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Multi quality Characteristics Model Integration of Aviation Equipment for Support Effectiveness Evaluation

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2017 2nd International Conference on Computer, Mechatronics and Electronic Engineering (CMEE 2017) ISBN: 978-1-60595-532-2

Multi-quality Characteristics Model Integration of Aviation Equipment for

Support Effectiveness Evaluation

Yang ZHOU

*

, Zhao-yang ZENG, Zhi-yu JIA, Yan ZHOU and Kai YUAN

China Aero-Polytechnology Establishment (CAPE), Beijing, China

*Corresponding author

Keywords: Support effectiveness evaluation, Reliability, Maintainability, Testability, Model integration, Aviation equipment.

Abstract. In order to evaluate support effectiveness of aviation equipment in development stage, which is based on multi-quality characteristics design analysis models instead of statistical data in operational stage, a method of model integration was studied in this paper. On the basis of support effectiveness evaluation model and simulation, reliability model, testability model and maintainability model can be integrated into support effectiveness evaluation model with integration method proposed in this paper. With support effectiveness evaluation in development stage, multi-quality characteristics problems can be found and solved early to improve operation capacity of aviation equipment.

Introduction

Support effectiveness is the measure of the equipment and its support system to economically and effectively achieve operational readiness and mission sustainability in the intended environment and conditions, which is a comprehensive reflection of multi-quality characteristics such as Reliability, Maintainability, Testability and Supportability. Support effectiveness evaluation of aviation equipment is a comprehensive evaluation of multi-quality characteristics, which can be used to measure the operational capacity of aviation equipment and support the balance of multi-quality characteristics and the reasonable allocation of resources.

Support effectiveness evaluation based on simulation has been used in decision making of aviation equipment operation and maintenance from last century. Many models and tools such as LCOM, MBSGM, Dyna-METRIC, TIGER, CASEE, and SIMLOX have been developed in United States and Europe, and applied in aviation equipment such as F-15E, F-16, C-17, F-22 and F-35 to improve support effectiveness and reduce life cycle cost [1].

Support effectiveness evaluation is generally based on statistical data of multi-quality characteristics in operation stage of aviation equipment. The design and analysis technology of multi-quality characteristics tends to be modeled with development of aviation equipment, and based on the design analysis model of multi-quality characteristics, support effectiveness evaluation can be used to predict the operation capacity and optimize multi-quality characteristics in development stage of aviation equipment. Therefore, multi-quality characteristics model integration of aviation equipment for support effectiveness evaluation is studied in this paper.

Support Effectiveness Evaluation of Aviation Equipment

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The key of support effectiveness evaluation of aviation equipment is support effectiveness modeling [3]. The support effectiveness evaluation model of aviation equipment is shown in Figure 1.

Figure 1. Support effectiveness evaluation model of aviation equipment.

Aviation Equipment Model

Equipment system is the main object to complete the operation mission and perform test, maintenance, and support work. The aviation equipment model is used to describe the aviation equipment system, and to model combat unit composed of many equipment, the configurations and features of different equipment.

Mission Model

The mission model is used to model the missions performed by the combat unit. It focuses on the typical mission profile of the aircraft, takes the combat and training plan of the combat unit and the operational program of aircraft as the modeling object. It is used to describe the occurrence, sequence, aircraft configurations required by missions and the logical relationship between missions.

Reliability, Maintainability, Testability Model

The reliability, maintainability, and testability model of aviation equipment contains fault definition, fault triggering mechanism, fault distribution function, maintenance process, maintenance time, test methods, testing process, test time, and the random sampling mechanism of these quality characteristics, in order to reproduce the level of equipment quality characteristics [4].

Supportability Model

The supportability model includes support organization model, support resource model, and support process model [5].

The support organization model is used to describe the types and functions of support organization under different maintenance systems, the level and function of support site which is the place to carry out support activities, and the hierarchical relationship and support relationship among different support sites.

The support resource model is used to describe the support resources such as manpower, spare parts, support equipment, support facilities and so on, including the functions and the object to support of the support resources, the related operation and maintenance activities, and the replenishment mechanism [6].

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Multi-quality Characteristics Model Integration of Aviation Equipment for Support Effectiveness Evaluation

Due to reliability, maintainability and testability design analysis model have their own principles and objectives, and it is difficult to directly assimilate into the support effectiveness evaluation. Therefore, on the basis of clearly ensuring the data requirement of the support effectiveness evaluation, it is necessary to research the data conversion and integration technology based on the quality characteristics design analysis model.

The technical solution of multi-quality characteristics model integration of aviation equipment for support effectiveness evaluation is shown in Figure 2. The reliability model includes Fault Model and mission reliability model. Driven by the mission of operation and training, the aircraft can be dispatched from the available aircraft to execute the mission according to the aircraft configuration required by the mission and resource requirements.

During the mission execution, fault of the aircraft is determined whether to appear by the Fault Model integration. If no fault occurs during the mission, the mission will be continued and the aircraft will be checked and return to available aircraft pool after the mission.

If a fault occurs during the mission, it will be determined whether the fault can be detected by the testability model integration. If the fault can not be detected during the mission execution, the mission will be continued ignoring the fault, and more detailed fault diagnosis will be performed for the aircraft after the mission by the testability model integration to isolate the fault LRU (Abbreviation of Line Replaceable Unit), and then troubleshooting for the fault will be performed by the maintenance model integration.

If the fault can be detected during the mission execution, it will be determined whether the fault affects the mission by the mission reliability model integration. If the fault affects the mission, the mission will be aborted and the aircraft will return. If the fault does not affect the mission, the mission will be continued and the aircraft will be checked after the mission. Troubleshooting for the fault will be performed after the aircraft return by the maintenance model integration.

