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.

为了检查和提高其效率，飞行过渡分析和结构完整性，提出了一种能够横扫和跨越机翼的优化变形无人飞行器，并对其进行了空气动力学和结构分析。使用Pollhamus升力理论检查了无人机的五个不同飞行模式的升阻比，以评估过渡阶段的空气动力性能。为了验证Pollhamus升力理论在确定变形无人系统的四种配置（即完全压缩，完全扩展，完全扫掠以及完全扩展和扫掠）的空气动力载荷时的有效性，我们使用了3D面板和Vortex格子方法。为了提高飞行过渡阶段的结构稳定性，进行有限元分析，以估计在负载和特定边界条件下无人机系统机翼上的压力。然后利用有限元模拟中的信息来确定结构稳定所需的支撑杆的数量以及支撑杆的理想位置。还通过模态和瞬态分析来分析机翼的振动质量。根据模态分析的结果，由于机翼的固有频率低，由于空气动力和干扰，很有可能发生颤振和振动响应。瞬态分析表明，由于激励力，通过机翼传播的应力波趋向于围绕支撑杆的圆周分布。