محاسبه توزیع پاسخ فرکانسی سازه کمربند گوه ای اتصال ماهواره به ماهواره بر ناشی از عدم قطعیت برخی پارامترهای سفتی محوری و خمشی

نوع مقاله : مقاله پژوهشی

نویسندگان

1 عضو هیات علمی / مجتمع دانشگاهی مواد و فناورهای ساخت، دانشگاه صنعتی مالک اشتر، تهران، ایران

2 مربی / مجتمع دانشگاهی مواد و فناورهای ساخت، دانشگاه صنعتی مالک اشتر، تهران، ایران

چکیده

عدم قطعیت پارامترها باعث می‏شود که رفتار سیستم‏ها نسبت به چیزی که انتظار می‏رود، تغییر کرده و یک ماهیت آماری پیدا کند. بنابراین در سیستم‏های پیچیده و حساس، همچون سازه ماهواره‏ بر و ماهواره متصل به آن، لازم است تاثیر عدم قطعیت بر رفتار دینامیکی بررسی شود. در این مقاله، مدل اجزاء محدود نوینی از سازه ماهواره‏بر و ماهواره شبیه سازی شده است که عدم قطعیت‏های اتصال کمربند گوه‏ای را لحاظ می‏کند. این مدل، بر مبنای روشی است که توزیع سفتی محوری و خمشی معادل اتصال کمربند گوه‏ای را با در نظر گرفتن عدم قطعیت‏ها محاسبه می‏کند. سپس رفتار ارتعاشی سازه با وجود عدم قطعیت‏ها بررسی شده و روشی برای محاسبه توزیع آماری پاسخ فرکانسی سازه کامل ارائه شده است. در نهایت طیف توزیع پاسخ فرکانسی سازه کامل در دو راستای طولی و عرضی (خمشی) محاسبه شده است. نتایج نشان می‌دهد انحراف معیار توزیع در محدوده فرکانسی نزدیک به فرکانس طبیعی خمشی متأثر از اتصال کمربند گوه‌ای، بیشترین مقدار را دارد که نشان دهنده تاثیر سفتی محلی این اتصال، بر پاسخ دینامیکی سازه در راستای عرضی است. همچنین انحراف معیار توزیع و در نتیجه تاثیر سفتی اتصال بر پاسخ دینامیکی سازه در راستای طولی، اندک و قابل صرف‌نظراست.

کلیدواژه‌ها

عنوان مقاله [English]

Reliability assessment of structures of satellite and satellite carrier connected by clamp band

نویسندگان [English]

  • Ali Davar 1
  • Reza Azarafza 1
  • Sayed sadradin Mousavi 2
1 Faculty of Materials & Manufacturing Processes, Malek Ashtar University of Technology, Tehran, Iran
2 Faculty of Materials & Manufacturing Processes, Malek Ashtar University of Technology, Tehran, Iran
چکیده [English]

Uncertainties of the parameters cause the behavior of the systems to statistical distribution and change from what is expected. Therefore, in complex and sensitive systems, such as structures of satellite carrier and satellite connected to it, it is necessary to investigate the effect of uncertainty on dynamic response. In this paper, a novel finite element model of structures of satellite carrier and satellite is simulated to take parameters uncertainties of clamp band joint into account. This model is based on a method that calculates the distribution of axial and flexural stiffness equivalent of the clamp band joint considering all of the uncertainty. Then the vibrational behavior of the structure despite the uncertainties is investigated and a method for calculating the statistical distribution of the frequency response of the complete structure is presented. Finally, the frequency response distribution spectrum of the complete structure in both longitudinal and transverse (bending) directions is calculated. The results show that the standard deviation of the distribution in the frequency range close to the normal bending frequency due to the connection of clamp band joint has the highest value, which shows the effect of local stiffness of this connection on the dynamic response of the structure in the transverse direction. Also, the standard deviation of the distribution and consequently the effect of clamp band stiffness on the dynamic response of the structure in the longitudinal direction is small and negligible.

