Closed-loop guidance laws for low-thrust spacecrafts

This paper attempts to compare the two methods of Takagi-Sugeno (TS) fuzzy logic and neighbouring optimal control (NOC), for closed-loop guidance laws of low-thrust spacecraft system equations. At first, the open-loop optimal guidance is considered as the optimal thrust steering program that will transfer the vehicle from an inclined low earth orbit to a high earth orbit. Secondly, proper closed-loop guidance laws are achieved, as the novelty of this work, to examine the robustness of the two methods with respect to min-effort criterion for low-thrust spacecrafts. This performance index will be better than customary min-time and will be investigated as a new trend in this field for closed-loop guidance. The results illustrate the viability and efficiency of TS and NOC methods as closed-loop guidance laws for low-thrust orbital manoeuvres regarding the robustness of this guidance against disturbances. Finally, results illustrate a better method to achieve closed-loop guidance for low-thrust spacecraft manoeuvres
 

مقالات
حجم فایل 469 کیلوبایت
زبان مقاله ENGLISH
سال انتشار 2014
محل انتشار Int. J. Modelling, Identification and Control
مشخصات کلی
تعداد صفحات 12
تعداد صفحات محصول 1-20

نظر بدهید

توجه: HTML ترجمه نمی شود!
    بد           خوب

Lorem ipsum dolor sit amet, consectetur adipiscing elit. Aliquam iaculis egestas laoreet. Etiam faucibus massa sed risus lacinia in vulputate dolor imperdiet. Curabitur pharetra, purus a commodo dignissim, sapien nulla tempus nisi, et varius nulla urna at arcu.Lorem ipsum dolor sit amet, consectetur adipiscing elit. Aliquam iaculis egestas laoreet. Etiam faucibus massa sed risus lacinia in vulputate dolor imperdiet. Curabitur pharetra, purus a commodo dignissim, sapien nulla tempus nisi, et varius nulla urna at arcuLorem ipsum dolor sit amet, consectetur adipiscing elit. Aliquam iaculis egestas laoreet. Etiam faucibus massa sed risus lacinia in vulputate dolor imperdiet. Curabitur pharetra, purus a commodo dignissim, sapien nulla tempus nisi, et varius nulla urna at arcu. 

Closed-loop guidance laws for low-thrust spacecrafts

  • تولید کننده: Iman Shafieenejad
  • شناسنامه: AS6-1004-paper
  • موجودی: در انبار
  • تاریخ چاپ: 2016-10-25
  • نویسنده: Iman Shafieenejad and A.B. Novinzadeh
  • ژورنال: Int. J. Modelling, Identification and Control
  • رایگان
  • قیمت بدون مالیات: رایگان

برچسب ها: optimal control theory; fuzzy logic; neighbouring optimal control; low-thrust orbital transfer