“…The other notable point is that by choosing an unsuitable time interval ( t), numerical instability can occur. This can a ect the results and an inappropriate utter speed, which are predicted by the present method [32]. For example, by choosing v = 49 m/sec and two di erent time intervals, as shown in Figure 15, di erent results are achieved.…”
The main aim of this paper is to develop an e cient aeroelastic tool for predicting the utter speed of a typical section in transonic regime. An implicit meshless method, based on Euler and Navier-Stokes equations, is conducted to simulate the transonic uid ow around an airfoil. This technique is applied directly to the di erential form of the aerodynamic governing equations and the time integration is carried out using a dual-time implicit time discretization scheme. The capabilities of the ow solution method are demonstrated by ow computations around NACA0012 airfoil under di erent ow conditions. For structural dynamics simulation, a typical section model with pitching and plunging motion capability is considered. Finally, the aeroelastic analysis of the 2D model is performed by the consecutive simulation of both structural and aerodynamic domains. Also, the e ect of viscosity and time interval choice between two structural and aerodynamic solvers on utter instability is studied. A comparison between the obtained results and those available in the literature shows the good accuracy of the present method.
“…The other notable point is that by choosing an unsuitable time interval ( t), numerical instability can occur. This can a ect the results and an inappropriate utter speed, which are predicted by the present method [32]. For example, by choosing v = 49 m/sec and two di erent time intervals, as shown in Figure 15, di erent results are achieved.…”
The main aim of this paper is to develop an e cient aeroelastic tool for predicting the utter speed of a typical section in transonic regime. An implicit meshless method, based on Euler and Navier-Stokes equations, is conducted to simulate the transonic uid ow around an airfoil. This technique is applied directly to the di erential form of the aerodynamic governing equations and the time integration is carried out using a dual-time implicit time discretization scheme. The capabilities of the ow solution method are demonstrated by ow computations around NACA0012 airfoil under di erent ow conditions. For structural dynamics simulation, a typical section model with pitching and plunging motion capability is considered. Finally, the aeroelastic analysis of the 2D model is performed by the consecutive simulation of both structural and aerodynamic domains. Also, the e ect of viscosity and time interval choice between two structural and aerodynamic solvers on utter instability is studied. A comparison between the obtained results and those available in the literature shows the good accuracy of the present method.
“…Do đó để đảm bảo máy bay hoạt động ổn định thì ngoài hệ thống điều khiển để đảm bảo cân bằng cho các chong chóng, hệ thống cánh chính cũng phải đảm bảo bền và ổn định. Việc phân tích trạng thái động của kết cấu cánh máy bay giúp đánh giá khả năng hoạt động của máy bay khi có nhiễu động liên quan đến các hiện tượng đàn hồi khí động như hiện tượng "flutter", hiện tượng "buffeting" xảy ra [6]. Từ đó cho phép thiết kế hệ thống điều khiển giảm rung động để tránh cấu trúc cánh máy bay biến dạng lớn và hư hỏng.…”
Bài báo đưa ra tính toán thiết kế kết cấu cho cánh máy bay UAV cỡ nhỏ làm bằng vật liệu composite phục vụ nhiệm vụ quan sát. Thiết kế dựa trên việc phân tích đáp ứng tĩnh và động của kết cấu cánh khi chịu tải khí động bằng phương pháp phần tử hữu hạn và đánh giá khả năng chịu tải của cánh theo tiêu chuẩn phá hủy Tsai-Wu. Ba mô hình cánh khác nhau thỏa mãn yêu cầu về khối lượng thiết kế được xem xét. Dựa trên các phân tích về trường chuyển vị, tr ường biến dạng và giá trị Tsai-Wu, bài báo đưa ra lựa chọn kết cấu cánh phù hợp
“…Marqui, Erturk, and Inman (2010) presented a time-domain piezoaeroelastic modeling and numerical simulations of a generator wing with embedded piezoceramics for continuous-and segmented-electrode configurations. Their wing-based piezoaeroelastic energy harvester model was obtained by combining an electromechanically coupled finite element (FE) model (Marqui, Erturk, & Inman, 2009) based on the classical plate theory with an unsteady vortex-lattice model (Benini, Belo, & Marques, 2004;Katz & Plotkin, 2001) representing the aerodynamic loads. They reported that low aerodynamic damping was obtained at low wind speeds and close to the linear flutter speed.…”
Section: Work Considering Linear Theoretical and Experimental Modelsmentioning
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