阅读说明：本技术 一种面向飞机维修的系统划分码编码方法 (System division code coding method for airplane maintenance ) 是由 勉力财 张九民 白茹冰 于 2020-12-29 设计创作，主要内容包括：本发明属于航空技术设计领域,公开了一种面向飞机维修的系统划分码编码方法。步骤一：获取飞机的总体、系统和分系统设计方案,将分系统分解为单元体；并梳理飞机系统、分系统和单元体之间的隶属关系；步骤二：对飞机系统进行系统编码,系统编码作为飞机系统划分码的第一部分,由第一、二位数字表示；步骤三：基于飞机系统编码,对飞机分系统进行分系统编码,分系统编码作为飞机系统划分码的第二部分,由第三位数字表示；步骤四：基于飞机分系统编码,对飞机的不同型号单元体进行单元体编码,作为飞机系统划分码的第三部分,由第五、六位数字表示；步骤五：基于飞机单元体编码,对装机数量大于1的同型号单元体的不同个体进行流水号编码。(The invention belongs to the field of aviation technical design and discloses a system partition code encoding method for airplane maintenance. The method comprises the following steps: acquiring the design scheme of the whole system and the subsystem of the airplane, and decomposing the subsystem into unit bodies; and carding membership relations among the airplane system, the subsystems and the unit bodies; step two: performing system coding on the aircraft system, wherein the system coding is used as a first part of a division code of the aircraft system and is represented by a first digit and a second digit; step three: performing subsystem coding on the aircraft subsystem based on the aircraft system code, wherein the subsystem coding is used as a second part of the aircraft system division code and is represented by a third digit; step four: based on the airplane subsystem codes, unit body codes are carried out on unit bodies of different models of airplanes, and the unit bodies are used as a third part of airplane system division codes and are represented by fifth and sixth digits; step five: based on the airplane unit body coding, serial number coding is carried out on different individuals of unit bodies with the same model number, the installed number of which is more than 1.)

1. A system division code coding method for airplane maintenance is characterized in that: the method comprises the following steps:

the method comprises the following steps: acquiring an overall design scheme, an aircraft system design scheme and an aircraft subsystem design scheme, and decomposing the aircraft subsystem into unit bodies; and carding membership relations among the airplane system, the airplane subsystem and the unit bodies;

step two: performing system coding on the aircraft system, wherein the system coding is used as a first part of a division code of the aircraft system and is represented by a first digit and a second digit;

step three: performing subsystem coding on the aircraft subsystem based on the aircraft system code, wherein the subsystem coding is used as a second part of the aircraft system division code and is represented by a third digit;

step four: based on the airplane subsystem codes, unit body codes are carried out on unit bodies of different models of airplanes, and the unit bodies are used as a third part of airplane system division codes and are represented by fifth and sixth digits;

step five: based on the airplane unit body coding, serial number coding is carried out on different individuals of unit bodies with the same model number, the installed number of which is more than 1.

2. The aircraft maintenance-oriented system division code encoding method of claim 1, wherein: in the second step, the aircraft systems are associated equipment combinations configured for completing a specific function, and each aircraft system comprises basic components and relevant mechanical control devices, electrical control devices and hydraulic control devices;

when a power source powers a single component or a single system, the power source is encoded in the system powered by the power source;

when a power source provides power to multiple systems, the power source is encoded individually as a system.

3. The aircraft maintenance-oriented system division code encoding method of claim 2, wherein: in the third step, if a certain subsystem needs to be further divided into subsystems; and coding the subdivision system, wherein the subdivision system code is used as a second part of the division code of the airplane system and is represented by a fourth digit.

4. The aircraft maintenance-oriented system division code encoding method of claim 3, wherein: in the third step, if a certain subsystem does not need to be divided into sub-subsystems; the fourth digit is 0.

5. The aircraft maintenance-oriented system division code encoding method of claim 4, wherein: when the unit cell is not subdivided and the number is 1, the sixth bit of the unit cell code cannot be 0, and the seventh and eight bits are represented by 00.

