CN112699638A - System division code coding method for airplane maintenance - Google Patents
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- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000012423 maintenance Methods 0.000 title claims abstract description 14
- 238000009960 carding Methods 0.000 claims abstract description 3
- 238000005192 partition Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 description 11
- 210000004027 cell Anatomy 0.000 description 8
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 6
- 239000002828 fuel tank Substances 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000009897 systematic effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 210000005056 cell body Anatomy 0.000 description 1
- 210000003850 cellular structure Anatomy 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 102000054766 genetic haplotypes Human genes 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F40/00—Handling natural language data
- G06F40/10—Text processing
- G06F40/12—Use of codes for handling textual entities
- G06F40/126—Character encoding
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
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Abstract
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.
Description
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
Claims (8)
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.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS55109030A (en) * | 1979-02-14 | 1980-08-21 | Shiro Okamura | Coding system |
| CN103020332A (en) * | 2012-10-22 | 2013-04-03 | 南京航空航天大学 | Intelligent virtual maintenance training system for civil aircraft |
| CN103870906A (en) * | 2012-12-14 | 2014-06-18 | 中航通飞研究院有限公司 | Encoding method of airplane parts |
| CN104991938A (en) * | 2015-07-07 | 2015-10-21 | 中国商用飞机有限责任公司 | Construction method for service view configuration database of civil airplane |
-
2020
- 2020-12-29 CN CN202011612623.6A patent/CN112699638A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS55109030A (en) * | 1979-02-14 | 1980-08-21 | Shiro Okamura | Coding system |
| CN103020332A (en) * | 2012-10-22 | 2013-04-03 | 南京航空航天大学 | Intelligent virtual maintenance training system for civil aircraft |
| CN103870906A (en) * | 2012-12-14 | 2014-06-18 | 中航通飞研究院有限公司 | Encoding method of airplane parts |
| CN104991938A (en) * | 2015-07-07 | 2015-10-21 | 中国商用飞机有限责任公司 | Construction method for service view configuration database of civil airplane |
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| Title |
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| 张嘉华 等: "试论军机用户技术资料的编码系统", 飞机设计, no. 02, 30 June 1997 (1997-06-30), pages 44 - 53 * |
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| 舒文科: ""A．T．A章节号在航空技术出版物中的应用", 航空标准化与质量, no. 1, 28 February 1994 (1994-02-28), pages 42 - 44 * |
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| 高军 等: "飞机系统的划分和编号及其在工程使用上的作用", 电子产品可靠性与环境试验, no. 01, 31 March 2006 (2006-03-31), pages 60 - 64 * |
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