کنترل و کاهش بارهای ناشی از تندباد در هواپیمای انعطاف‌پذیر

نوع مقاله : مقاله پژوهشی

نویسندگان

1 محقق-مجتمع دانشگاهی هوافضا- دانشگاه صنعتی مالک اشتر

2 دینامیک پرواز و کنترل-مجتمع دانشگاهی هوافضا-دانشگاه صنعتی مالک اشتر

3 دانشگاه صنعتی مالک اشتر

چکیده

وظیفه سیستم‌های کاهش بارهای تندباد کم کردن بارهای وارد بر بدنه پرنده در حال عبور از اغتشاشات جوی می‌باشد. استفاده از کنترل فعال در حالی که هواپیما از این اغتشاشات عبور می‌کند باعث کاهش بارهای وارد بر سازه، کاهش شتاب در نقاط خاص هواپیما شده و کیفیت پروازی آن را بهبود می‌بخشد. در این مقاله پاسخ یک هواپیمای انعطاف‌پذیر به تندباد با در نظر گرفتن یک مدل همگیر توسعه یافته به کمک روش لاگرانژ و آیرودینامیک شبه‌پایا مورد بررسی قرار گرفته است. بال بصورت انعطاف پذیر و بقیه هواپیما صلب در نظر گرفته می‌شود. مدل توسعه یافته به عنوان یک مدل پایه شامل دو مود جسم صلب و بال انعطاف پذیر مدل شده بصورت تیر با مودهای خمشی و پیچشی در نظر گرفته شده و پاسخ به الگوهای مختلف تندباد گسسته مورد بررسی قرار گرفته است. برای کاهش بارهای ناشی از تندباد از الویتور و فلپرون استفاده شده است و با استفاده از کنترل تطبیقی‌عصبی بر اساس وارون‌دینامیک سعی در کنترل نوسانات پیچ و شتاب وارده بر هواپیما شده است. پاسخ هواپیما به تندباد در حالت حلقه باز و حلقه بسته مقایسه شده است.

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Gust Load Alleviation of Flexible Aircraft

نویسندگان [English]

  • Javad Masrour 1
  • S.hossein sadati 2
  • Morteza Shahravi 3
1 Researcher/Aerospace complex- Malek Ashtar university-Tehran - Iran
2 Aerospace Engineering -Malek Ashtar University
3 Associate professor/Aerospace complex? Malek Ashtar University of Technology/ Tehran /Iran
چکیده [English]

Concerns about aircraft gust disturbance have increased not only because of the design cases that are not primarily structural but also because of gust influence on aircraft handling qualities and flight controllability. Load alleviation system duty is reducing loads caused by a gust on aircraft. Using active control when crossing gust causes alleviation of loads on aircraft and improves ride quality. In this paper gust response of a flexible aircraft has been simulated by using the Lagrange equation and quasi-steady aerodynamics. Wing has been considered as flexible and other parts have been considered rigid. Two degrees of freedom in pitch and plunge of rigid mode have been considered and the elastic wing has been modeled as a beam with torsion and bending. Gust responses with different profiles have been analyzed. Then by using elevators and aileron gust loads have been reduced. Feedback control has been used to decrease the pitch and heave acceleration of the aircraft. Closed and open-loop response to gust has been compared and it has been shown that pitch oscillations have been damped very well by elevator. Then by using elevators and flaperon gust loads have been reduced by using neural networks adaptive controller and classic controller. Comparison has been made between closed-loop and open loop response to gust.

کلیدواژه‌ها [English]

  • Flexible aircraft
  • Quasi-steady aerodynamics
  • Gust load alleviation
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