CN113928595B - Method for tailoring low-temperature test conditions of complete aircraft in laboratory - Google Patents
Method for tailoring low-temperature test conditions of complete aircraft in laboratory Download PDFInfo
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- CN113928595B CN113928595B CN202111550216.1A CN202111550216A CN113928595B CN 113928595 B CN113928595 B CN 113928595B CN 202111550216 A CN202111550216 A CN 202111550216A CN 113928595 B CN113928595 B CN 113928595B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
Abstract
The invention discloses a method for cutting low-temperature test conditions of a complete machine of an airplane in a laboratory, which comprises the following steps: firstly, screening special temperature of an external field low-temperature environment; secondly, quantitatively analyzing the performance of the key motion mechanism of the airplane in the outfield low-temperature environment; thirdly, preliminary cutting under low-temperature test conditions; fourthly, drawing a curve of the performance variation of the key movement mechanism of the airplane at the test temperature of the outfield low-temperature environment; fifthly, quantitatively measuring the performance of the key movement mechanism of the airplane in the low-temperature environment in the laboratory; drawing a curve of the performance variation of the key movement mechanism of the airplane at the test temperature of the low-temperature environment in the laboratory; seventhly, fitting the corresponding first curve and the second curve; eighthly, checking the goodness of fit by the R square. The invention integrates the action mechanism of the low-temperature test on the whole airplane into the cutting process, deeply considers the equivalence analysis and the environmental test verification of the outfield natural environment and the outfield laboratory, realizes the effective expansion of the cutting mode and the thinking, and is real and reasonable.
Description
Technical Field
The invention belongs to the technical field of low-temperature test condition cutting of a complete airplane, and particularly relates to a method for cutting low-temperature test conditions of a complete airplane in a laboratory.
Background
The existing airplane climate test is to enable a test airplane to be subjected to the action of various climate environmental stresses according to specified conditions and test sequences under the condition of simulating environmental conditions in a climate test cabin, such as typical climate environments of high temperature, low temperature, rain, fog, snow, freezing rain, ice accumulation, solar irradiation and the like, so as to examine the environmental adaptability of the test airplane. The climate test generally takes a full-state airplane as a test object, fixes the airplane at a corresponding position on the ground of a laboratory through a brake, a wheel gear or a mooring device, and usually needs the airplane to start an auxiliary power device, such as an APU (auxiliary power unit) or an engine, so as to detect the working performance. The low-temperature environment in the climate test refers to the climate environment from 20 ℃ to below-50 ℃, and the definition of GJB 6117-: "the environmental test work and content of the laboratory in each stage of the equipment life are cut, and the cutting is a component part of environmental engineering cutting. The existing climate environment test mainly comprises definite product characteristics, a climate environment section and a design test. And cutting to obtain environmental test items, test conditions and parameter values, test procedures, test sequences and failure criteria. The method is a general method for designing an environmental test of a common product, is not suitable for a full-state airplane, has high cost and poor effectiveness of a low-temperature test when the whole airplane is in a span range of about 70 ℃, needs to be cut in the temperature range, and rarely researches on the low-temperature test cutting technology of the whole airplane in a laboratory. Therefore, a method for cutting the low-temperature test condition of the whole airplane in the laboratory is absent at present, the simulation analysis of the response of the extreme low-temperature environmental stress to the environment of the complex system of the airplane is realized, and the equivalence analysis and the test verification of the internal field laboratory and the external field natural environment are also realized, so that the low-temperature test of the airplane in the laboratory is more reasonable and real.
Disclosure of Invention
The invention aims to solve the technical problem that the low-temperature test condition cutting method for the complete aircraft in the laboratory aims at overcoming the defects in the prior art, integrates the action mechanism of a low-temperature test on the complete aircraft into the cutting process, deeply considers the equivalence analysis and the environmental test verification of an external field natural environment and an internal field laboratory, realizes the effective expansion of the cutting mode and the thinking, ensures that the climate environment test of the complete aircraft in the laboratory is more real and reasonable, and has strong theoretical performance, good operability and universality and convenient popularization and use.
