CN112700129A - Spare part analysis method based on aviation application - Google Patents
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Abstract
The invention belongs to the technical field of aviation, and discloses a spare part analysis method based on aviation application, which comprises the following steps: the method comprises the following steps: taking the target of spare part guarantee as a boundary condition; the boundary condition value is determined according to the spare part guarantee stage; step two: modeling an analysis object by taking all Line Replaceable Units (LRUs) as the analysis object, wherein the modeling content comprises: the model, name, product type, manufacturer, repairable or not, the number of single machines, reliability index, importance level and development state; step three: selecting a corresponding calculation model according to the product type and the repairability in the modeling content in the step two, and calculating the initial quantity requirement of the spare parts by using the boundary condition in the step one and the single machine quantity and reliability index in the step two; step four: and correcting the preliminary quantity requirement of the spare parts formed in the third step by using the product importance level and the development state in the modeling content in the second step, and compiling a final spare part list according to a correction result.
Description
Technical Field
The invention belongs to the technical field of aviation, and relates to a spare part analysis method based on aviation application.
Background
The spare parts are used for replacing the parts with faults or failures when the equipment is maintained, so that the equipment is restored to be in a good and usable state. And analyzing the equipment spare part requirements according to the work items after the equipment guarantee analysis standard specification and the process are analyzed by using and maintaining tasks. In the whole design process of the equipment, the equipment is already in the final stage of design, the equipment trial verification stage is often entered, the spare part requirement analysis performed in the stage can only be used after the equipment is sized and batched, and the spare part requirement in the trial verification stage lacks analysis support. The analysis result at this stage is used as the initial spare part requirement, so that on one hand, the reliability indexes are still different, and on the other hand, the theoretical calculation lacks the engineering support.
Disclosure of Invention
The invention provides a spare part analysis method based on aviation application, which is used for finally forming initial spare part requirements by determining an analysis object, modeling a product, primarily determining quantity requirements and correcting data.
A spare part analysis method based on aviation application comprises the following steps:
the method comprises the following steps: taking the target of spare part guarantee as a boundary condition; the boundary condition value is determined according to the spare part guarantee stage;
step two: modeling an analysis object by taking all Line Replaceable Units (LRUs) as the analysis object, wherein the modeling content comprises: the model, name, product type, manufacturer, repairable or not, the number of single machines, reliability index, importance level and development state;
step three: selecting a corresponding calculation model according to the product type and the repairability in the modeling content in the step two, and calculating the initial quantity requirement of the spare parts by using the boundary condition in the step one and the single machine quantity and reliability index in the step two;
step four: and correcting the preliminary quantity requirement of the spare parts formed in the third step by using the product importance level and the development state in the modeling content in the second step, and compiling a final spare part list according to a correction result.
Further, in the step one, the spare part securing stage includes: a test-flight phase, an initial guarantee period, and a desired period of time after the initial guarantee period.
Further, in step one, the boundary condition includes: ensuring the period, the turnover period of the fault part, the number of the cluster, the flight intensity in the period and the probability;
and when the spare part guarantee stage is a test flight stage, taking values of the boundary conditions according to a test flight working plan.
Furthermore, the model number, name, manufacturer, reliability index and development state in the modeling content in the second step should be consistent with the agreement/record book.
Further, the number of machines in the modeled contents of step two is the number of LRUs in the system, and if a certain LRU has a plurality of systems installed, the LRUs are listed according to the system.
Furthermore, the importance level in the modeling content in the second step is divided into three levels, namely level 1-influencing safety, level 2-influencing task and level 3-influencing economy;
the development states include: newly developed, improved and stored in shelf.
Further, in the fourth step, the preliminary quantity requirement of the spare parts is corrected by the following method:
if the importance level of the line replaceable unit LRU is 3 or the development state is a shelf, reducing the requirement of the initial quantity of spare parts of the LRU;
if the importance level of the LRU of the line replaceable unit is 1 level or the development state is newly developed, increasing the initial quantity requirement of the spare parts of the LRU or using the LRU as a preferential purchase item;
and (3) for the LRU with the requirement of 0 for the initial quantity of the spare parts in the third step, the requirement for the initial quantity of the spare parts of the LRU is corrected and confirmed by integrating the reliability index, the importance level, the development state and the engineering experience.
Further, in the fourth step, if the spare part guarantee stage in the first step is a trial flight stage, a trial flight spare part list is compiled according to a correction result in the third step;
and if the spare part guarantee stage in the step one is other stages, correcting the initial spare part quantity requirement according to the test flight spare part list and the spare part consumption during the test flight to compile the spare part list in the corresponding stage.
Advantageous effects
According to the spare part analysis method based on the aviation application, the initial spare part requirement is formed finally through determining an analysis object, modeling a product, primarily determining quantity requirements and correcting data. The satisfaction rate and the utilization rate of spare parts can be effectively improved.