Figure 2. Technical solution of multi-quality characteristics model integration of aviation equipment for support effectiveness evaluation.

Multi-quality characteristics model integration for support effectiveness evaluation includes process integration and data integration.

Integration of Reliability Model and Support Effectiveness Evaluation Model

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Integration of Fault Model and Support Effectiveness Evaluation Model

Fault Model is used to model dynamic and static relationship of fault in different levels of complex systems with bottom-up transmission, and describe the structured relationship between LRU fault mode and system fault mode.

As the fault which often can be found is system fault in operation process, and the LRU fault sampling can be produced in simulation process of the support effectiveness evaluation model, so it is necessary to perform the occurrence of the system fault based on LRU fault sampling based on fault model.

The integration of Fault Model and support effectiveness evaluation model is implemented through data integration. According to the process integration, the data integration of the two models includes two aspects: one is the input data for the invocation of the Fault Model by the support effectiveness evaluation model, including all LRU and its fault modes data, and the LRU fault time data based on Monte Carlo Sampling, on the other hand is the output data from the fault model to the support effectiveness evaluation model, including the system fault model and time corresponding to LRU fault data.

Integration of Mission Reliability Model and Support Effectiveness Evaluation Model

Integration of Mission Reliability Model and Support Effectiveness Evaluation Model is the impact of fault in the mission modeling on the basis of fault-tolerant mechanism of mission system redundancy and dynamic reconfiguration.

The support effectiveness evaluation model will call the mission reliability model for each fault detected during flight preparation and flight. For the fault detected during flight in simulation process of the support effectiveness evaluation model, mission reliability model is called to perform mission reconstruction program and provide mission success criterion according to the mission and the aircraft functional structure, and it is determined whether to abort or continue the mission.

According to the process integration, the data integration of the two models includes two aspects: one is the input data for mission reliability model invocation, including mission plan and the aircraft configuration required by the mission data, on the other hand is the output data of mission reliability model, including the criteria of the fault detected during flight preparation influence the mission and the criteria of the fault detected during flight process influence the mission data.

Integration of Testability Model and Support Effectiveness Evaluation Model

The testability model is used to describe the modules, signals, fault modes, fault rates, test methods, test points and their relationships of product.

When a system function fails in simulation process of the support effectiveness evaluation model, the testability model will be called to determine whether the system fault can be detected during the mission process. Meanwhile, testability model is called to diagnose and isolate the detected system functional fault.

According to the process integration, the data integration of the two models includes two aspects: one is the input data for testability model invocation, which is system function fault modes data, on the other hand is the output data of testability model, including the detection analysis results of system fault modes, items and methods of test for fault detection data, and the fault isolation procedures, the timing, conditions, required resources of the test items for fault diagnosis data.

Integration of Maintainability Model and Support Effectiveness Evaluation Model

Maintainability model is used to describe product fault detection, diagnosis and maintenance process, as well as the support resources such as spare parts, support equipment and manpower required in the maintenance process.

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effectiveness evaluation model, and to determine whether the fault can be fixed and count required time and support resources.

According to the process integration, the data integration of the two models includes two aspects: one is the input data for maintainability model invocation, including the LRU fault, support system, the allocation of support resource data, on the other hand is the output data of maintainability model, including the methods, process, time of maintenance for the fault data, and the type and quantity of support resource consumed and occupied.

Summary

Based on support effectiveness evaluation model and simulation process, the reliability model, testability model and maintainability model can be integrated into support effectiveness evaluation model with process integration and data integration. A software tool of multi-quality characteristics model integration was developed, and the error between the simulation result with multi-quality characteristics models integration and the statistical result of support effectiveness evaluation was small based on actual data of an aviation equipment.

Reference

[1] B.Z. Zhang, Engineering Practice of Integrated Logistics Support for New Generation Fighter in Foreign Countries, Aviation Industry Press, Beijing, China, 2014.

[2] Y. Zhou, Z.Y. Zeng, Y. Zhou, Z.Y. Jia, Research on Simulation-based Support Effectiveness Evaluation of Military Aircraft, Aviation Maintenance & Engineering. 279(2014) 63-65.

[3] Y. Zhou, Z.Y. Zeng, Y. Zhou, Z.Y. Jia, K. Yuan, The Construction Method of Aviation Equipment Support Effectiveness Simulation Benchmark Model Based on Use Data, Aeronautical Science & Technology. 27 (2016) 42-47.

[4] Z.Y. Jia, Q.B. Chen, Z.Y. Zeng, Z.H. Xu, X. Guo, Models for Evaluating Maintenance Support Capability of Aviation Equipment Based on PHM, Proceedings of the IEEE 2012 Prognostics and System Health Management Conference. IEEE Computer Society, (2012) 3200-3204.

[5] W. Wang. Integrative Effective Evaluation Methods of Equipment Support System, Changsha, China: National University of Defense Technology, 2009.

[6] Z.Y. Jia, Q.B. Chen, Z.Y. Zeng, Z.H. Xu, X. Guo. Methods of Maintenance Resources Configuration and optimization for AMS Based on Effectiveness Evaluation, Advanced Materials Research. Trans Tech Publications, 476-478 (2012) 1105-1111.

[7] Y. Zhou, Z.Y. Zeng, Y. Zhou, Z.Y. Jia, Maintenance Support Process Modeling and Simulating Technology for Aviation Materiel, Proceedings of 10th International Conference on Reliability, Maintainability and Safety, Institute of Electrical and Electronics Engineers Inc., (2014) 1052-1055.

References

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