In order to solve the technical problems, the invention adopts the technical scheme that: a method for cutting low-temperature test conditions of a complete machine of an airplane in a laboratory is characterized by comprising the following steps:
step one, screening special temperature of an external field low-temperature environment, and the process is as follows:
step 101, according to a formula
Determining the primary special temperature of the low-temperature environment of the external field
Wherein i is a number of days and i =1, 2,.., 365 or 366, j is a number of hours and j =1, 2,.., 24,
representing the temperature at the j hour on day i of the year, when i =1,
the temperature at the jth hour of the last day of the previous year,
the temperature of the jth hour in the last but one day of the previous year, and the delta T is a temperature difference threshold;
step 102, filtering out the primary special temperature
Primary special temperature with less than 10% of occurrence probability
Remaining primary specific temperature
Is a special temperature of the low-temperature environment of the external field
；
Secondly, quantitatively analyzing the performance of the key movement mechanism of the airplane in the outfield low-temperature environment: inputting external field environment parameters according to a time sequence, performing low-temperature test on the whole airplane by using simulation software to obtain a thermal deformation cloud picture of the key movement mechanism of the airplane under a low-temperature condition, and acquiring the performance variation of the key movement mechanism of the airplane;
the external field environment parameters comprise special temperature of external field low-temperature environment
And ambient pressure, humidity, wind speed, wind direction, and irradiance at the corresponding time point;
the key movement mechanism of the airplane comprises a landing gear, a cabin door, a flap, a slat, an airframe structure, an airframe skin, a fuel system, a hydraulic system, an engine nacelle and an air conditioning system;
the performance variable quantity of the key movement mechanism of the airplane comprises deformation quantity and retraction time variable quantity of an undercarriage, deformation quantity and handle opening force deformation quantity of a cabin door, retraction time deformation quantity of a flap, retraction time deformation quantity of a slat, deformation quantity of a body structure, deformation quantity of a fuselage skin, oil temperature pressure variation quantity and oil leakage quantity deformation quantity of a fuel oil system, oil temperature pressure variation quantity of a hydraulic system, lock closing force deformation quantity of an engine nacelle and temperature regulation time variable quantity of an air conditioning system;
step three, preliminary cutting under low-temperature test conditions: in simulation software, preliminarily cutting out the special temperature of the outfield low-temperature environment according to the performance variation of the key movement mechanism of the airplane
；
The deformation amount and the retraction time variation of the landing gear, the deformation amount and the handle opening force deformation amount of the cabin door, the retraction time deformation amount of the flap, the retraction time deformation amount of the slat, the deformation amount of the body structure, the deformation amount of the body skin, the deformation amount of the oil temperature pressure and the oil leakage amount of the fuel oil system, the oil temperature pressure variation amount of the hydraulic system, the deformation amount of the locking and closing force of the engine nacelle and the temperature adjustment time variation amount of the air conditioning system respectively have respective variation threshold values, and when the special temperature of the external field low-temperature environment is met
When all the variable quantities do not exceed the respective variable quantity threshold, the special temperature of the outfield low-temperature environment is cut and removed
(ii) a When the temperature is lower than the temperature of the external fieldSpecific temperature of the environment
When any variable exceeds the variable threshold, the special temperature of the external field low-temperature environment is reserved
Specific temperature of the low temperature environment of the reserved external field
Test temperature of low-temperature environment of external field
；
Step four, drawing a curve of the performance variation of the aircraft key motion mechanism at the test temperature of the outfield low-temperature environment: drawing a first curve system comprising the performance variation of the key movement mechanism of the airplane at the test temperature of the outfield low-temperature environment;
and step five, quantitatively measuring the performance of the key movement mechanism of the airplane in the low-temperature environment in the laboratory: in the actual experiment process, the temperature of the laboratory is adjusted to reach the test temperature of the external field low-temperature environment in sequence
Measuring the performance variation of the key motion mechanism of the airplane;
step six, drawing a curve of the performance variation of the key movement mechanism of the airplane at the low-temperature environment test temperature in the laboratory: drawing a second curve system comprising the performance variation of each aircraft key movement mechanism at the test temperature of the low-temperature environment in the laboratory;
the number of the second curves in the second curve system is equal to the number of the first curves in the first curve system, and the second curves correspond to the first curves in the first curve system one by one;
and seventhly, fitting the corresponding first curve and the second curve: fitting the deformation of the corresponding second curve to be equal to that of the first curve to obtain the corresponding deformationThe temperature of the second curve being a function of the temperature of the first curve, i.e.
