مکانیک هوافضا

مکانیک هوافضا

اندازه‌گذاری و نمودار سطح شارژ مرجع سیستم جلوبرنده هواپیما هیبرید تحت شرایط خرابی

نوع مقاله : گرایش دینامیک، ارتعاشات و کنترل

نویسندگان
1 دانشجوی دکتری، دانشگاه علم و صنعت ایران، تهران، ایران
2 استاد، دانشگاه علم و صنعت ایران، تهران، ایران
چکیده
در این مقاله، روش اندازه‌گذاری و نمودار سطح شارژ مرجع برای یک هواپیمای هیبرید تحت شرایط خرابی ارائه شده است. با این هدف، ابتدا انواع ساختارهای سیستم جلوبرنده هیبرید به همراه اجزاء آنها معرفی شده است. سپس مودهای خرابی‌های اجزاء اصلی سیستم جلوبرنده هیبرید و تأثیر آن‌ها بر عملکرد هواپیما بررسی شده است. در ادامه، اندازه‌گذاری اجزاء سیستم جلوبرنده هیبرید موازی تحت خرابی‌های تمام توربین یا پک باتری، فرموله شده است. سپس نمودار سطح شارژ باتری مرجع به کمک شبیه‌سازی سیستم جلوبرنده هیبرید در طول یک مأموریت پروازی واقعی، باهدف تضمین فرود ایمن هواپیما در صورت خرابی تمام توربین‌ها ارائه شده است. به‌طوری که می‌بایستی مقدار سطح شارژ باتری در فاز کروز و نشستن به ترتیب حدود ۴۵-۳۵% و 65% باشد. در نهایت، با استفاده از نتایج حاصل از شبیه‌سازی هواپیما هیبرید موازی تحت مودهای خرابی بحرانی، درستی رویه اندازه‌گذاری پیشنهادی اثبات شده است. علاوه بر این، با ارائه نتایج شبیه‌سازی هواپیما هیبرید سالم ارضاشدن قیود عملکردی سیستم جلوبرنده هیبرید موازی صحه‌سنجی شده است.
کلیدواژه‌ها
موضوعات

عنوان مقاله English

Sizing and Reference SOC Trajectory of Hybrid Aircraft Propulsion System under Failure Conditions

نویسندگان English

Masoud Khasheinejad 1
Morteza Montazeri-Gh 2
1 PhD Student, Iran University of Science and Technology, Tehran, Iran
2 Professor, Iran University of Science and Technology, Tehran, Iran
چکیده English

In this paper, the sizing method and reference battery state of charge (SOC) trajectory for a hybrid aircraft under failure conditions are presented. With this aim, first, the types of hybrid-electric propulsion system (HEPS) structures along with their components are introduced. Then, the failure modes of HEPS main components and their impact on the aircraft performance are investigated. Next, the sizing of parallel HEPS under all-turbine and battery pack failures is formulated. Then, the reference SOC trajectory is presented by simulating the HEPS during a real flight mission, to ensure the safe landing of the aircraft in the event of all-turbine failure. So that the battery SOC in the cruise and descent phases should be about 35-45% and 65%, respectively. Finally, using the results of the parallel hybrid aircraft simulation under emergency failure modes, the correctness of the proposed sizing procedure has been proven. In addition, by presenting the simulation results of the healthy hybrid aircraft, the satisfaction of the performance constraints of the parallel HEPS has been validated.

کلیدواژه‌ها English

hybrid Propulsion Failure Modes Failure
Based Sizing Reference State of Charge Aircraft Simulation
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  • تاریخ دریافت 17 دی 1404
  • تاریخ بازنگری 08 اسفند 1404
  • تاریخ پذیرش 17 فروردین 1405
  • تاریخ انتشار 01 خرداد 1405