CN112434909B - A batch production satellite AIT process generation method based on element relationships - Google Patents

Abstract

Under the condition of meeting the requirement of the whole project of the satellite, a single-star skeleton flow formed by each flow module is established based on the matching relation among elements of working projects of the satellite AIT stage, the matching condition based on the element relation among the flow modules in the skeleton flow is obtained, a single-star possible solution flow set is obtained by calculation according to the matching condition based on the element relation among the flow modules in the skeleton flow, the possible solution flow set of the batch satellite is obtained according to the delivery time of the satellite and the limiting requirement of element resource guarantee conditions, and the optimal batch production flow of a target range is obtained by comparison; in the process of executing the flow, the rest items after the flow is interrupted are used as new target ranges, and the same calculation and comparison methods are adopted to obtain the dynamically optimized batch satellite AIT flow. The invention greatly improves the development progress of the batch production satellite, greatly saves resources, reduces the development cost and improves the utilization rate of production resources and the working efficiency.

Description

A batch production satellite AIT process generation method based on element relationships

Technical field

The invention relates to a method for generating AIT process for batch production satellites based on element relationships, which is applied to satellites, especially the field of AIT process design for batch production satellite development.

Background technique

In the satellite development process, after the development of component products is completed, the component products need to be integrated and assembled to form a complete satellite. After completing the testing and testing of the entire star, it is confirmed that the entire satellite meets the design and user requirements, and then the launch is carried out according to the requirements. The state of the field completes the final assembly and testing of the satellite before leaving the factory, and transports the satellite to the launch site to carry out launch work at the launch site. The integration, final assembly, and testing (including testing) of the entire satellite for component products is AIT. The satellite development stage corresponding to AIT is the satellite AIT stage. The satellite development process corresponding to AIT is the satellite AIT process.

In the satellite AIT process, it is generally necessary to conduct final assembly and testing at various stages, and complete mechanical tests, thermal tests, magnetic tests, EMC tests, and system-level docking with carrier, user and other systems as required. The traditional domestic satellite AIT process is based on several large test projects, and the traditional project sequence is fixed. When a project is unexpectedly interrupted, one has to wait for the project to restart, or continue with subsequent projects while enduring the necessary risks. .

In recent years, with the increase in the number of satellites developed and the construction needs of constellation systems, a series of satellites in the same or similar status have been developed in batches. In order to make full use of various development resources such as personnel and test sites and ensure the progress of development, the batch production satellite development model is gradually different from the single-satellite model, and the corresponding batch production satellite AIT process is also different from the single-satellite AIT process. In this regard, a typical domestic mass-produced satellite development project is the Beidou navigation satellite system. To adapt to the batch production satellite development of my country's Beidou global network and meet the engineering construction needs of rapid network, shorter and shorter satellite development and launch cycles are required. The most critical thing is to optimize the satellite AIT process while ensuring quality standards. An optimization method was adopted in the development of Beidou global network batch production satellites, which achieved the effect of optimizing the progress of a single satellite for 3 months. The batch production satellites also completed the Beidou network plan ahead of schedule.

Contents of the invention

The problem solved by the present invention is to overcome the shortcomings of traditional satellite AIT process design and provide a batch satellite AIT process generation method based on element relationships. The method of the present invention is based on the matching relationship between elements, which is the core relationship of the work project connection in the satellite AIT stage. Under the condition of meeting the requirements of the overall satellite project, the optimal (ie, the shortest cycle) batch production satellite AIT process can be designed, and It can achieve dynamic optimization during the execution process, greatly improving the development progress of batch production satellites; greatly reducing the number of personnel handovers between projects, saving resources such as manpower and equipment, thereby reducing development costs, improving production resource utilization and work efficiency, and can simplify the AIT process optimization applied to a single satellite.

