CN111639872A - Method for selecting and verifying civil aircraft failure mode and influence analysis test method - Google Patents
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Abstract
The invention provides a method for selecting and verifying a civil aircraft failure mode and influence analysis test method, which comprises the following steps of: s1, defining and outputting the hierarchy Y of the analyzed object; s2, determining and outputting the lowest appointed hierarchical unit of the analysis object; s3, collecting design materials of civil aircrafts and systems thereof; s4, determining the development stage T of the analysis object and outputting a related result; s5, determining an assessment formula of the civil aircraft failure mode and the influence analysis to obtain a final analysis scheme: s6, collecting civil aircraft product information according to the relevant tables; and S7, according to the civil aircraft product information collected in the S6, carrying out fault mode verification on the civil aircraft failure mode and influence analysis, and determining whether the civil aircraft failure mode and influence analysis are feasible. The invention provides a method for analyzing civil aircraft failure modes and influences, which is used for identifying potential functional failure modes of a whole machine or a key system, identifying key and important product functions and making corresponding prevention or improvement measures.
Description
Technical Field
The invention belongs to the field of civil aircraft reliability prediction, and particularly relates to a method for selecting and verifying a civil aircraft failure mode and influence analysis test method.
Background
FMEA analysis in the civil aircraft development is closely related to the reliability and safety work of the civil aircraft, and is also the core of the general characteristics of related products such as reliability and the like. In the current civil aircraft development process, single characteristics such as reliability, security set out from the demand of self, propose the different demands of FMEA technique, develop work separately. In addition, the implementation requirements of FMEA require standardized management, such as functional failure mode definition and failure criterion definition, many-to-one failure impact propagation mode, and the like. The project starts from the connotation of demand engineering, researches management contents such as a unified template of FMEA, a cutting principle and process using the unified template, implementation requirements and the like, establishes a standardized flow, reviews key points, and manages and maintains a unified data source.
The aircraft is formed by a plurality of devices according to complex interface relationships, and how to implement the level of the reliability of the whole aircraft on hardware design is an urgent problem to be solved, so that intensive research needs to be carried out on the cross-linking relationship between the functional FMEA and the hardware FMEA. The hardware and the function of the equipment have a mapping relation, for example, a plurality of pieces of equipment realize one function together, a certain piece of equipment can also realize a plurality of functions, and a plurality of complex relations exist between the functions, the hardware and the interfaces. Functional weak links of the whole machine are analyzed through the functional FMEA, and the hardware FMEA is a detailed design of the functional FMEA and is directly used for guiding the reliability design activities of equipment.
Aiming at complex characteristics of dynamics, multiple states, failure correlation and the like of an airplane and a system thereof, a system based on a function and reliability integrated model and a complete machine level function FMEA analysis method are researched, a function and system design data collection template of the airplane and a system thereof, a function model (reflecting interaction relation of system/complete machine functions, architecture and normal functions) construction method, fault model parameters and attribute definition rules, a fault logic model (describing fault propagation relation between the same level and cross-level in the system/complete machine) construction implementation requirement, an integrated model element and function FMEA analysis content mapping relation and the like are determined. An integrated model-based functional FMEA implementation flow and implementation key points are formed through research, and the system and complete machine level functional FMEA work development is supported.
Starting from the connotation of demand engineering, the FMEA technology of the airplane, which can meet the design analysis of reliability and safety, is researched, the FMEA technology based on a unified data source and standardization is formed, and the standardized implementation flow and the cutting requirements are established. Under the framework of system engineering, according to the design result of an airplane architecture, a functional model of the airplane can be established in the early stage of design, a functional fault control affecting operation (including operation reliability, safety and maintainability) is taken as a core through the extended definition of the functional model, a reliability analysis technology based on functional FMEA is established, and the reliability of civil aircrafts can be analyzed in a bottom-up mode from a component level to a system level and an airplane level. The specific research contents comprise:
aiming at complex characteristics of dynamics, multiple states, failure correlation and the like of an airplane and a system thereof, a system based on a function and reliability integrated model and a complete machine level function FMEA analysis method are researched, a function and system design data collection template of the airplane and a system thereof, a function model (reflecting interaction relation of system/complete machine functions, architecture and normal functions) construction method, fault model parameters and attribute definition rules, a fault logic model (describing fault propagation relation between the same level and cross-level in the system/complete machine) construction implementation requirement, an integrated model element and function FMEA analysis content mapping relation and the like are determined. An integrated model-based functional FMEA implementation flow and implementation key points are formed through research, and the system and complete machine level functional FMEA work development is supported.
