Aircraft development full life cycle characteristic analysis and control method

Abstract

The invention belongs to the technical field of airplane development full-life cycle characteristic analysis and control design, and particularly relates to an airplane development full-life cycle characteristic analysis and control method and system. Characteristic analysis and characteristic control are carried out according to an airplane development full-life cycle through two levels of characteristic analysis and characteristic control; characteristic analysis and control are dominated through a method of establishing a file system, so that the hidden danger of substandard product quality caused by the fact that key and important characteristics are not identified due to omission of key characteristic identification in the airplane development process can be reduced; and key and important characteristic work of the whole life cycle from identification of key and important characteristics, transmission of the key and important characteristics and management and control of the key and important characteristics in various research, production, test, manufacturing and maintenance guarantee can be realized, and traceability and transitivity of the key and important characteristics can be realized.

Description

Technical Field

[0001] The present application belongs to the technical field of full life cycle characteristic analysis and control design for aircraft development, and specifically relates to a full life cycle characteristic analysis and control method and system for aircraft development. Background Art

[0002] Characteristics are inherent attributes of products, which are the performance, parameters and other technical requirements of products. The main characteristics are function, interchangeability, life, safety and coordination. The management of characteristics requires a classification process based on their importance. Characteristics are generally divided into three categories: critical characteristics, important characteristics and general characteristics.

[0003] During the aircraft development process, characteristics need to be managed and controlled. At present, the characteristics management link in the aircraft development process is mainly concentrated on the characteristics category, characteristics classification, drawing number marking level and the quality control process of key parts. For the characteristics analysis and control of the entire aircraft development cycle, a reliable and efficient analysis and control process has not yet been established. In view of this, this application is proposed. Summary of the invention

[0004] The purpose of this application is to provide a method and system for analyzing and controlling characteristics of aircraft development throughout its entire life cycle, so as to overcome or alleviate at least one of the known technical deficiencies.

[0005] The technical solution of this application is:

[0006] On the one hand, a method for analyzing and controlling characteristics of the entire life cycle of aircraft development is provided, including a characteristic analysis link and a characteristic control link;

[0007] The characteristic analysis phase analyzes the characteristics, including aircraft-level characteristic analysis, structure / system-level characteristic analysis, and equipment-level characteristic analysis;

[0008] The characteristic control link controls the characteristics of the aircraft. The control elements mainly include demand management, technical status management, key process management, inspection management, measurement management, non-conforming product management, ground test management, test flight management, user information, field information, and fault reset.

[0009] The characteristic analysis phase and the characteristic control phase are carried out simultaneously according to the aircraft development cycle, covering the entire aircraft development cycle, including scheme design, preliminary design, detailed design, trial production and ground development tests, performance verification / identification flight tests and status identification, installation and finalization stage, mass production and service support stage.

[0010] According to at least one embodiment of the present application, in the above-mentioned aircraft development full life cycle characteristics analysis and control method, in the characteristics analysis stage, the aircraft characteristics are analyzed and divided into three categories: key characteristics, important characteristics and general characteristics.

[0011] According to at least one embodiment of the present application, in the above-mentioned aircraft development life cycle characteristic analysis and control method, in the characteristic analysis phase, when analyzing the aircraft-level characteristics, the aircraft-level functions and performance requirements are used as inputs to analyze the degree of impact of aircraft-level function and performance failures on the aircraft, and determine the aircraft-level characteristic level;

[0012] In the characteristic analysis phase, when analyzing the structural / system-level characteristics, the structural / system-level functions and performances and the aircraft-level characteristic analysis results are used as inputs to analyze the impact of structural / system-level function and performance failures on the aircraft and determine the structural / system-level characteristic levels;

[0013] In the characteristic analysis phase, when analyzing the equipment-level characteristics, the equipment's function, performance, failure mode, failure cause, etc. and the structural / system-level characteristic analysis results are used as input to analyze the impact of equipment function and performance failure on the aircraft and determine the function and performance characteristic level of the airborne equipment.

[0014] According to at least one embodiment of the present application, in the above-mentioned aircraft development full life cycle characteristic analysis and control method, in the characteristic analysis link, the aircraft-level characteristic analysis is carried out in the scheme design stage; the structure / system-level characteristic analysis starts and ends in the preliminary design stage and ends in the detailed design stage; the equipment-level characteristic analysis is carried out in the detailed design stage.

