论文部分内容阅读
针对翼-身组合体飞行器面对称布局的特点,利用模态振型的对称和反对称性,以分枝模态法建立结构的运动微分方程,结合CFD的当地流活塞理论计算飞行器的非定常气动力,建立飞行器全机组合体的气动弹性数学模型。对飞行器进行了来流为1.5~7马赫数下的颤振分析,结果与全CFD/CSD耦合时域仿真结果较好吻合,验证了本文方法在工程设计中的有效性和可行性。本文方法的效率在相同精度下比CFD/CSD耦合的时域方法高100倍。
According to the symmetrical and antisymmetric mode shapes of the wing-body combination aircraft, the differential equation of motion of the wing-body combination aircraft is established by using the branch mode method, and the local flow piston theory of CFD is used to calculate the non- Constant aerodynamic force, the establishment of aeroelastic mathematic model of the whole aircraft assembly. The flutter analysis of the aircraft with a flow rate of 1.5 to 7 Mach was performed. The results are in good agreement with the results of CFD / CSD coupled time domain simulations, which proves the effectiveness and feasibility of this method in engineering design. The efficiency of our method is 100 times higher than the CFD / CSD coupled time-domain method with the same accuracy.