The technical solution of the present invention is:

A batch production satellite AIT process generation method based on element relationships includes the following steps:

1) Determine the work content that multiple satellites need to carry out in the AIT phase, decompose the work content step by step until it cannot be divided anymore, obtain the work items that cannot be further divided, and use them as the basic unit of the work item set for the single-satellite AIT stage;

2) Determine the core elements of each work item in the satellite AIT stage to form an AIT work element set with the required granularity; determine the specific content of the core elements corresponding to each work item in the work item set in step 1); the core elements It is composed of several or all of the star elements, human elements, machine elements, material elements and environmental elements;

3) For each single satellite, analyze and determine the work projects that must be carried out in a fixed order, and form a list of project relationships with a tight coupling relationship for the single satellite; the remaining work projects that have no fixed order requirements are regarded as loosely coupled projects;

4) For each single star, the work items in the tightly coupled project relationship list are arranged in a fixed order to form a process module. At the same time, each loosely coupled project is also used as a process module to form a single star composed of various process modules. skeleton process;

5) Use the first item in the process module as the input item of the process module, and use the last item in the process module as the output item of the process module. According to the matching conditions of the element relationships between process modules, traverse all process modules and analyze Whether there is a match between the two process modules;

6) Permutation and combination, giving the possible arrangement schemes of all process modules, each scheme is regarded as a possible solution process set, and multiple possible solution process sets are obtained; that is, a possible solution is formed that includes the entire process of all work items in the satellite AIT stage process set;

7) Based on the factory order determined by the satellite launch time requirements and the restriction requirements of the resource guarantee conditions corresponding to the core elements of each work project, screen out a set of possible solution processes that meet the restriction requirements;

8) According to the user's detailed restriction requirements and weighting principles for satellite launch time, the possible solution processes obtained from step 7) are intensively compared to obtain the optimal set of possible solution processes as a mass production process to execute the production task.

During the execution of the mass production process, if the process execution of the mass production process is interrupted, a new process module is formed with the remaining unfinished work items of each satellite, and steps 6) to 8) are performed again to obtain the optimal batch production of the remaining unfinished items. The process is the dynamic optimization during the execution of the batch production satellite AIT process.

When the number of batch-produced satellites is set to 1, it is the generation method of the single-satellite AIT process.

The advantages of the present invention compared with the prior art are:

1) The present invention provides steps for realizing a batch production satellite AIT process generation method, which can obtain the batch production satellite AIT process with the shortest development cycle while meeting the overall satellite project requirements.

2) The method of the present invention is not only suitable for the AIT process design before the satellite carries out AIT work, but also suitable for dynamic optimization in the execution of the AIT process.

3) In addition to being suitable for the development of batch-produced satellites, the method of the present invention can also set the number of batch-produced satellites to 1, thereby being suitable for the development of single-satellites.

Description of the drawings

Figure 1 is a schematic diagram of the batch production satellite AIT process generation method based on element relationships of the present invention.

Figure 2 is a schematic flow chart of the single-star AIT stage before the present invention is adopted.

Figure 3 is a schematic flow diagram of the dual-star AIT stage before the present invention is adopted.

Figure 4 is a schematic flow diagram of a single satellite skeleton after adopting the present invention.

Figure 5 is a schematic flow diagram of the dual-star AIT stage after optimization using the present invention.

Detailed ways

This method can obtain the batch-production satellite AIT process with the shortest development cycle; and can achieve dynamic optimization during the execution of the process; in addition to being suitable for batch-production satellites, it is also suitable for single-satellite development, and can achieve dynamic optimization during the execution of the process. optimization.

