Helicopter turboshaft engine overall task index hierarchical decomposition method and system

Abstract

The invention relates to the technical field of helicopter turboshaft engines, and provides a helicopter turboshaft engine overall mission index hierarchical decomposition method and system, and the method comprises the steps: obtaining the use demand data information and typical mission profile of a helicopter equipped with a turboshaft engine; according to the use demand data information and the typical mission profile, performing hierarchical division on the overall mission indexes of the helicopter and the turboshaft engine; determining hierarchy task index types of hierarchies to which the helicopter and the turboshaft engine belong according to a hierarchy division result; and based on the hierarchical task index type of each hierarchy, determining a decomposition mapping relationship between the hierarchical task index types of each hierarchy. The overall task index hierarchical decomposition method for the turboshaft engine of the helicopter is a forward hierarchical mapping index decomposition method based on capability requirements, and a capability and index system is formed and used for supporting work such as argumentation, test subject planning and test assessment of the turboshaft engine.

Description

Technical Field

[0001] The present invention relates to the technical field of helicopter turboshaft engines, and in particular to a method and system for hierarchical decomposition of overall mission indicators of helicopter turboshaft engines. Background Art

[0002] The turboshaft engine is the power source for helicopter flight. It drives the rotor and tail rotor to rotate to generate lift and balance thrust through the output power of the turbine shaft. It has the characteristics of high speed, high temperature, and high intake flow. It is technically difficult, has a long development cycle, and requires a lot of funds. With the maturity of new materials and technologies, the engine functions are more powerful, and the requirements for performance, stability, reliability and other indicators are getting higher and higher. In this context, the difficulty of turboshaft engine demonstration and test assessment is increasing, and the requirements are increasing.

[0003] Equipment testing and assessment is an activity to verify, inspect and assess the technical scheme, technical performance and use effectiveness of equipment in a standardized organizational form in accordance with the prescribed procedures and conditions to meet the needs of equipment design, development, identification and mission use. Equipment testing plays an important role in discovering equipment problems and defects, mastering the basic data of equipment performance and effectiveness, strictly controlling equipment identification and finalization, and ensuring that the equipment is practical, easy to use and durable.

[0004] The analysis of the mission and capability requirements of equipment is one of the basic bases for equipment demonstration and test assessment, and is the first problem to be solved. Capability requirements play an important role in the demonstration of the overall indicators of turboshaft engines and the planning of test subjects. Capability requirements and overall indicators are the link between users and research and development departments. Due to the different technical backgrounds and thinking positions of both parties, both parties have different descriptions and understandings of turboshaft engines. Users focus on what capabilities the system should have and what tests can be used to comprehensively assess the various capabilities of the engine. The research and development department focuses on what means to achieve capabilities, how to implement various capabilities into specific system designs, and what are the relevant indicators. This inevitably leads to difficulties in converting capability requirements into overall indicators.

[0005] In recent years, in order to avoid the problems of "high scores and low capabilities" that may occur after delivery to users due to insufficient assessment of equipment test tasks, as well as the inconsistency between users' experience of equipment use and test and appraisal results, the field has vigorously promoted the adoption of new test and appraisal concepts and implemented new test and appraisal requirements, making the equipment test and appraisal in the new era form an integrated and diversified feature. At the same time, with the continuous increase in equipment capability requirements, the forward decomposition of indicators based on mission tasks and capability requirements has become more complex, and the formulation of test tasks has become more difficult, and it is easy to lose or be redundant. The relationship between capability requirement analysis and overall indicator requirements is a complex coupled nonlinear mapping relationship. Its transformation mapping lacks a systematic, scientific and standardized method. The generation of overall indicators is often determined according to technical solutions, and it is difficult to map changes in capability requirements to overall indicators.

[0006] With the transformation and development of equipment testing and appraisal, testing and appraisal work runs through the entire life cycle of equipment, covering project demonstration, scheme demonstration, engineering development, appraisal finalization, production deployment and use and maintenance stages, highlighting the system engineering concept, and transforming the task focus and implementation subject. Turboshaft engines have many technical indicators, which are greatly affected by the use environment and have a long assessment cycle. A large number of tests and test flights are required to verify and assess their performance indicators, efficiency indicators and applicability indicators. Among them, efficiency indicators, applicability indicators, reliability indicators and overhaul interval performance indicators need to be tested after the completion of the status appraisal combined with the long-term use of users. Summary of the invention

[0007] The purpose of the present invention is to solve at least one technical problem in the background technology and to provide a method and system for hierarchical decomposition of overall mission indicators of a helicopter turboshaft engine.