کلیدواژه‌ها [English]

  • Uncertainty
  • Clamp Band Joints
  • Reliability
  • Frequency Response

مراجع

[1] C. Li, Z. Zhang, Q. Yang and P. Li, Experiments on the geometrically nonlinear vibration of thin-walled cylindrical shells with points supported boundary condition, Journal of Sound and Vibration, Vol. 473, 115226, 2020.
[2] G. Li, Z. Nie, Y. Zeng, J. Pan and Z. Guan, New Simplified Dynamic Modeling Method of Bolted Flange Joints of Launch Vehicle, Journal of Vibration and Acoustics, Vol. 142, No. 2, 2020.
[3] Z.-Y. Qin, S.-Z. Yan and F.-L. Chu, Dynamic characteristics of launch vehicle and spacecraft connected by clamp band, Journal of Sound and Vibration, Vol. 330, pp. 2161-2173, 2011.
[4] Z. Y. Qin, S. Z. Yan and F. L. Chu, Dynamic analysis of clamp band joint system subjected to axial vibration, Journal of sound and vibration, Vol. 329, pp. 4486-4500, 2010.
[5] A. Davar, S. S. Mousavi and R. Azarafza, Reliability Analysis of Bearing Load Capacity of V-Clamp Band Under Parameters’ Uncertainty, Journal of Mechanical Engineering, Vol. 51, N0. 3, pp. 41-49, 2019. (in Persion)
[6] Z. Y. Qin, S. Z. Yan and F. L. Chu, Influence of clamp band joint on dynamic behavior of launching system in ascent flight, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Vol. 228, pp. 97-114, 2014.
[7] Z. Y. Qin, S. Z. Yan and F. L. Chu, Analytical modeling of clamp band joint under external bending moment, Aerospace Science and Technology, Vol. 25, pp. 45-55, 2013.
[8] Z. Y. Qin, S. Z. Yan and F. L. Chu, Dynamic analysis of slender launching system connected by clamp band joint using harmonic balance method, in Journal of Physics: Conference Series, Vol. 448, 2013.
[9] H. Li, M. Zhu, Z. Xu, Z. Wang and B. Wen, The influence on modal parameters of thin cylindrical shell under bolt looseness boundary, Shock and Vibration, Vol. 2016, pp. 1-15, 2016.
[10] Q. Tang, C. Li, H. She and B. Wen, Modeling and dynamic analysis of bolted joined cylindrical shell, Nonlinear Dynamics, Vol. 93, pp. 1953-1975, 2018.
[11] Q. Tang, C. Li, H. She and B. Wen, Vibration analysis of bolted joined cylindrical-cylindrical shell structure under general connection condition, Applied Acoustics, Vol. 140, pp. 236-247, 2018.
[12] F. Wang, J. Li, Y.-q. Li and Z. Luo, The investigation of vibration characteristics on the bolted disk--drum joints structure, Advances in Mechanical Engineering, Vol. 11, 1687814019831477, 2019.
[13] Y. Liu, J. Wang and L. Chen, Dynamic Characteristics of the Flange Joint with a Snap in Aero-Engine, International Journal of Acoustics and Vibration, Vol. 23, pp. 168-174, 2018.
[14] M. M. Ataei, H. Salarieh, H. NejatPishkenari and H. Jalili, Boundary control design for vibration suppression and attitude control of flexible satellites with multi-section appendages, Acta Astronautica, Vol. 173, pp. 22-30, 2020.
[15] T. Kitamura, K. Yoshida, H. Seko, Q. Shi, Analysis of shock response for satellite separation, Proceeding of ISME2012, USD2012, pp. 2091-2102, 2012.
[16] X. Wang, W. Liu, X. Li and Y. Sun, The Shock Response Prediction of Spacecraft Structure Based on Hybrid FE-SEA Method, Applied Sciences, Vol, 11, pp. 1-17, 2021.
[17] D. Cui, S. Yan, J. Li, Z. Qin and X. Guo, Dynamic analysis of satellite separation considering the flexibility of interface rings, Proc IMechE Part G: J Aerospace Engineering, Vol. 0, pp. 1–17.
[18] A. Davar, R. Azarafza, and S. S. Mousavi, Uncertainty analysis and reliability estimation of clamp band joints, Materials Science and Technology, Vol. 36, pp. 1487-1502, 2020.
[19] J. Odeon, Mechanics of elastic structures, New York: McGraw-Hill, Inc., 1976, pp. 83-130.
[20] C. Zheng, G. Ruo-fei and S. Lei, LM-3A series launch vechicle user's manual, China Academy of Launch Vehicle Technology, 2011.
[21] N. A. S. A. GD-ED, "2214, Marman Clamp System Design Guidelines, 2000.

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