CN113935117A - Thermal task proportion and temperature value determination method for civil aircraft thermal fatigue load spectrum - Google Patents

Thermal task proportion and temperature value determination method for civil aircraft thermal fatigue load spectrum Download PDF

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CN113935117A
CN113935117A CN202111549307.3A CN202111549307A CN113935117A CN 113935117 A CN113935117 A CN 113935117A CN 202111549307 A CN202111549307 A CN 202111549307A CN 113935117 A CN113935117 A CN 113935117A
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temperature
computer
aircraft
task
value
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CN113935117B (en
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吴敬涛
王彬文
成竹
邓文亮
张惠
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AVIC Aircraft Strength Research Institute
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Abstract

The invention discloses a method for determining the thermal task proportion and the temperature value of a civil aircraft thermal fatigue load spectrum, which comprises the following steps: acquiring temperature data when each aircraft on a flight line is in a cruising state; secondly, carrying out statistical analysis on a temperature data set of the aircraft in the cruising state; thirdly, determining the proportion of hot tasks in the thermal fatigue performance test; and fourthly, determining the hot task temperature in the thermal fatigue performance test. The method has simple steps and reasonable design, obtains the hot task temperatures and the hot task proportions of the cold day, the standard day and the hot day when the aircraft is in a cruising state, and is convenient for developing the design of researching the load spectrum of the thermal fatigue performance of the civil aircraft mixed structure.

Description

Thermal task proportion and temperature value determination method for civil aircraft thermal fatigue load spectrum
Technical Field
The invention belongs to the technical field of civil aircraft thermal fatigue performance tests, and particularly relates to a method for determining a thermal task proportion and a temperature value of a civil aircraft thermal fatigue load spectrum.
Background
Each commercial flight of a large civil subsonic aircraft comprises the stages of parking, ground taxiing, takeoff and running, departure, climbing, cruising, descending, approach, landing, sliding and the like. The flying speed, the external environment temperature, the solar radiation, the ground radiation, the system heat source and the like of the airplane in each stage are different, so that the structure temperature of the airplane in each stage is different in the flying process.
The temperature of the environment during the integral assembly of the airplane is generally between 15 and 28 ℃, and the internal force (except the internal force caused by the self weight) in the airplane structure at the assembly temperature can be considered to be absent. However, due to the difference in the coefficient of thermal expansion of the materials, changes in the temperature of the structure during each flight can cause additional loads to develop internally in the aircraft structure (particularly in hybrid structures where metal and composite materials are assembled because the coefficient of thermal expansion of metal is much greater than that of composite materials) and, in combination with mechanical loads, can have an effect on the fatigue and damage tolerance performance of the structure; and in some cases, too high or too low a temperature, in the hot or cold state for a long time, can also cause degradation of the performance of the aircraft structural material. Heat must be considered during the design process.
Therefore, when the research on the thermal fatigue performance of the civil aircraft mixed structure is carried out, the determination of the thermal task proportion and the temperature value of the aircraft is crucial to the thermal fatigue load spectrum of the mixed structure, and therefore a method for determining the thermal task proportion of the thermal fatigue load spectrum of the civil aircraft mixed structure is needed.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a method for determining the thermal task proportion and the temperature value of a civil aircraft thermal fatigue load spectrum, aiming at the defects in the prior art, the method has simple steps and reasonable design, obtains the thermal task temperatures and the thermal task proportions of a cold day, a standard day and a hot day when an aircraft is in a cruising state, and is convenient for developing the design of researching the load spectrum of the civil aircraft mixed structure thermal fatigue performance.
