کنترل فعال ارتعاشات و پایش سلامت به هنگام پنل ترک دار فضاپیمای انعطاف پذیر مجهز به وصله های پیزوالکتریک در مانور وضعیت

نوع مقاله : مقاله پژوهشی

نویسندگان

1 عضو هیات علمی / پژوهشگاه هوافضا

2 دانشجوی کارشناسی ارشد / پژوهشگاه هوافضا

چکیده

این مقاله به کنترل فعال ارتعاشات و پایش سلامت پنل ترکدار فضاپیمای انعطافپذیر در مانور وضعیت با استفاده از وصله های حسگر/عملگر پیزوالکتریک و روش فیدبک نرخ کرنش پرداخته است. پنل انعطافپذیر ترک دار با رویکرد تئوری تیر اویلر-برنولی و روش المان محدود مدلسازی شده و معادلات غیرخطی حرکت سیستم کاملاً کوپل صلب-انعطافپذیر با استفاده از روش لاگرانژ استخراج و با روش عددی نیومارک-بتا حل شده است. دو رویکرد، پایش سلامت به صورت آزمون و خطا و با اندازه گیری بیشینه نرخهای کرنش هر المان حین مانور (به صورت بهنگام ) در کنار کنترل ارتعاشات (با اعمال نیروی کنترلی مبتنی بر بیشترین مقادیر نرخ کرنش با تعداد معین و از پیش تعریف شده عملگرهای پیزوالکتریک)، در نظر گرفته شده است. بیشنه نرخهای کرنش با تغییر در شرایط مأموریت و جابجایی ترک در لحظه تغییر کرده و به طور همزمان عملگرهای متناظر فعال میشوند. همچنین به منظور شناسایی رفتار کل سیستم ترکدار، تابع انرژی متشکل از انرژیهای جنبشی و پتانسیل پنلهای انعطافپذیر و پارامترهای وضعیت بدنه صلب با لحاظ ضرایب وزنی مختلف ارزش دهی شده است که معیار مناسبی از عملکرد رویکرد دوم (الگوریتم هوشمند پیشنهادی) می باشد. شبیه سازیها برای مکانهای مختلف ترک و ورودیهای گشتاورهای خارجی وارد بر بدنه صلب فضاپیما در قالب یک مطالعه مقایسه ای در محیط متلب/سیمولینک، معیاری مناسب در تعیین تعداد، مکان عملگرها و کاهش هزینه های توان مصرفی در فضاپیماهای مدرن امروزی در مأموریتهای با دقت بالا میباشد.

کلیدواژه‌ها

عنوان مقاله [English]

Online Active Vibration Control and Health Monitoring of a Cracked Flexible Spacecraft Panels Equipped with Piezoelectric Patches During Attitude Maneuver

نویسندگان [English]

  • milad azimi 1
  • Mohammad Javad Chitgari 2
  • Seyed Hamed Hashemi Mehne 1
1 Iran, Tehran, Shahrake gharb square, Iranzamin Street, Havafaza dead end.
2 Aerospace Research Institute (Ministry of Science, Research and Technology)
چکیده [English]

This paper deals with active vibration control (AVC) and structural health monitoring of a maneuvering flexible spacecraft with a cracked panel using piezoelectric (PZT) sensor/actuator patches and strain rate feedback (SRF) method. The cracked panel is modeled using the Euler-Bernoulli beam theory and the finite element method (FEM). The nonlinear equations of motion of the fully coupled rigid-flexible system are extracted using the Lagrangian formulation and solved with Newmark-β algorithm. Two approaches of structural health monitoring; first, trial and error, and second, maximum strain rates (online measurement) along with AVC (applying control signals based on the maximum values of strain rates to the predefined number, but unknown locations of PZT actuators), are performed. The strain rates change directly with mission conditions and crack locations, and the corresponding actuators are activated simultaneously. Moreover, to identify the dynamic behavior of the whole, cracked system, an energy function with different weighting coefficients is introduced to propose a suitable criterion for the performance evaluation of the second approach. Simulations for different crack numbers and locations and external disturbances as a comparative study (in MATLAB/Simulink) demonstrate suitable criteria to determine the number and locations of actuators and reduce the power costs in modern spacecraft in high-precision missions.

کلیدواژه‌ها [English]

  • Vibrations-based
  • Structural health monitoring
  • Active vibration control
  • Flexible spacecraft
  • Strain rate feedback

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