نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 مهندسی مکانیک، پژوهشکده سامانه های ماهواره، پژوهشگاه فضایی ایران، تهران، ایران.

2 مهندسی مکانیک، دانشکده فنی، دانشگاه تهران، تهران، ایران.

3 مهندسی هوافضا، پژوهشکده سامانه‌های ماهواره، پژوهشگاه فضایی ایران، تهران، ایران.

چکیده

در این مطالعه یک بستر آزمون سخت‌افزار در حلقه، طراحی و پیاده‌سازی شده است که از دستگاه شبیه‌ساز آرایه‌های خورشیدی، بار الکتریکی برنامه‌پذیر، رایانة شبیه‌ساز، باتری‌ها و بردهای شارژر و توزیع در این حلقه استفاده شده است. حالت آرام‌سازی ماهواره به دلیل تغییرات سریع و غیرقابل‌پیش‌بینی زاویه خورشید با صفحات خورشیدی و عدم امکان آزمایش واقعی آن بر روی زمین از اهمیت ویژه‌ای برخوردار است. این بستر سخت‌افزار در حلقه قابلیت استفاده برای راستی‌آزمایی و آزمودن طراحی زیرسامانة توان الکتریکی برای هر نوع ماهواره را دارد. در این مقاله، به عنوان نمونه، این بستر برای یک ماهوارة مخابراتی پیاده‌سازی شده است. میزان تغییرات ولتاژ دو سر باتری، میزان ظرفیت شارژ شدة باتری، بررسی صحت برد توزیع و برد شارژر، بررسی میزان عمق دشارژ باتری و دفعات شارژ و دشارژ و بررسی ولتاژ دو سر باتری در برابر جریان‌های لحظه‌ای از موارد مورد بررسی در حالت آرام‌سازی می‌باشد.

کلیدواژه‌ها

عنوان مقاله [English]

HIL Experimental Analyses of Satellite Electrical Power Subsystem (EPS) in De-tumbling Mode

نویسندگان [English]

  • Hadi Hosseini Onari 1
  • ehsan maani 2
  • Vahid Bohlouri 3
  • Soheil Seyedzamani 3

1 Satellite Research Institute, Iranian Space Research Center, Tehran, Iran.

2 Department of Mechanical Engineering, University of Tehran, Tehran, Iran.

3 Satellite Research Institute, Iranian Space Research Center, Tehran, Iran.

چکیده [English]

    In this study, hardware in the loop (HIL) simulation consisting of solar array simulator, programmable electric load, charger board, distribution board and attitude and position simulator is designed and developed for the mentioned purpose. Because of satellite high angular velocity in de-tumbling mode, it is not possible to perform the experimental tests for power consumption analysis. Electricalpower HIL can be used for modifying, redesigning, and verification of the electricalpower subsystem design. The power consumption of communications satellite components is simulated in a de-tumbling mode. De-tumbling mode of operation is implemented in HIL test bed and the experimental results are extracted. The results consisting of battery voltage, battery capacity, current, depth of discharge and voltage stability are investigated. The results of this paper can be useful in the design, implementation and verification of electrical power subsystem for a wide range of satellites from LEO to GEO.

کلیدواژه‌ها [English]

  • Communication satellite
  • Electricalpower subsystem
  • De-tumbling mode
  • Hardware in loop
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