In order to solve the technical problems, the invention adopts the technical scheme that: a method for determining the thermal task proportion and the temperature value of a civil aircraft thermal fatigue load spectrum is characterized by comprising the following steps:
the method comprises the following steps of firstly, acquiring temperature data when each aircraft on a route is in a cruising state:
step 101, setting
Figure 434011DEST_PATH_IMAGE001
The plane flies along a preset route; wherein each airplane is respectively provided with a temperature sensor
Figure 848812DEST_PATH_IMAGE002
The temperature sensor carried on the overhead plane is recorded as
Figure 791360DEST_PATH_IMAGE003
A temperature sensor is arranged on the base plate, and the temperature sensor,
Figure 229295DEST_PATH_IMAGE003
and
Figure 649912DEST_PATH_IMAGE001
are all positive integers, and
Figure 122481DEST_PATH_IMAGE004
；
step 102, in the second step
Figure 547515DEST_PATH_IMAGE002
In the process that the plane flies along a preset air route and is in a cruising state, the first step
Figure 472746DEST_PATH_IMAGE002
The temperature sensor detects the flight altitude temperature according to the set sampling interval to obtain the second
Figure 697054DEST_PATH_IMAGE002
Setting the corresponding flight altitude temperature of each sampling moment of the plane; wherein the total number of sampling time is
Figure 758551DEST_PATH_IMAGE005
And is and
Figure 42902DEST_PATH_IMAGE005
is a positive integer;
step 103, adopting a computer pair
Figure 455428DEST_PATH_IMAGE001
Frame airplane
Figure 483427DEST_PATH_IMAGE005
Carrying out median processing on the corresponding aviation altitude temperatures at each sampling moment to obtain a temperature data set of the cruise state of the airplane;
step two, statistical analysis of the temperature data set of the aircraft cruise state:
carrying out statistical analysis on the temperature data set of the aircraft cruising state by adopting a computer, and obtaining a cumulative distribution curve chart; the abscissa of the cumulative distribution curve graph is a temperature value, and the ordinate of the cumulative distribution curve graph is a cumulative probability value;
step three, determining the hot task proportion in the thermal fatigue performance test:
step 301, performing linear fitting on the cumulative distribution curve graph by using MATLAB software by using a computer to obtain a first straight line segment, a second straight line segment and a third straight line segment in sequence; the first straight line section is located on a negative half shaft of an abscissa, and the third straight line section is located on a positive half shaft of the abscissa;
step 302, using a computer to make a vertical coordinate mark corresponding to the intersection point of the first straight line segment and the second straight line segment as a first cumulative probability value
Figure 727327DEST_PATH_IMAGE006
Marking the vertical coordinate mark corresponding to the intersection point of the third straight-line segment and the second straight-line segment as a second accumulative probability value
Figure 917000DEST_PATH_IMAGE007
(ii) a Wherein the content of the first and second substances,
Figure 816823DEST_PATH_IMAGE007
is greater than
Figure 382933DEST_PATH_IMAGE006
;
Step 303, using a computer to accumulate the first accumulationProbability value
Figure 684601DEST_PATH_IMAGE006
Recording the ratio of cold day tasks
Figure 45176DEST_PATH_IMAGE008
Will be
Figure 245344DEST_PATH_IMAGE009
The probability value of (D) is recorded as the standard daily task proportion
Figure 615145DEST_PATH_IMAGE010
Will be
Figure 505741DEST_PATH_IMAGE011
The probability value of is recorded as the hot day task proportion
Figure 302796DEST_PATH_IMAGE012
；
Step four, determining the hot task temperature in the thermal fatigue performance test:
step 401, using a computer to accumulate the probability in the ordinate as
Figure 911632DEST_PATH_IMAGE013
The corresponding temperature value is recorded as the temperature of the cold and hot tasks
Figure 85124DEST_PATH_IMAGE014
(ii) a The cumulative probability in the ordinate is calculated by a computer
Figure 158122DEST_PATH_IMAGE015
The corresponding temperature value is recorded as the standard solar heat task temperature
Figure 126078DEST_PATH_IMAGE016
The cumulative probability in the ordinate is calculated by a computer
Figure 222210DEST_PATH_IMAGE017
The corresponding temperature value is recorded as the temperature of the hot day heat task
Figure 933814DEST_PATH_IMAGE018
；
Step 402, using a computer to scale the ratio
Figure 799002DEST_PATH_IMAGE019
Cold weather and hot task temperature of
Figure 937859DEST_PATH_IMAGE020
Ratio of
Figure 838731DEST_PATH_IMAGE021
Standard day heat task temperature of
Figure 88447DEST_PATH_IMAGE022
And ratio of
Figure 73721DEST_PATH_IMAGE023
Hot day heat task temperature of
Figure 383479DEST_PATH_IMAGE024
As a load spectrum for an aircraft thermal fatigue performance test.
