مهندسی مکانیک مدرس

مهندسی مکانیک مدرس

مطالعه‌ی تجربی پارامترهای عملکردی یک تراستر پلاسمایی با رژیم تخلیه‌ی مانع دی‌الکتریک تحت میدان مغناطیسی

نوع مقاله : پژوهشی اصیل

نویسندگان
1 استادیار، دانشکده فناوری‌های نوین و مهندسی هوافضا، دانشگاه شهید بهشتی، تهران، ایران
2 دانشجوی کارشناسی ارشد، دانشکده فناوری‌های نوین و مهندسی هوافضا، دانشگاه شهید بهشتی، تهران، ایران
چکیده
در این پژوهش، جریان کانال ناشی از پلاسمای تخلیه­ی مانع دی الکتریک تحت میدان مغناطیسی اعمالی برای استفاده به عنوان تراستر در کاربردهای پیشرانشی پیشنهاد شده و به صورت تجربی مورد مطالعه قرار گرفته است. اندازه­گیری­های مقـادیر نیروی پیشـران و توان مصرفی تراسـتر به ازای مقادیر مخـتلف ضخـامت مانع دی­الکتریک انجام شده و داده­ها با مقادیر متناظر با حالت بدون میدان مغناطیسی مقایسه شده­اند. مشخص گردید که توان مصرفی و نیروی پیشران تراستر در حضور میدان مغناطیسی نسبت به حالت بدون آن، به ترتیب قدری کاهش و افزایش پیدا می­کنند. اندازه­گیری­ها نشان می­دهند که با افزایش یکنواخت ولتاژ اعمالی در دامنه 12 تا 26 کیلوولت، پارامترکارایی تا حداکثر مقدار خود افزایش و سپس کاهش می­یابد. یک تحلیل مبتنی بر قانون توانی برای آشکار کردن روابط بین پارامتر کارایی، نیروی پیشران، توان مصرفی و ولتاژ اعمالی برای تراستر برای حالت با و بدون میدان مغناطیسی ارائه شده است. نتایج نشان می­دهند که حضور میدان مغناطیسی و مانع دی­الکتریک ضخیم­تر می­توانند منجر به مقادیر بالاتر پارامترکارایی به ویژه پس از انتقال از رژیم برافروختگی به رژیم رگه­ای شوند. اثرات میکروکانال­های تخلیه در هر دو رژیم مذکور بر پارامتر کارایی مورد بحث قرار گرفته است. مشاهدات تجربی نشان می­دهند که در حضور میدان مغناطیسی، میکروکانال­های تخلیه­ی اضافی تولید شده و در امتداد خطوط میدان مغناطیسی توسعه می­یابند، به طوری که انتشار نفوذی تخلیه در پلاسما قوی­تر می­شود. مکانیزم فیزیکی حاکم بر این پدیده­ها تشریح شده و عمدتاً به میزان یونیزاسیون افزایش یافته­ی ناشی از میدان مغناطیسی مرتبط شده است.
کلیدواژه‌ها

موضوعات


عنوان مقاله English

Experimental study of the performance parameters of a plasma thruster using dielectric barrier discharge with the magnetic field

نویسندگان English

Mahdy Ahangar 1
Arefeh Hoseini 2
1 Assistant Professor, Faculty of New Technology & Aerospace Engineering, Shahid Beheshti University, Tehran, Iran
2 M.Sc. Student, Faculty of New Technology & Aerospace Engineering, Shahid Beheshti University, Tehran, Iran
چکیده English

In this research, the dielectric barrier discharge plasma driven channel flow with the applied magnetic field has been proposed for use as a thruster in propulsion applications and studied experimentally. Measurements of the thrust and consumed power of thruster for different values of the barrier thickness have been performed and the data have been compared with the corresponding ones without magnetic field. It is found that consumed power and thrust of the thruster in the presence of magnetic field are respectively little reduced and increased than that without the magnetic field. The measurements show that the effectiveness increases to a maximum and then drops as the operating voltage monotonically increases over a range from 12 to 26 kV. A power law analysis for revealing the relationships among the effectiveness, thrust, consumed power, and operating voltage has been presented for the thruster with and without the magnetic field. It is seen that the applied magnetic field and thicker dielectric barrier can lead to a higher effectiveness at the point of transition from the glow regime to the filamentary regime. The effects of micro-discharge channels on the effectiveness in the both regimes have been discussed. The observations indicate that in the presence of magnetic field, the additional micro-discharge channels are generated and develop along the magnetic field lines and the diffuse background emission of the discharge is stronger in plasma. The underlying physical mechanisms of mentioned phenomena have been explained and mainly ascribed to the enhanced ionization by applying the magnetic field.

کلیدواژه‌ها English

Experimental measurements
Power law
Filamentary regime
Monitor capacitor method
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https://www.kjmagnetics.com/calculator.asp
https://www.kjmagnetics.com/calculator.asp
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