Figure 1 shows a schematic diagram of the batch production satellite AIT process generation method based on element relationships of the present invention, which includes the following steps:

1) Determine the work content that multiple satellites need to carry out in the AIT phase, decompose the work content step by step until it cannot be divided anymore, obtain the work items that cannot be further divided, and use them as the basic unit of the work item set for the single-satellite AIT stage;

2) Determine the core elements of each work item in the satellite AIT stage to form an AIT work element set with the required granularity; determine the specific content of the core elements corresponding to each work item in the work item set in step 1); the core elements It is composed of several or all of the star elements, human elements, machine elements, material elements and environmental elements;

3) For each single satellite, analyze and determine the work projects that must be carried out in a fixed order, and form a list of project relationships with a tight coupling relationship for the single satellite; the remaining work projects that have no fixed order requirements are regarded as loosely coupled projects;

4) For each single star, the work items in the tightly coupled project relationship list are arranged in a fixed order to form a process module. At the same time, each loosely coupled project is also used as a process module to form a single star composed of various process modules. skeleton process;

5) Use the first item in the process module as the input item of the process module, and use the last item in the process module as the output item of the process module. According to the matching conditions of the element relationships between process modules, traverse all process modules and analyze Whether there is a match between the two process modules;

6) Permutation and combination, giving the possible arrangement schemes of all process modules, each scheme is regarded as a possible solution process set, and multiple possible solution process sets are obtained; that is, a possible solution is formed that includes the entire process of all work items in the satellite AIT stage Process set.

7) Based on the factory time sequence determined by the satellite launch time requirements and the restriction requirements of the resource guarantee conditions corresponding to the core elements of each work project, screen out a set of possible solution processes that meet the restriction requirements;

8) According to the user's detailed restriction requirements and weighting principles for satellite launch time, the possible solution processes obtained from step 7) are intensively compared to obtain the optimal set of possible solution processes as a mass production process to execute the production task.

During the execution of the mass production process, if the process execution of the mass production process is interrupted, a new process module is formed with the remaining unfinished work items of each satellite, and steps 6) to 8) are performed again to obtain the optimal batch production of the remaining unfinished items. The process is the dynamic optimization during the execution of the batch production satellite AIT process.

When the number of batch-produced satellites is set to 1, it is the generation method of the single-satellite AIT process.

Specific steps are as follows:

(1) Decompose the work content and determine the set of work items for a single satellite in the AIT stage. According to the needs of satellite development, determine the work content that needs to be carried out by the satellite in the AIT stage, decompose the work content step by step until it can no longer be decomposed, and obtain the work items that cannot be decomposed again and serve as the basic unit of the work items in the single-satellite AIT stage. gather. The principle for determining whether a project cannot be further divided is: the granularity of the project cannot be divided again in time, and once the project starts, it cannot be divided or interrupted until the end of the project. If it is divided or interrupted again, the entire project can only be restarted and completed. . For example, the entire satellite test work content can be divided into test items in different stages and different states, and the thermal test work content is generally non-decomposable items.

(2) Determine the core elements of each work project in the satellite AIT stage and the specific content of the core elements of each work project. Based on the determined set of work items for a single satellite in the AIT stage, determine the core elements of each work item in the AIT stage of the satellite to form an AIT work element set; for each work item of a single satellite in the AIT stage, determine the specific content of its elements . Each of the mentioned factors refers to the matching conditions when one project is connected to another project.

Generally, an element set can be formed from the five elements of "star, people, machine, material, and environment". The content corresponding to the five elements is as follows:

① The "star" element, that is, the status of the satellite related to the project, is a collection of three aspects: hardware status, software status, and overall satellite combination status. Each project has two "star" elements, input status and output status, which respectively correspond to the satellite status required to carry out the project and the satellite status after the project is carried out. The hardware status refers to the corresponding equipment that composes the satellite and needs to be installed in a complete set of satellites; the software status refers to the corresponding software loaded in the equipment; the entire satellite combination status refers to the overall assembly status of the satellite, including the entire satellite placement status and the status of each module. The entire satellite placement status Generally, there are two states: horizontal placement and vertical placement. The state of each compartment generally includes platform open/closed, load bay open/closed, etc. The definition and classification of the entire satellite combination state of different satellites will be different according to the characteristics of the satellite. . The three elements of hardware status, software status, and overall star combination status are treated independently of each other.