[0015] According to at least one embodiment of the present application, in the above-mentioned aircraft development life cycle characteristic analysis and control method, the characteristic control link performs different element control on key characteristics and important characteristics at different stages during the aircraft development life cycle, as follows:

[0016] During the design phase, aircraft-level requirements and aircraft-level technical status control are performed on key and important characteristics;

[0017] Conduct structural / system-level requirement control and structural / system-level technical status control on key and important characteristics during the preliminary design phase;

[0018] During the detailed design phase, the key and important characteristics of the airborne equipment and unit components shall be subject to demand control, technical status control and metrological control;

[0019] During the trial production and ground development test phase, key characteristics and important characteristics are subject to key process demand control, key process technical status control, key process control, inspection management, measurement management, non-conforming product management, ground test management, user information, field information, and fault zeroing control during production and testing;

[0020] During the performance verification and identification flight test phase, key characteristics and important characteristics are managed in terms of inspection management, measurement management, non-conforming product management, flight test management, field information management, and fault reporting and zeroing management.

[0021] During the installation and finalization stage, field information, fault reporting and zeroing management of key and important characteristics shall be controlled;

[0022] During the batch production and service assurance stages, key characteristics and important characteristics are controlled in terms of technical status, key processes, inspection management, measurement management, non-conforming product management, field service information management, fault reporting and zeroing management.

[0023] According to at least one embodiment of the present application, the above-mentioned aircraft development life cycle characteristics analysis and control method also includes a quality supervision link;

[0024] The quality supervision link conducts quality supervision on the characteristic analysis link and the characteristic control link at every stage of the aircraft development life cycle, and the supervision is in the form of internal review or external review.

[0025] According to at least one embodiment of the present application, the above-mentioned aircraft development life cycle characteristics analysis and control method further includes a document system establishment link;

[0026] In the process of establishing the document system, a three-level document system is established during the process of characteristic analysis and characteristic control. The first level of the document system stipulates the overall framework of the entire characteristic analysis and characteristic control links; the second level of the document system puts forward requirements for the characteristic analysis methods at the aircraft level, system level, and equipment level; the third level of the document system stipulates the specific content of the control elements at each stage of the entire life cycle of aircraft development.

[0027] On the other hand, a full life cycle characteristic analysis and control system for aircraft development is provided, characterized in that it includes a characteristic analysis module and a characteristic control module;

[0028] The characteristic analysis module is used to analyze the characteristics, including aircraft-level characteristic analysis, structure / system-level characteristic analysis, and equipment-level characteristic analysis;

[0029] The characteristic control module is used to control the characteristics of the aircraft. The control elements mainly include demand management, technical status management, key process management, inspection management, measurement management, non-conforming product management, ground test management, test flight management, user information, field information, and fault reset.

[0030] The characteristic analysis module and the characteristic control module carry out characteristic analysis and control synchronously according to the aircraft development cycle, covering the entire aircraft development cycle, including scheme design, preliminary design, detailed design, trial production and ground development testing, performance verification / identification flight testing and status identification, installation and finalization stage, mass production and service support stage.

[0031] According to at least one embodiment of the present application, in the above-mentioned aircraft development full life cycle characteristics analysis and management system, in the characteristics analysis module, the aircraft characteristics are analyzed and the characteristics are divided into three categories: key characteristics, important characteristics and general characteristics.

[0032] According to at least one embodiment of the present application, in the above-mentioned aircraft development life cycle characteristic analysis and management system, in the characteristic analysis module, when analyzing the aircraft-level characteristics, the aircraft-level functions and performance requirements are used as inputs to analyze the degree of impact of aircraft-level function and performance failures on the aircraft, and determine the aircraft-level characteristic level;

[0033] In the characteristic analysis module, when analyzing the structural / system-level characteristics, the structural / system-level functions and performances and the aircraft-level characteristics analysis results are used as inputs to analyze the impact of structural / system-level function and performance failures on the aircraft and determine the structural / system-level characteristics level;

[0034] In the characteristic analysis module, when analyzing the equipment-level characteristics, the equipment's function, performance, failure mode, failure cause, etc. and the structural / system-level characteristic analysis results are used as input to analyze the impact of equipment function and performance failure on the aircraft and determine the function and performance characteristic level of the airborne equipment.