[0008] To achieve the above object, the present invention provides a method for hierarchical decomposition of overall mission indicators of a helicopter turboshaft engine, comprising: Obtain the usage demand data and typical mission profiles of helicopters equipped with turboshaft engines; Based on the usage demand data information and typical mission profiles, the overall mission indicators of helicopters and turboshaft engines are divided into levels; Determine the hierarchical task indicator types of each level to which helicopters and turboshaft engines belong based on the hierarchical classification results; Based on the hierarchical task indicator types of each level, a decomposition mapping relationship between the hierarchical task indicator types of each level is determined.

[0009] According to one aspect of the present invention, the overall mission indicators of helicopters and turboshaft engines are hierarchically divided into the following categories based on the usage demand data information and typical mission profiles: The mission and task indicators of helicopters equipped with turboshaft engines to the key technical indicators of turboshaft engines are divided into five levels: mission layer, task layer, capability layer, indicator layer and key technical indicator layer according to the correspondence from collection to subset.

[0010] According to one aspect of the present invention, the hierarchical task indicator types of each level to which helicopters and turboshaft engines belong are determined according to the hierarchical division results, including: The hierarchical task indicator type of the mission layer is to meet the power requirements for the continuous use and mission execution of the helicopter; The hierarchical task indicator types of the task layer are the task scenarios that the helicopter is required to perform in different environments; The hierarchical task indicator type of the capability layer is the capability that a turboshaft engine should have to support a helicopter in completing various tasks; The hierarchical task indicator types of the indicator layer are indicators of the capabilities that a turboshaft engine-supported helicopter should have to complete various tasks, including: performance indicators, efficiency indicators, and system contribution rate indicators; The hierarchical task indicator types of the key technical indicator layer are key technical indicators and indicator parameters for achieving performance indicators, efficiency indicators and system contribution rate indicators.

[0011] According to one aspect of the present invention, based on the hierarchical task indicator types of each level, determining the decomposition mapping relationship between the hierarchical task indicator types of each level includes: The relevant level task indicator types of the capability layer are formed by decomposing and mapping the corresponding level task indicator types of the task layer; The relevant level task indicator types of the indicator layer are formed by decomposing and mapping the corresponding level task indicator types of the capability layer; The relevant hierarchical task indicator types of the key technical indicator layer are formed by decomposing and mapping the corresponding hierarchical task indicator types of the indicator layer.

[0012] To achieve the above object, the present invention also provides a helicopter turboshaft engine overall mission indicator hierarchical decomposition system, comprising: A helicopter mission information acquisition module is used to obtain the usage demand data information and typical mission profile of the helicopter equipped with the turboshaft engine; The mission indicator hierarchical division module divides the overall mission indicators of helicopters and turboshaft engines into different levels according to the usage demand data information and typical mission profiles; A hierarchical task indicator type determination module determines the hierarchical task indicator types of each level to which helicopters and turboshaft engines belong according to the hierarchical division results; The decomposition mapping relationship determination module determines the decomposition mapping relationship between the hierarchical task indicator types of each level based on the hierarchical task indicator types of each level.

[0013] To achieve the above-mentioned purpose, the present invention also provides an electronic device, including a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the computer program, when executed by the processor, implements the above-mentioned hierarchical decomposition method of the overall mission indicators of the helicopter turboshaft engine.

[0014] To achieve the above-mentioned purpose, the present invention also provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the above-mentioned method for hierarchical decomposition of overall mission indicators of a helicopter turboshaft engine is implemented.

[0015] According to the solution of the present invention, the hierarchical decomposition method of the overall mission indicators of helicopter turboshaft engines proposed in the present invention is a forward hierarchical mapping indicator decomposition method based on capability requirements, which forms a capability and indicator system to support the demonstration, test subject planning and test assessment of turboshaft engines.