Disclosure of Invention
In order to solve the above-mentioned deficiencies of the prior art, the present invention provides a method for selecting and verifying civil aircraft failure modes and impact analysis test methods, which uses several LRUs or subsystems as function modules, identifies potential functional failure modes of the whole machine or key system, identifies key and important product functions, and makes corresponding preventive or improvement measures.
Specifically, the invention provides a method for selecting and verifying a civil aircraft failure mode and influence analysis test method, which comprises the following steps:
s1, defining and outputting the hierarchy Y of the object to be analyzed, wherein the hierarchy output result of the object to be analyzed is A, S or C;
s2, determining and outputting the lowest agreed hierarchical unit of the analysis object, wherein the output result of the lowest agreed hierarchical unit of the analysis object is system level, equipment level, SRU level, functional circuit level and component level;
s3, collecting design materials of civil aircrafts and systems thereof, defining a functional model construction method, fault model parameters and attribute definition rules of the aircrafts, and establishing implementation requirements of a fault logic model and mapping relations between elements of the integrated model and functional FMEA analysis content, wherein the functional model comprises interaction relations reflecting systems, functions of the whole aircraft, architectures and normal functions, and the fault logic model comprises description systems and fault propagation relations between the same level/cross levels in the whole aircraft;
s4, determining a development stage T of the analysis object and outputting related results, wherein the development stage comprises a demand analysis stage, a scheme demonstration stage, a test stage initial stage, a batch production stage and a shaping stage, and the output results are X, F, C, E, D and P;
s5, determining an assessment formula of the civil aircraft failure mode and the influence analysis, and outputting a result to obtain a final analysis scheme and a table:
the specific assessment formula is as follows:
M＝g(Y,T)
g(T＝X∪F∪C0)＝F-FMEA；
g{(Y＝A∪S)∩(T＝E)}＝F-FMEA；
g{(Y＝C)∩(T＝E∪D)}＝D-FMEA；
g{(Y＝A∪S∪C)∩(T＝P)}＝P-FMEA；
g{(Y＝A∪S)∩(T＝F∪C0∪E∪D∪P)}＝FMES
wherein, Y is the hierarchy of the study; a-aircraft level; s-system level; c-equipment level; t-development stage; an X-demand analysis stage; f-scheme demonstration stage; c0-a preliminary phase; e-test stage; d, shaping; p-batch production stage;
the finally obtained analysis scheme comprises F-FMEA, D-FMEA, P-FMEA and FMES, wherein F-FMEA is functional FMEA, D-FMEA is hardware FMEA, P-FMEA is process FMEA, and FMES is failure mode analysis;
s6, collecting civil aircraft product information according to the following tables 1, 2, 3, 4 and 5, and analyzing according to the specific steps of GJB/Z1391;
TABLE 1 civil aircraft function FMEA worksheet
TABLE 2 hardware FMEA worksheet for civil aircraft electronic/electric products
TABLE 3 hardware FMEA worksheet of civil aircraft mechanical products
TABLE 4 civil aircraft process FMEA worksheet
Watch 5 civil FMEAS worksheet
And S7, according to the civil aircraft product information collected in the S6, carrying out fault mode verification on the civil aircraft failure mode and influence analysis, determining the reliability of the component and effective influence design, and verifying the correctness of the fault mode in the FMEA by adopting a high-acceleration life test in the component design process.
Preferably, the research objects in step S1 are divided according to the functional components of the civil aircraft.
Preferably, the study subject in step S1 is divided according to function and stored in the database.
Preferably, in step S7, in order to determine the reliability of the component and to effectively guide the design, the high accelerated life test method employed in the component design process is performed by the component supplier according to specifications established by the aircraft manufacturer.
