نویسندگان

1 صنعتی خواجه نصیرالدین طوسی

2 پژوهشگاه هوافضا - پژوهشکده سامانه های فضانوردی

چکیده

هدف از این مقاله، ارائة متدلوژی تخصیص قابلیت اطمینان زیرسامانه‌های ماهواره‌بر با استفاده از روش تحلیل سلسله مراتبی در فاز طراحی مفهومی است. تابع هدف در استفاده از این متدلوژی، قابلیت اطمینان است و معیارهای اصلی، فناوری، پیچیدگی، زمان عملکرد هر زیرسامانه و هزینه درنظرگرفته شده‌اند. برای به‌کارگیری روش تحلیل سلسله مراتبی در تخصیص قابلیت اطمینان زیرسامانه‌های ماهواره‌بر، از لینک کد مطلب (به‌منظور بررسی سازگاری و تعیین وزن‌هایتخصیص با استفاده از روش بردارهای ویژة ماتریسی) و نرم‌افزار اکسل(برای تشکیل ماتریس‌های مقایسة زوجی) استفاده می‌شود. برای این منظور، با استفاده از خروجی‌های نرم‌افزار طراحی مفهومی ماهواره‌بر سوخت مایع (LVCD)که توسط نویسندگان مقاله توسعه یافته است، مشخصه‌های زیرسامانه‌های ماهواره‌بر و زمان عملکرد هر زیرسامانه استخراج می‌شود و به عنوان ورودی این متدلوژی قرار خواهد گرفت. نتایج به‌دست آمده برای تخصیص قابلیت اطمینان به زیرسامانه‌های بلوک مرحلة دوم یک ماهواره‌بر سوخت مایع، میزان خطای روش را کمتر از 2% برآورد می‌کند که در بحث قابلیت اطمینان در فاز طراحی مفهومی قابل قبول است.

کلیدواژه‌ها

عنوان مقاله [English]

Reliability Allocation to Launch Vehicle Subsystems by Using AHP Method in Conceptual Design Phase

نویسندگان [English]

  • M. Mirshams 1
  • S. Irani
  • A. M. Akhlaghi
  • H. Naseh 2

چکیده [English]

The goal of this paper is presenting a methodology for reliability allocation to launch vehicle subsystems using Analytical Hierarchy Process (AHP) method in conceptual design phase. In this methodology, the goal function is reliability and the main considered criterions are technology, complexity, operational time of each subsystem and cost. For applying AHP method to launch vehicle subsystems reliability allocation, a Matlab code( for investigating compatibility and determining allocation weight factors by employing Matrix Eigen Vector Method) and a Excel sheet( for forming the comparison matrix) are employed. To this point, by using the outcomes of liquid-propellant launch vehicle conceptual design software (LVCD) which developed by authors, the launch vehicle specifications and operational time of each subsystems is derived and is feed to this methodology as input. The results of applying this method to launch vehicle reliability allocation for the second stage of a launch vehicle, shows the error of this method below 2%. It is clear that this small error in reliability issues in conceptual design phase is acceptable.

کلیدواژه‌ها [English]

  • Reliability Allocation
  • Launch Vehicle
  • Analytical hierarchy process (AHP)
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