The method for determining the thermal task proportion and the temperature value of the civil aircraft thermal fatigue load spectrum is characterized by comprising the following steps of: step 103 is implemented by using a computer pair
Figure 454203DEST_PATH_IMAGE025
Frame airplane
Figure 507610DEST_PATH_IMAGE026
Carrying out median processing on the corresponding aviation altitude temperatures at each sampling moment to obtain a temperature data set of the cruise state of the airplane, wherein the specific process is as follows:
step 1031 to
Figure 409707DEST_PATH_IMAGE027
Frame airplane
Figure 890367DEST_PATH_IMAGE026
The altitude temperature corresponding to each sampling moment is from small to smallIn large order and numbered sequentially as 1,.,
Figure 182808DEST_PATH_IMAGE028
to be connected to
Figure 39906DEST_PATH_IMAGE029
1 st high temperature of the plane
Figure 734192DEST_PATH_IMAGE028
The altitude temperature is respectively recorded as
Figure 385753DEST_PATH_IMAGE030
，...，
Figure 244119DEST_PATH_IMAGE031
(ii) a Wherein the content of the first and second substances,
Figure 639328DEST_PATH_IMAGE028
not more than
Figure 188121DEST_PATH_IMAGE026
；
Step 1032, when
Figure 276163DEST_PATH_IMAGE028
When the number is odd, according to the formula
Figure 543196DEST_PATH_IMAGE032
To obtain the first
Figure 742096DEST_PATH_IMAGE033
Temperature value of cruise state of gantry crane
Figure 207713DEST_PATH_IMAGE034
(ii) a When in use
Figure 466656DEST_PATH_IMAGE028
When the number is even, according to the formula
Figure 220985DEST_PATH_IMAGE035
Of 1 at
Figure 957997DEST_PATH_IMAGE033
Temperature value of cruise state of gantry crane
Figure 481382DEST_PATH_IMAGE034
(ii) a Wherein the content of the first and second substances,
Figure 911227DEST_PATH_IMAGE036
represents a rounding down operation;
step 1033, repeating step 1031 to step 1032 for a plurality of times to obtain the second
Figure 198857DEST_PATH_IMAGE037
Temperature value of cruise state of gantry crane
Figure 739560DEST_PATH_IMAGE038
(ii) a Wherein, the 1 st airplane is up to the first
Figure 383031DEST_PATH_IMAGE037
The flight time of the gantry aircraft covers a 12 month period of the year;
1034, adopting a computer to measure the temperature value of the 1 st airplane in the cruising state
Figure 718197DEST_PATH_IMAGE039
,., th
Figure 447119DEST_PATH_IMAGE040
Temperature value of cruise state of gantry crane
Figure 525934DEST_PATH_IMAGE041
Recorded as a temperature data set.
The method for determining the thermal task proportion and the temperature value of the civil aircraft thermal fatigue load spectrum is characterized by comprising the following steps of: in the second step, a computer is adopted to carry out statistical analysis on the temperature data set of the aircraft cruising state, and a cumulative distribution curve chart is obtained, and the specific process is as follows:
step 201, calculating the mean value and the variance of the temperature data set of the aircraft in the cruising state by adopting a computer to obtainTo a mean value corresponding to the temperature data set
Figure 86228DEST_PATH_IMAGE042
Sum variance
Figure 592296DEST_PATH_IMAGE043
；
Step 202, establishing a two-dimensional rectangular coordinate system by using a computer and taking the temperature value as a horizontal coordinate and the accumulated probability value as a vertical coordinate; wherein, the maximum temperature value of a two-dimensional rectangular coordinate system is set
Figure 808513DEST_PATH_IMAGE044
DEG C and minimum temperature value
Figure 691019DEST_PATH_IMAGE045
The group spacing is 10 ℃;
step 203, adopting a computer to calculate according to a formula
Figure 43503DEST_PATH_IMAGE046
To obtain a cumulative distribution function
Figure 986051DEST_PATH_IMAGE047
(ii) a Wherein the content of the first and second substances,
Figure 237035DEST_PATH_IMAGE048
it is meant that the random variable is,
Figure 657652DEST_PATH_IMAGE049
is shown at
Figure 130221DEST_PATH_IMAGE050
～
Figure 978092DEST_PATH_IMAGE051
Any real number in between;
step 204, adopting a computer to calculate the cumulative distribution function
Figure 903322DEST_PATH_IMAGE052
Drawn in a two-dimensional rectangular coordinate systemAnd (5) obtaining a cumulative distribution curve graph.
Compared with the prior art, the invention has the following advantages:
1. the method for determining the thermal task proportion and the temperature value of the civil aircraft thermal fatigue load spectrum is simple in steps, convenient to implement and easy and convenient to operate, and ensures that the thermal task temperatures and the thermal task proportions of the cold day, the standard day and the hot day are obtained when the aircraft is in a cruising state.