Preferably, the high accelerated life test is performed in step S7 by applying random vibration, rapid temperature change, voltage margin and frequency margin to the test part.
Preferably, the correctness of the failure mode in the FMEA is verified by HALT and HASS in step S7, if the result of the test can prove that the failure mode analyzed before is completely correct, the failure mode listed in the FMEA is verified to be correct, and if a new failure mode appears in the test, both the previous FMEA analysis and the test itself are proved to be failed.
Compared with the prior art, the invention has the following beneficial effects:
the invention provides a method for selecting and verifying a civil aircraft failure mode and an influence analysis test method, which takes a plurality of LRUs or subsystems as function modules, identifies potential functional failure modes of a complete machine or a key system, identifies key and important product functions, and makes corresponding prevention or improvement measures. Meanwhile, in order to determine the reliability of the components and effectively guide the design, the high-acceleration life test method adopted in the component design process is executed by a component supplier according to the specifications set by the aircraft manufacturer. The correctness of the failure modes in the FMEA is verified through HALT and HASS, if the result of the test can prove that the failure modes analyzed before are completely correct, the failure modes listed in the FMEA are verified to be correct, and if a new failure mode appears in the test, the failure of the previous FMEA analysis and the test per se are proved.
Drawings
FIG. 1 is a schematic flow diagram of the present invention; and
fig. 2 is a detailed flowchart in the embodiment of the present invention.
Detailed Description
Exemplary embodiments, features and aspects of the present invention will be described in detail below with reference to the accompanying drawings. In the drawings, like reference numbers can indicate functionally identical or similar elements. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
S1, defining and outputting the hierarchy Y of the object to be analyzed, wherein the hierarchy output result of the object to be analyzed is A, S or C;
s2, determining and outputting the lowest agreed hierarchical unit of the analysis object, wherein the output result of the lowest agreed hierarchical unit of the analysis object is system level, equipment level, SRU level, functional circuit level and component level;
s3, collecting design materials of civil aircrafts and systems thereof, defining a functional model construction method, fault model parameters and attribute definition rules of the aircrafts, and establishing implementation requirements of a fault logic model and mapping relations between elements of the integrated model and functional FMEA analysis content, wherein the functional model comprises interaction relations reflecting systems, functions of the whole aircraft, architectures and normal functions, and the fault logic model comprises description systems and fault propagation relations between the same level/cross levels in the whole aircraft;
s4, determining a development stage T of the analysis object and outputting related results, wherein the development stage comprises a demand analysis stage, a scheme demonstration stage, a test stage initial stage, a batch production stage and a shaping stage, and the output results are X, F, C, E, D and P;
s5, determining an assessment formula of the civil aircraft failure mode and the influence analysis, and outputting a result to obtain a final analysis scheme and a table:
the specific assessment formula is as follows:
M＝g(Y，T)
g(T＝X∪F∪C0)＝F-FMEA；
g{(Y＝A∪S)∩(T＝E)}＝F-FMEA；
g{(Y＝C)∩(T＝E∪D)}＝D-FMEA；
g{(Y＝A∪S∪C′)∩(T＝P)}＝P-FMEA；
g{(Y＝A∪S)∩(T＝F∪C0∪E∪D∪P)}＝FMES
wherein, Y is the hierarchy of the study; a-aircraft level; s-system level; c-equipment level; t-development stage; an X-demand analysis stage; f-scheme demonstration stage; c0-a preliminary phase; e-test stage; d, shaping; p-batch production stage;
the finally obtained analysis scheme comprises F-FMEA, D-FMEA, P-FMEA and FMES, wherein F-FMEA is functional FMEA, D-FMEA is hardware FMEA, P-FMEA is process FMEA, and FMES is failure mode analysis;
s6, collecting civil aircraft product information according to the following tables 1, 2, 3, 4 and 5, and analyzing according to the specific steps of GJB/Z1391;
TABLE 1 civil aircraft function FMEA worksheet
TABLE 2 hardware FMEA worksheet for civil aircraft electronic/electric products
TABLE 3 hardware FMEA worksheet of civil aircraft mechanical products
TABLE 4 civil aircraft process FMEA worksheet
Watch 5 civil FMEAS worksheet
And S7, according to the civil aircraft product information collected in the S6, carrying out fault mode verification on the civil aircraft failure mode and influence analysis, determining the reliability of the component and effective influence design, and verifying the correctness of the fault mode in the FMEA by adopting a high-acceleration life test in the component design process.
