CN111143409A - Aluminum alloy material design verification method for airworthiness certification - Google Patents
Aluminum alloy material design verification method for airworthiness certification Download PDFInfo
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- 238000012795 verification Methods 0.000 claims abstract description 97
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- G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
- G06F16/24—Querying
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
- G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
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Abstract
The invention provides a design verification method of an aluminum alloy material for airworthiness approval, which comprises the following steps of: matching airworthiness verification parameters of the aluminum alloy material with a verification database Q1: when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the verification database Q1, the aluminum alloy material passes verification; when the airworthiness verification parameters of the aluminum alloy material are unsuccessfully matched with the verification database Q1, the airworthiness verification parameters of the aluminum alloy material are matched with the universal standard database Q2, and when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the universal standard database Q2, the aluminum alloy material passes verification; when the airworthiness verification parameters of the aluminum alloy material are unsuccessfully matched with the universal standard database Q2, and when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the basic global database Q3, the aluminum alloy material passes verification. The embodiment of the invention can greatly improve the airworthiness verification efficiency of the aluminum alloy material, has high reliability, and can improve the reliability and accelerate the examination efficiency.
Description
Technical Field
The invention relates to the technical field of civil aircraft airworthiness, in particular to a design verification method for an aluminum alloy material for airworthiness approval.
Background
The metal materials used in airplanes mainly include aluminum alloys, steel, titanium alloys, copper alloys, and the like. The aluminum alloy mainly comprises 2024, 2124, 7075, 7050, 7475 and other aluminum alloy grades with excellent common performance, and the high-performance aluminum alloys mainly comprise 7150, 7055, 2524, 2026 and 2024 HDT.
The applicant can know through research that: the materials chosen for civil aircraft must comply with the provisions of the relevant provisions of airworthiness regulations. The selected material needs to consider the requirement of airworthiness, passes necessary tests and has certain use experience, thereby meeting the corresponding material specification requirement. In the technology meeting the airworthiness requirement, the selected material also meets the design requirement, and the following principles are also followed:
the economic efficiency is as follows: the selected material should have a certain economic tolerance, the material procurement and processing cost of the aircraft accounts for about 20% -30% of the whole aircraft cost, and in order to ensure the commercial success of the MA700 aircraft, the material cost and the material processing cost of the selected material must be effectively controlled.
Maturity: as a type of commercial aircraft which can be successfully put into operation, the selected material is a mature material which is used or is used by domestic aircrafts at home and abroad.
The advancement is as follows: in order to ensure that the airplane has certain commercial advantages for a long time, the selected materials are the mainstream materials used by civil airplane materials at home and abroad at present.
The implementation performance is as follows: the material selected by the airplane is easy to purchase, transport and have good processing and using performance in the operation and maintenance of manufacturers and subsequent airlines.
Environmental adaptability: the materials selected for the aircraft fully consider environmental applications and the impact on the environment.
At present, the aluminum alloy material design verification of airworthiness approval is mainly carried out by a manual experience method, and the current method is unreliable.
Disclosure of Invention
In view of this, in order to solve at least one technical problem in the prior art, the present invention provides a method for verifying an aluminum alloy material design for airworthiness certification.
The technical scheme of the invention is as follows:
a design verification method for an aluminum alloy material for airworthiness certification comprises the following steps:
s1, collecting the examined airworthiness verification parameters, and writing the collected examined airworthiness verification parameters into a verification database Q1;
collecting general standard parameters for airworthiness verification, and writing the collected general standard parameters into a general standard database Q2;
setting basic global airworthiness verification parameters, and writing the basic global airworthiness verification parameters into a basic global database Q3;
s2, collecting airworthiness verification parameters of the aluminum alloy material to be verified;
s3, matching airworthiness verification parameters of the aluminum alloy material with a verification database Q1:
when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the verification database Q1, the aluminum alloy material passes verification;
when the airworthiness verification parameters of the aluminum alloy material are unsuccessfully matched with the verification database Q1, the airworthiness verification parameters of the aluminum alloy material are matched with the universal standard database Q2, and when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the universal standard database Q2, the aluminum alloy material passes verification;
when the airworthiness verification parameters of the aluminum alloy material are unsuccessfully matched with the universal standard database Q2, and when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the basic global database Q3, the aluminum alloy material passes verification.