[0016] The present invention aims at the demonstration and identification requirements of helicopter turboshaft engines, and combines its structural and functional characteristics to conduct in-depth analysis and research from the aspects of mission task construction, task-capability mapping, capability-index decomposition and index system construction. By adopting the method of hierarchical system construction and decomposition mapping, according to the demonstration task process, a set of research and analysis methods for turboshaft engines from mission tasks to overall indicators based on hierarchical decomposition mapping is formed, realizing the key leap from qualitative demonstration to quantitative analysis. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A flowchart schematically showing a method for hierarchical decomposition of overall mission indicators of a helicopter turboshaft engine according to an embodiment of the present invention; Figure 2 The overall mission indicator level division and level mission indicator type decomposition mapping diagram of the helicopter and turboshaft engine of Example 1; Figure 3 This is a performance index decomposition diagram of Example 1. DETAILED DESCRIPTION

[0018] The content of the present invention will now be discussed with reference to exemplary embodiments. It should be understood that the embodiments discussed are only to enable those skilled in the art to better understand and thus implement the content of the present invention, rather than implying any limitation on the scope of the present invention.

[0019] As used herein, the term “including” and variations thereof are to be interpreted as open-ended terms meaning “including, but not limited to.” The term “based on” is to be interpreted as “based, at least in part, on.” The terms “one embodiment” and “an embodiment” are to be interpreted as “at least one embodiment.”

[0020] Figure 1 A flowchart schematically shows a method for hierarchical decomposition of overall mission indicators of a helicopter turboshaft engine according to an embodiment of the present invention. Figure 1 As shown, in this embodiment, the helicopter turboshaft engine overall mission indicator hierarchical decomposition method includes: Obtain the usage demand data and typical mission profiles of helicopters equipped with turboshaft engines; Based on the usage demand data information and typical mission profiles, the overall mission indicators of helicopters and turboshaft engines are divided into levels; Determine the hierarchical task indicator types of each level to which helicopters and turboshaft engines belong based on the hierarchical classification results; Based on the hierarchical task indicator types of each level, a decomposition mapping relationship between the hierarchical task indicator types of each level is determined.

[0021] Further, according to an embodiment of the present invention, the overall mission indicators of helicopters and turboshaft engines are hierarchically divided into the following categories based on the usage demand data information and typical mission profiles: The mission and task indicators of helicopters equipped with turboshaft engines to the key technical indicators of turboshaft engines are divided into five levels: mission layer, task layer, capability layer, indicator layer and key technical indicator layer according to the correspondence from collection to subset.

[0022] Further, according to an embodiment of the present invention, the hierarchical task indicator types of each level to which helicopters and turboshaft engines belong are determined according to the hierarchical division results, including: The type of hierarchical task indicators at the mission level is to meet the power requirements for the continuous use and mission execution of the helicopter; The hierarchical task indicator types of the task layer are the task scenarios that the helicopter is required to perform in different environments; The hierarchical task indicator type of the capability layer is the capability that a turboshaft engine should have to support a helicopter in completing various tasks; The hierarchical task indicator types of the indicator layer are indicators that should be possessed by the turboshaft engine to support the helicopter to complete various tasks, including: performance indicators, efficiency indicators and system contribution rate indicators; The hierarchical task indicator types of the key technical indicator layer are key technical indicators and indicator parameters for achieving performance indicators, efficiency indicators and system contribution rate indicators.

[0023] Further, according to an embodiment of the present invention, based on the hierarchical task indicator types of each level, determining the decomposition mapping relationship between the hierarchical task indicator types of each level includes: The relevant level task indicator types of the capability layer are formed by decomposing and mapping the corresponding level task indicator types of the task layer; The relevant level task indicator types of the indicator layer are formed by decomposing and mapping the corresponding level task indicator types of the capability layer; The relevant hierarchical task indicator types of the key technical indicator layer are formed by decomposing and mapping the corresponding hierarchical task indicator types of the indicator layer.

[0024] According to the above scheme of the present invention, the hierarchical decomposition method of the overall mission indicators of helicopter turboshaft engines proposed by the present invention is a forward hierarchical mapping indicator decomposition method based on capability requirements, which forms a capability and indicator system to support the demonstration, test subject planning and test assessment of turboshaft engines.