Depending on the granularity of the method, it can be implemented at a coarser level, giving the total hardware status of the satellite, the total software status of the satellite, and the total satellite combination status, such as hardware, software, and the entire satellite combination status. ; It can also be implemented at a finer level, giving a collection of each device, each software, and the overall star combination status, such as hardware 1, hardware 5,..., software 1, software 3,..., the entire star is placed horizontally, and the platform Open and load bay closed; this means that the hardware equipment such as Hardware 1 and Hardware 5 are complete, the software such as Software 1 and Software 3 are complete, and the satellite is in a state where the entire satellite is placed horizontally, the platform is open, and the load bay is closed. Each of these is called a "star" element.

②The "people" element, that is, the personnel conditions required to carry out the project, is a collection of four aspects: assembly personnel, testers, test personnel, and overall personnel. The general assembly personnel, testers, test personnel, and general personnel are respectively the various personnel responsible for the final assembly operation, the various personnel for the entire satellite test, the various personnel for the entire satellite test, and the various personnel for the overall work of the entire satellite. The four elements of assembly personnel, testers, testing personnel, and overall personnel are handled independently of each other.

Depending on the granularity of the method, it can be implemented at a coarser level, giving a collection of total assembly personnel, total testing personnel, total testing personnel, and total overall personnel, such as assembly personnel, testing personnel, testing personnel, and overall personnel. ; It can also be implemented at a finer level, giving a detailed set of personnel from four aspects, such as final assembly fitters, final assembly electrical installation personnel,..., test directors, test power supply personnel,..., thermal test directors, thermal test control personnel ,..., the overall personnel of the satellite, the overall personnel of the power supply,..., which means the general assembly personnel such as the general assembly fitters and the general assembly electrical installation personnel, the test personnel such as the test commander and the test power supply personnel, the thermal test commander and the thermal test controller and other test personnel, satellite The state that all personnel including general personnel and power supply personnel are fully prepared. Each of these is called a "human" element.

③The "machine" element, that is, the ground equipment support conditions required to carry out the project, is a collection of satellite ground tooling equipment and ground test equipment. Ground tooling equipment and ground test equipment are various types of ground equipment used for satellite assembly operations and complete satellite testing respectively. The two elements of ground tooling equipment and ground testing equipment are handled independently of each other.

Depending on the granularity of the method, it can be implemented at a coarser level, giving a collection of total assembly personnel, total testing personnel, total testing personnel, and total overall personnel, such as ground tooling equipment and ground testing equipment; it can also be implemented at a coarser level. Implementation at a finer level provides a detailed set of two aspects of ground equipment, such as ground support vehicles, solar wing deployment supports,..., general control test equipment, power supply test equipment,...; that is, ground support vehicles and solar wing deployment Ground tooling equipment such as brackets, general control test equipment, power supply test equipment and other ground test equipment are in complete condition. Each of these items is called a "machine" element.

④ "Materials" refers to the auxiliary material conditions required to carry out the project, especially the scarce material resource conditions. It is a collection of fasteners, brackets and auxiliary materials. Fasteners, brackets, and auxiliary materials are various types of auxiliary materials used for fastening, support, and other auxiliary operations. The three elements of fasteners, brackets and auxiliary materials are processed independently of each other.

Depending on the granularity of the method, it can be implemented at a coarser level, giving a collection of total fasteners, total brackets, and total auxiliary materials, such as fasteners, brackets, and auxiliary materials; it can also be implemented at a finer level. Realization, giving a detailed set of three auxiliary materials, such as screws, gaskets,..., camera brackets, battery brackets,..., nylon ties, silicone rubber,...; that is, fasteners such as screws and gaskets, The camera holder, battery holder and other brackets, as well as auxiliary materials such as nylon ties and silicone rubber are fully prepared. Each of these items is called a "material" element.

⑤ "Ring" refers to the environmental conditions required to carry out the project. It is a collection of ground environmental conditions required for satellite assembly or testing. Usually the environmental conditions include electrical measurement stations, noise test rooms, random vibration dynamics test rooms, and thermal vacuum tanks. EMC test room, leak detection room, etc.; under special circumstances, external conditions such as weather and geology may be included in field tests.