[0035] According to at least one embodiment of the present application, in the above-mentioned aircraft development full life cycle characteristics analysis and control system, in the characteristics analysis module, the analysis of aircraft-level characteristics is carried out in the scheme design stage; the analysis of structure / system-level characteristics begins and ends in the preliminary design stage and ends in the detailed design stage; and the analysis of equipment-level characteristics is carried out in the detailed design stage.

[0036] According to at least one embodiment of the present application, in the above-mentioned aircraft development life cycle characteristics analysis and management system,

[0037] The characteristic control module controls key characteristics and important characteristics in different stages during the entire life cycle of aircraft development, as follows:

[0038] During the design phase, aircraft-level requirements and aircraft-level technical status control are performed on key and important characteristics;

[0039] Conduct structural / system-level requirement control and structural / system-level technical status control on key and important characteristics during the preliminary design phase;

[0040] During the detailed design phase, the key and important characteristics of the airborne equipment and unit components shall be subject to demand control, technical status control and metrological control;

[0041] During the trial production and ground development test phase, key characteristics and important characteristics are subject to key process demand control, key process technical status control, key process control, inspection management, measurement management, non-conforming product management, ground test management, user information, field information, and fault zeroing control during production and testing;

[0042] During the performance verification and identification flight test phase, key characteristics and important characteristics are managed in terms of inspection management, measurement management, non-conforming product management, flight test management, field information management, and fault reporting and zeroing management.

[0043] During the installation and finalization stage, field information, fault reporting and zeroing management of key and important characteristics shall be controlled;

[0044] During the batch production and service assurance stages, key characteristics and important characteristics are controlled in terms of technical status, key processes, inspection management, measurement management, non-conforming product management, field service information management, fault reporting and zeroing management.

[0045] According to at least one embodiment of the present application, the above-mentioned aircraft development life cycle characteristics analysis and control system further includes a quality supervision module;

[0046] The quality supervision module is used to supervise the quality of characteristic analysis and control at every stage of the aircraft development life cycle, and the supervision is in the form of internal review or external review.

[0047] According to at least one embodiment of the present application, the above-mentioned aircraft development life cycle characteristics analysis and management system further includes a file system establishment module;

[0048] The file system establishment module is used to establish a three-layer file system during the characteristics analysis and control process. The first layer of the file system stipulates the overall framework of the entire characteristics analysis module and the characteristics control module; the second layer of the file system puts forward requirements for the aircraft-level, system-level and equipment-level characteristics analysis systems; the third layer of the file system stipulates the specific content of the control elements at each stage of the entire life cycle of aircraft development.

[0049] This application has at least the following beneficial technical effects:

[0050] The aircraft development full life cycle characteristic analysis and control method and system disclosed in the above-mentioned embodiment perform characteristic analysis and characteristic control in accordance with the aircraft development full life cycle through two levels of characteristic analysis and characteristic control, and make characteristic analysis and control explicit by establishing a document system. This can reduce the omission of key characteristic identification in the aircraft development process, which may lead to the hidden danger of substandard product quality caused by the failure to identify key and important characteristics, and can realize the key and important characteristic work of the whole life cycle from identification of key characteristics, transmission of key characteristics and control of key characteristics in various research, production, testing, manufacturing and maintenance assurance, and can realize the traceability and transmission of key characteristics. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Figure 1 It is a schematic diagram of a method for analyzing and controlling characteristics of aircraft development throughout its life cycle provided in an embodiment of the present application;

[0052] Figure 2 It is a schematic diagram of the aircraft development full life cycle characteristics analysis and control system provided in the embodiment of the present application.

[0053] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0054] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0055] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0056] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0057] A method for analyzing and controlling the characteristics of aircraft development throughout its life cycle, such as Figure 1 As shown, it includes characteristic analysis, characteristic control, quality supervision and document system establishment.

[0058] The characteristic analysis phase analyzes the characteristics, including aircraft-level characteristic analysis, structure / system-level characteristic analysis, and equipment-level characteristic analysis.

[0059] In the characteristic analysis phase, the aircraft characteristics are analyzed and divided into three categories: key characteristics, important characteristics and general characteristics.

[0060] In the characteristic analysis phase, when analyzing the aircraft-level characteristics, the aircraft-level functions and performance requirements are used as input to analyze the extent of the impact of aircraft-level function and performance failures on the aircraft and determine the aircraft-level characteristic level.