Wherein, in the step (A),
is the temperature fit value of the second curve, k is the scaling factor of the curve,
is the amount of translation for the curve transformation,
is the temperature of the corresponding first curve;
step eight, checking the goodness of fit by the R side: selecting
Checking and evaluating whether the fitting meets the fitting error when
When the test evaluation fitting meets the fitting error threshold, the temperature fitting value of each second curve in the second curve system forms the test temperature of the low-temperature environment in the laboratory
(ii) a When in use
When the fitting of the inspection evaluation does not meet the fitting error threshold, the scaling factor of the curve and the translation amount of the curve transformation in the step seven are adjusted until the scaling factor and the translation amount of the curve transformation do not meet the fitting error threshold
The test evaluation fit satisfies a fitting error threshold.
The low-temperature test condition cutting method for the whole aircraft in the laboratory is characterized by comprising the following steps of: the temperature difference threshold delta T is 5-10 ℃.
The low-temperature test condition cutting method for the whole aircraft in the laboratory is characterized by comprising the following steps of: the simulation software is CATIA simulation software.
The low-temperature test condition cutting method for the whole aircraft in the laboratory is characterized by comprising the following steps of: the fitting error threshold is not greater than 0.01.
The method has the advantages that the low-temperature test is integrated into the cutting process of the action mechanism of the whole airplane, the equivalence analysis and the environmental test verification of the outfield natural environment and the outfield laboratory are deeply considered, the cutting mode and the thinking are effectively expanded, the climate environment test of the whole airplane laboratory is more real and reasonable, and the method is strong in theory, good in operability and universality and convenient to popularize and use.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a block diagram of the process flow of the present invention.
Detailed Description
As shown in FIG. 1, the method for cutting the low-temperature test condition of the whole airplane in the laboratory comprises the following steps:
step one, screening special temperature of an external field low-temperature environment, and the process is as follows:
step 101, according to a formula
Determining the primary special temperature of the low-temperature environment of the external field
Wherein i is a number of days and i =1, 2,.., 365 or 366, j is a number of hours and j =1, 2,.., 24,
representing the temperature at the j hour on day i of the year, when i =1,
the temperature at the jth hour of the last day of the previous year,
the temperature of the jth hour in the last but one day of the previous year, and the delta T is a temperature difference threshold;
step 102, filtering out the primary special temperature
Primary special temperature with less than 10% of occurrence probability
Remaining primary specific temperature
Is a special temperature of the low-temperature environment of the external field
；
Secondly, quantitatively analyzing the performance of the key movement mechanism of the airplane in the outfield low-temperature environment: inputting external field environment parameters according to a time sequence, performing low-temperature test on the whole airplane by using simulation software to obtain a thermal deformation cloud picture of the key movement mechanism of the airplane under a low-temperature condition, and acquiring the performance variation of the key movement mechanism of the airplane;
the external field environment parameters comprise special temperature of external field low-temperature environment
And ambient pressure, humidity, wind speed, wind direction, and irradiance at the corresponding time point;
the key movement mechanism of the airplane comprises a landing gear, a cabin door, a flap, a slat, an airframe structure, an airframe skin, a fuel system, a hydraulic system, an engine nacelle and an air conditioning system;
the performance variable quantity of the key movement mechanism of the airplane comprises deformation quantity and retraction time variable quantity of an undercarriage, deformation quantity and handle opening force deformation quantity of a cabin door, retraction time deformation quantity of a flap, retraction time deformation quantity of a slat, deformation quantity of a body structure, deformation quantity of a fuselage skin, oil temperature pressure variation quantity and oil leakage quantity deformation quantity of a fuel oil system, oil temperature pressure variation quantity of a hydraulic system, lock closing force deformation quantity of an engine nacelle and temperature regulation time variable quantity of an air conditioning system;