Depending on the granularity of the method, it can be implemented at a coarser level, giving a set of total environmental conditions, such as environmental conditions; it can also be implemented at a finer level, giving a set of refined environmental conditions, such as testing and testing work. Position, temperature; that is, it represents the environmental conditions of the test station and ambient temperature. Each of these items is called a "ring" element.

The AIT work element set can use a coarse-grained method, expressed as {hardware, software, whole star combination status}; {hardware, software, whole star combination status}; {general assembly personnel, testers, test personnel, overall personnel}, {Ground tooling equipment, ground testing equipment}, {fasteners, brackets, auxiliary materials}, {environmental conditions}, or further refinement. Among them, "{hardware, software, whole star combination state}" that appears twice corresponds to the "star" aspects of the input state and output state respectively.

Adopting a coarse-grained method and directly using the five elements of "satellites, people, machines, materials, and environment" to form the AIT work element set, the subsequent solution of the optimal process for single satellites or batch production satellites will be low-complexity, but precise. If not refined enough, details may be ignored and affect the actual process execution; using a fine-grained method, these five aspects can be refined into element subsets to form an AIT work element set, and then the optimal single-satellite or batch-production satellite can be subsequently solved. The details of the process are thoughtful, but the complexity is high. The AIT work factor set corresponding to the granularity can be selected according to the degree of optimization requirements of the satellite model.

On the basis of determining the set of AIT work elements, determine the specific content of the elements of each project. For example, the elements of a certain item are expressed as: {battery pack, satellite placed horizontally}; {battery pack, transponder, satellite placed horizontally}; {general assembly and electrical installation personnel}, {whole satellite support vehicle}, {screws, washers}, {Electrical test station} means that the project needs to be carried out under battery assembly conditions and the satellite is placed horizontally. After completion, the battery pack and transponder are installed and the satellite is placed horizontally; it requires the operation of the general assembly and electrical installation personnel, and the entire satellite support vehicle is required The equipment requires two auxiliary materials, screws and gaskets, which are implemented at the electrical measurement station.

(3) Determine the single-satellite tightly coupled project relationship list. According to the standards, specifications, and specific work requirements of satellite development, the projects that must be carried out successively are analyzed and clarified. The relationship between the projects is a tightly coupled project relationship, and a list is given. Other projects are loosely coupled projects.

(4) Establish a single-star skeleton process. That is, the projects involved in the tightly coupled project relationship list are merged according to the tightly coupled project relationship, and the same projects are merged to establish process modules composed of each project. Each loosely coupled project is also treated as a process module to form a single star skeleton composed of each process module. process. The skeleton process refers to a loose process composed of various process modules. The skeleton process may not necessarily connect all projects, that is, the process modules may not necessarily connect. Adjust the process in the following two steps to obtain a process that connects all projects.

(5) Obtain the matching situation based on element relationships between each process module in the skeleton process. Use the following method to determine whether the element relationships between two process modules match:

① Use the first project and the last project in the process module as the input project and output project of the process module respectively.

②Analyze whether there is a match between the two process modules. If the input items of one process module B and the output items of another process module A meet the following matching conditions, then process module B is considered to match process module A:

a. The status of all "star" element items of the input status of the input item of process module B and the output status of the output item of process module A are exactly the same.

b. After the output project of process module A is completed and human resources are released, all "people" element items of the input project of process module B can meet the project requirements, that is, the human resources for carrying out the input project of process module B can be guaranteed.

c. After the output project of process module A is completed and the ground equipment resources are released, all the "machine" element items of the input project of process module B can meet the project requirements, that is, the ground equipment resources for the input project of process module B can be guaranteed.

d. After the output project of process module A is completed, all the "material" elements of the input project of process module B can meet the project requirements, that is, there are sufficient material resources to carry out the input project of process module B.

e. After the output project of process module A is completed and environmental resources are released, all "ring" element items of the input project of process module B can meet the project requirements, that is, the environmental resources of the input project of process module B can be guaranteed.