[0061] In the characteristic analysis phase, when analyzing the structure / system-level characteristics, the structure / system-level function and performance and the aircraft-level characteristic analysis results are used as input to analyze the impact of the failure of the structure / system-level function and performance on the aircraft and determine the structure / system-level characteristic level.

[0062] In the characteristic analysis phase, when analyzing the equipment-level characteristics, the equipment's function, performance, failure mode, failure cause, etc. and the structural / system-level characteristic analysis results are used as input to analyze the impact of equipment function and performance failure on the aircraft and determine the function and performance characteristic level of the airborne equipment.

[0063] The characteristic control link controls the aircraft characteristics. The control elements mainly include demand management, technical status management, key process management, inspection management, measurement management, non-conforming product management, ground test management, test flight management, user information, field information, and fault reset.

[0064] The characteristic analysis phase and the characteristic control phase are carried out simultaneously according to the aircraft development cycle, covering the entire aircraft development cycle, including scheme design, preliminary design, detailed design, trial production and ground development tests, performance verification / identification flight tests and status identification, installation and finalization stage, mass production and service support stage.

[0065] In the characteristic analysis phase, aircraft-level characteristic analysis is carried out in the scheme design stage; structure / system-level characteristic analysis begins and ends in the preliminary design stage and ends in the detailed design stage; equipment-level characteristic analysis is carried out in the detailed design stage.

[0066] Characteristics control link During the entire life cycle of aircraft development, different elements of key characteristics and important characteristics are controlled at different stages, as follows:

[0067] During the design phase, aircraft-level requirements and aircraft-level technical status control are performed on key and important characteristics;

[0068] Conduct structural / system-level requirement control and structural / system-level technical status control on key and important characteristics during the preliminary design phase;

[0069] During the detailed design phase, the key and important characteristics of the airborne equipment and unit components shall be subject to demand control, technical status control and metrological control;

[0070] During the trial production and ground development test phase, key characteristics and important characteristics are subject to key process demand control, key process technical status control, key process control, inspection management, measurement management, non-conforming product management, ground test management, user information, field information, and fault zeroing control during production and testing;

[0071] During the performance verification and identification flight test phase, key characteristics and important characteristics are managed in terms of inspection management, measurement management, non-conforming product management, flight test management, field information management, and fault reporting and zeroing management.

[0072] During the installation and finalization stage, field information, fault reporting and zeroing management of key and important characteristics shall be controlled;

[0073] During the batch production and service assurance stages, key characteristics and important characteristics are controlled in terms of technical status, key processes, inspection management, measurement management, non-conforming product management, field service information management, fault reporting and zeroing management.

[0074] The quality supervision link conducts quality supervision on the characteristic analysis link and characteristic control link at every stage of the aircraft development life cycle to ensure that the content of the characteristic analysis link is complete and accurate, the measures of the characteristic control link are implemented, and key and important parts are not missed in the development process. The form of quality supervision is not limited to internal review and external review.

[0075] In the process of establishing the document system, a three-level document system is established during the process of characteristic analysis and characteristic control. The first level of the document system stipulates the overall framework of the entire characteristic analysis and characteristic control links; the second level of the document system puts forward requirements for the characteristic analysis methods at the aircraft level, system level, and equipment level; the third level of the document system stipulates the specific content of the control elements at each stage of the entire life cycle of aircraft development.

[0076] On the other hand, a full life cycle characteristic analysis and control system for aircraft development is provided, characterized in that it includes a characteristic analysis module and a characteristic control module;

[0077] The characteristic analysis module is used to analyze the characteristics, including aircraft-level characteristic analysis, structure / system-level characteristic analysis, and equipment-level characteristic analysis;

[0078] The characteristic control module is used to control the characteristics of the aircraft. The control elements mainly include demand management, technical status management, key process management, inspection management, measurement management, non-conforming product management, ground test management, test flight management, user information, field information, and fault reset.

[0079] The characteristic analysis module and the characteristic control module carry out characteristic analysis and control synchronously according to the aircraft development cycle, covering the entire aircraft development cycle, including scheme design, preliminary design, detailed design, trial production and ground development testing, performance verification / identification flight testing and status identification, installation and finalization stage, mass production and service support stage.

[0080] Optionally, in the above-mentioned aircraft development full life cycle characteristics analysis and control system, in the characteristics analysis module, the aircraft characteristics are analyzed and divided into three categories: key characteristics, important characteristics and general characteristics.

