نوع مقاله : علمی پژوهشی

نویسندگان

1 استادیار، پژوهشگاه هوافضا، وزارت علوم تحقیقات و فناوری ، تهران، ایران.

2 مربی، دانشگاه آزاد اسلامی واحد تهران شمال، دانشکده فنی و مهندسی، تهران، ایران.

چکیده

این مقاله به طراحی قانون کنترلی برای مانور وضعیت و کاهش ارتعاشات باقی‌مانده یک فضاپیمای انعطاف‌پذیر مجهز به تراستر/چرخ عکس‌العملی و وصله‌های پیزوالکتریک پرداخته است. تئوری توسعه یافتة مبتنی بر طراحی تابع لیاپانوف با لحاظ دینامیک چرخ عکس‌العملی برای کنترل مانور و حسگر/عملگرهای پیزوالکتریک و استفاده از کنترلر فیدبک نرخ کرنش برای ارتعاشات باقی‌مانده پس از فاز دستیابی به زاویه مطلوب ارائه شده است. معادلات حرکت سیستم با لحاظ دینامیک غیرخطی و کاملاً کوپل جسم صلب-انعطاف‌پذیر فضاپیمای در مانور تک‌محوره با پیاده‌سازی روش مودهای فرضی و اصل همیلتون استخراج شده است. پایداری کلی سیستم صلب–انعطاف‏پذیر شامل انرژی‌های هاب صلب، پنل‌های انعطاف‌پذیر، وصله‌های پیزوالکتریک، چرخ عکس‌العملی و یک فنر پیچشی با به‌کارگیری ورودی‌های پیوسته (چرخ عکس‌العملی) و ناپیوسته کنترلی (تراستر با بکارگیری مدولاسیون پهنا-پالس/فرکانس-پالس) اثبات و ارتعاشات باقی‌مانده به حداقل رسیده است. عملکرد سیستم کنترل توسعه یافتة پیشنهادی در مقایسه با نمونه رایج آن و رویکرد کنترلی جانمایی قطب‌ها بررسی شده است. شبیه‌سازی‌های انجام شده برای یک مانور با زاویة بزرگ و کاهش قابل ملاحظه ارتعاشات ناشی از تحریک پنل‏های انعطاف‏پذیر بیانگر مزیت و کارایی روش پیشنهادی می‌باشد.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Vibration Suppression of a Maneuvering Flexible Spacecraft with Actuator Dynamic

نویسندگان [English]

  • Milad Azimi 1
  • Samad Moradi 2

1 Assistant Professor. Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran.

2 Educator. Department of Engineering, Islamic Azad University, North Tehran Branch, Tehran, Iran.

چکیده [English]

This paper presents a study concerning active vibration control of a smart, flexible spacecraft during attitude maneuver using thrusters/ a reaction wheel and piezoelectric patches. The large-angle maneuver and residual vibration of the spacecraft are controlled utilizing an extended Lyapunov-based design (ELD) and strain rate feedback (SRF) theory. The single-axis fully coupled rigid-flexible dynamic of the system is derived applying a Lagrangian approach and Assumed Mode Method (AMM). The system's overall stability, including energetic terms covering a hub, two flexible appendages, PZT sensor/actuator, RW dynamics, and torsional spring, has been proved, and the control law has been derived accordingly. A pulse-width pulse-frequency (PWPF) modulation is used to alleviate the excitations of high-frequency flexible modes. However, due to the fast maneuver, there are still residual vibrations in the system. Hence, the SRF algorithm using PZT is applied to prepare further vibration suppression. The performance of the proposed extended controller is compared to the conventional Lyapunov and pole placement control algorithms. The numerical results for simultaneously large angle attitude and vibration control of a flexible spacecraft through a comparative study verify the merits of the proposed approach. 

کلیدواژه‌ها [English]

  • Thrusters
  • Vibration Control
  • Flexible Spacecraft
  • Lyapunov Controller
  • Piezoelectric Patches
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