This paper aims to design a morphing wing with both Flexible Leading Edge (FLE) and Flexible Trailing Edge (FTE) by using cellular structures, which can help the wing boost the deformation to a greater extent on the premise that the weight is not changed, so as to play a greater role in aerodynamic control such as gust interference. First, as for structural design, based on NACA0012, a morphing wing model constructed by 3 forms of cell structures is proposed. Then, the aerodynamic characteristics under the interference of FLE and FTE are calculated by the Computational Fluid Dynamic (CFD) method. After the surrogate model is established to predict the lift coefficient of the wing effectively, the sensitivity analysis reveals that the main sensitivity index of FTE deflection angle β is 0.565, which has the greatest influence on the lift coefficient. And the total sensitivity index of FLE deflection angle γ is increased by 78.9%, which reveals a strong coupling relationship between FLE and FTE. Finally, using Finite Element Analysis (FEA) method and experiment, the deformation capability of the model under certain static loads are obtained. The results reveal that the maximum deflection angle of the morphing wing model can be ±22° at FLE and ±64° at FTE, indicating strong structural stiffness and resistance to bending breakage of the model. The presented results can be useful in the design of the cellular morphing wing with multiple flexible systems.

As one of the most promising types of Unmanned Aerial Vehicles (UAVs) powered by new energy sources, hydrogen-powered UAVs are closely linked to the concept of green aviation and low-altitude economic scenarios. To provide a reference for the design of hydrogen powered UAVs, this paper summarizes the key areas and technical issues involved in the development of hydrogen powered UAVs, and reviews relevant research. The review first outlines the development history, technical advantages, application scenarios, and common examples of hydrogen powered UAVs. Subsequently, it categorizes and discusses the key issues related to hydrogen powered UAVs in four major technical areas: overall design technology, structural design technology, power system design technology, and flight control technology. Moreover, the technical frontiers faced in each area and the current research conducted by researchers both domestically and internationally are analyzed. Finally, combining the relevant technological advancements, the paper proposes suggestions and outlooks for the development of hydrogen powered UAVs. The research indicates that the development potential of hydrogen powered UAVs has not been fully explored, and joint efforts across multiple disciplines and fields to leverage hydrogen's crucial role in extending UAV endurance are required so as to reduce onboard weight, and promote green aviation development.

The arresting process of carrier-based aircraft is widely recognized as a challenging task, characterized by the highest accident rate among all carrier-based aircraft operations. Dynamic simulation plays a crucial role in assessing the intricate responses of the arresting process, favoring the design of carrier-based aircraft. An efficient and accurate rigid-flexible coupling model for analyzing the dynamic response of the arresting process is proposed. By combining the dynamic characteristics of airframe, landing gear, arresting hook and arresting gear system, the rigid-flexible coupling dynamic model is established to reflect the relative motion of the coupling parts and arresting load. The dynamic model is verified through simulations of landing gear landing drops and by comparing the arresting simulation results with corresponding data in the US military standard. Additionally, simulations of the arresting process under different off-center distance and aircraft yaw angle are conducted to obtain the dynamic response of the aircraft during the arresting process. The result indicates that the rigid-flexible coupling dynamic model proposed is effective for analyzing the arresting dynamics response of carrier-based aircraft. The axial force of the arresting cable on both sides of the hook engagement point, pitch and yaw angle of aircraft are inconsistent under yaw and off-center arresting. The analysis method and obtained results provide valuable references for assessing the dynamic responses of carrier-based aircraft during arresting process and offer valuable in-sights in the design of carrier-based aircraft.