step three, preliminary cutting under low-temperature test conditions: in simulation software, preliminarily cutting out the special temperature of the outfield low-temperature environment according to the performance variation of the key movement mechanism of the airplane
；
The deformation amount and the retraction time variation of the landing gear, the deformation amount and the handle opening force deformation amount of the cabin door, the retraction time deformation amount of the flap, the retraction time deformation amount of the slat, the deformation amount of the body structure, the deformation amount of the body skin, the deformation amount of the oil temperature pressure and the oil leakage amount of the fuel oil system, the oil temperature pressure variation amount of the hydraulic system, the deformation amount of the locking and closing force of the engine nacelle and the temperature adjustment time variation amount of the air conditioning system respectively have respective variation threshold values, and when the special temperature of the external field low-temperature environment is met
When all the variable quantities do not exceed the respective variable quantity threshold, the special temperature of the outfield low-temperature environment is cut and removed
(ii) a When the temperature is special in the low-temperature environment of the external field
When any variable exceeds the variable threshold, the special temperature of the external field low-temperature environment is reserved
Specific temperature of the low temperature environment of the reserved external field
Test temperature of low-temperature environment of external field
；
Step four, drawing a curve of the performance variation of the aircraft key motion mechanism at the test temperature of the outfield low-temperature environment: drawing a first curve system comprising the performance variation of the key movement mechanism of the airplane at the test temperature of the outfield low-temperature environment;
and step five, quantitatively measuring the performance of the key movement mechanism of the airplane in the low-temperature environment in the laboratory: in the actual experiment process, the temperature of the laboratory is adjusted to reach the test temperature of the external field low-temperature environment in sequence
Measuring the performance variation of the key motion mechanism of the airplane;
step six, drawing a curve of the performance variation of the key movement mechanism of the airplane at the low-temperature environment test temperature in the laboratory: drawing a second curve system comprising the performance variation of each aircraft key movement mechanism at the test temperature of the low-temperature environment in the laboratory;
the number of the second curves in the second curve system is equal to the number of the first curves in the first curve system, and the second curves correspond to the first curves in the first curve system one by one;
and seventhly, fitting the corresponding first curve and the second curve: fitting the deformation of the corresponding second curve to be equal to the deformation of the first curve, and obtaining a functional expression of the temperature of the corresponding second curve and the temperature of the first curve, namely
Wherein, in the step (A),
is the temperature fit value of the second curve, k is the scaling factor of the curve,
is the amount of translation for the curve transformation,
is the temperature of the corresponding first curve;
step eight, checking the goodness of fit by the R side: selecting
Checking and evaluating whether the fitting meets the fitting error when
When the test evaluation fitting meets the fitting error threshold, the temperature fitting value of each second curve in the second curve system forms the test temperature of the low-temperature environment in the laboratory
(ii) a When in use
When the fitting of the inspection evaluation does not meet the fitting error threshold, the scaling factor of the curve and the translation amount of the curve transformation in the step seven are adjusted until the scaling factor and the translation amount of the curve transformation do not meet the fitting error threshold
The test evaluation fit satisfies a fitting error threshold.
