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کنترل تحملپذیر خطای مبتنی بر الگوریتم مود لغزشی انتگرالی و کنترل فعال ارتعاشات فضاپیمای انعطافپذیر در حضور اغتشاشات خارجی | ||
| مکانیک هوافضا | ||
| مقاله 10، دوره 19، شماره 1 - شماره پیاپی 71، خرداد 1402، صفحه 137-151 اصل مقاله (1.96 M) | ||
| نوع مقاله: گرایش دینامیک، ارتعاشات و کنترل | ||
| نویسندگان | ||
| میلاد عظیمی* 1؛ مرضیه اقلیمی دژ2؛ علیرضا علیخانی3 | ||
| 1نویسنده مسئول: استادیار، پژوهشکده سامانه‌های فضانوردی، پژوهشگاه هوافضا (وزارت علوم، تحقیقات و فناوری)، تهران، ایران | ||
| 2دانشجوی کارشناسی ارشد، پژوهشکده سامانه‌های فضانوردی، پژوهشگاه هوافضا (وزارت علوم، تحقیقات و فناوری)، تهران، ایران | ||
| 3دانشیار، پژوهشکده سامانه‌های فضانوردی، پژوهشگاه هوافضا (وزارت علوم، تحقیقات و فناوری)، تهران، ایران | ||
| تاریخ دریافت: 06 مهر 1401، تاریخ بازنگری: 24 مهر 1401، تاریخ پذیرش: 07 آذر 1401 | ||
| چکیده | ||
| در این مقاله به طراحی الگوریتمهای کنترل فعال ارتعاشات و کنترل مقاوم مود لغزشی انتگرالی جهت پایدارسازی وضعیت فضاپیمای انعطافپذیر در حضور اغتشاشات خارجی و خرابی عملگر پرداخته‌شده است. فضاپیما به‌صورت یک هاب صلب در مانور سه محوره به همراه دو پنل خورشیدی مجهز به حسگر/عملگرهای پیزوالکتریک در قالب یک سیستم دینامیکی کوپل صلب-انعطافپذیر مدل‌سازی شده است. ساختار کنترل تحملپذیر خطای غیرفعال مود لغزشی انتگرالی با بهرهگیری از یک الگوریتم کنترل نامی تناسبی-مشتقی و یک الگوریتم تحملپذیر خطای توسعه‌یافته با لحاظ خطای افزوده متغیر با زمان به‌منظور افزایش عملکرد، عدم تحریک مودهای انعطافپذیر و آسیب سیستم در فاز رسیدن به سطح لغزش طراحی‌شده است. بدین ترتیب با ورود سیستم به مود لغزش، رفتار دینامیک حلقه بسته شامل خطای عملگر، مشابه با سیستم سالم خواهد شد. جهت کاهش ارتعاشات ناشی از دینامیک وضعیت و خرابی عملگرها، الگوریتم کنترل فعال ارتعاشاتی نیز به‌طور هم‌زمان در تمام طول مانور فعالسازی میشود. عملکرد ساختار کنترل پیشنهادی با معیارهای میزان تحریک مودهای انعطافپذیر، تلاش کنترلی و دستیابی به پارامترهای مطلوب وضعیت در قالب یک مطالعه مقایسهای مزیت و برتری آن را نسبت به الگوریتم مود لغزشی انتگرالی بدون قابلیت تحملپذیری خطا نمایش میدهد. | ||
تازه های تحقیق | ||
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| کلیدواژه‌ها | ||
| پیزوالکتریک؛ کنترل تحملپذیر خطا؛ کنترل فعال ارتعاشات؛ کنترل مود لغزشی انتگرالی؛ فضاپیمای انعطافپذیر | ||
| عنوان مقاله [English] | ||
| Integral Sliding Mode Fault-Tolerant Control and Active Vibration Suppression of a Flexible Spacecraft in the Presence of External Disturbances | ||
| نویسندگان [English] | ||
| Milad Azimi1؛ Marzieh Eghlimi Dezh2؛ Alireza Alikhani3 | ||
| 1Corresponding author: Assistant Professor, Department of Astronautic, Aerospace Research Institute (Ministry of Science, Research and Technology), Tehran, Iran | ||
| 2M.Sc. Student, Department of Astronautic, Aerospace Research Institute (Ministry of Science, Research and Technology), Tehran, Iran | ||
| 3Associate Professor, Department of Astronautic, Aerospace Research Institute (Ministry of Science, Research and Technology), Tehran, Iran | ||
| چکیده [English] | ||
| An active vibration control algorithm and robust integral sliding mode control (SMC) are discussed to stabilize the attitude of the flexible spacecraft under external disturbances and actuator faults. As a coupled rigid-flexible dynamical system, the flexible spacecraft is modeled as a rigid hub with two solar panels equipped with piezoelectric (PZT) sensors and actuators. A passive fault-tolerant integral sliding mode control algorithm using a nominal proportional-derivative control algorithm and an improved fault-tolerant algorithm with time-varying additive fault is developed to increase system’s performance, prevent the system's flexible modes excitations in the phase of reaching the sliding surface. Therefore, when the system enters the sliding mode, the closed-loop dynamic behavior, including actuator faults, will be identical to that of the system without faults. It is possible to reduce the residual vibrations caused by the attitude dynamics and actuator faults by simultaneously activating the strain rate feedback (SRF) vibration control algorithm during the maneuver. The performance of the proposed integral fault-tolerant control in terms of the flexible modes excitation, the control effort, and achieving the desired attitude parameters in a comparative study demonstrated its advantage and superiority over the conventional integral sliding mode algorithms. | ||
| کلیدواژه‌ها [English] | ||
| Piezoelectric, Fault tolerant control, Active vibration control, Integral sliding mode control, Flexible spacecraft | ||
| مراجع | ||
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