CN103984815A - Multi-type information representative landing load spectrum compilation method - Google Patents
Multi-type information representative landing load spectrum compilation method Download PDFInfo
- Publication number
- CN103984815A CN103984815A CN201410198422.4A CN201410198422A CN103984815A CN 103984815 A CN103984815 A CN 103984815A CN 201410198422 A CN201410198422 A CN 201410198422A CN 103984815 A CN103984815 A CN 103984815A
- Authority
- CN
- China
- Prior art keywords
- flight
- representative
- loading spectrum
- data
- subject
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Other Investigation Or Analysis Of Materials By Electrical Means (AREA)
Abstract
The invention belongs to the field of fatigue, and relates to a multi-type information representative landing load spectrum compilation method. The method is characterized by comprising the following steps: determining a typical use mission profile; performing load spectrum flight test; performing statistical analysis on test flight data of the load spectrum; performing statistical analysis on outfield flight data; compiling flight-by-flight load spectrum. According to the method, the defects that a large amount of information loses in a data processing process, the compiled load spectrum can only represent the flight using situation of an individual aircraft and the like in the conventional representative landing load spectrum compilation technology are overcome, so that the compiled load spectrum reflects the actual flight using situation of the aircraft more really; therefore, the accuracy and the reliability of the analysis and the assessment of the service life are greatly improved.
Description
Technical field
The invention belongs to tired field, relate to a kind of many information and represent the loading spectrum preparation method of rising and falling.
Background technology
Domestic carrying out in high power-driven plane actual measurement loading spectrum compilation process, the representative methods of rising and falling that adopt more.This method is just used the concept in life-span from the beginning of compiling spectrum, find out the rising and falling of actual measurement section object median life that meets mathematical statistics concept by calculating, not only overcome averaging spectrum and can not consider the shortcoming of load sequence and the load position impact on structural life-time, also improved the reliability of determining the longevity.But be that representative is risen and fallen due to what compile that spectrum adopts, nature can lose some useful real measured datas, particularly, when actual measurement is risen and fallen when less, even if full choosing is surveyed rises and falls, and is also difficult to represent the service condition of a whole group of planes.Many information represents the loading spectrum preparation method of rising and falling, rise and fall on method basis in original representative, introduce outfield aircraft practical flight data, greatly increase and compile spectrum information, and selected representative is risen and fallen and carried out the method for necessary correction, make worked out loading spectrum can truly reflect the practical flight service condition of aircraft.
Summary of the invention
The object of the invention is:
The establishment of loading spectrum is to carry out the prerequisite of durability analysis and evaluation and basis, the present invention rises and falls on loading spectrum preparation method basis in original representative, the many information that propose a kind of high power-driven plane represent the loading spectrum preparation method of rising and falling, and make worked out loading spectrum can truly reflect the practical flight service condition of aircraft.
Technical scheme of the present invention is:
The concrete steps that application the method is carried out loading spectrum establishment are as follows:
The first, determine that typical case uses mission profile
According to the flight training subject in flying curriculum, determine that the typical case of aircraft uses mission profile.Typical case uses mission profile to determine by following principle:
A) respectively fly character and the content of the performed task of subject of same mission profile is substantially close;
B) the each flight of same mission profile section object flying height, speed, overload variation range and order are substantially close;
C) respectively fly time of subject flight of same mission profile is substantially close.
Table 1 typical case uses mission profile
| Sequence number | Task type | The number that rises and falls flies | Pilot time number often rises and falls | Total pilot time number |
| ? | ? | ? | ? | ? |
| ? | ? | ? | ? | ? |
| ? | ? | ? | ? | ? |
| ? | ? | ? | ? | ? |
| ? | ? | ? | ? | ? |
| ∑ | ? | ? | ? | ? |
The second, carry out loading spectrum flight actual measurement
Use mission profile to carry out loading spectrum flight actual measurement by typical case.It is inappropriate that each typical case's flight subject only carries out flight actual measurement, and this can not reflect real flight situation, has reduced accuracy and the reliability of measured data.Therefore, each typical flight section object repeats to survey number of times and should keep more than 5 times.As the restriction of receiving cycle and funds, for subjects such as the not too large formation of flight overload, instrument, course lines, multiplicity can be reduced to more than 3 times.
