طراحی، ساخت و آزمون یک رانشگر جت مقاومتی متناسب با شرایط اتمسفری

نوع مقاله : مقاله پژوهشی

نویسندگان

1 استادیار، پژوهشگاه فضایی ایران، تبریز، ایران

2 دانشجوی دکتری، پژوهشگاه فضایی ایران، تبریز، ایران

3 کارشناسی ارشد،پژوهشگاه فضایی ایران، تبریز، ایران

چکیده

هدف این مقاله طراحی و ساخت یک رانشگر جت مقاومتی بر اساس پیشران بوتان با قابلیت انجام آزمون در شرایط اتمسفری است. بخش­های مهم طراحی برای این سیستم عبارت‌اند از طراحی هیتر و نازل. هیتر مورداستفاده به‌صورت انتقال حرارت مستقیم طراحی شده و طراحی نازل نیز بر اساس روابط ترمودینامیکی حاکم بر نازل همگرا- واگرا و مناسب فشار خروجی اتمسفر انجام شده است. همچنین برای بررسی جریان سیال پیشرانه در نازل از شبیه­سازی CFD استفاده شده است. در ادامه رانشگر جت مقاومتی بر اساس طراحی انجام‌گرفته ساخته شده و آزمون­های تجربی برای صحه­سنجی آن انجام شده است. با بررسی پارامترهای عملکردی رانشگر جت مقاومتی از جمله نیروی رانش و ضربه ویژه حاصل از نتایج آزمون­های تجربی و روابط ترمودینامیکی، طراحی رانشگر صحه­گذاری می­شود. با درنظرگرفتن توان مبدل حرارتی 30 وات و همچنین بهینه­ترین شرایط موجود، بازده رانشگر برابر 21 درصد، نیروی رانش برابر 36 میلی نیوتن و ضربه ویژه برابر 9/35 ثانیه حاصل می­شود.

کلیدواژه‌ها

عنوان مقاله [English]

Design, Manufacturing and Testing of a Resistojet Suitable for Atmospheric Conditions

نویسندگان [English]

  • Morteza Farhid 1
  • Moharram Moharram 1
  • Arezoo Esmaeili 2
  • adel pourtaghi 3
1 Assistant ProfessorIranian Space Research Center, Tabriz, Iran
2 PhD student, Iran Space Research Institute, Tabriz, Iran
3 Master's degree, Iran Space Research Institute, Tabriz, Iran
چکیده [English]

The purpose of this paper is to design and manufacture a resistojet thruster based on butane propellant with the ability to perform tests in atmospheric conditions. The important sections for designing of this system are heater and nozzle design. The utilized heater is designed for direct heat transfer and the design of the nozzle is based on the thermodynamic relations governing a converging-diverging nozzle which is suitable for the atmospheric outlet pressure. CFD simulation has also been used to investigate the flow of propellant in the nozzle. In the following, the resistojet thruster was built based on the designing and experimental tests were carried out for its validation. By comparing the functional parameters of the thruster, such as thrust force and specific impulse from the experimental results and thermodynamic relationships, the design of the thruster is validated. Considering the heat exchanger power of 30 watts and also the most optimal conditions, the efficiency of the thruster is 21%, the thrust force is 36 millinewtons and the specific impact is computed as 35.9 seconds.

کلیدواژه‌ها [English]

  • Resistojet
  • Nozzle
  • Electrical Heater
  • Thrust Force
  • Specific Impulse

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https://creativecommons.org/licenses/by/4.0/

مراجع

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مکانیک سیالات و آیرودینامیک
دوره 12، شماره 2 - شماره پیاپی 32
پاییز و زمستان 1402
اسفند 1402
صفحه 141-152

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سابقه مقاله

  • تاریخ دریافت: 02 آبان 1402
  • تاریخ بازنگری: 28 دی 1402
  • تاریخ پذیرش: 05 بهمن 1402
  • تاریخ انتشار: 30 بهمن 1402

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