2. The method for determining the thermal task proportion and the temperature value of the civil aircraft thermal fatigue load spectrum has good use effect, firstly obtains the temperature data when each aircraft on an airline is in a cruising state, secondly performs statistical analysis on the temperature data set of the aircraft in the cruising state, and then determines the thermal task proportion in the thermal fatigue performance test and the thermal task temperature in the thermal fatigue performance test, thereby being convenient for further obtaining the load spectrum of the aircraft thermal fatigue performance test and being convenient for the aircraft thermal fatigue performance test.
3. In the process of acquiring temperature data when each aircraft on the airline is in a cruising state, the temperature data is acquired through the temperature acquisition module
Figure 127630DEST_PATH_IMAGE053
The plane flies along a preset route, and
Figure 517023DEST_PATH_IMAGE053
the navigation time of the overhead aircraft flying along the preset air route covers 12 months in one year, so that the temperature data set of the aircraft cruising state is wide in acquisition range.
In conclusion, the method has simple steps and reasonable design, obtains the hot task temperatures and the hot task proportions of the cold day, the standard day and the hot day when the aircraft is in the cruising state, and is convenient for developing the design of researching the load spectrum of the civil aircraft mixed structure thermal fatigue performance.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a flow chart of a method for determining a thermal task proportion and a temperature value of a civil aircraft thermal fatigue load spectrum.
Fig. 2 is a graph of the cumulative distribution of the present invention.
Fig. 3 is a graphical representation of a cumulative distribution plot of the present invention after linear fitting.
Detailed Description
A method for determining a thermal duty ratio and a temperature value of a civil aircraft thermal fatigue load spectrum as shown in fig. 1, the method comprising the steps of:
the method comprises the following steps of firstly, acquiring temperature data when each aircraft on a route is in a cruising state:
step 101, setting
Figure 801374DEST_PATH_IMAGE001
The plane flies along a preset route; wherein each airplane is respectively provided with a temperature sensor
Figure 213901DEST_PATH_IMAGE002
The temperature sensor carried on the overhead plane is recorded as
Figure 976321DEST_PATH_IMAGE003
A temperature sensor is arranged on the base plate, and the temperature sensor,
Figure 157903DEST_PATH_IMAGE003
and
Figure 613155DEST_PATH_IMAGE001
are all positive integers, and
Figure 824563DEST_PATH_IMAGE004
；
step 102, in the second step
Figure 390673DEST_PATH_IMAGE002
In the process that the plane flies along a preset air route and is in a cruising state, the first step
Figure 426762DEST_PATH_IMAGE002
The temperature sensor detects the flight altitude temperature according to the set sampling interval to obtain the second
Figure 52916DEST_PATH_IMAGE002
Setting the corresponding flight altitude temperature of each sampling moment of the plane; wherein the total number of sampling time is
Figure 440035DEST_PATH_IMAGE005
And is and
Figure 544257DEST_PATH_IMAGE005
is a positive integer;
step 103, adopting a computer pair
Figure 700432DEST_PATH_IMAGE001
Frame airplane
Figure 559803DEST_PATH_IMAGE005
Carrying out median processing on the corresponding aviation altitude temperatures at each sampling moment to obtain a temperature data set of the cruise state of the airplane;
step two, statistical analysis of the temperature data set of the aircraft cruise state:
carrying out statistical analysis on the temperature data set of the aircraft cruising state by adopting a computer, and obtaining a cumulative distribution curve chart; the abscissa of the cumulative distribution curve graph is a temperature value, and the ordinate of the cumulative distribution curve graph is a cumulative probability value;
step three, determining the hot task proportion in the thermal fatigue performance test:
step 301, performing linear fitting on the cumulative distribution curve graph by using MATLAB software by using a computer to obtain a first straight line segment, a second straight line segment and a third straight line segment in sequence; the first straight line section is located on a negative half shaft of an abscissa, and the third straight line section is located on a positive half shaft of the abscissa;