The 3rd, the statistical study of loading spectrum actual measurement flying quality
Each actual measurement flying quality is carried out to filtering, rain-flow counting, and carry out equivalent damage by formula (1) and calculate.
In formula:
for the equivalent normal g-load calculating according to measured data; M is the index of S-N Curve, generally gets 4～6; N
ifor the frequency of equivalent normal g-loads at different levels.
The 4th, outfield flying quality statistical study
By formula (1), the flight data in outfield is carried out to equivalent damage and calculate, merge, sort by typical case's subject that flies.The validity of application mathematical statistics verification msg:
D) give up maximum normal g-load in flight data and be less than 2 rise and fall;
E) remaining data are undertaken unreasonable giving up of rising and falling by " 2 σ criterion " in mathematical statistics, give up equivalent damage logarithm value rising and falling outside (u-2 σ, u+2 σ) interval;
F) the average equivalent that calculates valid data damages, and the average frequency of adding up normal g-loads at different levels.
Wherein u is the mean value of equivalent damage logarithm, and σ is logarithm standard deviation.
Representative for ensureing the outfield flying quality of statistics, every kind of flight section destination data will exceed 100 times rises and falls, much larger than more than 5 times actual measurement loading spectrum data.
The 5th, what representative was risen and fallen choosing and adjusting
In each flight subject measured data, choose the flight approaching with outfield average damage (instead of the damage of the average equivalent of measured data) and rise and fall, rise and fall as representative, and the data of representative being risen and fallen by following principle are carried out necessary adjustment:
C) the equivalent impairment value that representative is risen and fallen and the error of outfield assembly average are controlled in 5%;
The average result of the frequency of the normal g-loads at different levels that d) representative is risen and fallen and outfield statistics is suitable, and particularly the frequency of larger overload should be identical with statistics as much as possible.
Above-mentioned two principles are in course of adjustment and must meet simultaneously, this is also the many information representative most important technological innovation in loading spectrum preparation method of rising and falling, and can ensure that final representative rises to drop on equivalent damage and two aspects of the overload frequency at different levels meet aircraft practical flight service condition.
The 6th, establishment flies-continue-fly loading spectrum
The each flight section object representative of finally determining is risen and fallen and is used the flight number of times in mission profile to line up with random sequence by typical case, form fly-continue-fly loading spectrum.
Beneficial effect:
Many information represents the loading spectrum preparation method of rising and falling, having made up traditional representative rises and falls and compiles spectral technology and in data handling procedure, cause that bulk information is lost, the loading spectrum worked out only can represent the shortcomings such as indivedual aircraft flight service conditions, make worked out loading spectrum more truly reflect the practical flight service condition of aircraft, thereby greatly improve accuracy and the reliability of durability analysis and evaluation.
Brief description of the drawings
Fig. 1 overload moves in and out schematic diagram
Fig. 2 subject 1 represents the overload-time history curve rising and falling
Embodiment
Provided the application perfect information representative method of rising and falling and worked out the example of certain high power-driven plane loading spectrum below in conjunction with accompanying drawing.
The first, determine that according to the flying curriculum of this type aircraft typical case uses mission profile, totally 10 typical case's flight subjects.
Table 2 aircraft typical case uses mission profile
| Sequence number | Task type | The number that rises and falls flies | Pilot time number often rises and falls | Total pilot time number |
| 1 | Subject 1 | 4 | 1：30 | 6：00 |
| 2 | Subject 2 | 4 | 1：10 | 4：40 |
| 3 | Subject 3 | 4 | 1：10 | 4：40 |
| 4 | Subject 4 | 4 | 1：30 | 6：00 |
| 5 | Subject 5 | 4 | 1：30 | 6：00 |
| 6 | Subject 6 | 3 | 1：00 | 3：00 |
| 7 | Subject 7 | 3 | 1：00 | 3：00 |
| 8 | Subject 8 | 26 | 1：30 | 39：00 |
| 9 | Subject 9 | 2 | 1：30 | 3：00 |
| 10 | Subject 10 | 7 | 1：30 | 10：30 |
| ∑ | ? | 61 | ? | 86：50 |
The second, carry out loading spectrum flight actual measurement
Use mission profile to carry out loading spectrum flight actual measurement by typical case, for ensureing accuracy and the reliability of measured data, each typical section object is surveyed the number of times that rises and falls and is all exceeded 5 times, in table 3.