The advantages of the invention may be:
the test verification method can greatly improve the airworthiness verification efficiency of the aluminum alloy material, has high reliability, and can improve the reliability and accelerate the examination efficiency.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a schematic view of an aluminum alloy material design verification method for airworthiness certification according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Features and illustrative embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is in no way limited to any specific arrangement and method set forth below, but rather covers any improvements, substitutions and modifications in structure, method, and apparatus without departing from the spirit of the invention. In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
It should be noted that, in the case of conflict, the embodiments and features of the embodiments of the present invention may be combined with each other, and the respective embodiments may be mutually referred to and cited. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The materials selected for the aircraft fully consider environmental applications and the impact on the environment. At present, a systematic aluminum alloy material design verification method for airworthiness approval does not exist, and the systematic and economic aluminum alloy material design and verification method is provided to support the airworthiness evidence obtaining process of civil aircraft aluminum alloy materials.
In some embodiments, a method for certification of an aluminum alloy material design for certification of seaworthiness may include the steps of:
s1, collecting the examined airworthiness verification parameters, and writing the collected examined airworthiness verification parameters into a verification database Q1;
collecting general standard parameters for airworthiness verification, and writing the collected general standard parameters into a general standard database Q2;
setting basic global airworthiness verification parameters, and writing the basic global airworthiness verification parameters into a basic global database Q3;
s2, collecting airworthiness verification parameters of the aluminum alloy material to be verified;
s3, matching airworthiness verification parameters of the aluminum alloy material with a verification database Q1:
when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the verification database Q1, the aluminum alloy material passes verification;
when the airworthiness verification parameters of the aluminum alloy material are unsuccessfully matched with the verification database Q1, the airworthiness verification parameters of the aluminum alloy material are matched with the universal standard database Q2, and when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the universal standard database Q2, the aluminum alloy material passes verification;
when the airworthiness verification parameters of the aluminum alloy material are unsuccessfully matched with the universal standard database Q2, and when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the basic global database Q3, the aluminum alloy material passes verification.
In some embodiments, the method may further comprise:
when the airworthiness verification parameters of the aluminum alloy material are not matched with the basic global database Q3 successfully,
based on each basic global airworthiness verification parameter in the basic global database Q3, performing an experiment on the aluminum alloy material to be verified;
when the aluminum alloy materials completely pass through the experiment of each basic global airworthiness verification parameter in the basic global database Q3, the aluminum alloy materials pass the verification.
In some embodiments, the approved airworthiness verification parameters include one or more of the following: the aluminum alloy approved by the airworthiness department has chemical composition, mechanical property and microstructure.
In some embodiments, the common standard parameters include one or more of the following parameters: chemical compositions, mechanical properties and microstructures of aluminum alloys which are not examined by the airworthiness department but are internationally universal.
In some embodiments, the base global airworthiness verification parameters include one or more of the following: the aluminum alloy which is not approved by the airworthiness department and is not universal internationally is specially used for researching chemical compositions, mechanical properties and microstructures of the aluminum alloy of civil aircrafts.
In some embodiments, the method may further comprise:
when the airworthiness verification parameters of the aluminum alloy material are not matched with the basic global database Q3 successfully,
and carrying out planning test verification on the aluminum alloy material to be verified.
In some embodiments, performing a planned validation test on the aluminum alloy material to be validated may include: and (4) testing the aluminum alloy material based on the experimental outline and the standard text.
In some embodiments, the method may further comprise: and obtaining an experiment report and a conformity instruction file after the experiment is passed.
Fig. 1 is a schematic view of a design verification method for airworthiness certification of an aluminum alloy material according to an embodiment of the present invention.
FIG. 1 shows a method for verifying a design of an aluminum alloy material for airworthiness certification, comprising the following steps;
step 1, screening and selecting an aluminum alloy material for the airplane according to an airplane material selection principle, and preliminarily determining an aluminum alloy material system for the airplane;
step 2, preferentially selecting an aluminum alloy material which is mature in technology, complete in design data, relatively high in cost performance and has certain successful application experience; if the material specification obtains a batch of the CAAC of the civil aviation, the conformity of the material is shown only by adopting an MOC1 conformity description method, the material is not tested and verified, otherwise, the method in the step 3 is adopted for verification;
step 3, for the aluminum alloy material which can not show the conformity in the step 2;
step 4, according to the aluminum alloy material selected in the step 3, determining the selected material specification and the material specification verification test outline to be verified, and submitting the material specification verification test outline to the inspection of the department of the world;
and 5, verifying and evaluating whether the selected material can meet the requirement of the material specification through a test, and applying for a sighting test of a seaworthy department in the process.
