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Nonlinear aeroelastic analysis of a two-dimensional wing with control surface in supersonic flow

Acta Mechanica Sinica 2010年第3期26卷 401-407页

作者： Guoyong Zheng School of Civil Engineering and Architecture Central South University 410075 Changsha China

Based on the piston theory of supersonic flow and the energy method, a two dimensional wing with a control surface in supersonic flow is theoretically modeled, in which the cubic stiffness in the torsional direction of the control surface is considered. An approximate method of the cha- otic response analysis of the nonlinear aeroelastic system is studied, the main idea of which is that under the condi- tion of stable limit cycle flutter of the aeroelastic system, the vibrations in the plunging and pitching of the wing can approximately be considered to be simple harmonic excita- tion to the control surface. The motion of the control surface can approximately be modeled by a nonlinear oscillation of one-degree-of-freedom. The range of the chaotic response of the aeroelastic system is approximately determined by means of the chaotic response of the nonlinear oscillator. The rich dynamic behaviors of the control surface are represented as bifurcation diagrams, phase-plane portraits and PS diagrams. The theoretical analysis is verified by the numerical results.

关键词： Piston theory Supersonic flow Chaos control surface Limit cycle flutter

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Nonlinear Aeroelastic Responses of an Airfoil with a control surface by Precise Integration Method

Nonlinear Aeroelastic Responses of an Airfoil with a Control...

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作者： Xiwen Huang Suxin Xie Yunping Zhang Yanmao Chen Department of Mechanics Sun Yat-sen University Basic Course Teaching Department Jiangxi Industry Polytechnic College Nari Technology Development Limited Company

This paper presents a highly accurate algorithm,based on precise integration method（PIM）,to investigate the aeroelastic system of an airfoil with control *** nonlinear system is separated as linear sub-systems,which are solved by PIM *** each step,a predictor-corrector algorithm is proposed to detect switching points between *** examples show that,the presented algorithm is much more accurate and efficient than the widely-used Runge-Kutta ***,the Runge-Kutta method even provides false *** such high precision and efficiency,the presented algorithm has the potential to become a benchmark for comparison in solving piecewise-smooth dynamical systems.

关键词： Airfoil control surface Piecewise Aeroelastic Precise integration method

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Nonlinear aeroelastic analysis of a twin-tail boom UAV with rudder freeplay nonlinearities

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CHINESE JOURNAL OF AERONAUTICS 2024年第9期37卷 276-296页

作者： Bai, Liuyue Wu, Zhigang Yang, Chao Beihang Univ Sch Aeronaut Sci & Engn Beijing 100191 Peoples R China

The issue of nonlinear structural freeplays in aircraft has always been a significant concern. This study investigates the aeroelastic characteristics of a twin-tail boom Unmanned Aerial Vehicle (UAV) with simultaneous freeplay nonlinearity in its left and right rudders. A comprehensive Limit Cycle Oscillation (LCO) solution route is proposed for complex aircraft with multiple freeplays, which can consider both accuracy and efficiency. For the first time, this study reveals the unique LCO characteristics exhibited by twin-tail boom UAVs with rudder freeplays and provides simulations and explanations of interesting phenomena observed during actual flight. The governing equations are established using the free-interface component mode synthesis method, and the LCOs of the system are mainly solved through the improved time-domain numerical continuation method and frequency-domain numerical continuation method. Furthermore, the study investigates the influence of the left and right rudder freeplay size ratio on the LCO characteristics. The results demonstrate that the twin-tail boom UAV exhibits two stable LCO types: close and differing left and right rudder amplitudes. The proposed method successfully describes the complete LCO behaviors of the system. Overall, this study makes significant contributions to our understanding of the aeroelastic behavior of twin-tail boom UAVs with rudder freeplays. (c) 2024 Production and hosting by Elsevier Ltd. on behalf of Chinese Society of Aeronautics and Astronautics. This is an open access article under the CC BY-NC-ND license (http://***/ licenses/by-nc-nd/4.0/).

关键词： Aeroelasticity Freeplay nonlinearity Limit cycle oscillation Numerical continuation Component mode synthesis LIMIT-CYCLE OSCILLATION STRUCTURAL NONLINEARITIES control surface BIFURCATION-ANALYSIS DYNAMIC-ANALYSIS FLUTTER AIRFOIL INTEGRATION SYSTEMS CONTINUATION

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