The each typical section of table 3 object is surveyed the number of times that rises and falls
| Sequence number | Task type | Survey the number of times that rises and falls |
| 1 | Subject 1 | 7 |
| 2 | Subject 2 | 7 |
| 3 | Subject 3 | 7 |
| 4 | Subject 4 | 9 |
| 5 | Subject 5 | 9 |
| 6 | Subject 6 | 9 |
| 7 | Subject 7 | 9 |
| 8 | Subject 8 | 9 |
| 9 | Subject 9 | 7 |
| 10 | Subject 10 | 7 |
| ∑ | ? | 80 |
The 3rd, the statistical study of loading spectrum actual measurement flying quality
Each actual measurement flight is risen and fallen and carried out the calculating of equivalent damage, the results are shown in Table 3.
The each typical section of table 3 object is surveyed the number of times that rises and falls
The 4th, outfield flying quality statistical study
Taking subject 8 as example, the equivalent damage of statistics outfield flying quality.
The outfield flying quality statistical study of table 4 subject 8
| Sequence number | Code name rises and falls | Equivalent damage | Equivalent damage logarithm value |
| 1 | 616044 | 39.46 | 1.5962 |
| 2 | 816044 | 73.41 | 1.8657 |
| 3 | 18281103 | 79.59 | 1.9009 |
| 4 | 213052 | 85.22 | 1.9305 |
| 5 | 04-290501 | 86.10 | 1.9350 |
| 6 | 18291104 | 89.02 | 1.9495 |
| 7 | 18281104 | 91.38 | 1.9608 |
| ...... | ? | ? | ? |
| 136 | 15130501 | 5236.09 | 3.7190 |
| 137 | 10030602 | 5839.21 | 3.7664 |
| 138 | 12050801 | 5880.92 | 3.7694 |
| 139 | 7030601 | 7211.17 | 3.8580 |
| 140 | 5130503 | 9754.89 | 3.9892 |
| 141 | 11130501 | 12107.16 | 4.0830 |
| 142 | 29210702 | 15131.30 | 4.1799 |
| Mean value | ? | ? | 2.8391 |
| Standard deviation | ? | ? | 0.45996 |
| u-2σ | ? | ? | 1.9192 |
| u+2σ | ? | ? | 3.7590 |
By " 2 σ criterion ", give up 1st～3 and 137～142 flying qualities.
The 5th, what representative was risen and fallen choosing and adjusting
The average damage of the field data of adding up by table 5 and table 6 and the average frequency of overloads at different levels, rise and fall and adjust representative, and the equivalent damage of adjustment the results are shown in Table 7.
What table 5 representative was risen and fallen chooses
| Sequence number | Task type | The impairment value that representative is risen and fallen | The average damage of field data | Error % |
| 1 | Subject 1 | 1345.8623 | 3020.5654 | -55.44 |
| 2 | Subject 2 | 2434.4116 | 3318.2355 | -26.64 |
| 3 | Subject 3 | 1892.0038 | 1753.8448 | 7.88 |
| 4 | Subject 4 | 13515.714 | 11038.7641 | 22.44 |
| 5 | Subject 5 | 4393.3621 | 4548.3464 | -3.41 |
| 6 | Subject 6 | 7953.7329 | 6774.9355 | 17.40 |
| 7 | Subject 7 | 10421.087 | 12401.2779 | -15.97 |
| 8 | Subject 8 | 772.4209 | 1044.4614 | -26.05 |
| 9 | Subject 9 | 325.1367 | 338.2100 | -3.87 |
| 10 | Subject 10 | 1850.3292 | 1910.9486 | -3.17 |
The fly average frequency of overloads at different levels of table 6 outfield
The equivalent impairment value that table 7 representative is risen and fallen after adjusting
| Sequence number | Task type | Equivalent impairment value after adjustment | The average damage of field data | Error % |
| 1 | Subject 1 | 3161.5097 | 3020.5654 | 4.67 |
| 2 | Subject 2 | 3441.7433 | 3318.2355 | 3.72 |
| 3 | Subject 3 | 1824.3603 | 1753.8448 | 4.02 |
| 4 | Subject 4 | 11518.2463 | 11038.7641 | 4.34 |
| 5 | Subject 5 | 4665.3832 | 4548.3464 | 2.57 |
| 6 | Subject 6 | 6792.0515 | 6774.9355 | 0.25 |
| 7 | Subject 7 | 13005.4617 | 12401.2779 | 4.87 |
| 8 | Subject 8 | 1088.8117 | 1044.4614 | 4.25 |
| 9 | Subject 9 | 340.3092 | 338.2100 | 0.62 |
| 10 | Subject 10 | 1968.6919 | 1910.9486 | 3.02 |
After Fig. 2 has provided and adjusted, subject 1 represents the overload-time history curve rising and falling.