step 302, using a computer to make a vertical coordinate mark corresponding to the intersection point of the first straight line segment and the second straight line segment as a first cumulative probability value
Figure 168639DEST_PATH_IMAGE006
Marking the vertical coordinate mark corresponding to the intersection point of the third straight-line segment and the second straight-line segment as a second accumulative probability value
Figure 342132DEST_PATH_IMAGE007
(ii) a Wherein the content of the first and second substances,
Figure 352813DEST_PATH_IMAGE007
is greater than
Figure 320769DEST_PATH_IMAGE006
;
Step 303, using a computer to calculate the first cumulative probability value
Figure 416901DEST_PATH_IMAGE006
Recording the ratio of cold day tasks
Figure 675975DEST_PATH_IMAGE008
Will be
Figure 806742DEST_PATH_IMAGE009
The probability value of (D) is recorded as the standard daily task proportion
Figure 945599DEST_PATH_IMAGE010
Will be
Figure 529028DEST_PATH_IMAGE054
The probability value of is recorded as the hot day task proportion
Figure 778743DEST_PATH_IMAGE012
；
Step four, determining the hot task temperature in the thermal fatigue performance test:
step 401, using a computer to accumulate the probability in the ordinate as
Figure 764017DEST_PATH_IMAGE013
The corresponding temperature value is recorded as the temperature of the cold and hot tasks
Figure 136092DEST_PATH_IMAGE014
(ii) a The cumulative probability in the ordinate is calculated by a computer
Figure 206816DEST_PATH_IMAGE055
Corresponding temperatureThe value is recorded as the standard day heat task temperature
Figure 260223DEST_PATH_IMAGE016
The cumulative probability in the ordinate is calculated by a computer
Figure 100003DEST_PATH_IMAGE056
The corresponding temperature value is recorded as the temperature of the hot day heat task
Figure 580663DEST_PATH_IMAGE018
；
Step 402, using a computer to scale the ratio
Figure 873104DEST_PATH_IMAGE019
Cold weather and hot task temperature of
Figure 41786DEST_PATH_IMAGE020
Ratio of
Figure 736073DEST_PATH_IMAGE021
Standard day heat task temperature of
Figure 387634DEST_PATH_IMAGE022
And ratio of
Figure 432950DEST_PATH_IMAGE023
Hot day heat task temperature of
Figure 828160DEST_PATH_IMAGE024
As a load spectrum for an aircraft thermal fatigue performance test.
In this embodiment, step 103 is performed by using a computer pair
Figure 376953DEST_PATH_IMAGE057
Frame airplane
Figure 464994DEST_PATH_IMAGE058
Carrying out median processing on the corresponding aviation altitude temperatures at each sampling moment to obtain a temperature data set of the cruise state of the airplane, wherein the specific process is as follows:
step 1031 to
Figure 794344DEST_PATH_IMAGE027
Frame airplane
Figure 727665DEST_PATH_IMAGE026
The corresponding navigational temperature of each sampling moment is sequenced from small to large and is numbered as 1 in sequence,
Figure 396544DEST_PATH_IMAGE028
to be connected to
Figure 655487DEST_PATH_IMAGE029
1 st high temperature of the plane
Figure 144237DEST_PATH_IMAGE028
The altitude temperature is respectively recorded as
Figure 146828DEST_PATH_IMAGE030
，...，
Figure 483263DEST_PATH_IMAGE031
(ii) a Wherein the content of the first and second substances,
Figure 647528DEST_PATH_IMAGE028
not more than
Figure 889154DEST_PATH_IMAGE026
；
Step 1032, when
Figure 429856DEST_PATH_IMAGE028
When the number is odd, according to the formula
Figure 807748DEST_PATH_IMAGE059
To obtain the first
Figure 408494DEST_PATH_IMAGE033
Temperature value of cruise state of gantry crane
Figure 934153DEST_PATH_IMAGE034
(ii) a When in use
Figure 278547DEST_PATH_IMAGE028
When the number is even, according to the formula
Figure 776524DEST_PATH_IMAGE060
Of 1 at
Figure 282592DEST_PATH_IMAGE033
Temperature value of cruise state of gantry crane
Figure 498809DEST_PATH_IMAGE034
(ii) a Wherein the content of the first and second substances,
Figure 381315DEST_PATH_IMAGE036
represents a rounding down operation;
step 1033, repeating step 1031 to step 1032 for a plurality of times to obtain the second
Figure 62961DEST_PATH_IMAGE037
Temperature value of cruise state of gantry crane
Figure 739930DEST_PATH_IMAGE038
(ii) a Wherein, the 1 st airplane is up to the first
Figure 177865DEST_PATH_IMAGE037
The flight time of the gantry aircraft covers a 12 month period of the year;
1034, adopting a computer to measure the temperature value of the 1 st airplane in the cruising state
Figure 864061DEST_PATH_IMAGE039
,., th
Figure 133368DEST_PATH_IMAGE040
Temperature value of cruise state of gantry crane
Figure 246818DEST_PATH_IMAGE041
Recorded as a temperature data set.