Step 6, submitting the materials and the test outline of the aluminum alloy materials formed in the step 3-5 together to a seaworthiness examining and determining department for examination, and submitting data to be approved by a local party if the test result can meet the requirement of seaworthiness compliance; if no compliance is indicated, the method is terminated.
It should be noted that the above-mentioned flow operations may be combined and applied in different degrees, and for simplicity, implementation manners of various combinations are not described again, and those skilled in the art may flexibly adjust the sequence of the above-mentioned operation steps according to actual needs, or flexibly combine the above-mentioned steps, and the like.
It should be noted that the implementation manner of the functional components shown in the above embodiments may be hardware, software, firmware, or a combination thereof. When implemented in hardware, it may be, for example, an electronic circuit, an Application Specific Integrated Circuit (ASIC), suitable firmware, plug-in, function card, or the like. When implemented in software, the elements of the invention are the programs or code segments used to perform the required tasks. The program or code segments may be stored in a machine-readable medium or transmitted by a data signal carried in a carrier wave over a transmission medium or a communication link. A "machine-readable medium" may include any medium that can store or transfer information. Examples of a machine-readable medium include electronic circuits, semiconductor memory devices, ROM, flash memory, Erasable ROM (EROM), floppy disks, CD-ROMs, optical disks, hard disks, fiber optic media, Radio Frequency (RF) links, and so forth. The code segments may be downloaded via computer networks such as the internet, intranet, etc.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (8)
1. A design verification method for an aluminum alloy material for airworthiness certification is characterized by comprising the following steps:
s1, collecting the examined airworthiness verification parameters, and writing the collected examined airworthiness verification parameters into a verification database Q1;
collecting general standard parameters for airworthiness verification, and writing the collected general standard parameters into a general standard database Q2;
setting basic global airworthiness verification parameters, and writing the basic global airworthiness verification parameters into a basic global database Q3;
s2, collecting airworthiness verification parameters of the aluminum alloy material to be verified;
s3, matching airworthiness verification parameters of the aluminum alloy material with a verification database Q1:
when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the verification database Q1, the aluminum alloy material passes verification;
when the airworthiness verification parameters of the aluminum alloy material are unsuccessfully matched with the verification database Q1, the airworthiness verification parameters of the aluminum alloy material are matched with the universal standard database Q2, and when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the universal standard database Q2, the aluminum alloy material passes verification;
when the airworthiness verification parameters of the aluminum alloy material are unsuccessfully matched with the universal standard database Q2, and when the airworthiness verification parameters of the aluminum alloy material are successfully matched with the basic global database Q3, the aluminum alloy material passes verification.
2. The method of claim 1, further comprising:
when the airworthiness verification parameters of the aluminum alloy material are not matched with the basic global database Q3 successfully,
based on each basic global airworthiness verification parameter in the basic global database Q3, performing an experiment on the aluminum alloy material to be verified;
when the aluminum alloy materials completely pass through the experiment of each basic global airworthiness verification parameter in the basic global database Q3, the aluminum alloy materials pass the verification.
3. The method of claim 1, wherein the approved airworthiness verification parameters comprise one or more of the following:
the aluminum alloy approved by the airworthiness department has chemical composition, mechanical property and microstructure.
4. The method of claim 1, wherein the common standard parameters include one or more of the following parameters:
chemical compositions, mechanical properties and microstructures of aluminum alloys which are not examined by the airworthiness department but are internationally universal.
5. The method of claim 1, wherein the base global airworthiness verification parameters comprise one or more of:
the aluminum alloy which is not approved by the airworthiness department and is not universal internationally is specially used for researching chemical compositions, mechanical properties and microstructures of the aluminum alloy of civil aircrafts.
6. The method of claim 1, further comprising:
when the airworthiness verification parameters of the aluminum alloy material are not matched with the basic global database Q3 successfully,
and carrying out planning test verification on the aluminum alloy material to be verified.
7. The method according to any one of claims 1 to 6, wherein the aluminium alloy material to be verified is subjected to a planned verification test comprising:
and (4) testing the aluminum alloy material based on the experimental outline and the standard text.
8. The method of claim 7, further comprising:
and obtaining an experiment report and a conformity instruction file after the experiment is passed.
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| CN112782362A (en) * | 2020-12-29 | 2021-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Method for verifying seaworthiness conformance of civil aircraft structural member laser forming technology |
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Application publication date: 20200512 |