CN116227975A

CN116227975A - Method for determining life parts of military aircraft

Info

Publication number: CN116227975A
Application number: CN202211675090.5A
Authority: CN
Inventors: 雷长春; 张翠青; 涂美霞; 李凯; 黄轶华; 刘世华; 邹蕊; 刘欣; 吴慧钦; 王志强
Original assignee: Jiangxi Hongdu Aviation Industry Group Co Ltd
Current assignee: Jiangxi Hongdu Aviation Industry Group Co Ltd
Priority date: 2022-12-26
Filing date: 2022-12-26
Publication date: 2023-06-06

Abstract

The invention discloses a method for determining a life part of a military aircraft, which is based on a maintenance analysis method (MSG-3) which is universal for civil aviation and takes reliability as a center, optimizes a logic decision process in system/power device analysis, and obtains whether the life part is the life part after the following analysis is carried out on airborne equipment: 1. whether the product failure mode is related to wear; 2. whether the product functional failure affects the flight safety; 3. whether the functional failure of the product has a task effect or a great economic effect; 4. whether or not the maintenance work is applicable and effective depending on the situation; 5. whether the repair or scrapping work for reducing the failure rate is applicable and effective; according to the catalogue of the longevity parts determined by the method, the aircraft can be guaranteed to improve the attendance rate of the aircraft on the premise of meeting the requirements of flight safety and task completion, the outfield maintenance work and the whole life cycle cost of the aircraft are reduced to the maximum extent, and the market competitiveness is improved.

Description

Method for determining life parts of military aircraft

Technical Field

The invention belongs to the field of aviation general quality characteristic analysis, and discloses a method for determining a life part of a military aircraft.

Background

At present, the GJB 5921-2007 "aircraft longevity inventory Programming requirement" according to the military aircraft longevity inventory "only indicates that" longevity refers to the project which is inconsistent with the whole service life and maintenance period of the aircraft and needs separate and special control in the military aircraft, aero-engine, weapon system and airborne equipment "in the requirements, and the specific longevity determination principle is not defined.

The service life part catalogue of the military aircraft is a direct basis file for controlling the service life of the off-board equipment of the aircraft, the flight safety/task completion of the aircraft can be directly influenced by the absence of items of the on-board equipment in the catalogue, the attendance rate of the aircraft can be reduced due to excessive items, and the total life cycle cost of the aircraft can be increased, so that how to reasonably determine the service life part is related to the use experience of the aircraft after delivering users.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provides a method for determining the life parts of a military aircraft.

The technical scheme of the invention is as follows:

a method for determining the longevity of a military aircraft, based on the general reliability-centric maintenance analysis method (MSG-3) for civil aviation, for the analysis and processing of on-board equipment as follows:

s1: analyzing whether the functional failure of the product is related to the loss, if so, entering S2, otherwise, not including the catalogue of the longevity parts;

s2: analyzing whether the functional failure of the product affects the safety, wherein the affecting the safety comprises the following two layers of meanings: functional failure or secondary damage from functional failure, if the safety is affected, entering S5, otherwise entering S3;

s3: analyzing whether the product functional failure has a task influence or a great economic influence, if so, entering S4, otherwise, not including the catalogue of the longevity parts;

s4: analyzing whether the maintenance work is applicable and effective or not, if so, not including the catalogue of the longevity parts, otherwise, entering S5;

s5: and analyzing whether the repair or scrapping work for reducing the failure rate is applicable and effective, if so, incorporating the life part catalogue, otherwise, not incorporating the life part catalogue.

Further, the tasking effect in S3 means that the job is expedient if the risk of failure can be reduced to an acceptable level; economic impact refers to if the operating costs are lower than the repair costs.

Further, in S3 and S4, the applicable means: the product must exhibit a functionally worsening characteristic for a certain identifiable period of use (P-F interval), and a large part of the item must survive the period of use (P-F interval); the effective means that: work must be able to reduce the risk of failure to ensure safety (safety impact)/work must be able to reduce the risk of failure to an acceptable level (mission impact)/work must be economical, i.e. the cost of work must be lower than the cost of preventing failure (economic impact).