[0081] Optionally, in the above-mentioned aircraft development life cycle characteristic analysis and control system, in the characteristic analysis module, when analyzing the aircraft-level characteristics, the aircraft-level function and performance requirements are used as input to analyze the degree of impact of aircraft-level function and performance failure on the aircraft, and determine the aircraft-level characteristic level;

[0082] In the characteristic analysis module, when analyzing the structural / system-level characteristics, the structural / system-level functions and performances and the aircraft-level characteristics analysis results are used as inputs to analyze the impact of structural / system-level function and performance failures on the aircraft and determine the structural / system-level characteristics level;

[0083] In the characteristic analysis module, when analyzing the equipment-level characteristics, the equipment's function, performance, failure mode, failure cause, etc. and the structural / system-level characteristic analysis results are used as input to analyze the impact of equipment function and performance failure on the aircraft and determine the function and performance characteristic level of the airborne equipment.

[0084] Optionally, in the above-mentioned aircraft development full life cycle characteristics analysis and control system, in the characteristics analysis module, the analysis of aircraft-level characteristics is carried out in the scheme design stage; the analysis of structure / system-level characteristics begins and ends in the preliminary design stage and ends in the detailed design stage; and the analysis of equipment-level characteristics is carried out in the detailed design stage.

[0085] Optionally, in the above-mentioned aircraft development life cycle characteristics analysis and control system,

[0086] The characteristic control module controls key characteristics and important characteristics in different stages during the entire life cycle of aircraft development, as follows:

[0087] During the design phase, aircraft-level requirements and aircraft-level technical status control are performed on key and important characteristics;

[0088] Conduct structural / system-level requirement control and structural / system-level technical status control on key and important characteristics during the preliminary design phase;

[0089] During the detailed design phase, the key and important characteristics of the airborne equipment and unit components shall be subject to demand control, technical status control and metrological control;

[0090] During the trial production and ground development test phase, key characteristics and important characteristics are subject to key process demand control, key process technical status control, key process control, inspection management, measurement management, non-conforming product management, ground test management, user information, field information, and fault zeroing control during production and testing;

[0091] During the performance verification and identification flight test phase, key characteristics and important characteristics are managed in terms of inspection management, measurement management, non-conforming product management, flight test management, field information management, and fault reporting and zeroing management.

[0092] During the installation and finalization stage, field information, fault reporting and zeroing management of key and important characteristics shall be controlled;

[0093] During the batch production and service assurance stages, key characteristics and important characteristics are controlled in terms of technical status, key processes, inspection management, measurement management, non-conforming product management, field service information management, fault reporting and zeroing management.

[0094] Optionally, the above-mentioned aircraft development life cycle characteristics analysis and control system also includes a quality supervision module;

[0095] The quality supervision module is used to supervise the quality of characteristic analysis and control at every stage of the aircraft development life cycle, and the supervision is in the form of internal review or external review.

[0096] Optionally, the above-mentioned aircraft development life cycle characteristics analysis and control system also includes a document system establishment module;

[0097] The file system establishment module is used to establish a three-layer file system during the characteristics analysis and control process. The first layer of the file system stipulates the overall framework of the entire characteristics analysis module and the characteristics control module; the second layer of the file system puts forward requirements for the aircraft-level, system-level and equipment-level characteristics analysis systems; the third layer of the file system stipulates the specific content of the control elements at each stage of the entire life cycle of aircraft development.

[0098] The aircraft development full life cycle characteristic analysis and control method and system disclosed in the above-mentioned embodiment perform characteristic analysis and characteristic control in accordance with the aircraft development full life cycle through two levels of characteristic analysis and characteristic control, and make the characteristic analysis and control explicit by establishing a document system, thereby reducing errors and omissions in system requirements and development activities, and ensuring that the system meets the safety requirements of airworthiness regulations.

[0099] In addition, technicians in the field should also be able to realize that the various modules and units of the aircraft development full life cycle characteristics analysis and control system disclosed in the embodiments of the present application can be implemented by electronic hardware, computer software or a combination of the two. In order to clearly illustrate the interchangeability of hardware and software, this application generally describes them according to their functions. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Technicians in the field can choose to adopt different methods to implement the described functions for each specific application and its actual constraints, but such implementation should not be considered to be beyond the scope of this application.