Drawings
Fig. 1 is a schematic flow chart of a spare part analysis method based on aviation application.
Detailed Description
A spare part analysis method based on aviation application, as shown in fig. 1, includes the following steps:
step 1: the method comprises the following steps of (1) referring a target of spare part guarantee as a boundary condition, wherein the target mainly comprises a guarantee period, a fault part turnover period, a guarantee cluster number, flight intensity in the period, guarantee probability and the like; when the analysis of the test flight spare parts is carried out, the boundary conditions such as guarantee period and the like take values according to a test flight working plan; when the analysis of the test flight spare parts is not carried out, taking relevant parameters in an initial guarantee period or other specified time periods according to a spare part guarantee stage;
example (c): the section of description, namely boundary conditions of the test flight spare part analysis, is x years of a test flight period, x FH (mean turnover) of fault parts during the test flight period, x machines are put into the test flight, and each machine flies x FH (mean flight) every year and has a spare part guarantee probability x'. The 'test flight period x years' is a guarantee period, 'the mean turnover period of fault parts during test flight' is a turnover period of fault parts, 'the number of groups of machines in test flight is guaranteed,' the mean flight per year x FH 'of each machine is the flight intensity in the period, and the guarantee probability x' of spare parts is the guarantee probability of spare parts.
In the comprehensive protection and recommendation of a certain model, a description of a section, namely x years of an airplane guarantee period, x FH (mean turnover of faulty parts) in the guarantee period, x frames of airplanes deployed in a base station, x FH (mean flight per year) of each airplane and x parts guarantee probability is the boundary condition of initial parts analysis. The ' x years of the guarantee period of the airplane ' is the guarantee period, ' the mean turnover period of the fault parts in the guarantee period ' is the turnover period of the fault parts, ' x frames of the base-deployed airplanes ' is the number of guarantee clusters, ' the mean flying strength per year of each frame ' x FH ' is the flying strength in the period, and the guarantee probability x of the spare parts is the guarantee probability of the spare parts.
Step 2: and modeling an analysis object, wherein all external field replaceable units LRU of the whole machine are used as the analysis object, and the modeling content comprises model, name, belonging system, single machine number, manufacturer, reliability index, importance level, repairability, product type, development state, effectiveness and the like. Wherein the model, name, manufacturer, reliability index and development state should be consistent with the protocol/record book for easy purchase; the number of the single machines is the number of the LRU in the system, and if the LRUs installed in the multiple systems exist, the LRUs are respectively listed according to the systems; the importance level is divided according to three levels, the influence safety is level 1, the influence task is level 2, and the influence economy is level 3; the product types are divided according to three types, namely mechanical, electronic and electromechanical; validity is applicable for batch-to-batch; the development state is divided into three types, namely new development, improvement and shelf.
Example (c): LRU modeling information
And step 3: selecting an applicable calculation model according to the product type and the repairability in the modeling information in the step 2, calculating and preliminarily forming the requirement of the quantity of spare parts according to the national military standard or other relevant standards by using the boundary conditions in the step 1 and the quantity of single machines, reliability indexes and the like in the step 2; when the boundary condition is tested, the calculation result is the quantity requirement of the test flight spare parts, otherwise, the calculation result is the quantity requirement of the spare parts of other corresponding stages;
example (c): taking the example parameters in the step 2 as an example, according to the characteristics of electromechanical products and repairability, selecting a proper calculation model, bringing the calculation model into the boundary condition of the trial flight spare parts, calculating to obtain that the number of the trial flight spare parts is 3, bringing the calculation model into the boundary condition of the initial guarantee, and calculating to obtain that the number of the initial spare parts is 5.
And 4, step 4: correcting the preliminary quantity requirement formed in the step 3 by using the product importance level and the development state in the modeling information in the step 2, and reducing the quantity requirement as appropriate when the importance level is 3 or the development state is a shelf; when the importance level is 1 or the development state is newly researched, increasing the quantity demand or serving as a preferential purchasing project as required; for the spare parts which are calculated to be 0 in the step 3, the reliability index, the importance level, the development state, the engineering experience and the like are comprehensively corrected and confirmed; when the boundary condition is tested, the correction result is compiled into a test flight spare part list; otherwise, the test flight spare part list and the spare part consumption condition during the test flight are also used as reference items for correcting the calculation result in the step 3, and the correction result is compiled into the spare part list.