FMES provides a clear summary of the FMEA results, and should provide top-level failure impact and detection methods, as well as include flight phase information and detection modes. Is a summary of entries in the FMEA report that have the same fault impact (typically system level), i.e. fault pattern in the FMES, which fault pattern (lower level) of the FMEA will constitute a potential cause of a fault in the FMES.
The fault modes of the traditional FMEA are listed according to experience, but are not necessarily correct, the fault modes need to be verified, at present, the fault mode verification work is never carried out, and the method indicates that the fault mode verification is required for the civil FMEA.
In order to determine the reliability of the components and to effectively influence the design, highly accelerated life tests should be employed as early as possible in the component design process, which should be carried out by the component supplier in accordance with the specifications of the aircraft manufacturer.
The purpose of this technique is to quickly expose the design weaknesses, so that the component can be redesigned, and the robustness of the component is improved. Techniques are used to apply random vibrations to the test part, rapid temperature changes, voltage margins, frequency margins and any other suitable stress that may help to find problems in the design or manufacturing process.
The failure modes in the FMEA can be verified by the HALT and HASS tests, if the results of the tests prove that the failure modes analyzed before are completely correct, the failure modes listed in the FMEA are verified to be correct, but if a new failure mode appears in the tests, the failure of the FMEA analysis before and the tests themselves are proved, in which case there is a great problem that affects the development process of the whole equipment, so that caution is taken when taking the HALT or HASS tests.
Finally, it should be noted that: the above-mentioned embodiments are only used for illustrating the technical solution of the present invention, and not for limiting the same; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (6)
1. A method for selecting and verifying a civil aircraft failure mode and an influence analysis test method is characterized by comprising the following steps: which comprises the following steps:
s1, defining and outputting the hierarchy Y of the object to be analyzed, wherein the hierarchy output result of the object to be analyzed is A, S or C;
s2, determining and outputting the lowest agreed hierarchical unit of the analysis object, wherein the output result of the lowest agreed hierarchical unit of the analysis object is system level, equipment level, SRU level, functional circuit level and component level;
s3, collecting design materials of civil aircrafts and systems thereof, defining a functional model construction method, fault model parameters and attribute definition rules of the aircrafts, and establishing implementation requirements of a fault logic model and mapping relations between elements of the integrated model and functional FMEA analysis content, wherein the functional model comprises interaction relations reflecting systems, functions of the whole aircraft, architectures and normal functions, and the fault logic model comprises description systems and fault propagation relations between the same level/cross levels in the whole aircraft;
s4, defining a development stage T of the analysis object and outputting related results, wherein the development stage comprises a demand analysis stage, a scheme demonstration stage, a test stage initial sample stage, a batch production stage and a shaping stage, and the output result is X, F, C0E, D and P;
s5, determining an assessment formula of the civil aircraft failure mode and the influence analysis, and outputting a result to obtain a final analysis scheme and a table:
the specific assessment formula is as follows:
M＝g(Y，T)
g(T＝X∪F∪C0)＝F-FMEA；
g{(Y＝A∪S)∩(T＝E)}＝F-FMEA；
g{(Y＝C)∩(T＝E∪D)}＝D-FMEA；
g{(Y＝A∪S∪C)∩(T＝P)}＝P-FMEA；
g{(Y＝A∪S)∩(T＝F∪C0∪E∪D∪P)}＝FMES
wherein, Y is the hierarchy of the study; a-aircraft level; s-system level; c-equipment level; t-development stage; an X-demand analysis stage; f-scheme demonstration stage; c0-a preliminary phase; e-test stage; d, shaping; p-batch production stage;
the finally obtained analysis scheme comprises F-FMEA, D-FMEA, P-FMEA and FMES, wherein F-FMEA is functional FMEA, D-FMEA is hardware FMEA, P-FMEA is process FMEA, and FMES is failure mode analysis;
s6, collecting civil aircraft product information according to the following tables 1, 2, 3, 4 and 5, and analyzing according to the specific steps of GJB/Z1391;
TABLE 1 civil aircraft function FMEA worksheet
TABLE 2 hardware FMEA worksheet for civil aircraft electronic/electric products
TABLE 3 hardware FMEA worksheet of civil aircraft mechanical products
TABLE 4 civil aircraft process FMEA worksheet
Watch 5 civil FMEAS worksheet
And S7, according to the civil aircraft product information collected in the S6, carrying out fault mode verification on the civil aircraft failure mode and influence analysis, determining the reliability of the component and effective influence design, and verifying the correctness of the fault mode in the FMEA by adopting a high-acceleration life test in the component design process.
