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Reliability assessment of folding wing system deployment performance considering failure correlation
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School of Mechanical Engineering & Automation, Northeastern University, Shenyang 110819, P. R. China
Key Laboratory of Vibration and Control of Aero-Propulsion System Ministry of Education, Shenyang 110819, P. R. China
School of Mechanical Engineering, Suzhou University of Science and Technology, Suzhou 215009, P. R. China
Submission date: 2023-08-29
Final revision date: 2023-10-20
Acceptance date: 2023-11-10
Online publication date: 2023-11-15
Publication date: 2023-11-15
Corresponding author
Liyang Xie   

Northeastern University, Shenyang, China
Eksploatacja i Niezawodność – Maintenance and Reliability 2024;26(1):175085
  • Dynamic model of the folding wing mechanism with joint clearances is developed and solved.
  • The system reliability models with failure correlation are established.
  • The new evaluation methods for the system reliability models are proposed.
  • Variation rules of system reliability with different distribution parameters are analyzed.
The reliability of folding wing deployment performance greatly impacts flight vehicle reliability. Based on the dynamic analysis theory, the deployment dynamic model of folding wing mechanism with joint clearances is established and solved. Considering the failure correlation, the system reliability models are developed for both cases, without considering synchronization and considering synchronization. For the former, a solution method combining saddle point approximation and numerical integration is proposed. For the latter, an estimation method based on a combination of the fourth order moment Pearson distribution family and the numerical integration is proposed. The efficiency and accuracy of the proposed methods are verified through examples. In addition, the trend of the system reliability change when the distribution parameters of random variables are different is also analyzed. From the perspective of improving reliability, the above study can provide theoretical guidance and data support for the design, manufacturing and service process of the folding wing mechanism system.
All authors gratefully acknowledge the selfless support from the National Science and Technology Major Project (J2019 IV 0002 0069) and the Fundamental Research Funds for the Central Universities (N2303015) N2303015). Thanks for the editor and
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