[0025] According to the above scheme of the present invention, the present invention targets the demonstration and identification requirements of helicopter turboshaft engines, combines its structural and functional characteristics, and conducts in-depth analysis and research from the aspects of mission task construction, task-capability mapping, capability-index decomposition and index system construction. By adopting the method of hierarchical system construction and decomposition mapping, according to the demonstration task process, a set of research and analysis methods of turboshaft engines from mission tasks to overall indicators based on hierarchical decomposition mapping is formed, realizing the key leap from qualitative demonstration to quantitative analysis.

[0026] Furthermore, to achieve the above-mentioned purpose, the present invention also provides a helicopter turboshaft engine overall mission indicator hierarchical decomposition system, comprising: A helicopter mission information acquisition module is used to obtain the usage demand data information and typical mission profile of the helicopter equipped with the turboshaft engine; The mission indicator hierarchical division module divides the overall mission indicators of helicopters and turboshaft engines into different levels according to the usage demand data information and typical mission profiles; A hierarchical task indicator type determination module determines the hierarchical task indicator types of each level to which helicopters and turboshaft engines belong according to the hierarchical division results; The decomposition mapping relationship determination module determines the decomposition mapping relationship between the hierarchical task indicator types of each level based on the hierarchical task indicator types of each level.

[0027] Further, according to an embodiment of the present invention, the overall mission indicators of helicopters and turboshaft engines are hierarchically divided into the following categories based on the usage demand data information and typical mission profiles: The mission and task indicators of helicopters equipped with turboshaft engines to the key technical indicators of turboshaft engines are divided into five levels: mission layer, task layer, capability layer, indicator layer and key technical indicator layer according to the correspondence from collection to subset.

[0028] Further, according to an embodiment of the present invention, the hierarchical task indicator types of each level to which helicopters and turboshaft engines belong are determined according to the hierarchical division results, including: The type of hierarchical task indicators at the mission level is to meet the power requirements for the continuous use and mission execution of the helicopter; The hierarchical task indicator types of the task layer are the task scenarios that the helicopter is required to perform in different environments; The hierarchical task indicator type of the capability layer is the capability that a turboshaft engine should have to support a helicopter in completing various tasks; The hierarchical task indicator types of the indicator layer are indicators that should be possessed by the turboshaft engine to support the helicopter to complete various tasks, including: performance indicators, efficiency indicators and system contribution rate indicators; The hierarchical task indicator types of the key technical indicator layer are key technical indicators and indicator parameters for achieving performance indicators, efficiency indicators and system contribution rate indicators.

[0029] Further, according to an embodiment of the present invention, based on the hierarchical task indicator types of each level, determining the decomposition mapping relationship between the hierarchical task indicator types of each level includes: The relevant level task indicator types of the capability layer are formed by decomposing and mapping the corresponding level task indicator types of the task layer; The relevant level task indicator types of the indicator layer are formed by decomposing and mapping the corresponding level task indicator types of the capability layer; The relevant hierarchical task indicator types of the key technical indicator layer are formed by decomposing and mapping the corresponding hierarchical task indicator types of the indicator layer.

[0030] According to the above scheme of the present invention, the helicopter turboshaft engine overall mission indicator hierarchical decomposition system proposed by the present invention is a forward hierarchical mapping indicator decomposition system based on capability requirements, which forms a capability and indicator system to support the demonstration, test subject planning and test assessment of the turboshaft engine.

[0031] According to the above scheme of the present invention, the present invention targets the demonstration and identification requirements of helicopter turboshaft engines, combines its structural and functional characteristics, and conducts in-depth analysis and research from the aspects of mission task construction, task-capability mapping, capability-index decomposition and index system construction. By adopting the method of hierarchical system construction and decomposition mapping, according to the demonstration task process, a set of research and analysis methods of turboshaft engines from mission tasks to overall indicators based on hierarchical decomposition mapping is formed, realizing the key leap from qualitative demonstration to quantitative analysis.

[0032] Furthermore, to achieve the above-mentioned purpose, the present invention also provides an electronic device, including a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein when the computer program is executed by the processor, the above-mentioned hierarchical decomposition method of the overall mission indicators of the helicopter turboshaft engine is implemented.

[0033] Furthermore, to achieve the above-mentioned purpose, the present invention also provides a computer-readable storage medium, on which a computer program is stored, and when the computer program is executed by a processor, the above-mentioned hierarchical decomposition method of the overall mission indicators of the helicopter turboshaft engine is implemented.