The invention has the beneficial effects that:

according to the catalogue of the longevity parts determined by the method, the aircraft can be guaranteed to improve the attendance rate of the aircraft on the premise of meeting the requirements of flight safety and task completion, the outfield maintenance work and the whole life cycle cost of the aircraft are reduced to the maximum extent, and the market competitiveness is improved.

Drawings

FIG. 1 is a flow chart of the implementation process of the invention.

Detailed Description

The present invention will be further described by way of the following examples, however, the scope of the present invention is not limited to the following examples.

Examples: a method for determining the life of a military aircraft, as shown in fig. 1, is based on the general reliability-centric maintenance analysis method (MSG-3) for civil aviation, which optimizes the logic decision process in the system/power plant analysis, and performs the following analysis and processing on-board equipment:

s2: analyzing whether the functional failure of the product affects the safety, wherein the affecting the safety comprises the following two layers of meanings: functional failure or secondary damage from functional failure, if security is affected then S5 is entered, otherwise S3 is entered, wherein: secondary damage from a functional failure includes a direct detrimental effect on safety (e.g., engine blade flying out to damage sensors) and a combination of a hidden functional failure and another related system or backup failure has a direct detrimental effect on safety (e.g., the inability of fire bottles to extinguish fires and engine fires);

s3: analyzing whether the product functional failure has a mission effect or a significant economic effect, if so, entering S4, otherwise, not including the life part catalogue, wherein: by tasking is meant that the job is expedient if the risk of failure can be reduced to an acceptable level; economic impact means that if the cost of the job is lower than the cost of repair, the job is ready to do;

s4: analyzing whether the maintenance work is applicable and effective or not, if so, not including the catalogue of the longevity parts, otherwise, entering S5, S3 and S4, wherein the application means that: the product must exhibit a functionally worsening characteristic for a certain identifiable period of use (P-F interval), and a large part of the item must survive the period of use (P-F interval); the effective means that: work must be able to reduce the risk of failure to ensure safety (safety impact)/work must be able to reduce the risk of failure to an acceptable level (mission impact)/work must be economical, i.e. the cost of work must be lower than the cost of preventing failure (economic impact).

Taking the landing gear as an example of a landing gear,

s1, analyzing whether the functional failure of the landing gear is related to the loss, analyzing that the landing gear can generate fatigue damage due to the impact load when landing, wherein the failure is related to the loss, and entering S2;

s2, analyzing whether the functional failure of the landing gear affects safety, analyzing that the breakage caused by fatigue damage of the landing gear can cause the aircraft to be damaged when landing, seriously affecting the flight safety, and entering S5;

and S5, analyzing whether the repair or scrapping work of the landing gear is applicable and effective, and repairing and replacing the landing gear according to the set lifting number can reduce the probability of structural damage of the landing gear, so that the landing gear is controlled as a life part according to the logic decision.

While the fundamental and principal features of the invention and advantages of the invention have been shown and described, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.

Claims

1. A method of determining a life span of a military aircraft, comprising: the method is based on a maintenance analysis method (MSG-3) which is universal for civil aviation and takes reliability as a center, and the following analysis and treatment are carried out on airborne equipment:

2. A method of determining a life span of a military aircraft as in claim 1, wherein: the tasking effect in S3 means that the job is appropriate if the risk of failure can be reduced to an acceptable level; economic impact refers to if the operating costs are lower than the repair costs.

3. A method of determining a life span of a military aircraft as in claim 1, wherein: in S3 and S4, the applicable means: the product must exhibit a functionally worsening characteristic for a certain identifiable period of use (P-F interval), and a large part of the item must survive the period of use (P-F interval);

the effective means that: work must be able to reduce the risk of failure to ensure safety (safety impact)/work must be able to reduce the risk of failure to an acceptable level (mission impact)/work must be economical, i.e. the cost of work must be lower than the cost of preventing failure (economic impact).