In this embodiment, the temperature difference threshold Δ T is 5 to 10 ℃.
In this embodiment, the simulation software is CATIA simulation software.
In this embodiment, the fitting error threshold is not greater than 0.01.
When the method is used, the action mechanism of the low-temperature test on the whole airplane is integrated into the cutting process, the equivalence analysis and the environmental test verification of the outfield natural environment and the outfield laboratory are deeply considered, the cutting mode and the thinking are effectively expanded, the climate environment test of the whole airplane laboratory is more real and reasonable, and the climate environment test cutting method is strong in theory, and good in operability and universality.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.
Claims (4)
1. A method for cutting low-temperature test conditions of a complete machine of an airplane in a laboratory is characterized by comprising the following steps:
step one, screening special temperature of an external field low-temperature environment, and the process is as follows:
step 101, according to a formula
Determining the primary special temperature of the low-temperature environment of the external field
Wherein i is a number of days and i =1, 2,.., 365 or 366, j is a number of hours and j =1, 2,.., 24,
representing the temperature at the j hour on day i of the year, when i =1,
the temperature at the jth hour of the last day of the previous year,
the temperature of the jth hour in the last but one day of the previous year, and the delta T is a temperature difference threshold;
step 102, filtering out the primary special temperature
Primary special temperature with less than 10% of occurrence probability
Remaining primary specific temperature
Is a special temperature of the low-temperature environment of the external field
；
Secondly, quantitatively analyzing the performance of the key movement mechanism of the airplane in the outfield low-temperature environment: inputting external field environment parameters according to a time sequence, performing low-temperature test on the whole airplane by using simulation software to obtain a thermal deformation cloud picture of the key movement mechanism of the airplane under a low-temperature condition, and acquiring the performance variation of the key movement mechanism of the airplane;
the external field environment parameters comprise special temperature of external field low-temperature environment
And ambient pressure, humidity, wind speed, wind direction, and irradiance at the corresponding time point;
the key movement mechanism of the airplane comprises a landing gear, a cabin door, a flap, a slat, an airframe structure, an airframe skin, a fuel system, a hydraulic system, an engine nacelle and an air conditioning system;
the performance variable quantity of the key movement mechanism of the airplane comprises deformation quantity and retraction time variable quantity of an undercarriage, deformation quantity and handle opening force deformation quantity of a cabin door, retraction time deformation quantity of a flap, retraction time deformation quantity of a slat, deformation quantity of a body structure, deformation quantity of a fuselage skin, oil temperature pressure variation quantity and oil leakage quantity deformation quantity of a fuel oil system, oil temperature pressure variation quantity of a hydraulic system, lock closing force deformation quantity of an engine nacelle and temperature regulation time variable quantity of an air conditioning system;
step three, preliminary cutting under low-temperature test conditions: in simulation software, preliminarily cutting out the special temperature of the outfield low-temperature environment according to the performance variation of the key movement mechanism of the airplane
；
The deformation amount and the retraction time variation of the landing gear, the deformation amount and the handle opening force deformation amount of the cabin door, the retraction time deformation amount of the flap, the retraction time deformation amount of the slat, the deformation amount of the body structure, the deformation amount of the body skin, the deformation amount of the oil temperature pressure and the oil leakage amount of the fuel oil system, the oil temperature pressure variation amount of the hydraulic system, the deformation amount of the locking and closing force of the engine nacelle and the temperature adjustment time variation amount of the air conditioning system respectively have respective variation threshold values, and when the special temperature of the external field low-temperature environment is met
When all the variable quantities do not exceed the respective variable quantity threshold, the special temperature of the outfield low-temperature environment is cut and removed
(ii) a When the temperature is special in the low-temperature environment of the external field
When any variable exceeds the variable threshold, the special temperature of the external field low-temperature environment is reserved