In this embodiment, in the second step, a computer is used to perform statistical analysis on the temperature data set of the aircraft cruising state, and a cumulative distribution curve chart is obtained, which specifically includes the following processes:
step 201, calculating the mean value and the variance of the temperature data set of the aircraft in the cruising state by adopting a computer to obtain the mean value corresponding to the temperature data set
Figure 172049DEST_PATH_IMAGE042
Sum variance
Figure 396357DEST_PATH_IMAGE043
；
Step 202, establishing a two-dimensional rectangular coordinate system by using a computer and taking the temperature value as a horizontal coordinate and the accumulated probability value as a vertical coordinate; wherein, the maximum temperature value of a two-dimensional rectangular coordinate system is set
Figure 723433DEST_PATH_IMAGE044
DEG C and minimum temperature value
Figure 7784DEST_PATH_IMAGE045
The group spacing is 10 ℃;
step 203, adopting a computer to calculate according to a formula
Figure 967780DEST_PATH_IMAGE046
To obtain a cumulative distribution function
Figure 995779DEST_PATH_IMAGE047
(ii) a Wherein the content of the first and second substances,
Figure 177362DEST_PATH_IMAGE048
it is meant that the random variable is,
Figure 632614DEST_PATH_IMAGE049
is shown at
Figure 532437DEST_PATH_IMAGE050
～
Figure 98547DEST_PATH_IMAGE051
Any real number in between;
step 204, adopting a computer to calculate the cumulative distribution function
Figure 196953DEST_PATH_IMAGE052
And drawing in a two-dimensional rectangular coordinate system to obtain a cumulative distribution curve chart.
In this embodiment, during the in-service use, carry out the thermal fatigue performance test to the aircraft according to the load spectrum that obtains, be convenient for and then judge whether aircraft mixing mechanism takes place to damage.
In this embodiment, as shown in fig. 2, a cumulative distribution curve obtained through the second step is shown; the abscissa of the cumulative distribution curve graph is a temperature value, and the ordinate of the cumulative distribution curve graph is a cumulative probability value.
In this embodiment, as shown in fig. 3, the first straight line segment, the second straight line segment and the third straight line segment obtained through the second step are shown in the figure, and the obtained first straight line segment, the second straight line segment and the third straight line segment are obtained
Figure 823107DEST_PATH_IMAGE006
Is 12.5 percent of the total weight of the mixture,
Figure 944647DEST_PATH_IMAGE061
the content was 87.5%.
In this embodiment, the median is obtained in step 1032
Figure 314448DEST_PATH_IMAGE062
Temperature value of cruise state of gantry crane
Figure 470623DEST_PATH_IMAGE063
And the accuracy of acquiring the temperature data is improved.
In this embodiment, during the temperature data acquisition process when each aircraft on the airline is in the cruising state, the temperature data acquisition process is performed by
Figure 267678DEST_PATH_IMAGE064
The plane flies along a preset route, and
Figure 188098DEST_PATH_IMAGE065
the navigation time of the overhead aircraft flying along the preset air route covers 12 months in one year, so that the temperature data set of the aircraft cruising state is wide in acquisition range. In conclusion, the method has simple steps and reasonable design, obtains the hot task temperatures and the hot task proportions of the cold day, the standard day and the hot day when the aircraft is in the cruising state, and is convenient for developing the design of researching the load spectrum of the civil aircraft mixed structure thermal fatigue performance.