[0100] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A method for analyzing and controlling characteristics of the entire life cycle of aircraft development, characterized in that: Including characteristic analysis and characteristic control; The characteristic analysis phase analyzes the characteristics, including aircraft-level characteristic analysis, structure / system-level characteristic analysis, and equipment-level characteristic analysis; The characteristic control link controls the characteristics of the aircraft. The control elements mainly include demand management, technical status management, key process management, inspection management, measurement management, non-conforming product management, ground test management, test flight management, user information, field information, and fault reset. The characteristic analysis phase and the characteristic control phase are carried out simultaneously according to the aircraft development cycle, covering the entire aircraft development cycle, including scheme design, preliminary design, detailed design, trial production and ground development tests, performance verification / identification flight tests and status identification, installation and finalization stage, mass production and service support stage.

2. The method for analyzing and controlling the characteristics of the entire life cycle of aircraft development according to claim 1 is characterized in that: In the characteristic analysis phase, the aircraft characteristics are analyzed and divided into three categories: key characteristics, important characteristics and general characteristics.

3. The method for analyzing and controlling the characteristics of the entire life cycle of aircraft development according to claim 2 is characterized in that: In the characteristic analysis phase, when analyzing aircraft-level characteristics, the aircraft-level functions and performance requirements are used as input to analyze the impact of aircraft-level function and performance failures on the aircraft and determine the aircraft-level characteristic level; In the characteristic analysis phase, when analyzing the structural / system-level characteristics, the structural / system-level functions and performances and the aircraft-level characteristic analysis results are used as inputs to analyze the impact of structural / system-level function and performance failures on the aircraft and determine the structural / system-level characteristic levels; In the characteristic analysis phase, when analyzing the equipment-level characteristics, the equipment's function, performance, failure mode, failure cause, etc. and the structural / system-level characteristic analysis results are used as input to analyze the impact of equipment function and performance failure on the aircraft and determine the function and performance characteristic level of the airborne equipment.

4. The method for analyzing and controlling the characteristics of the entire life cycle of aircraft development according to claim 3 is characterized in that: In the characteristic analysis phase, aircraft-level characteristic analysis is carried out in the scheme design stage; structure / system-level characteristic analysis begins and ends in the preliminary design stage and ends in the detailed design stage; equipment-level characteristic analysis is carried out in the detailed design stage.

5. The method for analyzing and controlling the characteristics of the entire life cycle of aircraft development according to claim 4 is characterized in that: Characteristics control link During the entire life cycle of aircraft development, different elements of key characteristics and important characteristics are controlled at different stages, as follows: During the design phase, aircraft-level requirements and aircraft-level technical status control are performed on key and important characteristics; Conduct structural / system-level requirement control and structural / system-level technical status control on key and important characteristics during the preliminary design phase; During the detailed design phase, the key and important characteristics of the airborne equipment and unit components shall be subject to demand control, technical status control and metrological control; During the trial production and ground development test phase, key characteristics and important characteristics are subject to key process demand control, key process technical status control, key process control, inspection management, measurement management, non-conforming product management, ground test management, user information, field information, and fault zeroing control during production and testing; During the performance verification and identification flight test phase, key characteristics and important characteristics are managed in terms of inspection management, measurement management, non-conforming product management, flight test management, field information management, and fault reporting and zeroing management. During the installation and finalization stage, field information, fault reporting and zeroing management of key and important characteristics shall be controlled; During the batch production and service assurance stages, key characteristics and important characteristics are controlled in terms of technical status, key processes, inspection management, measurement management, non-conforming product management, field service information management, fault reporting and zeroing management.

6. The method for analyzing and controlling the characteristics of the entire life cycle of aircraft development according to claim 5 is characterized in that: It also includes quality supervision; The quality supervision link conducts quality supervision on the characteristic analysis link and the characteristic control link at every stage of the aircraft development life cycle, and the supervision is in the form of internal review or external review.

7. The method for analyzing and controlling the characteristics of the entire life cycle of aircraft development according to claim 6 is characterized in that: It also includes the establishment of a document system; The document system establishment phase establishes a three-layer document system during the feature analysis phase and feature control phase. The first layer of the document system specifies the overall framework of the entire feature analysis phase and feature control phase. The second level of the document system sets forth requirements for characteristic analysis methods at the aircraft level, system level, and equipment level. The third level of the document system specifies the specific contents of control elements at each stage of the aircraft development life cycle.