2. The method for selecting and verifying civil aircraft failure modes and impact analysis test methods according to claim 1, characterized in that: the research object in step S1 is divided according to the functional components of the civil aircraft.
3. The method for selecting and verifying civil aircraft failure modes and impact analysis test methods according to claim 1, characterized in that: the study object in step S1 is divided according to function and stored in the database.
4. The method for selecting and verifying civil aircraft failure modes and impact analysis test methods according to claim 1, characterized in that: in order to determine the reliability of the component and to effectively guide the design in step S7, the high accelerated life test method employed in the component design process is performed by the component supplier according to specifications established by the aircraft manufacturer.
5. The method for selecting and verifying civil aircraft failure modes and impact analysis test methods according to claim 4, characterized in that: in step S7, a high accelerated life test is performed by applying random vibration, rapid temperature change, voltage margin, and frequency margin to the test part.
6. The method for selecting and verifying civil aircraft failure modes and impact analysis test methods according to claim 1, characterized in that: in step S7, the correctness of the failure mode in the FMEA is verified through HALT and HASS, if the result of the test can prove that the failure mode analyzed before is completely correct, the failure mode listed in the FMEA is verified to be correct, and if a new failure mode appears in the test, both the previous FMEA analysis and the test themselves are proved to be failed.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112711851A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Fault diagnosis demand data model construction method |
| CN114048633A (en) * | 2021-12-24 | 2022-02-15 | 中国飞机强度研究所 | Airplane high and cold test matrix design method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005234861A (en) * | 2004-02-19 | 2005-09-02 | Mitsubishi Electric Corp | Management device and management system |
| CN103760886A (en) * | 2013-12-02 | 2014-04-30 | 北京航空航天大学 | Newly-developed aviation electronic product hardware comprehensive FMECA method |
| CN103955556A (en) * | 2014-03-27 | 2014-07-30 | 北京交通大学 | Fault logical modeling method for high speed railway train operation control vehicle-mounted system |
| US20150134398A1 (en) * | 2013-11-08 | 2015-05-14 | Jin Xing Xiao | Risk driven product development process system |
-
2020
- 2020-06-04 CN CN202010502041.6A patent/CN111639872B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005234861A (en) * | 2004-02-19 | 2005-09-02 | Mitsubishi Electric Corp | Management device and management system |
| US20150134398A1 (en) * | 2013-11-08 | 2015-05-14 | Jin Xing Xiao | Risk driven product development process system |
| CN103760886A (en) * | 2013-12-02 | 2014-04-30 | 北京航空航天大学 | Newly-developed aviation electronic product hardware comprehensive FMECA method |
| CN103955556A (en) * | 2014-03-27 | 2014-07-30 | 北京交通大学 | Fault logical modeling method for high speed railway train operation control vehicle-mounted system |
Non-Patent Citations (1)
| Title |
|---|
| 杜熠;刘萌萌;宋成军;苏峰;: "面向复杂系统的测试性试验验证技术研究", 计算机测量与控制 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112711851A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Fault diagnosis demand data model construction method |
| CN114048633A (en) * | 2021-12-24 | 2022-02-15 | 中国飞机强度研究所 | Airplane high and cold test matrix design method |
| CN114048633B (en) * | 2021-12-24 | 2022-04-12 | 中国飞机强度研究所 | Airplane high and cold test matrix design method |
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