[0034] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiment described herein is only an optimal embodiment of the present invention and is only used to explain the present invention, and does not limit the scope of protection of the present invention. All other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0035] Example 1

[0036] The hierarchical decomposition method of the overall mission indicators of helicopter turboshaft engines includes: S1. Obtaining the use demand data and typical mission profile of helicopters equipped with turboshaft engines; S2. Based on the usage demand data information and typical mission profiles, the overall mission indicators of helicopters and turboshaft engines are divided into levels; S3. Determine the hierarchical task indicator types of each level to which helicopters and turboshaft engines belong based on the hierarchical classification results; S4. Based on the hierarchical task indicator types of each level, determine the decomposition mapping relationship between the hierarchical task indicator types of each level.

[0037] like Figure 2 As shown, the mission and task indicators of helicopters equipped with turboshaft engines and the key technical indicators of turboshaft engines are divided into five levels: mission layer, task layer, capability layer, indicator layer and key technical indicator layer according to the correspondence between the collection and the subset; In this embodiment, the mission layer and task layer are related to helicopters equipped with turboshaft engines and belong to the top-level requirements. The mission layer is used as the power installed in a certain type of helicopter to meet the power requirements of the helicopter for continuous use and mission execution. The task layer is the mission scenarios that the helicopter equipped with the engine is required to perform in different environments, such as cross-sea flight, 3000-meter flight on the plateau, 4500-meter flight on the plateau, etc., and the flight performance of the helicopters in each mission profile is listed at the same time.

[0038] By decomposing the hierarchical task indicator types of the helicopter's mission layer (such as typical flight missions in marine environments), the hierarchical task indicator types of the capability layer (such as high temperature environment operation capability, marine environment operation capability, helicopter air bleed capability, and motor power generation capability, etc.) that the turboshaft engine should have to support the helicopter in completing the corresponding mission are mapped out. When the helicopter performs different flight missions, the engine needs to have multiple capabilities to support it, and the transition from the mission layer to the capability layer is completed in a multi-mapping manner.

[0039] The hierarchical task indicator types of the indicator layer are decomposed from the hierarchical task indicator types of the capability layer, and are mainly divided into three categories: performance indicators, efficiency indicators, and system contribution rate indicators. The assessment methods and stages of each type of indicator are different, and they need to be classified and implemented in stages. Finally, the indicator layer is refined and decomposed into the key technical indicators of the engine and the parameters of each indicator are given (for example, the efficiency indicator is decomposed, such as Figure 3 as shown) to assess the engine's capability level.

[0040] In this embodiment, the method of obtaining key technical indicators through the above-mentioned hierarchical forward reasoning decomposition can characterize the overall indicators that meet the typical flight missions of helicopters and the capabilities of turboshaft engines. This characterization method presents the overall assessment indicators of the turboshaft engine in a hierarchical, comprehensive, and non-redundant manner, which facilitates the classification assessment and evaluation of different types of indicators.

[0041] Those skilled in the art will appreciate that the modules and algorithm steps described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of the present invention.

[0042] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working processes of the above-described devices and equipment can refer to the corresponding processes in the aforementioned method implementation methods, and will not be repeated here.

[0043] In the embodiments provided in the present application, it should be understood that the disclosed devices and methods can be implemented in other ways. For example, the device embodiments described above are only schematic. For example, the division of the modules is only a logical function division. There may be other division methods in actual implementation, such as multiple modules or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of devices or modules, which can be electrical, mechanical or other forms.

[0044] The modules described as separate components may or may not be physically separated, and the components shown as modules may or may not be physical modules, that is, they may be located in one place or distributed on multiple network modules. Some or all of the modules may be selected according to actual needs to achieve the purpose of the embodiments of the present invention.

[0045] In addition, each functional module in the embodiment of the present invention may be integrated into one processing module, or each module may exist physically separately, or two or more modules may be integrated into one module.

[0046] If the functions are implemented in the form of software function modules and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention can be essentially or partly embodied in the form of a software product that contributes to the prior art. The computer software product is stored in a storage medium and includes several instructions for enabling a computer device (which can be a personal computer, server, or network device, etc.) to perform all or part of the steps of the energy-saving signal sending / receiving method of each embodiment of the present invention. The aforementioned storage medium includes: various media that can store program codes, such as USB flash drives, mobile hard disks, ROM, RAM, magnetic disks, or optical disks.