The 6th, establishment flies-continue-fly loading spectrum
The representative random sequence of rising and falling after adjusting is lined up, form fly-continue-fly loading spectrum.In table 8, the digital number in table represents respectively flight subject 1～10.
Table 8 flies-continue-fly the order that applies of loading spectrum
Claims (3)
1. information more than represents the loading spectrum preparation method of rising and falling, and it is characterized in that, comprises following concrete steps:
The first, determine that typical case uses mission profile
According to the flight training subject in flying curriculum, determine that the typical case of aircraft uses mission profile;
The second, carry out loading spectrum flight actual measurement
Use mission profile to carry out loading spectrum flight actual measurement by typical case, each typical flight section object repeats to survey number of times and keeps more than 3 times;
The 3rd, the statistical study of loading spectrum actual measurement flying quality
Each actual measurement flying quality is carried out to filtering, rain-flow counting, and carry out equivalent damage by formula (1) and calculate;
In formula:
for the equivalent normal g-load calculating according to measured data; M is the index of S-N Curve, gets 4～6; N
ifor the frequency of equivalent normal g-loads at different levels;
The 4th, outfield flying quality statistical study
By formula (1), the flight data in outfield is carried out to equivalent damage and calculate, merge, sort by typical case's subject that flies;
The 5th, establishment flies-continue-fly loading spectrum
The each flight section object representative of finally determining is risen and fallen and is used the flight number of times in mission profile to line up with random sequence by typical case, form fly-continue-fly loading spectrum.
2. many information according to claim 1 represents the loading spectrum preparation method of rising and falling, and it is characterized in that, applies the validity of mathematical statistics verification msg in described the 4th step:
A) give up maximum normal g-load in flight data and be less than 2 rise and fall;
B) remaining data are undertaken unreasonable giving up of rising and falling by " 2 σ criterion " in mathematical statistics, give up equivalent damage logarithm value rising and falling outside (u-2 σ, u+2 σ) interval;
C) the average equivalent that calculates valid data damages, and the average frequency of adding up normal g-loads at different levels;
Wherein u is the mean value of equivalent damage logarithm, and σ is logarithm standard deviation,
Representative for ensureing the outfield flying quality of statistics, every kind of flight section destination data will exceed 100 times rises and falls, and is greater than above actual measurement loading spectrum data 5 times.
