کد مقاله کد نشریه سال انتشار مقاله انگلیسی نسخه تمام متن
757308 1462503 2016 10 صفحه PDF دانلود رایگان
عنوان انگلیسی مقاله ISI
Singularity problem of control moment gyro cluster with vibration isolators
ترجمه فارسی عنوان
مسئله تکینگی خوشه گوی کنترل لحظه ای با ایزولاتورهای ارتعاش
کلمات کلیدی
ماهواره تکینگی، منطق فرماندهی، خطای گشتاور، جداسازی لرزش
موضوعات مرتبط
مهندسی و علوم پایه سایر رشته های مهندسی مهندسی هوافضا
چکیده انگلیسی

As powerful torque amplification actuators, control moment gyros (CMGs) are often used in the attitude control of many state-of-the-art high resolution satellites. However, the disturbance generated by the CMGs can not only reduce the attitude stability of a satellite but also deteriorate the performance of optic payloads. Currently, CMG vibration isolators are widely used to target this problem. The isolators can affect the singularity of the CMG system as they are placed between the CMGs and the satellite bus and provide additional freedoms to the CMG system due to their flexibility. The formulation of the output torque of a CMG is studied first considering the dynamic imbalance of its spin rotor and then the deformation angle as a result of the isolator’s flexibility is calculated. With the additional freedoms, the influence of isolator on the singularity problem is studied and a new steering logic to escape from the singular states is proposed.

ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Chinese Journal of Aeronautics - Volume 29, Issue 1, February 2016, Pages 238–247
نویسندگان
, ,