ACTIVE LOAD CONTROL OF A REGIONAL AIRCRAFT WING EQUIPPED WITH MORPHING WINGLETS 机翻标题: 暂无翻译,请尝试点击翻译按钮。

会议集名/来源
Proceedings of the ASME Conference on Smart Materials, Adaptive Structures and Intelligent Systems 2018: SMASIS 2018, September 10-12, 2018, San Antonio, Texas, USA, volume 1. Development and Characterization of Multifunctional Materials; Modeling, Simulation, and Control of Adaptive Systems; Integrated System Design and Implementation
出版年
2018
页码
V001T04A02-V001T04A02
会议地点
San Antonio
作者单位
Politecnico di MilanoItalSystem s.r.lItalSystem s.r.lCentro Italiano Ricerche AerospazialiPolitecnico di Milano
作者
Federico Fonte;Giuseppe Iannaccone;Nicola Cimminiello;Ignazio Dimino;Sergio Ricci
摘要
Morphing winglets are innovative aircraft devices capable to adaptively enhance aircraft lift distribution throughout the flight mission while providing augmented roll and yaw control capability. Within the scope of the Clean Sky 2 REG IADP, this paper deals with nonlinear simulations of a regional aircraft wing equipped with active morphing winglets in manoeuvring conditions. The fault tolerant morphing winglet architecture is based on two independent and asynchronous control surfaces with variable camber and differential settings capability. The mechanical system is designed to face different flight static and dynamic situations by a proper action on the movable control tabs. The potential for reducing wing and winglet loads by means of the winglet control surfaces is numerically assessed by means of static aeroelastic analyses, using a feedforward manoeuvre load alleviation controller. An electro-mechanical Matlab/Simulink model of the actuation architecture is used as design tool to preliminary evaluate the complete system performance and the ability to cope with the expected morphing aeroshapes. Then, the aeroelastic model of the aircraft is combined with the nonlinear simulator of the response of the winglet actuation system to evaluate a symmetric and asymmetric manoeuvres obtained by a sudden deflection of the main control surfaces. The use of the morphing winglet tabs shows to alleviate the wing loads in such conditions. The introduction of the dynamic actuator model leads to a reduction of the performances with respect to predictions of the static analyses but a reduction of the manoeuvre loads can still be observed.
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