飛機陣風(fēng)響應(yīng)仿真計算及載荷減緩技術(shù)研究.pdf

1、南京航空航天大學(xué)碩士學(xué)位論文飛機陣風(fēng)響應(yīng)仿真計算及載荷減緩技術(shù)研究姓名：曹九發(fā)申請學(xué)位級別：碩士專業(yè)：飛行器設(shè)計指導(dǎo)教師：沈宏良2010-12飛機陣風(fēng)響應(yīng)仿真計算及載荷減緩技術(shù)研究 IIAbstract The work presented in the paper is to research the flight simulation of gust response and gust load a

2、lleviation technology. When encountering gust, the airplane appear bump,and the load acting on aircraft wing changes rapidly, which decreases aircraft ride quality and reduces structural life- tim

3、e. Especially for the future flexible aircraft, due to the significant flexibility effect, the body movement and the structure movement appear dynamic coupling, which has a greater impact on flig

4、ht safety. As a consequence, the gust load alleviation system based on active control technology is introduced, which can inhibit the response of the aircraft against the gust, slow wing flutter intensit

5、y, improve the fatigue strength of the wing structure, and improve the ride quality. The research in this paper could be divided into three parts. Firstly, the atmospheric turbulence model bas

6、ed on the rational spectral theory is established in both frequency domain for flight control law design and time- domain for flight simulation. Secondly, the flight dynamic model considering fl

7、exible structure is established, which is used to analyze the dynamic characteristics of the airplane. Finally, based on LQG/LIT methods, the optimizing design for gust alleviation system is est

8、ablished in order to minimize the comprehensive goal considering the aircraft flying qualities, performance and vibration reducing. The simulation results show that the proposed atmospheric turbulen

9、ce model is fit for gust alleviation system design, and the designed flight control law based on multi- objective optimization method has great positive effects on reducing the airplane’ s gust