3. many information according to claim 1 represents the loading spectrum preparation method of rising and falling, and it is characterized in that, choosing with method of adjustment that representative is risen and fallen is:
In each flight subject measured data, choose and damage approaching flight with outfield average and rise and fall, rise and fall as representative, and the data of representative being risen and fallen by following principle are adjusted:
A) the equivalent impairment value that representative is risen and fallen and the error of outfield assembly average are controlled in 5%,
The frequency of the normal g-loads at different levels that b) representative is risen and fallen is consistent with the average result of outfield statistics, and the frequency of overload is identical with statistics;
Above-mentioned two principles are in course of adjustment and must meet simultaneously.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410198422.4A CN103984815A (en) | 2014-05-12 | 2014-05-12 | Multi-type information representative landing load spectrum compilation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410198422.4A CN103984815A (en) | 2014-05-12 | 2014-05-12 | Multi-type information representative landing load spectrum compilation method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103984815A true CN103984815A (en) | 2014-08-13 |
Family
ID=51276784
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410198422.4A Pending CN103984815A (en) | 2014-05-12 | 2014-05-12 | Multi-type information representative landing load spectrum compilation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103984815A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105468853A (en) * | 2015-11-26 | 2016-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft arresting hook load spectrum compilation method |
| CN105550446A (en) * | 2015-12-14 | 2016-05-04 | 中国航空工业集团公司成都飞机设计研究所 | Control plane skewness containing control plane load spectrum compilation method |
| CN105574247A (en) * | 2015-12-14 | 2016-05-11 | 南京航空航天大学 | Compilation method for general standard test load spectrum of aero-engine |
| CN106529094A (en) * | 2016-11-30 | 2017-03-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Typical flight action-based aircraft severe load spectrum compilation method |
| CN106777551A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter low cycle fatigue loading composes preparation method |
| CN110489914A (en) * | 2019-08-27 | 2019-11-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of durability calculation method equivalent based on stress damage |
| CN110705141A (en) * | 2019-08-30 | 2020-01-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Fatigue load spectrum determination method for external airplane accessory casing fixing device |
| CN110926976A (en) * | 2019-12-09 | 2020-03-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Evaluation method for service life gain after three-dimensional additive repair |
| CN112699478A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Universal aircraft wing test load spectrum compiling method |
| CN112749683A (en) * | 2021-01-27 | 2021-05-04 | 吉林大学 | Rain flow counting method capable of reserving load time sequence |
| CN118133571A (en) * | 2024-04-30 | 2024-06-04 | 北京航空航天大学 | Task type load spectrum compiling method for heavy equipment land transportation fatigue damage assessment |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102556365A (en) * | 2011-12-21 | 2012-07-11 | 西安航空制动科技有限公司 | Accelerated life test method of aircraft brake system |
| CN102680221A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test method for full-aircraft main operating system of aircraft |
| EP2560152A1 (en) * | 2011-08-15 | 2013-02-20 | Honeywell International Inc. | Aircraft vision system including a runway position indicator |
-
2014
- 2014-05-12 CN CN201410198422.4A patent/CN103984815A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2560152A1 (en) * | 2011-08-15 | 2013-02-20 | Honeywell International Inc. | Aircraft vision system including a runway position indicator |
| CN102556365A (en) * | 2011-12-21 | 2012-07-11 | 西安航空制动科技有限公司 | Accelerated life test method of aircraft brake system |
| CN102680221A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test method for full-aircraft main operating system of aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 陆华: "《全信息代表飞行起落疲劳载荷谱编制方法研究》", 《飞机设计》 * |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105468853A (en) * | 2015-11-26 | 2016-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft arresting hook load spectrum compilation method |
| CN105550446A (en) * | 2015-12-14 | 2016-05-04 | 中国航空工业集团公司成都飞机设计研究所 | Control plane skewness containing control plane load spectrum compilation method |
| CN105574247A (en) * | 2015-12-14 | 2016-05-11 | 南京航空航天大学 | Compilation method for general standard test load spectrum of aero-engine |
| CN105574247B (en) * | 2015-12-14 | 2018-07-24 | 南京航空航天大学 | A kind of aero-engine benchmark test loading spectrum preparation method |
| CN105550446B (en) * | 2015-12-14 | 2018-08-24 | 中国航空工业集团公司成都飞机设计研究所 | A kind of rudder face loading spectrum preparation method of the degree of bias containing rudder face |
| CN106777551A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter low cycle fatigue loading composes preparation method |