Specific temperature of the low temperature environment of the reserved external field
Test temperature of low-temperature environment of external field
；
Step four, drawing a curve of the performance variation of the aircraft key motion mechanism at the test temperature of the outfield low-temperature environment: drawing a first curve system comprising the performance variation of the key movement mechanism of the airplane at the test temperature of the outfield low-temperature environment;
and step five, quantitatively measuring the performance of the key movement mechanism of the airplane in the low-temperature environment in the laboratory: in the actual experiment process, the temperature of the laboratory is adjusted to reach the test temperature of the external field low-temperature environment in sequence
Measuring the performance variation of the key motion mechanism of the airplane;
step six, drawing a curve of the performance variation of the key movement mechanism of the airplane at the low-temperature environment test temperature in the laboratory: drawing a second curve system comprising the performance variation of each aircraft key movement mechanism at the test temperature of the low-temperature environment in the laboratory;
the number of the second curves in the second curve system is equal to the number of the first curves in the first curve system, and the second curves correspond to the first curves in the first curve system one by one;
and seventhly, fitting the corresponding first curve and the second curve: fitting the deformation of the corresponding second curve to be equal to the deformation of the first curve, and obtaining a functional expression of the temperature of the corresponding second curve and the temperature of the first curve, namely
Wherein, in the step (A),
is the temperature fit value of the second curve, k is the scaling factor of the curve,
is the amount of translation for the curve transformation,
is the temperature of the corresponding first curve;
step eight, checking the goodness of fit by the R side: selecting
Checking and evaluating whether the fitting meets the fitting error when
When the test evaluation fitting meets the fitting error threshold, the temperature fitting value of each second curve in the second curve system forms the test temperature of the low-temperature environment in the laboratory
(ii) a When in use
When the fitting of the inspection evaluation does not meet the fitting error threshold, the scaling factor of the curve and the translation amount of the curve transformation in the step seven are adjusted until the scaling factor and the translation amount of the curve transformation do not meet the fitting error threshold
The test evaluation fit satisfies a fitting error threshold.
2. The method for cutting the low-temperature test condition of the complete machine of the airplane in the laboratory according to claim 1, which is characterized in that: the temperature difference threshold delta T is 5-10 ℃.
3. The method for cutting the low-temperature test condition of the complete machine of the airplane in the laboratory according to claim 1, which is characterized in that: the simulation software is CATIA simulation software.
4. The method for cutting the low-temperature test condition of the complete machine of the airplane in the laboratory according to claim 1, which is characterized in that: the fitting error threshold is not greater than 0.01.
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| CN111413563A (en) * | 2020-03-31 | 2020-07-14 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | Method for determining environmental adaptability test conditions of helicopter airborne electronic equipment |
| CN113720702A (en) * | 2021-08-08 | 2021-11-30 | 中国飞机强度研究所 | Material external field low-temperature test response equivalence method based on equivalence theory |
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2021
- 2021-12-17 CN CN202111550216.1A patent/CN113928595B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| DE102005041427A1 (en) * | 2005-08-31 | 2007-03-01 | Endress + Hauser Conducta Gesellschaft für Mess- und Regeltechnik mbH + Co. KG | Sensor e.g. gas sensor, simulator for testing process system behavior, has control circuit that simulates temporal processing of measuring signals of sensors and provides corresponding output signal to measuring section interface |
| CN102951286A (en) * | 2011-08-16 | 2013-03-06 | 波音公司 | Variable camber fluid-dynamic body utilizing optimized smart materials |
| CN108168893A (en) * | 2017-12-13 | 2018-06-15 | 中国飞机强度研究所 | A kind of interior aircraft engine running experience compensated with air system |
| CN111413563A (en) * | 2020-03-31 | 2020-07-14 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | Method for determining environmental adaptability test conditions of helicopter airborne electronic equipment |
| CN113720702A (en) * | 2021-08-08 | 2021-11-30 | 中国飞机强度研究所 | Material external field low-temperature test response equivalence method based on equivalence theory |
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