نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 دانشیار، گروه مهندسی هوافضا، دانشکده علوم و فنون نوین ، دانشگاه تهران، تهران، ایران

2 دانشجوی دکتری، گروه هوافضا،‌ دانشکدة علوم و فنون نوین، دانشگاه تهران، تهران، ایران

3 استادیار، بخش سنجش از دور، گروه نقشه برداری، دانشکده عمران، دانشگاه تربیت دبیر شهید رجایی، تهران، ایران

4 استادیار، پژوهشکده سامانه های ماهواره، پژوهشگاه فضایی، تهران، ایران

چکیده

ماهواره‌های سنجش از دور مشاهدة زمین که به صورت غیرفعال سطح زمین را اسکن و تصاویر با قدرت تفکیک مکانی زیر یک متر تولید می‌نمایند قادرند حول هر سه محور بدنة خود مانور کنند و همزمان با مانور وضعیت از جهات مختلف از ناحیة هدف تصویربرداری نمایند. سخت‌گیرانه‌ترین الزامات میانی حاکم بر عملکرد زیرسیستم تعیین و کنترل وضعیت آنها در مد‌های چرخش‌‌زدایی و نشانه‌روی دقیق اعمال می‌شود و شامل قابلیت مانور، چابکی، دقت و پایداری می‌باشد. در این تحقیق ابتدا روابط تحلیلی و آماری میان معیارهای کمّی الزامات میانی و قدرت تفکیک مکانی که به عنوان یک الزام سطح بالای مأموریتی مطرح است استخراج و با توجه به آن درایورهای طراحی چرخ‌های عکس‌العملی استخراج شده است. سپس در یک نمونه ماهوارة عملیاتی، با استفاده از تکنیک دیاگرام تطبیق، ابتدا مشخصات و ابعاد محمولة اپتیکی، سپس ابعاد و جرم ماهواره و پس از آن قابلیت تولید گشتاور و ظرفیت مومنتوم چرخ‌های عکس‌العملی و مومنتومی تخمین زده شده است.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Rapid Performance Sizing of Reaction Wheels in a Very High Resolution Remote Sensing Satellite Using Matching Diagram Technique

نویسندگان [English]

  • Amir Reza Kosari 1
  • Alireza Ahmadi 2
  • Alireza Sharifi 3
  • Masoud Khoshsima 4

1 Associate Professor‎, Faculty of New Sciences and Technologies, University of Tehran, Tehran, IRAN

2 Ph.D. Student‎, Department of Aerospace, faculty of New Sciences and Technologies, University of Tehran, Tehran, Iran

3 Assistant Professor‎, Department of survey engineering, Faculty of civil engineering, Shahid rajaee teacher training University, Tehran, IRAN

4 Assistant Professor‎و, Satellite Systems Research Institute, iranian space research center

چکیده [English]

Very High Resolution Passive Scan Agile Earth Observation Satellites are able to maneuver around all their three body axes and scan the target area in different directions, simultaneously. The most stringent mid-level requirements which dominate their attitude determination and control subsystem performance are applied in detumbling and fine pointing modes. These performance requirements are maneuverability, agility, accuracy and stability. In this research, first, we derive the analytical and statistical relationships between quantitative criteria of mid-level requirements and spatial resolution as a high-level mission requirement, next the design drivers of reaction wheels are extracted consequently. Then the size, mass and consuming power of an operational satellite and the reaction wheels torque authority and momentum capacity is guesstimated based on its imaging payload size and specifications.

کلیدواژه‌ها [English]

  • Agile Satellite
  • Remote Sensing
  • Earth Observation
  • Passive Scan
  • Imaging Payload
  • Attitude Determination and Control Subsystem
  • Performance Sizing
  • Matching Diagram
 
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