(6) Calculate the set of processes to obtain possible solutions for a single star. According to the matching between the process modules in the skeleton process based on the element relationship, manual or computer analysis is performed to arrange all the solutions for the arrangement of all process modules, forming a full-process solution combination that includes all work items in the satellite AIT stage, that is, possible solutions process set. If process module B matches process module A, process module B can be arranged immediately after process module A in the AIT process. When using computer analysis, the matching and mismatching situations between the two process modules can be represented by values 1 and 0 respectively to support computer software algorithms.

When computer analysis resources are not available or manual analysis workload is heavy, simplified methods can also be used to obtain a relatively better set of possible solutions. Simplified methods generally include:

①Traditional sequential method. Sequence loosely coupled projects into a skeleton process in a traditional order.

②Simple swap method. For a small number of major loosely coupled projects, make simple adjustments to the order of redemption projects with acceptable manual workload.

③ Borrowing method of other star elements. Borrow the element resources of other satellites in batch production to give priority to the AIT work of the target satellite, that is, exchange and change the element resource guarantee conditions of different satellites in batch production.

(7) Compare and obtain the optimal process for batch production of satellites within the target range. According to the order of delivery time required by the satellite launch time, as well as the key resource guarantee conditions of the "star" (such as a key domestically produced single machine cannot be delivered and installed on the satellite before October), the key resource guarantee conditions of "people" (such as the same person cannot be Carry out work on two satellites at the same time), the key resource guarantee conditions for "machine" (such as only one bracket truck), the key resource guarantee conditions for "materials" (such as silicone rubber will not be available until after October), and the conditions for "environment" In order to meet the restriction requirements of resource guarantee conditions (such as the thermal vacuum tank being used for other aerospace models from May to December but not for this model), the possible process sets for batch production of each satellite are combined to meet the constraints. The combination of the processes of each satellite based on the conditions, that is, the set of processes that can be solved by batch production satellites. According to the user's requirements for the first launch time, final launch time, whether to launch in batches according to stages and the batch launch time limit requirements of the batch satellite, and in accordance with the weighting principle given by the user, the best solution is obtained from the process set comparison of the batch satellite. Excellent batch production process.

When the number of satellites is 1, the periods of multiple possible processes for the satellite are directly compared, and the process with the shortest period is the optimal process for a single satellite.

(8) During the execution of the optimal batch production process, if the batch production satellite AIT work will be completed smoothly, if a project problem occurs and the process is interrupted, the remaining unfinished projects of each satellite will be used as the new process design target range (i.e. Work item set), according to the disposal strategy for interrupted projects (adjustment, suspension, etc. strategies with other projects), recalculate the possible process set for obtaining the remaining projects, compare the optimal batch production process for obtaining the remaining projects, and execute the new best Optimize the batch production process and realize dynamic optimization during the execution of the batch production process.

Example

Taking a certain batch-production satellite model project as an example, in order to improve the progress of batch-production development, a batch-production satellite AIT process generation method based on factor relationships was used to identify the process links that can be optimized for the single-satellite and double-satellite processes before optimization, and formed the optimized process. In the new double-star development process, a series of process optimization measures have been carried out to greatly improve the development efficiency:

(1) Figure 2 shows the single-star process before optimization, and Figure 3 shows the double-star process before optimization. The work content of the single-satellite process includes satellite assembly, cabin assembly, satellite assembly wire test, satellite assembly wireless test, whole-satellite mechanical test, docking with the carrier, whole-satellite thermal test, comprehensive docking, pre-factory assembly test, and factory final assembly. Decompose the work content and determine the set of work items for a single satellite in the AIT stage: satellite assembly, docking with the carrier, and comprehensive docking cannot be further decomposed. The final assembly of the cabin is divided into platform final assembly, load bay final assembly, three-cabin docking, and satellite final assembly line testing. It is divided into stand-alone delivery, software drop welding, platform assembly, platform testing, load bay assembly, load bay test, and B state test. The satellite assembly wireless test/EMC test is divided into wireless state final assembly, C state test/EMC test, and wireless state post-processing. Final assembly, the whole satellite mechanical test is divided into wireless state final assembly, vibration test and noise test, and wireless state post-final assembly. The thermal test is divided into satellite thermal test modification, cabin thermal test modification, thermal vacuum test, final assembly after thermal test, and final assembly before leaving the factory. Electrical testing is divided into pre-factory assembly and pre-factory electrical testing.