[0047] The above description is only a preferred embodiment of the present application and an explanation of the technical principles used. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solution formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the above features are replaced with the technical features with similar functions disclosed in this application (but not limited to) by each other.

[0048] It should be understood that the size of the serial numbers of each step in the content of the invention and the implementation methods of the present invention does not absolutely mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the implementation methods of the present invention.

Claims

1. A hierarchical decomposition method for the overall mission indicators of helicopter turboshaft engines, characterized in that: include: Obtain the usage demand data and typical mission profiles of helicopters equipped with turboshaft engines; Based on the usage demand data information and typical mission profiles, the overall mission indicators of helicopters and turboshaft engines are divided into levels; Determine the hierarchical task indicator types of each level to which helicopters and turboshaft engines belong based on the hierarchical classification results; Based on the hierarchical task indicator types of each level, a decomposition mapping relationship between the hierarchical task indicator types of each level is determined.

2. The helicopter turboshaft engine overall mission indicator hierarchical decomposition method according to claim 1 is characterized in that: According to the use demand data information and typical mission profiles, the overall mission indicators of helicopters and turboshaft engines are divided into levels: The mission and task indicators of helicopters equipped with turboshaft engines to the key technical indicators of turboshaft engines are divided into five levels: mission layer, task layer, capability layer, indicator layer and key technical indicator layer according to the correspondence from collection to subset.

3. The helicopter turboshaft engine overall mission indicator hierarchical decomposition method according to claim 2 is characterized in that: According to the hierarchical classification results, the hierarchical task indicator types of each level of helicopters and turboshaft engines are determined, including: The hierarchical task indicator type of the mission layer is to meet the power requirements for the continuous use and mission execution of the helicopter; The hierarchical task indicator types of the task layer are the task scenarios that the helicopter is required to perform in different environments; The hierarchical task indicator type of the capability layer is the capability that a turboshaft engine should have to support a helicopter in completing various tasks; The hierarchical task indicator types of the indicator layer are indicators of the capabilities that a turboshaft engine-supported helicopter should have to complete various tasks, including: performance indicators, efficiency indicators, and system contribution rate indicators; The hierarchical task indicator types of the key technical indicator layer are key technical indicators and indicator parameters for achieving performance indicators, efficiency indicators and system contribution rate indicators.

4. The helicopter turboshaft engine overall mission indicator hierarchical decomposition method according to claim 3 is characterized in that: Based on the hierarchical task indicator types of each level, the decomposition mapping relationship between the hierarchical task indicator types of each level is determined, including: The relevant level task indicator types of the capability layer are formed by decomposing and mapping the corresponding level task indicator types of the task layer; The relevant level task indicator types of the indicator layer are formed by decomposing and mapping the corresponding level task indicator types of the capability layer; The relevant hierarchical task indicator types of the key technical indicator layer are formed by decomposing and mapping the corresponding hierarchical task indicator types of the indicator layer.

5. The helicopter turboshaft engine overall mission indicator hierarchical decomposition system is characterized by: include: A helicopter mission information acquisition module is used to obtain the usage demand data information and typical mission profile of the helicopter equipped with the turboshaft engine; The mission indicator hierarchical division module divides the overall mission indicators of helicopters and turboshaft engines into different levels according to the usage demand data information and typical mission profiles; A hierarchical task indicator type determination module determines the hierarchical task indicator types of each level to which helicopters and turboshaft engines belong according to the hierarchical division results; The decomposition mapping relationship determination module determines the decomposition mapping relationship between the hierarchical task indicator types of each level based on the hierarchical task indicator types of each level.

6. An electronic device, characterized in that The invention comprises a processor, a memory and a computer program stored in the memory and executable on the processor, wherein when the computer program is executed by the processor, the method for hierarchical decomposition of overall mission indicators of a helicopter turboshaft engine as described in any one of claims 1 to 4 is implemented.

7. A computer-readable storage medium, characterized in that The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the method for hierarchical decomposition of overall mission indicators of a helicopter turboshaft engine according to any one of claims 1 to 4 is implemented.

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