مدل‌سازی، طراحی و تست رانشگر فضایی نوع تک پیشرانه هیدرازینی برای نیروی تراست کم و کاربرد تغییر وضعیت ماهواره

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشجوی دکتری تخصصی مهندسی شیمی، دانشگاه آزاد اسلامی واحد علوم و تحقیقات، تهران، ایران

2 دانشیار مهندسی شیمی، دانشگاه صنعتی مالک اشتر، تهران، ایران

3 استادیار مهندسی شیمی، دانشگاه آزاد اسلامی واحد علوم و تحقیقات، تهران، ایران

چکیده

در این پژوهش یک سیستم پیشرانش فضایی نوع تک پیشرانه برای ایجاد نیروی تراست پنج نیوتنی و ضربه ویژه 220 ثانیه با کاربرد تنظیم حرکت یا تغییر وضعیت ماهواره مدل‌سازی و طراحی گردیده است.این مدل از دو بخش اصلی شامل یک راکتور کاتالیستی با خوراک هیدرازین، کاتالیست نیکل 15 درصد بر پایه گاما آلومینا و یک نازل همگرا- واگرا تشکیل شده است. راکتور مدل کاتالیستی، بستر ثابت، یک بعدی، جریان پایدار و آدیاباتیک با واکنش‌های تجزیه هتروژنی است. عملکرد فرایند با انجام دو واکنش تجزیه هتروژنی هیدرازین و آمونیاک و تبدیل به گازهای سبک هیدروژن و نیتروژن با دمای بالا بوده، سپس با خروج گاز از بستر و نازل نیروی رانش حاصل می‌گردد. کاتالیست از روش اشباع‌سازی مرطوب ساخته شده و ویژگی‌های لازم با آزمایش‌های آنالیز کمی، کیفی و حرارتی تعیین می‌گردد. نتایج مدل‌سازی شامل متغیرهای جرم، انرژی، سینتیکی، فیزیکی و شیمیایی در رانشگر فضایی است. از مزیت‌های مهم این طراحی اندازه‌گیری و پیش‌بینی متغیرها است. برای تعیین عملکرد و درستی مدل طراحی و آزمایشی(در شرایط اتمسفری و استاتیک) در شاخص‌هایی مثل نیروی رانش، ضربه ویژه، افت فشار بستر، حداقل مقدار تجزیه آمونیاک با شرایط سینتیکی و عملیاتی یکسان مورد بررسی قرار گرفت. نتایج حاصل تطابق مناسب داشته و مورد تأیید می‌باشند.

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Modeling, Design and Testing of Space Thruster Type Hydrazine Monopropellant for the Low Propulsion and the Application of Satellite Status Change

نویسندگان [English]

  • H. ebrahim 1
  • Sh. Ghanbari Pakdehi 2
  • S. A. Alavi 3
1 Ph. D. Student of Chemical Engineering, Islamic Azad University, Science and Research Branch, Tehran, Iran
2 Associate Professor of Chemical Engineering, Malek Ashtar University of Technology, Tehran, Iran
3 Assistant Professor of Chemical Engineering, Islamic Azad University, Science and Research Branch, Tehran, Iran
چکیده [English]

In the present study, a space thruster system type monopropellant has been modeled and designed so as to create a Five- Newton thrust force(propulsion) and specific impulse of 220 seconds, with the usage of adjusting motion or changing the position of the satellite. This model consists of two major parts including a catalytic reactor with hydrazine feed, 15% nickel catalyst based on gamma alumina and a convergent-divergent nozzle. The catalytic reactor model is a fixed bed, one-dimensional, steady state and adiabatic with heterogeneous decomposition reactions. The process functions by performing two heterogeneous decomposition reactions of hydrazine and ammonia and converting to light gases (hydrogen and nitrogen) with high temperatures. Subsequently, the thrust force will be obtained by the evolution of the gas from bed and nozzle. The catalyst is made up of wet impregnation method and the required characteristics are specified by quantitative, qualitative and thermal analysis tests. The outcomes of modelling include mass, energy, kinetic, physical and chemical variables in the space propulsion. It is also considered as one of the important advantages of designing the measurement and predicting the variables. So as to determine the performance and validity of the model, indicators such as the thrust force, specific impulse, bed pressure drop and the minimum of ammonia decomposition has been scrutinized with the same kinetic and operating conditions in the designing and experimental model (in atmospheric conditions and static).
The obtained results are consistent and have been verified.

کلیدواژه‌ها [English]

  • Heterogeneous Decomposition
  • Modeling
  • Hydrazine
  • Adiabatic
  • Thruster
  • Monopropellant
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