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 (3)

1. A method for determining the thermal task proportion and the temperature value of a civil aircraft thermal fatigue load spectrum is characterized by comprising the following steps:
the method comprises the following steps of firstly, acquiring temperature data when each aircraft on a route is in a cruising state:
step 101, setting
Figure 605809DEST_PATH_IMAGE001
The plane flies along a preset route; wherein each airplane is respectively provided with a temperature sensor
Figure 796750DEST_PATH_IMAGE002
The temperature sensor carried on the overhead plane is recorded as
Figure 397496DEST_PATH_IMAGE003
A temperature sensor is arranged on the base plate, and the temperature sensor,
Figure 860838DEST_PATH_IMAGE003
and
Figure 205232DEST_PATH_IMAGE001
are all positive integers, and
Figure 437630DEST_PATH_IMAGE004
；
step 102, in the second step
Figure 271594DEST_PATH_IMAGE002
In the process that the plane flies along a preset air route and is in a cruising state, the first step
Figure 222232DEST_PATH_IMAGE002
The temperature sensor detects the flight altitude temperature according to the set sampling interval to obtain the second
Figure 104738DEST_PATH_IMAGE002
Setting the corresponding flight altitude temperature of each sampling moment of the plane; wherein the total number of sampling time is
Figure 457222DEST_PATH_IMAGE005
And is and
Figure 399770DEST_PATH_IMAGE005
is a positive integer;
step 103, adopting a computer pair
Figure 837704DEST_PATH_IMAGE001
Frame airplane
Figure 835485DEST_PATH_IMAGE005
Carrying out median processing on the corresponding aviation altitude temperatures at each sampling moment to obtain a temperature data set of the cruise state of the airplane;
step two, statistical analysis of the temperature data set of the aircraft cruise state:
carrying out statistical analysis on the temperature data set of the aircraft cruising state by adopting a computer, and obtaining a cumulative distribution curve chart; the abscissa of the cumulative distribution curve graph is a temperature value, and the ordinate of the cumulative distribution curve graph is a cumulative probability value;
step three, determining the hot task proportion in the thermal fatigue performance test:
step 301, performing linear fitting on the cumulative distribution curve graph by using MATLAB software by using a computer to obtain a first straight line segment, a second straight line segment and a third straight line segment in sequence; the first straight line section is located on a negative half shaft of an abscissa, and the third straight line section is located on a positive half shaft of the abscissa;
step 302, using a computer to make a vertical coordinate mark corresponding to the intersection point of the first straight line segment and the second straight line segment as a first cumulative probability value
Figure 42476DEST_PATH_IMAGE006
Marking the vertical coordinate mark corresponding to the intersection point of the third straight-line segment and the second straight-line segment as a second accumulative probability value
Figure 155925DEST_PATH_IMAGE007
(ii) a Wherein the content of the first and second substances,
Figure 81156DEST_PATH_IMAGE007
is greater than
Figure 305464DEST_PATH_IMAGE006
;
Step 303, using a computer to calculate the first cumulative probability value
Figure 632540DEST_PATH_IMAGE006
Recording the ratio of cold day tasks
Figure 713628DEST_PATH_IMAGE008
Will be
Figure 126155DEST_PATH_IMAGE009
The probability value of (D) is recorded as the standard daily task proportion
Figure 154154DEST_PATH_IMAGE010
Will be
Figure 335737DEST_PATH_IMAGE011
The probability value of (D) is recorded as the hot dayTask proportion
Figure 790989DEST_PATH_IMAGE012
；
Step four, determining the hot task temperature in the thermal fatigue performance test:
step 401, using a computer to accumulate the probability in the ordinate as
Figure 425232DEST_PATH_IMAGE013
The corresponding temperature value is recorded as the temperature of the cold and hot tasks
Figure 804392DEST_PATH_IMAGE014
(ii) a The cumulative probability in the ordinate is calculated by a computer
Figure 106061DEST_PATH_IMAGE015
The corresponding temperature value is recorded as the standard solar heat task temperature
Figure 732214DEST_PATH_IMAGE016
The cumulative probability in the ordinate is calculated by a computer
Figure 853754DEST_PATH_IMAGE017
The corresponding temperature value is recorded as the temperature of the hot day heat task
Figure 223555DEST_PATH_IMAGE018
；
Step 402, using a computer to scale the ratio
Figure 379730DEST_PATH_IMAGE019
Cold weather and hot task temperature of
Figure 239102DEST_PATH_IMAGE020
Ratio of
Figure 847938DEST_PATH_IMAGE021
Standard day heat task temperature of
Figure 755851DEST_PATH_IMAGE022
And ratio of
Figure 766532DEST_PATH_IMAGE023
Hot day heat task temperature of
Figure 734488DEST_PATH_IMAGE024
As a load spectrum for an aircraft thermal fatigue performance test.
