نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 دانشکده مهندسی هوافضا، دانشگاه صنعتی شریف، تهران، ایران

2 پژوهشکده سامانه های ماهواره، پژوهشگاه فضایی ایران، تهران، ایران

چکیده

مدارهای هاله‌ای به واسطه ویژگی‌هایی همچون حرکت‌های تناوبی حول نقطه تعادلی برای رصد و مطالعه فضا اهمیت ویژه‌ای دارند. از این رو، مقاله حاضر به طراحی مسیر انتقال بهینه به مدار هاله‌ای پرداخته است. برای حل این مسئله کنترل بهینه از رویکرد هموتوپی در کنار روش پرتابی استفاده شده‌است. این روش باعث بهبود سرعت همگرایی و رسیدن به حدس اولیه بهتری می‌شود. مسیر بهینه طراحی‌شده، فضاپیمایی در مدار حول زمین را به یک مدار هاله‌ای حول نقطه لاگرانژی L1 سیستم سه جسم زمین-ماه منتقل می‌کند. سیستم پیشران فضاپیما از نوع تراست-کم با ضربه ویژه ثابت در نظر گرفته شده است. رویکرد هموتوپی دامنه گسترده‌ای دارد که از آن میان، روش ادامه‌ی هموتوپی در این پژوهش مدنظر قرار گرفته‌است. هدف از مسیر طراحی شده، انتقال با کمینه مصرف سوخت است که به کمک رویکرد هموتوپی از تغییر شکل حل مساله کمینه مصرف انرژی به دست آمده است. در واقع رویکرد هموتوپی سبب تسهیل حل مساله دشوار کمینه مصرف سوخت شده است.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Homotopy-based optimal trajectory design to transfer from Earth orbit to halo orbits

نویسندگان [English]

  • Ghasem Heydari 1
  • Maryam Kiani 1
  • S. Hossein Pourtakdost 1
  • Mohammad Sayanjali 2

1 Department of Aerospace engineering, Sharif University of Technology, Tehran IRAN

2 Space System Research center, Iran Space Center, Tehran, Iran

چکیده [English]

Halo orbits are of importance for observation and study of the space due to their specific characteristics including the orbital position and the periodic motion. In this regards, present paper has focused on optimal trajectory planning to transfer to halo orbits. To this aim, homotopy approach has been adopted for optimal trajectory design. This approach has improved the convergence rate and insensitivity of the problem to initial guess. The designed trajectory transfers a spacecraft orbiting the Earth to a Halo orbit around Lagrangian point L1 of the Earth-moon restricted three-body system. The propulsion system has been assumed to be low thrust with constant specific impulse. Homotopy approach has a broad domain of applicability and methods in which continuation method has been employed here among them. The optimal designed trajectory minimizes the fuel consumption via transforming solution of the minimum energy problem utilizing the homotopy approach. This approach simplifies solution of the complex problem of minimum fuel indeed.

کلیدواژه‌ها [English]

  • Halo Orbit
  • Homotopy Approach
  • Homotopy Continuation Method
  • Shooting Method
  • Optimal Trajectory Design
  • Orbit Transfer
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