulation for 60min, and vibrating; heating to 60 deg.C, maintaining the temperature for 120min, performing ground work simulation for 60min, and vibrating.
2. An aircraft comprehensive test method according to claim 1, characterized in that in said step 3, the standard measurement procedure comprises:
firstly, the temperature is reduced to a low temperature value, and after heat preservation, the aircraft is vibrated according to vibration conditions.
3. The aircraft comprehensive test method of claim 2, wherein in step 3, the standard measurement process further comprises: and after the vibration is finished, heating to a high temperature value, after heat preservation, vibrating the aircraft again according to the vibration condition, and finishing the test after the vibration is finished.
4. The aircraft comprehensive test method according to claim 1, wherein in the step 6, the aircraft comprehensive stress test is performed once according to the actual comprehensive stress test process, and test results of the aircraft temperature test, the vibration test and the comprehensive stress test are obtained.
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| 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 |
| CN114323600A (en) * | 2021-11-22 | 2022-04-12 | 北京机电工程研究所 | Comprehensive stress reliability strengthening test method |
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| CN101900788B (en) * | 2009-05-25 | 2013-06-05 | 北京圣涛平试验工程技术研究院有限责任公司 | Test method for detecting reliability of product |
| CN102494880B (en) * | 2011-11-24 | 2014-04-02 | 北京航空航天大学 | Design method for integrated stress, acceleration and service life testing profile of astronautic drive component |
| CN103513647B (en) * | 2013-07-10 | 2015-12-09 | 西安航空制动科技有限公司 | A kind of synthetic chemistry laboratory test method of antiskid braking control box |
| CN107064665B (en) * | 2016-12-01 | 2019-08-09 | 中国北方车辆研究所 | Electronic product combined stress strenuous test method |
| US10810501B1 (en) * | 2017-10-20 | 2020-10-20 | Amazon Technologies, Inc. | Automated pre-flight and in-flight testing of aerial vehicles by machine learning |
| CN107870276A (en) * | 2017-11-03 | 2018-04-03 | 北京空间技术研制试验中心 | Method of testing for the component of spacecraft |
| CN109540559A (en) * | 2018-11-27 | 2019-03-29 | 上海航天计算机技术研究所 | A kind of stress resultant screening test method being applicable in on-board equipment |
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