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Aerodynamic analysis and structural integrity for optimal performance of sweeping and spanning morphing unmanned air vehicles

机译：空气动力学分析和结构完整性，实现扫除与跨越无人驾驶车辆的最佳性能

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An optimized morphing unmanned aerial vehicle capable of sweeping and spanning its wings is proposed and analyzed aerodynamically and structurally in order to examine and improve its efficiency, flight transition analysis, and structural integrity. The lift to drag ratio of five different flight modes of the drone is examined using the Pollhamus lift theory to evaluate the aerodynamic performance during the transition phases. To verify Pollhamus lift theory in the determination of the aerodynamic loads for the four configurations of the morphing unmanned system, namely, fully compressed, fully expanded, fully swept, and fully expanded and swept, 3D panel and Vortex Lattice Methods are used. In order to improve the structural stability during the transition phase of the flight, a finite element analysis is conducted to approximate pressures on the wings of the unmanned system under a load and specific boundary conditions. The information from the finite element simulations is then utilized to determine the number of support rods needed for structural stability and the ideal positions of the rods. The vibratory qualities of the wings are also analyzed through modal and transient analyses. According to the results of the modal analysis, because of the low natural frequency of the wing, there is a strong possibility of flutter and a vibratory response due to the aerodynamic force and disturbances. The transient analysis demonstrates that the stress waves propagating through the wings, due to an excitation force, tend to localize around the circumference of the support rods. (C) 2020 Elsevier Masson SAS. All rights reserved.
机译：一种优化的变形无人空中的空气，能够在空气动力学和结构上进行扫描和跨越其翅膀，以便检查和改善其效率，飞行过渡分析和结构完整性。使用Pollhamus Lift理论研究了五种不同飞行模式的升力与无人机的五种不同飞行模式的拖曳比率来评估过渡阶段期间的空气动力学性能。为了验证Follhamus Lift理论，在确定变形无人系统的四种配置的空气动力载荷中，使用完全压缩，完全扩展，完全扫描，完全扩展和完全扩展，3D面板和涡流晶格方法。为了改善飞行的过渡阶段期间的结构稳定性，在负载和特定边界条件下进行有限元分析以近似于无人系统的翅膀上的压力。然后利用来自有限元模拟的信息来确定结构稳定性和杆的理想位置所需的支撑杆的数量。通过模态和瞬态分析，还分析了翅膀的振动质量。根据模态分析的结果，由于机翼的较低频率低，由于空气动力和干扰，存在强烈的颤动和振动反应的可能性。瞬态分析表明，由于激发力，通过翼传播的应力波倾向于围绕支撑杆的圆周定位。 （c）2020 Elsevier Masson SAS。版权所有。

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