6. The aircraft maintenance-oriented system division code encoding method of claim 5, wherein: when the unit body consists of 2-9 components, the sixth bit of the unit body code is 0, the fifth bit of the unit body component code is the same as the fifth bit of the unit body code, and the sixth bit of the unit body component code is represented by 1-9.

7. The aircraft maintenance-oriented system division code encoding method of claim 6, wherein: when a cell is shared by multiple subsystems or sub-subsystems, the third and fourth bits of the cell code are 00.

8. The aircraft maintenance-oriented system division code encoding method of claim 6, wherein: and when the unit bodies are the same type of pipelines or torsion bars with different specifications, serial number coding is carried out according to the unit bodies with the same type.

Technical Field

The invention belongs to the field of aviation technical design, and relates to a system partition code encoding method for airplane maintenance.

Background

The new generation of airplanes more adopt state-based maintenance technologies, and accurate maintenance becomes the dominant aircraft maintenance work. The method comprises the steps that initial configuration data of an airplane are required to be established for accurate maintenance, wherein the initial configuration data reflect the product composition of the airplane and comprise product lists and product installation position information; in addition, the hierarchical relationship among systems, subsystems, sub-subsystems and detachable components of the airplane and the information such as basic information, membership, installation position, working environment and the like of each installed unit body are expressed, so that proper maintenance work can be carried out according to the specific situation of each unit body. Therefore, the basis for realizing accurate maintenance is to uniquely identify each unit body of the machine. SNS codes (system division codes) can identify aircraft, systems, components, and affiliations between them. The SNS numbers specified by the standards typically consist of 6-bit 3-parts, and cannot identify every LRU on the aircraft, without the use of individual piece-based precision maintenance and state-of-the-art control. Therefore, in order to meet the data requirements of the state-based management of the information assurance, unique identification of each piece of LRU of the installation needs to be realized.

Disclosure of Invention

The SNS coding mode specified by the GJB6600 and the GJB4855 is expanded from 6 bits to 8 bits to form an SNS coding mode consisting of four parts, and an 8-bit SNS coding flow and a coding rule are established. The coding of the unit bodies with non-unique installation number is completed by increasing the serial number of the single machine number in the fourth part, so that each unit body of the installation machine is guaranteed to have a system division code with unique identification.

A system division code coding method for airplane maintenance comprises the following steps:

the method comprises the following steps: acquiring a total design scheme, a system design scheme and a subsystem design scheme of the airplane, and decomposing the subsystem into unit bodies; and carding membership relations among the airplane system, the subsystems and the unit bodies;

step two: performing system coding on the aircraft system, wherein the system coding is used as a first part of a division code of the aircraft system and is represented by a first digit and a second digit;

step three: performing subsystem coding on the aircraft subsystem based on the aircraft system code, wherein the subsystem coding is used as a second part of the aircraft system division code and is represented by a third digit;

step four: based on the airplane subsystem codes, unit body codes are carried out on unit bodies of different models of airplanes, and the unit bodies are used as a third part of airplane system division codes and are represented by fifth and sixth digits;

step five: based on the airplane unit body coding, serial number coding is carried out on different individuals of unit bodies with the same model number, the installed number of which is more than 1.

Further, in the second step, the aircraft systems are associated equipment combinations configured for completing a specific function, and each system comprises basic components and relevant mechanical control devices, electric control devices and hydraulic control devices;

when a power source powers a single component or a single system, the power source is encoded in the system powered by the power source;

when a power source provides power to multiple systems, the power source is encoded individually as a system.

Further, in the third step, if a certain subsystem needs to be further divided into sub-subsystems; and coding the subdivision system, wherein the subdivision system code is used as a second part of the division code of the airplane system and is represented by a fourth digit.

Further, in the third step, if a certain subsystem does not need to be divided into sub-subsystems; the fourth digit is 0.

