مدلسازی و تحلیل ناپایداری‌های آیروالاستیک در هواپیمای کامل انعطاف‌پذیر با استفاده از فرمول‌بندی شبه‌مختصات و مدل آیرودینامیکی حداقل متغیر حالت

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشکده مهندسی هوافضا، دانشگاه مالک اشتر، تهران، ایران

2 دانشکده مهندسی هوافضا، دانشگاه خواجه نصیرالدین طوسی، تهران، ایران

چکیده

هدف در کار حاضر ارائه‌ی یک مدل تحلیلی از هواپیمای انعطاف­‌پذیر کامل می‌­باشد که بتواند اثر مودهای دینامیک پرواز را در ناپایداری­‌های آیروالاستیک مورد بررسی قرار دهد. مدل پیشنهادی بر پایه‌ی دستگاه شبه‌مختصات استخراج شده و در آن، هواپیما به‌ عنوان یک سازه‌ی چندجزئی انعطاف‌پذیر شامل بدنه، بال‌ها و دم‌ها مدل می ­شود. نیروهای آیرودینامیکی وارد بر بال و دم با استفاده از روش حداقل متغیر حالت مدل­سازی می­شوند. این مدل انواع ناپایداری‌های آیروالاستیکی نظیر فلاتر جسم آزاد مود تناوب کوتاه و مود رول، فلاتر متقارن و پادمتقارن بال را شناسایی می­‌کند. نتایج حاصل از تحلیل‌ها نشان می‌دهد که تنها فلاترهای پادمتقارن بال و مود رول تحت تأثیر ممان اینرسی رول قرار دارند؛ به‌طوری‌که با افزایش ممان اینرسی رول، سرعت فلاتر در هر دو پدیده افزایش می‌یابد. از سوی دیگر ممان اینرسی پیچ و جرم در مود پلانج بر فلاتر متقارن بال و فلاتر جسم آزاد مود تناوب کوتاه مؤثر هستند. افزایش ممان اینرسی مود پیچ منجر به کاهش سرعت فلاتر بال متقارن و در مقابل، افزایش سرعت فلاتر جسم آزاد مود تناوب کوتاه می‌شود. همچنین، افزایش جرم در مود پلانج باعث افزایش سرعت فلاتر در هر دو پدیده فلاتر بال متقارن و فلاتر جسم آزاد مود تناوب کوتاه می‌گردد.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Modeling and Analysis of Aeroelastic Instabilities in a Flexible Full Aircraft Using Quasi-Coordinate Formulation and Minimum State Aerodynamic Model

نویسندگان [English]

  • Salman Shafaghat 1
  • Mohammadali Noorian 2
1 Faculty of Aerospace Engineering, Malek-Ashtar University of Technology
2 Aerospace Facutly,, K N Toosi University of Technology
چکیده [English]

The present study aims to develop an analytical model of a fully flexible aircraft capable of capturing the influence of flight dynamic modes on aeroelastic instabilities. The proposed formulation is based on the quasi-coordinate framework, wherein the aircraft is modeled as a multi-component flexible structure comprising the fuselage, wings, and tails. The aerodynamic forces acting on the wings and tails are modeled using the minimum state method. The model identifies various types of aeroelastic instabilities, including short-period and roll body-freedom flutter, as well as symmetric and antisymmetric wing flutter. The results indicate that only antisymmetric wing flutter and roll-mode body-freedom flutter are significantly influenced by roll moment of inertia, such that increasing the roll inertia raises the flutter velocity in both phenomena. Conversely, pitch moment of inertia and plunging mass predominantly affect symmetric wing flutter and short-period body-freedom flutter. Specifically, an increase in pitch inertia reduces the symmetric wing flutter velocity but increases the short-period body-freedom flutter velocity. Additionally, increasing the plunging mass elevates the flutter velocity for both symmetric wing and short-period body-freedom modes.

کلیدواژه‌ها [English]

  • Flexible Aircraft
  • Quasi-Coordinate Formulation
  • Minimum State Variable Method
  • Wing Flutter
  • Body Freedom Flutter
  • Effects of Flight Dynamic Modes

مراجع

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نشریه مهندسی مکانیک امیرکبیر
دوره 57، شماره 3
خرداد 1404
صفحه 283-302

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