مطالعه عددی تاثیر اندازه ذرات و طول بستر کاتالیستی بر نیروی پیشران و ضربه ویژه یک رانشگر تک‌پیشرانه

نوع مقاله : گرایش پیشرانش و انتقال حرارت

نویسنده

شریف

چکیده

رانش‏گرهای تک‏پیشرانه با توجه به سادگی ساختمان و قابلیت اطمینان بالایی که دارند،  به‏طور گسترده در ماهواره­ها مورد استفاده قرار   می­گیرند. یک رانشگر تک‏پیشرانه از سه بخش انژکتور، محفظه تجزیه و نازل تشکیل شده است. پیشرانه از طریق انژکتور روی بستر کاتالیستی متشکل از  ذرات کاتالیست پاشیده شده و بلافاصله تجزیه می­شود. گاز ناشی از تجزیه پیشرانه در نازل شتاب گرفته و نیروی پیشران تولید می­کند. در این تحقیق، یک رانشگر  تک‏پیشرانه هیدرازینی با بستر کاتالیستی از جنس فلز فعال ایریدیم به‏صورت عددی تحلیل می­شود. معادلات حاکم بر انتقال جرم و حرارت داخل بستر کاتالیستی به صورت یک‏بعدی مدل‏سازی می­شوند. لازم به‏ذکر است که به دلیل عدم وجود تعادل شیمیایی و ترمودینامیکی بین دو فاز، معادلات انتقال جرم و حرارت جداگانه­ای مطابق تحقیق شنکار و همکارانش برای فازهای جامد و گاز نوشته شده است. همچنین، برای محاسبه نیروی پیشران و ضربه ویژه مجموعه رانشگر، نازل همگرا-واگرا  به‏صورت صفربعدی تحلیل   می­شود. با استفاده از این روش،  تاثیر قطر  ذرات بستر کاتالیستی و طول محفظه تجزیه به­عنوان دو فاکتور مهم روی عملکرد یک رانشگر نمونه بررسی می­شود. نتایج حاصل نشان می­دهند که با کاهش قطر  ذرات تشکیل­ دهنده بستر کاتالیستی،  طول بهینه محفظه تجزیه کاهش یافته و ضربه ویژه بیشینه تا حدودی افزایش می­یابد.

کلیدواژه‌ها

عنوان مقاله [English]

Numerical Study of Catalyst Bed Length and Particle Size Effect on the Monopropellant Thruster Specific Impulse and Thrust

نویسنده [English]

  • mohamadreza salimi
sharif
چکیده [English]

Monopropellant thrusters are very popular in satellite propulsion systems due to their simplicity and reliability. A monopropellant thruster commonly consists of three major components: injector, decomposition chamber and nozzle. Fuel is injected over catalyst bed through an injector and decomposed there instantaneously. The resulting hot gases are expanded through the nozzle section and produce thrust. In this study a Hydrazine monopropellant thruster with Iridium based catalyst bed is analyzed numerically. To this end, one dimensional heat and mass transfer equations are simulated numerically inside the catalyst bed. Since, decomposed gases are not in thermal and chemical equilibrium with catalyst solid particles, two sets of equations are solved for solid and fluid phases (based on the Shankar et al. research). Additionally, a zero-dimension analysis is performed for convergence-divergence nozzle to compute thrust and specific impulse. Using this method, effects of particles size and decomposition chamber length on thruster performance are investigated. The related results indicate that, decreasing the catalyst particles, decreases optimum decomposition chamber length and increases specific impulse.          

کلیدواژه‌ها [English]

  • Monopropellant Thrusters
  • Catalytic Decomposition
  • Thermal and Chemical Non-equilibrium
  • Catalyst particles Size
  • Decomposition Chamber Length

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سابقه مقاله

  • تاریخ دریافت: 10 دی 1397
  • تاریخ بازنگری: 23 بهمن 1397
  • تاریخ پذیرش: 12 آذر 1398
  • تاریخ انتشار: 01 فروردین 1399

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