Further, when the unit cell is not subdivided and the number is 1, the sixth bit of the unit cell code cannot be 0, and the seventh and eighth bits are represented by 00.

Further, when the unit body is composed of 2-9 components, the sixth bit of the unit body code is 0, the fifth bit of the unit body component code is the same as the fifth bit of the unit body code, and the sixth bit of the unit body component code is represented by 1-9.

Further, when a cell is shared by a plurality of subsystems or a plurality of subsystems, the third and fourth bits of the cell code are 00.

And further, when the unit bodies are the same type of pipelines or torsion bars with different specifications, serial number coding is carried out according to the unit bodies with the same type.

Drawings

FIG. 1 is a schematic illustration of an aircraft system division code;

FIG. 2 is a flow chart of a system partition code encoding method for aircraft maintenance;

FIG. 3 is a schematic diagram of membership between aircraft systems, subsystems and cell bodies.

Detailed Description

The invention is further illustrated by the following specific embodiments:

the SNS coding mode specified by the GJB6600 and the GJB4855 is expanded from 6 bits to 8 bits to form an SNS coding mode consisting of four parts, and an 8-bit SNS coding flow and a coding rule are established. The coding of the unit bodies with non-unique installation number is completed by increasing the serial number of the single machine number in the fourth part, so that each unit body of the installation machine is guaranteed to have a system division code with unique identification, as shown in fig. 1.

A precision repair oriented product coding method, as shown in fig. 2, the product coding method comprising:

step 1: collecting the overall scheme, the system scheme and the sub-system scheme of the airplane. According to the membership of each level of the airplane, the airplane is divided into subsystems from the system to the subsystem and the subsystem until the airplane is decomposed into each unit body, as shown in fig. 3.

Step 2: based on the overall scheme of the airplane, the airplane system is coded according to the division of the airplane in the overall scheme. The system code is represented by the 1 st and 2 nd digit as the first part of the SNS code. The representation of the systematic code is x-00-00-00. The system code is used for reference of the GJB4855 system code. If the system is not specified in the GJB4855, the Standby number custom representation can be started. (see Table 1 for system code examples)

a) A system is a combination of interrelated devices configured to perform a particular function. Each system includes its basic components and all mechanical, electrical and hydraulic controls associated with the system.

b) When a power source (e.g., an electrical, pneumatic, or hydraulic source) powers a single component or a single function system, then the power source is encoded in the component or system to which the power source is provided.

c) When one power source provides power for two or more systems, the main power source is independently coded (see a power system and a hydraulic source system in table 1), and the auxiliary power sources are respectively coded in related systems/chapters (for example, the power source, the air source, the hydraulic source and the like provide auxiliary power sources for the undercarriage and the cabin door, and the auxiliary power sources are coded in the undercarriage and the cabin door chapters).

TABLE 1 systematic encoding example

Name of system	Encoding	Remarks for note
			Flight control system	27-00-00-00
Fuel oil subsystem	28-00-00-00
			Power supply system	24-00-00-00
Hydraulic source system	29-00-00-00
			Liquid cooling system	90-00-00-00	Starting standby number

And step 3: based on the system scheme of the airplane, the subsystems of the airplane are divided according to the system scheme of the airplane, and the subsystems are coded. The subsystem is represented by the 3 rd digit as the second part of the SNS code. A subsystem is represented by the form XXX-0-00-00. The subsystem code is referenced with GJB 4855. If the subsystem is not in the GJB4855, the Standby number custom representation may be launched. Some subsystems are complex and require further division into component-subsystems, which are represented by the 4 th digit as the second part of the SNS code. The expression of the sub-division system is XXX-XX-00-00. Numbering is done in sequence from 1 to 9, depending on the complexity of the subsystem. (examples of subsystem and subsystem codes are shown in Table 2) Table 2 examples of subsystem and subsystem codes