In particular, the project decomposition results of the entire project at different stages can be obtained based on the ECRS method while covering the overall goal of satellite AIT.

(2) Based on the above work project set of a single satellite in the AIT stage, determine the AIT work element set and the specific content of the elements of each project. In this embodiment, the five elements of {satellites, people, machines, materials, and environment} are: To reduce the complexity of the description of the present invention, only the "hardware status" and "ring" elements of the "star" element are refined. The corresponding AIT work element set is schematically represented as {platform single machine, load bay single machine, star table thermal control component, star table Table large components}, software status, whole satellite combination status}; {platform single machine, load bay single machine, star watch thermal control parts, star watch large components}, software status, whole star combination status}; {general assembly personnel, testers, Test personnel, general personnel}; {ground tooling equipment, ground testing equipment}; {fasteners, brackets, auxiliary materials}; {test test station, external wireless interference}.

(3) In accordance with satellite development standards, specifications, and specific work requirements, it is determined that there is a tightly coupled project relationship between the following projects: software drop welding, stand-alone delivery; satellite assembly/stand-alone delivery, load bay final assembly/platform final assembly; load bay final assembly/platform Final assembly, three-cabin docking; in-cabin thermal test modification/star table thermal test modification, thermal test, final assembly after thermal test; wireless test test before final assembly, C status test/EMC test; wireless test test before final assembly, vibration test and noise test, Connect with the carrier. The mentioned "load bay final assembly/platform final assembly, three-cabin docking" means that the load bay final assembly and platform final assembly are carried out in parallel, and then closely connected to the three-cabin docking, and other expressions are similar.

It can be seen that there is no strict sequence relationship between thermal vacuum test, vibration test and noise test. C-state test/EMC test, vibration test and noise test all require wireless state final assembly and wireless state post-assembly. The process before optimization has not been better adjusted. The connection between loosely coupled projects and other projects.

(4) Establish process modules composed of each project according to the tightly coupled project relationship list. Each loosely coupled project is also treated as a process module. The single-star skeleton process composed of each process module is established as shown in Figure 4. The process module includes the start Process module, end process module, other process modules, other process modules include wireless process module (process module from wireless test pre-test assembly to wireless test pre-test assembly), thermal test process module (star table thermal test modification, cabin thermal test modification Process module modified after thermal testing) and comprehensive docking process module.

(5) Obtain the matching between each process module in the skeleton process based on element relationships. As shown in Table 1, the matching of each process module in the first column of the table with each process module in the first row, "1" means matching, "0" ” indicates a mismatch for purposes of computer analysis. For example, the wireless process module does not match the start process module (the satellite status of the wireless process module requires the solar wing to be arranged, which is different from the uninstalled solar wing status of the "star" aspect element of the output status of the start process module), while the thermal test module can match the start process Module (because all aspects of the elements match).

Table 1 Examples of matching between each process module based on element relationships

Note: In the table, "1" means matching and "0" means not matching, for computer analysis.

(6) Calculate the set of processes to obtain possible solutions for a single star. When the number of process modules is small and the complexity is small, the permutation and combination of each process module can be manually given, that is, the process set of possible solutions, including {start process module, comprehensive docking module, thermal test module, wireless process module, end Process module}, and {start process module, thermal test module, comprehensive docking module, wireless process module, end process module}, a total of 2 solutions. There is no difference in progress between these two solutions, so they are both optimal processes for a single star.