Example (c): taking the number requirement of the test flight spare parts calculated in the step 3 as an example, the importance level of the reversing valve is 3, the number requirement of the goods shelf products is reduced as appropriate, the number requirement of the test flight spare parts is modified from 3 to 1, and a test flight spare part list is as follows;
taking the initial spare part quantity requirement calculated in the step 3 as an example, the importance level of the reversing valve is 3, the requirement of the goods shelf product on the test flight spare part is 1, the fault during the test flight is low, the quantity requirement is reduced as appropriate, the initial spare part requirement is modified from 5 to 2, and the initial spare part list is as follows;
Claims (8)
1. a spare part analysis method based on aviation application is characterized by comprising the following steps: the method comprises the following steps:
the method comprises the following steps: taking the target of spare part guarantee as a boundary condition; the boundary condition value is determined according to the spare part guarantee stage;
step two: modeling an analysis object by taking all Line Replaceable Units (LRUs) as the analysis object, wherein the modeling content comprises: the model, name, product type, manufacturer, repairable or not, the number of single machines, reliability index, importance level and development state;
step three: selecting a corresponding calculation model according to the product type and the repairability in the modeling content in the step two, and calculating the initial quantity requirement of the spare parts by using the boundary condition in the step one and the single machine quantity and reliability index in the step two;
step four: and (4) correcting the preliminary quantity requirement of the spare parts formed in the step three by using the importance level and the development state in the modeling content in the step two, and compiling a final spare part list according to a correction result.
2. A spare part analysis method based on aeronautical applications according to claim 1, characterized in that: in the first step, the spare part securing stage includes: a test-flight phase, an initial guarantee period, and a desired period of time after the initial guarantee period.
3. A spare part analysis method based on aeronautical applications according to claim 2, characterized in that: in step one, the boundary condition includes: ensuring the period, the turnover period of the fault part, the number of the cluster, the flight intensity in the period and the probability;
and when the spare part guarantee stage is a test flight stage, taking values of the boundary conditions according to a test flight working plan.
4. A spare part analysis method based on aeronautical applications according to claim 3, characterized in that: the model, name, manufacturer, reliability index and development state in the modeling content in the second step are consistent with the protocol.
5. Spare part analysis method based on aeronautical applications according to claim 4, characterized in that: the number of the single machines in the modeling content of the second step is the number of the line replaceable unit LRUs in the system, and if a certain LRU has a plurality of system installations, the LRUs are respectively listed according to the system.
6. Spare part analysis method based on aeronautical applications according to claim 5, characterized in that: the importance level in the modeling content in the second step is divided into three levels, namely level 1-influencing safety, level 2-influencing task and level 3-influencing economy;
the development states include: newly developed, improved and stored in shelf.
7. A spare part analysis method based on aeronautical applications according to claim 6, characterized in that: in the fourth step, the requirement of the initial quantity of the spare parts is corrected in the following way:
if the importance level of the line replaceable unit LRU is 3 or the development state is a shelf, reducing the requirement of the initial quantity of spare parts of the LRU;
if the importance level of the LRU of the line replaceable unit is 1 level or the development state is newly developed, increasing the initial quantity requirement of the spare parts of the LRU or using the LRU as a preferential purchase item;
and (3) for the LRU with the requirement of 0 for the initial quantity of the spare parts in the third step, the requirement for the initial quantity of the spare parts of the LRU is corrected and confirmed by integrating the reliability index, the importance level, the development state and the engineering experience.
8. A spare part analysis method based on aeronautical applications according to claim 7, characterized in that: in the fourth step, if the spare part guarantee stage in the first step is a trial flight stage, a trial flight spare part list is compiled according to the correction result in the third step;
and if the spare part guarantee stage in the step one is other stages, correcting the initial spare part quantity requirement according to the test flight spare part list and the spare part consumption during the test flight to compile the spare part list in the corresponding stage.
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| CN101853448A (en) * | 2010-05-25 | 2010-10-06 | 北京航空航天大学 | Method for predicting spare part demand in equipment manufacturing process |
| CN102136032A (en) * | 2011-03-16 | 2011-07-27 | 北京航空航天大学 | Process-based method for establishing equipment reliability maintenance safety (RMS) requirement model |
| CN110414553A (en) * | 2019-06-14 | 2019-11-05 | 中国人民解放军海军工程大学 | A kind of spare part reliability estimation method and system merging multi-source information |
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Patent Citations (3)
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| CN101853448A (en) * | 2010-05-25 | 2010-10-06 | 北京航空航天大学 | Method for predicting spare part demand in equipment manufacturing process |
| CN102136032A (en) * | 2011-03-16 | 2011-07-27 | 北京航空航天大学 | Process-based method for establishing equipment reliability maintenance safety (RMS) requirement model |
| CN110414553A (en) * | 2019-06-14 | 2019-11-05 | 中国人民解放军海军工程大学 | A kind of spare part reliability estimation method and system merging multi-source information |
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| 原石中: "民用飞机备件需求量预测方法研究", 航空工程与维修, pages 47 * |
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