2. The method for determining the thermal mission ratio and the temperature value of the civil aircraft thermal fatigue load spectrum according to claim 1, wherein: step 103 is implemented by using a computer pair
Figure 830620DEST_PATH_IMAGE025
Frame airplane
Figure 871387DEST_PATH_IMAGE026
Carrying out median processing on the corresponding aviation altitude temperatures at each sampling moment to obtain a temperature data set of the cruise state of the airplane, wherein the specific process is as follows:
step 1031 to
Figure 736575DEST_PATH_IMAGE027
Frame airplane
Figure 875432DEST_PATH_IMAGE028
The corresponding navigational temperature of each sampling moment is sequenced from small to large and is numbered as 1 in sequence,
Figure 458860DEST_PATH_IMAGE029
to be connected to
Figure 974155DEST_PATH_IMAGE030
1 st high temperature of the plane
Figure 756166DEST_PATH_IMAGE029
The altitude temperature is respectively recorded as
Figure 65925DEST_PATH_IMAGE031
，...，
Figure 136649DEST_PATH_IMAGE032
(ii) a Wherein the content of the first and second substances,
Figure 190056DEST_PATH_IMAGE029
not more than
Figure 29836DEST_PATH_IMAGE028
；
Step 1032, when
Figure 510496DEST_PATH_IMAGE029
When the number is odd, according to the formula
Figure 68516DEST_PATH_IMAGE033
To obtain the first
Figure 473083DEST_PATH_IMAGE034
Temperature value of cruise state of gantry crane
Figure 167370DEST_PATH_IMAGE035
(ii) a When in use
Figure 84510DEST_PATH_IMAGE029
When the number is even, according to the formula
Figure 864248DEST_PATH_IMAGE036
Of 1 at
Figure 259457DEST_PATH_IMAGE034
Temperature value of cruise state of gantry crane
Figure 73829DEST_PATH_IMAGE035
(ii) a Wherein the content of the first and second substances,
Figure 958609DEST_PATH_IMAGE037
represents a rounding down operation;
step 1033, repeating step 1031 to step 1032 for a plurality of times to obtain the second
Figure 225642DEST_PATH_IMAGE038
Temperature value of cruise state of gantry crane
Figure 424542DEST_PATH_IMAGE039
(ii) a Wherein, the 1 st airplane is up to the first
Figure 93421DEST_PATH_IMAGE038
The flight time of the gantry aircraft covers a 12 month period of the year;
1034, adopting a computer to measure the temperature value of the 1 st airplane in the cruising state
Figure 86784DEST_PATH_IMAGE040
,., th
Figure 841114DEST_PATH_IMAGE041
Temperature value of cruise state of gantry crane
Figure 889710DEST_PATH_IMAGE042
Recorded as a temperature data set.
3. The method for determining the thermal mission ratio and the temperature value of the civil aircraft thermal fatigue load spectrum according to claim 1, wherein: in the second step, a computer is adopted to carry out statistical analysis on the temperature data set of the aircraft cruising state, and a cumulative distribution curve chart is obtained, and the specific process is as follows:
step 201, calculating the mean value and the variance of the temperature data set of the aircraft in the cruising state by adopting a computer to obtain the mean value corresponding to the temperature data set
Figure 413095DEST_PATH_IMAGE043
Sum variance
Figure 842940DEST_PATH_IMAGE044
；
Step 202, establishing a two-dimensional rectangular coordinate system by using a computer and taking the temperature value as a horizontal coordinate and the accumulated probability value as a vertical coordinate; wherein, the maximum temperature value of a two-dimensional rectangular coordinate system is set
Figure 84565DEST_PATH_IMAGE045
DEG C and minimum temperature value
Figure 359689DEST_PATH_IMAGE046
The group spacing is 10 ℃;
step 203, adopting a computer to calculate according to a formula
Figure 3160DEST_PATH_IMAGE047
To obtain a cumulative distribution function
Figure 400643DEST_PATH_IMAGE048
(ii) a Wherein the content of the first and second substances,
Figure 129565DEST_PATH_IMAGE049
it is meant that the random variable is,
Figure 208379DEST_PATH_IMAGE050
is shown at
Figure 706356DEST_PATH_IMAGE051
～
Figure 478003DEST_PATH_IMAGE052
Any real number in between;
step 204, adopting a computer to calculate the cumulative distribution function
Figure 428642DEST_PATH_IMAGE053
And drawing in a two-dimensional rectangular coordinate system to obtain a cumulative distribution curve chart.
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