(7) Compare the optimal process for mass production of dual satellites. The two satellites named M1 and M2 are required to start AIT work and launch from the factory at the same time. The single-satellite process is solution A ({start process module, comprehensive docking module, thermal test module, wireless process module, end process module}), or Solution B ({Start Process Module, Thermal Test Module, Comprehensive Docking Module, Wireless Process Module, End Process Module}) can be combined to obtain the process set of possible solutions for the double satellite satellite. There are three solutions, namely AA and BB. , AB (consistent with the actual effect of BA, and the same solution as BA), that is, both stars use process A, both use process B, and use three combined processes of process A and process B respectively. According to the user's requirement to complete development as soon as possible, the two stars choose different processes to avoid resource conflicts in the same process modules and ensure parallel development progress. In the actual project, since the two satellites share a thermal vacuum tank, the thermal test-related parts of the batch production process of process A and process B were partially optimized, the thermal vacuum test was merged, and the comprehensive docking of the two satellites and the satellite thermal test were combined. The test modification and the cabin thermal test modification are crossed. The final optimal process for batch production of dual-satellite satellites is shown in Figure 5.

Contents not described in detail in the specification of the present invention belong to the well-known techniques of those skilled in the art.

Claims (5)

1. A batch production satellite AIT process generation method based on element relationships, which is characterized by including the following steps: 1) Determine the work content that multiple satellites need to carry out in the AIT phase, decompose the work content step by step until it cannot be divided anymore, obtain the work items that cannot be further divided, and use them as the basic unit of the work item set for the single-satellite AIT stage; 2) Determine the core elements of each work item in the satellite AIT stage to form an AIT work element set with the required granularity; determine the specific content of the core elements corresponding to each work item in the work item set described in step 1); 3) For each single satellite, analyze and determine the work projects that must be carried out in a fixed order, and form a list of project relationships with a tight coupling relationship for the single satellite; the remaining work projects that have no fixed order requirements are regarded as loosely coupled projects; 4) For each single star, the work items in the tightly coupled project relationship list are arranged in a fixed order to form a process module. At the same time, each loosely coupled project is also used as a process module to form a single star composed of various process modules. skeleton process; 5) Use the first item in the process module as the input item of the process module, and use the last item in the process module as the output item of the process module. According to the matching conditions of the element relationships between process modules, traverse all process modules and analyze Check whether there is a match between two process modules, and obtain the matching relationship between different process modules; 6) Permutation and combination. Based on the matching relationship obtained in step 5), possible arrangement schemes of all process modules are given. Each scheme is used as a possible solution process set to obtain multiple possible solution process sets; 7) Based on the factory order determined by the satellite launch time requirements and the restriction requirements of the resource guarantee conditions corresponding to the core elements of each work project, screen out a set of possible solution processes that meet the restriction requirements; 8) According to the user's detailed restriction requirements and weighting principles for satellite launch time, the possible solution processes obtained from step 7) are intensively compared to obtain the optimal set of possible solution processes as a mass production process to execute the production task. 2. A method for generating AIT process for batch production of satellites based on element relationships according to claim 1, characterized in that: during the execution of the mass production process, if the process execution of the mass production process is interrupted, the remaining unfinished process of each satellite will be The work items form a new process module, and steps 6) to 8) are performed again to obtain the optimal batch production process for the remaining unfinished projects, which is the dynamic optimization during the execution of the batch production satellite AIT process. 3. A method for generating a batch-production satellite AIT process based on element relationships according to claim 1, characterized in that: when the number of batch-produced satellites is set to 1, it is a method for generating a single-satellite AIT process. 4. A batch production satellite AIT process generation method based on element relationships according to any one of claims 1 to 3, characterized in that: the core elements in step 2) are composed of satellite-related elements, human-related elements, It consists of several or all of the mechanical factors, material factors and environmental factors. 5. A method for generating batch satellite AIT processes based on element relationships according to claim 4, characterized in that: the set of possible solution processes in step 6) includes the entire process of all work items in the satellite AIT stage.