8. An aircraft development life cycle characteristics analysis and control system, characterized in that: Including feature analysis module and feature control module; The characteristic analysis module is used to analyze the characteristics, including aircraft-level characteristic analysis, structure / system-level characteristic analysis, and equipment-level characteristic analysis; The characteristic control module is used to control the characteristics of the aircraft. The control elements mainly include demand management, technical status management, key process management, inspection management, measurement management, non-conforming product management, ground test management, test flight management, user information, field information, and fault reset. The characteristic analysis module and the characteristic control module carry out characteristic analysis and control synchronously according to the aircraft development cycle, covering the entire aircraft development cycle, including scheme design, preliminary design, detailed design, trial production and ground development testing, performance verification / identification flight testing and status identification, installation and finalization stage, mass production and service support stage.

9. The aircraft development full life cycle characteristics analysis and control system according to claim 8, characterized in that: In the characteristic analysis module, the aircraft characteristics are analyzed and divided into three categories: key characteristics, important characteristics and general characteristics.

10. The aircraft development full life cycle characteristics analysis and control system according to claim 9, characterized in that: In the characteristic analysis module, when analyzing the aircraft-level characteristics, the aircraft-level functions and performance requirements are used as input to analyze the degree of impact of aircraft-level function and performance failure on the aircraft and determine the aircraft-level characteristic level; In the characteristic analysis module, when analyzing the structural / system-level characteristics, the structural / system-level functions and performances and the aircraft-level characteristics analysis results are used as inputs to analyze the impact of structural / system-level function and performance failures on the aircraft and determine the structural / system-level characteristics level; In the characteristic analysis module, when analyzing the equipment-level characteristics, the equipment's function, performance, failure mode, failure cause, etc. and the structural / system-level characteristic analysis results are used as input to analyze the impact of equipment function and performance failure on the aircraft and determine the function and performance characteristic level of the airborne equipment.

11. The aircraft development full life cycle characteristics analysis and control system according to claim 10, characterized in that: In the characteristic analysis module, the analysis of aircraft-level characteristics is carried out in the scheme design stage; the analysis of structure / system-level characteristics begins and ends in the preliminary design stage and ends in the detailed design stage; the analysis of equipment-level characteristics is carried out in the detailed design stage.

12. The aircraft development life cycle characteristics analysis and control system according to claim 11, characterized in that: The characteristic control module controls key characteristics and important characteristics in different stages during the entire life cycle of aircraft development, as follows: During the design phase, aircraft-level requirements and aircraft-level technical status control are performed on key and important characteristics; Conduct structural / system-level requirement control and structural / system-level technical status control on key and important characteristics during the preliminary design phase; During the detailed design phase, the key and important characteristics of the airborne equipment and unit components shall be subject to demand control, technical status control and metrological control; During the trial production and ground development test phase, key characteristics and important characteristics are subject to key process demand control, key process technical status control, key process control, inspection management, measurement management, non-conforming product management, ground test management, user information, field information, and fault zeroing control during production and testing; During the performance verification and identification flight test phase, key characteristics and important characteristics are managed in terms of inspection management, measurement management, non-conforming product management, flight test management, field information management, and fault reporting and zeroing management. During the installation and finalization stage, field information, fault reporting and zeroing management of key and important characteristics shall be controlled; During the batch production and service assurance stages, key characteristics and important characteristics are controlled in terms of technical status, key processes, inspection management, measurement management, non-conforming product management, field service information management, fault reporting and zeroing management.

13. The aircraft development life cycle characteristics analysis and control system according to claim 12, characterized in that: It also includes a quality supervision module; The quality supervision module is used to supervise the quality of characteristic analysis and control at every stage of the aircraft development life cycle, and the supervision is in the form of internal review or external review.

14. The aircraft development full life cycle characteristics analysis and control system according to claim 13, characterized in that: It also includes a file system establishment module; The file system establishment module is used to establish a three-layer file system in the process of feature analysis and control. The first layer of the file system specifies the overall framework of the entire feature analysis module and feature control module. The second level of the document system sets forth requirements for the characteristic analysis systems at the aircraft level, system level, and equipment level. The third level of the document system specifies the specific contents of the control elements at each stage of the aircraft development life cycle.

Images