| CN106777551B (en) * | 2016-11-29 | 2020-02-21 | 中国直升机设计研究所 | Helicopter low-cycle fatigue load spectrum compilation method |
| CN106529094A (en) * | 2016-11-30 | 2017-03-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Typical flight action-based aircraft severe load spectrum compilation method |
| CN110489914B (en) * | 2019-08-27 | 2023-01-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Durability calculation method based on stress damage equivalence |
| CN110489914A (en) * | 2019-08-27 | 2019-11-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of durability calculation method equivalent based on stress damage |
| CN110705141A (en) * | 2019-08-30 | 2020-01-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Fatigue load spectrum determination method for external airplane accessory casing fixing device |
| CN110705141B (en) * | 2019-08-30 | 2023-06-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Fatigue load spectrum determining method for external aircraft accessory case fixing device |
| CN110926976A (en) * | 2019-12-09 | 2020-03-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Evaluation method for service life gain after three-dimensional additive repair |
| CN112699478A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Universal aircraft wing test load spectrum compiling method |
| CN112699478B (en) * | 2020-12-29 | 2022-10-11 | 中国航空工业集团公司西安飞机设计研究所 | Universal aircraft wing test load spectrum compiling method |
| CN112749683A (en) * | 2021-01-27 | 2021-05-04 | 吉林大学 | Rain flow counting method capable of reserving load time sequence |
| CN118133571A (en) * | 2024-04-30 | 2024-06-04 | 北京航空航天大学 | Task type load spectrum compiling method for heavy equipment land transportation fatigue damage assessment |
| CN118133571B (en) * | 2024-04-30 | 2024-07-05 | 北京航空航天大学 | Task type load spectrum compiling method for heavy equipment land transportation fatigue damage assessment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103984815A (en) | Multi-type information representative landing load spectrum compilation method | |
| CN105023195B (en) | Containing distributed photovoltaic evaluation method for distribution network reliability | |
| CN104061960B (en) | Pressure altitude parameter determination method on a kind of subsonic flight body | |
| CN105279691A (en) | Financial transaction detection method and equipment based on random forest model | |
| CN103646138A (en) | Time terminated acceleration acceptance sampling test optimum design method based on Bayesian theory | |
| CN115824545B (en) | Method and system for determining fatigue damage acceleration endurance test conditions of airborne equipment | |
| CN106920013A (en) | A kind of method of quality control of surface air temperature observational data | |
| CN103246821A (en) | Simulation-based multi-stress small sample accelerated life test scheme design optimization method | |
| CN112199793B (en) | Damage equivalent test spectrum optimization method for non-Gaussian load | |
| CN109252855B (en) | Method and device for determining final cumulative yield of gas well | |
| CN104778354A (en) | Method for evaluating storage life of regular sampling detection type products | |
| CN109376179A (en) | A kind of sample equilibrating method in data mining | |
| CN107798149B (en) | Aircraft maintainability assessment method | |
| CN109685334A (en) | A kind of new hydrological model simulation evaluation method based on Multiscale Theory | |
| CN115453064A (en) | Fine particle air pollution cause analysis method and system | |
| CN106599448B (en) | A kind of gear train Tolerance Optimization calculation method based on DYNAMIC RELIABILITY | |
| CN112800540B (en) | Aircraft engine load spectrum task segment modeling method based on Gaussian process regression | |
| CN104198998A (en) | Clustering treatment based CFAR (Constant False Alarm Rate) detection method under non-uniform background | |
| CN108830444A (en) | A kind of assessment of raob data and modification method and device | |
| CN108646688B (en) | A kind of process parameter optimizing analysis method based on recurrence learning | |
| CN104732049A (en) | Method for correcting hydrogen absorption performance curve of hydrogen absorption material | |
| US20150330317A1 (en) | Real-time vehicle data acquisition and analysis | |
| CN105550855A (en) | Undergraduate-oriented campus project and applicant mutual-matching system and method | |
| CN115688316A (en) | Multi-level reliability evaluation method for aircraft engine based on unit data recombination | |
| CN104281750A (en) | Service life distribution method suitable for bathtub-curve fault rates |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C53 | Correction of patent of invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Sun Cong Inventor after: Chen Liang Inventor after: Sui Fucheng Inventor after: Zhou Lijun Inventor before: Chen Liang Inventor before: Sui Fucheng Inventor before: Zhou Lijun |
|
| COR | Change of bibliographic data |
Free format text: CORRECT: INVENTOR; FROM: CHEN LIANG SUI FUCHENG ZHOU LIJUN TO: SUN CONG CHEN LIANG SUI FUCHENG ZHOU LIJUN |
|
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20140813 |
|
| RJ01 | Rejection of invention patent application after publication |