طراحی مأموریت بهینه به منظور سفر اکتشافی به ماه

نوع مقاله: مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 پژوهشگاه هوافضا

2 صنعتی خواجه نصیرالدین طوسی

3 دانشگاه صنعتی خواجه نصیرالدین طوسی

چکیده

هدف اصلی مقاله، معرفی روش طراحی مأموریت اکتشافی به ماه براساس فناوری موجود در کشور است. طراحی مأموریت اکتشافی ماه شامل مدار انتقالی بهینه و حامل فضایی می­شود. مدار انتقالی بهینه براساس مسئله سه جسم محدود دایروی (CRTBP) برای مدل‌سازی حرکت یک فضاپیما در سیستم زمین/ ماه طراحی شده است. برای این منظور، مدار انتقالی بهینه روش CRTBP را به عنوان مدل دینامیکی اتخاذ نمودهو مسیر انتقالی سه بعدی زمین به ماه را با هزینه پایین به دست می‌دهد. این روش بدلیل هزینه و قابلیت دسترسی به شیب‌های مداری مختلف در عزیمت از زمین و تقرب به ماه، دارای ارجحیت و انعطاف بیشتر نسبت به روش انتقال هاهمن است. روندنمای بهینه طراحی مفهومی حامل فضایی (LVCD) بر مبنای بهینه­سازی پارامترهای اصلی طراحیاست. روندنمای مذکور (LVCD) در بستر نرم­افزاری به منظور ایجاد امکان برای جستجوی فضای طراحی و همچنین کاهش زمان و هزینه برای فاز طراحی مفهومی کدنویسی شده است. فرآیند بهینه­سازی نسبت به تابع هدف و قیود طراحی در یک حلقه تکرار صورت گرفته است. در نهایت، قابلیت حامل فضایی طراحی شده برای ارضا الزامات ماموریتی مورد ارزیابی قرار گرفته است.

کلیدواژه‌ها


عنوان مقاله [English]

Optimal Mission Design for Moon Exploration Expedition

نویسندگان [English]

  • Hassan Naseh 1
  • Mehran Mirshams 2
  • Elyas Fadakar 3
  • Mehdi Jafari Nadoushan 3
1 ARI
2 K. N. Toosi University of Technology
3 K. N. Toosi University of Technology
چکیده [English]

The main goal of this paper is to introduce the Moon exploration mission design based on existing technology.The Moon exploration mission design entailsoptimal maneuvering orbit, payload and launch vehicle design. Optimal maneuvering orbit is designed with respect to Circular Restricted Three Body Problem (CRTBP) to model the motion of a spacecraft in the Earth/Moon system. To this end, optimal maneuvering orbitadopted CRTBP as dynamical model and obtained three-dimensional Earth to Moon transfers with low cost. This method is more preferable and flexible than Hohmann transfer because of its lower cost and its access to various inclinations in departure and arrival.The optimal Launch Vehicle Conceptual Design (LVCD) algorithm is based on optimization of major design parameters. LVCD algorithm is coded in a software to let the design engineer explore the design space and to reduce the cost and time of the conceptual design phase that is developed by the authors.The optimization process is performed subject to the restrictions and the performance index is optimized in a mutual iteration mechanism. Consequently, the designed launch vehicle ability to satisfy the mission objectives and its requirements is evaluated.

کلیدواژه‌ها [English]

  • Mission design
  • Moon exploration
  • Circular restricted three body problem
  • Launch vehicle conceptual design
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