بررسی عملکرد تراستر دومولفه‌ای با نرم‌افزار توسعه یافته تحلیل محفظه رانش موتورهای فضایی

عیدی عطارزاده, مسعود; سرآبادانی, عطیه; داورنیا, غزال; خسروبیگی, حامد; فرشچی, محمد; رمضانی, علیرضا

doi:10.22034/jsst.2021.1223

نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

¹ دانشکده مهندسی هوافضا، دانشگاه صنعتی شریف، تهران، ایران

² دفتر خدمات فناوری ، دانشگاه صنعتی شریف، تهران، ایران

³ دفتر خدمات فناوری، دانشگاه صنعتی شریف، تهران، ایران

⁴ پژوهشکده سامانه‌های حمل‌ و نقل فضایی، پژوهشگاه فضایی ایران، تهران، ایران

https://doi.org/10.22034/jsst.2021.1223

چکیده

در مرحله طراحی موتورهای پیشران فضایی، استفاده از نرم‌افزارهایی با هزینه‌ی محاسباتی کم، از اهمیت فوق‌العاده‌ای برخوردار است. در این مقاله یک نرم‌افزار مدل‌سازی محفظه رانش موتورهای فضایی دومؤلفه‌ای در مقیاس کوچک توسعه داده می‌شود. با استفاده از مدل‌های پاشش و تبخیر، فرآیندهای تزریق پیشرانه و توزیع تبخیر محاسبه می‌گردد. حلگر احتراقی با استفاده از سینتیک شیمیایی، فرآیند احتراق درون محفظه را به صورت یک‌بعدی در راستای محور محفظه رانش محاسبه می‌کند. حلگر خنک‌کاری، میزان انتقال حرارت از گازهای داغ به فیلم‌های خنک‌کاری و محیط بیرون را پیش‌بینی می‌کند. اعتبارسنجی مدل‌ها نشان می‌دهد که خطای آن‌ها در شبیه‌سازی فرآیندها قابل‌قبول است. با استفاده از ابزار توسعه داده شده، عملکرد تراستر دومؤلفه‌ای شرکت آستریوم با سوخت منومتیل‌هیدرازین و تتراکسید نیتروژن و سینتیک احتراقی گسترده، مورد بررسی قرار گرفته است. نتایج نشان می‌دهد که دمای گازهای درون محفظه یکنواخت نبوده و دارای پیک است. همچنین فرآیند تبخیر قطرات سوخت و اکسنده تا گلوگاه نازل ادامه دارد.

کلیدواژه‌ها

20.1001.1.20084560.1400.14.2.3.2

عنوان مقاله [English]

Investigation of a Bi-propellant Thruster by a Developed Space Engine’s Thrust Chamber Analysis Code

نویسندگان [English]

Masoud EidiAttarZade ¹
Atiyeh SarAbadani ²
ghazal davarnia ³
Hamed Khosrobeygi ²
Mohammad Farshchi ¹
alireza Ramezani ⁴

¹ Aerospace Engineering University, Sharif University of Technology, Tehran, Iran

² Sharif Technology Services Complex, Sharif University of Technology, Tehran. Iran

³ Sharif Technology Services Complex, Sharif University of Technology, Tehran, Iran

⁴ Space Transportation Research Institute, Iranian Space Research Center, Tehran,Iran

چکیده [English]

Numerical modeling of space engines aside the experimental test is routine. In the design step of such engines, low-cost softwares are vital. In this paper, small-scale space engine thrust chamber analysis code will be developed. In this code, propellant injection and evaporation distribution will be modelled. 1D Combustion solver calculates the reactions of distributed fuel and oxidizer through the thrust chamber axis by chemical mechanisms. Then the cooling solver computes the heat transfer from hot gases to the film cooling layer and the outer surroundings. Validation shows acceptable errors in the modelling of processes. By this developed code, the performance of the Astrium bi-propellant thruster with MonoMethylHydrazine and NitrogenTetrOxide and distributed chemical reaction has been investigated. Results show that hot gas temperature inside the combustor is not uniform and has a peak. Furthermore, the evaporation of the propellant droplets is continued to the nozzle throat.

کلیدواژه‌ها [English]

Analysis Code
Injection
Combustion
Bi-propellant Thruster
Space Engine

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علوم و فناوری فضایی

بررسی عملکرد تراستر دومولفه‌ای با نرم‌افزار توسعه یافته تحلیل محفظه رانش موتورهای فضایی

مراجع

مراجع

دوره 14، شماره 2 - شماره پیاپی 47
تیر 1400
صفحه 47-37

بررسی عملکرد تراستر دومولفه‌ای با نرم‌افزار توسعه یافته تحلیل محفظه رانش موتورهای فضایی

مراجع

مراجع

دوره 14، شماره 2 - شماره پیاپی 47تیر 1400صفحه 47-37

دوره 14، شماره 2 - شماره پیاپی 47
تیر 1400
صفحه 47-37