Subsystem/subsystem name	Encoding	Remarks for note
			Aileron control subsystem	27-10-00-00
Rudder control subsystem	27-20-00-00
			Storage subsystem	28-10-00-00
Fuel tank divides branch system	28-11-00-00
			Ventilation and separation system for fuel tank	28-12-00-00
Distribution subsystem	28-20-00-00

And 4, step 4: based on the subsystem scheme of the airplane, the unit bodies of the airplane are coded according to coding rules. The haplotype type is the third part of SNS coding and consists of the 5 th and 6 th digits. The unit cell type is expressed in the form of "× -00". (see Table 3 for Unit body Assembly, coding examples of Unit bodies)

a) When no further division is needed below the unit cell, which is the final division in the SNS, the identification of specific devices can be accomplished. At this time, the 6 th position cannot be 0, the 4 th part, the 7 th and 8 th positions, are directly represented by 00 in the form of XXXX-XX-01-00 to XX-XX-99-00, and 10, 20, 30 … 90 is encountered to automatically skip over

b) If the unit cell is complex and needs to be divided continuously, the unit cell components can be coded by 10, 20, 30 … 90, and the division of the unit cell can be represented by 11, 12, 13 … 19 and the like.

c) When the installed number of the unit bodies on the airplane is more than or equal to 2, the unit bodies are not finally divided in the SNS at the moment, and the unit bodies need to be further divided by using a fourth part code.

d) When some components, devices in the system are common to many other subsystems or sub-subsystems in the system, these components, devices should be discussed under the heading of the system and divided in the second or third section. For example: independent steering engines, load mechanisms, pull rods, rocker arms, transmission shafts, universal joints, supports, pull rods and the like in a 27-chapter operating system are common to a plurality of subsystems or sub-subsystems in the chapter, so that the components and equipment are coded under the titles of 27-00-00-00.

TABLE 3 Unit body Assembly, Unit body coding example

Unit body assembly, unit body name	Encoding	Remarks for note
			Flight control computer	27-00-01-00
Main flight control panel	27-00-02-00
			Aileron control module	27-10-01-00
Aileron actuating cylinder	27-10-02-00
			Course control device	27-20-10-00
Pedal component	27-20-11-00
			Load mechanism	27-20-12-00
Outside rudder actuator cylinder	27-20-21-00
			Inner rudder actuator cylinder	27-20-22-00
Gravity oil filler port assembly	28-11-01-00
			One-way valve	28-11-02-00
Deposit valve	28-11-03-00

And 5: and (3) coding the unit bodies which are not unique to the installation of the airplane according to the coding rule on the basis of the installation number of the airplane unit bodies. (examples of the code of the installed unique unit are shown in Table 4)

a) The single machine quantity serial number is a unique identification code for the unit bodies with non-unique installed quantity, and is represented in the form of x-01-x-99, 10, 20, 30 … 90 does not need to jump in the middle, and serial numbers can be carried out.

b) The single machine quantity serial number is a unique identification code for pipelines and torsion bars of the same type and different specifications, and is represented in the form of (XXX) -XXX-01-XXX-99), 10, 20 and 30 … 90 are encountered in the middle, no jump number is needed, and serial numbers can be carried out.

c) The standard components and joint type unit bodies adopted in a structure or a system in a large number do not need serial number identification.

TABLE 4 installation of non-unique Unit body code examples

Installation non-unique unit body name	Encoding	Remarks for note
			Flight control computer	27-00-01-01
Flight control computer	27-00-01-02
			Flight control computer	27-00-01-03
Aileron control module	27-10-01-01
			Aileron control module	27-10-01-02
One-way valve	28-11-02-01
			One-way valve	28-11-02-02
One-way valve	28-11-02-03
			One-way valve	28-11-02-04
One-way valve	28-11-02-05
			One-way valve	28-11-02-06
One-way valve	28-11-02-07
			One-way valve	28-11-02-08
One-way valve	28-11-02-09
			One-way valve	28-11-02-10
One-way valve	28-11-02-11

TABLE 5 aircraft code example